A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flig
A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope.
대표청구항▼
1. A method to control hovering flight of a rotary aircraft, the rotary aircraft having a longitudinal controller and a lateral controller, the method comprising: defining a first flight envelope having a first groundspeed threshold;defining a second flight envelope having a second groundspeed thres
1. A method to control hovering flight of a rotary aircraft, the rotary aircraft having a longitudinal controller and a lateral controller, the method comprising: defining a first flight envelope having a first groundspeed threshold;defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope;engaging an automatic hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope;engaging an automatic position hold with a control law position hold architecture as the aircraft enters the second flight envelope; andinterchanging the automatic hover hold and the automatic position hold as the rotary aircraft moves between the first flight envelope and the second flight envelope;wherein at least one of the engaging the automatic hover hold and the engaging an automatic position hold is performed in response to at least one of the longitudinal controller and the lateral controller being in a detent position. 2. The method of claim 1, further comprising: maneuvering the rotary aircraft within the first envelope with a translational rate command, the translational rate command being adapted to control longitudinal flight of the rotary aircraft with movement of the longitudinal controller and lateral flight of the rotary aircraft with movement of the lateral controller. 3. The method of claim 1, further comprising: disengaging the translational rate command as the aircraft groundspeed exceeds the first groundspeed threshold. 4. The method of claim 1, wherein the first groundspeed threshold is 10 knots. 5. The method of claim 1, wherein the second groundspeed threshold is 1 knot. 6. The method of claim 1, wherein engaging automatic hover flight within the first envelope is achieved when both the longitudinal controller and the lateral controller are released. 7. The method of claim 1, wherein engaging a position hold flight is achieved when both the longitudinal controller and the lateral controller are released. 8. The method of claim 1, further comprising: transitioning between a high speed envelope to the first envelope by decreasing acceleration of the rotary aircraft by moving the longitudinal controller in the aft position and then using an aft beep to trim the aircraft at a higher pitch angle;wherein the aircraft will decelerate at a constant rate and then automatically hover upon entry in the first flight envelope. 9. The method of claim 8, further comprising: fine tuning the deceleration of the aircraft with a aft beep switch operably associated with the longitudinal controller and adapted to trim the rotary aircraft at a higher pitch angle. 10. The method of claim 1, wherein the translational rate command mode engages if the movement of the lateral controller is less than a predetermined displacement value; and wherein the an attitude command mode engages if the movement of the lateral controller is greater than a predetermined displacement value. 11. The method of claim 10, wherein the predetermined displacement value is 0.4 inches. 12. The method of claim 1, further comprising: engaging the automatic hover hold in response to at least one of a detected pilot medical condition, a visual brownout indicated by a pilot, and a detected equipment failure. 13. A flight control system for a rotary aircraft, the rotary aircraft having a longitudinal controller, a lateral controller, a directional controller, and a vertical controller, the control system comprising: a longitudinal loop design having: a forward speed hold loop;a pitch attitude loop; anda pitch rate loop;wherein the forward speed hold loop automatically engages when the longitudinal controller is returned to a detent position and the aircraft groundspeed is outside a first groundspeed threshold; andwherein longitudinal maneuverability of the rotary aircraft is controlled by either the pitch attitude loop or the pitch rate loop when the longitudinal controller is out of the detent position;a lateral loop design having: a lateral speed hold loop; anda roll rate loop;wherein the lateral speed hold loop automatically engages when the lateral controller is returned to a detent position and the aircraft groundspeed is outside the first groundspeed threshold; andwherein lateral maneuverability of the rotary aircraft is controlled by either the lateral speed hold loop or the roll rate loop when the lateral controller is out of the detent position;a directional loop design having: a yaw rate command loop; anda heading hold loop;wherein the heading hold loop will be re-engaged automatically during flight in the first groundspeed threshold when the directional controller is in detent; anda vertical control loop design having: a vertical speed hold loop; andan altitude hold loop;wherein the altitude hold loop automatically engages when the vertical controller is returned to a detent position and the aircraft groundspeed is inside the first groundspeed threshold; andwherein vertical maneuverability of the rotary aircraft is controlled by the vertical speed hold loop if the vertical controller is out of the detent position. 14. The control system of claim 13, further comprising: a steady state attitude search method associated with the forward speed hold loop, the steady state attitude search method being adapted to increase a stabilization of the forward speed hold loop and a stabilization speed of the lateral speed hold loop. 15. The control system of claim 13, further comprising: a longitudinal speed beep operably associated with the longitudinal loop design. 16. The control system of claim 13, further comprising: a bank attitude loop operably associated with the roll rate loop. 17. The control system of claim 13, further comprising: a fader switch operably associated with the lateral speed hold loop and the roll rate loop, the fader switch being adapted to smooth the transition between the lateral speed hold loop and the roll rate loop. 18. The control system of claim 11, further comprising: a lateral beep switch adapted to fine-tune the rotary aircraft hover position with improved precision. 19. A method for high speed transition to hover for an aircraft, comprising: commanding a nose pitch attitude and a deceleration rate with a longitudinal controller;activating a longitudinal aft beep while continuing to hold pitch attitude with the longitudinal controller;releasing an aft longitudinal controller to hold pitch attitude;automatically decelerating the aircraft at a constant rate;defining a first flight envelope having a first groundspeed threshold; andengaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope;wherein the engaging the hover hold is initiated in response to the longitudinal controller being in a detent position. 20. The method of claim 19, further comprising: adjusting a deceleration rate of the aircraft by changing the pitch attitude with a longitudinal beep switch.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (9)
Caldwell Donald G. (Mesa AZ) Osder Stephen S. (Scottsdale AZ), Automated helicopter flight control system.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.