IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0612088
(2009-11-04)
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등록번호 |
US-8355861
(2013-01-15)
|
우선권정보 |
EP-08168257 (2008-11-04) |
발명자
/ 주소 |
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출원인 / 주소 |
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인용정보 |
피인용 횟수 :
2 인용 특허 :
2 |
초록
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A method for automatically determining an avoidance maneuver in an automatic collision avoidance system of an aircraft. A maximum kinematic acceleration envelope is determined by determining a multitude of avoidance maneuver angle kinematic acceleration pairs in a kinematic acceleration plane, and i
A method for automatically determining an avoidance maneuver in an automatic collision avoidance system of an aircraft. A maximum kinematic acceleration envelope is determined by determining a multitude of avoidance maneuver angle kinematic acceleration pairs in a kinematic acceleration plane, and interpolating gaps between points, thus creating a curve. The curve is called maximum kinematic acceleration envelope. The curve may also be approximated by an analytical expression. An adjusted kinematic acceleration envelope is formed in the plane by forming a new envelope. The new envelope at each point laying closer to or at the same distance from an origin as the points of the maximum kinematic acceleration envelope and such that there is only one value of the kinematic acceleration a for a given avoidance maneuver angle. An avoidance maneuver angle is received for which a suitable bank angle and a suitable normal load is to be determined. Determining The magnitude of the kinematic acceleration a corresponding to the adjusted kinematic acceleration envelope for the avoidance maneuver angle is determined by reading the envelope curve, or if the curve is an analytical expression, calculating the curve by using the analytical expression. The normal load is determined based on the kinematic acceleration, and the avoidance maneuver angle. The bank angle is determined based on the kinematic acceleration and the avoidance maneuver angle.
대표청구항
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1. A method to carry out in a computer for automatically determining an avoidance manoeuvre in an automatic collision avoidance system of an aircraft, the method comprising: determining, by said computer, a maximum kinematic acceleration envelope for a number of avoidance manoeuvre angles by determi
1. A method to carry out in a computer for automatically determining an avoidance manoeuvre in an automatic collision avoidance system of an aircraft, the method comprising: determining, by said computer, a maximum kinematic acceleration envelope for a number of avoidance manoeuvre angles by determining a corresponding number of corresponding kinematic accelerations in a kinematic acceleration plane, hereby defining a number of points, and interpolating the gaps between the points, thus creating the maximum kinematic acceleration envelope;forming, by said computer, an adjusted kinematic acceleration envelope in said aircraft by forming a new envelope, the new envelope at each point laying closer to or at the same distance from the origin as the points of the maximum kinematic acceleration envelope and such that for a given avoidance manoeuvre angle (ε), there is one value of the kinematic acceleration (a);receiving, by said computer, a desired avoidance manoeuvre angle (ε);determining, by said computer, the magnitude of the kinematic acceleration (a) corresponding to the adjusted kinematic acceleration envelope for the avoidance manoeuvre angle (ε), by reading the adjusted envelope curve;determining, by said computer, a normal load (nz), and a bank angle (φ) based on the kinematic acceleration (a), and the avoidance manoeuvre angle (ε); and guiding the aircraft in accordance with the generated avoidance manoeuver. 2. The method according to claim 1, wherein the maximum kinematic acceleration envelope is approximated by an analytical expression. 3. The method according to claim 1, wherein the adjusted kinematic acceleration envelope is approximated by an analytical expression and wherein the kinematic acceleration (a) is calculated by using said analytical expression. 4. The method according to claim 1, wherein the normal load (nz) is determined as a square root expression. 5. The method according to claim 1, wherein the bank angle is determined as arcus sinus function of an expression. 6. The method according to claim 4, wherein the normal load (nz) is determined as nz=√{square root over (a2+2ag cos ε cos θ+g2 cos2 θ)}. 7. The method according to claim 5, wherein the bank angle (Φ) is determined as ϕ=arcsin(asinɛnz). 8. The method according to claim 1, for an aircraft capable of automatically performing a collision avoidance manoeuvre for selecting the two collision avoidance manoeuvre parameters normal load, and bank angle, further comprising: receiving a desired avoidance manoeuvre angle ε as an angle in a kinematic acceleration plane;calculating a first transition point (εt1) as the absolute avoidance manoeuvre angle above which it would be most efficient for the aircraft to do a manoeuvre at maximum bank angle and use a normal load to attain the desired avoidance manoeuvre angle (ε), to achieve an avoidance manoeuvre with a maximum curvature, given the constraints of the aircraft in question, in order to quickly leave a trajectory having great risk of collision;calculating a second transition point (εt2) as the absolute avoidance manoeuvre angle above which it would be more efficient for the aircraft to do a manoeuvre at minimum normal load and use a bank angle to attain the desired avoidance manoeuvre angle (ε), to achieve an avoidance manoeuvre with the maximum curvature, given the constraints of the aircraft in question, in order to quickly leave a trajectory having great risk of collision;comparing the absolute value of the desired avoidance manoeuvre angle ε with the values of the first transition point εt1 and the second transition point (εt2)acting according to one of the following casesCase 1: If the absolute value of desired avoidance manoeuvre angle ε is greater than zero but less than the value of transition point (εti) then the suggested parameters for avoidance manoeuvre is set as follows:the normal load is set to maximum normal load (nz,max);the bank angle (Φ) is set to a value which would create the desired avoidance manoeuvre angle when executed together with the suggested normal load;Case 2: If the absolute value of desired avoidance manoeuvre angle ε is greater than the value of the first transition point εt1 but less than the value of the second transition point εt2 then the suggested parameters for avoidance manoeuvre is set as follows:the normal load is set to a value, which would create the desired avoidance manoeuvre angle when executed together with the suggested bank angle (Φ);the bank angle (Φ) is set to maximum allowed bank angle (Φmax)Case 3: If the absolute value of desired avoidance manoeuvre angle (ε) is greater than the value of the second transition point (εt2) then the suggested parameters for collision avoidance manoeuvre is set as follows:the normal load is set to minimum normal load (nz,min) the bank angle (Φ) is set to a value, which would create the desired avoidance manoeuvre angle when executed together with the suggested normal load. 9. A sense and avoidance system for an aerial vehicle, comprising: an avoidance manoeuvre parameter generator configured to carry out in a computer a method comprisingdetermining, by said computer, a maximum kinematic acceleration envelope for a number of avoidance manoeuvre angles by determining a corresponding number of corresponding kinematic accelerations in a kinematic acceleration plane, hereby defining a number of points, and interpolating the gaps between the points, thus creating the maximum kinematic acceleration envelope,forming, by said computer, an adjusted kinematic acceleration envelope in said plane by forming a new envelope, the new envelope at each point laying closer to or at the same distance from the origin as the points of the maximum kinematic acceleration envelope and such that for a given avoidance manoeuvre angle (ε), there is one value of the kinematic acceleration (a),receiving, by said computer, a desired avoidance manoeuvre angle (ε),determining, by said computer, the magnitude of the kinematic acceleration (a) corresponding to the adjusted kinematic acceleration envelope for the avoidance manoeuvre angle (e), by reading the adjusted envelope curve, anddetermining, by said computer, a normal load (nz), and a bank angle (φ) based on the kinematic acceleration (a), and the avoidance manoeuvre angle (ε). 10. The sense and avoidance system according to claim 9, wherein the aerial vehicle is manned. 11. An avoidance manoeuvre parameter generator for carrying out the method according to claim 1. 12. The sense and avoidance system according to claim 9, wherein the aerial vehicle is unmanned.
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