A method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpanded jet of rotating body vehicle

Abstract

The present invention belongs to the technical field of aerodynamic control of aircraft lateral jets, and discloses a method for evaluating the effective range of attitude angles of high temperature effects of lateral underexpanded jets of rotating body aircraft. The method includes: defining the aircraft body coordinate system and circumferential angle, and defining the angle between the aircraft velocity vector and the coordinate plane; calculating the direct force / torque component of the hot jet. The number of jets and their azimuth angles are calibrated, and it is assumed that the jet direction is perpendicular to the x-axis; fitting the aerodynamic force / torque coefficients under cold and hot jet states; calculating the ratio of the difference between the aerodynamic force / torque coefficient fitting functions under cold and hot jet states and the jet direct force / torque coefficient fitting function; and finally evaluating the effective range of attitude angles under high temperature effects of lateral underexpanded jets. Through accurate modeling and calculation of the jet effect, the jet influence under different flight conditions can be effectively evaluated to avoid the problem of failure of the high temperature effect of the underexpanded hot jet.

Description

Technical Field

[0001] The invention belongs to the technical field of aerodynamic control of aircraft lateral jets, and in particular relates to a method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpanded jets of a rotating body aircraft. Background Art

[0002] Lateral jet control is an effective and mature technical solution for aircraft attitude and trajectory control. Depending on the type of jet device installed, the jet can be divided into two control schemes: cold jet and hot jet according to the gas temperature. The temperature difference between the cold jet and the downflow gas under flight conditions is small, while the temperature difference between the hot jet is large. The high temperature effect generated by the hot jet will cause differences in the flow state dominated by expansion in the flow field, thereby affecting the control performance of the jet and the aerodynamic characteristics of the aircraft.

[0003] In actual flight, when the angle of the jet airflow is not perpendicular to the incoming flow, there will be two states: headwind and leeward. When the headwind angle is too large, the airflow after the interference between the underexpanded jet and the incoming flow will wrap part of the aircraft in a certain area near the nozzle and downstream, forming a limited range of jet interference zone; when the leeward angle is too large, as the velocity component of the incoming flow in the normal direction outside the object surface increases, the jet interference zone gradually moves away from the object surface. Both of these situations will cause the high temperature effect of the underexpanded hot jet to fail, and then lead to a decrease in the difference in aerodynamic force and torque between the cold and hot jet states. Therefore, the jet high temperature effect is only effective within a certain attitude angle range. Summary of the invention

[0004] The object of the present invention is to provide a method for evaluating the effective range of the attitude angle of the high temperature effect of the lateral under-expanded jet of a rotating body aircraft in response to the above-mentioned problems, hoping to improve the problem that in actual flight, the effective range of the attitude angle of the high temperature effect of the lateral under-expanded jet cannot be evaluated, thereby causing the high temperature effect of the under-expanded hot jet to fail, and further affecting the jet control design scheme of the rotating body aircraft.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft, the method comprising the following steps: S100: defining the aircraft body coordinate system and the circumferential angle; agreeing that the origin of the coordinate system is O, any direction along the axis of the rotating body aircraft is the x-axis, any direction perpendicular to the x-axis is the y-axis, and the direction of the z-axis is determined by the right-hand rule; agreeing that the y-axis direction is the circumferential angle The positive direction of the x-axis right-hand rule is the direction in which the circumferential angle increases, and the circumferential angle ranges from 0° to 360°. Define the angle between the aircraft velocity vector and the xOy plane, that is, the sideslip angle is , the angle between the projection of the velocity vector on the xOy plane and the x-axis, that is, the angle of attack is ; S200: Calculate the sum of the direct forces and moments of all the hot jet nozzles; where the number of nozzles is recorded as , for an angle of attack of , the sideslip angle is In the state The circumferential angle of the jet is recorded as , the jet exit direction is perpendicular to the x-axis; S300: Fitting the aerodynamic force and moment coefficients under the cold and hot jet states, wherein the aerodynamic force and moment data of the cold and hot jet states are obtained by input; S400: Calculating the function of the absolute value of the ratio of the fitting function of the aerodynamic force and moment coefficients of the cold and hot jet states to the fitting function of the jet direct force and moment coefficients; S500: Evaluating the effective range of the attitude angle of the high temperature effect of the lateral underexpanded jet.

[0007] Further, the sum of the coefficient components is set and its value is calculated according to the formula, and the step S200 includes:

[0008] The direct force coefficient of the thermal jet The components on the y-axis and z-axis are respectively denoted as and :

[0009]

[0010]

[0011] in, is the number of nozzles, The angle of attack is , the sideslip angle is In the state A jet, is the circumferential angle of the nozzle orientation, and the jet emission direction is perpendicular to the x-axis;

[0012] The sum of the thrust components of all jets on the y-axis and z-axis is recorded as and :

[0013]

[0014]

[0015] Record The axial coordinate of the nozzle axis is , the axial coordinate of the center of mass of the aircraft is , For the The axial distance from the jet to the center of mass of the vehicle:

[0016]

[0017] Taking the center of mass as the coordinate origin, calculate the The direct moment coefficients of the jet on the y-axis and z-axis are respectively expressed as and :

[0018]

[0019]

[0020] in, For the The axial distance from the jet to the center of mass of the vehicle is is the sum of the thrust components of the jet on the y-axis, is the sum of the thrust components of the jet on the z-axis;

[0021] The sum of the direct moment coefficients of all jets on the y-axis and z-axis are respectively expressed as and :

[0022]

[0023]

[0024] in, For the The direct moment coefficient of the jet about the y-axis; For the The direct moment coefficient of the jet about the z-axis; is the number of nozzles.

[0025] Further, the components of aerodynamic force and moment under the cold and hot jet states are fitted, and the step S300 includes:

[0026] Each identical Different angles Y-direction force coefficient under angle , z-direction force coefficient , the moment coefficient about the y-axis , torque coefficient about z axis , the sum of the jet direct force coefficients in the y-axis direction , the sum of the jet direct force coefficients in the z-axis direction , the sum of the jet direct moment coefficients about the y-axis The sum of the jet direct moment coefficient about the z axis Data pair Angle fitting;

[0027] Obtain the y-direction force coefficient function that changes with the angle of attack under the hot spray state , z-direction force coefficient function , the torque coefficient function about the y-axis , the torque coefficient function about the z-axis , the function of the sum of the jet direct force coefficients in the y-axis direction , the function of the sum of the jet direct force coefficients in the z-axis direction , the function of the sum of the jet direct moment coefficients about the y-axis Function of the sum of the jet direct moment coefficients about the z axis ;

[0028] And the y-direction force coefficient function under cold spray state changes with the angle of attack , z-direction force coefficient function , the torque coefficient function about the y-axis , the torque coefficient function about the z-axis .

[0029] Further, a function of the absolute value of the ratio of the difference between the aerodynamic force and moment coefficient fitting functions of the cold spray and hot spray states to the jet direct force and moment coefficient fitting functions is calculated, and the step S400 includes:

[0030] The absolute value of the ratio of the difference between the y-direction force coefficient fitting function of the cold spray state and the hot spray state to the sum of the direct force coefficients of the jet in the y-axis direction, the absolute value of the ratio of the difference between the z-direction force coefficient fitting function and the sum of the direct force coefficients of the jet in the z-axis direction, the absolute value of the ratio of the difference between the moment coefficient fitting function about the y-axis and the sum of the direct moment coefficients of the jet about the y-axis, and the absolute value of the ratio of the difference between the moment coefficient fitting function about the z-axis and the sum of the direct moment coefficients of the jet about the z-axis are calculated respectively, and are recorded as , , and :

[0031]

[0032]

[0033]

[0034]

[0035] in, and Respectively represent the minimum and maximum values ​​of the angle of attack in the input aerodynamic force and moment data; is the y-direction force coefficient function under the thermal spray state, is the z-direction force coefficient function under the thermal spray state, is the torque coefficient function of the y-axis under the thermal spray state, is the torque coefficient function about z axis in the thermal spray state, is the function of the sum of the jet direct force coefficients in the y-axis direction under the thermal spray state, is the function of the sum of the direct force coefficients of the jet in the z-axis direction under the thermal spray state, is the function of the sum of the jet direct moment coefficients about the y-axis in the hot spray state, It is a function of the sum of the jet direct moment coefficients about the z axis in the hot spray state; is the y-direction force coefficient function under cold spray state, is the z-direction force coefficient function under cold spray state, is the torque coefficient function of the y-axis under cold spray state, is the torque coefficient function about the z-axis in the cold spray state.

[0036] Furthermore, the step S500 includes:

[0037] Given the effective range of the jet high temperature effect on the aircraft attitude angle, the standards are different When the angle is , the absolute value of the ratio of the difference between the cold and hot spray states in the y direction force coefficient to the sum of the jet direct force coefficients in the y direction is recorded as The absolute value of the ratio of the difference between the z-direction force coefficient and the sum of the jet direct force coefficients in the z-axis direction is recorded as The absolute value of the ratio of the difference of the moment coefficients about the y-axis to the sum of the jet direct moment coefficients about the y-axis is recorded as , and the absolute value of the ratio of the difference between the moment coefficients about the z-axis and the sum of the jet direct moment coefficients about the z-axis is recorded as ;

[0038] Substitute into the function respectively , , and Perform inequality calculations:

[0039]

[0040]

[0041]

[0042]

[0043] in, and Represent the minimum and maximum values ​​of the angle of attack in the input aerodynamic force and moment data, respectively.

[0044] Furthermore, in step S300,

[0045] When the jet directions of all nozzles are consistent with the direction or the opposite direction of the y-axis or z-axis, there will be a situation where the direct force component of the jet in one direction is 0;

[0046] when When , the y-direction force coefficient, the moment coefficient about the z-axis and the jet direct moment coefficient about the z-axis are not considered;

[0047] when When , the z-direction force coefficient, the moment coefficient about the y-axis and the jet direct moment coefficient about the y-axis are not considered;

[0048] in, and are the sum of the thrust components of all jets on the y-axis and z-axis respectively.

[0049] Further, after completing steps S100-S500, all Effectiveness of angular state calculation for high temperature effect of transverse underexpanded jet Angular range, to obtain the effective range of attitude angle of the lateral underexpanded jet high temperature effect of the aircraft under the flight conditions corresponding to the input aerodynamic force and moment coefficient.

[0050] Furthermore, in step S200, component data of the direct force and moment of the thermal jet are obtained by input.

[0051] Furthermore, the range is set according to the actual scenario, and different High temperature effect of lateral underexpanded jet at angle of attack The effective range is marked from small to large according to the angle of attack. , then the effective range of the angle of attack of the underexpanded jet high temperature effect is:

[0052]

[0053]

[0054]

[0055]

[0056] in, is the y-direction force The lower limit of the effective range of the segment angle of attack, is the y-direction force The upper limit of the effective range of the segment angle of attack; is the z-direction force The lower limit of the effective range of the segment angle of attack, is the z-direction force The upper limit of the effective range of the segment angle of attack; is the moment about the z-axis at The lower limit of the effective range of the segment angle of attack, is the moment about the z-axis at The upper limit of the effective range of the segment angle of attack; is the moment about the y-axis at The lower limit of the effective range of the segment angle of attack, is the moment about the z-axis at The upper limit of the valid range of the segment angle of attack.

[0057] Furthermore, in order to fit different scenarios, in step S500, the standard of the effective range of the jet high temperature effect on the aircraft attitude angle is set according to actual needs.

[0058] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0059] 1. By calculating the sum of the components of the direct force and moment of the hot jet, fitting the aerodynamic coefficients under the cold and hot jet states, and calculating the function of the absolute value of the ratio of the fitting functions of the aerodynamic force and moment coefficients of the cold and hot jet states to the fitting functions of the direct force and moment coefficients of the jet, the effective range of the attitude angle of the high temperature effect of the lateral underexpanded jet is evaluated, thereby determining the range of the attitude angle and avoiding the problem of failure of the high temperature effect of the underexpanded hot jet.

[0060] 2. Based on the aerodynamic force and torque data of cold and hot jets under the same flight conditions, the effective range of the attitude angle of the jet high temperature effect is evaluated by the proportion of the difference between the cold and hot jet power and torque in the jet direct force and torque, avoiding the problem of failure of the high temperature effect of the under-expanded hot jet. BRIEF DESCRIPTION OF THE DRAWINGS

[0061] Figure 1 is a flow chart of the method of the present invention;

[0062] Figure 2 is a side view of the aircraft of the present invention;

[0063] Figure 3 It is a front view of the aircraft of the present invention. DETAILED DESCRIPTION

[0064] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0065] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0066] A method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpanded jet of a rotating body aircraft is applicable to the evaluation of the effective range of attitude angle of high temperature effect of the jet of a rotating body aircraft controlled by any number of lateral underexpanded hot jets. Based on the aerodynamic force and torque data of cold and hot jet working conditions under the same flight conditions, the method evaluates the effective range of attitude angle of high temperature effect of the jet by the proportion of the difference between the cold and hot jet power and torque in the direct force and torque of the jet.

[0067] like Figure 1-Figure 3 As shown, the method comprises the following steps:

[0068] S100: According to Figure 2 and Figure 3 The aircraft shown in the figure defines the direction from the tail to the head of the aircraft along the axis of the rotating body as the x-axis, and stipulates that nozzles 1, 2, 3 and 4 are at circumferential angles is 30°, 120°, 210° and 300°, the y-axis points to the circumferential angle 0°, z-axis pointing The angle of the aircraft is 90°, and the clockwise direction of the rear view of the aircraft is the direction in which the circumferential angle increases. In the figure, D represents the diameter of the rotating body aircraft, and CG represents the center of mass position.

[0069] S200: The magnitude and direction of the jet direct force and moment obtained by computational fluid dynamics steady-state calculation are used as data input. The aircraft condition parameters are shown in Table 1. The aircraft reference length is taken as 1m and the reference area is taken as 1m. 2 , only nozzle 1 is opened, and the thermal jet direct force coefficient is shown in Table 2. The distance from nozzle 1 to the center of mass is 0.075m, and the components of the absolute value of the sum of the jet direct force and moment are calculated and shown in Table 3.

[0070] Table 1 Aircraft condition parameters

[0071]

[0072] Table 2 Thermal jet direct force coefficient table

[0073]

[0074] Table 3 Jet direct force and moment components

[0075]

[0076] S300: Fit the aerodynamic force and moment coefficients obtained by the computational fluid dynamics steady-state calculation. The input aerodynamic force and moment coefficients are shown in Table 4. Table 4 includes Table 4-1 and Table 4-2, which respectively list the aerodynamic force and moment coefficients in the hot spray state and the cold spray state. The y-direction force coefficient function of the hot spray state is obtained by fitting the least squares method. , z-direction force coefficient function , the torque coefficient function about the y-axis , the torque coefficient function about the z-axis , y-direction force coefficient function of cold spray state , z-direction force coefficient function , the torque coefficient function about the y-axis , the torque coefficient function about the z-axis , a function of the jet direct force coefficient in the y-axis direction , the function of the jet direct force coefficient in the z-axis direction , the function of the jet direct moment coefficient about the y-axis , the function of the jet direct moment coefficient about the z axis , respectively:

[0077] (1)

[0078] (2)

[0079] (3)

[0080] (4)

[0081] (5)

[0082] (6)

[0083] (7)

[0084] (8)

[0085] (9)

[0086] (10)

[0087] (11)

[0088] (12)

[0089] Table 4 Aerodynamic force and moment coefficients

[0090] Table 4-1 Aerodynamic force and moment coefficients under hot spray conditions

[0091]

[0092] Table 4-2 Aerodynamic force and moment coefficients in cold spray state

[0093]

[0094] S400: A function for calculating the absolute value of the ratio of the difference between the cold spray and hot spray y-direction force coefficient fitting functions and the jet direct force coefficient fitting function in the y-axis direction. , the absolute value of the ratio of the difference between the z-direction force coefficient fitting function and the jet direct force coefficient fitting function in the z-axis direction , the absolute value of the ratio of the difference between the moment coefficient fitting function about the y-axis and the jet direct moment coefficient fitting function about the y-axis Function of the absolute value of the ratio of the difference between the moment coefficient fitting function about the z-axis and the jet direct moment coefficient fitting function about the y-axis :

[0095] (13)

[0096] (14)

[0097] (15)

[0098] (16)

[0099] S500: The standard for the effective range of the attitude angle of the jet high temperature effect is the absolute value of the ratio of the difference between the cold jet and hot jet y-direction force coefficients to the sum of the jet direct force coefficients in the y-axis direction. , the absolute value of the ratio of the difference in z-direction force coefficients to the sum of the jet direct force coefficients in the z-axis direction , the absolute value of the ratio of the difference in moment coefficients about the y-axis to the sum of the jet direct moment coefficients about the y-axis The absolute value of the ratio of the difference between the moment coefficient about the z-axis and the sum of the jet direct moment coefficients about the z-axis Are not less than 2%. Solve the inequality:

[0100] (17)

[0101] Combining formula (13) we get: ; Solve the inequality:

[0102] (18)

[0103] Combining formula (14) we get: ; Solve the inequality:

[0104] (19)

[0105] Combining formula (15) we get: ; Solve the inequality:

[0106] (20)

[0107] Combining formula (16) we get: .

[0108] Finally, it is obtained that for the aircraft under the flight conditions corresponding to the input aerodynamic force and torque coefficient, the attitude angle range in which the difference of the jet high temperature effect on the y-direction force accounts for no less than 2% of the y-direction component of the jet direct force is The attitude angle range in which the difference in the z-direction force influence is not less than 2% of the z-direction component of the jet direct force is The attitude angle range in which the difference in the influence of the aerodynamic torque on the y-axis is not less than 2% of the torque of the jet direct force on the y-axis is The attitude angle range in which the difference in the influence of the aerodynamic torque on the z-axis is not less than 2% of the torque of the jet direct force on the z-axis is .

[0109] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft, characterized in that: The evaluation method comprises the following steps: S100: Define the coordinate system and circumferential angle of the aircraft body; define the origin of the coordinate system as O, any direction along the axis of the rotating body aircraft as the x-axis, any direction perpendicular to the x-axis as the y-axis, and determine the direction of the z-axis by the right-hand rule; define the y-axis direction as the circumferential angle The positive direction of the x-axis right-hand rule is the direction in which the circumferential angle increases, and the circumferential angle ranges from 0° to 360°. Define the angle between the aircraft velocity vector and the xOy plane, that is, the sideslip angle is , the angle between the projection of the velocity vector on the xOy plane and the x-axis, that is, the angle of attack is ; S200: Calculate the sum of the direct forces and moments of all the hot jet nozzles; where the number of nozzles is recorded as , for an angle of attack of , the sideslip angle is In the state The circumferential angle of the jet is recorded as , the jet emission direction is perpendicular to the x-axis; S300: fitting aerodynamic force and moment coefficients under cold and hot jet states, wherein aerodynamic force and moment data under cold and hot jet states are obtained by input; S400: Calculate the function of the absolute value of the ratio of the difference between the aerodynamic force and moment coefficient fitting functions of the cold spray and hot spray states to the jet direct force and moment coefficient fitting functions; S500: Evaluate the effective range of attitude angles for high temperature effects of lateral underexpanded jets; After completing steps S100-S500, Effectiveness of angular state calculation for high temperature effect of transverse underexpanded jet Angular range, to obtain the effective range of attitude angle of the lateral underexpanded jet high temperature effect of the aircraft under the flight conditions corresponding to the input aerodynamic force and moment coefficient.

2. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 1 is characterized in that: The step S200 includes: The direct force coefficient of the thermal jet The components on the y-axis and z-axis are respectively denoted as and : in, is the number of nozzles, The angle of attack is , the sideslip angle is In the state A jet, is the circumferential angle of the nozzle orientation, and the jet emission direction is perpendicular to the x-axis; The sum of the thrust components of all jets on the y-axis and z-axis is recorded as and : Record The axial coordinate of the nozzle axis is , the axial coordinate of the center of mass of the aircraft is , For the The axial distance from the jet to the center of mass of the vehicle: Taking the center of mass as the coordinate origin, calculate the The direct moment coefficients of the jet on the y-axis and z-axis are respectively expressed as and : in, For the The axial distance from the jet to the center of mass of the vehicle is is the sum of the thrust components of the jet on the y-axis, is the sum of the thrust components of the jet on the z-axis; The sum of the direct moment coefficients of all jets on the y-axis and z-axis are respectively expressed as and : in, For the The direct moment coefficient of the jet about the y-axis; For the The direct moment coefficient of the jet about the z-axis; is the number of nozzles.

3. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 1, characterized in that: The step S300 includes: Each identical Different angles Y-direction force coefficient under angle , z-direction force coefficient , the moment coefficient about the y-axis , torque coefficient about z axis , the sum of the jet direct force coefficients in the y-axis direction , the sum of the jet direct force coefficients in the z-axis direction , the sum of the jet direct moment coefficients about the y-axis The sum of the jet direct moment coefficient about the z axis Data pair Angle fitting; Obtain the y-direction force coefficient function that changes with the angle of attack under the hot spray state , z-direction force coefficient function , the torque coefficient function about the y-axis , the torque coefficient function about the z-axis , the function of the sum of the jet direct force coefficients in the y-axis direction , the function of the sum of the jet direct force coefficients in the z-axis direction , the function of the sum of the jet direct moment coefficients about the y-axis Function of the sum of the jet direct moment coefficients about the z axis ; And the y-direction force coefficient function under cold spray state changes with the angle of attack , z-direction force coefficient function , the torque coefficient function about the y-axis , the torque coefficient function about the z-axis .

4. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 3, characterized in that: The step S400 includes: The absolute value of the ratio of the difference between the y-direction force coefficient fitting function of the cold spray state and the hot spray state to the sum of the direct force coefficients of the jet in the y-axis direction, the absolute value of the ratio of the difference between the z-direction force coefficient fitting function and the sum of the direct force coefficients of the jet in the z-axis direction, the absolute value of the ratio of the difference between the moment coefficient fitting function about the y-axis and the sum of the direct moment coefficients of the jet about the y-axis, and the absolute value of the ratio of the difference between the moment coefficient fitting function about the z-axis and the sum of the direct moment coefficients of the jet about the z-axis are calculated respectively, and are recorded as , , and : in, and They represent the minimum and maximum values ​​of the angle of attack in the input aerodynamic force and moment data, respectively; is the y-direction force coefficient function under the hot spray state, is the z-direction force coefficient function under the thermal spray state, is the torque coefficient function of the y-axis under the thermal spray state, is the torque coefficient function about the z-axis under the thermal spray state, is the function of the sum of the jet direct force coefficients in the y-axis direction under the thermal spray state, is the function of the sum of the direct force coefficients of the jet in the z-axis direction under the thermal spray state, is the function of the sum of the jet direct moment coefficients about the y-axis in the hot spray state, It is a function of the sum of the jet direct moment coefficients about the z axis in the hot spray state; is the y-direction force coefficient function under cold spray state, is the z-direction force coefficient function under cold spray state, is the torque coefficient function of the y-axis under cold spray state, is the torque coefficient function about the z-axis under cold spraying state.

5. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 4, characterized in that: The step S500 includes: Given the effective range of the jet high temperature effect on the aircraft attitude angle, the standards are different When the angle is , the absolute value of the ratio of the difference between the cold and hot spray states in the y direction force coefficient to the sum of the jet direct force coefficients in the y direction is recorded as The absolute value of the ratio of the difference between the z-direction force coefficient and the sum of the jet direct force coefficients in the z-axis direction is recorded as The absolute value of the ratio of the difference of the moment coefficients about the y-axis to the sum of the jet direct moment coefficients about the y-axis is recorded as , and the absolute value of the ratio of the difference in moment coefficients about the z-axis to the sum of the jet direct moment coefficients about the z-axis is recorded as ; Substitute into the function respectively , , and Perform inequality calculations: in, and They represent the minimum and maximum values ​​of the angle of attack in the input aerodynamic force and moment data, respectively.

6. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 3, characterized in that: In step S300, When the jet directions of all nozzles are consistent with the direction or opposite direction of the y-axis or z-axis, there will be a situation where the direct force component of the jet in one direction is 0; when When , the y-direction force coefficient, the moment coefficient about the z-axis and the jet direct moment coefficient about the z-axis are not considered; when When , the z-direction force coefficient, the moment coefficient about the y-axis and the jet direct moment coefficient about the y-axis are not considered; in, and are the sum of the thrust components of all jets on the y-axis and z-axis respectively.

7. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 1, characterized in that: In the step S200, component data of the direct force and moment of the thermal jet are obtained by input.

8. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 5, characterized in that: Calculated differently High temperature effect of lateral underexpanded jet at angle of attack The effective range is marked from small to large according to the angle of attack. , then the effective range of the angle of attack of the underexpanded jet high temperature effect is: in, is the y-direction force The lower limit of the effective range of the segment angle of attack, is the y-direction force The upper limit of the effective range of the segment angle of attack; is the z-direction force The lower limit of the effective range of the segment angle of attack, is the z-direction force The upper limit of the effective range of the segment angle of attack; is the moment about the z-axis at The lower limit of the effective range of the segment angle of attack, is the moment about the z-axis at The upper limit of the effective range of the segment angle of attack; is the moment about the y-axis at The lower limit of the effective range of the segment angle of attack, is the moment about the z-axis at The upper limit of the valid range of the segment angle of attack.

9. The method for evaluating the effective range of attitude angle of high temperature effect of lateral underexpansion jet of a rotating body aircraft according to claim 5, characterized in that: In step S500, the standard of the effective range of the jet high temperature effect on the aircraft attitude angle is set according to actual needs.

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