A hypersonic vehicle transverse asymmetry online trim control method

Abstract

The application is a kind of lateral asymmetry online trimming control method of hypersonic aircraft, which comprises the following steps: firstly, constructing a lateral asymmetry hypersonic aircraft model; then, setting a sideslip angle and a roll angle judgment threshold of the hypersonic aircraft in the lateral asymmetry hypersonic aircraft model, detecting the lateral asymmetry of the hypersonic aircraft, judging whether the lateral asymmetry exists, if the lateral asymmetry exists, judging whether the hypersonic aircraft is controllable according to the detected abnormal information, if the hypersonic aircraft is uncontrollable, dynamically controlling the rudder of the hypersonic aircraft through control law reconstruction, and giving a systematic solution of the lateral asymmetry of the hypersonic aircraft from the aspects of asymmetry model construction, detection method, controllability analysis and automatic trimming control law design, so that the roll and sideslip caused by the asymmetry can be corrected without increasing additional trimming surfaces, and the flight safety of the hypersonic aircraft is ensured.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of flight control, and particularly relates to a lateral asymmetry online trimming control method for a hypersonic aircraft. BACKGROUND

[0002] The hypersonic aircraft has high flight speed, high flight altitude and strong penetration capability, can effectively perform high-altitude high-speed reconnaissance and penetration attack, and has an important role in the military field. However, due to the high speed of the hypersonic aircraft, the dynamic pressure on the aircraft body is large, and a small lateral aerodynamic asymmetry of the aircraft body will bring about large asymmetric aerodynamic force and moment. The reasons for the asymmetry of the aircraft body usually include unevenness of the fuselage material, design defects of the wing and the rudder surface, asymmetric elastic deformation of the structure under large dynamic pressure, manufacturing and installation errors of the rudder surface and the like. Due to the characteristics of the hypersonic aircraft itself, the reaction to the small aerodynamic asymmetry is more sensitive than that of other unmanned aerial vehicles, and the lateral aerodynamic asymmetry will seriously affect the flight safety of the hypersonic aircraft, and even cause disastrous consequences such as loss of control of the aircraft. Therefore, the lateral aerodynamic asymmetry is difficult to avoid and should not be ignored in the flight control design.

[0003] After years of research, the flight control of unmanned aerial vehicles has formed a mature flight control theory, and through a large number of engineering practices, a feasible and efficient engineering design method has been formed. In a typical flight control system design, it is usually assumed that the controlled aircraft is a symmetrical layout, that is, the inertia product I xy = I yz = 0, and then the air dynamic force and moment acting on the aircraft are controlled by adjusting the deflection angle of the control aerodynamic rudder surface. For the case of lateral asymmetry, preliminary research work has been carried out for the case of double-engine single-engine shutdown, flight load asymmetry and the like, but there is no multiplier theory or universal solution method for the flight control problem of lateral asymmetry. SUMMARY

[0004] The purpose of the application is to provide a lateral asymmetry online trimming control method for a hypersonic aircraft, so as to solve the problem of lateral asymmetry of the hypersonic aircraft in the prior art.

[0005] The technical scheme of the application is: a lateral asymmetry online trimming control method for a hypersonic aircraft, comprising:

[0006] The flight characteristics of the hypersonic aircraft are set, and a lateral asymmetry model of the hypersonic aircraft is constructed;

[0007] The side slip angle and the roll angle threshold of the hypersonic aircraft are set, the lateral asymmetry of the hypersonic aircraft is detected, the size of the lateral asymmetry of the hypersonic aircraft is judged, and if the set threshold is exceeded, the next step is executed;

[0008] For the detected abnormal information, a controllability condition of the hypersonic vehicle under lateral asymmetry condition is defined, a controllability equation of the hypersonic vehicle under lateral asymmetry condition is established, and controllability of the hypersonic vehicle is judged, if the hypersonic vehicle is judged to be uncontrollable, the next step is executed;

[0009] An online trim control structure under lateral asymmetry is established, a control law under lateral asymmetry is designed, and the control law of the hypersonic vehicle is reconstructed.

[0010] Preferably, the control law reconstruction method of the hypersonic vehicle is:

[0011] n typical working points of the hypersonic vehicle are selected;

[0012] Aerodynamic calculation and wind tunnel test are performed to obtain aerodynamic parameters under the typical working points and force and moment coefficients C iy0 , C il0 , C in0 , i = 1, 2, …, n;

[0013] The controllability equation is solved to obtain the aileron and rudder trim rudder deflection δ ia0 , δ ir0 , i = 1, 2, …, n;

[0014] In actual flight, actual flight data is obtained, and δ a0 , δ r0 is obtained by using the typical working point calculation according to the obtained actual flight data;

[0015] It is judged whether the obtained δ a0 , δ r0 satisfies the trim accuracy requirement, if not, the rudder dynamic control is used to offset the untrimmed force and moment, and the aileron and rudder control amount is:

[0016]

[0017] The aileron and rudder control amount is used to control the rudder-rudder and the hypersonic vehicle;

[0018] The hypersonic vehicle working φ and φ cmd = 0 are subtracted and input into a controller, the hypersonic vehicle working and are subtracted and input into another controller, and then the controller is added to generate new aileron and rudder control amount, and the calculation is repeated.

[0019] Preferably, the δ a0 , δ r0 are calculated by interpolation method.

[0020] Preferably, the hypersonic vehicle flight characteristics are set as:

[0021] The hypersonic vehicle is a six-degree-of-freedom rigid body;

[0022] The influence of engine mass change on the dynamics of the hypersonic vehicle is ignored;

[0023] The center of mass of the hypersonic vehicle always moves on the body axis.

[0024] Preferably, the modeling method of the lateral asymmetric hypersonic vehicle model is:

[0025] The American coordinate system O b (X b , Y b , Z b ) is adopted, the body axis X b is on the symmetry axis of the vehicle, pointing to the head of the hypersonic vehicle; the Z b axis is on the principal plane of symmetry of the hypersonic vehicle, perpendicular to the X b axis, pointing downward; the Y b axis is perpendicular to the principal plane of symmetry of the hypersonic vehicle, forming a right-hand coordinate system;

[0026] The lateral state variables of the hypersonic vehicle are defined to include lateral translation and rotation around the X b , Z b axes S = [v, p, r, φ] T , wherein v is the movement speed of the Y b axis of the vehicle body axis system, p and r are the rotation angular velocities around the X b , Z b axes, respectively, and φ is the roll angle; the control variables of the vehicle are U = [δ a , δ r ] T , δ a , δ r , respectively, are the control amounts of the aileron and rudder channels;

[0027] When the hypersonic vehicle is in flight, the lateral force and moment calculation equations are as follows:

[0028]

[0029] wherein S ref is the reference area of the vehicle, b is the wingspan of the vehicle, V is the airspeed, Q = ρV 2 / 2 is the dynamic pressure on the vehicle, and Cy , C l , C n are side force coefficient, roll moment coefficient, yaw moment coefficient, respectively;

[0030] wherein C y , C l , C n are the calculation equations of:

[0031]

[0032] wherein C y0 , C l0 , C n0 are side force coefficient, roll moment coefficient, yaw moment coefficient, respectively, caused by lateral asymmetry; C yβ , C lβ , C nβ are partial derivatives of side force coefficient C y , roll moment coefficient C l , yaw moment coefficient C n with respect to side slip angle β; are partial derivatives of C y , C l , C n with respect to aileron control amount δ a ; are partial derivatives of C y , C l , C n with respect to rudder control amount δ r ; C lp , C np , C lr , C nr are partial derivatives of C l , C n with respect to roll angle rate p, yaw angle rate r;

[0033] Then the calculation equation of the resultant force and the resultant moment on the lateral side of the hypersonic vehicle is:

[0034]

[0035] Preferably, the lateral asymmetry detection equation of the hypersonic vehicle is:

[0036]

[0037] wherein φ f , β f , is a judgment threshold, is a roll angle, and β is a side slip angle, These are the rates of change of roll angle and heading angle over time, respectively.

[0038] Preferably, the controllability equation of the supersonic vehicle under lateral asymmetry conditions is:

[0039]

[0040] Where, δ amax δ rmax These are: maximum trim allowable rudder deflection for ailerons and rudder, β max For the maximum permissible sideslip angle, C y C l C n Aileron control δ a Partial derivatives of C; y0 C l0 C n0 These are: the lateral force coefficient, rolling moment coefficient, and yaw moment coefficient caused by lateral asymmetry, δ a β0 is the aileron channel control, β0 is the sideslip angle caused by lateral asymmetry, and δ is the aileron channel control. a0 δ r0 These are: the aileron and rudder channel control amounts resulting from lateral asymmetry.

[0041] This application discloses a lateral asymmetric online trim control method for hypersonic vehicles. First, a lateral asymmetric hypersonic vehicle model is constructed. Then, within this model, thresholds are set for the hypersonic vehicle's sideslip angle, roll angle, and rate of change. Lateral asymmetry detection is performed to determine if lateral asymmetry exists. If it does, the detected anomaly information is used to determine whether the hypersonic vehicle is controllable. If it is uncontrollable, the rudder is dynamically controlled through control law reconstruction to correct the roll and sideslip caused by the asymmetry, ensuring the hypersonic vehicle's flight safety. Attached Figure Description

[0042] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0043] Figure 1 This is a schematic diagram of the overall process of this application;

[0044] Figure 2 This is a schematic diagram of the overall control structure of the aircraft control law in this application. Detailed Implementation

[0045] For the purpose, technical solutions and advantages of the embodiments of the present application to be clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

[0046] A transverse asymmetry online trim control method for a hypersonic vehicle, as shown in the figure, comprises the following steps: Figure 1

[0047] Step S100, transverse asymmetry modeling of the hypersonic vehicle

[0048] The flight characteristics of the hypersonic vehicle are set to build the transverse asymmetry hypersonic vehicle model;

[0049] The hypersonic vehicle is modeled based on the following flight characteristics:

[0050] (1) The hypersonic vehicle is a six-degree-of-freedom rigid body;

[0051] (2) The influence of engine mass change on the dynamics of the hypersonic vehicle is ignored;

[0052] (3) The center of mass of the hypersonic vehicle always moves on the body axis.

[0053] The specific modeling method of the transverse asymmetry hypersonic vehicle model is:

[0054] The model is built using the American coordinate system O b (X b , Y b , Z b ), the body axis X b is on the symmetry axis of the vehicle, pointing to the head of the hypersonic vehicle; the Z b axis is on the principal plane of symmetry of the hypersonic vehicle, perpendicular to the X b axis pointing downward; the Y b axis is perpendicular to the principal plane of symmetry of the hypersonic vehicle, forming a right-hand coordinate system;

[0055] The transverse state variables of the hypersonic vehicle are defined to include lateral translation and rotation around the X b , Z b axes S = [v, p, r, φ] T , where v is the movement speed of the Y b axis of the vehicle body axis system, p and r are the rotation angular velocities around the X b , Z b axes, and φ is the roll angle; the control variables of the vehicle are U = [δ a , δ r ] T , δ a , δ r ​The control amount of the aileron and rudder passage, respectively.

[0056] (1) The lateral model of hypersonic vehicle under lateral symmetry condition

[0057] First, the hypersonic vehicle under lateral symmetry condition is analyzed. In ideal case, the aerodynamic shape, weight distribution, engine thrust of the vehicle should be completely symmetric. In the process of hypersonic flight steady straight flight, the aerodynamic force and moment should be symmetric about X b , Z b axis, the gravity should be vertical to the ground in the main symmetry plane of the vehicle, and the point of action and direction of the combined force of engine thrust should be in the main symmetry plane of the vehicle.

[0058] Assuming that the hypersonic vehicle is laterally symmetric, the lateral force and moment balance equations of the hypersonic vehicle are as follows:

[0059]

[0060] Where, m、 q, p, r, w、 are: the mass of the vehicle, the derivative of Y b axis speed with respect to time, the pitch rate, the roll rate, the yaw rate, the Z b axis speed, the derivative of the yaw rate with respect to time, the derivative of the roll rate with respect to time; Y is the aerodynamic force on the Y b axis of the vehicle, G y is the component of gravity on the Y b axis. I zz , I yy , I zz are the three-axis rotational inertia of the vehicle, I xz is the inertia product. M x =L is the roll moment of the vehicle, M z =N is the yaw moment of the vehicle.

[0061] Then, the equation (1) is linearized at the typical operating point, and the lateral linear model of the hypersonic vehicle is obtained as follows: Where, S l =[Δv Δp Δr Δφ] T is the lateral state, U l =[Δδ a Δδ r ] T is the lateral control amount,

[0062] The coefficient matrix is:

[0063]

[0064] (2) Lateral model of hypersonic vehicles under lateral asymmetry conditions

[0065] Due to factors such as non-uniformity of fuselage materials, design defects in wings and control surfaces, asymmetric elastic deformation of the structure under high dynamic pressure, and manufacturing and installation errors of control surfaces, lateral aerodynamic deviations exist in the airframe. Furthermore, due to the inherent characteristics of hypersonic aircraft, the airframe experiences high dynamic pressure, and even small lateral aerodynamic asymmetries will result in significant asymmetric aerodynamic forces and moments. Hypersonic aircraft are more sensitive to even minor aerodynamic asymmetries than other unmanned aerial vehicles (UAVs), and these cannot be ignored when designing flight control systems.

[0066] After considering asymmetric aerodynamic forces and moments, the equations for calculating the lateral forces and moments of a hypersonic vehicle during flight are as follows:

[0067]

[0068] Among them, S ref Let b be the reference area of ​​the aircraft, v be the wingspan of the aircraft, and V be the airspeed. Q = ρV 2 / 2 represents the dynamic pressure exerted on the aircraft, C y C l C n These are the lateral force coefficient, rolling moment coefficient, and yaw moment coefficient, respectively.

[0069] Among them, C y C l C n The calculation equation is as follows:

[0070]

[0071] Among them, C y0 C l0 C n0 These are the lateral force coefficient, rolling moment coefficient, and yaw moment coefficient caused by lateral asymmetry, respectively; C yβ C lβ C nβ The lateral force coefficients C y Rolling moment coefficient C l Yaw moment coefficient C n Partial derivative with respect to the sideslip angle β; C y C l C n Aileron control δ a The partial derivatives; C y C l C n rudder control δ r Partial derivatives of C;lp , C np , C lr , C nr , C l , C n Partial derivative of roll rate p, yaw rate r;

[0072] For the lateral symmetry aircraft, the horizontal steady flight, the lateral force and moment of the fuselage is zero, that is:

[0073]

[0074] For the lateral asymmetry of hypersonic aircraft, due to the asymmetric aerodynamic characteristics, the aircraft will produce additional lateral force, roll distance and yaw moment when flying horizontally, at this time the lateral aerodynamic force or moment is not zero. At this time C y , C l , C n Equivalent calculation can be made as follows:

[0075]

[0076] The calculation equation of the lateral force and moment of the hypersonic aircraft is:

[0077]

[0078] By establishing a lateral asymmetry hypersonic aircraft model, the influence of asymmetric aerodynamic force and moment on the flight of the hypersonic aircraft can be considered comprehensively, so that the flight control system design is more realistic.

[0079] Step S200, the lateral asymmetry detection method of the hypersonic aircraft

[0080] The sideslip angle and roll angle of the hypersonic aircraft and the change rate judgment threshold are set to detect the lateral asymmetry of the hypersonic aircraft;

[0081] If the control is applied by the aileron and rudder trim deflection designed under the ideal symmetric condition, according to formula (6), (7), the lateral force and moment caused by aerodynamic asymmetry will produce sideslip angle, roll and heading angle rate, and finally in the roll angle φ0, sideslip angle β0, the lateral force and moment caused by roll and sideslip will reach a balance state with the aerodynamic asymmetric force and moment, that is, the aircraft maintains a fixed roll and sideslip attitude forward flight.

[0082] Therefore, the detection condition of the lateral asymmetry of the aircraft can be:

[0083]

[0084] wherein φ f , β f , is a judgment threshold, φ is a roll angle, β is a sideslip angle, are a roll angle rate of change over time, a heading angle rate of change over time, respectively. That is, the roll angle and the sideslip angle are greater than the threshold in the equilibrium state, but no obvious roll and heading angle rate is generated.

[0085] The roll and sideslip angles of the hypersonic vehicle are judged by formula (8). If the threshold is not exceeded, it indicates that the roll angle and the sideslip angle are greater than the threshold in the equilibrium state, but no obvious roll and heading angle rate is generated, and the next step is executed. If the threshold is exceeded, it indicates that the roll angle and the sideslip angle are less than the threshold in the equilibrium state, and the roll angle and the sideslip angle need to be corrected.

[0086] Step S300, a hypersonic vehicle lateral asymmetry control method

[0087] When the hypersonic vehicle has lateral aerodynamic asymmetry, the most simple and effective method is to implement flight control law reconstruction, so that the flight control system can compensate for the influence of aerodynamic asymmetry on the aircraft by using control surfaces, thereby ensuring that the aircraft can continue to fly safely.

[0088] The embodiment adopts an active control law reconstruction method,

[0089] For the detected abnormal information, a controllability condition of the hypersonic vehicle under lateral asymmetry condition is defined, a controllability equation of the hypersonic vehicle under lateral asymmetry condition is established, and controllability of the hypersonic vehicle is judged, so that the control law can be modified or redesigned according to the current abnormality, to ensure that the aircraft has the ability to complete the flight task under the abnormal condition.

[0090] The specific steps are as follows:

[0091] (1) Hypersonic vehicle controllability judgment

[0092] The prerequisite for control law reconstruction is to have sufficient control surfaces and effective control force and moment for the detected abnormality, so as to keep the aircraft controllable.

[0093] According to formula (6), to offset the aerodynamic force and moment caused by aerodynamic asymmetry, the aileron deflection δ a , the rudder deflection δ r , the roll angle, and the sideslip angle need to be adjusted to the equilibrium state. Since there are three one-degree polynomial functions of the side force coefficient, the roll moment coefficient, and the yaw moment coefficient in formula (6), but only δ a , δ rTwo control parameters cannot guarantee trim under all conditions. Therefore, the corrections to the roll angle or sideslip angle must be relaxed to achieve lateral balance of the aircraft.

[0094] Taking into account the requirements for the horizontal landing of the hypersonic vehicle and the operation of the related instruments and equipment it carries, this embodiment adopts an appropriate relaxation of the sideslip angle correction to ensure that the wings are level during flight.

[0095] Therefore, the controllability equation of an aircraft under lateral asymmetric conditions can be defined as:

[0096] There is aileron deflection δ a0 rudder deflection δ r0 A smaller sideslip angle β0 makes

[0097]

[0098] Where, δ amax δ rmax These are the maximum trim allowable rudder deflections for the aileron and rudder, respectively, β. max For the maximum permissible sideslip angle, C y0 C l0 C n0 These are: the lateral force coefficient, rolling moment coefficient, and yaw moment coefficient caused by lateral asymmetry, δ a β0 is the aileron channel control, β0 is the sideslip angle caused by lateral asymmetry, and δ is the aileron channel control. a0 δ r0 These are: the aileron and rudder channel controllability resulting from lateral asymmetry, i.e., the controllability of this aerodynamically asymmetric aircraft.

[0099] If it is determined that the hypersonic vehicle is uncontrollable, the next step is to reconstruct the control law.

[0100] Step S400, Hypersonic vehicle control law reconstruction

[0101] Establish a lateral asymmetric online trim control structure, design a lateral asymmetric online trim control law, and reconstruct the control law of the hypersonic vehicle.

[0102] like Figure 2 As shown, the control law reconstruction method for hypersonic vehicles is as follows:

[0103] Step S410: Select n typical operating points of hypersonic vehicles. The specific number of typical operating points can be adaptively selected according to the different types of hypersonic vehicles.

[0104] Step S420: Perform aerodynamic calculations and wind tunnel tests to obtain aerodynamic parameters at typical operating points. C inβThe force and moment coefficient C resulting from asymmetry iy0 C il0 C in0 , i = 1, 2, ..., n;

[0105] Step S430: Solve the controllability equation, i.e., equation (9), to obtain the aileron and rudder trim deflection δ at each typical operating point. ia0 δ ir0 , i = 1, 2, ..., n;

[0106] Step S440: During actual flight, acquire actual flight data, and calculate δ based on the acquired actual flight data using typical operating points. a0 δ r0 ;

[0107] Preferably, δ a0 δ r0 The results are obtained by interpolation at typical operating points. It should be noted that the interpolation method is only one embodiment of the present invention. Methods based on linear / nonlinear fitting of data, methods based on neural network data regression, etc., are also within the scope of protection of this application.

[0108] Step S450, determine the obtained δ a0 δ r0 If the trim accuracy requirements are not met, dynamic rudder control is used to counteract the untrimmed forces and moments, resulting in the following aileron and rudder control values:

[0109]

[0110] Control of the hypersonic vehicle is achieved through aileron and rudder maneuvers, which control the servo-control surfaces and the hypersonic aircraft.

[0111] Step S460, the φ and φ generated by the hypersonic vehicle during operation cmd The result of subtraction (=0) is input into a PID controller to process the output generated by the hypersonic vehicle. and After the subtraction operation is performed, the input is sent to another PID controller. Then, the controller performs addition operations with the two PID controllers respectively to generate new aileron and rudder control values, and then calculates them in a loop.

[0112] By repeatedly adjusting the aileron and rudder control, dynamic control of the rudder is achieved, thereby stabilizing the roll angle φ around 0.

[0113] The application firstly constructs a lateral asymmetry hypersonic vehicle model, and then sets the sideslip angle and roll angle and their change rate threshold values in the lateral asymmetry hypersonic vehicle model to detect the lateral asymmetry of the hypersonic vehicle, judge whether there is lateral asymmetry, if there is, judge whether the hypersonic vehicle is controllable according to the detected abnormal information, if not, dynamically control the rudder of the hypersonic vehicle through control law reconstruction, and give a systematic solution to the lateral asymmetry of the hypersonic vehicle from the aspects of asymmetry model construction, detection method, controllability analysis and automatic trimming control law design, and realize lateral automatic trimming control by using the aileron and rudder of the hypersonic vehicle itself, without adding additional trimming surfaces, so as to correct the roll and sideslip caused by asymmetry and ensure the flight safety of the hypersonic vehicle, and provide an engineering solution for coping with lateral aerodynamic asymmetry in flight test and actual flight mission scenarios.

[0114] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A method for lateral asymmetry on-line trim control of a hypersonic vehicle, characterized in that, The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. Aerodynamic calculation and wind tunnel test are carried out to obtain aerodynamic parameters at typical working points , , , , , , , and force and moment coefficients caused by asymmetry , , , i = 1, 2, …, n; Solving the controllability equation, the aileron and rudder trim deflection at each typical operating point is obtained , , i = 1, 2, …, n; In the actual flight process, actual flight data is acquired, and the trim control rudder deflection is calculated according to the obtained actual flight data and the typical working point , ; whether the obtained 、 satisfies the trim accuracy requirement, if not, the rudder dynamic control is used to offset the untrimmed force and moment, and the aileron and rudder control amounts are obtained as follows: ； The application relates to a control law reconstruction method for a hypersonic vehicle. The high supersonic vehicle working and =0 into a controller, the high supersonic vehicle working and into another controller, and then the controller generates new aileron and rudder control amounts after adding the two controllers, and the calculation is repeated. The application relates to a control law reconstruction method for a hypersonic vehicle. ； wherein , are the aileron, rudder maximum trim allowable deflection, respectively, is the maximum allowable sideslip angle, , , are: , , the partial derivative of the side force coefficient with respect to the aileron control input; , , , are the side force coefficient, roll moment coefficient, yaw moment coefficient, respectively, resulting from the lateral asymmetry, is the aileron channel control input, is the sideslip angle resulting from the lateral asymmetry, , are the aileron, rudder channel control input, respectively, resulting from the lateral asymmetry.

2. The method of claim 1, wherein: The , Obtained by interpolation method calculation through typical working point.

3. The method of claim 1, wherein The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle. The application relates to a control law reconstruction method for a hypersonic vehicle.

4. The method of claim 1, wherein The application relates to a control law reconstruction method for a hypersonic vehicle. With the American coordinate system, the body coordinate system X b Axis in the aircraft symmetry axis, pointing to the head of the hypersonic aircraft; Z b Axis in the main symmetry plane of the hypersonic aircraft, perpendicular to X b Axis pointing downward; Y b Axis perpendicular to the main symmetry plane of the hypersonic aircraft, forming a right-hand coordinate system; The lateral and directional state variables of a hypersonic vehicle are defined as the lateral translation and rotation about the X b b Y b b b roll angle;​​​​​​​ The aircraft control variables are , , are the aileron and rudder channel control amounts, respectively. The application relates to a control law reconstruction method for a hypersonic vehicle. ； wherein, is the reference area of the aircraft, b is the wingspan of the aircraft, V is the airspeed, is the dynamic pressure experienced by the aircraft, , , are the side force coefficient, the roll moment coefficient, the yaw moment coefficient, respectively; wherein , , the calculation equation is: ； wherein , , are the side force coefficient, the roll moment coefficient, the yaw moment coefficient, respectively, caused by the lateral asymmetry; , , are the partial derivatives of the side force coefficient , the roll moment coefficient , the yaw moment coefficient with respect to the sideslip angle ; , , are the partial derivatives of the side force coefficient , , with respect to the aileron control ; , , are the partial derivatives of the side force coefficient , , with respect to the rudder control ; , , , are the partial derivatives of the side force coefficient , with respect to the roll rate p, the yaw rate r; The application relates to a control law reconstruction method for a hypersonic vehicle. 。 5. 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