[특허]Method and device for automatically protecting an aircraft against an excessive descent rate

Airbus Operations (SAS)

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특허 상세정보

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Method and device for automatically protecting an aircraft against an excessive descent rate

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00 G05D-001/06
미국특허분류(USC)	701/005; 701/007; 701/008; 701/009; 701/010; 701/011; 244/004R
출원번호	US-0023917 (2011-02-09)
등록번호	US-8818577 (2014-08-26)
우선권정보	FR-10 51073 (2010-02-16)
발명자 / 주소	Louise, Pascale Cortet, Emmanuel Grandperret, Erwin
출원인 / 주소	Airbus Operations (SAS)
대리인 / 주소	Wood, Herron & Evans, LLP
인용정보	피인용 횟수 : 1 인용 특허 : 24

초록
▼

A device includes means for generating and applying to an aircraft protecting orders avoiding a flight with an excessive descent rate. More specifically, the device includes components configured to perform a series of operations including measuring the current vertical speed and the current height of the aircraft and comparing these flight parameters with a safety envelope defining couples of vertical speed and height that are indicative of an excessive descent rate. If the current vertical speed and height are located in the safety envelope, a protecti...

대표
청구항
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1. A method for automatically protecting an aircraft against an excessive descent rate, the method comprising the following string of successive operations: a) measuring with a set of information sources a current vertical speed and a current height of the aircraft with respect to the ground, referred to as current flight parameters, and measuring with a different set of information sources independent from the set of information sources a current auxiliary vertical speed and a current auxiliary height of the aircraft with respect to the ground, referred to as current auxiliary flight parameters;b) comparing with a comparing device these current flight parameters with at least one flight envelope, referred to as a safety envelope, depending on an unauthorized flight envelope, the unauthorized flight envelope defining couples of vertical speed and height, illustrating an excessive descent rate and that are not authorized for the aircraft, and separately and independently comparing the current auxiliary flight parameters with at least one auxiliary safety envelope such that comparing the current flight parameters with the at least one safety envelope is performed independently from comparing the current auxiliary flight parameters with the at least one auxiliary safety envelope, and triggering a protection only at least if simultaneously: the current flight parameters are located in the safety envelope; andthe current auxiliary flight parameters are located in the auxiliary safety envelope; andc) should the protection be triggered: generating protecting orders automatically upon the triggering with a calculation unit for controlling the control surfaces of the aircraft acting on the current vertical speed, the protecting orders configured to cause the aircraft to avoid being located in the unauthorized flight envelope; andapplying the protecting orders automatically upon generation of the protecting orders with a surface operating device to the control surfaces and without requiring added actions or workload for a crew of the aircraft. 2. The method according to claim 1, wherein the safety envelope corresponds to the unauthorized flight envelope, to which a safety margin has been added, and in step c), protecting orders are generated such that the protecting orders prevent the aircraft from getting in the unauthorized flight envelope. 3. The method according to claim 2, wherein in step c): an intermediate order is determined, representing a vertical acceleration value γz, by means of the following equation: γz=(Vz2−Vmax2)/(2*h) wherein:Vz is the measured current vertical speed of the aircraft;Vmax is the maximum vertical speed authorized at the current height according to the unauthorized flight envelope; andh is the current measured height of the aircraft; andwherein the intermediate order is converted into deflection angles of the control surfaces, representing the protecting orders. 4. The method according to claim 1, wherein the safety envelope represents the unauthorized flight envelope, and in step c), protecting orders are generated such that the protecting orders avoid the aircraft from staying in the unauthorized flight envelope. 5. The method according to claim 4, further comprising: in step c), a lateral maneuver is additionally controlled, resulting in wings of the aircraft being flat again. 6. The method of claim 1 further comprising: deactivating a preliminarily triggered protection automatically when the conditions of the current flight parameters being located in the safety envelope are no longer fulfilled. 7. The method according to claim 6, wherein the safety envelope corresponds to the unauthorized flight envelope, to which a safety margin has been added, and in step c), protecting orders are generated such that the protecting orders prevent the aircraft from getting in the unauthorized flight envelope. 8. The method according to claim 7, wherein in step c): an intermediate order is determined, representing a vertical acceleration value γz, by means of the following equation: γz=(Vz2−Vmax2)/(2*h) wherein:Vz is the measured current vertical speed of the aircraft;Vmax is the maximum vertical speed authorized at the current height according to the unauthorized flight envelope; andh is the current measured height of the aircraft; andwherein the intermediate order is converted into deflection angles of the control surfaces, representing the protecting orders. 9. The method according to claim 6, wherein the safety envelope represents the unauthorized flight envelope, and in step c), protecting orders are generated such that the protecting orders avoid the aircraft from staying in the unauthorized flight envelope. 10. The method according to claim 9, further comprising: in step c), a lateral maneuver is additionally controlled, resulting in wings of the aircraft being flat again. 11. A device for automatically protecting an aircraft against an excessive descent rate, the device comprising: a first device for automatically measuring the current vertical speed and the current height of the aircraft, referred to as current flight parameters;first auxiliary elements for measuring a current auxiliary vertical speed and a current auxiliary height with respect to the ground of the aircraft, referred to as current auxiliary flight parameters, the first auxiliary elements independent from the first device;a second device able to emit a protection trigger signal, the second device including a comparing device that configured to compare the current flight parameters with at least one flight envelope, referred to as a safety envelope, depending on an unauthorized flight envelope, the unauthorized flight envelope defining couples of vertical speed and height, illustrating an excessive descent rate and not being authorized for the aircraft, and the comparing device also configured to compare the current auxiliary flight parameters with an auxiliary safety envelope separately and independent from the comparing of current flight parameters to the at least one flight envelope, the second device also including a signaling device for emitting a trigger signal only if simultaneously: the current flight parameters are located in the safety envelope; andthe current auxiliary flight parameters are located in the auxiliary safety envelope;a third device for automatically generating, upon emitting of the trigger signal, protecting orders for controlling control surfaces of the aircraft acting on the current vertical speed, the protecting orders configured to cause the aircraft to avoid being located in the unauthorized flight envelope;a fourth device for automatically applying the protecting orders to the control surfaces upon generation of the protecting orders and without requiring added actions or workload for a crew of the aircraft. 12. The device according to claim 11, wherein the second device is independent and distinct from the third device. 13. The device according to claim 11, wherein the second device is integrated into a calculator comprising the third device. 14. The device according to claim 11, further comprising: an indication device for making a crew member aware of the emission of the trigger signal by the signaling device.

이 특허에 인용된 특허 (24)

이 특허를 인용한 특허 피인용횟수: 1

Prosser, Kevin. Aircraft flight envelope protection and recovery autopilot. USP20190310228692.

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Method and device for automatically protecting an aircraft against an excessive descent rate

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Method and device for automatically protecting an aircraft against an excessive descent rate

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