Method and a device for determining and optimizing parameters that are characteristic of the operation of a rotary wing aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G07C-005/08
B64D-043/00
B64C-027/04
출원번호
US-0059440
(2016-03-03)
등록번호
US-9536358
(2017-01-03)
우선권정보
FR-15 00411 (2015-03-04)
발명자
/ 주소
Germanetti, Serge
출원인 / 주소
Airbus Helicopters
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A method of determining parameters that are characteristics of the operation of a vehicle having a power plant with at least one engine and mechanical transmission means, sensors, and display means. During the method, various items of information about the aircraft, its state and/or its operation an
A method of determining parameters that are characteristics of the operation of a vehicle having a power plant with at least one engine and mechanical transmission means, sensors, and display means. During the method, various items of information about the aircraft, its state and/or its operation and/or its environment are measured, and then, for at least one parameter Pi relating to the state and the operation of the aircraft there are determined a first limit value Pi_lim for the parameter Pi, a second value Pi_X for each parameter Pi to enable the aircraft to perform a predetermined maneuver X, and an instantaneous third value Pi_inst for each parameter Pi. Thereafter, each first, second, and third values Pi_lim, Pi_X, Pi_inst is displayed simultaneously in order to show up the relative position of second and third values Pi_X and Pi_inst relative to a first value Pi_lim for each parameter Pi.
대표청구항▼
1. A method of determining parameters that are characteristic of the operation of a vehicle, the vehicle having a power plant having at least one engine and main gearbox, a control assembly for controlling movements of the vehicle, a plurality of sensors, at least one computer, at least one memory,
1. A method of determining parameters that are characteristic of the operation of a vehicle, the vehicle having a power plant having at least one engine and main gearbox, a control assembly for controlling movements of the vehicle, a plurality of sensors, at least one computer, at least one memory, and at least one display, the method comprising the following steps: measuring various items of information about the environment of the vehicle, and/or the state and the operation of the vehicle and of the power plant, and/or the states of the control assembly, and/or the position and the movements of the vehicle relative to its environment; determining via the at least one computer an available power margin for each engine of the power plant relative to a minimum guaranteed power, the available power margin characterizing an aging state of each engine of the power plant; determining via the at least one computer an available maximum power from each engine of the power plant by taking account of the available power margin; determining via the at least one computer at least one power characteristic of each engine of the power plant corresponding to performing a predetermined maneuver X of the vehicle, determining via the at least one computer at least a first value Pi_lim corresponding to the available maximum power of each engine of the power plant, and a limit value that a parameter Pi must not exceed, Pi being a parameter relative to the state or to the operation of the vehicle, or to the state or the operation of the power plant, or to the states of the control assembly, or to the position or to the movements of the vehicle relative to its environment; determining via the at least one computer at least one second value Pi_X corresponding to a characteristic power of each engine for performing a predetermined maneuver X of the vehicle and to which the parameter Pi must be equal in order to enable the vehicle to perform the predetermined maneuver X; and simultaneously displaying on a common graphics type representation each first value Pi_lim and each second value Pi_X in order to show clearly the relative position between a first value Pi_lim and each second value Pi_X for each parameter Pi. 2. A method according to claim 1, characterized by the following steps: determining via the at least one computer an instantaneous power Wminst delivered by each engine of the power plant; determining via the at least one computer at least one third value Pi_inst corresponding to the instantaneous power Wminst delivered by each engine and equal to an instantaneous value of each parameter Pi; and displaying each third value Pi_inst on the graphics type representation. 3. A method according to claim 1, wherein each second value Pi_X and each third value Pi_inst, if any, is displayed on the at least one display as a percentage relative to the first value Pi_lim corresponding to the parameter Pi. 4. A method according to claim 1, wherein each first value Pi_lim, each second value Pi_X, and each third value Pi_inst, if any, is displayed on the at least one display as a percentage relative to a reference value of the parameter Pi. 5. A method according to claim 1, wherein the vehicle is a rotary wing aircraft having a main rotor with main blades, the control assembly controlling variation in the collective pitch of the main blades, and values for the collective pitch of the main blades are displayed on the at least one display, which values correspond respectively to each first value Pi_lim, to each second value Pi_X, and to each third value Pi_inst, if any. 6. A method according to claim 2, wherein each first value Pi_lim, each second value Pi_X, and each third value Pi_inst is displayed on a first limit indicator (FLI) of the vehicle. 7. A method according to claim 1, wherein an estimated instantaneous mass Minst is determined for the vehicle via the at least one computer in order to determine each characteristic power. 8. A method according to claim 7, wherein an available maximum total power at the power plant equal to the sum of the available maximum powers of each engine is used by the at least one computer to determine a maximum mass that can be transported by the vehicle, the maximum transportable mass being the difference between the mass of the vehicle for which a total power delivered by the power plant is equal to the available maximum total power in application of performance curves of the vehicle while taking account of the available power margin, and the estimated instantaneous mass Minst of the vehicle. 9. A method according to claim 1, wherein the vehicle is a rotary wing aircraft having a main rotor with main blades, an anti-torque rotor with secondary blades, and the main gearbox drives rotation of the main rotor and the anti-torque rotor when the aircraft is hovering with its horizontal speed Vh and its vertical speed Vz being substantially zero, and the functional characteristics of the aircraft are characterized in particular by a series of first performance curves using a first formula carried out by the at least one computer: Wσ·(NR0NR)3=k·f1[Mσ·(NR0NR)2] where W is a flight power of the aircraft (10), σ is a reduction coefficient, k is a coefficient for the influence of the ground on the behavior of the aircraft as a function of the height Hz of the aircraft above the ground, M is the estimated mass of the aircraft, NR0 is a setpoint for the speed of rotation of the main rotor, NR is the real speed of rotation of the main rotor, and ƒ1 is a first function represented by a series of first performance curves for the aircraft, the flight power W of the aircraft being equal to the sum of the powers delivered by each engine of the power plant minus accessory power needed for powering equipment on board the aircraft, the method comprising the following steps: calculating via the at least one computer the reduction coefficient σ such that: σ=(P0T0)calculating via the at least one computer a first value A1 such that: A1=Mσ·(NR0NR)2measuring the height Hz of the aircraft above the ground;determining via the at least one computer the influence coefficient k corresponding to the height Hz;using a first performance curve of the aircraft in application of the first function ƒ1 corresponding to the flight conditions of the aircraft and as a function of the first value A1 to determine a second value A2 as carried out by the at least one computer such that: A2=f1[Mσ·(NR0NR)2]using the second value A2 to calculate a first characteristic power Wk of the aircraft when hovering with or without the ground effect depending on the influence coefficient k, as carried out by the at least one computer, such that: Wk=k·A2·σ·(NRNR0)3. 10. A method according to claim 9, wherein the following step is performed by the at least one computer: defining the influence coefficient k as being equal to 1, corresponding to hovering flight outside the ground effect of the aircraft, and using the second value A2 to calculate a second characteristic power Wk=1 of the aircraft when hovering outside the ground effect of the aircraft such that: Wk-1=A2·σ·(NRNR0)3. 11. A method according to claim 10, wherein a mark is displayed on a scale representing the height Hz of the aircraft above the ground, the mark indicating the lowest height Hzk that corresponds to the coefficient k being equal to 1. 12. A method according to claim 9, comprising the following steps carried out by the at least one computer: defining the influence coefficient k equal to a minimum value kmini corresponding to hovering flight of the aircraft at ground level; and using the second value A2 to calculate the third characteristic power Wkmini of the aircraft when the aircraft is hovering at ground level such that: Wkmini=kmini·A2·σ·(NRNR0)3. 13. A method according to claim 9, comprising the following steps carried out by the at least one computer: defining the influence coefficient k as being equal to a minimum value kmini corresponding to the aircraft hovering at ground level;using the second value A2 to calculate a third characteristic power Wkmini of the aircraft when hovering at ground level such that: Wkmini=kmini·A2·σ·(NRNR0)3,determining a total torque that needs to be supplied by the power plant corresponding to a power of the power plant lying in the range from the third characteristic power Wkmini to the first characteristic power Wk;applying the total torque to the power plant, thereby automatically leading to slow descent towards a landing; andadjusting the influence coefficient k during the descent of the aircraft as a function of the reduction in the height Hz and thus in the first characteristic power Wk, and consequently adjusting the total power to be delivered by the power plant until the aircraft. 14. A method according to claim 9, wherein the control assembly controls variation in the collective pitch and in the cyclic pitch of the main blades and the following steps are performed by the at least one computer: defining the influence coefficient k equal to a minimum value kmini corresponding to the aircraft hovering at ground level;using the second value A2 to calculate a third characteristic power Wkmini of the aircraft when hovering at ground level such that: Wkmini=kmini·A2·σ·(NRNR0)3,determining a collective pitch for the main blades corresponding to a power from the power plant lying in the range from the third characteristic power Wkmini to the first characteristic power Wk;applying the collective pitch to the main blades, thereby automatically leading to slow descent towards a landing; andadjusting the influence coefficient k during the descent of the aircraft as a function of the reduction in the height Hz and thus in the first characteristic power Wk, and consequently adjusting the collective pitch until the aircraft lands. 15. A method according to claim 1, wherein when the vehicle is a rotary wing aircraft in cruising flight, its vertical speed Vz being substantially zero, use is made of a series of second performance curves in application of a second formula W=ƒ2(Vh) carried out by the at least one computer, where W is a flight power of the aircraft and Vh is the horizontal speed of the aircraft, and a horizontal straight line tangential to the second curve that corresponds to the flight conditions of the aircraft to determine via the at least one computer a fourth characteristic power Wend of the aircraft and a first characteristic horizontal speed Vend of the aircraft, thereby making it possible for the at least one computer to obtain a maximum flight duration for the aircraft, the flight power W of the aircraft being equal to the sum of the powers delivered by each engine of the power plant minus an accessory power needed for powering equipment on board the aircraft. 16. A method according to claim 1, wherein when the vehicle is a rotary wing aircraft in cruising flight, its vertical speed Vz being substantially zero, use is made of a second series of performance curves in application of a second formula W=ƒ2(Vh) carried out by the at least one computer, where W is a flight power of the aircraft, Vh is the horizontal speed of the aircraft, and ƒ2 is a second function represented by a series of second performance curves of the aircraft, and a straight line tangential to the second curve that corresponds to the flight conditions of the aircraft and that passes through the origin point of the plot of the second curve to determine via the at least one computer a fifth characteristic power Wrange of the aircraft and a second characteristic horizontal speed Vrange of the aircraft making it possible for the at least one computer to obtain a maximum range for the aircraft, the flight power W of the aircraft being equal to the sum of the powers delivered by each engine of the power plant minus an accessory power needed for powering equipment on board the aircraft. 17. A method according to claim 16, wherein in the event of the aircraft being subjected to longitudinal wind, the straight line tangential to the second curve does not pass through the origin point of the plot of the second curve but passes through a point that is offset along the abscissa axis from the origin point of the plot by the value of the longitudinal wind speed. 18. A method according to claim 1, wherein when the vehicle is a rotary wing aircraft climbing, its vertical speed Vz being non-zero, use is made of functional characteristics of the aircraft characterized in particular by a series of third performance curves in application of a third formula carried out by the at least one computer: (Wσ)Vy=f3(Mσ);where W is a flight power of the aircraft, σ is a reduction coefficient, M is the estimated mass of the aircraft, Vy is the optimum rate of climb of the aircraft, ƒ3 being a third function represented by a series of third performance curves of the aircraft, the ratio: (Wσ)Vy being obtained by the at least one computer for a vertical speed Vz of the aircraft equal to the optimum climb rate Vy of the aircraft, such that a sixth characteristic power WVy of the aircraft corresponds to the optimum climb rate Vy, the flight power W of the aircraft being equal to the sum of the powers delivered by each engine of the power plant minus an accessory power needed to power equipment on board the aircraft, and the following steps are performed by the at least one computer: calculating the reduction coefficient σ such that: σ=(P0T0)calculating a third value A3 such that: A3=(Mσ)using a third performance curve of the aircraft in application of the third function ƒ3 corresponding to the flight conditions of the aircraft and as a function of the third value A3 to determine via the at least one computer a fourth value A4 such that: A4=f3(Mσ)using the fourth value A4 to calculate the sixth characteristic power WVy corresponding to the optimum climb rate Vy, such that WVy=A4·σ. 19. A method according to claim 1, wherein the parameter Pi is selected from the following list or else is a logical or arithmetic combination of at least two of the elements of the following list as carried out by the at least one computer: a total torque delivered by the power plant or else an outlet torque from the main gearbox, or else a torque delivered by an engine; a total power delivered by the power plant or a power delivered by one of the engines; a speed of the vehicle relative to the air, or a speed of the vehicle relative to the ground; a height of the vehicle relative to a reference; a temperature inside an engine; and a speed of rotation of an element of an engine. 20. A method according to claim 1, wherein when the vehicle is a rotary wing aircraft having a main rotor with main blades, an anti-torque rotor with secondary blades, the main gearbox drives the main rotor and the anti-torque rotor, and the control assembly controls variation in the collective pitch and in the cyclic pitch of the main blades and controls the collective pitch of the secondary blades, the parameter Pi is selected from the following list or else is a logical or arithmetic combination of at least two elements from the following list as carried out by the at least one computer: a total torque delivered by the power plant or a torque delivered by one of the engines or indeed a rotor torque at a mast for driving the main rotor in rotation, or indeed a torque at the anti-torque rotor;a total power delivered by the power plant or indeed a power delivered by one of the engines;a speed of the aircraft relative to the air or a speed of the aircraft relative to the ground;a height of the aircraft relative to a reference;a temperature inside an engine;a speed of rotation of an element of an engine;a position of a control surface of the aircraft or a pitch value of the main blades of the main rotor, or indeed of the secondary blades of the anti-torque rotor;a collective pitch control position for the main blades of the main rotor;a cyclic pitch control position for the main blades of the main rotor; anda collective pitch control position for the secondary blades of the anti-torque rotor. 21. A method according to claim 1, wherein the second values Pi_X to which the parameter Pi must be equal to enable the vehicle (10) to perform a predetermined maneuver X forms a range of values for the parameter Pi. 22. A method according to claim 2, wherein at least one third value Pi_inst equal to an instantaneous value of each parameter Pi is determined via the at least one computer, and the following are displayed: each first value Pi_lim; each second value Pi_X; and each third value Pi_inst for that one of the parameters Pi selected from at least two parameters (Pi, Pj) for which the difference between the first value Pi_lim and the third value Pi_inst associated respectively with each of the parameters (Pi, Pj) is the smallest. 23. A device for determining parameters that are characteristic of the operation of a vehicle, the vehicle having a power plant with at least one engine and a main gearbox, the vehicle also having a control assembly, the device having a plurality of sensors, at least one computer, at least one memory, and a display, the sensors providing measurements of various items of information about the environment of the vehicle and/or the state and the operation of the vehicle and of its equipment, and/or the position and the movements of the vehicle relative to its environment, the at least one computer receiving the measurements from the sensors and processing the information, wherein the memory stores performance curves of the vehicle and computer instructions, the at least one computer using the computer instructions to perform the method according to claim 1 for determining parameters that are characteristics of the operation of the vehicle.
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이 특허에 인용된 특허 (7)
Francois Daniel Claude,FRX, Aircraft flight indicator.
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