Method and device for reducing the induced speeds in vortices in the wake of an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/00
B64C-013/16
출원번호
US-0738214
(2008-10-16)
등록번호
US-8336827
(2012-12-25)
우선권정보
FR-07 58344 (2007-10-16)
국제출원번호
PCT/FR2008/051869
(2008-10-16)
§371/§102 date
20100813
(20100813)
국제공개번호
WO2009/053649
(2009-04-30)
발명자
/ 주소
Journade, Jerome
출원인 / 주소
Airbus Operations SAS
대리인 / 주소
Perman & Green, LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying ch
A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying changes in the aerodynamic configurations of the aircraft liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, —for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex, —carrying out, along the course of the aircraft, at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space.
대표청구항▼
1. A method for creating a continuous protected space along a path of an airplane, in which said protected space a maximum speed Vtc induced in a vortex of radius Rtc of a wake of airplane is reduced through increasing the radius Rtc of the vortex, said method comprising: a prior step of identifying
1. A method for creating a continuous protected space along a path of an airplane, in which said protected space a maximum speed Vtc induced in a vortex of radius Rtc of a wake of airplane is reduced through increasing the radius Rtc of the vortex, said method comprising: a prior step of identifying two or more changes of aerodynamic configurations for the airplane to trigger wake disturbances having the effect of increasing the radius Rtc of the vortex by a predefined value as a result of the wake disturbance in a given time;for each identified configuration for triggering such a wake disturbance, determining propagation characteristics along the vortex in an upstream direction, opposite to a direction of movement of the airplane along the airplane path, and in a downstream direction, corresponding to a direction of movement of the airplane along the airplane path, of the wake disturbances in sections of the vortex proximate a section of the vortex where said configuration change had been carried out;carrying out at least two of the aerodynamic configuration changes along the path of the airplane separated by a distance such that spaces, in which effects of the wake disturbances resulting from each of said at least two configuration changes are propagated along the vortex during a predefined length of time, are separated by a distance along the airplane path of almost zero or overlap along the airplane path so as to create a continuous protected space along the airplane path in which the maximum speed Vtc of the vortex is reduced because of the wake disturbance by at least a predefined value. 2. A method according to claim 1 in which the propagation characteristics of a wake disturbance comprise: a length of time ΔTps corresponding to the time required so that the radius Rtc of the vortex increases by a predefined value ΔRt % in a section of the vortex under the effect of the wake disturbance after said wake disturbance has reached a section of the vortex;a propagation speed Vpp-upstream of the wake disturbance along the vortex in the upstream direction;a propagation speed Vpp-downstream of the wake disturbance along the vortex in the downstream direction. 3. A method according to claim 2 in which the distance separating a point of a the first configuration change from a point of a second configuration change, following the first configuration change along the flight path of airplane, is a function of a separation distance Ds between the airplane and a following airplane located upstream on approximately the same path as the airplane and a speed Vav of the following airplane, said value Vav being a measured value of the following airplane's speed or an estimated value of the following airplane's speed, or an arbitrary value overestimating the following airplane's speed. 4. A method according to claim 3 in which the distance separating the first and the second configuration changes is less than or approximately equal to the sum of a distance Ddownstream downstream of the point of the first configuration change along the path of the airplane and a distance Dupstream upstream of the point of the second configuration change along the path of the airplane with: Ddownstream=(Ds−ΔTps ×Vav)×Vpp-downstream/(Vav-Vpp-downstream), with the values of ΔTps and Vpp-downstream chosen from the propagation characteristics of the wake disturbance associated with the first configuration change;Dupstream=(Ds−ΔTps ×Vav) ×Vpp-upstream/(Vav+Vpp-upstream), with the values of ATps and Vpp-upstream chosen from the propagation characteristics of the wake disturbance associated with the second configuration change. 5. A method according to claim 3 in which a {speed Vav−distance Ds} pair is chosen, from {speed−distance} pairs associated to different models of following airplanes envisaged, to determine the distances between the configuration changes so as to produce a protected space compatible with any one whatsoever of said different models of following airplanes envisaged. 6. A method according to claim 1 in which the configuration changes are realized by changes of position of mobile surfaces of airplane, and or by a change in the attitude of airplane during a landing. 7. A method according to claim 6 in which the configuration changes are realized along a path corresponding to an approach phase of airplane ending in a landing at a point Att such that the continuous protected space extends from a point of the approach path away from the point Att through to at least point Att. 8. A device for creating a continuous protected space along a path of an airplane, in which said protected space a maximum speed Vtc induced in a vortex of radius Rtc of a wake of airplane is reduced through increasing the radius Rtc of the vortex as a result of a wake disturbance, wherein the device comprises: at least one memory in which are stored information representative of wake disturbance propagation characteristics along the vortex, in an upstream direction, opposite to a direction of movement of the airplane along the airplane path, and in a downstream direction, corresponding to a direction of movement of the airplane along the airplane path, triggered by changes of aerodynamic configurations of the airplane and information about the airplane and its environment;means of calculation for generating, using information stored in the memory, instructions for successive changes of aerodynamic configurations of the airplane such that wake disturbances having the effect of increasing the radius Rtc of the vortex caused by said configuration changes are propagated along the vortex such that at least two successive configuration changes are separated on the airplane path by a distance such that spaces, in which effects of the wake disturbances resulting from each of said at least two configuration changes are propagated along the vortex during a predefined length of time, are separated by a distance along the airplane path of almost zero or overlap along the airplane path and create the continuous protected space along the airplane path, in which the maximum speed Vtc of the vortex is reduced because of the wake disturbance by at least a predefined value, after a predefined time. 9. A device according to claim 8 comprising means of generating an alarm signal when the configuration changes carried out do not conform to the configuration changes likely to create a continuous protected space.
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이 특허에 인용된 특허 (4)
Crouch Jeffrey D. ; Spalart Philippe R., Active system for early destruction of trailing vortices.
Corjon, Alexandre; Leweke, Thomas; Laporte, Florent, Process and device for accelerating the destruction of at least two vortices in the wake of a moving body, particularly an aircraft.
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