Combined airspeed and inertial data for rotorcraft longitudinal control
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G01P-005/00
B64C-027/26
G01P-005/16
G05D-001/10
B64C-027/06
B64C-027/82
B64D-043/02
B64C-017/06
G01C-021/18
B64C-013/50
출원번호
US-0465417
(2017-03-21)
등록번호
US-10101749
(2018-10-16)
발명자
/ 주소
Gillett, Luke Dafydd
Worsham, II, Robert Earl
출원인 / 주소
Bell Helicopter Textron Inc.
대리인 / 주소
Slater Matsil, LLP
인용정보
피인용 횟수 :
0인용 특허 :
13
초록▼
A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal accelera
A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal acceleration from the inertial sensors. The FCC generates a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed and generates a scaled and filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration. The FCC combines the filtered indication of longitudinal airspeed with the scaled and filtered indication of longitudinal acceleration to generate a determined longitudinal airspeed. The FCC generates a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed.
대표청구항▼
1. A rotorcraft, comprising: a plurality of airspeed sensors;a plurality of inertial sensors;a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft, wherein the FCC is configured to: receive a first indication of longitudinal airspeed from the plurality of airs
1. A rotorcraft, comprising: a plurality of airspeed sensors;a plurality of inertial sensors;a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft, wherein the FCC is configured to: receive a first indication of longitudinal airspeed from the plurality of airspeed sensors;receive a first indication of longitudinal acceleration from the plurality of inertial sensors;generate a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed;generate a filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration;multiply the filtered indication of longitudinal acceleration by a gain constant to generate a second indication of longitudinal acceleration;combine the filtered indication of longitudinal airspeed with the second indication of longitudinal acceleration to generate a determined longitudinal airspeed; andgenerate a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed. 2. The rotorcraft of claim 1, wherein the plurality of airspeed sensors comprise a plurality of pitot tubes. 3. The rotorcraft of claim 1, wherein the plurality of inertial sensors comprise a plurality of gyroscopic sensors. 4. The rotorcraft of claim 1, wherein the FCC is configured to receive the median indication of longitudinal airspeed of a plurality of indications of longitudinal airspeed from the plurality of airspeed sensors. 5. The rotorcraft of claim 1, wherein the FCC is configured to receive the median indication of longitudinal acceleration of a plurality of indications of longitudinal acceleration from the plurality of inertial sensors. 6. The rotorcraft of claim 1, wherein the filtered indication of longitudinal airspeed is generated from a low-pass filtering of the first indication of longitudinal airspeed. 7. The rotorcraft of claim 1, wherein the filtered indication of longitudinal acceleration is generated from a low-pass filtering of the first indication of longitudinal acceleration and the gain constant is based on a time constant of the low-pass filtering. 8. The rotorcraft of claim 1, wherein the determined longitudinal airspeed has less time lag than the filtered indication of longitudinal airspeed. 9. A flight control system computer (FCC) for a rotorcraft, comprising: a processor; anda non-transitory computer-readable storage medium storing a program to be executed by the processor, the program including instructions for providing control of the rotorcraft, the instructions for providing control of the rotorcraft including instructions for: receiving measured longitudinal airspeed data from an airspeed sensor;processing the measured longitudinal airspeed data using a first low-pass filter;receiving measured acceleration data from an acceleration sensor;processing the measured acceleration data using a second low-pass filter having a selectable gain;adding the processed acceleration data to the processed longitudinal airspeed data to reduce a phase lag of the processed longitudinal airspeed data; andcontrolling one or more flight control elements of the rotorcraft based on the processed longitudinal airspeed data. 10. The system of claim 9, wherein the selectable gain comprises a gain of about 0.5 to about 2.0 multiplied by a time constant of the second low-pass filter. 11. The system of claim 9, wherein the first low-pass filter and the second low-pass filter are first-order filters. 12. The system of claim 9, wherein the first low-pass filter and the second low-pass filter have the same time constant. 13. The system of claim 12, wherein the time constant is between 1.5 and 10 seconds. 14. The system of claim 9, wherein the processed longitudinal airspeed data has less higher-frequency noise than the measured longitudinal airspeed data. 15. A method, comprising: receiving airspeed data from an airspeed sensor of a rotorcraft;receiving acceleration data from an inertial sensor of the rotorcraft;filtering the airspeed data to generate filtered airspeed data, the filtered airspeed data having a phase lag relative to the airspeed data;filtering the acceleration data to generate filtered acceleration data;multiplying the filtered acceleration data by a gain constant to generate gain-multiplied and filtered acceleration data, the gain constant based on the filtering of the acceleration data;summing the filtered airspeed data with the gain-multiplied and filtered acceleration data to reduce the phase lag of the filtered airspeed data, the summing generating an indication of longitudinal velocity of the rotorcraft having a smaller phase lag relative to the airspeed data than the filtered airspeed data;receiving, by a flight control computer (FCC) of the rotorcraft, the indication of longitudinal velocity; andcontrolling, by the FCC of the rotorcraft, operation of the rotorcraft based on the indication of longitudinal velocity. 16. The method of claim 15, wherein receiving airspeed data comprises receiving longitudinal airspeed data. 17. The method of claim 15, wherein receiving acceleration data comprises receiving longitudinal acceleration data. 18. The method of claim 15, wherein filtering the airspeed data comprises using a digital filter. 19. The method of claim 18, wherein the digital filter is a low-pass filter. 20. The method of claim 15, wherein filtering the acceleration data reduces noise in the acceleration data.
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