Выделить слова:


Патент США №	10703506
Автор(ы)	Miralles и др.
Дата выдачи	07 июля 2020 г.

Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube

РЕФЕРАТ

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

Авторы:

Carlos Thomas Miralles (Burbank, CA), Guan H Su (Rowland Heights, CA), Alexander Andryukov (Simi Valley, CA), John McNeil (Tujunga, CA)

Патентообладатель:

Имя	Город	Штат	Страна	Тип
AEROVIRONMENT, INC.	Simi Valley	CA	US

Заявитель:

AEROVIRONMENT, INC. (Simi Valley, CA)

ID семейства патентов

44067166

Номер заявки:

16/574,344

Дата регистрации:

18 сентября 2019 г.

Prior Publication Data


	Document Identifier	Publication Date
	US 20200140120 A1	May 7, 2020

Отсылочные патентные документы США


Application Number	Filing Date	Patent Number	Issue Date
16137196	Sep 20, 2018	10450089
14887675	Nov 13, 2018	10124909
13234044	Nov 17, 2015	9187184
13229377	Aug 13, 2013	8505430
PCT/US2010/048313	Sep 9, 2010
61240987	Sep 9, 2009
61241001	Sep 9, 2009
61240996	Sep 9, 2009

Класс патентной классификации США:	1/1
Класс совместной патентной классификации:	F41F 1/00 (20130101); F42B 39/14 (20130101); B64F 1/04 (20130101); B64F 1/06 (20130101); B64C 39/024 (20130101); F41A 21/02 (20130101); F41F 3/042 (20130101); B64C 2201/102 (20130101); B64C 2201/201 (20130101); B64C 2201/146 (20130101); B64C 2201/08 (20130101)
Класс международной патентной классификации (МПК):	B64F 1/04 (20060101); F41F 3/042 (20060101); F42B 39/14 (20060101); B64C 39/02 (20060101); F41F 1/00 (20060101); B64F 1/06 (20060101); F41A 21/02 (20060101)

Использованные источники

[Referenced By]

Патентные документы США


2512069	June 1950	Mull
2752110	June 1956	Peterson
2792962	May 1957	Granfelt
2996011	August 1961	Dunlap
3083936	April 1963	Rethorst
3107616	October 1963	Boaz et al.
3107617	October 1963	F et al.
3147939	September 1964	Clarkson
3223361	December 1965	Girard
3262391	July 1966	Shober
3306163	February 1967	Griessen
3347466	October 1967	Nichols
3415467	December 1968	Barringer
3724319	April 1973	Zabelka et al.
3789353	January 1974	Hunter et al.
3808940	May 1974	Schillreff et al.
3916560	November 1975	Becker
3939967	February 1976	Tenney et al.
4022403	May 1977	Chiquet
4090684	May 1978	Look et al.
4106727	August 1978	Ortell
4209147	June 1980	Jones
4277038	July 1981	Yates et al.
4296894	October 1981	Schnabele et al.
4301708	November 1981	Mussey
4354646	October 1982	Raymer
4364531	December 1982	Knoski
4383663	May 1983	Nichols
4408538	October 1983	Deffayet et al.
4410151	October 1983	Hoppner et al.
4541593	September 1985	Cabrol
4553718	November 1985	Pinson
4568040	February 1986	Metz
4590862	May 1986	Grabarek et al.
4664338	May 1987	Steuer et al.
H400	January 1988	Hammon et al.
4730793	March 1988	Thurber, Jr. et al.
4735148	April 1988	Holtzman et al.
4776255	October 1988	Smith
4841867	June 1989	Garrett
4958571	September 1990	Puckett
4990921	February 1991	Chisholm
4997144	March 1991	Wolff et al.
D317003	May 1991	Tribe et al.
5106033	April 1992	Phan
5112006	May 1992	Palmer
5115711	May 1992	Bushagour et al.
5118052	June 1992	Alvarez Calderon F
5141175	August 1992	Harris
5193517	March 1993	Taylor et al.
5303695	April 1994	Shopsowitz
5322243	June 1994	Stoy
5370032	December 1994	Reuche et al.
5417139	May 1995	Boggs et al.
5458041	October 1995	Sun et al.
5458042	October 1995	Cante
5566073	October 1996	Margolin
5581250	December 1996	Khvilivitzky
5582364	December 1996	Trulin et al.
5615846	April 1997	Shmoldas et al.
5671138	September 1997	Bessacini et al.
5671899	September 1997	Nicholas et al.
5695153	December 1997	Britton et al.
5722618	March 1998	Jacobs et al.
5780766	July 1998	Schroppel
5819717	October 1998	Johnson et al.
5833782	November 1998	Crane et al.
5855339	January 1999	Mead et al.
5874727	February 1999	Harraeus et al.
5884872	March 1999	Greenhalgh
5890441	April 1999	Swinson et al.
5899410	May 1999	Garrett
5904724	May 1999	Margolin
5927648	July 1999	Woodland
5933263	August 1999	Kinstler
5965836	October 1999	Rakov
D417639	December 1999	Carichner et al.
6043867	March 2000	Saban
6053452	April 2000	Yamakawa et al.
6056237	May 2000	Woodland
6122572	September 2000	Yavnai
6244535	June 2001	Felix
6354182	March 2002	Milanovich
6359833	March 2002	English
6371002	April 2002	MacLeod
6392213	May 2002	Martorana et al.
6418870	July 2002	Lanowy et al.
6422507	July 2002	Lipeles
D461159	August 2002	Miralles
6467733	October 2002	Young et al.
6496151	December 2002	Ferreri et al.
6535816	March 2003	Smith
6567044	May 2003	Carroll
6568309	May 2003	MacLeod
6571715	June 2003	Bennett et al.
6601795	August 2003	Chen
6672533	January 2004	Regebro
6678394	January 2004	Nichani
6722252	April 2004	O'Dwyer
6847865	January 2005	Carroll
6851347	February 2005	Plunkett
6851647	February 2005	Rosenbaum et al.
6923404	August 2005	Liu et al.
6931775	August 2005	Burnett
6967614	November 2005	Wardell et al.
6978970	December 2005	Purcell
7014141	March 2006	Cox et al.
7083140	August 2006	Dooley
7093789	August 2006	Barocela et al.
7207254	April 2007	Veitch et al.
7210654	May 2007	Cox et al.
7216429	May 2007	Logan et al.
7237750	July 2007	Chiu et al.
7275973	October 2007	Ong
7299130	November 2007	Mulligan et al.
7302316	November 2007	Beard et al.
7338010	March 2008	Corder et al.
7343232	March 2008	Duggan et al.
7367525	May 2008	McKendree et al.
7398721	July 2008	Alberding et al.
7414706	August 2008	Nichols et al.
7484450	February 2009	Hunn et al.
7520204	April 2009	Williams et al.
7559505	July 2009	Janka
7581702	September 2009	Olson et al.
7584925	September 2009	Miller et al.
7631833	December 2009	Ghaleb et al.
7742436	June 2010	Carrillo et al.
7793606	September 2010	LaCour
7800645	September 2010	Nonoyama et al.
7816635	October 2010	Fink
7841559	November 2010	O'Shea
7883051	February 2011	Sammy
7900869	March 2011	Kessler et al.
7934456	May 2011	Heitmann et al.
8056480	November 2011	Brydges-Price
8068983	November 2011	Vian et al.
8089033	January 2012	Zank et al.
8089034	January 2012	Hammerquist
8109212	February 2012	O'Dwyer
8178825	May 2012	Goossen et al.
8424233	April 2013	Cronin et al.
8439301	May 2013	Lussier et al.
8444082	May 2013	Foch
8505430	August 2013	Miralles et al.
8657226	February 2014	McGinnis
8686326	April 2014	Dennison et al.
8692171	April 2014	Miller et al.
8887641	November 2014	Manole et al.
8924069	December 2014	Kaneshige et al.
8985504	March 2015	Tao et al.
9108713	August 2015	Tao et al.
9187184	November 2015	Miralles et al.
9703295	July 2017	Neal et al.
D813761	March 2018	Balaresque et al.
9947230	April 2018	Hu et al.
2002/0030142	March 2002	James
2002/0062730	May 2002	Thornton
2003/0006340	January 2003	Harrison et al.
2003/0089219	May 2003	Gorman
2003/0094536	May 2003	LaBiche
2003/0136873	July 2003	Churchman
2003/0155463	August 2003	Cox et al.
2003/0173459	September 2003	Fanucci et al.
2003/0178527	September 2003	Eisentraut et al.
2003/0192985	October 2003	Lipeles
2004/0030449	February 2004	Solomon
2004/0068351	April 2004	Solomon
2004/0167682	August 2004	Beck et al.
2004/0194614	October 2004	Wang
2004/0217230	November 2004	Fanucci et al.
2005/0004723	January 2005	Duggan et al.
2005/0004759	January 2005	Siegel
2005/0011397	January 2005	Eches
2005/0051667	March 2005	Arlton et al.
2005/0077424	April 2005	Schneider
2005/0127242	June 2005	Rivers
2005/0139363	June 2005	Thomas
2005/0178898	August 2005	Yuen
2005/0195096	September 2005	Ward et al.
2005/0204910	September 2005	Padan
2005/0218260	October 2005	Corder et al.
2005/0255842	November 2005	Dumas et al.
2005/0258306	November 2005	Barocela et al.
2005/0274845	December 2005	Miller et al.
2006/0011777	January 2006	Arlton et al.
2006/0086241	April 2006	Miller et al.
2006/0132753	June 2006	Nichols et al.
2006/0253254	November 2006	Herwitz
2006/0255205	November 2006	Gleich et al.
2007/0018033	January 2007	Fanucci et al.
2007/0023582	February 2007	Steele et al.
2007/0057115	March 2007	Newton
2007/0125904	June 2007	Janka
2007/0152098	July 2007	Sheahan et al.
2007/0157843	July 2007	Roemerman et al.
2007/0158911	July 2007	Torre
2007/0210953	September 2007	Abraham et al.
2007/0215751	September 2007	Robbins et al.
2007/0246601	October 2007	Layton
2008/0041221	February 2008	Gaigler
2008/0071431	March 2008	Dockter et al.
2008/0074312	March 2008	Cross et al.
2008/0078865	April 2008	Burne
2008/0087763	April 2008	Sheahan et al.
2008/0088719	April 2008	Jacob et al.
2008/0093501	April 2008	Miller et al.
2008/0111021	May 2008	Toth et al.
2008/0133069	June 2008	Rica et al.
2008/0148927	June 2008	Alberding et al.
2008/0177432	July 2008	Deker et al.
2008/0206718	August 2008	Jaklitsch et al.
2008/0215195	September 2008	Jourdan et al.
2008/0217486	September 2008	Colten et al.
2008/0243371	October 2008	Builta et al.
2009/0007765	January 2009	Hunn et al.
2009/0008495	January 2009	Koenig
2009/0045290	February 2009	Small et al.
2009/0050750	February 2009	Goossen
2009/0100995	April 2009	Fisher
2009/0114762	May 2009	Hurty
2009/0134273	May 2009	Page et al.
2009/0157233	June 2009	Kokkeby et al.
2009/0193996	August 2009	Brydges-Price
2009/0242690	October 2009	Sammy
2009/0302151	December 2009	Holmes
2009/0321094	December 2009	Thomas
2010/0012774	January 2010	Fanucci et al.
2010/0025543	February 2010	Kinsey et al.
2010/0042269	February 2010	Kokkeby et al.
2010/0042273	February 2010	Meunier et al.
2010/0121575	May 2010	Aldridge et al.
2010/0141503	June 2010	Baumatz
2010/0198514	August 2010	Miralles
2010/0212479	August 2010	Heitmann
2010/0213309	August 2010	Parks
2010/0264260	October 2010	Hammerquist
2010/0281745	November 2010	Condon et al.
2010/0282917	November 2010	O'Shea
2010/0314487	December 2010	Boelitz et al.
2011/0035149	February 2011	McAndrew et al.
2011/0057070	March 2011	Lance et al.
2011/0084162	April 2011	Goossen et al.
2011/0146525	June 2011	Caillat
2011/0226174	September 2011	Parks
2012/0000390	January 2012	Heitmann
2012/0068002	March 2012	Unger et al.
2012/0205488	August 2012	Powell et al.
2012/0267473	October 2012	Tao et al.
2014/0172200	June 2014	Miralles
2015/0008280	January 2015	Smoker
2015/0053193	February 2015	Pruett et al.

Зарубежные патентные документы


2659111	Jul 2011	CA
85104530	Jan 1987	CN
2769834	Apr 2006	CN
200960979	Oct 2007	CN
200967562	Oct 2007	CN
200967562	Oct 2007	CN
101198520	Jun 2008	CN
101249891	Aug 2008	CN
101473184	Jul 2009	CN
101495367	Jul 2009	CN
3048598	Apr 1990	DE
2188713	Oct 1987	GB
2434783	Aug 2007	GB
60188799	Sep 1985	JP
S60188799	Sep 1985	JP
64028096	Jan 1989	JP
02291703	Dec 1990	JP
05106997	Apr 1993	JP
1993106997	Apr 1993	JP
05149696	Jun 1993	JP
06273098	Sep 1994	JP
07089492	Apr 1995	JP
H0789492	Apr 1995	JP
09026300	Jan 1997	JP
2000266499	Sep 2000	JP
2001153599	Jun 2001	JP
2001206298	Jul 2001	JP
2003177000	Jun 2003	JP
2004271216	Sep 2004	JP
2005500774	Jan 2005	JP
2005067398	Mar 2005	JP
2005240841	Sep 2005	JP
2007228065	Sep 2007	JP
2008536736	Sep 2008	JP
9712195	Apr 1997	WO
03017419	Feb 2003	WO
2003017419	Feb 2003	WO
2005001372	Jan 2005	WO
2005023642	Mar 2005	WO
2006097592	Sep 2006	WO
2008020448	Feb 2008	WO

Другие источники

Aerovironment,Inc. et al, International Search Reports for Serial No. PCT/US2010/048313 dated May 26, 2011. cited by applicant .
Andreas Parsch; Coyote; Advanced Ceramics Research; 2006; . (Year: 2006). cited by applicant .
BusinessWire; First Test Flight of Coyote Unmanned Aircraft System; Jan. 19, 2010; YouTube; ,https://www.youtube.com/watch?v=0MmdHLRxIN4>. (Year: 2010). cited by applicant .
International Search Repot for Serial No. PCT/US2010/048313 dated May 26, 2011. cited by applicant .
European Search Report for EP Application No. EP 10833732, dated Jun. 1, 2015. cited by applicant .
European Search Report for Serial No. EP161799150 dated Jan. 17, 2017. cited by applicant .
International Search Report for PCT/US2010/048323 dated Jun. 20, 2011. cited by applicant .
International Search Report for Serial No. PCT/US10/22942 dated Sep. 27, 2010. cited by applicant .
International Search Report for Serial No. PCT/US2010/048323 dated Jun. 20, 2011. cited by applicant .
International Search Report for serial No. PCT/US2010/048313 dated May 26, 2011. cited by applicant .
Supplementary EP Search Report for EP Serial No. EP10833731 completed Nov. 4, 2014. cited by applicant .
Tares Unmanned Combat Air Vehicle (UCAV), Germany, [retrieved on Feb. 24, 2010], Retrieved from the Internet:. cited by applicant .
Tares Unmanned Combat Air Vehicle (UCAV), Germany, [retrieved on Feb. 24, 2010], Retrieved from the Internet:<URL:http://www.army-technology.com/projects/taifun/>. cited by applicant .
Wikipedia, "Sabot", https://en.wikipedia.org/wiki/Sabot; archived on Feb. 24, 2011 by Internet Archive, https://web.archive.org/web/ 20100224075656/https://en.wikipedia.org/wiki/Sabot; accessed Oct. 10, 2018 (Year:2011). cited by applicant.

Главный эксперт: Benedik; Justin M
Уполномоченный, доверенный или фирма: Brooks Acordia IP Law, PC Yedidsion; Pejman Aagaard; Eric

Текст решения-прецедента

ПЕРЕКРЁСТНАЯ ССЫЛКА НА "РОДСТВЕННЫЕ" ЗАЯВКИ

This application is a continuation of patent application Ser. No. 16/137,196 filed Sep. 20, 2018, which is a continuation of patent application Ser. No. 14/887,675 filed Oct. 20, 2015, which issued as U.S. Pat. No. 10,124,909 on Nov. 13, 2018, which is a continuation of patent application Ser. No. 13/234,044, filed Sep. 15, 2011, which issued as U.S. Pat. No. 9,187,184 on Nov. 17, 2015, which is a continuation of patent application Ser. No. 13/229,377, filed Sep. 9, 2011, which issued as U.S. Pat. No. 8,505,430 on Aug. 13, 2013, which is a continuation of International Application No. PCT/US2010/048313, filed Sep. 9, 2010, which claims priority to and the benefit of U.S. Provisional Patent Application Ser. No. 61/240,996 filed Sep. 9, 2009, U.S. Provisional Patent Application Ser. No. 61/240,987 filed Sep. 9, 2009, and U.S. Provisional Patent Application Ser. No. 61/241,001 filed Sep. 9, 2009, all of which are hereby incorporated herein by reference in their entirety for all purposes.

ФОРМУЛА ИЗОБРЕТЕНИЯ

What is claimed is:

1. A method comprising: transmitting, by a transmitter disposed within a launcher volume of a launcher, wireless communication via one or more RF signals transmitted wirelessly through a launcher wall of the launcher, wherein the launcher volume is defined by the launcher wall, and wherein the launcher wall comprises a continuous radio-frequency (RF) permeable material.

2. The method of claim 1 further comprising: receiving, by a receiver disposed within the launcher volume of the launcher, wireless communication via one or more RF signals received wirelessly through the launcher wall of the launcher.

3. The method of claim 2, wherein the received one or more RF signals are received by an RF antenna disposed within the launcher volume.

4. The method of claim 2 further comprising: transmitting, by an external communications node, the one or more RF signals received by the receiver disposed within the launcher volume of the launcher.

5. The method of claim 2, wherein the one or more RF signals received by the receiver comprise at least one of: a reconnaissance waypoint information, a surveillance optimizing trajectory information, a target data, and a flight plan information.

6. The method of claim 1, wherein the transmitter is positioned to transmit wirelessly through the launcher wall of the launcher.

7. The method of claim 1 further comprising: generating gas by one or more gas generating canisters during a launch of an unmanned aerial vehicle (UAV) disposed within the launcher volume; and retaining the generated gas within the launcher volume after the launch of the UAV.

8. The method of claim 1, wherein the transmitted wireless communication comprises a status of an unmanned aerial vehicle (UAV) disposed within the launcher volume.

9. The method of claim 1, wherein the transmitted wireless communication comprises a status of the launcher.

10. The method of claim 9, wherein the status of the launcher comprises at least one of: a battery level and a result of a self-diagnosis.

11. A method comprising: engaging an unmanned aerial vehicle (UAV) within a launcher volume by a sabot, wherein the launcher volume is defined by an inner wall, wherein the sabot is dimensioned to provide a pressure seal at the inner wall, and wherein the sabot is tethered to the inner wall.

12. The method of claim 11 further comprising: orienting an open end of the sabot toward a high pressure volume, wherein the tethered sabot is hollow.

13. The method of claim 12 further comprising: attaching the tether within a hollow of the sabot.

14. The method of claim 13 further comprising: attaching the tether to the inner wall retaining the high pressure volume.

15. The method of claim 14 wherein the tether has a payout length that prevents the sabot from fully exiting the launcher volume.

16. The method of claim 11 further comprising: generating gas by one or more gas generating canisters during a launch of the UAV disposed within the launcher volume.

17. The method of claim 16 further comprising: retaining the generated gas within the launcher volume after the launch of the UAV.

18. The method of claim 16 further comprising: forming a high-pressure volume between the sabot and the one or more gas generating canisters during the launch of the UAV.

19. The method of claim 11 further comprising: applying a membrane seal over an open end of the launcher volume thereby preventing outside elements from entering the launcher volume prior to launch.

20. The method of claim 19 further comprising: applying a cap over the membrane seal.

ОПИСАНИЕ

ОБЛАСТЬ ТЕХНИКИ

Embodiments include launch tubes and canisters, report-suppressing launch tubes, and sabots for an unmanned aerial vehicle (UAV). Embodiments also pertain to systems comprising one or more UAVs, and to a system comprising a command node and a launcher containing a UAV in a pre-launch state configured to receive command signals from the command node.

УРОВЕНЬ ТЕХНИКИ

Typically UAVs are shipped to a launch site in an unassembled state. At the site they are assembled, tested, and then launched. Launching is typically executed by hand, by an elastic tether, a powered wench, from a moving vehicle, or some combination thereof. Such methods can be time consuming and/or cumbersome. Once launched, a UAV may receive uplinks and may be guided by a human-in-the-loop, a human intermittently up-linking course corrections, e.g., via supervisory control, or by a preloaded intercept/strike point in combination with an onboard flight path guidance generator and outputs of inertial sensors and/or from a Global Positioning System (GPS) receiver.

СУЩНОСТЬ

Embodiments may include articles such as an unmanned aerial vehicle (UAV) launch tube comprising: (a) at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture; (b) at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture; and (c) one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. The at least one inner layer of prepreg substrate may comprise epoxy prepreg Kevlar.TM. or other light weight composites. The at least one outer layer of prepreg substrate may comprise epoxy prepreg Kevlar.TM. or other light weight composites. The one or more structural panels may comprise balsawood or a light weight composite. In some embodiments, the one or more structural panels may comprise four structural panels, where each panel comprises a cylindrical segment, and each panel has a planar surface defined by a chord length and a cylindrical height. Each proximate planar surface may be disposed orthogonally relative to one another, each structural panel having a first lateral edge and a second lateral edge perpendicular to the chord length, where the first lateral edge of a first structural panel is proximate to, but not contacting, a first lateral edge of a second structural panel. The second lateral edge of the first structural panel may be proximate to, but not contacting, a first lateral edge of a third structural panel. The first lateral edge of a fourth structural panel may be proximate to, but not contacting, a second lateral edge of a second structural panel. The second lateral edge of the fourth structural panel may be proximate to, but not contacting, a second lateral edge of a third structural panel, where the planar surfaces of each of the four structural panels may be aligned with a launch tube centerline. In addition, each of the four structural panels may be disposed between the inner layer of epoxy prepreg substrate and the outer layer of epoxy prepreg substrate. Embodiments include articles such as an unmanned aerial vehicle (UAV) launch tube configured for report suppression comprising a structural element configured to engage the UAV within a launcher volume defined by an inner wall. The article may be dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall. The structural element may have a hollow, or cavity, having an open end oriented toward a high pressure volume and a tether attached within a hollow or cavity of the article and may be attached to the inner wall retaining the high pressure volume.

Additional embodiments may include methods and UAV systems comprising: (a) a communications node; and (b) a launcher comprising a UAV configured to receive, in a pre-launch state, command inputs from the communications node. In some embodiments, the UAV in a pre-launch state is further configured to transmit to a communications node UAV status data responsive to a received query signal. In some embodiments, the RF antenna of the UAV is contained within the launcher volume. In some embodiments, the launch propulsion system is configured to receive RF signals.

КРАТКОЕ ОПИСАНИЕ РИСУНКОВ

Embodiments are illustrated by way of example and not limitation in the figures of the accompanying drawings, and in which:

FIG. 1 is a top-side perspective view of an exemplary launch tube embodiment;

FIG. 2 is a bottom-side perspective view of a portion of an exemplary launch tube embodiment;

FIG. 3 is cross-sectional view of an exemplary launch tube embodiment;

FIG. 4 is an exemplary depiction of a launch tube configured as a UAV carrying case embodiment of the present invention;

FIG. 5 is an exemplary depiction of a launch tube configured as a UAV carrying case embodiment of the present invention;

FIG. 6 is an exemplary depiction of a launch tube configured as a UAV carrying case embodiment with support struts and footing deployed;

FIG. 7 is a top-side perspective view of an exemplary tethered sabot embodiment of the present invention;

FIG. 8 is a top view of an exemplary tethered sabot embodiment of the present invention;

FIG. 9 is a cross-sectional view of an exemplary tethered sabot embodiment of the present invention;

FIGS. 10A-10E depict an exemplary UAV launch using a tethered sabot embodiment of the present invention;

FIGS. 11A-11B depict, in a cross-sectional view of the distal end of a lunch tube, an exemplary UAV launch using a tethered sabot embodiment of the present invention;

FIG. 12A is a bottom-side perspective view of an exemplary UAV in a pre-launch state;

FIG. 12B depicts an exemplary UAV with its airfoils deployed and its pusher propeller rotating;

FIG. 13 is a bottom-side perspective view of a portion of an exemplary launch tube embodiment;

FIG. 14 depicts an exemplary functional block diagram of the UAV processing and guidance and control subsystem; and

FIG. 15 is a top-level system architecture of a system embodiment.

ПОДРОБНОЕ ОПИСАНИЕ

FIG. 1 is a top-side perspective view of an exemplary launch tube 100 embodiment. The top, or open end 110, of the exemplary launch tube presents a square-shaped aperture having rounded corners. Disposed between an outer layer of prepreg substrate 120 and an inner layer of prepreg substrate 130 are four structural panels 141-144.

FIG. 2 is a bottom-side perspective view of a portion of an exemplary launch tube embodiment 200. The bottom, or closed end 210, of the exemplary launch tube presents an end 220 curved about an axis collinear with a first footing pivot point protrusion 230 where a second footing pivot point protrusion is opposite the first footing pivot point protrusion 230, but not shown in the figure.

FIG. 3 is a cross-sectional view 300 of the exemplary launch tube embodiment of FIG. 1 showing four structural panels 141-144 disposed about a launch tube centerline. A non-cylindrical UAV may be placed and launched from such a volume. Each panel is shown having an outer surface curvature 311 representative of a radius of curvature 322 greater than the distance 323 from the outer surface 350 to the launch tube centerline 360. Each panel 141-144 is shown having a planar inner surface 312 representative of a chord length 313. Accordingly, an end face 314 of each panel 141-144 in the present cross-sectional view is a circular segment. Each panel is shown disposed between an inner layer of prepreg substrate 370 and an outer layer of prepreg substrate 380. The panels are shown disposed apart from one another, with there being space 390 between the lateral edges 318, 319 of the panels. Accordingly, the inner layer of prepreg substrate 370 and the outer layer of prepreg substrate 380 contact one another at the corners 301-304 of the right parallelepiped-shaped volume 305. The outer layer of prepreg substrate 380 defines in cross-sectional view, a substantially ovoid-shaped outside perimeter. In some embodiments the inner layer 370 and outer layer 380 may comprise epoxy prepreg Kevlar.TM. or a composite material, or combinations of both, and the structural panels may comprise balsawood or a light weight composite material, or combination of both.

FIG. 4 is an exemplary depiction of a launch tube configured as a UAV carrying case 400 embodiment. A footing 410 is shown rotatably attached to the launch tube 405 via a footing pivot point protrusion 230. A first strut or leg 420 is shown rotatably attached to the launch tube 405 proximate to the top 110 of the launch tube. A second strut or leg is disposed opposite the first strut and is not shown in this figure. A cap 430 is shown covering the otherwise open end of the launch tube and is shown restrained by a circumferential strap 431.

FIG. 5 is an exemplary depiction of a launch tube configured as a UAV carrying case embodiment in a partially deployed state. That is, the cap 430 is shown removed, exposing the open end of the launch tube that may have an optional membrane seal 540 as shown. The seal 540 may be a frangible film applied to repel sand, soil, moisture, and/or grit from entering the launch tube during pre-launch preparations. The footing 410 is shown partially rotated away from the launch tube and the first strut or leg 420 is shown partially rotated into a support position.

FIG. 6 is an exemplary depiction of a launch tube 600 configured as a UAV carrying case embodiment with support struts 420 and footing 410 deployed. The use of the term "tube" is done so with the intent to indicate a volume from which a UAV may be launched and not to limit the shape of the volume to a cylindrical tube. The angle 610 of the pair of struts or pair of legs may be adjusted to accommodate a desired launch angle 601 relative to local level 602. Likewise, the angle 620 between the launch tube and the footing may be adjusted to accommodate the desired launch angle 601. In some embodiments, the pair of struts or pair of legs 420 may comprise segments of differing diameters allowing for a telescoping of the distal segment 422 into and out of the proximal segment 421. In these embodiments, the overall length of the legs may be adjusted, either to accommodate uneven local terrain, and to accommodate a desired launch angle 601, or both. The footing 410 may be sized to receive the down force from a boot and/or a mass to further enhance the stiction between the lower surface of the footing and the local ground surface 602. The top of the launch tube 630 may include a frangible membrane to protect the internal launcher volume from grit, sand, moisture and the effects of weather. Once the launcher is positioned on a surface, the launcher 600 may be remotely controlled for purposes of uploading mission information to the UAV while the UAV is in a pre-launch state and for purposes of receiving UAV status information.

Embodiments include an unmanned aerial vehicle (UAV) launch tube that may comprise a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall, and tethered to the inner wall. In some embodiments, the tethered sabot may be hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume.

For a launcher having a right parallelepiped aperture, an exemplary tethered sabot 700 embodiment as depicted in FIG. 7 may be used. The sabot may be made of carbon fiber, e.g., a prepreg carbon fiber shaped over a form and cured to yield a hollow article, open at one end. The sabot may have a channel 710 for receiving a pusher propeller assembly of a UAV. The sabot may also have a depression 720 for receiving gas outside of the volume provided by the hollow. The sabot is shown depicting an end portion 730 of a structural element that may span the width of the sabot to provide for a structural attachment for a tether. A portion of a tether 740 is shown extending from the hollow of the sabot.

FIG. 8 is a top view of an exemplary tethered sabot 700 embodiment. The structural element 810 may be a rod, and may span the width of the sabot 700. A loop portion 820 of the tether may engage the structural element 810. The tether 740 may be silicone prepreg, braided Kevlar.TM. where an end of the tether 740 may be tucked within the braiding of the tether 740 after looping the structural element 810 and further cured.

FIG. 9 is a cross-sectional view of the sabot 700 taken from the top view of FIG. 8 depicting the tether 740 engaging the structural element 810 within the hollow 910 of the sabot 700.

FIG. 10A illustrates a cross-sectional view of a loaded launcher 1010, such as the launcher depicted in FIGS. 1 and 2; loaded with a UAV 1020 such as the UAV depicted in FIG. 3. In this example, the launcher 1010 is shown having an optional frangible seal 1030. Two gas-generating canisters 1041, 1042 are shown disposed within the aft volume 1001 of the launcher 1010. An exemplary tethered sabot 1050 is shown disposed between the gas-generating canisters 1041, 1042 and the UAV 1020.

FIG. 10B illustrates, in the cross-sectional view of FIG. 10A, a first gas-generating canister 1041 increasing the pressure--as depicted by the smoke cloud 1002--within the volume 1001 between the inner aft wall 1011 of the launcher 1010 and the sabot 1050. The tether 1060 may be attached to the inner base wall 1013 via a tether reel or winding element 1014. Relative to FIG. 10A, the sabot 1050 is shown displaced along the launch tube--in this example a right parallelepiped volume--and moving with it the UAV 1020. The UAV is shown breaking the frangible seal 1030 and beginning to exit the launcher 1010.

FIG. 10C illustrates, in the cross-sectional view of FIG. 10A, the second gas-generating canister 1042 increasing, or sustaining, the pressure (as depicted by the second smoke cloud 1003) within the volume between the inner aft wall 1012 of the launcher 1010 and the sabot 1050. The sabot 1050 is shown displaced further along the launch tube, the tether 1060 is shown in a payout length, and, moved with the sabot 1050, the UAV 1020 is shown substantially outside of the launcher.

FIG. 10D illustrates, in the cross-sectional view of FIG. 10A, the sabot 1050 fully displaced within the launch tube, constrained from further travel by the tether 1060, and retaining the gas within the launcher volume.

FIG. 10E illustrates, in the cross-sectional view of FIG. 10A, the sabot 1050 fully displaced within the launch tube, constrained from further travel by the tether 1060, and retaining the gas within the launcher volume and allowing the seeping 1090 of gas from the launcher volume into the surrounding atmosphere.

FIG. 11A depicts, a cross-sectional view of the distal, an unsealed, end of a lunch tube 1100, as the sabot 1050 approaches full payout as depicted in FIG. 10D. In some embodiments using hot or warm gas generators, the sabot 1050 travels approximately no further than the location depicted in FIG. 11A, and a seepage of gas to atmosphere is around the sabot as the sabot may shrink in a cooling cycle from having been heated by the gas. In some embodiments using warm or cool gas generators, the sabot 1050 may travel to partially extend from the rim 1120 of the launcher (FIG. 11B) where gas may seep 1110 from the side depression 720 once the sabot lip 701 has cleared the launcher rim 1120. By retaining the sabot 1050 via the tether 1060, the launcher retains, for a brief period, a substantial portion of the pressure waves, i.e., the report, and heat produced by rapid gas generation. Post-launch, the launcher diffuses the pressure from the launcher via seepage about the sabot 1050.

In some embodiments, the sabot 1050 may expand out to contact the inner wall or walls of the launcher due to the pressure exerted on the interior of the sabot 1050 by the gas from the gas generators. This expansion can cause, or at least facilitate, the formation of a seal between the sabot 1050 and the inner wall or walls and in doing so prevent or limit the passage of gas around the sabot 1050 during its movement along the tube. In certain embodiments, the sabot may be configured to form gaps between the sabot and the inner wall or inner walls of the launcher. The size of such gaps may be set to provide a desired amount of gas leakage. In some embodiments, the sabot 1050 may be sized to allow enough gas leakage to prevent the launcher from becoming too hot from containing the launch gases such that the structural integrity of the launcher is compromised or breached. Accordingly, sabot 1050 embodiments may be sized to limit gas leakage to limit the sound propagation of the sonic waves generated during the launch process.

FIG. 12A depicts, in a bottom-side perspective view, an exemplary UAV in a pre-launch state 1200, i.e., with its wing 1210 and tail surfaces 1220 folded beneath the fuselage of the vehicle. Also shown is a propeller hub 1230 about which a propeller may be rotatably mounted. The air vehicle may include a radio frequency (RF) antenna 1231 conformal with or extending from the vehicle. Whether the tube volume is a right cylinder, a right parallelepiped, or some other shape, the cross-section or cross-sections of the UAV may be insufficient to maintain an air-tight fit between the vehicle and the inner walls of the launcher. Accordingly, for launches based on gas pressure, a sabot may be disposed between the gas source and the UAV. FIG. 12B depicts an exemplary UAV in a launched state 1201 with its airfoils 1210, 1220 deployed and its pusher propeller 1232 rotating.

FIG. 13 is a side elevational view of the air vehicle 1300 embodiment loaded into a forward portion of a launcher 1310. The aft portion of the launcher 1320 is shown having a pair of gas-generating canisters 1331, 1332 and may include an RF antenna 1333 and receiver unit 1334, and a power source 1336, such as a battery for powering the launcher. In some embodiments the power source 1336 can also power the UAV 1300 while it is in the launcher 1310, allowing for maximum battery life for the UAV's battery after leaving the launcher 1310. Balsawood and epoxy prepreg Kelvar.TM. are examples of structural elements having high RF permeability. Accordingly, RF antenna and receiver elements of the UAV and/or RF antenna and receiver elements of the launch propulsion unit may receive RF commands from a command node with negligible signal attenuation due to the launcher structure.

FIG. 14 depicts an exemplary functional block diagram of the UAV processing and guidance and control subsystem 1400 where the guidance sensor 1414 provides information about the external environment pertaining to seeking processing of a seeker processing 1420. A guidance sensor 1414, and more generally, a guidance sensor suite, may include a passive and/or active radar subsystem, an infrared detection subsystem, an infrared imaging subsystem, a visible light imaging subsystem such as a video camera-based subsystem, an ultraviolet light detection subsystem, and combinations thereof. The seeker processing 1420 may include both image processing and target tracking processing, and target designation or re-designation input 1421 that may be received from an uplink receiver 1435 and/or as an output of a guidance process 1430. The image processing and/or target tracking information 1422 may be transmitted via a downlink transmitter 1423, which may be a part of an uplink/downlink transceiver. The guidance processor 1430, in executing instructions for guidance processing, may take in the target information 1424 from the seeker processing 1420, and UAV flight status information such as position, velocity and attitude from the GPS receiver 1431, and gyroscopes and accelerometers 1432, if any. Once in flight, the guidance processor 1430, to receive reconnaissance waypoints and/or surveillance optimizing trajectories, may reference a memory store 1433. For system embodiments, the guidance process 1430 may receive, by way of an external data port 1434, e.g., during a pre-launch phase, or by way of an uplink receiver 1435, e.g., during a post-launch phase, receive and/or upload reconnaissance waypoints and/or surveillance optimizing trajectories. The guidance processor 1430, as part of executing instructions for determining flight path, a trajectory, or a course steering angle and direction, may reference the waypoint and/or surveillance optimizing trajectory information, particularly when not in a terminal homing mode. The guidance processor 1430 may receive a command via an uplink receiver 1435 to set an initial post-launch mode or flight plan. The uplink receiver 1435 may receive commands, target data, and or flight plan information from a communications node while the UAV is in a pre-launch state.

An example of a terminal homing mode may be proportional navigation with a gravity bias for strike sub-modes of the terminal homing mode, and an acceleration bias for aerial intercept sub-modes of the terminal homing mode. The guidance processing 1430 and autopilot processing 1440 may execute instructions to effect a bank-to-turn guidance, for example, in an elevon embodiment, to redirect the air vehicle by re-orienting its velocity vector. For example, one or more control surfaces may be re-oriented via one or more control surface actuators 1450 causing forces and torques to reorient the air vehicle and the portion of its linear acceleration that is orthogonal to its velocity vector. The portion of the linear acceleration of the air vehicle that is along the velocity vector is greatly affected by aerodynamic drag, and the linear acceleration may be increased via a motor processor 1460 and a propeller motor 1470. For embodiments with full three-axis control, additional control topologies may be implemented including skid-to-turn and other proportion-integral-differential guidance and control processing architectures as well. The seeker processing 1420, guidance processing 1430, motor processing 1460, and/or autopilot processing 1440 may be executed by a single microprocessor having addressable memory and/or the processing may be distributed to two or more microprocessors in distributed communication, e.g., via a data bus.

FIG. 15 is a top-level system architecture of a system 1500 embodiment. Ground vehicles 1501, aircraft 1502, spacecraft 1503, airborne surveillance or airborne communication nodes 1504, or ground, human-portable, communication nodes 1505 may transmit command signals via an RF link 1511-1515 to a launcher 1520 embodiment, that may be, for example, the embodiment depicted in FIG. 13. In some embodiments, the UAV, in a pre-launch state, may output along an RF link 1511-1515 to a requesting node 1501-1505, status information, e.g., battery levels, and the results of self-diagnostics. Launcher embodiments provide for a self-contained RF node via the UAV contained in the launcher. For example, the UAV may be placed in a standby mode, and remain responsive to a received RF signal that may command a full power-up, and thereafter the UAV in the launcher may be ready to be committed to launch--e.g., by an RF command of an offsite command node. The self-contained launcher-UAV may be deployed and left at a prospective launch site for a protracted period of time, and thereafter may be powered up and launched responsive to one or more command signals from an offsite or otherwise remote command node.

It is contemplated that various combinations and/or sub-combinations of the specific features and aspects of the above embodiments may be made and still fall within the scope of the invention. Accordingly, it should be understood that various features and aspects of the disclosed embodiments may be combined with or substituted for one another in order to form varying modes of the disclosed invention. Further it is intended that the scope of the present invention herein disclosed by way of examples should not be limited by the particular disclosed embodiments described above.

* * * * *

Патент США №

Автор(ы)

Дата выдачи