A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the re
A system and method for controlling a deceleration profile of an aircraft, includes a processor and memory that receives a signal indicative of a deceleration command; receives signals indicative of a sensed velocity and a commanded heading rate; determines a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate; determines an estimated deceleration command as a function of the commanded velocity; and determines an actual deceleration command in response to the determining of the estimated deceleration command.
대표청구항▼
1. A method for controlling a deceleration profile of an aircraft, comprising: determining the deceleration profile to obtain a hover condition at a commanded location; andadjusting the deceleration profile in a continuous manner by manual input from a pilot, wherein adjusting comprises: receiving,
1. A method for controlling a deceleration profile of an aircraft, comprising: determining the deceleration profile to obtain a hover condition at a commanded location; andadjusting the deceleration profile in a continuous manner by manual input from a pilot, wherein adjusting comprises: receiving, with a processor, a signal indicative of a deceleration command;receiving with the processor, signals indicative of a sensed velocity and a commanded heading rate;determining, with the processor, a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate;determining, with the processor, an estimated deceleration command as a function of the commanded velocity; anddetermining, with the processor, an actual deceleration command in response to the determining of the estimated deceleration command. 2. The method of claim 1, wherein the receiving of the deceleration command further comprises receiving longitudinal and lateral deceleration commands. 3. The method of claim 1, wherein the determining of the commanded velocity further comprises determining a commanded longitudinal velocity and a commanded lateral velocity. 4. The method of claim 3, further comprising determining a longitudinal velocity error signal indicative of a difference between the commanded longitudinal velocity and a sensed longitudinal velocity. 5. The method of claim 4, further comprising determining a longitudinal commanded gain ratio as a function of the longitudinal velocity error signal and a total velocity magnitude. 6. The method of claim 5, further comprising determining a lateral commanded gain ratio as a function of the lateral velocity error signal and a total velocity magnitude. 7. The method of claim 6, further comprising determining the estimated deceleration command as a function of the total velocity magnitude. 8. The method of claim 3, further comprising determining a lateral velocity error signal indicative of a difference between the commanded lateral velocity and a sensed lateral velocity. 9. The method of claim 1, further comprising determining a commanded acceleration in response to the receiving of the deceleration command. 10. The method of claim 9, further comprising determining a second error value indicative of a difference between the commanded acceleration and a sensed acceleration. 11. The method of claim 1, further comprising determining a Translational Rate Command response wherein controller deflection correlates to steady state velocity. 12. A system for controlling a deceleration profile of an aircraft, comprising a propeller comprising a plurality of blades, wherein the propeller is associated with a sensor;a processor; andmemory having instructions stored thereon that, when executed by the processor, cause the system to: determine the deceleration profile to obtain a hover condition at a commanded location, wherein the deceleration profile is adjustable in a continuous manner by manual input from a pilot;receive a signal indicative of a deceleration command;receive signals indicative of a sensed velocity and a commanded heading rate;determine a commanded velocity in response to the receiving of the deceleration command and the commanded heading rate;determine an estimated deceleration command as a function of the commanded velocity; anddetermine an actual deceleration command in response to the determining of the estimated deceleration command. 13. The system of claim 12, wherein the processor is configured to receive longitudinal and lateral deceleration commands. 14. The system of claim 12, wherein the processor is configured to determine a commanded longitudinal velocity and a commanded lateral velocity. 15. The system of claim 14, wherein the processor is configured to determine a longitudinal velocity error signal indicative of a difference between the commanded longitudinal velocity and a sensed longitudinal velocity. 16. The system of claim 15, wherein the processor is configured to determine a longitudinal commanded gain ratio as a function of the longitudinal velocity error signal and a total velocity magnitude. 17. The system of claim 14, wherein the processor is configured to determine a lateral velocity error signal indicative of a difference between the commanded lateral velocity and a sensed lateral velocity. 18. The system of claim 17, wherein the processor is configured to determine a lateral commanded gain ratio as a function of the lateral velocity error signal and a total velocity magnitude. 19. The system of claim 12, wherein the processor is configured to determine a commanded acceleration in response to the receiving of the deceleration command. 20. The system of claim 19, wherein the processor is configured to determine a second error value indicative of a difference between the commanded acceleration and a sensed acceleration.
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이 특허에 인용된 특허 (4)
Skutecki Edmund R. (Glendale AZ), Approach to hover control system for helicopters.
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