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Патент США №	9939526
Автор(ы)	Jinkins и др.
Дата выдачи	10 апреля 2018 г.

Display system and method using weather radar sensing

РЕФЕРАТ

An enhanced vision method uses or an enhanced vision system includes an onboard weather radar system configured to improve angular resolution and/or resolution in range. The onboard weather radar system generates image data representative of the external scene topography of a runway environment associated with radar returns received by the onboard weather radar system. The radar returns are in an X-band or a C-band. The enhanced vision system also includes a display in communication with the onboard weather radar system and is configured to display an image associated with the image data that is generated by the onboard weather radar system. The enhanced vision system can also be used as an enhanced flight vision system.

Авторы:

Richard D. Jinkins (Rewey, WI), Richard M. Rademaker (Rijswijk, NL), Daniel L. Woodell (Cedar Rapids, IA), Sergey B. Shishlov (Melbourne, IA)

Патентообладатель:

Имя	Город	Штат	Страна	Тип
Richard D. Jinkins Richard M. Rademaker Daniel L. Woodell Sergey B. Shishlov	Rewey Rijswijk Cedar Rapids Melbourne	WI N/A IA IA	US NL US US

Заявитель:

Rockwell Collins, Inc. (Cedar Rapids, IA)

ID семейства патентов

55919514

Номер заявки:

14/536,330

Дата регистрации:

07 ноября 2014 г.

Prior Publication Data


	Document Identifier	Publication Date
	US 20160131739 A1	May 12, 2016

Класс патентной классификации США:	1/1
Класс совместной патентной классификации:	G01S 13/953 (20130101); G01S 7/12 (20130101); Y02A 90/18 (20180101)
Класс международной патентной классификации (МПК):	G01S 13/95 (20060101); G01S 7/12 (20060101)
Область поиска:	;342/26B

Использованные источники

[Referenced By]

Патентные документы США


2416155	February 1947	Chubb
2849184	August 1958	Arden et al.
2929059	March 1960	Parker
2930035	March 1960	Altekruse
2948892	August 1960	White
2965894	December 1960	Sweeney
2994966	August 1961	Senitsky et al.
3031660	April 1962	Young
3049702	August 1962	Schreitmueller
3064252	November 1962	Varela
3070795	December 1962	Chambers
3071766	January 1963	Fenn
3072903	January 1963	Meyer
3089801	May 1963	Tierney et al.
3107351	October 1963	Milam
3113310	December 1963	Standing
3129425	April 1964	Sanner
3153234	October 1964	Begeman et al.
3175215	March 1965	Blasberg et al.
3212088	October 1965	Alexander et al.
3221328	November 1965	Walter
3241141	March 1966	Wall
3274593	September 1966	Varela et al.
3325807	June 1967	Burns et al.
3334344	August 1967	Colby, Jr.
3339199	August 1967	Pichafroy
3373423	March 1968	Levy
3397397	August 1968	Barney
3448450	June 1969	Alfandari et al.
3618090	November 1971	Garrison
3680094	July 1972	Bayle et al.
3716855	February 1973	Asam
3739380	June 1973	Burdic et al.
3781878	December 1973	Kirkpatrick
3810175	May 1974	Bell
3815132	June 1974	Case et al.
3816718	June 1974	Hall et al.
3851758	December 1974	Makhijani et al.
3866222	February 1975	Young
3885237	May 1975	Kirkpatrick
3956749	May 1976	Magorian
4024537	May 1977	Hart
4058701	November 1977	Gruber et al.
4058710	November 1977	Altmann
4063218	December 1977	Basov et al.
4235951	November 1980	Swarovski
4277845	July 1981	Smith et al.
4405986	September 1983	Gray
4435707	March 1984	Clark
4481519	November 1984	Margerum
4532515	July 1985	Cantrell et al.
4594676	June 1986	Breiholz et al.
4595925	June 1986	Hansen
4598292	July 1986	Devino
4628318	December 1986	Alitz
4646244	February 1987	Bateman et al.
4649388	March 1987	Atlas
4654665	March 1987	Kiuchi et al.
4685149	August 1987	Smith et al.
4760396	July 1988	Barney et al.
4828382	May 1989	Vermilion
4843398	June 1989	Houston et al.
4912477	March 1990	Lory et al.
4914436	April 1990	Bateman et al.
4924401	May 1990	Bice et al.
4939513	July 1990	Paterson et al.
4951059	August 1990	Taylor, Jr.
4953972	September 1990	Zuk
4965573	October 1990	Gallagher et al.
4987419	January 1991	Salkeld
5045855	September 1991	Moreira
5047779	September 1991	Hager
5047781	September 1991	Bleakney
5049886	September 1991	Seitz et al.
5166688	November 1992	Moreira
5173703	December 1992	Mangiapane et al.
5175554	December 1992	Mangiapane et al.
5198819	March 1993	Susnjara
5202690	April 1993	Frederick
5247303	September 1993	Cornelius et al.
5273553	December 1993	Hoshi et al.
5311183	May 1994	Mathews et al.
5329391	July 1994	Miyamoto et al.
5332998	July 1994	Avignon et al.
5345241	September 1994	Huddle
5365356	November 1994	McFadden
5383457	January 1995	Cohen
5442364	August 1995	Lee et al.
5539409	July 1996	Mathews et al.
5559515	September 1996	Alimena et al.
5559518	September 1996	Didomizio
5566840	October 1996	Waldner et al.
5592178	January 1997	Chang et al.
5678303	October 1997	Wichmann
5736957	April 1998	Raney
5820080	October 1998	Eschenbach
5828332	October 1998	Frederick
5831570	November 1998	Ammar
5839080	November 1998	Muller et al.
5867119	February 1999	Corrubia et al.
5894286	April 1999	Morand et al.
5918517	July 1999	Malapert et al.
5920276	July 1999	Frederick
5923279	July 1999	Bamler et al.
5936575	August 1999	Azzarelli et al.
5942062	August 1999	Hassall et al.
5945926	August 1999	Ammar et al.
5950512	September 1999	Fields
5959762	September 1999	Bandettini et al.
5978715	November 1999	Briffe et al.
6002347	December 1999	Daly et al.
6023240	February 2000	Sutton
6061016	May 2000	Lupinski et al.
6061022	May 2000	Menegozzi et al.
6064942	May 2000	Johnson et al.
6075484	June 2000	Daniel et al.
6092009	July 2000	Glover
6112141	August 2000	Briffe et al.
6112570	September 2000	Hruschak
6122570	September 2000	Muller et al.
6127944	October 2000	Daly et al.
6128066	October 2000	Yokozeki
6128553	October 2000	Gordon et al.
6138060	October 2000	Conner et al.
6150901	November 2000	Auken
6154151	November 2000	McElreath et al.
6154169	November 2000	Kuntman
6157339	December 2000	Sato et al.
6157891	December 2000	Lin
6163021	December 2000	Mickelson
6166661	December 2000	Anderson et al.
6169770	January 2001	Henely
6178391	January 2001	Anderson et al.
6184816	February 2001	Zheng et al.
6188330	February 2001	Glover
6194980	February 2001	Thon
6199008	March 2001	Aratow et al.
6201494	March 2001	Kronfeld
6204806	March 2001	Hoech
6205400	March 2001	Lin
6208284	March 2001	Woodell et al.
6219592	April 2001	Muller et al.
6233522	May 2001	Morici
6236351	May 2001	Conner et al.
6259400	July 2001	Higgins et al.
6266114	July 2001	Skarohlid
6278799	August 2001	Hoffman
6281832	August 2001	McElreath
6285298	September 2001	Gordon
6285337	September 2001	West et al.
6285926	September 2001	Weiler et al.
6289277	September 2001	Feyereisen et al.
6311108	October 2001	Ammar et al.
6317468	November 2001	Meyer
6317690	November 2001	Gia
6317872	November 2001	Gee et al.
6340946	January 2002	Wolfson et al.
6345127	February 2002	Mitchell
6359585	March 2002	Bechman et al.
6366013	April 2002	Leenders et al.
6373418	April 2002	Abbey
6374286	April 2002	Gee et al.
6377202	April 2002	Kropfli et al.
6377892	April 2002	Johnson et al.
6388607	May 2002	Woodell
6388608	May 2002	Woodell et al.
6388724	May 2002	Campbell et al.
6389354	May 2002	Hicks et al.
6401038	June 2002	Gia
6411890	June 2002	Zimmerman
6421000	July 2002	McDowell
6421603	July 2002	Pratt et al.
6424288	July 2002	Woodell
6426717	July 2002	Maloratsky
6426720	July 2002	Ross et al.
6427122	July 2002	Lin
6441773	August 2002	Kelly et al.
6445310	September 2002	Bateman et al.
6448922	September 2002	Kelly
6452511	September 2002	Kelly et al.
6456236	September 2002	Hauck et al.
6456238	September 2002	Posey
6462703	October 2002	Hedrick
6473026	October 2002	Ali-Mehenni et al.
6473037	October 2002	Vail et al.
6473240	October 2002	Dehmlow
6481482	November 2002	Shimotomai
6492934	December 2002	Hwang et al.
6501424	December 2002	Haendel et al.
6512476	January 2003	Woodell
6512527	January 2003	Barber et al.
6516272	February 2003	Lin
6516283	February 2003	McCall et al.
6520056	February 2003	Nemeth et al.
6525674	February 2003	Kelly et al.
6531669	March 2003	Miller et al.
6549161	April 2003	Woodell
6567728	May 2003	Kelly et al.
6574030	June 2003	Mosier
6577947	June 2003	Kronfeld et al.
6590528	July 2003	Dewulf
6591171	July 2003	Ammar et al.
6593875	July 2003	Bergin et al.
6600443	July 2003	Landt
6603425	August 2003	Woodell
6614057	September 2003	Silvernail et al.
6650275	November 2003	Kelly et al.
6650291	November 2003	West et al.
6653947	November 2003	Dwyer et al.
6667710	December 2003	Cornell et al.
6681668	January 2004	Smirle
6690298	February 2004	Barber et al.
6690299	February 2004	Suiter
6690317	February 2004	Szeto et al.
6697008	February 2004	Sternowski
6697012	February 2004	Lodwig et al.
6710663	March 2004	Berquist
6714186	March 2004	Mosier et al.
6724344	April 2004	Stockmaster et al.
6731236	May 2004	Hager et al.
6738011	May 2004	Evans
6739929	May 2004	Furukawa et al.
6741203	May 2004	Woodell
6741208	May 2004	West
6744382	June 2004	Lapis et al.
6744408	June 2004	Stockmaster
6757624	June 2004	Hwang et al.
6760155	July 2004	Murayama et al.
6771626	August 2004	Golubiewski et al.
6782392	August 2004	Weinberger et al.
6799095	September 2004	Owen et al.
6803245	October 2004	Auch et al.
6804614	October 2004	McGraw et al.
6806846	October 2004	West
6807538	October 2004	Weinberger et al.
6813777	November 2004	Weinberger et al.
6819983	November 2004	McGraw
6822617	November 2004	Mather et al.
6825804	November 2004	Doty
6832538	December 2004	Hwang
6839017	January 2005	Dillman
6842288	January 2005	Liu et al.
6850185	February 2005	Woodell
6862323	March 2005	Loper
6862501	March 2005	He
6865452	March 2005	Burdon
6879280	April 2005	Bull et al.
6879886	April 2005	Wilkins et al.
6882302	April 2005	Woodell et al.
6908202	June 2005	Graf et al.
6917396	July 2005	Hiraishi et al.
6918134	July 2005	Sherlock et al.
6933885	August 2005	Stockmaster et al.
6938258	August 2005	Weinberger et al.
6950062	September 2005	Mather et al.
6959057	October 2005	Tuohino
6972727	December 2005	West et al.
6977608	December 2005	Anderson et al.
6984545	January 2006	Grigg et al.
6990022	January 2006	Morikawa et al.
6992614	January 2006	Joyce
6995726	February 2006	West et al.
6998648	February 2006	Silvernail
6998908	February 2006	Sternowski
6999022	February 2006	Vesel et al.
6999027	February 2006	Stockmaster
7002546	February 2006	Stuppi et al.
7010398	March 2006	Wilkins et al.
7023375	April 2006	Klausing et al.
7026956	April 2006	Wenger et al.
7028304	April 2006	Weinberger et al.
7030945	April 2006	Umemoto et al.
7034753	April 2006	Elsallal et al.
7042387	May 2006	Ridenour et al.
7053796	May 2006	Barber
7057549	June 2006	Block
7064680	June 2006	Reynolds et al.
7069120	June 2006	Koenck et al.
7089092	August 2006	Wood et al.
7092645	August 2006	Sternowski
7098913	August 2006	Etherington et al.
7109912	September 2006	Paramore et al.
7109913	September 2006	Paramore et al.
7123260	October 2006	Brust
7129885	October 2006	Woodell et al.
7145501	December 2006	Manfred et al.
7148816	December 2006	Carrico
7151507	December 2006	Herting
7158072	January 2007	Venkatachalam et al.
7161525	January 2007	Finley et al.
7170446	January 2007	West et al.
7170959	January 2007	Abbey
7180476	February 2007	Guell et al.
7191406	March 2007	Barber et al.
7196329	March 2007	Wood et al.
7205933	April 2007	Snodgrass
7209070	April 2007	Gilliland et al.
7212216	May 2007	He et al.
7218268	May 2007	Vandenberg
7219011	May 2007	Barber
7242343	July 2007	Woodell
7242345	July 2007	Raestad et al.
7250903	July 2007	McDowell
7265710	September 2007	Deagro
7269657	September 2007	Alexander et al.
7272472	September 2007	McElreath
7273403	September 2007	Yokota et al.
7280068	October 2007	Lee et al.
7289058	October 2007	Shima
7292178	November 2007	Woodell et al.
7292180	November 2007	Schober
7295150	November 2007	Burlet et al.
7295901	November 2007	Little et al.
7301496	November 2007	Honda et al.
7307576	December 2007	Koenigs
7307577	December 2007	Kronfeld et al.
7307583	December 2007	Woodell et al.
7312725	December 2007	Berson et al.
7312743	December 2007	Ridenour et al.
7317427	January 2008	Pauplis et al.
7321332	January 2008	Focke et al.
7337043	February 2008	Bull
7349154	March 2008	Aiura et al.
7352292	April 2008	Alter et al.
7361240	April 2008	Kim
7372394	May 2008	Woodell et al.
7373223	May 2008	Murphy
7375678	May 2008	Feyereisen et al.
7379014	May 2008	Woodell et al.
7379796	May 2008	Walsdorf et al.
7381110	June 2008	Sampica et al.
7417578	August 2008	Woodell et al.
7417579	August 2008	Woodell
7423578	September 2008	Tietjen
7446697	November 2008	Burlet et al.
7446938	November 2008	Miyatake et al.
7452258	November 2008	Marzen et al.
7474262	January 2009	Alland
7479920	January 2009	Niv
7486220	February 2009	Kronfeld et al.
7486291	February 2009	Berson et al.
7492304	February 2009	Woodell et al.
7492305	February 2009	Woodell et al.
7515087	April 2009	Woodell et al.
7515088	April 2009	Woodell et al.
7525448	April 2009	Wilson et al.
7528765	May 2009	Woodell et al.
7528915	May 2009	Choi et al.
7541970	June 2009	Godfrey et al.
7541971	June 2009	Woodell et al.
7551451	June 2009	Kim et al.
7557735	July 2009	Woodell et al.
7566254	July 2009	Sampica et al.
7570177	August 2009	Reynolds et al.
7576680	August 2009	Woodell
7603209	October 2009	Dwyer et al.
7609200	October 2009	Woodell et al.
7612706	November 2009	Honda et al.
7616150	November 2009	Woodell
7633428	December 2009	McCusker et al.
7633430	December 2009	Wichgers et al.
7633584	December 2009	Umemoto et al.
7639175	December 2009	Woodell
7664601	February 2010	Daly, Jr.
7675461	March 2010	McCusker et al.
7693621	April 2010	Chamas
7696921	April 2010	Finley et al.
7714767	May 2010	Kronfeld et al.
7733264	June 2010	Woodell et al.
7783427	August 2010	Woodell et al.
7783429	August 2010	Walden et al.
7791529	September 2010	Filias et al.
7808422	October 2010	Woodell et al.
7814676	October 2010	Sampica et al.
7843380	November 2010	Woodell
7859448	December 2010	Woodell et al.
7859449	December 2010	Woodell et al.
7864103	January 2011	Weber et al.
7868811	January 2011	Woodell et al.
7872594	January 2011	Vesel
7889117	February 2011	Woodell et al.
7889118	February 2011	Finley et al.
7927440	April 2011	Matsuhira
7929086	April 2011	Toyama et al.
7965223	June 2011	McCusker
7965225	June 2011	Dickerson et al.
8035547	October 2011	Flanigan et al.
8038498	October 2011	Miyauchi et al.
8045098	October 2011	Kitagawa et al.
8059025	November 2011	D'Addio
8068984	November 2011	Smith et al.
8072368	December 2011	Woodell
8077078	December 2011	Woodell et al.
8102487	January 2012	Kitagawa et al.
8118075	February 2012	Sampica et al.
8137498	March 2012	Sampica et al.
8140223	March 2012	Whitehead et al.
8159464	April 2012	Gribble et al.
8232917	July 2012	Scherzinger et al.
8296065	October 2012	Haynie et al.
8373580	February 2013	Bunch et al.
8410975	April 2013	Bell et al.
8477062	July 2013	Kanellis
8486535	July 2013	Nemeth et al.
8493241	July 2013	He
8515600	August 2013	McCusker
8540002	September 2013	Sampica et al.
8558731	October 2013	Woodell
8576112	November 2013	Garrec et al.
8583315	November 2013	Whitehead et al.
8594879	November 2013	Roberge et al.
8603288	December 2013	Sampica et al.
8634993	January 2014	McClure et al.
8639416	January 2014	Jones et al.
8643533	February 2014	Woodell et al.
8691043	April 2014	Sampica et al.
8717226	May 2014	Bon et al.
8773301	July 2014	Woodell
8896480	November 2014	Wilson et al.
8909471	December 2014	Jinkins et al.
8917191	December 2014	Tiana et al.
8936057	January 2015	Sampica et al.
9354633	May 2016	McCusker et al.
2001/0023390	September 2001	Gia
2001/0050372	December 2001	Krijn et al.
2001/0053648	December 2001	Furukawa et al.
2002/0039070	April 2002	Ververs et al.
2002/0111717	August 2002	Scherzinger et al.
2002/0116125	August 2002	Lin
2002/0116126	August 2002	Lin
2002/0158256	October 2002	Yamada et al.
2002/0179229	December 2002	Chuzles
2002/0185600	December 2002	Kerr
2002/0187284	December 2002	Kinoshita et al.
2003/0021491	January 2003	Brust
2003/0038916	February 2003	Nakano et al.
2003/0043315	March 2003	Umemoto et al.
2003/0071828	April 2003	Wilkins et al.
2003/0089214	May 2003	Fukuta et al.
2003/0093187	May 2003	Walker
2003/0102999	June 2003	Bergin et al.
2003/0156238	August 2003	Hiraishi et al.
2003/0160718	August 2003	Nagasaku
2003/0174396	September 2003	Murayama et al.
2003/0180528	September 2003	Flosenzier et al.
2003/0189606	October 2003	Moon et al.
2003/0195672	October 2003	He
2003/0216859	November 2003	Martell et al.
2003/0222887	December 2003	Wilkins et al.
2004/0044445	March 2004	Burdon
2004/0059473	March 2004	He
2004/0066645	April 2004	Graf et al.
2004/0072575	April 2004	Young et al.
2004/0083038	April 2004	He
2004/0145499	July 2004	Schmidt et al.
2004/0160341	August 2004	Feyereisen et al.
2004/0160364	August 2004	Regev
2004/0181318	September 2004	Redmond et al.
2004/0264549	December 2004	Hoole
2005/0004748	January 2005	Pinto et al.
2005/0052451	March 2005	Servantie
2005/0126679	June 2005	Kim
2005/0136625	June 2005	Henseler et al.
2005/0150289	July 2005	Osborne
2005/0174350	August 2005	Ridenour et al.
2005/0200502	September 2005	Reusser et al.
2005/0225481	October 2005	Bonthron
2005/0230563	October 2005	Corcoran, III
2006/0004497	January 2006	Bull
2006/0097895	May 2006	Reynolds et al.
2006/0098452	May 2006	Choi et al.
2006/0164284	July 2006	Pauplis et al.
2006/0207967	September 2006	Bocko et al.
2006/0215265	September 2006	Miyatake et al.
2006/0227012	October 2006	He
2006/0244636	November 2006	Rye et al.
2006/0245171	November 2006	Kim et al.
2006/0290253	December 2006	Yeo et al.
2006/0290531	December 2006	Reynolds et al.
2007/0001897	January 2007	Alland
2007/0002078	January 2007	He et al.
2007/0008214	January 2007	Wasiewicz
2007/0013575	January 2007	Lee et al.
2007/0018887	January 2007	Feyereisen et al.
2007/0032951	February 2007	Tanenhaus et al.
2007/0060063	March 2007	Wright et al.
2007/0146364	June 2007	Aspen
2007/0171094	July 2007	Alter et al.
2007/0176794	August 2007	Feyereisen et al.
2007/0179684	August 2007	He
2007/0228586	October 2007	Merrill et al.
2007/0247350	October 2007	Ryan
2007/0279253	December 2007	Priest
2007/0297736	December 2007	Sherman et al.
2008/0018524	January 2008	Christianson
2008/0051947	February 2008	Kemp
2008/0074308	March 2008	Becker et al.
2008/0111731	May 2008	Hubbard et al.
2008/0145610	June 2008	Muller et al.
2008/0180351	July 2008	He
2008/0305721	December 2008	Ohashi et al.
2009/0021397	January 2009	Wipf et al.
2009/0040070	February 2009	Alter et al.
2009/0040772	February 2009	Laney
2009/0046229	February 2009	Umemoto et al.
2009/0148682	June 2009	Higuchi
2009/0152391	June 2009	McWhirk
2009/0153783	June 2009	Umemoto
2009/0164067	June 2009	Whitehead et al.
2009/0207048	August 2009	He et al.
2009/0279030	November 2009	Toyama et al.
2009/0279175	November 2009	Laney et al.
2010/0033499	February 2010	Gannon et al.
2010/0103353	April 2010	Yamada
2010/0297406	November 2010	Schaffer et al.
2010/0312428	December 2010	Roberge et al.
2010/0312461	December 2010	Haynie et al.
2011/0037616	February 2011	Leutelt et al.
2011/0054729	March 2011	Whitehead et al.
2011/0075070	March 2011	Kitagawa et al.
2011/0141405	June 2011	Kitagawa et al.
2011/0165361	July 2011	Sherman et al.
2011/0184594	July 2011	Manfred et al.
2011/0273325	November 2011	Goldman
2011/0282580	November 2011	Mohan
2011/0304479	December 2011	Chen et al.
2012/0053831	March 2012	Halder
2012/0150426	June 2012	Conway
2012/0174445	July 2012	Jones et al.
2012/0215410	August 2012	McClure et al.
2013/0041529	February 2013	He et al.
2013/0234884	September 2013	Bunch
2014/0009324	January 2014	Ranney
2015/0211883	July 2015	He
2016/0131739	May 2016	Jinkins et al.

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2006-218658	Aug 2006	JP
2006-334912	Dec 2006	JP
2006-348208	Dec 2006	JP
2007-206559	Aug 2007	JP
2007-302398	Nov 2007	JP
2008-238607	Jan 2008	JP
WO-93/05634	Mar 1993	WO
WO-2009/133102	Nov 2009	WO
WO-2011/089474	Jul 2011	WO

Другие источники

US. Appl. No. 11/851,323, filed Sep. 6, 2007, McCusker. cited by applicant .
U.S. Appl. No. 11/863,219, filed Sep. 27, 2007, Woodell. cited by applicant .
U.S. Appl. No. 11/863,221, filed Sep. 27, 2007, Woodell. cited by applicant .
U.S. Appl. No. 11/899,801, filed Sep. 6, 2007, Woodell et al. cited by applicant .
U.S. Appl. No. 11/900,002, filed Sep. 6, 2007, Woodell et al. cited by applicant .
U.S. Appl. No. 12/167,200, filed Jul. 2, 2008, Woodell et al. cited by applicant .
U.S. Appl. No. 12/167,203, filed Jul. 2, 2008, Woodell. cited by applicant .
U.S. Appl. No. 12/167,208, filed Jul. 2, 2008, Dickerson et al. cited by applicant .
U.S. Appl. No. 12/180,293, filed Jul. 25, 2008, Woodell et al. cited by applicant .
U.S. Appl. No. 12/786,169, filed May 24, 2010, Nemeth et al. cited by applicant .
U.S. Appl. No. 13/224,992, filed Sep. 2, 2011, Hufnagel et al. cited by applicant .
U.S. Appl. No. 13/250,307, filed Mar. 30, 2011, Jinkins. cited by applicant .
U.S. Appl. No. 13/250,798, filed Sep. 30, 2011, Jinkins. cited by applicant .
"MountainScope.TM. on a TabletPC," PCAvionics.TM., printed from website www.pcavionics.com on Aug. 28, 2007, 1 page. cited by applicant .
TAWS Class A and Class B, Terrain Awareness and Warning Systems, Universal.RTM. Avionics Systems Corporation, Sep. 2007, 6 pages. cited by applicant .
"TAWS Terrain Awareness and Warning System," Universal.RTM. Avionics, printed from website www.uasc.com on Aug. 28, 2007, 2 pages. cited by applicant .
Adams, Charlotte, "Synthetic Vision: Picturing the Future," Avionics magazine, Oct. 1, 2006, printed from website www.aviationtoday.com, 4 pages. cited by applicant .
Adams, Charlotte, "Synthetic Vision: Picturing the Future," Avionics magazine, Solutions for Global Airspace Electronics, Oct. 2006, cover and pp. 22-29. cited by applicant .
Advisory Action for U.S. Appl. No. 12/009,472, dated Feb. 25, 2013, 3 pages. cited by applicant .
Advisory Action for U.S. Appl. No. 13/538,957, dated Jun. 14, 2013, 6 pages. cited by applicant .
Blue Mountain Avionics' Products, printed from website www.bluemountainavionics.com on Aug. 28, 2007, 4 pages. cited by applicant .
Carter, S. P., D. D. Blankenship, M. E. Peters, D. A. Young, J. W. Holt, and D. L. Morse (2007), Radar-based subglacial lake classification in Antarctica, Geochem. Geophys. Geosyst., 8, 003016, doi:10.1029/2006GC001408, 20 pages. cited by applicant .
Final Office Action on U.S. Appl. No. 13/250,798 dated Sep. 4, 2014, 22 pages. cited by applicant .
Final Office Action on U.S. Appl. No. 13/867,556 dated Jul. 3, 2014, 11 pages. cited by applicant .
Final Office Action on U.S. Appl. No. 13/250,307 dated Jun. 11, 2014, 8 pages. cited by applicant .
Final Office Action on U.S. Appl. No. 13/250,798 dated Aug. 7, 2015, 21 pages. cited by applicant .
G2000, Garmin, printed from website https://buy.garmin.com/shop/shop.do?cID=153&pID=97668 on Jun. 28, 2011, 2 pages. cited by applicant .
G3000, Garmin, printed from website https://buy.garmin.com/shop/shop.do?cID=153&pID=66916 on Jun. 28, 2011, 2 pages. cited by applicant .
G5000, Garmin, printed from website https://buy.garmin.com/shop/shop.do?cID=153&pID=90821&ra=true on Apr. 20, 2011, 2 pages. cited by applicant .
Non-Final Office Action on U.S. Appl. No. 13/250,798 dated Mar. 18, 2015, 21 pages. cited by applicant .
Non-Final Office Action on U.S. Appl. No. 14/301,199 dated Sep. 9, 2015, 18 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/009,372, dated Oct. 13, 2011, 8 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/009,373, dated Jun. 16, 2010, 4 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/009,472, dated Sep. 5, 2013, 8 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/786,169, dated Mar. 28, 2013, 6 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 13/538,957, dated Oct. 3, 2013, 13 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,372, dated Dec. 20, 2010, 10 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,372, dated Jun. 13, 2011, 9 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,373, dated Dec. 30, 2009, 14 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,472, dated Apr. 16, 2012, 16 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,472, dated Jan. 14, 2011, 14 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,472, dated Mar. 20, 2013, 15 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,472, dated Nov. 3, 2011, 15 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/009,472, dated Nov. 9, 2012, 15 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/263,282, dated Jan. 5, 2012, 10 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/786,169, dated Jan. 18, 2013, 14 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/892,563, dated Feb. 19, 2013, 12 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/224,992, dated Feb. 28, 2013, 10 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/250,307, dated Nov. 5, 2013, 11 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/538,957, dated Apr. 4, 2013, 19 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/538,957, dated Oct. 5, 2012, 18 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/743,182, dated Apr. 8, 2013, 10 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/786,169, dated Jul. 20, 2012, 8 pages. cited by applicant .
Office Action in Japanese Patent Application 2015-116688, dated Aug. 25, 2015, 4 pages. cited by applicant .
Office Action in Japanese Patent Application 2015-116716, dated Aug. 25, 2015, 3 pages. cited by applicant .
Office Action on U.S. Appl. No. 12/236,464, dated Feb. 11, 2014, 21 pages. cited by applicant .
Office Action on U.S. Appl. No. 12/236,464, dated Jun. 22, 2011, 14 pages. cited by applicant .
Office Action on U.S. Appl. No. 13/250,798 dated Apr. 23, 2014, 15 pages. cited by applicant .
Office Action on U.S. Appl. No. 13/867,556 dated Feb. 7, 2014, 11 pages. cited by applicant .
Office Action U.S. Appl. No. 11/787,460, dated Aug. 31, 2010, 18 pages. cited by applicant .
Office Action with English Translation received in Korean Patent Application 10-2010-7017278, dated Aug. 26, 2015, 5 pages. cited by applicant .
Pictures of DELPHINS, printed from website www.tunnel-in-the-sky.tudelft.nl on Aug. 28, 2007, 4 pages. cited by applicant .
Restriction Requirement for U.S. Appl. No. 13/867,556, dated Dec. 26, 2013, 6 pages. cited by applicant .
Van Kasteren, Joost, "Tunnel-in-the-Sky, Synthetic vision simplifies the pilot's job and enhances safety," printed from website www.delftoutlook.tudelft.nl on Aug. 28, 2007, 13 pages. cited by applicant .
Walker, GD-Itronix Dynavue Technology, The Ultimate Outdoor-Readable Touch-Screen Display, Rugged PC Review, 4 pages. cited by applicant .
U.S. Appl. No. 12/236,464, filed Sep. 23, 2008, Rockwell Collins. cited by applicant .
U.S. Appl. No. 13/627,788, filed Sep. 26, 2012, Rockwell Collins. cited by applicant .
U.S. Appl. No. 13/857,955, filed Apr. 5, 2013 Barber et al. cited by applicant .
U.S. Appl. No. 13/250,798, filed Sep. 30, 2011, Rockwell Collins. cited by applicant .
U.S. Appl. No. 14/301,199, filed Jun. 10, 2014, Rockwell Collins. cited by applicant .
U.S. Appl. No. 14/482,681, filed Sep. 10, 2014, Rockwell Collins. cited by applicant .
Airports Authority of India, Chapter 7: Visual AIDS for Navigation--Lights, available prior to Jan. 1, 2005, retrieved from the internet at: http://www.aai.aero/aai_employees/chapter_7.pdf on Sep. 26, 2014, 33 pages. cited by applicant .
Brailovsky et al., REVS122: A Radar-Based Enhanced Vision System for Degraded Visual Environments, Proc. of SPIE vol. 9087 908708-1, retrieved from the internet at http://proceedings.spiedigitallibrary.org on Jun. 25, 2014, 13 pages. cited by applicant .
Federal Aviation Administration, Advisory Circular AC 90-106, "Enhanced Flight Vision Systems", initiated by AFS-400, dated Jun. 2, 2010, 55 pages. cited by applicant .
Federal Aviation Administration, Aeronautical Information Manual (AIM) Basic Flight Information and ATC Procedures, dated Jul. 24, 2014, 2 pages. cited by applicant .
Fountain, J.R., Digital Terrain Systems, Airborne Navigation Systems Workshop (Digest No. 1997/169), IEE Colloquium, pp. 4/1-4/6, Feb. 21, 1997. cited by applicant .
Honeywell, RDR-4B Forward looking windshear detection / weather radar system user's manual with radar operating guidelines, Rev. 6, Jul. 2003, 106 pages. cited by applicant .
Johnson, A., et al., Vision Guided Landing of an Autonomous Helicopter in Hazardous Terrain, Robotics and Automation, 2005. ICRA 2005. Proceedings of the 2005 IEEE International Conference, pp. 3966-3971, Apr. 18-22, 2005. cited by applicant .
Kuntman, D., Airborne system to address leading cause of injuries in non-fatal airline accidents, ICAO Journal, Mar. 2000, 4 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 11/863,221, dated Aug. 2, 2010, 9 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 11/899,801, dated Aug. 19, 2010, 5 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 11/900,002, dated Sep. 14, 2010, 5 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/167,200, dated Oct. 28, 2010, 5 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/167,203, dated Jun. 21, 2013, 7 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/167,208, dated Mar. 21, 2011, 8 pages. cited by applicant .
Notice of Allowance for U.S. Appl. No. 12/180,293, dated Aug. 4, 2011, 8 pages. cited by applicant .
Notice of Allowance on U.S. Appl. No. 13/241,051 dated Aug. 28, 2014, 9 pages. cited by applicant .
Notice of Allowance on U.S. Appl. No. 13/247,742 dated Jul. 30, 2014, 9 pages. cited by applicant .
Office Action for U.S. Appl. No. 11/851,323, dated Aug. 6, 2009, 23 pages. cited by applicant .
Office Action for U.S. Appl. No. 11/851,323, dated Dec. 15, 2010, 13 pages. cited by applicant .
Office Action for U.S. Appl. No. 11/851,323, dated Jul. 5, 2012, 23 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/167,200, dated Jul. 21, 2010, 6 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/167,203, dated Aug. 26, 2010, 11 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/167,203, dated Sep. 21, 2012, 6 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/167,208, dated Dec. 30, 2009, 10 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/167,208, dated Jun. 3, 2010, 11 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/167,208, dated Oct. 19, 2010, 8 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/180,293, dated Jan. 4, 2011, 5 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/180,293, dated Jul. 28, 2010, 8 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/976,871, dated Feb. 15, 2012, 8 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/976,871, dated Jul. 10, 2012, 4 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/976,871, dated May 6, 2013, 5 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/976,871, dated Nov. 21, 2012, 5 pages. cited by applicant .
Office Action for U.S. Appl. No. 12/976,871, dated Oct. 9, 2013, 5 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/183,314, dated Aug. 14, 2013, 11 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/183,314, dated Mar. 28, 2013, 12 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/474,559, dated Aug. 28, 2013, 10 pages. cited by applicant .
Office Action for U.S. Appl. No. 13/474,559, dated Dec. 28, 2012, 8 pages. cited by applicant .
Office Action on U.S. Appl. No. 13/241,051 dated Feb. 27, 2014, 21 pages. cited by applicant .
Office Action on U.S. Appl. No. 13/247,742 dated Dec. 3, 2013, 11 pages. cited by applicant .
REVS Product Information Sheet, Sierra Nevada Corporation, dated May 7, 2014, 2 pages. cited by applicant .
Skolnik, Introduction to Radar Systems, McGraw Hill Book Company, 2001, 3 pages. cited by applicant .
Skolnik, Radar Handbook (McGraw Hill Book Company), 1990, 23 pages. cited by applicant .
Synthetic Vision System, en.wikipedia.org/wiki/Synthetic_vision_system, retrieved Feb. 28, 2013, 4 pages. cited by applicant .
Technical Standard Order, TSO-C115b, Airborne Area Navigation Equipment Using Multi-Sensor Inputs, Department of Transportation, Federal Aviation Administration, Sep. 30, 1994, 11 pages. cited by applicant .
U.S. Office Action on U.S. Appl. No. 11/900,002 dated Jun. 8, 2010. cited by applicant .
U.S. Office Action on U.S. Appl. No. 13/247,742 dated Apr. 16, 2014, 15 pages. cited by applicant .
Vadlamani, A., et al., Improving the detection capability of spatial failure modes using downward-looking sensors in terrain database integrity monitors, Digital Avionics Systems Conference, 2003. DASC-03. The 22nd, vol. 2, pp. 9C.5-91-12 vol. 2, Oct. 12-16, 2003. cited by applicant .
Wang et al., A Simple Based on DSP Antenna Controller of Weather Radar, 2001 CIE International Conference, 4 pages. cited by applicant .
Non-Final Office Action on U.S. Appl. No. 13/250,798 dated Feb. 26, 2016, 9 pages. cited by applicant .
Notice of Allowance on U.S. Appl. No. 12/263,282 dated Jan. 29, 2016, 8 pages. cited by applicant .
Notice of Allowance on U.S. Appl. No. 14/301,199 dated Mar. 1, 2016, 11 pages. cited by applicant .
First Office Action on Korean Patent Application No. 10-2016-7013740, dated Sep. 19, 2016, 7 pages. cited by applicant .
U.S. Appl. No. 14/841,558, filed Aug. 31, 2015, Rockwell Collins, Inc. cited by applicant .
McGray et al., Air Operators, Airlines, Manufacturers and Interested Industry Stakeholders & Aero Chart Forum-Utilizing EFVS technology and incorporating it into FAA NextGen, Federal Aviation Administration, Apr. 23, 2014 & Apr. 30, 2014, 34 pages. cited by applicant .
Non-Final Office Action on U.S. Appl. No. 13/250,798, dated Sep. 9, 2016, 6 pages. cited by applicant .
Notice of Allowance on U.S. Appl. No. 13/250,798, dated Sep. 28, 2016, 10 pages. cited by applicant .
Non-Final Office Action on U.S. Appl. No. 14/482,681, dated Dec. 20, 2016, 9 pages. cited by applicant .
English Translation of Japanese Notice of Reasons for Rejection in Japanese Application No. 2016-001165, dated Apr. 25, 2017, 1 page. cited by applicant .
Non-Final Office Action on U.S. Appl. No. 14/270,587, dated May 8, 2017, 16 pages. cited by applicant .
First Office Action with English Translation of Chinese Application No. 201510005057.5, dated Apr. 25, 2017, 8 pages. cited by applicant.

Главный эксперт: Adams; Tashiana R
Assistant Examiner: Seraydaryan; Helena H
Уполномоченный, доверенный или фирма: Suchy; Donna P. Barbieri; Daniel M.

ФОРМУЛА ИЗОБРЕТЕНИЯ

What is claimed is:

1. An airborne weather radar system used for enhanced vision, comprising: an antenna; and a control circuit configured to provide radar beams via the antenna toward external surroundings and configured to receive radar returns, wherein the control circuit is configured to process the radar returns to provide image data associated with the external surroundings, wherein the weather radar system has increased range resolution and angular resolution when used for enhanced vision of external scene topography than when used for weather radar sensing functions, the control circuit configured to transmit successive pulses with discrete increasing frequency steps such that radar returns from clutter in an ambiguous range are different from radar returns from targets, the control circuit configured to reject the radar returns from clutter in the ambiguous range, the radar beams being in the X-band or the C-band, the image data being for providing a visual image of external scene topography to a pilot.

2. The system of claim 1, wherein the angular resolution is increased using a beam sharpening technique and de-convolution of a beam point spread function.

3. The system of claim 1, wherein the antenna is a switched aperture antenna, and the control circuit is further configured to process the radar returns to determine a high resolution estimate of a target angle relative to a bore site of the antenna based on switching between transmitting and receiving on a full aperture and transmitting on the full aperture while receiving on a partial aperture.

4. The system of claim 1, wherein the control circuit is configured to provide a perspective enhanced image as the visual image on a display in response to the image data.

5. The system of claim 1, wherein the radar beams are provided as separate pulses with discrete increasing frequency steps.

6. The system of claim 5, wherein the frequency steps hop over restricted or undesired frequencies.

7. A method of providing a real time sensor image, the method comprising: receiving radar returns from an X-band or C-band airborne weather radar system, the X-band or C-band airborne weather radar system including a switched aperture antenna, wherein the radar returns can be processed to have increased range resolution and angular resolution when used for providing a real time sensor image of external scene topography than when used for weather radar sensing functions; processing the radar returns to determine a high resolution estimate of a target angle relative to a bore site of the antenna based on switching between transmitting and receiving on a full aperture and transmitting on the full aperture while receiving on a partial aperture; and filtering the radar returns to identify areas having a reflectivity lower than a predetermined value to provide a visual image of the external scene topography based on the radar returns.

8. The method of claim 7, wherein the radar returns of the X-band or C-band airborne weather radar system comprise a switched aperture, sequential lobing or monopulse weather radar system.

9. The method of claim 7, further comprising displaying an aircraft situation display image on a head down display using the visual image.

10. The method of claim 7, further comprising providing radar beams associated with the radar returns, the radar beams are provided using beam sharpening techniques.

11. The method of claim 10, wherein the beam sharpening techniques comprise a sub-aperture or split aperture technique, the method further comprising using a complex conjugate method to remove Doppler-induced phase changes by cancellation to determine the target angle based on a change in phase center.

12. The method of claim 10, wherein the radar beams are provided using ultra wide band pulses, intra pulse compression, or inter pulse compression.

13. The method of claim 12, wherein the radar beams are provided using stepped frequency compression.

14. An enhanced vision system, comprising: a weather radar system configured to enhance resolution in range when used for providing an enhanced image of a runway environment than when used for weather radar sensing functions, wherein the weather radar system generates image data representative of the runway environment associated radar returns received by the weather radar system, the radar returns being in an X-band or a C-band, wherein the weather radar system is configured to transmit successive pulses with discrete increasing frequency steps such that radar returns from clutter in an ambiguous range are different from radar returns from targets, the weather radar system configured to reject the radar returns from clutter in the ambiguous range; and a display in communication with the weather radar system and configured to display an image associated with the radar returns.

15. The system of claim 14, wherein the weather radar system includes processing electronics that are configured to provide increased angular resolution using beam sharpening.

16. The system of claim 14, wherein the display is a head down display or head up display.

17. The system of claim 14, wherein the enhanced vision system is used as an enhanced flight vision system.

ОПИСАНИЕ

CROSS-REFERENCE TO RELATED PATENT APPLICATIONS

The present application is related to U.S. patent application Ser. No. 14/482,681 filed Sep. 10, 2014 by Wood et al., U.S. patent application Ser. No. 14/301,199 filed on Jun. 10, 2014 by McCusker et al, U.S. patent application Ser. No. 13/627,788 filed on Sep. 26, 2012; U.S. patent application Ser. No. 12/892,563 filed on Sep. 28, 2010, U.S. patent application Ser. No. 13/250,798 filed on Sep. 30, 2011, U.S. patent application Ser. No. 12/236,464 filed on Sep. 28, 2008, U.S. patent application Ser. No. 12/167,200 filed on Jul. 2, 2008, U.S. patent application Ser. No. 12/180,293 filed on Jul. 25, 2008, U.S. patent application Ser. No. 13/247,742 filed on Sep. 28, 2011, U.S. patent application Ser. No. 11/851,323 filed on Sep. 6, 2007, U.S. patent application Ser. No. 11/904,491 filed on Sep. 26, 2007, U.S. patent application Ser. No. 13/241,051 filed on Sep. 22, 2011, U.S. patent application Ser. No. 12/263,282 filed on Oct. 31, 2008 and U.S. patent application Ser. No. 12/180,293 filed on Jul. 25, 2008, all of which are herein incorporated by reference in their entireties and assigned to the assignee of the present application.

УРОВЕНЬ ТЕХНИКИ

An aircraft uses an enhanced vision system (EVS) to provide imagery to an aircraft crew. The imagery can include an airport terminal area and runway environment when meteorological conditions prevent a clear natural view of the external surroundings of the aircraft through the windscreen. For example, the EVS may overlay an image of an airport terminal area and runway environment over the pilot's natural unaided view of the external surroundings of the aircraft through the aircraft's cockpit windscreen. Such imagery can improve the situational awareness of the flight crew during instrument approach procedures in low visibility conditions such as fog. That same enhanced vision system can be used as an FAA-certified enhanced flight vision systems (EFVS) which can allow pilots landing under instrument flight rules to operate below certain specified altitudes during instrument approaches even when the airport environment is not visible. For example, under Title 14 of the Code of Federal Regulations, part 91, a pilot may not descend below decision altitude (DA) or minimum descent altitude (MDA) to 100 feet above the touchdown zone elevation (TDZE) from a straight-in instrument approach procedure (IAP), other than Category II or Category III, unless the pilot can see certain required visual references. Such visual references include, for example, the approach lighting system, the threshold lighting system, and the runway edge lighting system. The pilot may, however, use an EFVS to identify the required visual references in low visibility conditions where the pilot's natural unaided vision is unable to identify these visual references. Accordingly, the use of an EFVS may minimize losses due to the inability of the pilot to land the plane and deliver cargo and/or passengers on time in low visibility conditions.

EVS imagery is typically presented to the pilot flying (PF) on a head up display (HUD). The HUD is typically a transparent display device that allows the PF to view EVS imagery while looking at the external surroundings of the aircraft through the cockpit windscreen. As long as visibility conditions outside of the aircraft permit the PF to see the external surroundings of the aircraft through the cockpit windscreen, the PF can verify that the EVS is functioning properly such that the imagery on the HUD is in alignment with the PF's view of the external surroundings of the aircraft.

EVS imagery is sometimes also presented to the pilot monitoring (PM) on a head down display (HDD). For example, in some countries, the system must present the EVS imagery to the PM for confirmation that the EVS information is a reliable and accurate indicator of the required visual references. The PM may also use the EVS imagery to determine whether the PF is taking appropriate action during approach and landing procedures. The HDD is typically a non-transparent display device mounted adjacent to or within a console or instrument panel of the aircraft.

An EVS typically uses either a passive or active sensing system to acquire data used to generate imagery of the airport terminal area and runway environment. A typical passive sensor, such as a forward looking infrared (FLIR) camera or visible light spectrum camera, receives electromagnetic energy from the environment and outputs data that may be used by the system to generate video images from the point of view of the camera. The camera is installed in an appropriate position, such as in the nose of an aircraft, so that the PF may be presented with an appropriately scaled and positioned video image on the HUD having nearly the same point of view as the PF when viewing the external surroundings of the aircraft through the HUD. However, while passive sensors provide higher quality video imagery, they may be unable to identify required visual references in certain low visibility conditions such as heavy fog.

Active sensing systems, such as millimeter wavelength (MMW) radar systems (e.g., 94 GHz), transmit electromagnetic energy into the environment and then receive return electromagnetic energy reflected from the environment. The active sensing system is typically installed in an appropriate position, such as in the nose of an aircraft. Active sensing systems are expensive and require space on-board the aircraft that is required for other types of equipment. In addition, MMW radar systems require expensive radome technology.

Additionally, both passive FLIR cameras and active millimeter wavelength radar systems may have limited range in certain low visibility conditions such as heavy fog.

Thus, there is a need for real time or near real time sensing systems for and methods of providing enhanced vision at longer ranges and in inclement weather. Further, there is a need for real time or near real time sensing systems for and methods of providing enhanced vision imagery that is less expensive and does not require additional space on the aircraft. There is also a need for display systems for and methods of providing images of the external scene topography using radar data from a weather radar system. There is still a further need for systems for and methods of providing images of the runway environment derived from weather radar data where such images enable operation below certain specified altitudes during instrument approaches. Further still, there is a need for systems and methods that achieve higher resolution imaging using X-band and C-band radar data.

It would be desirable to provide a system and/or method that provides one or more of these or other advantageous features. Other features and advantages will be made apparent from the present specification. The teachings disclosed extend to those embodiments which fall within the scope of the appended claims, regardless of whether they accomplish one or more of the aforementioned needs.

СУЩНОСТЬ

In one aspect, embodiments of the inventive concepts disclosed herein are directed to an image processing system for enhanced vision including a processor and memory coupled to the processor. The memory contains program instructions that, when executed, causes the processor to provide radar beams and receive radar returns with improved angular and/or range resolution for deriving image data of the external scene topography.

In a further aspect, embodiments of the inventive concepts disclosed herein are directed to a vision method which uses or a vision system which includes a weather radar system configured to enhance resolution in range and in azimuth. The weather radar system generates image data associated with radar returns received by the weather radar system. The radar returns are in an X-band or a C-band. The vision system also includes a display in communication with the weather radar system configured to display an image associated with the image data.

In a further aspect, embodiments of the inventive concepts disclosed herein are directed to an airborne weather radar system which provides enhanced vision. The weather radar system includes an antenna, and a control circuit configured to provide radar beams via the antenna toward external surroundings and configured to receive radar returns. The control circuit is configured to process the radar returns to provide image data associated with the external surroundings. The weather radar system provides increased range resolution and increased angular resolution compared to weather radar sensing functions for the radar returns used to provide the image data. The radar beams are in the X-band or the C-band, and the image data is for providing a visual image of the external scene topography to a pilot.

In a further aspect, embodiments of the inventive concepts disclosed herein are directed to a method that provides a real time sensor image. The method includes receiving radar returns from an X-band or C-band airborne weather radar system. The radar returns can be processed to have increased range resolution and angular resolution and are received from external surroundings. The method also includes providing a visual image of the external scene topography based on the radar returns.

КРАТКОЕ ОПИСАНИЕ РИСУНКОВ

Implementations of the inventive concepts disclosed herein may be better understood when consideration is given to the following detailed description thereof. Such description makes reference to the annexed drawings, which are not necessarily to scale, and in which some features may be exaggerated and some features may be omitted or may be represented schematically in the interest of clarity. Like reference numerals in the figures may represent and refer to the same or similar element, feature, or function. In the drawings:

FIG. 1 is a schematic illustration of an aircraft control center or cockpit, according to an exemplary embodiment of the inventive concepts disclosed herein;

FIG. 2 is a schematic general block diagram of a display system for displaying an image derived from radar data, according to an exemplary embodiment of the inventive concepts disclosed herein;

FIG. 3 is a flow diagram showing an exemplary process used by the system illustrated in FIG. 2, according to a further exemplary embodiment of the inventive concepts disclosed herein;

FIG. 4 is an illustration of an image derived from radar data provided by the display system illustrated in FIG. 2 according to an exemplary embodiment of the inventive concepts disclosed herein; and

FIG. 5 is an illustration of an image derived from radar data and merged with HUD symbology provided by the display system illustrated in FIG. 2 according to yet another exemplary embodiment of the inventive concepts disclosed herein.

ПОДРОБНОЕ ОПИСАНИЕ

Before describing in detail the inventive concepts disclosed herein, it should be observed that the inventive concepts disclosed herein include, but are not limited to, a novel structural combination of data/signal processing components and communications circuits, and not in the particular detailed configurations thereof. Accordingly, the structure, methods, functions, control and arrangement of components, software, and circuits have, for the most part, been illustrated in the drawings by readily understandable block representations and schematic diagrams, in order not to obscure the disclosure with structural details which will be readily apparent to those skilled in the art, having the benefit of the description herein. Further, the inventive concepts disclosed herein are not limited to the particular embodiments depicted in the exemplary diagrams, but should be construed in accordance with the language in the claims.

According to various exemplary embodiments, an EVS or display system may be provided with radar sensing and imagery displayable to a pilot or co-pilot on an aircraft display, such as an HDD or HUD. For example, the display system may include or use a weather radar system to display an image based upon radar return data. In some embodiments, a Doppler weather radar system may be configured to have enhanced resolution (e.g., angular resolution and/or range resolution). Reflectivity of radar returns from runway structures in an airport terminal or runway environment, such as, an approach lighting system, a threshold lighting system, and or a runway edge lighting system, can be sensed. As will be appreciated, using a weather radar system configured according to the various exemplary embodiments provides greater range than millimeter wavelength radar sensing systems or passive FLIR or visible light camera systems in low visibility conditions, such as, heavy fog, given the weather radar system's superior ability of weather radar system to penetrate heavy fog.

Using the weather radar system configured according to the various exemplary embodiments may also provide EVS imagery having sufficient accuracy in low visibility conditions (given that many of the visual references required under Title 14 of the Code of Federal Regulations, part 91, such as, approach lighting systems, threshold lighting systems, runway edge lighting systems, and other runway structures, are metallic structures that exhibit high radar reflectivity). The imagery may allow lower landing minima (e.g., 100 feet or less) in some embodiments. In some embodiments, the lack of radar returns from the runway surface combined with runway structures and lights can provide a suitable image for runway identification by the pilot.

The display system includes a radar processing module in communication with the radar system and configured to generate high resolution radar image data for display in some embodiments. The image data is processed to provide a two-dimensional aircraft situation display (e.g., vertical profile display or plan view display) or three dimensional or perspective aircraft situation display image representative of the 3-D positions of runway structures in an airport terminal or runway environment based on the radar returns as described in U.S. patent application Ser. Nos. 14/301,199 and 14/482,681 incorporated herein by reference in their entireties in some embodiments. For example, the radar processing module can be embodied as a processor and a non-transitory memory containing program instructions that, when executed, cause the processor to provide radar beams and receive radar returns and generate image data from the radar returns. In some embodiments, program instructions stored on the non-transitory medium can cause the processor to filter the radar returns data to remove noise.

According to certain exemplary embodiments, a radar system such as a weather radar system, can be used to detect features of a runway environment. Utilizing the high radar cross section associated with metal content of runway lighting advantageously allows detection to be achieved whether at day or night, regardless of whether runway lights are on or are off in some embodiments. In one embodiment, the regular, periodic, equal spacing nature of visual aids, such as, approach lighting system, runway edge lights, taxi way lights, and center line lights, can be identified from the image generated from the radar data. In certain embodiments, the systems and methods can be utilized as extension to a combined vision system (CVS).

Referring to FIG. 1, a display system 10 is provided in an aircraft having an aircraft control center 11 or cockpit. The aircraft control center 11 includes flight displays 20 embodied as head down displays (HDDs). The aircraft control center 11 can also include a combiner 21 association with a head up display (HUD) system. In some embodiments, the combiner 21 is provided as part of a wearable HUD. Conformal images are provided on the combiner 21 in some embodiments.

The flight displays 20 and the combiner 21 can be used to provide information to the flight crew, thereby increasing visual range and enhancing decision-making abilities. In an exemplary embodiment, the flight displays 20 and the combiner 21 can include a weather display, a joint display, a weather radar map and a terrain display. Further, the flight displays 20 may include images from a synthetic vision system (SVS) or an enhanced vision system (EVS) (e.g., an EFVS). For example, the flight displays 20 can include a display configured to display a perspective image of terrain and/or weather information. Other views of terrain and/or weather information may also be provided (e.g., plan view, horizontal view, vertical view, or combinations thereof). Additionally, the flight displays 20 can be implemented using any of a variety of display technologies, including CRT, LCD, organic LED, dot matrix display, and others.

According to some embodiments, the display system 10 is configured to provide an image based upon radar data to at least one of the displays 20 or the combiner 21. In FIG. 1, the image on the combiner 21 includes a runway 23 or features 29 associated with the runway 23 as viewed from the aircraft (e.g., during approach and/or landing). In some embodiments, at least one of the displays 20 or the combiner 21 displays a merged image of terrain derived from two or more of enhanced vision data, radar data, and SVS data. Advantageously, real time radar data can be provided to provide a real time, all weather detection of the runway features 29 associated with the runway 23 in one embodiment. Advantageously, the radar data allows the runway 23 and its orientation to be viewed by one or more pilots in challenging weather conditions in some embodiments.

In some embodiments, a symbol or icon for the runway 23 and extended centerline 27 can be provided on the displays 20 or the combiner 21. In some embodiments, the runway 23 and extended centerline 27 can be associated with SVS data. A set of runway features 29, such as, approach lighting system or other runway and taxi way lights, can be indicated on the displays 20 or the combiner 21 in some embodiments. The runway features 29 can be associated with radar data in some embodiments.

Referring to FIG. 2, the display system 10 can be utilized for providing an image to any of the displays 20 or the combiner 21. The display system 10 is in communication with or includes a radar system 102, a synthetic vision system (SVS) 111 and an enhanced vision system (EVS) 112. The EVS 112 and the SVS 111 are optional in some embodiments. The display system 10 can include an HDD computer 132 and a HUD computer 134. The display system 10 includes a memory 153 for storing enhanced vision frame from the EVS 112, a memory 152 for storing enhanced vision frame from the SVS 111, a filter 154, an image renderer 155, a memory 156 for storing the radar image from the image renderer 155, an image merge function module 160, and an image merge control/configuration module 162.

The filter 154, the image renderer 155, the image merge module 160, and the image merge control/configuration module 162 can be embodied as software modules operating on a computing platform or a processor 175 and can be stored on a non-transitory medium. The processor 175 can be part of or integrated with the radar system 102, the SVS 111, the EVS 112, HDD display computer 132, or HUD computer 134 in certain embodiments. In one embodiment, processor 175 is an independent platform.

The radar system 102 is a weather radar system generally located inside the nose of the aircraft, inside a cockpit of the aircraft, on the top of the aircraft or on the tail of the aircraft in some embodiments. The radar system 102 can include a radar data storage unit 180, a radar antenna 182 and a processor 185. The radar system 102 can be a weather radar system, such as, a Multiscan.TM. radar system from Rockwell Collins, Inc. configured as described herein. The radar system 102 can utilize a split, half or sub-aperture or other technique for obtaining radar data associated with external surroundings in some embodiments. The radar system 102 can use the split or sub-aperture techniques of the radar systems described in U.S. application Ser. Nos. 13/627,788, 12/892,563, 13/250,798, 12/236,464, and 12/167,200 and U.S. Pat. No. 8,077,078, incorporated herein by reference and assigned to the assignee of the present application. The type of the radar system 102 and data gathering techniques are not discussed in the specification in a limiting fashion.

The processor 185 receives radar returns (e.g., weather radar returns data) from the radar antenna 182, processes the radar returns and provides the radar data in radar data storage unit 180. In certain embodiments, the data stored in radar data storage unit 180 can be stored as an image frame representing the data from a radar scan of the external surroundings (e.g., a runway environment).

The radar system 102 provides radar data (e.g., weather radar data) in the storage unit 180 to a filter 154 in one embodiment. In one embodiment, the image renderer 155 or other image generator can generate an image frame from the data stored in radar data storage unit 180 or filtered by the filter 154 and provides this to memory 156. Alternatively, the processor 185 can build the frame or image based upon radar return data from the radar system 102. Similarly, the SVS 111 can provide data or a frame for SVS image received by a memory 152. Alternatively, the display system 10 can provide the data or image frame to the memory 152 in response to data from the SVS 111. Similarly, the EVS 112 can provide data or a frame for EVS image received by a memory 153. Alternatively, the display system 10 can provide the data or image frame to the memory 153 in response to data from the EVS 112.

The radar data associated with the external surroundings can represent detected targets and the location of the detected targets. Targets include terrain, man-made features, objects, runways, etc. Improved angular resolution and range resolution techniques allow the location of the targets to be more accurately determined and represented in image data in some embodiments. The radar system 102 scans the external surroundings in front of the aircraft to sense the location of targets. The radar system 102 can utilize clutter suppression and Doppler filtering to improve performance in some embodiments.

In some embodiments, the radar system 102 provides data representing a 120 degree field of view in accordance with a weather radar sweep which takes approximately five seconds to complete in one embodiment. The sweep can be limited during approach to be a 30 degree sweep which requires five seconds before new data is available for display in certain embodiments. The sweep is directed toward the surface of the Earth so that returns are obtained which allow runway environment features to be detected. Various types of sweeps, scans and timings of sweeps and scans can be utilized without departing from the scope of the invention.

The radar system 102 embodied as a weather radar allows existing avionic equipment to be used as a real-time sensor for providing a radar-derived enhanced image of the external scene topography to the pilot in some embodiments. The image or representation generated by the radar system 102 is provided on the displays 20 or the combiner 21 can function as an EVS to provide situation awareness to the pilot in some embodiments. In other embodiments, the image or representation generated by the radar system 102 is provided on the displays 20 or the combiner 21 can function as an EFVS to allow lower landing minima.

The radar system 102 includes a range resolution module 190 and an angle resolution module 192 in some embodiments. The range resolution module 190 advantageously increases the range resolution of the radar system 102 when compared to conventional weather sensing operations in some embodiments. The angle resolution module 190 advantageously increases the angle resolution of the radar system 102 when compared to conventional weather sensing operations in some embodiments. The increased resolution in range and angle allows a higher resolution image to be provided on the displays 20 and the combiner 21 in some embodiments. The range resolution module 190 and the angle resolution module 192 can be software modules executed by the processor 185.

According to some embodiments, the radar system 102 under control of the angle resolution module 192 can use a beam sharpening method to achieve increased angular resolution. In some embodiments, the radar system 102 can utilize techniques such as beam sharpening (e.g., horizontal beam sharpening) and de-convolution of the beam point spread function for improved angular resolution. In some embodiments, the radar system 102 can use beam sharpening as a process that improves the antenna-induced poor angular resolution (e.g., due to the beam width). There are many methods that can be used such as: Doppler Beam Sharpening, Synthetic Aperture Radar (SAR), Monopulse Radar, Sub-Aperture Radar or Split-Aperture Radar, etc. Mathematical methods can be utilized to determine a center of the radar echo for identifying runway features. Techniques for beam sharpening are discussed in U.S. patent application Ser. Nos. 13/627,788, 12/892,563, 13/250,798, 12/236,464, and 12/167,200 and U.S. Pat. No. 8,077,078 incorporated herein by reference in their entireties.

The radar system 102 can use the radar antenna 182 configured as a switched aperture antenna for beam sharpening. The radar system 102 can also be configured for sequential lobing or monopulse operation to accurately estimate at which angle the target was located within the radar beam. In some embodiments, the radar beams provided by the radar antenna 182 and returns received by the radar antenna 182 associated with the radar system 102 can be separated into two or more portions and can be used to determine an angle from the radar antenna 182 to a target or a vector from the radar antenna 182 to a target such as a runway feature. The vector can be represented as an angle (bore site angle) and range to the target. Various processes can be utilized to calculate the angle or vector to the target.

The radar system 102 uses the radar antenna 182 that toggles between transmitting and receiving on the full aperture and transmitting on the full aperture while receiving on the partial aperture in some embodiments. These techniques can be used to accurately estimate at which angle the target was located within the radar beam and can be used to improve the accuracy of the Doppler calculations correcting for those angles. The received returns can be processed to determine a high resolution estimate of a target angle relative to the bore site of the antenna beam. According to some embodiments, the returns can be processed using a complex conjugate multiplication method to determine the target angle. The processing can be related to sequential lobing processing but is executed in the phase domain as opposed to the common amplitude domain in some embodiments.

In some embodiments, the radar system 102 uses sequential lobing techniques where two antennas that are close to the same place may be used, going back and forth between the two antennas. An amplitude signature or phase signature that varies between the two halves of the antennas may be used to obtain data about target position for detected targets (e.g., an object such as other aircraft, terrain, towers). Sequential lobing generally does not use phase comparisons with moving targets due to Doppler-induced phase changes that contaminate the phase center measurement. However, using a complex conjugate multiply method allows the Doppler-induced phase changes to be removed by cancellation. Therefore, a change in phase center between multiple different sub-apertures may be determined and used to determine angle to target.

In some embodiments, the range resolution module 190 provides higher resolution by increasing the effective waveform bandwidth of the radar system 102. The range resolution module 190 can use stepped-frequency compression in some embodiments. To provide higher range resolution, the range resolution module 192 can control the radar system 102 to provide ultra-wideband radar (UWB) beams (e.g., extremely narrow pulses with high power), or to provide intra pulse compression (frequency of phase modulation of the transmitted pulse) in some embodiments. Frequency coding techniques including the common linear frequency modulation (LFM) or chirp method, and discrete coded segments within the pulse can be utilized in some embodiments. Phase coding techniques including binary phase codes as well as various polyphase codes can be utilized in some embodiments. To provide higher range resolution, the range resolution module 192 can control the radar system 102 to provide interpulse pulse compression or stepped frequency compression (e.g., successive pulses with discrete increasing frequency steps) in some embodiments. In some embodiments, stepped frequency compression advantageously achieves high effective bandwidth with narrow instantaneous bandwidth. The receive bandwidth is smaller, has lower noise bandwidth, and a higher signal to noise ratio in some embodiments. Analog-to-digital sampling rates are lower (vs. pulse-compression) in some embodiments. In addition, the stepped frequency compression also has a smaller peak power (e.g., when compared to impulse), provides flexible transmit frequency control, can "hop" over restricted or undesired transmit frequencies, enables adaptive/cognitive frequency use, and rejects later received clutter from earlier transmit pulses in some embodiments. Further, the stepped frequency compression provides returns from clutter in ambiguous ranges that have frequencies that are different from returns from targets and rejects ambiguous clutter returns in the receiver IF filter of the radar system 102 in some embodiments. Stepped frequency compression generally does not achieve range resolution with a single pulse, requires transmit, receive and processing of a group of pulses for any one bin, and has more pronounced range-Doppler coupling (e.g., different Doppler shifts for each frequency) in some embodiments.

According to one embodiment, the SVS 111 can be any electronic system or device for providing a computer generated image of the external scene topography. The image can be from the perspective of the aircraft flight deck as derived from aircraft attitude, high-precision navigation solutions, and a database of terrain, obstacles and runway features. Generally, only those terrain, obstacle, and runway features which are contained in the current version of the SVS database are displayed in a conventional system. In some embodiments, the pilot uses the synthetic vision images as enhancements to available visual cues.

According to one embodiment, the EVS 112 can be any electronic system or device for providing a sensed image of the external scene topography. The EVS 112 can be an infrared camera in one embodiment.

In some embodiments, the display system 10 combines or fuses images from the HUD computer 134, the SVS 111 and/or the EVS 112 with the image derived from radar data from the radar system 102 to provide an overall image provided to the pilot according to one embodiment. In some embodiment, the image derived from the radar data are fused with HUD symbology for the displays 20 or the combiner 21.

The SVS 111 can include a terrain database and a processor according to one exemplary embodiment. The terrain database can be used to create a perspective image of the scene in front of the aircraft on a two-dimensional display or a three dimensional display. The terrain database can employ topographical colors similar to those depicted on standard aeronautical charts.

The SVS 111 can also receive aircraft position data from an aircraft data source. The aircraft data source can include any system or sensor (or combination thereof) that provides navigation data or aircraft flight parameters. For example, a typical navigation system in an aircraft has numerous sub-systems. Sub-systems which provide aircraft position data and flight parameter data could include, but are not limited to, an inertial navigation system (INS), a global navigation satellite system (e.g., global positioning system (GPS)), air data sensors, compasses, and a flight management computer (FMC).

In some embodiments, the filter 154 processes the radar data for better image quality. The filter 154 can be located in the radar system 102. The filter 154 can reduce noise and employ anti-speckling filtering, Kalman filtering, Chebyshev filtering, adaptive filtering, smoothing, etc. The filter 154 can also perform anti-aliasing in some embodiments. Techniques for increasing image quality and identifying runway features are discussed in U.S. patent application Ser. No. 14/482,681 and incorporated herein by reference.

In order to facilitate generation of clearer images, the processor 185 and/or the filter 154 may be configured to filter the radar returns data to identify areas having a reflectivity lower than a predetermined value. In some embodiments, low energy areas may be zeroed out based on their corresponding reflectivity values, such that the area will be rendered transparent. Such filtering may result in a final image with only highly reflective structures in an airport terminal area or runway environment, such as an approach lighting system, a threshold lighting system, and or a runway edge lighting system.

In some embodiments, the radar data from the radar data storage unit 180 is provided to filter 154, the image renderer 155, and the provided as image data to memory 156 and to the HUD computer 134 or the HDD display computer 132 for providing images on the displays 20 or the combiner 21. In another embodiment, the radar data can be provided as image data to an image merge function module 160. The image merge function module 160 receives an EVS frame from the memory 153 or an SVS frame from the memory 152 and merges the data to appropriately display an EVS image or an SVS image with the image derived from the radar data.

The processor 175 executes a fusion processing algorithm for fusing the frames from the memory 152, the memory 153, and the memory 156 provided as video signals in some embodiments. This fusion process may include special formatting (positioning, sizing, cropping, etc.) of specific features or the entire image from a specific image source based on other sensor inputs or aircraft. After the combined or fused image has been completed, the entire image is sized to fit appropriately within the total HUD field-of-view (e.g., with HUD symbology) and conformally overlay the outside scene, which is viewed through the combiner 21 of the HUD. In addition, the overall fused image contrast is standardized with the brightness/contrast to support the brightness/contrast controls of the HUD.

The processors 175 and 185 can be any hardware and/or software processor or processing architecture capable of executing instructions and operating on navigational and radar data. The processors 175 and 185 can be capable of determining navigational information such as altitude, heading, bearing, and location based on data from aircraft sensors. Applicants note that flow 300 can be performed in various equipment on the aircraft including in the HUD computer 134, a display processor, the weather radar system 102, a navigation system, the SVS 111, etc. in accordance with an exemplary embodiment. The processors 175 and 185 may be, or may include, one or more microprocessors, an application specific integrated circuit (ASIC), a circuit containing one or more processing components, a group of distributed processing components, circuitry for supporting a microprocessor, or other hardware configured for processing.

Image merge control configuration module 162 can provide format adjustments to data. The SVS 111 and the radar system 102 can have their own specific interface type and format. Also, each display of the displays 20 and the combiner 21 may require specific formatting. A standard format can be a format used in HUD processing functions. The image control configuration module 138 can be implemented in hardware, software, or combinations thereof.

Real time images derived from radar data allow the pilot exact and very reliable confirmation of the presence of a runway in some embodiment. In one embodiment, localization of the pattern of runway environment features, such as the runway approach lights or the runway edge lights allows easy recognition of the location of the runway with respect to the aircraft. In some embodiments the image data can be processed to provide a two-dimensional aircraft situation display (e.g., vertical profile display or plan view display). In other embodiments the image data can be processed to provide a three dimensional or perspective aircraft situation display image representative of the 3-D positions of runway environment features.

With reference to FIG. 3, a flow 300 can be performed by the display system 10 in some embodiments. At an operation 302, the weather radar system 102 provides a weather radar scan comprised of multiple radar beams. The radar beams are provided according to beam sharpening techniques and stepped frequency compression techniques in a way to increase the angular and range resolution in some embodiments. At an operation 304, radar returns are received according to the beam sharpening techniques and the stepped frequency compression techniques to increase the angular and range resolution in some embodiments. At an operation 306, the radar returns are processed to obtain image data in some embodiments. As discussed above, filtering or related techniques can be performed in an optional step by the filter 154. At an operation 308, the image data is merged with other image data, such as overlay symbology or sources of SVS or other EVS images. Operation 308 is optional.

At an operation 310, the image associated with the image data is displayed on a display via a display computer such as the HUD display computer 132 or the HUD computer 134. After operation 310, flow 300 returns to operation 302 in some embodiments.

With reference to FIG. 4, an image 400 of the external scene topography derived from radar associated with storage unit 180 includes features 402 associated with runway approach lights.

With reference to FIG. 5, an image 600 derived from the radar data is provided with HUD symbols 602. The HUD symbols 602 are shown in static format as a representative example only.

The radar system 102 generally operates by sweeping a radar beam horizontally and/or vertically along the sky for weather detection. For example, radar system 102 may conduct a first horizontal sweep directly in front of the aircraft and a second horizontal sweep downward at some tilt angle (e.g., 20 degrees down). Returns from different tilt angles may be electronically merged to form a composite image for display on an electronic display, such as the displays 20 and the combiner 21 in the aircraft control center 11. Sensing of the external surroundings can be performed at higher resolutions than the weather sensing and use one or more beams directed toward the external surroundings. Sensing of the external surroundings can be performed in a more forward looking direction with smaller azimuthal sweeps than are used for weather detection in some embodiments. GPS and/or other navigation information can be used to point the radar beam toward the external surroundings associated with an airport in some embodiments.

In some embodiments, the weather radar system 102 may operate in a weather sense mode until approach or landing. During approach or landing, the weather radar system 102 alternatively performs radar data gathering for sensing of the external surroundings, radar data gathering for weather sensing, and radar data gathering for wind shear detection. In some embodiments, during approach or landing, the weather radar system 102 alternatively performs radar data gathering for sensing of external surroundings, and radar data gathering for wind shear detection or other hazard detection. During approach or landing, weather radar system 102 alternatively performs radar data gathering for sensing of external surroundings, and radar data gathering for weather sensing in some embodiments. In some embodiments, weather sensing operations are suspended during approach and landing.

The scope of this disclosure should be determined by the claims, their legal equivalents and the fact that it fully encompasses other embodiments which may become apparent to those skilled in the art. All structural, electrical and functional equivalents to the elements of the above-described disclosure that are known to those of ordinary skill in the art are expressly incorporated herein by reference and are intended to be encompassed by the present claims. A reference to an element in the singular is not intended to mean one and only one, unless explicitly so stated, but rather it should be construed to mean at least one. No claim element herein is to be construed under the provisions of 35 U.S.C. .sctn.112, sixth paragraph, unless the element is expressly recited using the phrase "means for." Furthermore, no element, component or method step in the present disclosure is intended to be dedicated to the public, regardless of whether the element, component or method step is explicitly recited in the claims.

Embodiments of the inventive concepts disclosed herein have been described with reference to drawings. The drawings illustrate certain details of specific embodiments that implement the systems and methods and programs of the present disclosure. However, describing the embodiments with drawings should not be construed as imposing any limitations that may be present in the drawings. The present disclosure contemplates methods, systems and program products on any machine-readable media for accomplishing its operations. Embodiments of the inventive concepts disclosed herein may be implemented using an existing computer processor, or by a special purpose computer processor incorporated for this or another purpose or by a hardwired system.

As noted above, embodiments within the scope of the inventive concepts disclosed herein include program products comprising non-transitory machine-readable media for carrying or having machine-executable instructions or data structures stored thereon. Such machine-readable media may be any available media that may be accessed by a computer or other machine with a processor. By way of example, such machine-readable media may comprise RAM, ROM, EPROM, EEPROM, CD-ROM or other optical disk storage, magnetic disk storage or other magnetic storage devices, or any other medium which may be used to carry or store desired program code in the form of machine-executable instructions or data structures and which may be accessed by a computer or other machine with a processor. Thus, any such a connection is properly termed a machine-readable medium. Combinations of the above are also included within the scope of machine-readable media. Machine-executable instructions comprise, for example, instructions and data which cause processor to perform a certain function or group of functions.

Embodiments in the inventive concepts disclosed herein have been described in the general context of method steps which may be implemented in one embodiment by a program product including machine-executable instructions, such as program code, for example in the form of program modules executed by machines in networked environments. Generally, program modules include routines, programs, objects, components, data structures, etc. that perform particular tasks or implement particular abstract data types. Machine-executable instructions, associated data structures, and program modules represent examples of program code for executing steps of the methods disclosed herein. The particular sequence of such executable instructions or associated data structures represent examples of corresponding acts for implementing the functions described in such steps.

As previously indicated, embodiments in the present disclosure may be practiced in a networked environment using logical connections to one or more remote computers having processors. Those skilled in the art will appreciate that such network computing environments may encompass many types of computers, including personal computers, hand-held devices, multi-processor systems, microprocessor-based or programmable consumer electronics, network PCs, minicomputers, mainframe computers, and so on. Embodiments in the disclosure may also be practiced in distributed computing environments where tasks are performed by local and remote processing devices that are linked (either by hardwired links, wireless links, or by a combination of hardwired or wireless links) through a communications network. In a distributed computing environment, program modules may be located in both local and remote memory storage devices.

The database or system memory may include read only memory (ROM) and random access memory (RAM). The database may also include a magnetic hard disk drive for reading from and writing to a magnetic hard disk, a magnetic disk drive for reading from or writing to a removable magnetic disk, and an optical disk drive for reading from or writing to a removable optical disk such as a CD ROM or other optical media. The drives and their associated machine-readable media provide nonvolatile storage of machine-executable instructions, data structures, program modules and other data for the computer. User interfaces, as described herein, may include a computer with monitor, keyboard, a keypad, a mouse, joystick or other input devices performing a similar function.

It should be noted that although the diagrams herein may show a specific order and composition of method steps, it is understood that the order of these steps may differ from what is depicted. For example, two or more steps may be performed concurrently or with partial concurrence. Also, some method steps that are performed as discrete steps may be combined, steps being performed as a combined step may be separated into discrete steps, the sequence of certain processes may be reversed or otherwise varied, and the nature or number of discrete processes may be altered or varied. The order or sequence of any element or apparatus may be varied or substituted according to alternative embodiments. Accordingly, all such modifications are intended to be included within the scope of the present disclosure.

The foregoing description of embodiments has been presented for purposes of illustration and description. It is not intended to be exhaustive or to limit the subject matter to the precise form disclosed, and modifications and variations are possible in light of the above teachings or may be acquired from practice of the subject matter disclosed herein. The embodiments were chosen and described in order to explain the principals of the disclosed subject matter and its practical application to enable one skilled in the art to utilize the disclosed subject matter in various embodiments and with various modifications as are suited to the particular use contemplated. Other substitutions, modifications, changes and omissions may be made in the design, operating conditions and arrangement of the embodiments without departing from the scope of the presently disclosed subject matter.

While the exemplary embodiments illustrated in the figures and described above are presently preferred, it should be understood that these embodiments are offered by way of example only. Other embodiments may include, for example, structures with different data mapping or different data. The disclosed subject matter is not limited to a particular embodiment, but extends to various modifications, combinations, and permutations that nevertheless fall within the scope and spirit of the appended claims.

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