Flight performance analysis and evaluation method and simulation test system of morphing aircraft

Abstract

The embodiment of the invention discloses a flight performance analysis and evaluation method and a simulation test system for a morphing aircraft, and the method comprises the steps: obtaining a pneumatic pulling deviation range and a core evaluation index through the analysis of the body pneumatic data in the deformation process of the morphing aircraft, building a flight performance test action library of the morphing aircraft, and carrying out the simulation test of the morphing aircraft. Selecting at least one group of test actions from the flight performance test action library to carry out a desktop simulation test; based on the aerodynamic parameter bias matrix, the variant aircraft is controlled to execute the selected test action in the desktop simulation test process, and flight data of the variant aircraft executing the test action is recorded in real time in the desktop simulation test process; and calculating a core evaluation index according to the flight data so as to evaluate the flight performance of the morphing aircraft. The technical scheme provided by the embodiment of the invention solves the problems that if a flight performance analysis and evaluation mode of a conventional aircraft is applied to the morphing aircraft, a large number of wind tunnel tests and simulation calculation need to be carried out due to large dependence on the accuracy of a morphing aircraft simulation model, so that the performance evaluation workload is increased, and the performance evaluation cost is reduced. The working cost is increased, and the working efficiency is relatively low.

Description

Technical Field

[0001] The present invention relates to, but is not limited to, the field of aviation testing technology, and in particular to a flight performance analysis and evaluation method and a simulation test system for a variant aircraft. Background Art

[0002] Morphing aircraft is an important development direction for future aircraft to expand their flight envelope and improve their flight capabilities. However, due to the existence of the morphing mechanism, the flight state of a morphing aircraft is much more complicated than that of a conventional aircraft. This complexity is reflected in the fact that the actual flight state of the aircraft is often quite different from the simulation model, especially during the deformation process.

[0003] If the flight performance analysis and evaluation method of conventional aircraft is applied to variant aircraft, the accuracy of the variant aircraft simulation model will be highly dependent. In order to obtain accurate aerodynamic data, a large number of wind tunnel tests or simulation calculations are often required to obtain the variant aircraft simulation model. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned technical problems, the embodiments of the present invention provide a flight performance analysis and evaluation method and a simulation test system for a variant aircraft, so as to solve the problem that the flight performance analysis and evaluation method of a conventional aircraft is applied to a variant aircraft. Due to the heavy reliance on the accuracy of the simulation model of the variant aircraft, a large number of wind tunnel tests and simulation calculations are required, which leads to an increase in the workload of performance evaluation, an increase in work costs, and low work efficiency.

[0005] Technical solution of the present invention: In a first aspect, an embodiment of the present invention provides a flight performance analysis and evaluation method of a variant aircraft, comprising:

[0006] By analyzing the aerodynamic data of the variant aircraft during its deformation process, the aerodynamic deviation range and core evaluation indicators are obtained, and a flight performance test action library for the variant aircraft is established. At least one group of test actions are selected from the flight performance test action library to carry out desktop simulation test experiments. Based on the aerodynamic parameter deviation matrix, the variant aircraft is controlled to perform the selected test actions during the desktop simulation test, and the flight data of the variant aircraft performing the test actions is recorded in real time during the desktop simulation test. The core evaluation indicators are calculated based on the flight data to evaluate the flight performance of the variant aircraft.

[0007] Optionally, the flight performance analysis and evaluation method of the variant aircraft as described above includes the following steps:

[0008] Step 1: Determine the range of aerodynamic deviation by analyzing the aerodynamic data of the main body of the variant aircraft during its deformation process; and set core evaluation indicators in combination with the design requirements of the variant aircraft;

[0009] Step 2, establishing a flight performance test action library for variant aircraft;

[0010] Step 3, generating an aerodynamic parameter deviation matrix according to the range of aerodynamic deviation and the variant aircraft simulation model, deflecting the aerodynamic derivatives in the variant aircraft simulation model, and generating aerodynamic data after deflection;

[0011] Step 4, randomly selecting at least one set of test actions from the flight performance test action library of the variant aircraft, combining the aerodynamic data after deflection obtained in step 3, performing a desktop simulation test, and recording the flight data of the variant aircraft in the simulation test; wherein, during the desktop simulation test, the variant aircraft is controlled to perform the selected test actions, and the flight data of the variant aircraft during the test actions is recorded in real time during the desktop simulation test;

[0012] Step 5: Calculate the core evaluation indicators based on the flight data recorded during the desktop simulation test for evaluation.

[0013] Optionally, in the flight performance analysis and evaluation method of the variant aircraft as described above, step 1 comprises:

[0014] Step 11, determining a range of aerodynamic deviation according to a range in which actual aerodynamic parameters of the variant aircraft simulation model deviate from aerodynamic parameters of the static configuration during the deformation process;

[0015] Step 12, based on the flight performance requirements of the variant aircraft, the configuration switching during the deformation process, and the need to maintain controllable and stable flight capabilities during the control mode switching process, set the core evaluation indicators.

[0016] Optionally, in the flight performance analysis and evaluation method of the variant aircraft as described above, step 2 comprises:

[0017] According to the flight mission of the variant aircraft and the flight actions of the variant aircraft during the transformation process, a flight performance test action library of the variant aircraft is constructed; wherein the flight actions in the flight performance test action library include: wing deployment, wing folding, fixed pitch angle climb, constant speed climb, roll, left yaw, right yaw, left roll, right roll, fixed pitch angle dive, constant speed dive, and level flight.

[0018] Optionally, in the flight performance analysis and evaluation method of the variant aircraft as described above, step 3 comprises:

[0019] Step 31, according to the range of aerodynamic deflection, the variant aircraft simulation model and the design requirements of aerodynamic deflection, the number of simulations is set, and a random number generation method is adopted to generate an aerodynamic parameter deflection matrix;

[0020] Step 32, after the aerodynamic parameter deviation matrix is ​​input into the variant aircraft simulation model, the aerodynamic parameter deviation matrix is ​​multiplied by the corresponding aerodynamic derivative in the variant aircraft simulation model to generate the deflected aerodynamic data.

[0021] Optionally, in the flight performance analysis and evaluation method of the variant aircraft as described above, step 4 comprises:

[0022] Step 41, randomly select at least one set of test actions from the flight performance test action library of the variant aircraft, and generate a flight action sequence from the at least one set of test actions

[0023] Step 42, setting a flight mission according to the flight action sequence generated in step 41, and performing a desktop simulation test based on the flight mission and the aerodynamic data after the deflection;

[0024] Step 43, during the desktop simulation test, the variant aircraft is controlled to execute the selected test action, and the flight data of the variant aircraft executing the test action is recorded in real time during the desktop simulation test.

[0025] Optionally, in the flight performance analysis and evaluation method of the variant aircraft as described above, before step 5, the method further includes:

[0026] Step 5a, performing a desktop simulation test by repeatedly executing steps 3 to 4 to generate different aerodynamic parameter deflection matrices and their corresponding aerodynamic data after deflection, and recording multiple sets of flight data of the variant aircraft in the desktop simulation test;

[0027] The step 5 specifically includes:

[0028] The evaluation is carried out by calculating the core evaluation indicators based on multiple sets of recorded flight data.

[0029] Optionally, in the flight performance analysis and evaluation method of the variant aircraft as described above, after step 5, the method further includes:

[0030] Step 6, by repeatedly executing steps 3 to 5, to generate different aerodynamic parameter deflection matrices and their corresponding aerodynamic data after deflection, perform multiple desktop simulation tests, and calculate the core evaluation indicators for evaluation in each simulation test.

[0031] In a second aspect, an embodiment of the present invention further provides a simulation test system for a variant aircraft, the simulation test system is used to perform flight performance analysis and evaluation of the variant aircraft, the simulation test system includes: a memory and a processor;

[0032] Wherein, the memory is configured to store executable instructions;

[0033] The processor is specifically configured to implement the flight performance analysis and evaluation method of the variant aircraft as described in any one of the above when executing the executable instructions stored in the memory.

[0034] Beneficial effects of the present invention: The embodiments of the present invention provide a flight performance analysis and evaluation method and simulation test system for a variant aircraft. By analyzing the aerodynamic data of the main body of the variant aircraft during its deformation process, the aerodynamic deviation range and core evaluation indicators are obtained, and a flight performance test action library for the variant aircraft is established. At least one group of test actions are selected from the flight performance test action library to carry out a desktop simulation test. Based on the aerodynamic parameter deviation matrix, the variant aircraft is controlled to execute the selected test actions during the desktop simulation test, and the flight data of the variant aircraft executing the test actions is recorded in real time during the desktop simulation test. The core evaluation indicators are calculated based on the flight data to evaluate the flight performance of the variant aircraft. It has the following beneficial effects:

[0035] (1) The method provided by the present invention is specifically a new flight performance analysis and evaluation method for variant aircraft suitable for the desktop simulation stage;

[0036] (2) The designers of the present invention consider reducing the reliance on model accuracy during the design and evaluation process, and simulate the complex deformation process of the variant aircraft by using the aerodynamic deflection method. This method does not require large-scale wind tunnel test data support, can effectively reduce the number of wind tunnel tests and the workload of simulation calculations, and reduces the requirements for preliminary data and the difficulty of evaluation of flight performance.

[0037] (3) The method provided by the present invention designs core evaluation indicators, and specifically supplements the traditional aircraft evaluation indicator system for the characteristics of variant aircraft, so that the obtained results are more in line with the characteristics of variant aircraft;

[0038] (4) The method provided by the present invention does not require the physical structure of a real aircraft, and uses a computational simulation method for evaluation, which reduces the hardware requirements for flight performance evaluation, is more conducive to implementation, reduces R&D costs, and improves R&D efficiency;

[0039] (5) The method provided by the present invention adopts a random combination of flight actions. By randomly selecting a combination of flight actions, the flight state of the aircraft can be simulated more realistically and specifically, which is conducive to the evaluation of the entire flight process of the aircraft.

[0040] The flight performance analysis and evaluation method of the variant aircraft provided in the embodiment of the present invention can realize the analysis and evaluation of the flight performance of the variant aircraft, and has the characteristics of simple method, strong feasibility, higher safety and more reliable evaluation results. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0042] Figure 1 A flowchart of a method for analyzing and evaluating the flight performance of a variant aircraft provided by an embodiment of the present invention;

[0043] Figure 2 A simulation schematic diagram of simulation number 1 in the flight performance analysis and evaluation method of a variant aircraft provided in an embodiment of the present invention;

[0044] Figure 3 A simulation schematic diagram of simulation number 2 in the flight performance analysis and evaluation method of a variant aircraft provided in an embodiment of the present invention;

[0045] Figure 4 A simulation schematic diagram of simulation number 2 in the flight performance analysis and evaluation method of a variant aircraft provided in an embodiment of the present invention;

[0046] in, Figure 2 , Figure 3 and Figure 4 Figure a, Figure b, Figure c, Figure d, Figure e and Figure f respectively represent the simulation effects of 6 groups of test actions. DETAILED DESCRIPTION

[0047] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0048] The above background technology has already explained the importance of variant aircraft in aircraft development; however, due to the complex structure of the variant mechanism in the variant aircraft, there is often a large difference between the actual flight state and the simulation model, especially during the deformation process. This leads to the fact that if the flight performance analysis and evaluation method of conventional aircraft is applied to the variant aircraft, due to the heavy reliance on the accuracy of the variant aircraft simulation model, a large number of wind tunnel tests and simulation calculations are required, which leads to an increase in the workload of performance evaluation, an increase in work costs, and low work efficiency.

[0049] In response to the above problems, an embodiment of the present invention provides a flight performance analysis and evaluation method and a simulation test system for a variant aircraft, which can realize the analysis and evaluation of the flight performance of the variant aircraft, and has the characteristics of simple method, strong feasibility, higher safety and more reliable evaluation results.

[0050] The embodiments of the present invention provide a flight performance analysis and evaluation method and a simulation test system for a variant aircraft, which simulates the complex deformation process of the variant aircraft through an aerodynamic pulling method, does not require large-scale wind tunnel test data support, and reduces the initial data requirements and evaluation difficulty of flight performance evaluation.

[0051] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0052] An embodiment of the present invention provides a flight performance analysis and evaluation method for a variant aircraft. The design concept of the flight performance analysis and evaluation method is as follows:

[0053] By analyzing the aerodynamic data of the variant aircraft during its deformation process, the aerodynamic deflection range and core evaluation indicators are obtained, and a flight performance test action library of the variant aircraft is established. At least one group of test actions are selected from the flight performance test action library to carry out desktop simulation test experiments. Based on the aerodynamic parameter deflection matrix, the variant aircraft is controlled to perform the selected test actions during the desktop simulation test, and the flight data of the variant aircraft performing the test actions is recorded in real time during the desktop simulation test. The core evaluation indicators are calculated based on the flight data to evaluate the flight performance of the variant aircraft.

[0054] Figure 1 A flowchart of a method for analyzing and evaluating the flight performance of a variant aircraft provided in an embodiment of the present invention is shown in FIG. Figure 1 The flight performance analysis and evaluation method of a variant aircraft provided in an embodiment of the present invention comprises the following steps:.

[0055] Step 1: Determine the range of aerodynamic deviation by analyzing the aerodynamic data of the main body of the variant aircraft during its deformation process; and set core evaluation indicators in combination with the design requirements of the variant aircraft;

[0056] Step 2, establishing a flight performance test action library for variant aircraft;

[0057] Step 3, generating an aerodynamic parameter deviation matrix according to the range of aerodynamic deviation and the variant aircraft simulation model, deflecting the aerodynamic derivatives in the variant aircraft simulation model, and generating aerodynamic data after deflection;

[0058] Step 4, randomly selecting at least one set of test actions from the flight performance test action library of the variant aircraft, combining the aerodynamic data after deflection obtained in step 3, performing a desktop simulation test, and recording the flight data of the variant aircraft in the simulation test; wherein, during the desktop simulation test, the variant aircraft is controlled to perform the selected test actions, and the flight data of the variant aircraft during the test actions is recorded in real time during the desktop simulation test;

[0059] Step 5: Calculate the core evaluation indicators based on the flight data recorded during the desktop simulation test for evaluation.

[0060] In one implementation of the embodiment of the present invention, the implementation process of the above step 1 may include:

[0061] Step 11, determining a range of aerodynamic deviation according to a range in which actual aerodynamic parameters of the variant aircraft simulation model deviate from aerodynamic parameters of the static configuration during the deformation process;

[0062] Step 12, based on the flight performance requirements of the variant aircraft, the configuration switching during the deformation process, and the need to maintain controllable and stable flight capabilities during the control mode switching process, set the core evaluation indicators.

[0063] In an implementation of the embodiment of the present invention, the implementation of the above step 2 may include:

[0064] According to the flight mission of the variant aircraft and the flight actions of the variant aircraft during the transformation process, a flight performance test action library of the variant aircraft is constructed; wherein the flight actions in the flight performance test action library include: wing deployment, wing folding, fixed pitch angle climb, constant speed climb, roll, left yaw, right yaw, left roll, right roll, fixed pitch angle dive, constant speed dive, and level flight.

[0065] In an implementation of the embodiment of the present invention, the implementation process of the above step 3 may include:

[0066] Step 31, according to the range of aerodynamic deviation, the variant aircraft simulation model and the design requirements of aerodynamic deviation, the number of simulations is set, and a random number generation method is adopted to generate an aerodynamic parameter deviation matrix; in this step, for example, a Monte Carlo shooting method is adopted to generate the aerodynamic parameter deviation matrix;

[0067] Step 32, after the aerodynamic parameter deviation matrix is ​​input into the variant aircraft simulation model, the aerodynamic parameter deviation matrix is ​​multiplied by the corresponding aerodynamic derivative in the variant aircraft simulation model to generate the deflected aerodynamic data.

[0068] In an implementation of the embodiment of the present invention, the implementation process of the above step 4 may include:

[0069] Step 41, randomly selecting at least one set of test actions from a flight performance test action library of the variant aircraft, and generating a flight action sequence from the at least one set of test actions;

[0070] Step 42, setting a flight mission according to the flight action sequence generated in step 41, and performing a desktop simulation test based on the flight mission and the aerodynamic data after the deflection;

[0071] Step 43, during the desktop simulation test, the variant aircraft is controlled to execute the selected test action, and the flight data of the variant aircraft executing the test action is recorded in real time during the desktop simulation test.

[0072] In an implementation manner of the embodiment of the present invention, the above method provided by the embodiment of the present invention may further perform the following before step 5:

[0073] Step 5a, by repeatedly executing steps 3 to 4, to generate different aerodynamic parameter deflection matrices and their corresponding aerodynamic data after deflection, perform a desktop simulation test, and record multiple sets of flight data of the variant aircraft in the desktop simulation test.

[0074] Accordingly, step 5 in the implementation method specifically includes:

[0075] The evaluation is carried out by calculating the core evaluation indicators based on multiple sets of recorded flight data.

[0076] Furthermore, after step 5, the implementation method further includes:

[0077] Step 6, by repeatedly executing steps 3 to 5, to generate different aerodynamic parameter deflection matrices and their corresponding aerodynamic data after deflection, perform multiple desktop simulation tests, and calculate the core evaluation indicators for evaluation in each simulation test.

[0078] The flight performance analysis and evaluation method of a variant aircraft provided by an embodiment of the present invention has the following beneficial effects:

[0079] (1) The method provided by the present invention is specifically a new flight performance analysis and evaluation method for variant aircraft suitable for the desktop simulation stage;

[0080] (2) The designers of the present invention consider reducing the reliance on model accuracy during the design and evaluation process, and simulate the complex deformation process of the variant aircraft by using the aerodynamic deflection method. This method does not require large-scale wind tunnel test data support, can effectively reduce the number of wind tunnel tests and the workload of simulation calculations, and reduces the requirements for preliminary data and the difficulty of evaluation of flight performance.

[0081] (3) The method provided by the present invention designs core evaluation indicators, and specifically supplements the traditional aircraft evaluation indicator system for the characteristics of variant aircraft, so that the obtained results are more in line with the characteristics of variant aircraft;

[0082] (4) The method provided by the present invention does not require the physical structure of a real aircraft, and uses a computational simulation method for evaluation, which reduces the hardware requirements for flight performance evaluation, is more conducive to implementation, reduces R&D costs, and improves R&D efficiency;

[0083] (5) The method provided by the present invention adopts a random combination of flight actions. By randomly selecting a combination of flight actions, the flight state of the aircraft can be simulated more realistically and specifically, which is conducive to the evaluation of the entire flight process of the aircraft.

[0084] The flight performance analysis and evaluation method of the variant aircraft provided in the embodiment of the present invention can realize the analysis and evaluation of the flight performance of the variant aircraft, and has the characteristics of simple method, strong feasibility, higher safety and more reliable evaluation results.

[0085] Based on the flight performance analysis and evaluation method of the variant aircraft provided by the embodiment of the present invention, the embodiment of the present invention also provides a simulation test system of the variant aircraft, the simulation test system is used to perform flight performance analysis and evaluation of the variant aircraft, the simulation test system includes: a memory and a processor;

[0086] Wherein, the memory is configured to store executable instructions;

[0087] The processor is specifically configured to implement the flight performance analysis and evaluation method of the variant aircraft provided by any of the above embodiments when executing the executable instructions stored in the memory.

[0088] The following is a schematic illustration of an implementation of the flight performance analysis and evaluation method for a variant aircraft provided by the present invention through an embodiment.

[0089] Step 1, determine the range of aerodynamic pull deviation and set the core evaluation index;

[0090] First, based on the analysis of the body data of the variant aircraft during its deformation process, the aerodynamic pull deviation δ x The value range of .

[0091] The variant aircraft simulation model used in this embodiment contains 22 aerodynamic derivatives. According to the CAD calculation results, during the dynamic deformation process of the wing, the maximum range of its lift, drag and pitch moment deviation from the static configuration is 20%, so the range of its aerodynamic pull deviation is set to be a maximum of 20% above and below the original data, that is, δ x ∈[0.8,1.2].

[0092] Secondly, core evaluation indicators are set based on the flight performance requirements of variant aircraft, configuration switching during the deformation process, and the need to maintain controllable, stable and stable flight capabilities during control mode switching.

[0093] The core evaluation indicators in this step are divided into two categories: the first category is flight control accuracy, including: pitch angle control accuracy (°), with an accuracy range of ±0.5°; altitude control accuracy (m), with an accuracy range of ±9m when the roll angle is 0-1°, ±20 or ±0.3% when the roll angle is 1-30°, whichever is greater, and ±30 or ±4.0% when the roll angle is above 30°, whichever is greater; roll angle control accuracy (°), with an accuracy range of ±1.0°; heading angle control accuracy (°), with an accuracy range of ±0.5°.

[0094] The second category is switching transient, including: maximum transient longitudinal overload increment (g) for configuration switching, requiring the longitudinal overload increment not to exceed 1g; maximum transient longitudinal overload increment (g) for configuration control mode, requiring the longitudinal overload increment not to exceed 0.5g; maximum roll angular rate increment (° / s) for configuration switching, requiring the roll angular rate increment not to exceed 10° / s; maximum roll angular rate increment (° / s) for configuration control mode, requiring the roll angular rate increment not to exceed 5° / s.

[0095] Step 2, establishing a flight performance test action library for variant aircraft;

[0096] The flight performance test action library in this step can be established based on the flight mission of the variant aircraft and the flight actions of the variant aircraft during the transformation process. The flight actions included in the flight performance test action library of the variant aircraft are: wing deployment, wing folding, fixed pitch angle climb, constant speed climb, roll, left yaw, right yaw, left roll, right roll, fixed pitch angle dive, constant speed dive, and level flight.

[0097] Step 3, generating aerodynamic parameter pull-bias matrix;

[0098] In this step, the aerodynamic parameter deflection matrix can be generated by any random number generation method. In this embodiment, the random() function provided in the MATLAB software is used for generation.

[0099] The variant aircraft simulation model used in this embodiment includes 22 aerodynamic derivatives, and the generated aerodynamic parameter deviation matrix is ​​a 22*1 matrix δ A =[δ1,δ2,……,δ x , ..., δ 22 ], each of which has a value range of δ x ∈[0.8,1.2].

[0100] Step 4, input the corresponding aerodynamic parameter deviation matrix into the flight simulation system used to perform the test experiment, and deflect the aerodynamic derivatives in the variant aircraft simulation model, that is, multiply the aerodynamic parameter deviation matrix by the corresponding aerodynamic derivatives in the variant aircraft simulation model to generate deflected aerodynamic data.

[0101] In this step, taking the pitch moment coefficient in the model as an example, the pitch moment coefficient (angle of attack) Cm0 corresponds to the pull matrix δ A The first term δ1 in the equation is δ0real, so the aerodynamic data of this term after deflection generated in the actual simulation is: Cm0real=Cm0*δ1; the pitch moment derivative Cmq caused by the pitch angular velocity corresponds to the deflection matrix δ AThe second term δ2 in the aerodynamic parameter deflection matrix is: Cmqreal = Cmq*δ2. x Multiplying it with the corresponding aerodynamic derivative will give the aerodynamic data after deflection.

[0102] Step 5, randomly select flight actions to generate a flight action sequence. In this embodiment, the following six groups of test actions are selected to generate a flight action sequence, namely: (1) fixed pitch angle climb; (2) a combination of uniform climb, level flight, and wings spread; (3) left roll; (4) right roll; (5) uniform climb; and (6) a combination of dive and right yaw.

[0103] Step 6, set the flight mission in the flight simulation system according to the above-mentioned flight action sequence, perform flight simulation, and record flight data. The recorded flight data include: flight altitude HB (m), flight speed VIAS (m / s), yaw angle YAW (°), angle of attack AOA (°), longitudinal overload NZ (g), pitch angle PIT (°), wing folding angle Ftheta (°), lateral overload NY (g), roll angle BANK (°), pitch angle rate ROP (° / s), roll angle rate ROR (° / s), yaw angle rate ROY (° / s). Figure 2 As shown, it is a simulation schematic diagram of simulation number 1 in the flight performance analysis and evaluation method of the variant aircraft provided by an embodiment of the present invention; specifically, the flight simulation is performed according to the flight action sequence (including the above 6 groups of test actions); Figure 2 Figure a, Figure b, Figure c, Figure d, Figure e and Figure f respectively represent the simulation effects of 6 groups of test actions.

[0104] Step 7, calculate the core evaluation index based on the flight data obtained in step 6.

[0105] Step 8: Evaluate the core evaluation indicators.

[0106] Step 9: Determine whether the simulation times are completed, if not, repeat the above steps 3 to 8. The following Table 1 shows the working mode control accuracy and switching transient of simulation times 1.

[0107] Table 1 Working mode control accuracy and switching transient, simulation times 1

[0108]

[0109] Figure 3 A simulation schematic diagram of simulation number 2 in the flight performance analysis and evaluation method of a variant aircraft provided in an embodiment of the present invention; Figure 4 A simulation schematic diagram of simulation number 2 in the flight performance analysis and evaluation method of a variant aircraft provided in an embodiment of the present invention; Figure 3and Figure 4 Figure a, Figure b, Figure c, Figure d, Figure e and Figure f respectively represent the simulation effects of 6 groups of test actions.

[0110] Tables 2 and 3 below show the working mode control accuracy and switching transient of simulation times 2 and 3 respectively.

[0111] Table 2 Working mode control accuracy and switching transient, simulation times 2

[0112]

[0113] Table 3 Working mode control accuracy and switching transient, simulation times 2

[0114]

[0115] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A flight performance analysis and evaluation method for a variant aircraft, characterized in that: include: By analyzing the aerodynamic data of the variant aircraft during its deformation process, the aerodynamic deflection range and core evaluation indicators are obtained, and a flight performance test action library of the variant aircraft is established. At least one set of test actions is selected from the flight performance test action library to conduct desktop simulation tests. Based on the aerodynamic parameter deviation matrix, the variant aircraft is controlled to perform the selected test action during the desktop simulation test, and the flight data of the variant aircraft performing the test action is recorded in real time during the desktop simulation test; the core evaluation indicators are calculated based on the flight data to evaluate the flight performance of the variant aircraft.

2. The flight performance analysis and evaluation method of a variant aircraft according to claim 1, characterized in that: The steps include: Step 1: Determine the range of aerodynamic deviation by analyzing the aerodynamic data of the main body of the variant aircraft during its deformation process; and set core evaluation indicators in combination with the design requirements of the variant aircraft; Step 2, establishing a flight performance test action library for variant aircraft; Step 3, generating an aerodynamic parameter deviation matrix according to the range of aerodynamic deviation and the variant aircraft simulation model, deflecting the aerodynamic derivatives in the variant aircraft simulation model, and generating aerodynamic data after deflection; Step 4, randomly selecting at least one set of test actions from the flight performance test action library of the variant aircraft, combining the aerodynamic data after deflection obtained in step 3, performing a desktop simulation test, and recording the flight data of the variant aircraft in the simulation test; wherein, during the desktop simulation test, the variant aircraft is controlled to perform the selected test actions, and the flight data of the variant aircraft during the test actions is recorded in real time during the desktop simulation test; Step 5: Calculate the core evaluation indicators based on the flight data recorded during the desktop simulation test for evaluation.

3. The flight performance analysis and evaluation method of a variant aircraft according to claim 2, characterized in that: The step 1 comprises: Step 11, determining a range of aerodynamic deviation according to a range in which actual aerodynamic parameters of the variant aircraft simulation model deviate from aerodynamic parameters of the static configuration during the deformation process; Step 12, based on the flight performance requirements of the variant aircraft, the configuration switching during the deformation process, and the need to maintain controllable and stable flight capabilities during the control mode switching process, set the core evaluation indicators.

4. The flight performance analysis and evaluation method of a variant aircraft according to claim 2, characterized in that: The step 2 comprises: According to the flight mission of the variant aircraft and the flight actions of the variant aircraft during the transformation process, a flight performance test action library of the variant aircraft is constructed; wherein the flight actions in the flight performance test action library include: wing deployment, wing folding, fixed pitch angle climb, constant speed climb, roll, left yaw, right yaw, left roll, right roll, fixed pitch angle dive, constant speed dive, and level flight.

5. The flight performance analysis and evaluation method of a variant aircraft according to claim 2, characterized in that: The step 3 comprises: Step 31, according to the range of aerodynamic deflection, the variant aircraft simulation model and the design requirements of aerodynamic deflection, the number of simulations is set, and a random number generation method is adopted to generate an aerodynamic parameter deflection matrix; Step 32, after the aerodynamic parameter deviation matrix is ​​input into the variant aircraft simulation model, the aerodynamic parameter deviation matrix is ​​multiplied by the corresponding aerodynamic derivative in the variant aircraft simulation model to generate the deflected aerodynamic data.

6. The flight performance analysis and evaluation method of a variant aircraft according to claim 2, characterized in that: The step 4 comprises: Step 41, randomly select at least one set of test actions from the flight performance test action library of the variant aircraft, and generate a flight action sequence from the at least one set of test actions Step 42, setting a flight mission according to the flight action sequence generated in step 41, and performing a desktop simulation test based on the flight mission and the aerodynamic data after the deflection; Step 43, during the desktop simulation test, the variant aircraft is controlled to execute the selected test action, and the flight data of the variant aircraft executing the test action is recorded in real time during the desktop simulation test.

7. The flight performance analysis and evaluation method of a variant aircraft according to any one of claims 2 to 6, characterized in that: Before step 5, the method further includes: Step 5a, performing a desktop simulation test by repeatedly executing steps 3 to 4 to generate different aerodynamic parameter deflection matrices and their corresponding aerodynamic data after deflection, and recording multiple sets of flight data of the variant aircraft in the desktop simulation test; The step 5 specifically includes: The evaluation is carried out by calculating the core evaluation indicators based on multiple sets of recorded flight data.

8. The flight performance analysis and evaluation method of a variant aircraft according to any one of claims 2 to 6, characterized in that: After step 5, the method further includes: Step 6, by repeatedly executing steps 3 to 5, to generate different aerodynamic parameter deflection matrices and their corresponding aerodynamic data after deflection, perform multiple desktop simulation tests, and calculate the core evaluation indicators for evaluation in each simulation test.

9. A simulation test system for a variant aircraft, characterized in that: The simulation test system is used to perform flight performance analysis and evaluation of a variant aircraft, and the simulation test system includes: a memory and a processor; Wherein, the memory is configured to store executable instructions; The processor is specifically configured to implement the flight performance analysis and evaluation method of the variant aircraft according to any one of claims 1 to 8 when executing the executable instructions stored in the memory.

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