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Патент США №	7469863
Автор(ы)	Speer
Дата выдачи	30 декабря 2008 г.

Systems and methods for automatically and semiautomatically controlling aircraft refueling

РЕФЕРАТ

Aerial refueling systems and associated methods are disclosed. A system in accordance with one embodiment of the invention includes an operator input device configured to receive operator inputs and direct a first input signal corresponding to a target position for an aerial refueling device. A sensor can be positioned to detect a location of at least one of the aerial refueling device and a receiver aircraft, and can be configured to direct a second input signal. A controller can be operatively coupled to the operator input device and the sensor to receive the first and second input signals and direct a command signal to adjust the position of the aerial refueling device in response to both the first and second input signals, unless either or both of the input signals are absent or below a threshold value. Accordingly, the system can respond to both automatically generated sensor data and data input by an operator. A fully automated version of the system can be installed on an unmanned aircraft having additional capabilities, for example, electronic surveillance and/or jamming capabilities.

Авторы:	Thomas E. Speer (Seattle, WA)
Заявитель:	The Boeing Company (Chicago, IL)
ID семейства патентов	36499375
Номер заявки:	11/090,347
Дата регистрации:	24 марта 2005 г.

Класс патентной классификации США:	244/135A
Класс совместной патентной классификации:	B64D 39/00 (20130101)
Класс международной патентной классификации (МПК):	B64D 39/00 (20060101)
Область поиска:	;244/135A

Использованные источники

[Referenced By]

Патентные документы США


724675	April 1903	Decker
2091916	August 1937	Evans
2213680	September 1940	Share
2414509	January 1947	Andre
2453553	November 1948	Tansley
2475635	July 1949	Parsons
2552991	May 1951	McWhorter
2668066	February 1954	Stadelhofer
2670913	March 1954	Castor et al.
2712831	July 1955	Day
2859002	November 1958	Leisy
2875787	March 1959	Evans
2879017	March 1959	Smith
2919937	January 1960	Dovey
2953332	September 1960	Cobham et al.
2954190	September 1960	Le Clair
2960295	November 1960	Schulz
2967684	January 1961	Knecht
2973171	February 1961	Ward et al.
3063470	November 1962	Forster
3091419	May 1963	Mosher
3103234	September 1963	Washburn
3206232	September 1965	Gleason
3680311	August 1972	Harbonn et al.
3747873	July 1973	Layer et al.
3836117	September 1974	Panicali
3917196	November 1975	Pond et al.
3928903	December 1975	Richardson et al
4044834	August 1977	Perkins
4072283	February 1978	Weiland
4088154	May 1978	Patton et al.
4095761	June 1978	Anderson et al.
4119294	October 1978	Schnorrenberg et al.
4129270	December 1978	Robinson et al.
4149739	April 1979	Morris
4150803	April 1979	Fernandez
4231536	November 1980	Ishimitsu et al.
4236686	December 1980	Barthelme et al.
4327784	May 1982	Denniston
4408943	October 1983	McTamaney et al.
4438793	March 1984	Brown
4471809	September 1984	Thomsen et al.
4477040	October 1984	Karanik
4534384	August 1985	Graham et al.
4540144	September 1985	Perrella
4586683	May 1986	Kerker
4612089	September 1986	Hauptmann
4665936	May 1987	Furrer et al.
H297	July 1987	Schultz
4717099	January 1988	Hubbard
4796838	January 1989	Yamamoto
4883102	November 1989	Gabrielyan et al.
4929000	May 1990	Annestedt, Sr.
5131438	July 1992	Loucks
5141178	August 1992	Alden et al.
5255877	October 1993	Lindgren et al.
5393015	February 1995	Piasecki
5427333	June 1995	Kirkland
5449203	September 1995	Sharp
5449204	September 1995	Greene et al.
5499784	March 1996	Crabere et al.
5530650	June 1996	Biferno et al.
5539624	July 1996	Dougherty
5573206	November 1996	Ward
5785276	July 1998	Ruzicka
5810292	September 1998	Garcia, Jr. et al.
5904729	May 1999	Ruzicka
5906336	May 1999	Eckstein
5921294	July 1999	Greenhalgh et al.
5996939	December 1999	Higgs et al.
6044242	March 2000	Kakiwaki et al.
6076555	June 2000	Hettinger et al.
6119981	September 2000	Young et al.
6145788	November 2000	Mouskis et al.
6302448	October 2001	Van Der Meer et al.
6305336	October 2001	Hara et al.
6324295	November 2001	Valery et al.
6326873	December 2001	Faria et al.
6375123	April 2002	Greenhalgh et al.
6408429	June 2002	Marrion et al.
6428054	August 2002	Zappa et al.
6454212	September 2002	Bartov
6464173	October 2002	Bandak
6467725	October 2002	Coles et al.
6588465	July 2003	Kirkland et al.
6598830	July 2003	Ambrose et al.
6601800	August 2003	Ollar
6604711	August 2003	Sinha et al.
6651933	November 2003	von Thal et al.
6655136	December 2003	Holt et al.
6658329	December 2003	Howard et al.
6669145	December 2003	Green
6676379	January 2004	Eccles et al.
6752357	June 2004	Thal et al.
6779758	August 2004	Vu et al.
6796527	September 2004	Munoz et al.
6819982	November 2004	Doane
6824105	November 2004	Edwards et al.
6832743	December 2004	Schneider et al.
6837462	January 2005	von Thal et al.
6848720	February 2005	Carns et al.
7108015	September 2006	Lombari et al.
2003/0038214	February 2003	Bartov
2003/0097658	May 2003	Richards
2003/0115863	June 2003	Holt et al.
2003/0136874	July 2003	Gjerdrum
2003/0218097	November 2003	Vu et al.
2004/0129865	July 2004	Doane
2004/0195909	October 2004	Hamzeh et al.
2005/0055143	March 2005	Doane
2006/0000949	January 2006	Schroeder
2006/0011782	January 2006	Schroeder
2006/0038076	February 2006	Schroeder
2006/0071475	April 2006	James
2006/0278759	December 2006	Carns
2006/0278763	December 2006	Carns et al.
2006/0284018	December 2006	Carns
2007/0069071	March 2007	Near et al.

Зарубежные патентные документы


2744674	Apr 1979	DE
29901583	May 1999	DE
10013751	Oct 2001	DE
0236584	Sep 1987	EP
0780292	Jun 1997	EP
0807577	Nov 1997	EP
1094001	Apr 2001	EP
1361156	Nov 2003	EP
1447605	Aug 2004	EP
1695911	Aug 2006	EP
555984	Sep 1943	GB
2237251	May 1991	GB
2257458	Jan 1993	GB
2373488	Sep 2002	GB
2 405 384	Mar 2005	GB
128459	May 2003	IL
2111154	May 1998	RU
2140381	Oct 1999	RU
2142897	Dec 1999	RU
673798	Jul 1979	SU
953345	Aug 1982	SU
386966	Apr 2000	TW
WO-85/02003	May 1985	WO
WO-91/06471	May 1991	WO
WO-97/33792	Sep 1997	WO
WO-98/07623	Feb 1998	WO
WO-98/39208	Sep 1998	WO
WO-98/54053	Dec 1998	WO
WO-02/24529	Mar 2002	WO
WO-02/055385	Jul 2002	WO
WO-02/76826	Oct 2002	WO
WO-03/102509	Dec 2003	WO

Другие источники

http://www.aviationtoday.com/print/av/categories/military/669.html, Smart Tanker. cited by examiner .
Keller, George R., "Hydraulic System Analysis", pp. 40-41, 1985, Hydraulics & Pheumatics, Cleveland, Ohio. cited by other .
U.S. Appl. No. 11/067,331, filed Feb. 25, 2005, Crangle. cited by other .
U.S. Appl. No. 11/078,210, filed Mar. 11, 2005, Smith. cited by other .
U.S. Appl. No. 11/157,245, filed Jun. 20, 2005, Takacs et al. cited by other .
U.S. Appl. No. 11/217,696, filed Sep. 1, 2005, Schuster et al. cited by other .
U.S. Appl. No. 11/258,819, filed Oct. 26, 2005, Cutler et al. cited by other .
Flug Revue, "Airbus (Air Tanker) A330-200 Tanker," Jan. 26, 2004; www.flug-revue.rotor.com/FRTypen/FRA3302T.htm; MotorpPresse Stuttgart, Bonn, German (5 pgs). cited by other .
Thales Avionics Ltd., "Air Tanker Bids for Future Strategic Tanker Aircraft," Jul. 3, 2001; www.thalesavionics.net/press/pr43.html; (3 pgs). cited by other .
Wikipedia, the free encyclopedia, "Electroactive Polymers," http://en.wikipedia.org/wiki/Electroactive.sub.--polymers, last update Feb. 27, 2005 (2 pages). cited by other .
IFFC/Firefly III F-15; http://home.att.net/jbaugher1/fl.sub.--17.html; accessed Jul. 17, 2008; Mar. 4, 2000; 1 pg. cited by other .
Kopp, Carlo, "Integrated Flight and Fire Control", Sep. 1982; Australian Aviation; p. 66-68. cited by other .
Cord, Thomas J., "IFFC Flying Qualities Simulation", (date unknown); Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, Ohio; pp. 296-300. cited by other.

Главный эксперт: Collins; Timothy D
Уполномоченный, доверенный или фирма: Perkins Coie LLP

ФОРМУЛА ИЗОБРЕТЕНИЯ

I claim:

1. An aerial refueling system, comprising: an operator input device configured to receive operator inputs and direct a first input signal corresponding to a target position for an aerial refueling device; a sensor positioned to detect a location of a receiver aircraft, the sensor being configured to direct a second input signal corresponding to a location of the receiver aircraft; and a controller operatively coupled to the operator input device and the sensor to receive both the first and second input signals, the controller being configured to direct a command signal to adjust the position of the aerial refueling device in response to both the first and second input signals.

2. The system of claim 1 wherein the controller is configured to sum signals based at least in part on the first and second signals and direct the command signal based on the sum.

3. The system of claim 1 wherein the controller is configured to sum signals based at least in part on portions of the first and second signals and corresponding to motion along a first axis independently of signals based at least in part on portions of the first and second signals corresponding to motion along a second axis, wherein the second axis is generally orthogonal to the first axis.

4. The system of claim 1 wherein the controller includes a limiter configured to limit the effect of the second input signal when the second input signal corresponds to a target motion greater than a threshold amount.

5. The system of claim 1 wherein the controller is configured to continually receive input signals from both the operator input device and the sensor.

6. The system of claim 1 wherein the controller is configured to direct a command signal based only on the first input signal when the second input signal is absent or below a threshold value, and wherein the controller is configured to direct a command signal based only on the second input signal when the first input signal is absent or below a threshold value.

7. The system of claim 1 wherein at least one of the sensor and the controller is configured to detect a difference in position between the aerial refueling device and the receiver aircraft, and wherein the controller is configured to direct a command signal that moves the aerial refueling device in a direction that reduces the difference in position.

8. The system of claim 1, further comprising an actuator coupled to the controller and the operator input device, the actuator being configured to move the operator input device in a manner that is consistent with the command signal.

9. The system of claim 1 wherein the sensor includes a photosensitive sensor coupled to a target recognition device.

10. The system of claim 1, further comprising the aerial refueling device, and wherein the aerial refueling device includes a deployable boom.

11. The system of claim 1, further comprising: the aerial refueling device; a tanker aircraft carrying the aerial refueling device; and a receiver aircraft positioned proximate to the tanker aircraft.

12. The system of claim 11 wherein the receiver aircraft is an unmanned air vehicle.

13. The system of claim 1, further comprising: the aerial refueling device, and wherein the aerial refueling device includes a generally rigid boom that is movable between a stowed position and a deployed position; and a tanker aircraft carrying the boom, the controller, the operator input device, and the sensor; wherein the sensor includes a plurality of cameras coupled to a target recognition device, the target recognition device including a computer-readable medium containing instructions to recognize at least portions of the boom and a receiver aircraft.

14. The system of claim 1 wherein the controller includes a computer readable medium containing instructions to direct a change in position of the aerial refueling device.

15. An aerial refueling system, comprising: input means for receiving operator inputs and directing a first input signal corresponding to a target position for an aerial refueling device; sensor means for detecting a location of at least one of the aerial refueling device and a receiver aircraft and directing a second input signal; and control means for controlling a position of the aerial refueling device, the control means being operatively coupled to the input means and the sensor means to receive both the first and second input signals, the control means being configured to adjust the position of the aerial refueling device in response to both the first and second input signals.

16. The system of claim 15 wherein the control means is configured to direct a command signal based only on the first input signal when the second input signal is absent or below a threshold value, and wherein the control means is configured to direct a command signal based only on the second input signal when the first input signal is absent or below a threshold value.

17. An aerial refueling system, comprising: an operator input device configured to receive operator inputs and direct a first input signal corresponding to a target position for an aerial refueling device; a sensor positioned to detect a location of a receiver aircraft, the sensor being configured to direct a second input signal corresponding to a location of the receiver aircraft; and a controller operatively coupled to the operator input device and the sensor to receive the first and second input signals, the controller being configured to direct a command signal to adjust the position of the aerial refueling device in response to both the first and second input signals unless either or both of the first and second input signals are absent or below a threshold value, wherein the controller is configured to sum signals based at least in part on the first and second signals and direct the command signal based on the sum.

18. An aerial refueling system, comprising: an operator input device configured to receive operator inputs and direct a first input signal corresponding to a target position for an aerial refueling device; a sensor positioned to detect a location of a receiver aircraft, the sensor being configured to direct a second input signal corresponding to a location of the receiver aircraft; and a controller operatively coupled to the operator input device and the sensor to receive the first and second input signals, the controller being configured to direct a command signal to adjust the position of the aerial refueling device in response to both the first and second input signals unless either or both of the first and second input signals are absent or below a threshold value, wherein the controller includes a limiter configured to limit the effect of the second input signal when the second input signal corresponds to a target motion greater than a threshold amount.

ОПИСАНИЕ

ОБЛАСТЬ ТЕХНИКИ

The present invention is directed generally toward systems and methods for automatically and semiautomatically refueling aircraft, including systems and methods that incorporate operator input and sensor input when coupling receiver aircraft to refueling devices.

УРОВЕНЬ ТЕХНИКИ

In-flight refueling (or air-to-air refueling) is an important method for extending the range of aircraft traveling long distances over areas having no feasible landing or refueling points. Although in-flight refueling is a relatively common operation, especially for military aircraft, the aircraft to be refueled (e.g., the receiver aircraft) must be precisely positioned relative to the tanker aircraft in order to provide safe engagement while the fuel is dispensed to the receiver aircraft. The requirement for precise relative spatial positioning of the two rapidly moving aircraft makes in-flight refueling a challenging operation.

There are currently two primary systems for in-flight refueling. One is a hose and drogue system, which includes a refueling hose having a drogue disposed at one end. The hose and drogue are trailed behind the tanker aircraft once the tanker aircraft is on station. The pilot of the receiver aircraft then flies the receiver aircraft to intercept and couple with the drogue for refueling. Another existing system is a boom refueling system. The boom refueling system typically includes a rigid boom extending from the tanker aircraft, with a probe and nozzle at its distal end. The boom also includes airfoils controlled by a boom operator stationed on the refueling aircraft. The airfoils allow the boom operator to actively maneuver the boom with respect to the receiver aircraft, which flies in a fixed refueling position below and aft of the tanker aircraft.

One approach to addressing the challenge associated with precisely positioning the tanker aircraft relative to the receiver aircraft is to automate the process. For example, one existing arrangement includes using cameras housed in the tanker aircraft to determine the distance between the receiver aircraft and the tip of a refueling boom carried by the tanker aircraft. The system can then be used to automatically control the position of the boom to mate with a corresponding refueling receptacle of the receiver aircraft. The system can be configured to allow the boom operator to take control of the movement of the boom, for example, if the automatic system malfunctions or if for any reason the refueling boom must be directed away from the receiver aircraft. While generally effective, this approach may not provide the optimum level of controllability in all refueling situations.

СУЩНОСТЬ

The following summary is provided for the benefit of the reader only, and does not limit the invention as set forth by the claims. The invention is directed generally toward systems and methods for automatically and/or semiautomatically refueling aircraft. A system in accordance with one aspect of the invention includes an operator input device configured to receive operator inputs and direct a first input signal corresponding to a target position for an aerial refueling device. The system can further include a sensor positioned to detect a location of at least one of the aerial refueling device and a receiver aircraft. The sensor can be configured to direct a second input signal corresponding to a location of at least one of the aerial refueling device and the receiver aircraft. The system can still further include a controller operatively coupled to the operator input device and the sensor to receive the first and second input signals. The controller can be configured to direct a command signal to adjust the position of the aerial refueling device in response to both the first and second input signals, unless either or both of the first and second input signals are absent or below a threshold value.

In particular aspects of the invention, the controller is configured to sum signals based at least in part on the first and second signals and direct the command signal based on the sum. In further particular aspects, the controller can be configured to sum portions of the first and second signals corresponding to motion along a first axis independently of portions of the first and second signals corresponding to motion along a second (e.g., orthogonal) axis.

A method in accordance with another aspect of the invention is directed to refueling an aircraft in flight. The method can include receiving a first signal from an operator input device, with the first signal corresponding to a target position for an aerial refueling device. The method can further include receiving a second input signal from a sensor, with the second input signal corresponding to the position of at least one of the aerial refueling device and a receiver aircraft. The method can still further include directing a change in the position of the aerial refueling device based on both the first and second input signals, unless at least one of the first and second input signals is absent or below a threshold value.

Still another aspect of the invention is directed to an unmanned aerial refueling system. The system can include an unmanned aircraft carrying a refueling device, and a controller configured to automatically control a position of the refueling device relative to a receiver aircraft. The system can still further include an electronic facility that is configured to be projected from the unmanned aircraft, e.g., for surveillance and/or electronic jamming. Accordingly, the system can serve as an unmanned strike support aircraft with a refueling capability.

КРАТКОЕ ОПИСАНИЕ РИСУНКОВ

FIG. 1 is a partially schematic, isometric illustration of a tanker aircraft refueling a receiver aircraft in accordance with an embodiment of the invention.

FIG. 2 is a partially schematic illustration of a system for controlling an aerial refueling device in accordance with an embodiment of the invention.

FIG. 3 is a flow diagram illustrating a method for controlling motion of an aerial refueling device in accordance with an embodiment of the invention.

FIG. 4 is a partially schematic, side elevation view of a tanker aircraft refueling a receiver aircraft in accordance with an embodiment of the invention.

FIG. 5 is a partially schematic, top isometric view of a representative receiver aircraft.

FIG. 6 is a schematic illustration of a system configured to receive sensor data and operator input for controlling a refueling boom in accordance with an embodiment of the invention.

FIGS. 7A-7C illustrate autonomous, unmanned aerial refueling aircraft configured in accordance with further embodiments of the invention.

ПОДРОБНОЕ ОПИСАНИЕ

Existing automated aerial refueling systems provide several advantages over a purely manual boom positioning arrangement. However, these systems may not be ideal in all situations. For example, these systems are typically configured to operate in one of two mutually exclusive modes: a first mode in which positioning the boom is completely automated, or a second mode in which positioning the boom is completely manual. However, these systems are unable to handle a situation in which the boom operator may wish to assist, but not take over, control of the boom.

The present disclosure describes systems for automatically refueling aircraft, including systems that receive inputs from both sensors and a human operator. Certain specific details are set forth in the following description and in FIGS. 1-7C to provide a thorough understanding of various embodiments of the invention. Well-known structures, systems and methods often associated with such systems have not been shown or described in detail to avoid unnecessarily obscuring the description of the various embodiments of the invention. In addition, those of ordinary skill in the relevant art will understand that additional embodiments of the invention may be practiced without several of the details described below.

Many embodiments of the invention described below may take the form of computer-executable instructions, including routines executed by a programmable computer. Those skilled in the relevant art will appreciate that the invention can be practiced on computer systems other than those shown and described below. The invention can be embodied in a special-purpose computer or data processor that is specifically programmed, configured or constructed to perform one or more of the computer-executable instructions described below. Accordingly, the term "computer" as generally used herein refers to any data processor and can include Internet appliances and hand-held devices (including palm-top computers, wearable computers, cellular or mobile phones, multi-processor systems, processor-based or programmable consumer electronics, network computers, mini computers and the like). Information handled by these computers can be presented at any suitable display medium, including a CRT display or LCD.

The information can also be practiced in distributed environments, where tasks or modules are performed by remote processing devices that are linked through a communications network. In a distributed computing environment, program modules or subroutines may be located in local and remote memory storage devices. Aspects of the invention described below may be stored or distributed on computer-readable media, including magnetic or optically readable or removable computer disks, as well as distributed electronically over networks. Data structures and transmissions of data particular to aspects of the invention are also encompassed within the scope of the invention.

FIG. 1 illustrates a system 160 that includes a tanker aircraft 100 in the process of refueling a receiver aircraft 110 with an aerial refueling device 120 configured in accordance with an embodiment of the invention. The tanker aircraft 100 has a fuselage 101, wings 102, and one or more engines 103 (two are shown in FIG. 1 as being carried by the wings 102). In other embodiments, the aircraft 100 can have other configurations. In a particular aspect of the embodiment shown in FIG. 1, the aerial refueling device 120 can include a refueling boom 121 having actuatable control surfaces 122. The positions of the control surfaces 122 can be adjusted to "fly" the boom 121 into engagement with the receiver aircraft 110. The position of the boom 121 can be controlled based on inputs received automatically via a sensor, as well as inputs received from a human operator. Accordingly, this arrangement can allow the operator to control the boom 121 during selected periods of time, and can allow the system 110 to automatically control the boom 121 at other times, without requiring the operator to direct the system 160 to switch back and forth between autonomous and manual control. Furthermore, the operator can control the location of the boom 121 with assistance from the automatic portion of the system 160, while allowing the operator the opportunity to override the automatic portion of the system 160 at any point. Further aspects of the manner in which the system 160 operates are described below.

FIG. 2 schematically illustrates components of the system 160 initially described above with reference to FIG. 1. The system 160 can include a controller 230 that controls the motion of the aerial refueling device 120, based on inputs received from an operator input device 250 and a sensor 240. The operator input device 250 can include a joystick 251 or other suitable manual input control device (e.g., a yoke). The sensor 240 can include an optical sensor, for example, a pair of cameras or other photosensitive detectors 241 that provide a stereoscopic image to the controller 230. The controller 230 can combine the input signals (in a manner described in greater detail below with reference to FIG. 6) and, based upon the combination of the signals, direct a command signal to the aerial refueling device 120 to change a position of the device.

In one embodiment, the aerial refueling device 120 can include the boom 121. Accordingly, the controller 230 can direct actuation of the control surfaces 122 to provide for lateral motion of the boom 121 (as indicated by arrow A) and vertical or pitch motion of the boom 121 (as indicated by arrow B). The controller 230 can also control axial actuation of a deployable boom tip 123, as indicated by arrow C.

In a particular aspect of this embodiment, the controller 230 can be coupled to an actuator 252 that is in turn coupled to the operator input device 250 to provide feedback to the operator. Accordingly, when the controller 230 directs a command signal to move the boom 121 in a particular manner, a corresponding command signal can be directed to the actuator 252 to move the operator input device 250 in a corresponding manner. As a result, an operator placing a hand very lightly on the joystick 251 will feel the joystick 251 move in a manner that tracks the motion of the boom 121, and in a manner that is commanded by the controller 230 based upon the sensor 240. If the operator places any force (e.g., greater than a threshold level of force) on the joystick 251, the operator's input can also influence the position of the boom 121. In a particular aspect of this embodiment, the rate at which the controller 230 will direct a motion of the boom 121 based on the operator's input, will vary proportionately to the force applied by the operator to the operator input device 250. Suitable operator input devices 250 for performing this function are available from MPC Products Corporation of Skokie, Ill.

FIG. 3 is a flow diagram illustrating a process 300 for directing the motion of a boom or other aerial refueling device. In process portion 302, the process 300 includes receiving a first input signal from an operator input device, and in process portion 304, the process includes receiving a second input signal from a sensor. The first input signal can correspond to a target position for the aerial refueling device, and the second signal can correspond to an actual position of the refueling device and/or the receiver aircraft. As used herein in this context, the term "position" can refer to an absolute position or a relative position. For example, position can refer to an absolute position (e.g., based on GPS data or other data) of the boom and/or receiver aircraft. In another example, position can refer to a position of the boom and/or the receiver aircraft relative to the tanker aircraft or relative to each other. In particular embodiments, position can refer to the separation distance between the boom and the receiver aircraft.

In process portion 306, the process 300 can include automatically determining an error between the actual boom position and a target boom position, based on the second input signal. The authority granted to the automatic motion control of the aerial refueling device can then be limited (process portion 308). Accordingly, process portion 308 can prevent the automatic portion of the system from overwhelming a large manual operator input. The process can then include directing the motion of the aerial refueling device to reduce the error, based on both the first and second signals (process portion 310).

In a particular embodiment, process portion 310 can include directing the motion of the aerial refueling device based on both the first and second signals, unless either or both input signals are absent or below a threshold value. For example, if the operator applies no force to the operator input device (or applies a very small force), then the system can direct the motion of the boom based entirely on the automatically determined position error value. Conversely, if the automatically determined position error value is zero (e.g., the aerial refueling device is accurately positioned for refueling), but the operator applies a force to the operator input device, the system will allow the operator to override the automatically determined position error value. The system can continuously monitor both the first and second signals so as to seamlessly transition between fully automated motion, fully manual motion and motion based on both manual and automated inputs.

FIG. 4 illustrates a partially schematic, partially cut away side view of the tanker aircraft 100 refueling the receiver aircraft 110 in accordance with an embodiment of the invention. In one aspect of this embodiment, a sensor pod 442 houses the sensor 240 (FIG. 2) at a location where the sensor 240 can detect the positions of the boom 121 and the receiver aircraft 110. Accordingly, the sensor or sensors 240 located within the sensor pod 442 can have a sensor field of view 443 that extends downwardly and aft from the sensor pod 442. The sensors within the sensor pod 442 can be configured to detect a position of at least one of the receiver aircraft 110 and the boom 121 so as to determine a position error E. For example, the position error E can be the vector distance between the tip of the boom 121 and a refueling receptacle 411 of the aircraft and can accordingly have components in multiple coordinate directions (e.g., azimuth and elevation).

FIG. 5 illustrates a receiver aircraft 510 having a configuration different than that of the aircraft 110 shown in FIG. 4, and illustrates one suitable position for a fuel receptacle 511. The fuel receptacle 511 can have a distinctive visual appearance and/or can include visual cue markings 512 that assist the sensor(s) in precisely identifying the location of the fuel receptacle 511. In one embodiment, a single sensor or pair of sensors can be used to optically determine the distance between the boom tip and the receptacle. In another embodiment, the boom (not visible in FIG. 5) can have a separate position sensor associated with it (e.g., an accelerometer and associated processor) and the position detected by the boom position sensor can be combined with the visual image of the fuel receptacle 511 to determine the distance between the boom tip and the fuel receptacle 511. Suitable systems and methods for making the position error determinations are disclosed in U.S. Pat. No. 6,752,357 and U.S. Pat. No. 5,530,650, both incorporated herein in their entireties by reference.

FIG. 6 is a schematic illustration of a system 660 configured to carry out tasks described above with reference to FIGS. 1-5. In one aspect of this embodiment, many of the functions described in connection with the system 660 can be carried out by the controller 230 described above with reference to FIG. 2. For example, the controller 230 can include a target recognition component 663 that receives sensor data 661. The target recognition component 663 can be configured to determine the location of the receiver aircraft receptacle and the tip of the refueling boom. A summing component 664 can determine a position error based on the difference between the receptacle location and the boom tip location. A limiter 665 can limit the position error signal that is based on the sensor data 661. The limiter 665 can accordingly be used to ensure that operator inputs beyond the limiter value will be sufficient to override inputs based on the sensor data 661. This arrangement can also allow the operator to manually make gross movements of the boom, while allowing automated portions of the system (e.g., based on the sensor data 661) to fine-tune the location of the boom. The automatically determined position error signal is then summed with the operator input 662 by another summing component 666, and the resultant error signal is then acted upon by a series of boom control laws 667. The output of the boom control laws 667 is one or more control effector commands 668 that direct the boom to a target location (e.g., the receptacle of the receiver aircraft) via actuators and/or other devices.

One feature of several embodiments of the systems and methods described above with reference to FIGS. 1-6 is that they can include directing the position of an aerial refueling device (e.g., a deployable boom) based on automated sensor input, as well as input from a human operator. This is unlike some conventional systems, which operate in either an automatic mode or a manual mode, but are not configured to simultaneously act on both automated sensor input information and manual input information. An advantage of this arrangement is that the manual operator can remain in the control loop at all times without affecting the ability or the system to continue providing automatically determined inputs for the motion of the boom. The operator can easily alternate between being an active or passive participant in the control loop without taking any action other than simply touching or releasing (respectively) the manual input control device. As a result, the operator can easily direct the boom away from the receiver aircraft if such an action is necessary and, once it is again appropriate for the boom to be automatically positioned close to the receiver aircraft, the operator can simply release the operator input device and allow the boom to be automatically directed to the receiver aircraft refueling receptacle.

Another advantage of the foregoing feature is that it can allow the operator and the automated sensors to simultaneously control different aspects of the motion of the refueling device. For example, the operator may wish to automatically have the boom aligned laterally with the refueling receptacle, but have the tip of the boom above the receiver aircraft (e.g., to allow the pilot of the receiver aircraft greater flexibility in positioning his aircraft, or for other reasons). Accordingly, the boom operator can apply a pitch-directed force to the input device to control the pitch of the boom, while allowing the operator input device to move laterally, thereby allowing the automated portion of the system to direct the lateral motion of the boom. In other embodiments, the motion can be divided between the operator and the automated sensor in different manners. For example, the automated sensor can be used to control both the pitch and lateral position of the boom, and the operator can control the extension or retraction of the probe tip.

Still another advantage of features of several of the foregoing embodiments is that they can be used to gradually shift from a fully manual boom operation to a fully automated boom operation. For example, during system testing, pilot training, and/or boom operator training, the operator can remain in the control loop to position the boom for as long as it takes for the operator, the tanker aircraft pilot, and the receiver aircraft pilot to become comfortable with the automated motion of the boom. The operator can gradually reduce the input he or she provides as this comfort level increases, and can ultimately oversee a completely hands-off operation, while remaining available to intervene for an emergency breakaway procedure or other acute procedure.

As described above, the foregoing system can, in some cases, be used in a fully automated manner to direct the motion of the aerial refueling device without any human intervention. Accordingly, this system can be installed on unmanned aerial refueling aircraft. Examples of such aircraft are illustrated in FIGS. 7A, 7B, and 7C. In a particular aspect of the embodiments shown in FIGS. 7A-7C, these unmanned aircraft can include not only an automatic refueling capability, but can also include other capabilities that make the aircraft suitable as unmanned strike support aircraft. Such capabilities can include antennae 704 integrated with the aircraft wings and used for air-to-ground surveillance, air-to-air surveillance, air traffic control (e.g., aircraft proximity) and/or other surveillance tasks. These aircraft can also use the additional electronic capability for other purposes, for example, to jam electronic signals from target aircraft or ground facilities. Because these capabilities are integrated with an unmanned aerial refueling tanker, the aircraft can perform surveillance tasks while being on station and available to refuel either manned aircraft or unmanned aircraft. This combination of capabilities can significantly increase the utility of the aircraft.

From the foregoing, it will be appreciated that specific embodiments of the invention have been described herein for purposes of illustration, but that various modifications may be made without deviating from the invention. For example, the signals transmitted by the sensor may include a visual indication of the receiver aircraft and/or the refueling system, or these signals can include other characteristics (e.g., the position of the boom relative to the tanker aircraft, based on input from displacement sensors). Aspects of the invention described in the context of particular embodiments may be combined or eliminated in other embodiments. For example, the refueling systems can be installed on aircraft having configurations other than those described above, and/or can be used to control aerial refueling devices other than those described above (e.g., hose and drogue devices). Further, while advantages associated with certain embodiments of the invention have been described in the context of those embodiments, other embodiments may also exhibit such advantages, and not all embodiments need necessarily exhibit such advantages to fall within the scope of the invention. Accordingly, the invention is not limited, except as by the appended claims.

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Systems and methods for automatically and semiautomatically controlling aircraft refueling

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