CN106777573B - Simulation method for landing range of aircraft air-drop emptying auxiliary fuel tank - Google Patents
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Abstract
A simulation method for the landing range of an air drop-down auxiliary fuel tank of an airplane comprehensively analyzes the influence of factors such as the flight height, the speed, the attitude angle, the atmospheric wind speed and the like of the airplane on the drop-in motion track of the air drop-down auxiliary fuel tank by researching the motion mechanism of the air drop-down auxiliary fuel tank of the airplane, calculates the pneumatic characteristic of the auxiliary fuel tank, the separation characteristic of an external object of the air drop-in auxiliary fuel tank of the airplane and the initial flight parameters of the drop-in air drop-in auxiliary fuel tank, establishes a flight track simulation model of the drop-in air drop-in auxiliary fuel tank by combining the mass characteristic of the air drop-in auxiliary fuel tank, obtains the parameters in the simulation model by numerical calculation or experimental measurement of a computer, finally obtains the landing range result of the air drop-in auxiliary fuel tank by real-time simulation calculation, further determines the flight airspace range, is efficient and rapid, and the calculated landing, providing support for determining flight airspace.
Description
Technical Field
The invention relates to the technical field of aviation delivery range calculation simulation, in particular to a method for simulating the landing range of an aircraft aerial delivery emptying auxiliary fuel tank.
Background
At present, the research aiming at the aerial release of the hangings of the airplane mainly comprises two aspects: firstly, when throwing external hanging objects such as an auxiliary fuel tank, a conventional bomb, a guided weapon and the like, whether the airplane collides with the external hanging objects or not can be judged; and the second is the research of the trajectory and guidance technology, such as the range and the hit precision of the conventional externally hung weapons such as bombs and guided weapons after being thrown and launched. Although the problem of throwing safety separated from the airplane in the throwing process can be considered in the air-throwing and air-emptying auxiliary fuel tank of the airplane, the throwing track of the air-emptying auxiliary fuel tank from the airplane to the landing is not researched in a relevant way because the air-emptying auxiliary fuel tank does not belong to a weapon. Meanwhile, the size and the volume of the empty auxiliary fuel tank are relatively large, so that the weight is light after fuel oil is used up, and after the empty auxiliary fuel tank is thrown into the air of the airplane, the range of the possible landing points of the empty auxiliary fuel tank is large under the influence of airflow interference, initial throwing altitude speed and atmospheric wind speed of the airplane. In the past, in order to avoid densely populated areas to guarantee safety of people and property, a large airspace field with waste people smoke is generally selected when the auxiliary fuel tank is thrown and emptied, but the difficulty of selecting a large airspace is increased at the present of high-speed development in cities and countryside and increase of civil airline, and higher limit requirements are provided for the allowable airspace, so that the landing range of the auxiliary fuel tank thrown and emptied in the air by an airplane needs to be predicted, and a reference is provided for selecting the airspace size. From published documents, a simulation method for the landing range of the aircraft air drop-in empty auxiliary fuel tank is lacked at present, and the refinement degree of the drop-in flight airspace planning is still to be improved.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a simulation method for the landing range of the aircraft air drop-in empty drop-out auxiliary fuel tank, so as to solve the defects in the background technology.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a method for simulating the falling range of an aircraft air-drop emptying auxiliary fuel tank comprises the following specific steps:
1) calculating the aerodynamic characteristics of the drop tank
According to the geometric shape of the auxiliary oil tank, the aerodynamic characteristics of the auxiliary oil tank are obtained by adopting CFD numerical calculation, the aerodynamic characteristics of the auxiliary oil tank comprise a lift coefficient, a drag coefficient, a pitching moment coefficient, a lateral force coefficient, a rolling moment coefficient and a yawing moment coefficient which change along with the attack angle and the Mach number, the maximum cross-sectional area of the auxiliary oil tank is taken according to the reference area, and the total length of the auxiliary oil tank is taken according to the reference length; the related pneumatic characteristics of the auxiliary oil tank can also be obtained through a wind tunnel test;
2) calculating the separation characteristic of the external hanging object of the auxiliary fuel tank of the air input and discharge of the aircraft
According to the aerodynamic characteristics of the airplane, the aerodynamic characteristics of the auxiliary fuel tank and the quality characteristics of the empty auxiliary fuel tank, calculating the separation characteristics of the external hanging objects of the airplane in the process of throwing the empty auxiliary fuel tank of the airplane under the influence of the flow field of the airplane by adopting a CFD numerical method to obtain the flight Mach number and the attack angle of the airplane for ensuring the throwing separation safety of the empty auxiliary fuel tank, and simultaneously obtaining the throwing separation initial speed, the attack angle and the attitude angle parameters of the empty auxiliary fuel tank relative to the airplane; the separation characteristic of the plug-in of the aircraft dropped-in empty auxiliary fuel tank can also be obtained through a wind tunnel test;
3) calculating initial flight parameters of auxiliary fuel tank when throwing
According to the separation characteristic of the plug-in of the aircraft drop-in and air-release bellytank, the flight height, speed and attitude angle of the aircraft are given within the limit range of Mach number and attack angle of the aircraft drop-in and air-release bellytank, and the initial flight parameters of the initial speed, height and attitude angle of the drop-in and air-release bellytank are calculated by combining the initial state of the drop-in of the air-release bellytank relative to the aircraft;
4) flight path simulation model for establishing aircraft air-drop time-space auxiliary fuel tank
According to the initial speed of the empty drop tank relative to the body axis of the airplane, the flying height, speed and attitude angle of the airplane are combined, and the influence of the superposed atmospheric wind speed is considered, so that the speed of the empty drop tank relative to the ground axis is obtained when the empty drop tank is thrown:
VxE_0＝V0×cosθ+V1+Vwx
VyE_0＝V0×sinθ+Vwy
wherein, VxE_0Initial forward speed relative to the ground shaft when the empty auxiliary oil tank is thrown;
VyE_0relative earth axis when throwing empty auxiliary oil tankThe initial normal velocity of;
V1the vacuum speed of the plane flight of the airplane;
Vwxthe horizontal component of the atmospheric wind speed relative to the earth axis;
Vwyis the vertical component of the atmospheric wind speed relative to the earth axis;
when the empty auxiliary oil tank is put in, the vacuum speed V of the empty auxiliary oil tankqInitial velocity V of the empty drop tank relative to the aircraft body axis0Vacuum speed V for plane flight with airplane1Vector sum of, i.e. forward speed V relative to earth axis when empty drop tank is droppedxE_0Normal velocity V with respect to earth axisyE_0The sum of the vectors of (a) and (b),
after the auxiliary air oil tank is put in, the horizontal speed is reduced due to the influence of aerodynamic force and self weight, the descending speed is gradually increased, and the height is reduced until the auxiliary air oil tank falls to the ground;
the aerodynamic force of the air drop tank during the whole flight is calculated as:
D＝cx×q×S；L＝cy×q×S；
aerodynamic coefficient c of auxiliary fuel tankx、cyAccording to the Mach number M value of the current state, carrying out interpolation calculation to obtain the Mach number M value; quick press
Rho is the atmospheric density of the air pressure height;
the trajectory angle phi of the empty fuel tank in the whole flight process is calculated as follows:
wherein, VxEThe horizontal speed of the empty auxiliary oil tank on the ground shaft system is positive when the horizontal direction is forward;
VyEthe vertical speed of the empty auxiliary oil tank on the ground axis system is positive vertically upwards;
the resultant force of the empty auxiliary fuel tank in the whole flying process is decomposed to the components on the earth axis system as follows:
FxE＝－L×sinφ－D×cosφ；
FyE＝L×cosφ－D×sinφ－G；
wherein, FxEThe horizontal component of the force of the empty auxiliary oil tank on the ground axis system is positive horizontally forwards;
FyEthe vertical component of the force of the empty auxiliary oil tank on the ground axis is positive in the vertical direction;
the flight acceleration of the empty fuel tank on the earth axis during the whole flight process is as follows:
axE＝FxE/m；
ayE＝FyE/m；
wherein m is the mass of the empty auxiliary oil tank;
axEthe horizontal acceleration of the empty auxiliary oil tank on the ground shaft system is positive in the horizontal forward direction;
ayEthe vertical acceleration of the empty auxiliary oil tank on the ground axis system is positive in the vertical direction;
according to the acceleration on the ground axis, the flight speed on the ground axis is obtained by integration as follows:
VxE＝∫axEdt；
VyE＝∫ayEdt；
then, according to the speed of the ground shafting, the flight distance on the ground shafting is obtained by integration as follows:
Lx＝∫VxEdt；
Ly＝∫VyEdt；
by numerical integration iteration, the vertical distance L of the auxiliary fuel tank when emptyyWhen the variable quantity is equal to the initial height of the empty drop tank when the empty drop tank is thrown in, the empty drop tank falls to the ground, and the flying horizontal distance of the empty drop tank is Lx；
The calculation method of the lateral distance of the air-drop fuel tank is consistent with the calculation method of the flying horizontal distance of the air-drop fuel tank, only the initial horizontal speed is replaced by the corresponding initial lateral speed and the influence of atmospheric crosswind is superposed, so that a flying track simulation model of the air-drop fuel tank of the airplane is established, and then simulation parameters are input into the flying track simulation model, so that the falling range of the air-drop fuel tank of the airplane is obtained.
Has the advantages that: according to the method, the flight trajectory simulation model for throwing the space-time auxiliary fuel tank is established by calculating the pneumatic characteristic of the auxiliary fuel tank, the external hanging separation characteristic of the aircraft throwing air auxiliary fuel tank and the initial flight parameters of the throwing space-time auxiliary fuel tank and combining the mass characteristic of the air auxiliary fuel tank, and the simulation parameters are input into the flight trajectory simulation model, so that the landing range of the aircraft throwing air auxiliary fuel tank is obtained, the method is efficient and rapid, the calculated landing range is accurate, and support is provided for determining a flight airspace.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
A simulation method for the landing range of an air drop-down auxiliary fuel tank of an airplane comprehensively analyzes the influence of factors such as the flight height, the speed, the attitude angle and the atmospheric wind speed of the airplane on the drop-in motion track of the air drop-down auxiliary fuel tank by researching the motion mechanism of the air drop-down auxiliary fuel tank of the airplane, calculates the pneumatic characteristic of the auxiliary fuel tank, the separation characteristic of an external object of the air drop-in auxiliary fuel tank of the airplane and the initial flight parameters of the air drop-in auxiliary fuel tank, establishes a flight track simulation model of the air drop-in auxiliary fuel tank by combining the quality characteristic of the air drop-in auxiliary fuel tank, obtains the parameters in the simulation model by the numerical calculation or experimental measurement of a computer, and finally calculates the flight parameters such as the flight height, the track, the attitude, the speed, the time and the like of the air drop-down auxiliary fuel tank by real; the method comprises the following specific steps:
1) calculating the aerodynamic characteristics of the drop tank
According to the geometric shape of the auxiliary oil tank, the aerodynamic characteristics of the auxiliary oil tank are obtained by adopting CFD numerical calculation, the aerodynamic characteristics mainly comprise a lift coefficient, a resistance coefficient, a pitching moment coefficient, a lateral force coefficient, a rolling moment coefficient and a yawing moment coefficient which change along with the attack angle and the Mach number, the maximum cross-sectional area of the auxiliary oil tank is taken according to the reference area, and the total length of the auxiliary oil tank is taken according to the reference length; the related pneumatic characteristics of the auxiliary oil tank can also be obtained through a wind tunnel test;
2) calculating the separation characteristic of the external hanging object of the auxiliary fuel tank of the air input and discharge of the aircraft
According to the aerodynamic characteristics of the airplane, the aerodynamic characteristics of the auxiliary fuel tank and the quality characteristics of the empty auxiliary fuel tank, calculating the separation characteristics of the external stores of the airplane in the process of throwing the empty auxiliary fuel tank of the airplane under the influence of the flow field of the airplane by adopting a CFD numerical method, obtaining the flight Mach number and the attack angle of the airplane for ensuring the throwing separation safety of the empty auxiliary fuel tank through calculation, and simultaneously obtaining the throwing separation initial speed, the attack angle and the attitude angle parameters of the empty auxiliary fuel tank relative to the airplane; the separation characteristic of the plug-in of the aircraft dropped-in empty auxiliary fuel tank can also be obtained through a wind tunnel test;
3) calculating initial flight parameters of auxiliary fuel tank when throwing
According to the separation characteristic of the plug-in of the aircraft drop-in and air-release bellytank, the flight height, speed and attitude angle of the aircraft are given within the limit range of Mach number and attack angle of the aircraft drop-in and air-release bellytank, and the initial flight parameters of the initial speed, height and attitude angle of the drop-in and air-release bellytank are calculated by combining the initial state of the drop-in of the air-release bellytank relative to the aircraft;
4) flight trajectory simulation model for building throwing time-space auxiliary fuel tank
According to the initial speed of the throwing of the empty bellytank relative to the body axis of the airplane, the flying height, speed and attitude angle of the airplane are combined, and the influence of the superposed atmospheric wind speed is considered, so that the speed of the empty bellytank relative to the ground axis when the empty bellytank is thrown is calculated:
VxE_0＝V0×cosθ+V1+Vwx
VyE_0＝V0×sinθ+Vwy
wherein, VxE_0Initial forward speed relative to the ground shaft when the empty auxiliary oil tank is thrown;
VyE_0initial normal speed relative to the earth axis when the empty auxiliary oil tank is thrown;
V1the vacuum speed of the plane flight of the airplane;
Vwxthe horizontal component of the atmospheric wind speed relative to the earth axis;
Vwyis the vertical component of the atmospheric wind speed relative to the earth axis;
when the empty auxiliary oil tank is put in, the vacuum speed V of the empty auxiliary oil tankqInitial velocity V of the empty drop tank relative to the aircraft body axis0Vacuum speed V for plane flight with airplane1Vector sum of, i.e. forward speed V relative to earth axis when empty drop tank is droppedxE_0Normal velocity V with respect to earth axisyE_0Vector sum of (c):
after the auxiliary air oil tank is put in, the horizontal speed is reduced due to the influence of aerodynamic force and self weight, the descending speed is gradually increased, and the height is reduced until the auxiliary air oil tank falls to the ground;
the aerodynamic force of the air drop tank during the whole flight is calculated as:
D＝cx×q×S；L＝cy×q×S；
aerodynamic coefficient c of auxiliary fuel tankx、cyAccording to the Mach number M value of the current state, carrying out interpolation calculation to obtain the Mach number M value; quick press
Rho is the atmospheric density of the air pressure height;
the trajectory angle phi of the empty fuel tank in the whole flight process is calculated as follows:
wherein, VxEThe horizontal speed of the empty auxiliary oil tank on the ground shaft system is positive when the horizontal direction is forward;
VyEthe vertical speed of the empty auxiliary oil tank on the ground axis system is positive vertically upwards;
the resultant force of the empty auxiliary fuel tank in the whole flying process is decomposed to the components on the earth axis system as follows:
FxE＝－L×sinφ－D×cosφ；
FyE＝L×cosφ－D×sinφ－G；
wherein, FxEThe horizontal component of the force of the empty auxiliary oil tank on the ground axis system is positive horizontally forwards;
FyEthe vertical component of the force of the empty auxiliary oil tank on the ground axis is positive in the vertical direction;
the flight acceleration of the empty fuel tank on the earth axis during the whole flight process is as follows:
axE＝FxE/m；
ayE＝FyE/m；
wherein m is the mass of the empty auxiliary oil tank;
axEthe horizontal acceleration of the empty auxiliary oil tank on the ground shaft system is positive in the horizontal forward direction;
ayEthe vertical acceleration of the empty auxiliary oil tank on the ground axis system is positive in the vertical direction;
according to the acceleration on the ground axis, the flight speed on the ground axis is obtained by integration as follows:
VxE＝∫axEdt；
VyE＝∫ayEdt；
then, according to the speed of the ground shafting, the flight distance on the ground shafting is obtained by integration as follows:
Lx＝∫VxEdt；
Ly＝∫VyEdt；
by numerical integration iteration, the vertical distance L of the auxiliary fuel tank when emptyyWhen the variable quantity is equal to the initial height of the empty drop tank when the empty drop tank is thrown in, the empty drop tank falls to the ground, and the flying horizontal distance of the empty drop tank is Lx；
The calculation method of the lateral distance of the air-drop fuel tank is consistent with the calculation method of the flying horizontal distance of the air-drop fuel tank, only the initial horizontal speed is replaced by the corresponding initial lateral speed and the influence of atmospheric crosswind is superposed, so that a flight path simulation model for throwing the air-drop fuel tank is established, the air-drop fuel tank throwing range is calculated according to the simulation method under the condition that the atmospheric wind speed is 30m/s by taking the case that the aircraft flies at the flying height of 3km and the surface speed of 600km/h for throwing the air-drop fuel tank, namely the required field area for throwing the air-drop fuel tank is 6.1km multiplied by 4.4km, and support is provided for determining a flying airspace.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (4)
1. A simulation method for the falling range of an aircraft air-drop emptying auxiliary fuel tank is characterized by comprising the following specific steps:
1) calculating the aerodynamic characteristics of the drop tank
According to the geometric shape of the auxiliary oil tank, the aerodynamic characteristics of the auxiliary oil tank are obtained by adopting CFD numerical calculation, and the aerodynamic characteristics of the auxiliary oil tank comprise a lift coefficient, a drag coefficient, a pitching moment coefficient, a lateral force coefficient, a rolling moment coefficient and a yawing moment coefficient which change along with the attack angle and the Mach number;
2) calculating the separation characteristic of the external hanging object of the auxiliary fuel tank of the air input and discharge of the aircraft
According to the aerodynamic characteristics of the airplane, the aerodynamic characteristics of the auxiliary fuel tanks and the quality characteristics of the empty auxiliary fuel tanks, a CFD numerical method is adopted to calculate the external hanging object separation characteristics of the airplane in the process of throwing the empty auxiliary fuel tanks of the airplane under the influence of the flow field of the airplane, so that the flying Mach number and the attack angle of the airplane for ensuring the throwing separation safety of the empty auxiliary fuel tanks are obtained, and meanwhile, the throwing separation initial speed, the attack angle and the attitude angle parameters of the empty auxiliary fuel tanks relative to the airplane are obtained;
3) calculating initial flight parameters of auxiliary fuel tank when throwing
According to the separation characteristic of the plug-in of the aircraft drop-in and air-release bellytank, the flight height, speed and attitude angle of the aircraft are given within the limit range of Mach number and attack angle of the aircraft drop-in and air-release bellytank, and the initial flight parameters of the initial speed, height and attitude angle of the drop-in and air-release bellytank are calculated by combining the initial state of the drop-in of the air-release bellytank relative to the aircraft;
4) flight path simulation model for establishing aircraft air-drop time-space auxiliary fuel tank
According to the initial speed of the empty drop tank relative to the body axis of the airplane, the flying height, speed and attitude angle of the airplane are combined, and the influence of the superposed atmospheric wind speed is considered, so that the speed of the empty drop tank relative to the ground axis is obtained when the empty drop tank is thrown:
VxE_0＝V0×cosθ+V1+Vwx
VyE_0＝V0×sinθ+Vwy
wherein, VxE_0Initial forward speed relative to the ground shaft when the empty auxiliary oil tank is thrown;
VyE_0initial normal speed relative to the earth axis when the empty auxiliary oil tank is thrown;
V1the vacuum speed of the plane flight of the airplane;
Vwxthe horizontal component of the atmospheric wind speed relative to the earth axis;
Vwyis the vertical component of the atmospheric wind speed relative to the earth axis;
when the empty auxiliary oil tank is put in, the vacuum speed V of the empty auxiliary oil tankqInitial velocity V of the empty drop tank relative to the aircraft body axis0Vacuum speed V for plane flight with airplane1Vector sum of, i.e. forward speed V relative to earth axis when empty drop tank is droppedxE_0Normal velocity V with respect to earth axisyE_0The sum of the vectors of (a) and (b),
after the auxiliary air oil tank is put in, the horizontal speed is reduced due to the influence of aerodynamic force and self weight, the descending speed is gradually increased, and the height is reduced until the auxiliary air oil tank falls to the ground;
the aerodynamic force of the air drop tank during the whole flight is calculated as:
D＝cx×q×S；L＝cy×q×S；
wherein, aerodynamic coefficient c of the auxiliary oil tankx、cyAccording to the Mach number M value of the current state, carrying out interpolation calculation to obtain the Mach number M value; quick press
Rho is the atmospheric density of the air pressure height;
the trajectory angle phi of the empty fuel tank in the whole flight process is calculated as follows:
wherein, VxEThe horizontal speed of the empty auxiliary oil tank on the ground shaft system is positive when the horizontal direction is forward;
VyEthe vertical speed of the empty auxiliary oil tank on the ground axis system is positive vertically upwards;
the resultant force of the empty auxiliary fuel tank in the whole flying process is decomposed to the components on the earth axis system as follows:
FxE＝－L×sinφ－D×cosφ；
FyE＝L×cosφ－D×sinφ－G；
wherein, FxEThe horizontal component of the force of the empty auxiliary oil tank on the ground axis system is positive horizontally forwards;
FyEthe vertical component of the force of the empty auxiliary oil tank on the ground axis is positive in the vertical direction;
the flight acceleration of the empty fuel tank on the earth axis during the whole flight process is as follows:
axE＝FxE/m；
ayE＝FyE/m；
wherein m is the mass of the empty auxiliary oil tank;
axEhorizontal acceleration of empty auxiliary fuel tank on the earth's axisHorizontal forward is positive;
ayEthe vertical acceleration of the empty auxiliary oil tank on the ground axis system is positive in the vertical direction;
according to the acceleration on the ground axis, the flight speed on the ground axis is obtained by integration as follows:
VxE＝∫axEdt；
VyE＝∫ayEdt；
then, according to the speed of the ground shafting, the flight distance on the ground shafting is obtained by integration as follows:
Lx＝∫VxEdt；
Ly＝∫VyEdt；
by numerical integration iteration, the vertical distance L of the auxiliary fuel tank when emptyyWhen the variable quantity is equal to the initial height of the empty drop tank when the empty drop tank is thrown in, the empty drop tank falls to the ground, and the flying horizontal distance of the empty drop tank is Lx；
The calculation method of the lateral distance of the air-drop fuel tank is consistent with the calculation method of the flying horizontal distance of the air-drop fuel tank, only the initial horizontal speed is replaced by the corresponding initial lateral speed and the influence of atmospheric crosswind is superposed, so that a flying track simulation model of the air-drop fuel tank of the airplane is established, and then simulation parameters are input into the flying track simulation model, so that the falling range of the air-drop fuel tank of the airplane is obtained.
2. The method for simulating the landing range of the aircraft drop-in-air drop-out drop tank as claimed in claim 1, wherein in the step 1), the reference area of the geometric shape of the drop tank is the maximum cross-sectional area of the drop tank, and the reference length is the total length of the drop tank.
3. The method for simulating the landing range of the aircraft drop-in air auxiliary fuel tank as claimed in claim 1, wherein in the step 1), the relevant aerodynamic characteristics of the auxiliary fuel tank can be obtained by a wind tunnel test.
4. The method for simulating the landing range of the aircraft drop-in passenger fuel tank as claimed in claim 1, wherein in the step 2), the separation characteristic of the plug-in of the aircraft drop-in passenger fuel tank can be obtained by a wind tunnel test.
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