IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0955296
(2007-12-12)
|
등록번호 |
US-7671761
(2010-04-21)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
4 |
초록
▼
The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from
The system contains a receiver in communication with a programmable device. The receiver receives a first horizontal distance from the aircraft to a threshold of the runway, an angle of a glide path, and a threshold crossing height. The programmable device determines a projected ground distance from the aircraft to the threshold. The programmable device determines a projected ground distance from the threshold to a glide path intercept point. The programmable device determines a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point. The programmable device determines a synthetic altitude above runway for the aircraft.
대표청구항
▼
What is claimed is: 1. A method for determining an altitude of an aircraft relative to a runway, the method comprising: receiving information of a horizontal distance from the aircraft to a runway threshold, associated with a runway, the surface of the runway defining a runway plane; determining a
What is claimed is: 1. A method for determining an altitude of an aircraft relative to a runway, the method comprising: receiving information of a horizontal distance from the aircraft to a runway threshold, associated with a runway, the surface of the runway defining a runway plane; determining a projected ground distance from the aircraft to the runway threshold; determining a projected ground distance from the runway threshold to a glide path intercept point, based on a projected aircraft glide path angle and a runway threshold crossing height; determining a vertical height along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point; and determining a synthetic altitude of the aircraft above runway based on the current vertical height of the aircraft and a predetermined vertical error or angular deviation component. 2. The method of claim 1, further comprising utilizing the synthetic altitude as an input to a navigation control for the aircraft. 3. The method of claim 2, further comprising landing the aircraft using said navigation control. 4. The method of claim 1, further comprising triggering a control law action when the synthetic altitude above runway reaches a predetermined value. 5. The method of claim 4, wherein the control law action includes at least one of reconfiguring at least one control law, annunciating a flight level, and initiating a fault response. 6. The method of claim 4, further comprising monitoring a horizontal integrity limit, and initiating a control law action when the horizontal integrity limit has been exceeded. 7. The method of claim 4, wherein at least one of the control laws, warning detection, and fault response altitude triggers, are independent of at least one of terrain and aircraft altitude. 8. The method of claim 4, wherein the runway has an uneven, upsloping or downsloping pre-runway terrain, and including landing the aircraft under automatic control on said runway. 9. The method of claim 1, wherein the horizontal distance and vertical error information is provided to the aircraft by a satellite. 10. The method of claim 1, wherein the step of receiving horizontal distance information from the aircraft to the runway threshold further comprises determining a laterally projected slant distance between a Guidance Control Point on the aircraft and a landing threshold point on the runway. 11. The method of claim 1, including providing a library of runway characteristics selected from the group consisting of threshold crossing height, distance from the runway threshold to the glide path intercept point, and the glidepath angle, and retrieving one or more of said characteristics from said library. 12. A system for determining an altitude of an aircraft relative to a runway, the surface of the runway defining a runway plane, the system comprising: a receiver in communication with a programmable device, the receiver receiving data representing horizontal distance from the aircraft to a runway threshold, an angle of a glide path, and a runway threshold crossing height; and the programmable device determining a projected ground distance from the aircraft to the runway threshold, a projected ground distance from the threshold to a glide path intercept point, a vertical value along the glide path relative to a projected ground distance between the aircraft and the glide path intercept point, and based on the foregoing determines a synthetic altitude of the aircraft. 13. The system of claim 12, wherein the programmable device is mounted within the aircraft. 14. The system of claim 12, wherein the receiver is a digital multi-mode receiver. 15. The system of claim 12, wherein the horizontal distance from the aircraft to the runway threshold further comprises a laterally projected angular distance between a Guidance Control Point on the aircraft and a landing threshold point on the runway. 16. The system of claim 12, wherein the programmable device monitors a horizontal integrity limit; said system further comprising an output device indicating to a user whether the horizontal integrity limit has exceeded a predefined integrity requirement. 17. An article of manufacture comprising computer program code embodied in computer-readable medium comprising instructions that when executed are used to compute a synthetic altitude above a runway, the method comprising: receiving horizontal distance information of the distance from an aircraft to a runway threshold associated with a runway, the surface of the runway defining a runway plane; determining a projected ground distance from the aircraft to the runway threshold; determining a distance from the runway threshold to a glide path intercept point based on a projected aircraft glide path angle and a threshold crossing height; determining a current height of the aircraft above the runway plane based on the projected ground distance and the distance from the runway threshold to a glide path intercept point; and determining an aircraft synthetic altitude above the runway plane based on the current height of the aircraft and a predetermined vertical error or angular deviation component. 18. The article of manufacture of claim 17, wherein said computer-readable program code triggers a control law action when the synthetic altitude above runway reaches a predetermined value. 19. The article of manufacture of claim 17, wherein the computer-readable program code determines if a ground integrity limit has been exceeded. 20. The article of manufacture of claim 19, wherein the computer readable program code terminates determination of the synthetic altitude above runway for the aircraft when the ground integrity limit has exceeded a predetermined integrity requirement.
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