A method for flight performance analysis and evaluation of a variant aircraft and a simulation test system

Abstract

This invention discloses a method and simulation test system for analyzing and evaluating the flight performance of a variant aircraft. The method includes: analyzing the aerodynamic data of the variant aircraft during its deformation process to obtain the aerodynamic deflection range and core evaluation indicators; establishing a flight performance test action library for the variant aircraft; selecting at least one set of test actions from the flight performance test action library to conduct desktop simulation tests; controlling the variant aircraft to execute the selected test actions during the desktop simulation test based on the aerodynamic parameter deflection matrix, and recording the flight data of the variant aircraft executing the test actions in real time during the desktop simulation test; calculating the core evaluation indicators based on the flight data to evaluate the flight performance of the variant aircraft. The technical solution provided by this invention solves the problem that if the flight performance analysis and evaluation methods of conventional aircraft are applied to variant aircraft, the high dependence on the accuracy of the variant aircraft simulation model requires a large number of wind tunnel tests and simulation calculations, which leads to increased workload, increased operating costs, and low efficiency in performance evaluation.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of aviation testing technology, and particularly to a method for analyzing and evaluating the flight performance of a variant aircraft and a simulation test system. Background Technology

[0002] Transformer aircraft represent an important development direction for expanding the flight envelope and enhancing flight capabilities of future aircraft. However, due to the existence of morphing mechanisms, the flight state of morpher aircraft is far more complex than that of conventional aircraft. This complexity is reflected in the significant differences between the actual flight state of the aircraft and the simulation model, especially during the transformation process.

[0003] If the flight performance analysis and evaluation methods of conventional aircraft are applied to variant aircraft, the accuracy of the variant aircraft simulation model becomes 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] The purpose of this invention is to address the aforementioned technical problems by providing a method and simulation test system for analyzing and evaluating the flight performance of a variant aircraft. This addresses the issue that applying conventional aircraft flight performance analysis and evaluation methods to variant aircraft, which relies heavily on the accuracy of the variant aircraft simulation model, requires extensive wind tunnel testing and simulation calculations, leading to increased workload, higher costs, and lower efficiency in performance evaluation.

[0005] The technical solution of the present invention: In a first aspect, embodiments of the present invention provide a method for analyzing and evaluating the flight performance of a variant aircraft, comprising:

[0006] By analyzing the aerodynamic data of the variant aircraft during its transformation process, the aerodynamic deflection range and core evaluation indicators are obtained. A flight performance test maneuver library for the variant aircraft is established, and at least one set of test maneuvers is selected from the library to conduct desktop simulation tests. Based on the aerodynamic parameter deflection matrix, the variant aircraft is controlled to execute the selected test maneuvers during the desktop simulation test, and the flight data of the variant aircraft executing the test maneuvers 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 for the variant aircraft described above includes the following steps:

[0008] Step 1: By analyzing the aerodynamic data of the variant aircraft during its deformation process, determine the range of aerodynamic deflection; and set core evaluation indicators in conjunction with the design requirements of the variant aircraft.

[0009] Step 2: Establish a flight performance test maneuver library for the variant aircraft;

[0010] Step 3: Based on the aerodynamic deflection range and the variant aircraft simulation model, generate an aerodynamic parameter deflection matrix, deflect the aerodynamic derivatives in the variant aircraft simulation model, and generate deflected aerodynamic data.

[0011] Step 4: Randomly select at least one set of test actions from the flight performance test action library of the variant aircraft, combine it with the aerodynamic data after pull-off obtained in Step 3, execute the desktop simulation test, and record the flight data of the variant aircraft in the simulation test; wherein, during the desktop simulation test, control the variant aircraft to execute the selected test actions, and record the flight data of the variant aircraft in real time during the execution of the test actions.

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

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

[0014] Step 11: Determine the range of aerodynamic deflection based on the range of actual aerodynamic parameters deviating from static configuration aerodynamic parameters during the deformation process of the variant aircraft simulation model.

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

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

[0017] Based on the flight missions of the variant aircraft and the flight maneuvers of the variant aircraft during transformation, a flight performance test maneuver library for the variant aircraft is constructed. The flight maneuvers in the flight performance test maneuver library include: wing deployment, wing folding, constant pitch angle climb, uniform speed climb, roll, left yaw, right yaw, left roll, right roll, constant pitch angle dive, uniform speed dive, and level flight.

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

[0019] Step 31: Based on the range of aerodynamic deflection, the variant aircraft simulation model, and the design requirements of aerodynamic deflection, set the number of simulations and generate the aerodynamic parameter deflection matrix using a random number generation method.

[0020] Step 32: After inputting the aerodynamic parameter bias matrix into the variant aircraft simulation model, multiply the aerodynamic parameter bias matrix with the corresponding aerodynamic derivative in the variant aircraft simulation model to generate biased aerodynamic data.

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

[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 at least one set of test actions.

[0023] Step 42: Set the flight mission according to the flight action sequence generated in step 41, and perform a desktop simulation test based on the flight mission and the aerodynamic data after the pull-off.

[0024] Step 43: During the desktop simulation test, control the variant aircraft to perform the selected test actions, and record the flight data of the variant aircraft in real time during the execution of the test actions.

[0025] Optionally, in the flight performance analysis and evaluation method for the variant aircraft described above, before step 5, the following steps are also included:

[0026] Step 5a: By repeating steps 3 to 4, a desktop simulation test is performed by generating different aerodynamic parameter pull matrices and their corresponding pull-up aerodynamic data, and multiple sets of flight data of the variant aircraft in the desktop simulation test are recorded.

[0027] Step 5 specifically includes:

[0028] The evaluation is based on core evaluation indicators calculated from multiple sets of recorded flight data.

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

[0030] Step 6: By repeating steps 3 to 5, multiple desktop simulation tests are performed to generate different aerodynamic parameter bias matrices and their corresponding biased aerodynamic data, and core evaluation indicators are calculated and evaluated in each simulation test.

[0031] Secondly, embodiments of the present invention also provide a simulation test system for a variant aircraft, the simulation test system being used to perform flight performance analysis and evaluation of the variant aircraft, the simulation test system comprising: a memory and a processor;

[0032] The memory is configured to store executable instructions;

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

[0034] The beneficial effects of this invention are as follows: This invention provides a method and simulation test system for analyzing and evaluating the flight performance of a variant aircraft. By analyzing the aerodynamic data of the variant aircraft during its transformation process, the aerodynamic pull-off range and core evaluation indicators are obtained. A flight performance test action library for 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 pull-off 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. Core evaluation indicators are calculated based on the flight data to evaluate the flight performance of the variant aircraft. This invention has the following beneficial effects:

[0035] (1) The method provided by the present invention is a novel method for analyzing and evaluating the flight performance of variant aircraft in the desktop simulation stage;

[0036] (2) The designers of this invention considered to weaken the dependence on the accuracy of the model in the design and evaluation process, and simulated the complex deformation process of the variant aircraft by aerodynamic deflection method. It does not require large-scale wind tunnel test data support, which can effectively reduce the number of wind tunnel tests and the workload of simulation calculation, and reduce the early data requirements and evaluation difficulty of flight performance evaluation.

[0037] (3) The method provided by the present invention designs core evaluation indicators and specifically supplements them to the characteristics of variant aircraft on the basis of the traditional aircraft evaluation indicator system, so that the results are more consistent 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, but uses a computational simulation method for evaluation, which reduces the hardware requirements for flight performance evaluation, makes it easier to implement, 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 combinations of flight actions, the flight state of the aircraft can be simulated more realistically and specifically, which is beneficial to the evaluation of the entire flight process of the aircraft.

[0040] The flight performance analysis and evaluation method for variant aircraft provided in this invention can be used to analyze and evaluate the flight performance of variant aircraft. It is characterized by its simplicity, high feasibility, higher safety, and more reliable evaluation results. Attached Figure Description

[0041] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

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

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

[0044] Figure 3 A simulation diagram illustrating simulation number 2 in the flight performance analysis and evaluation method for the variant aircraft provided in this embodiment of the invention;

[0045] Figure 4 A simulation diagram illustrating simulation number 2 in the flight performance analysis and evaluation method for the variant aircraft provided in this embodiment of the invention;

[0046] in, Figure 2 , Figure 3 and Figure 4 Figures a, b, c, d, e, and f in the diagram represent the simulation effects of the six test actions, respectively. Detailed Implementation

[0047] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0048] As explained in the background section, variability aircraft play a crucial role in aircraft development. However, due to the complex structure of the variator mechanism in variability aircraft, there are often significant differences between the actual flight conditions and the simulation model, especially during the transformation process. This means that applying conventional aircraft flight performance analysis and evaluation methods to variability aircraft is highly dependent on the accuracy of the variability aircraft simulation model, requiring extensive wind tunnel testing and simulation calculations. This increases the workload of performance evaluation, raises costs, and reduces efficiency.

[0049] To address the aforementioned issues, embodiments of the present invention provide a method and simulation test system for analyzing and evaluating the flight performance of variant aircraft. This method can analyze and evaluate the flight performance of variant aircraft and features simplicity, high feasibility, enhanced safety, and more reliable evaluation results.

[0050] The present invention provides a method and simulation test system for analyzing and evaluating the flight performance of variant aircraft. It simulates the complex deformation process of variant aircraft by aerodynamic deflection, without the need for large-scale wind tunnel test data, thus reducing the early data requirements and evaluation difficulty for flight performance assessment.

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

[0052] This invention provides a method for analyzing and evaluating the flight performance of a variant aircraft. The design concept of this method is as follows:

[0053] By analyzing the aerodynamic data of the variant aircraft during its transformation process, the aerodynamic deflection range and core evaluation indicators are obtained. A flight performance test maneuver library for the variant aircraft is established, and at least one set of test maneuvers is selected from the library to conduct desktop simulation tests. Based on the aerodynamic parameter deflection matrix, the variant aircraft is controlled to execute the selected test maneuvers during the desktop simulation test, and the flight data of the variant aircraft executing the test maneuvers 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 illustrating a method for analyzing and evaluating the flight performance of a variant aircraft, as provided in this embodiment of the invention, is shown below. Figure 1 The flight performance analysis and evaluation method for variant aircraft provided in this embodiment of the invention includes the following steps:

[0055] Step 1: By analyzing the aerodynamic data of the variant aircraft during its deformation process, determine the range of aerodynamic deflection; and set core evaluation indicators in conjunction with the design requirements of the variant aircraft.

[0056] Step 2: Establish a flight performance test maneuver library for the variant aircraft;

[0057] Step 3: Based on the aerodynamic deflection range and the variant aircraft simulation model, generate an aerodynamic parameter deflection matrix, deflect the aerodynamic derivatives in the variant aircraft simulation model, and generate deflected aerodynamic data.

[0058] Step 4: Randomly select at least one set of test actions from the flight performance test action library of the variant aircraft, combine it with the aerodynamic data after pull-off obtained in Step 3, execute the desktop simulation test, and record the flight data of the variant aircraft in the simulation test; wherein, during the desktop simulation test, control the variant aircraft to execute the selected test actions, and record the flight data of the variant aircraft in real time during the execution of the test actions.

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

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

[0061] Step 11: Determine the range of aerodynamic deflection based on the range of actual aerodynamic parameters deviating from static configuration aerodynamic parameters during the deformation process of the variant aircraft simulation model.

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

[0063] In one implementation of this invention, step 2 above may include:

[0064] Based on the flight missions of the variant aircraft and the flight maneuvers of the variant aircraft during transformation, a flight performance test maneuver library for the variant aircraft is constructed. The flight maneuvers in the flight performance test maneuver library include: wing deployment, wing folding, constant pitch angle climb, uniform speed climb, roll, left yaw, right yaw, left roll, right roll, constant pitch angle dive, uniform speed dive, and level flight.

[0065] In one implementation of this invention, step 3 may include:

[0066] Step 31: Based on the range of aerodynamic deflection, the variant aircraft simulation model, and the design requirements of aerodynamic deflection, set the number of simulations and generate the aerodynamic parameter deflection matrix using a random number generation method; in this step, for example, the Monte Carlo target shooting method can be used to generate the aerodynamic parameter deflection matrix.

[0067] Step 32: After inputting the aerodynamic parameter bias matrix into the variant aircraft simulation model, multiply the aerodynamic parameter bias matrix with the corresponding aerodynamic derivative in the variant aircraft simulation model to generate biased aerodynamic data.

[0068] In one implementation of this invention, step 4 may include:

[0069] 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 at least one set of test actions;

[0070] Step 42: Set the flight mission according to the flight action sequence generated in step 41, and perform a desktop simulation test based on the flight mission and the aerodynamic data after the pull-off.

[0071] Step 43: During the desktop simulation test, control the variant aircraft to perform the selected test actions, and record the flight data of the variant aircraft in real time during the execution of the test actions.

[0072] In one implementation of this invention, the method provided by this invention may further be executed before step 5:

[0073] Step 5a: By repeating steps 3 to 4, a desktop simulation test is performed to generate different aerodynamic parameter bias matrices and their corresponding biased aerodynamic data, and multiple sets of flight data of the variant aircraft in the desktop simulation test are recorded.

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

[0075] The evaluation is based on core evaluation indicators calculated from multiple sets of recorded flight data.

[0076] Furthermore, this implementation method, after step 5, also includes:

[0077] Step 6: By repeating steps 3 to 5, multiple desktop simulation tests are performed to generate different aerodynamic parameter bias matrices and their corresponding biased aerodynamic data, and core evaluation indicators are calculated and evaluated in each simulation test.

[0078] The flight performance analysis and evaluation method for variant aircraft provided in this invention has the following beneficial effects:

[0079] (1) The method provided by the present invention is a novel method for analyzing and evaluating the flight performance of variant aircraft in the desktop simulation stage;

[0080] (2) The designers of this invention considered to weaken the dependence on the accuracy of the model in the design and evaluation process, and simulated the complex deformation process of the variant aircraft by aerodynamic deflection method. It does not require large-scale wind tunnel test data support, which can effectively reduce the number of wind tunnel tests and the workload of simulation calculation, and reduce the early data requirements and evaluation difficulty of flight performance evaluation.

[0081] (3) The method provided by the present invention designs core evaluation indicators and specifically supplements them to the characteristics of variant aircraft on the basis of the traditional aircraft evaluation indicator system, so that the results are more consistent 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, but uses a computational simulation method for evaluation, which reduces the hardware requirements for flight performance evaluation, makes it easier to implement, 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 combinations of flight actions, the flight state of the aircraft can be simulated more realistically and specifically, which is beneficial to the evaluation of the entire flight process of the aircraft.

[0084] The flight performance analysis and evaluation method for variant aircraft provided in this invention can be used to analyze and evaluate the flight performance of variant aircraft. It is characterized by its simplicity, high feasibility, higher safety, and more reliable evaluation results.

[0085] Based on the flight performance analysis and evaluation method for variant aircraft provided in the embodiments of the present invention, the embodiments of the present invention also provide a simulation test system for variant aircraft, which is used to perform flight performance analysis and evaluation of variant aircraft. The simulation test system includes: a memory and a processor.

[0086] The memory is configured to store executable instructions;

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

[0088] The following example illustrates the implementation of the flight performance analysis and evaluation method for variant aircraft provided by the present invention.

[0089] Step 1: Determine the range of aerodynamic deflection and set core evaluation indicators;

[0090] First, based on the analysis of the body data during the deformation process of the variant aircraft, the aerodynamic deflection δ was determined. x The range of values ​​for .

[0091] The variant aircraft simulation model used in this embodiment includes 22 aerodynamic derivatives. Based on CAD calculations, during the dynamic deformation of the wing, its lift, drag, and pitching moment deviate from the static configuration by a maximum range of 20%. Therefore, the range of aerodynamic deflection is set to fluctuate by a maximum of 20% above or below the original data, i.e., δ. x ∈[0.8,1.2].

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

[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 to 1°, ±20 or ±0.3% when the roll angle is 1 to 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°; and heading angle control accuracy (°), with an accuracy range of ±0.5°.

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

[0095] Step 2: Establish a flight performance test maneuver library for the variant aircraft;

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

[0097] Step 3: Generate the aerodynamic parameter pull matrix;

[0098] In this step, the aerodynamic parameter pull matrix can be generated using any random number generation method. In this embodiment, the random() function built into the MATLAB software is used.

[0099] The variant aircraft simulation model used in this embodiment contains 22 aerodynamic derivatives, and the generated aerodynamic parameter deflection matrix is ​​a 22*1 matrix δ. A = [δ1, δ2, ..., δ x , ..., δ 22 Each of its terms takes values ​​ranging from δ. x ∈[0.8,1.2].

[0100] Step 4: Input the corresponding aerodynamic parameter biasing matrix into the flight simulation system used to perform the test experiment, and bias the aerodynamic derivatives in the variant aircraft simulation model. That is, multiply the aerodynamic parameter biasing matrix with the corresponding aerodynamic derivatives in the variant aircraft simulation model to generate biased aerodynamic data.

[0101] In this step, taking the pitching moment coefficient in the model as an example, the pitching moment coefficient (angle of attack) Cm0 corresponds to the pull-off matrix δ. A The first term δ1 in the equation, therefore, the aerodynamic data for this term generated in the actual simulation after the yaw is: Cm0real=Cm0*δ1; the derivative of the pitch moment caused by the pitch angular velocity Cmq corresponds to the yaw matrix δ AThe second term δ2 in the matrix is ​​used to calculate the aerodynamic data for this term after the stretching in the actual simulation: Cmqreal = Cmq * δ2. Similarly, all the stretching values ​​δ in the aerodynamic parameter stretching matrix are calculated. x Multiplying the result by the corresponding aerodynamic derivative yields the aerodynamic data after deflection.

[0102] Step 5: Randomly select flight maneuvers and generate flight maneuver sequences. In this embodiment, the following 6 test maneuvers were selected to generate flight maneuver sequences: (1) constant pitch angle climb; (2) combination of constant speed climb, level flight, and wing deployment; (3) left roll; (4) right roll; (5) constant speed climb; (6) combination of dive and right yaw.

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

[0104] Step 7: Calculate the core evaluation indicators based on the flight data obtained in Step 6.

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

[0106] Step 9: Determine if the simulation count has been completed. If not, repeat steps 3 through 8 above. Table 1 below shows the working mode control accuracy and switching transients for simulation count 1.

[0107] Table 1. Working mode control accuracy and switching transients, simulation count 1

[0108]

[0109] Figure 3 A simulation diagram illustrating simulation number 2 in the flight performance analysis and evaluation method for the variant aircraft provided in this embodiment of the invention; Figure 4 A simulation diagram illustrating simulation number 2 in the flight performance analysis and evaluation method for the variant aircraft provided in this embodiment of the invention; Figure 3and Figure 4 Figures a, b, c, d, e, and f in the diagram represent the simulation effects of the six test actions, respectively.

[0110] Tables 2 and 3 below show the working mode control accuracy and switching transients for simulations number 2 and 3, respectively.

[0111] Table 2. Working mode control accuracy and switching transients, simulation times: 2

[0112]

[0113] Table 3. Working mode control accuracy and switching transients, simulation times: 2

[0114]

[0115] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A method for analyzing and evaluating the flight performance of a variant aircraft, characterized in that, include: Step 1: By analyzing the aerodynamic data of the variant aircraft during its deformation process, determine the range of aerodynamic deflection; and set core evaluation indicators in conjunction with the design requirements of the variant aircraft. Step 2: Establish a flight performance test maneuver library for the variant aircraft; Step 3: Based on the aerodynamic deflection range and the variant aircraft simulation model, generate an aerodynamic parameter deflection matrix, deflect the aerodynamic derivatives in the variant aircraft simulation model, and generate deflected aerodynamic data. Step 4: Randomly select at least one set of test actions from the flight performance test action library of the variant aircraft, combine it with the aerodynamic data after pull-off obtained in Step 3, execute the desktop simulation test, and record the flight data of the variant aircraft in the simulation test; wherein, during the desktop simulation test, control the variant aircraft to execute the selected test actions, and record the flight data of the variant aircraft in real time during the execution of the test actions. Step 5: Calculate core evaluation indicators based on flight data recorded during desktop simulation testing for evaluation; Step 1 includes: Step 11: Determine the range of aerodynamic deflection based on the range of actual aerodynamic parameters deviating from static configuration aerodynamic parameters during the deformation process of the variant aircraft simulation model. Step 3 includes: Step 31: Based on the range of aerodynamic deflection, the variant aircraft simulation model, and the design requirements of aerodynamic deflection, set the number of simulations and generate the aerodynamic parameter deflection matrix using a random number generation method. Step 32: After inputting the aerodynamic parameter bias matrix into the variant aircraft simulation model, multiply the aerodynamic parameter bias matrix with the corresponding aerodynamic derivative in the variant aircraft simulation model to generate biased aerodynamic data.

2. The method for analyzing and evaluating the flight performance of a variant aircraft according to claim 1, characterized in that, Step 1 further includes: Step 12: Based on the flight performance requirements of the variant aircraft, the configuration switching during the transformation process, and the need to maintain controllable and stable flight capability during the control mode switching process, set the core evaluation indicators.

3. The method for analyzing and evaluating the flight performance of a variant aircraft according to claim 1, characterized in that, The step 2 includes: Based on the flight missions of the variant aircraft and the flight maneuvers of the variant aircraft during transformation, a flight performance test maneuver library for the variant aircraft is constructed. The flight maneuvers in the flight performance test maneuver library include: wing deployment, wing folding, constant pitch angle climb, uniform speed climb, roll, left yaw, right yaw, left roll, right roll, constant pitch angle dive, uniform speed dive, and level flight.

4. The method for analyzing and evaluating the flight performance of a variant aircraft according to claim 1, characterized in that, Step 4 includes: 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 at least one set of test actions. Step 42: Set the flight mission according to the flight action sequence generated in step 41, and perform a desktop simulation test based on the flight mission and the aerodynamic data after the pull-off. Step 43: During the desktop simulation test, control the variant aircraft to perform the selected test actions, and record the flight data of the variant aircraft in real time during the execution of the test actions.

5. The method for analyzing and evaluating the flight performance of a variant aircraft according to any one of claims 1 to 4, characterized in that, Before step 5, the following is also included: Step 5a: By repeating steps 3 to 4, a desktop simulation test is performed by generating different aerodynamic parameter pull matrices and their corresponding pull-up aerodynamic data, and multiple sets of flight data of the variant aircraft in the desktop simulation test are recorded. Step 5 specifically includes: The evaluation is based on core evaluation indicators calculated from multiple sets of recorded flight data.

6. The method for analyzing and evaluating the flight performance of a variant aircraft according to any one of claims 1 to 4, characterized in that, Following step 5, the method further includes: Step 6: By repeating steps 3 to 5, multiple desktop simulation tests are performed to generate different aerodynamic parameter bias matrices and their corresponding biased aerodynamic data, and core evaluation indicators are calculated and evaluated in each simulation test.

7. 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 the variant aircraft. The simulation test system includes: a memory and a processor; The memory is configured to store executable instructions; The processor is specifically configured to implement the flight performance analysis and evaluation method for the variant aircraft as described in any one of claims 1 to 6 when executing the executable instructions stored in the memory.

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