Method and device for displaying the limits of flight margins for an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G08G-005/04
G08G-005/00
G05D-001/00
G05F-007/00
G01W-001/10
G08B-023/00
G01C-023/00
G01C-021/00
출원번호
US-0815333
(2010-06-14)
등록번호
US-9536432
(2017-01-03)
우선권정보
FR-09 02874 (2009-06-12)
발명자
/ 주소
Laurent, Eric
Marty, Nicolas
Flotte, Laurent
출원인 / 주소
Thales
대리인 / 주소
Baker & Hostetler LLP
인용정보
피인용 횟수 :
1인용 특허 :
9
초록▼
A method of displaying, for a system for anti-collision monitoring of an aircraft, the limits of flight margins in relation to obstructions located in a flight zone, and a device for displaying the limits of operational flight margins and the limits of alert zones, is provided. The operational fligh
A method of displaying, for a system for anti-collision monitoring of an aircraft, the limits of flight margins in relation to obstructions located in a flight zone, and a device for displaying the limits of operational flight margins and the limits of alert zones, is provided. The operational flight margins in the flight zones not initially envisaged, and the limits of the alert zones around the trajectory of the aircraft, are presented.
대표청구항▼
1. A method of determining and displaying on a display device of a system for anti-collision monitoring of an aircraft, limits of flight margins in relation to obstructions located in a flight zone, the monitoring system generating collision alerts for obstructions located in a protection envelope o
1. A method of determining and displaying on a display device of a system for anti-collision monitoring of an aircraft, limits of flight margins in relation to obstructions located in a flight zone, the monitoring system generating collision alerts for obstructions located in a protection envelope of the aircraft and being able to calculate at least one flight maneuver predefined in a vertical plane, the method comprising: determining current flight parameters comprising current position, altitude, heading, speed including vertical speed, angle of approach, and roll rate of the aircraft, with avionic systems transmitting the aircraft's flight parameters in real time,determining a current trajectory comprising a vertical trajectory in the vertical plane extrapolated from said current flight parameters with the anti-collision system,calculating a plurality of radial trajectories in vertical planes distributed over the flight zone with the anti-collision monitoring system, said radial trajectories being rectilinear prolongations, beyond the protection envelope, of the current vertical trajectory of the aircraft in the vertical planes according to an azimuthal angular interval defined in the system,calculating and displaying on the display device in the flight zone a first monitoring zone with the anti-collision monitoring system in a form of a sector of disk surrounding the current trajectory of the aircraft and a second monitoring zone outside of the first monitoring zone in the flight zone, and the second monitoring zone being formed by a left lateral sector and a right lateral sector with respect to a direction of movement of the aircraft,calculating flight maneuvers of a first type with the anti-collision monitoring system, wherein the first type of flight maneuver includes three flight phases: a first flight phase corresponding to an anticipation phase,a second flight phase corresponds to a circular arc trajectory for joining up with a climb trajectory, anda third flight phase corresponds to a climb maneuver,based on the radial trajectories belonging to the first monitoring zone, and calculating flight maneuvers of a second type with the anti-collision monitoring system, wherein the second type of flight maneuver includes three phases: a first flight phase corresponds to an anticipation phase,a second flight phase corresponding to a circular arc trajectory for joining up with a climb trajectory with a flattening out phase, anda third flight phase corresponding to the flattening out, based on the radial trajectories belonging to the second monitoring zone,calculating the parameters for carrying out the flight maneuvers with the anti-collision monitoring system, comprising a point of intersection with an obstruction, based on each radial trajectory, said parameters comprising the position of the point of initiation of the maneuver, anddisplaying on the display device the current position of the aircraft and the position of the point of initiation of the flight maneuver closest to the current position of the aircraft for each obstruction and for each radial trajectory, said points of initiation of the flight maneuvers of all the radial trajectories representing flight margin limits of the aircraft at its current position in relation to the obstructions on the flight zone,wherein the display device displays the delimitations between the first flight zone and the second flight zone. 2. The method as claimed in claim 1, wherein the flight margins are displayed for obstructions located beyond the protection envelope of the aircraft and for which the monitoring system would trigger collision alerts if the aircraft exceeded these limits while moving according to the instantaneous flight parameters of the aircraft. 3. The method as claimed in claim 2, wherein the flight maneuver of the first type is an initiation and an execution of a climb trajectory of the aircraft. 4. The method as claimed in claim 3, wherein the flight maneuver of the second type is an initiation and an execution of a flattening out trajectory of the aircraft. 5. The method as claimed in claim 4, wherein the position of the first monitoring zone is correlated with the current dynamic turning parameters of the aircraft in such a way that in the event of turning of the aircraft the sector of disk is moved in rotation as a function of the angle of turn. 6. The method as claimed in claim 1, wherein delimitations between the first flight zone and the second flight zone are displayed. 7. The method as claimed in claim 1, wherein limits of flight margins are displayed in a flight zone in two dimensions. 8. The method as claimed in claim 1, wherein limits of flight margins are displayed in a flight zone in three dimensions. 9. A device of a system for anti-collision monitoring of an aircraft for determining and displaying the limits of flight margins in relation to obstructions located in a flight zone, the monitoring system generating collision alerts for obstructions located in a protection envelope of the aircraft and being able to calculate at least one flight maneuver predefined in a vertical plane, the device comprising: avionic systems for determining current flight parameters comprising current position, altitude, heading, speed including vertical speed, angle of approach, and roll rate of the aircraft and transmitting said flight parameters in real time,the device being configured for determining a current trajectory comprising a vertical trajectory in a vertical plane extrapolated from said current flight parameters,the device being further configured for calculating a plurality of radial trajectories in vertical planes distributed over the flight zone with the anti-collision monitoring system, said radial trajectories being rectilinear prolongations, beyond the protection envelope, of the current vertical trajectory of the aircraft in the vertical planes according to an azimuthal angular interval defined in the system,the device being configured for calculating and displaying on a display in the flight zone a first monitoring zone in a form of a sector of disk surrounding the current trajectory of the aircraft generated by the anti-collision monitoring system and a second monitoring zone outside of the first monitoring zone generated by the anti-collision monitoring system, the second monitoring zone being formed by a left lateral sector and a right lateral sector with respect to a direction of movement of the aircraft, the first monitoring zone displaying the limits of an anti-collision alert zones in relation to obstructions and the second monitoring zone displaying the operational flight margins in relation to obstructions, andthe device being configured for calculating flight maneuvers of a first type which includes three flight phases:a first flight phase corresponding to an anticipation phase,a second flight phase corresponding to a circular arc trajectory for joining up with a climb trajectory, anda third flight phase corresponding to the climb trajectory,based on the radial trajectories belonging to the first monitoring zone,the device being further configured for calculating flight maneuvers of a second type which includes three flight phases:a first flight phase corresponding to an anticipation phase,a second flight phase corresponding to a circular arc trajectory for joining up with a climb trajectory with a flattening out phase, anda third flight phase corresponding to the flattening out, based on the radial trajectories belonging to the second monitoring zone,the device being further configured for:calculating the parameters for carrying out the flight maneuvers comprising a point of intersection with an obstruction, based on each radial trajectory, said parameters comprising the position of the point of initiation of the maneuver, anddisplaying on the display the current position of the aircraft and the position of the point of initiation of the flight maneuver closest to the current position of the aircraft for each obstruction and for each radial trajectory, said points of initiation of the flight maneuvers of all the radial trajectories representing flight margin limits of the aircraft at its current position in relation to the obstructions on the flight zone,wherein the display displays the delimitations between the first flight zone and the second flight zone. 10. The device as claimed in claim 9, wherein an alert zone represents the positions of the obstructions located beyond the protection envelope of the aircraft and for which the monitoring system would trigger collision alerts if the aircraft exceeded these limits while moving according to the instantaneous flight parameters of the aircraft. 11. The device as claimed in claim 10, wherein it displays the delimitations between the first flight zone and the second flight zone.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.