Flight control augmentation system and method for high aspect ratio aircraft including motorglider aircraft, optionally piloted vehicles (OPVs) and unpiloted air vehicles (UAVs)
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/28
B64C-009/12
B64C-013/16
B64C-019/02
B64C-009/10
B64C-009/18
B64C-009/20
B64C-013/04
B64C-039/02
G05D-001/06
B64C-009/00
출원번호
US-0677512
(2015-04-02)
등록번호
US-10183738
(2019-01-22)
발명자
/ 주소
Arnold, Marc
출원인 / 주소
Arnold, Marc
대리인 / 주소
Lathrop Gage LLP
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor w
A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.
대표청구항▼
1. A method of augmenting controls of high aspect ratio aircraft comprising: reading a mode switch having at least a manual mode, a loiter-cruise mode, and an auto-landing mode;when the mode switch is in the manual or loiter-cruise modes, sensing a position of a spoiler control and driving both a le
1. A method of augmenting controls of high aspect ratio aircraft comprising: reading a mode switch having at least a manual mode, a loiter-cruise mode, and an auto-landing mode;when the mode switch is in the manual or loiter-cruise modes, sensing a position of a spoiler control and driving both a left and a right spoiler servo to position left and right spoilers at a symmetrical position determined by the spoiler control;when the mode switch is in the auto-landing mode, configuring the left spoiler servo to a left spoiler position dependent on aileron and throttle position, and the right spoiler servo to a right spoiler position dependent on aileron and throttle position, the left and right spoiler positions differing whenever the aileron position is not centered, and an average of the left and right spoiler positions being an average spoiler position representing more fully deployed left and right spoilers when the throttle position is at a low-power setting than an average spoiler position when the throttle position is at a high-power setting. 2. The method of claim 1, further comprising: when the mode switch is in the auto-landing mode, configuring flap position according to a function of airspeed as appropriate for landing. 3. The method of claim 1, further comprising: when the mode switch is in the auto-landing mode, driving a flap servo to position flaps in a flaps-up position and both the right and left spoiler servos to a fully deployed position when a lift dump switch is activated, a squat switch senses ground contact, and the throttle position is at a low-power setting. 4. The method of claim 1, wherein the mode switch has an auto-ground position, and wherein, when the mode switch is in the auto-ground position: when a squat switch senses ground contact and a flap control switch is in a particular position, automatically configuring a flap servo to raise flaps to a low-lift position suitable for ground operations; andwhen the squat switch senses ground contact and groundspeed is less than a maximum taxi speed, driving both left and right spoiler servos to a fully-deployed position. 5. The method of claim 1 wherein the mode switch has an auto-takeoff position, and when the mode switch is in the auto-takeoff position: if a flap control switch is set to a particular position, configuring a flap servo to position flaps at a minimum-lift position so long as a squat switch detects ground contact and airspeed remains below a minimum takeoff airspeed threshold, then upon the squat switch detecting an absence of ground contact and airspeed above the minimum takeoff airspeed, configuring the flap servo to position the flaps at a low-drag, high-lift, configuration; andif the flap control switch is set to any other position, configuring the flap servo to position the flaps at a configuration determined by the flap control switch; andmonitoring throttle position, and if the throttle is positioned at idle, a Lift Dump switch is activated, and the squat switch detects ground contact, using the flap servo to position flaps at a minimum lift setting and using the left and right spoiler drivers to deploy the left and right spoilers to a minimum lift position. 6. The method of claim 5, wherein the mode switch has an auto-ground position, and wherein, when the mode switch is in the auto-ground position: when the squat switch senses ground contact and the flap control switch is in a particular predetermined position, configuring the flap servo to raise flaps to a low-lift position suitable for ground operations; andwhen the squat switch sense ground contact and groundspeed is less than a maximum taxi speed, driving both left and right spoiler servos to a fully-deployed position. 7. The method of claim 5, wherein the mode switch has an Auto-Max Endurance position, and wherein the method further comprises: when the mode switch is in the auto-max endurance position, read airspeed and/or angle of attack, determining an optimum flap setting therefrom, and, if the flap control switch is set to a particular position, configuring the flap servo to position the flaps at the optimum flap setting;when the mode switch is in the auto-max endurance position, determining an optimum power setting, comparing throttle position to the optimum power setting, and providing throttle adjustment guidance to a pilot when the throttle power position is not at the optimum setting; andwhen the mode switch is in the auto-max endurance position, using the left and right spoiler servo drivers to position the left and right spoilers at a fully retracted position unless commanded otherwise by a position of a spoiler switch, whereupon the spoiler servo drivers are configured to deploy both left and right spoilers evenly and sound a warning horn if retractable landing gear is not down and locked when flaps and the left and right spoilers are detected as being in landing configuration. 8. The method of claim 1, wherein the mode switch has an Auto-Max Endurance position, and wherein the method further comprises: when the mode switch is in the auto-max endurance position, read airspeed and/or angle of attack, determining an optimum flap setting therefrom, and, if a flap control switch is set to a particular position, configuring a flap servo driver to position the flaps at the optimum flap setting;when the mode switch is in the auto-max endurance position, determining an optimum power setting, comparing throttle position to the optimum power setting, and providing throttle adjustment guidance to a pilot when the throttle power position is not at the optimum power setting; andwhen the mode switch is in the auto-max endurance position, using the spoiler servo drivers to position the left and right spoilers at a fully retracted position unless commanded otherwise by a position of a spoiler switch, whereupon the spoiler servos drivers are configured to deploy left and right spoilers evenly and sound a warning horn if retractable landing gear is not down and locked when flaps and the left and right spoilers are detected as being in landing configuration. 9. The method of claim 1, wherein the mode switch has an auto-ground position, and wherein, when the mode switch is in the auto-ground position: when a squat switch senses ground contact and a flap control switch is in a particular predetermined position, configuring a flap servo to raise flaps to a low-lift position suitable for ground operations; andwhen the squat switch sense ground contact and groundspeed is less than a maximum taxi speed, driving both left and right spoiler servos to a fully-deployed position.
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이 특허에 인용된 특허 (3)
Buus, Henning; MacFie, Thomas D.; Justad, Odd, Electric command spoiler system.
Everett, Michael Louis; Everett, Louis Jackson; Ruiz, Jr., Mario, Method and apparatus for automatically controlling aircraft flight control trim systems.
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