Redundant system for the indication of heading and attitude in an aircraft
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0889311
(2000-01-12)
|
우선권정보 |
SE-199900113 (1999-01-18) |
국제출원번호 |
PCT/SE00/00034
(2000-01-12)
|
국제공개번호 |
WO00/42482
(2000-07-20)
|
발명자
/ 주소 |
- Adebjö
- rk, Peter
- Nordlund, Per-Johan
- Carlsson, Carl-Olof
|
출원인 / 주소 |
|
대리인 / 주소 |
Swidler Berlin Shereff Friedman, LLP
|
인용정보 |
피인용 횟수 :
7 인용 특허 :
3 |
초록
▼
A method and an arrangement for synthetically calculating redundant attitude and redundant heading by means of existing data in an aircraft. In one embodiment the heading of the aircraft is available and in another embodiment the heading is calculated from a magnetic heading sensor. When the heading
A method and an arrangement for synthetically calculating redundant attitude and redundant heading by means of existing data in an aircraft. In one embodiment the heading of the aircraft is available and in another embodiment the heading is calculated from a magnetic heading sensor. When the heading is available (redundant heading) attitude is calculated by weighting together the signals from and angular rate gyros ( 2 ) in the aircraft's flight control system, information from air data (altitude, speed, angle of attack) as well as information about heading (redundant heading). When the heading is not available, attitude and heading are calculated in one embodiment with the aid of Kalman filters ( 11, 22 ) by weighting together the signals from the angular rate gyros in the aircraft's control system, information from air data (altitude, speed, angle of attack and sideslip angle) as well as information from a magnetic heading detector existing in the aircraft.
대표청구항
▼
1. Method for synthetically calculating redundant attitude for an aircraft when a heading of the aircraft is known, using data existing in the aircraft, including angular rates p, q, r around x-, y- and z-coordinates of an aircraft-fixed (body frame) coordinate system, air data information including
1. Method for synthetically calculating redundant attitude for an aircraft when a heading of the aircraft is known, using data existing in the aircraft, including angular rates p, q, r around x-, y- and z-coordinates of an aircraft-fixed (body frame) coordinate system, air data information including speed, altitude and angle of attack of the aircraft, and the heading information, wherein the method includes the steps:calculating the attitude based on the aircraft-fixed angular rates p, q, r; andcorrecting the calculated attitude using the air data and the heading information. 2. Method according to claim 1, wherein the heading information is obtained from a heading gyro. 3. Method according to claim 1, wherein the step of calculating the attitude comprises the step of integrating out the attitude via information about the body-frame angular rates (p, q and r) obtained from the aircraft-fixed angular rate gyros of the aircraft. 4. Method according to claim 3, wherein correction of the integrated-out attitude takes place with the aid of attitude calculated on the basis of air data information and heading information. 5. Arrangement for synthetically calculating redundant attitude for an aircraft when a heading of the aircraft is known, using data existing in the aircraft, including body-frame angular rates (p, q and r) of the aircraft, air data including at least speed, altitude and angle of attack of the aircraft, and the heading information, wherein the arrangement includes an integration routine operable to integrate out the attitude of the aircraft from information about the body-frame angular rates (p, q and r) of the aircraft; and a correction routine operable to correct the calculated attitude using a reference attitude determined from air data and redundant heading information. 6. Arrangement according to claim 5, wherein the heading information is obtained from a heading gyro. 7. Arrangement according to claim 5, wherein the integration routine is further operable to integrate out the attitude of the aircraft from the body-frame angular rates (p, q and r) of the aircraft obtained from body-frame angular rate gyros of the aircraft. 8. Arrangement according to claim 7, wherein the integration routine receives a zero-error-compensated body-frame angular rate gyro signal. 9. Arrangement according to claim 5, wherein the correction routine if further operable to calculate a reference attitude using air data information and the redundant heading information. 10. Arrangement according to claim 5, further comprising a routine operable to obtain a synthetically-generated corrected attitude by generating a difference between the attitude obtained from the integration routine and an error signal that represents an error between the integrated attitude and the reference attitude.
이 특허에 인용된 특허 (3)
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Sicre Jean-Luc,FRX ; Guillard Patrice,FRX, Aircraft piloting aid system using a head-up display.
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Krogmann Uwe (berlingen DEX) Bessel Jurgen (berlingen DEX), Integrated redundant reference system for the flight control and for generating heading and attitude informations.
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Doty James H., Synthesized attitude and heading inertial reference.
이 특허를 인용한 특허 (7)
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Debailleul, Frédéric, Hybrid inertial navigation system based on a kinematic model.
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Ganesan, Eshwar Prasad; Ranganathan, Murali; Borneman, Jeffrey L.; Kunwer, Moid M., Method and apparatus for managing a communication link.
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Adebj?rk, Peter; Nordlund, Per-Johan; Carlsson, Carl-Olof, Redundant system for the indication of heading and attitude in an aircraft.
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Lee,Charles A., Self-calibration for an inertial instrument based on real time bias estimator.
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Andersson, Gert; Rodjegard, Henrik, Sensor device.
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Brenner, Mats Anders; Morrison, John R.; Kimmel, Danny Thomas; Hansen, Jay Joseph, Systems and methods for attitude fault detection based on air data and aircraft control settings.
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Brenner, Mats Anders; Ahlbrecht, Mark A.; Morrison, John R., Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals.
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