Aircraft flight envelope protection and recovery autopilot
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/16
G05D-001/00
B64D-045/00
B64C-013/18
G08G-005/00
출원번호
US-0470776
(2017-03-27)
등록번호
US-10228692
(2019-03-12)
발명자
/ 주소
Prosser, Kevin
출원인 / 주소
Gulfstream Aerospace Corporation
대리인 / 주소
LKGlobal | Lorenz & Kopf, LLP
인용정보
피인용 횟수 :
0인용 특허 :
106
초록▼
Systems and aircraft are provided. An avionics system for an aircraft includes: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition; a trajectory flight condition module configured to estimate a modeled flight condition of the
Systems and aircraft are provided. An avionics system for an aircraft includes: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition; a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path; a limit comparison module configured to determine whether the modeled flight condition violates aircraft limits; and a violation indicator module configured to generate an indication of impending violation.
대표청구항▼
1. An avionics system for an aircraft, the avionics system comprising: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft a
1. An avionics system for an aircraft, the avionics system comprising: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path, wherein the trajectory flight condition module comprises: a vertical velocity module configured to calculate a vertical velocity of the aircraft on the potential aircraft path;an energy state module configured to calculate an energy state of the aircraft on the potential aircraft path; andan airspeed prediction module configured to estimate an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit; anda violation indicator module configured to generate an indication of impending violation. 2. The avionics system of claim 1, wherein the energy state module is further configured to calculate the energy state based on a rate of climb of the aircraft at full power and on a rate of descent of the aircraft at idle power. 3. The avionics system of claim 2, wherein the energy state module is further configured to calculate the energy state based on a current power setting of the aircraft, a current power capability of the aircraft, a speedbrake position on the aircraft, a landing gear setting, a flap setting, and an engine health of the aircraft. 4. An avionics system for an aircraft, the avionics system comprising: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path;a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit;a violation indicator module configured to generate an indication of impending violation; anda potential path generation module configured to generate a plurality of trajectories from which the trajectory selection module selects the potential aircraft path, wherein the trajectory selection module is configured to select a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path. 5. The avionics system of claim 4, wherein the potential path generation module is further configured to generate the plurality of trajectories to cover at least six different directions for a potential escape recovery. 6. The avionics system of claim 4, wherein the potential path generation module is further configured to generate a landing path of the plurality of trajectories in response to a potential landing indicator, wherein the limit comparison module is configured to determine whether the aircraft will violate the aircraft limit by following the landing path. 7. The avionics system of claim 6, further comprising a recovery autopilot configured to guide the aircraft along the potential aircraft path in response to the potential aircraft path being a last trajectory of the plurality of trajectories to lack a violation indication. 8. The avionics system of claim 1, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit. 9. The avionics system of claim 1, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a capability limit as the aircraft limit. 10. The avionics system of claim 1, further comprising a terrain conflict module configured to determine whether the potential aircraft path indicates a terrain conflict, and wherein the violation indication module is further configured to generate the indication of impending violation based on the terrain conflict. 11. An aircraft comprising: a sensor system configured to provide aircraft flight condition data;an actuator system configured to manipulate control surfaces of the aircraft; anda control system comprising: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path, wherein the trajectory flight condition module comprises: a vertical velocity module configured to calculate a vertical velocity of the aircraft on the potential aircraft path;an energy state module configured to calculate an energy state of the aircraft on the potential aircraft path; andan airspeed prediction module configured to estimate an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit; anda violation indicator module configured to generate an indication of impending violation. 12. The aircraft of claim 11, wherein the energy state module is further configured to calculate the energy state based on a rate of climb of the aircraft at full power and on a rate of descent of the aircraft at idle power. 13. The aircraft of claim 12, wherein the energy state module is further configured to calculate the energy state based on a current power setting of the aircraft, a current power capability of the aircraft, a speedbrake position on the aircraft, a landing gear setting, a flap setting, and an engine health of the aircraft. 14. An aircraft comprising: a sensor system configured to provide aircraft flight condition data;an actuator system configured to manipulate control surfaces of the aircraft; anda control system comprising: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path;a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit;a violation indicator module configured to generate an indication of impending violation; anda potential path generation module configured to generate a plurality of trajectories from which the trajectory selection module selects the potential aircraft path, wherein the trajectory selection module is configured to select a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path. 15. The aircraft of claim 14, wherein the potential path generation module is further configured to generate the plurality of trajectories to cover at least six different directions for a potential escape recovery. 16. The aircraft of claim 14, wherein the potential path generation module is further configured to generate a landing path of the plurality of trajectories in response to a potential landing indicator, wherein the limit comparison module is configured to determine whether the aircraft will violate the aircraft limit by following the landing path. 17. The aircraft of claim 16, wherein the control system further comprises a recovery autopilot configured to guide the aircraft along the potential aircraft path in response to the potential aircraft path being a last trajectory of the plurality of trajectories to lack a violation indication. 18. The aircraft of claim 11, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit. 19. The aircraft of claim 14, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit. 20. The avionics system of claim 4, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit. 21. The avionics system of claim 4, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a capability limit as the aircraft limit. 22. The avionics system of claim 4, further comprising a terrain conflict module configured to determine whether the potential aircraft path indicates a terrain conflict, and wherein the violation indication module is further configured to generate the indication of impending violation based on the terrain conflict. 23. An avionics system for an aircraft, the avionics system comprising: means for selecting a potential aircraft path relative to a current aircraft flight condition;means for estimating a modeled flight condition of the aircraft along the potential aircraft path, wherein the means for estimating a modeled flight condition of the aircraft along the potential path comprises: means for calculating a vertical velocity of the aircraft on the potential aircraft path;means for calculating an energy state of the aircraft on the potential aircraft path; andmeans for estimating an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state; andmeans for determining whether the modeled flight condition violates an aircraft limit; andmeans for generating an indication of impending violation. 24. An avionics system for an aircraft, the avionics system comprising: means for selecting a potential aircraft path relative to a current aircraft flight condition;means for estimating a modeled flight condition of the aircraft along the potential aircraft path;means for determining whether the modeled flight condition violates an aircraft limit;means for generating an indication of impending violation; andmeans for generating a plurality of trajectories from which to select the potential aircraft path, wherein the means for generating a plurality of trajectories is configured to select a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path. 25. An aircraft comprising: means for providing aircraft flight condition data;means for manipulating control surfaces of the aircraft; andmeans for: selecting a potential aircraft path relative to a current aircraft flight condition;estimating a modeled flight condition of the aircraft along the potential aircraft path, comprising: calculating a vertical velocity of the aircraft on the potential aircraft path;calculating an energy state of the aircraft on the potential aircraft path; andestimating an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;determining whether the modeled flight condition violates an aircraft limit; andgenerating an indication of impending violation. 26. An aircraft comprising: means for providing aircraft flight condition data;means for manipulating control surfaces of the aircraft; andmeans for: selecting a potential aircraft path relative to a current aircraft flight condition;estimating a modeled flight condition of the aircraft along the potential aircraft path;determining whether the modeled flight condition violates an aircraft limit;generating an indication of impending violation; andgenerating a plurality of trajectories from which to select the potential aircraft path, wherein generating a plurality of trajectories includes selecting a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path.
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