A high-load flight simulation method and a high-load flight simulation system

Abstract

The present invention provides a high-load flight simulation method and a high-load flight simulation system. The method establishes a corresponding relationship between actual psychological and physiological parameter values ​​and actual flight status, corrects the control of a high-load flight simulator control system according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values, and adjusts the simulated flight status information of the high-load flight simulator so that the corresponding relationship between the simulated psychological and physiological parameter values ​​and the simulated flight status is adapted to the corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight status. A high-load flight simulation system with an adaptation method is also provided. The present invention can improve the fidelity of a continuous high-load simulated flight environment through comprehensive human perception to meet training requirements.

Description

Technical Field

[0001] The present invention relates to the technical field of high-load flight simulation, and in particular to a high-load flight simulation method and a high-load flight simulation system. Background Art

[0002] The outstanding acceleration motion produced by the aerial stunts and tactical flying maneuvers of high-performance stunt planes and fighter planes brings strong stimulation to the pilots, directly affecting their operating skills, physiological and psychological state, and having a significant impact on the combat performance and combat capability of the fighter planes. It poses a threat to flight safety and has attracted great attention from all countries.

[0003] Most tactical flight courses contain "high G-force and high load" actions. Simply using an aircraft for high load training will consume the precious life of the aircraft and may damage the aircraft or even cause a flight accident. High load flight training must be conducted frequently and repeatedly to bring the advanced performance of the aircraft into play. Therefore, there is an urgent need for training equipment with high load simulation function - "high load tactical flight simulator".

[0004] Conventional simulators currently used at home and abroad only have instantaneous loads. Since there is no continuous load, they can only meet basic flight training and cannot give pilots the real feeling of fighter jet combat flight. Therefore, advanced countries are competing to invest heavily in the development of flight simulators with continuous loads for flight training. In the simulated flight with continuous high loads, the flight acceleration vector field acts on the human body, so that the pilot's vision, hearing, proprioception, and abdominal sense are aware of the impact of the environment, and the pilot's physiology and psychology are changed due to the stimulation of this acceleration vector field. The prior art already has a technology for evaluating the fidelity of motion perception simulation of continuous load simulators, such as patent CN111785124, a method for evaluating the fidelity of motion perception simulation of continuous load simulators, but it only adds the consideration of the direction perception error factor caused by the direction. Although the evaluation of simulation fidelity does increase the consideration factors, as mentioned above, the stimulation of continuous high load on pilots will produce physiological and psychological changes. During the pilot's driving process, there is not only sensory perception of speed, direction, weightlessness and overweight, but also a strong psychological and physiological reaction. The psychological and physiological changes reflect the direct impact of continuous high load on the pilot's control skills and mental ability. During the actual flight, a skilled pilot will consciously control the psychological and physiological tolerance of the control action according to his own psychology and physiology. However, since the simulator uses a centrifuge combined with related mechanical parts to simulate the flight state formed by the control action, the same flight state that the pilot hopes to form by the same driving operation may have an unpredictable greater instantaneous force or torque than the real aircraft, and cannot match the simulated real flight state. It needs to be further adjusted through the feedback system in time. However, since these previous instantaneous forces and torques may have exceeded the physiological and psychological tolerance of the simulator pilot, the simulator pilot loses consciousness or suffers significant damage to the body's physiological functions and cannot complete further compensation adjustments. Therefore, this patent application does not take into account the pilot's comprehensive perception formed by the overall psychological and physiological factors that have a greater impact during the flight, and the benchmark for the comparison process is unclear. Not only can it not truly evaluate the fidelity of the simulated flight of the continuous load simulator, but it may also cause psychological and physiological damage to the simulator pilot. Obviously, the existing technology does not establish the realism of the simulated flight of the continuous load simulator and the actual flight from the perspective of overall psychological and physiological factors, that is, it does not use comprehensive perception to establish simulation training that meets the training requirements, so that the simulator can be corrected in time when the simulator pilot has psychological and physiological discomfort, to avoid the situation where the instantaneous force and torque are too large and exceed the pilot's physiological and psychological tolerance, and to ensure the physical and mental health of the simulator pilot. Summary of the invention

[0005] In order to solve the technical problem that the prior art has not been able to improve the realism of a continuous high-load simulated flight environment through comprehensive human perception to meet training requirements, the present invention proposes a high-load flight simulation method and a high-load flight simulation system, which can improve the realism of a continuous high-load simulated flight environment through comprehensive human perception to meet training requirements.

[0006] The present invention provides the following specific solutions:

[0007] A high-load flight simulation method, characterized in that a large amount of existing empirical aerodynamic parameters are associated with the actual psychological and physiological parameters of the pilot during flight, and a corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight state is established;

[0008] The simulated psychological and physiological data of the pilot in the simulated flight state simulated for the actual flight state of the actual flight on the high-load flight simulator are collected by sensors to obtain simulated psychological and physiological parameter values, and the control of the high-load flight simulator control system is corrected according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values, and the simulated flight state information of the high-load flight simulator is adjusted so that the further detected simulated psychological and physiological parameter values ​​are adapted to the actual psychological and physiological parameter values, so that the corresponding relationship between the simulated psychological and physiological parameter values ​​and the simulated flight state is adapted to the corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight state, and the simulated flight state information includes displacement parameters and rod force parameters for driving the high-load flight simulator control mechanism.

[0009] Preferably, the actual flight state and the simulated flight state both include at least one of boundary flight, entering and recovering from a stall, and entering and recovering from a spin, and the large number of subjects is more than sixty.

[0010] Further preferably, the control of the control system is corrected, which means that the high-load simulation aerodynamic equation parameters of the high-load flight simulator are corrected according to the difference to obtain a correction amount, and new simulated flight state information is formed, and then the action of the high-load flight simulator control system is corrected so that the simulator pilot obtains a comprehensive feeling of manipulation of the control mechanism that is adapted to the actual flight state; the high-load simulation aerodynamic equation parameters include longitudinal aerodynamic coefficients and lateral aerodynamic coefficients, the longitudinal aerodynamic coefficients and lateral aerodynamic coefficients include the correction amount, and the actual psychological and physiological parameters include existing empirical parameters of aviation medicine and animal experiments.

[0011] Further preferably, the actual psychological and physiological parameter values ​​and simulated psychological and physiological parameter values ​​collected by the sensor are psychological and physiological parameter values ​​obtained by substituting the psychological and physiological data collected by the sensor fitted on the pilot's head and face into the psychological and physiological parameters.

[0012] Further preferably, the longitudinal aerodynamic coefficient and the lateral aerodynamic coefficient of the high-load simulation aerodynamic equation respectively include:

[0013] Longitudinal aerodynamic coefficients, including drag coefficient in the stable coordinate system , lift coefficient , and the pitch moment coefficient in the body coordinate system , the calculation formula is as follows:

[0014]

[0015] in, Zero lift drag coefficient, Induced drag coefficient, Reynolds number variation The correction amount, The drag coefficient correction amount caused by the damping plate, The additional drag coefficient correction amount caused by external attachments, Predictive control to correct the drag coefficient, The correction amount of the drag coefficient according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model;

[0016]

[0017] in, The lift coefficient at zero angle of attack is The elasticity of the aircraft structure The influence coefficient of Lift coefficient parameters, Angle of attack, Aeroelastic correction factor for lift coefficient slope, The derivative of the lift coefficient with respect to the horizontal tail deviation angle, Fully moving horizontal tail deflection angle, Predictive control to lift coefficient correction, The correction amount of lift coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0018] in, Aeroelastic correction factor for lift coefficient slope, Fully moving horizontal tail control derivative, Fully moving horizontal tail deflection angle, The relative position of the aircraft mass on the mean aerodynamic chord of the wing, The relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, The correction amount of the relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, Dimensionless longitudinal damping derivative, Dimensionless wash flow time derivative, The dimensionless angular velocity of the aircraft about its body axis, The relative position of the lift angle of attack, Predictive control correction of pitch moment coefficient, The correction amount of the pitch moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0019] Lateral aerodynamic coefficients, including side force coefficients in the stable coordinate system and the rolling moment in the body coordinate system , Yaw moment coefficient , the calculation formula is as follows:

[0020]

[0021] in , is the side force coefficient generated by a sideslip angle of 1°, Aircraft structural elasticity The incremental impact of is the sideslip angle, Aircraft structural elasticity The influence coefficient of The side force coefficient generated by a 1° rudder deflection is, Rudder, Predictive control of the lateral force coefficient correction, The correction amount of the lateral force coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0022]

[0023] in, Heading stability, Aircraft structural elasticity The incremental impact of Aileron deflection 1° produces , aileron, Machine structure elasticity The incremental impact of Rudder efficiency, Rudder, Dimensionless cross derivatives on the lateral side, , Dimensionless lateral damping derivative, Yaw angular velocity, , The total moving tail deflection 1° produces , Tail differential, , The correction amount of the yaw moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0024]

[0025] Lateral static stability, Aileron efficiency, aileron, Transverse dimensionless damping derivative, , Dimensionless cross derivatives on the lateral side, Yaw angular velocity, Aircraft structural elasticity The influence coefficient of The total moving tail deflection 1° produces , Tail differential, , The roll moment coefficient correction amount is made according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model.

[0026] A high-load flight simulation system, characterized by comprising a high-load flight simulation module, a human perception processing module and a main control computer module,

[0027] The high-load flight simulation module is a device that provides flight load, flight attitude adjustment, flight control, simulated scene and simulated sound, and includes a cockpit, a load-bearing base, a power system, and a signal acquisition and communication system. The cockpit includes a control mechanism, a visual unit and an audio unit. The signal acquisition and communication system collects information from the control mechanism, the visual unit and the audio unit and transmits it to the main control computer module, and receives control information from the main control computer module to control the device.

[0028] The human perception processing module includes a flexible wearable wireless sensor for detecting the pilot's psychology and physiology, a signal receiving module and a processing module. The signal receiving module receives the simulated psychological and physiological parameter values ​​collected by the flexible wearable wireless sensor and inputs them into the processing module. The processing module stores a human comprehensive perception model. The human comprehensive perception model stores the correspondence between the actual psychological and physiological parameter values ​​and the actual flight state established by associating a large number of existing empirical aerodynamic parameters with the actual psychological and physiological parameter values ​​of the pilot during the flight, and the high-load simulation aerodynamic equation from the main control computer module. The processing module compares the simulated psychological and physiological parameter values ​​with the actual psychological and physiological parameter values, and corrects the parameters of the high-load simulation aerodynamic equation according to the difference between the two, so as to obtain the correction amount of the human comprehensive perception model to the high-load simulation aerodynamic equation parameters, and transmits the correction amount to the main control computer module;

[0029] The main control computer module establishes a high-load simulation aerodynamic equation based on the aircraft aerodynamic mathematical model. The parameters of the high-load simulation aerodynamic equation include longitudinal aerodynamic coefficients and lateral aerodynamic coefficients. The longitudinal aerodynamic coefficients and lateral aerodynamic coefficients include corrections to the parameters of the high-load simulation aerodynamic equation by the human body comprehensive perception model. At the same time, control information combined with the corrections is generated, including corresponding flight parameters, simulated scenes, simulated sounds and other information, and transmitted to the high-load flight simulation module. The high-load flight simulation module forms simulated flight state information based on the control information, that is, new parameter values ​​of corresponding parameters of the control mechanism, visual unit and audio unit, so that the simulated flight state formed by the high-load flight simulator pilot operating the control mechanism and the simulated psychological and physiological parameter values ​​generated by the simulator pilot are adapted to the actual psychological and physiological parameter values ​​under the corresponding actual flight state.

[0030] Preferably, the flexible wearable wireless sensor comprises: a flexible substrate material, a plurality of signal electrodes, a signal amplifier, a filter circuit, an analog-to-digital converter and a wireless transmission module;

[0031] The flexible substrate material provides stable support and enables the sensor to fit snugly against the skin;

[0032] The signal electrodes are arranged on the flexible base material, including forehead electrodes, eye electrodes and jaw electrodes respectively contacting corresponding parts of the head and face, the forehead electrodes are used to collect brain electrical signals, the eye electrodes are used to collect eye movement signals, and the jaw electrodes are used to collect mandibular electromyographic signals;

[0033] The signal amplifier is connected to the signal electrode and is used to amplify the signal data collected by the signal electrode;

[0034] The filtering circuit is connected to the signal amplifier and is used to remove noise and interference in the signal data;

[0035] The analog-to-digital converter is connected to the filtering circuit and is used to convert the filtered signal into a digital signal;

[0036] The wireless transmission module is connected to the analog-to-digital converter and is used to transmit the digital signal to a receiving device.

[0037] Further preferably, the eye electrodes include upper eyelid electrodes and lower eyelid electrodes respectively contacting corresponding parts of the eyes, measuring potential changes caused by eye movement to collect eye movement signals, and evaluating eye movement by analyzing the eye movement signals.

[0038] Further preferably, the jaw electrodes include temporalis muscle electrodes and mandibular electrodes respectively contacting corresponding parts of the jaw, and measuring electrical activities of the mandibular muscles to collect mandibular electromyographic signals.

[0039] Further preferably, the wireless transmission module uses WiFi or Bluetooth transmission to transmit data, and the flexible substrate material is made of polyimide or silicone.

[0040] Further preferably, the longitudinal aerodynamic coefficient and the lateral aerodynamic coefficient of the high-load simulation aerodynamic equation respectively include:

[0041] Longitudinal aerodynamic coefficients, including drag coefficient in the stable coordinate system , lift coefficient and the pitch moment coefficient in the body coordinate system , the calculation formula is as follows:

[0042] in, Zero lift drag coefficient, Induced drag coefficient, Reynolds number variation The correction amount, The drag coefficient correction amount caused by the damping plate, The additional drag coefficient correction amount caused by external attachments, Predictive control to correct the drag coefficient, The correction amount of the drag coefficient according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model;

[0043]

[0044] in, The lift coefficient at zero angle of attack is The elasticity of the aircraft structure The influence coefficient of Lift coefficient parameters, Angle of attack, Aeroelastic correction factor for lift coefficient slope, The derivative of the lift coefficient with respect to the horizontal tail deviation angle, Fully moving horizontal tail deflection angle, Predictive control to lift coefficient correction, The correction amount of lift coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0045] in, Aeroelastic correction factor for lift coefficient slope, Fully moving horizontal tail control derivative, Fully moving horizontal tail deflection angle, The relative position of the aircraft mass on the mean aerodynamic chord of the wing, The relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, The correction amount of the relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, Dimensionless longitudinal damping derivative, Dimensionless wash flow time derivative, The dimensionless angular velocity of the aircraft about its body axis, The relative position of the lift angle of attack, Predictive control correction of pitch moment coefficient, The correction amount of the pitch moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0046] Lateral aerodynamic coefficients, including side force coefficients in the stable coordinate system and the rolling moment in the body coordinate system , Yaw moment coefficient , the calculation formula is as follows:

[0047]

[0048] in , is the side force coefficient generated by a sideslip angle of 1°, Aircraft structural elasticity The incremental impact of is the sideslip angle, Aircraft structural elasticity The influence coefficient of The side force coefficient generated by a 1° rudder deflection is, Rudder, Predictive control of the lateral force coefficient correction, The correction amount of the lateral force coefficient according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model;

[0049]

[0050] in, Heading stability, Aircraft structural elasticity The incremental impact of Aileron deflection 1° produces , aileron, Machine structure elasticity The incremental impact of Rudder efficiency, Rudder, Dimensionless cross derivatives on the lateral side, , Dimensionless lateral damping derivative, Yaw angular velocity, , The total moving tail deflection 1° produces , Tail differential, , The correction amount of the yaw moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0051]

[0052] Lateral static stability, Aileron efficiency, aileron, Transverse dimensionless damping derivative, , Dimensionless cross derivatives on the lateral side, Yaw angular velocity, Aircraft structural elasticity The influence coefficient of The total moving tail deflection 1° produces , Tail differential, , The roll moment coefficient correction amount is made according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model.

[0053] Beneficial effects of the present invention:

[0054] The existing technology has a large number of empirical aerodynamic parameters and a large number of flight mechanics data corresponding to different aircraft models. The ministerial standard QJ2015-90 has released 81 aerodynamic parameters. Aviation medicine and animal experiments have a history of more than 40 years in my country in the psychological and physiological research of humans and animals in various body shapes and overweight environments, and have accumulated a large amount of empirical data. Therefore, combining a large number of actual empirical aerodynamic parameters, actual flight psychological and physiological tests, and aviation medicine animal experiments and other existing comprehensive research results can obtain different comprehensive body perception data of pilots in different specific flight states (flight postures). For the first time, the present invention associates these parameters and data with the psychological and physiological feelings (comprehensive body perception and parameters and data describing these perceptions) of pilots in these body shapes and pressures according to the aerodynamic parameters involved in different actual flight states and the resulting pilot postures and pressures, and aviation medicine and other research, and establishes a corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight state, so that high load can be collected through sensors. The simulated psychological and physiological parameter values ​​of the pilot in the simulated flight state corresponding to the actual flight state on the flight simulator are adjusted according to the differences between the simulated psychological and physiological parameter values ​​of the high-load flight simulator and the actual psychological and physiological parameter values, and then the control system of the high-load flight simulator (the high-load flight simulation module in the high-load flight simulation system) is adjusted, so that the simulated flight state of the simulator of the present invention can reach 80% to 85% of the actual flight state, and the corresponding pilot's real-time body perception (including psychological and physical comprehensive perception) and the comprehensive perception of flight in the actual flight state are also adapted by about 80% to 85%.

[0055] Specifically, the present invention provides a high-load flight simulation method and simulation system, which establishes a high-load simulation aerodynamic equation through a main control computer module, and generates control information for simulating continuous high-load flight in combination with a drag coefficient correction, a lift coefficient correction, and a pitch moment coefficient correction generated by a human body perception processing module, including simulated flight parameters, simulated scene parameters, simulated sound parameters, and other information, which are applied to the high-load flight simulation module to realize continuous load simulation flight; the human body perception processing module uses a portable wireless sensor to collect simulated psychological and physiological parameters of the pilot in continuous load flight, and processes the simulated psychological and physiological parameter values ​​according to the correspondence between the actual psychological and physiological parameter values ​​stored in the human body comprehensive perception model and the actual flight state, thereby adjusting the aerodynamic equation according to the difference between the aerodynamic parameter data of the simulated flight state of the high-load flight simulator and the aerodynamic parameter data of the actual flight state, including Equivalent predictive control correction, The correction amount of the human body comprehensive perception model is transmitted to the main control computer module, which forms new control information and applies it to the high-load flight simulation module to correct the control mechanism, visual unit and audio unit. When the simulator pilot subsequently manipulates the flight state, the simulated psychological and physiological perceptions produced by the simulator on the pilot, that is, the real-time comprehensive body perception, is adapted to the comprehensive flight perception of the pilot of the real aircraft in this flight state.

[0056] The high-load modeling of the present invention has both the characteristics of previous flight simulators and the embedding of a unique human comprehensive perception model, which is combined with the high-load flight simulation module to form control information, forming characteristics similar to motion platform control. These control information combined with comprehensive perception are information data that previous flight simulators have not accessed or collected, thereby improving the realism of flight training. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] Figure 1 This is a framework diagram of a high-load flight simulation system based on a portable wireless sensor in Example 1;

[0058] Figure 2 A comparison diagram of the simulator load spectrum curve of Example 2 and the actual fighter flight load spectrum curve;

[0059] Figure 3 This is a graph showing the change trend of the mental ability curves of sea flight and simulated flight as a function of the altitude (simulated altitude) S in Example 1.

[0060] Figure 4 A schematic diagram of a flexible wearable wireless sensor provided in this application. DETAILED DESCRIPTION

[0061] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0062] A high-load flight simulation method of this embodiment can obtain the corresponding relationship between the pilot's flight process corresponding to certain specific flight states, that is, the actual flight state and the actual psychological and physiological parameter values ​​by associating existing psychological and physiological parameters and data such as psychological, muscle and nerve reactions under different gravity accelerations and different body postures in aviation medicine and animal experiments with actual empirical aerodynamic parameters, that is, flight control parameters, under more than 60 specific flight states. The simulators of the prior art use at most a dozen groups of aerodynamic parameters, which is far less than the number of the present invention. Aviation medicine is the study of people's adaptability to aircraft and the ability of aircraft to act on people, specifically the physiological reactions and psychological stimulation of pilots. The corresponding relationship can also be obtained directly by testing the corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight state under different flight states when the pilot is performing a real flight. Therefore, the corresponding relationship between the above-mentioned actual psychological and physiological parameter values ​​and the actual flight state can be obtained in a variety of ways. The actual flight state and the simulated flight state both include at least one of boundary flight, entering and recovering from a stall, and entering and recovering from a spin. The large number of subjects is more than 60 (basically covering all aviation combat training subjects, including special subjects such as "stall-spin"), preferably more than 80. The ministerial standard QJ2015-90 publishes more than 80 aerodynamic parameters, which can accurately describe various flight states.

[0063] The simulated psychological and physiological data of the pilot in the simulated flight state simulated for the actual flight state of an actual flight on the high-load flight simulator are collected by sensors to obtain simulated psychological and physiological parameter values, and the control of the high-load flight simulator control system is corrected according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values, and the simulated flight state information of the high-load flight simulator is adjusted so that the further detected simulated psychological and physiological parameter values ​​are adapted to the actual psychological and physiological parameter values, so that the corresponding relationship between the simulated psychological and physiological parameter values ​​and the simulated flight state is adapted to the corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight state, and the simulated flight state information includes displacement parameters and rod force parameters for driving the high-load flight simulator control mechanism.

[0064] The control of the control system is corrected, which means that the parameters of the high-load simulation aerodynamic equation of the high-load flight simulator are corrected according to the difference to obtain a correction amount, and new simulated flight state information is formed, and then the action of the high-load flight simulator control system is corrected, so that the simulator pilot's operation of the control mechanism enables the simulator pilot to obtain a comprehensive feeling that is adapted to the operation of the actual flight state; the parameters of the high-load simulation aerodynamic equation include longitudinal aerodynamic coefficients and lateral aerodynamic coefficients, and the longitudinal aerodynamic coefficients and lateral aerodynamic coefficients include correction amounts for the high-load simulation aerodynamic equations, and the psychological and physiological parameters include existing empirical parameters and data from aviation medicine and animal experiments.

[0065] The actual psychological and physiological parameter values ​​and simulated psychological and physiological parameter values ​​collected by the sensors include the psychological and physiological parameter values ​​collected by the sensors attached to the pilot's head and face for approximately the same flight conditions (actual flight conditions and simulated flight conditions).

[0066] Under high-load flight, different flight states correspond to different aerodynamic equations and other different parameter values, and the pilots' perceptions of the flight process in different flight states also correspond to different specific psychological and physiological values. If there are differences between the parameter values ​​of psychological and physiological perceptions, it means that there are differences in the parameter values ​​of certain parameters of the aerodynamic equations. The corresponding parameters of the aerodynamic equations are adjusted to reduce the difference and applied to the high-load flight simulator in real time until the parameter values ​​of the simulated comprehensive perception of the flight state are adapted to the parameter values ​​of the actual comprehensive perception. This will enable the simulator to more realistically simulate real high-load flight.

[0067] Specifically, a high-load flight simulation system using the high-load flight simulation method is as follows: Figure 1 As shown, it includes: a high-load flight simulation module, a human perception processing module, and a main control computer module;

[0068] The high-load flight simulation module is a device that provides simulated actions of flight load, flight attitude adjustment, flight control, simulated scene and simulated sound, and includes a cockpit, a load-bearing base, a power system, and a signal acquisition and communication system. The cockpit includes a control mechanism, a visual unit and an audio unit. The signal acquisition and communication system collects information (operation information) from the control mechanism, the visual unit and the audio unit and transmits it to the main control computer module, and receives control information from the main control computer module to control the device;

[0069] The human perception processing module includes a flexible wearable wireless sensor for detecting the pilot's psychology and physiology, a signal receiving module and a processing module. The signal receiving module receives the simulated psychological and physiological parameter values ​​collected by the flexible wearable wireless sensor and inputs them into the processing module. The processing module stores a human comprehensive perception model. The human comprehensive perception model stores the correspondence between the actual psychological and physiological parameter values ​​and the actual flight state established by associating a large number of existing empirical aerodynamic parameters with the actual psychological and physiological parameters of the pilot during flight, and the high-load simulation aerodynamic equation from the main control computer module. The processing module compares the simulated psychological and physiological parameter values ​​with the actual psychological and physiological parameter values, and corrects the parameters of the high-load simulation aerodynamic equation according to the simulated correction amount formed by the difference between the two, so as to obtain the correction amount of the human comprehensive perception model to the high-load simulation aerodynamic equation, and transmit the correction amount to the main control computer module;

[0070] The main control computer module establishes a high-load simulation aerodynamic equation according to the aircraft aerodynamic mathematical model, and the parameters of the high-load simulation aerodynamic equation include longitudinal aerodynamic coefficient and lateral aerodynamic coefficient, and the longitudinal aerodynamic coefficient and lateral aerodynamic coefficient include the correction amount of the human body comprehensive perception model to the high-load simulation aerodynamic equation; at the same time, generates control information combined with the correction amount, including corresponding flight parameters, simulated scenes and simulated sounds, and transmits it to the high-load flight simulation module; the high-load flight simulation module forms updated simulated flight state information according to the control information, that is, the corresponding parameter values ​​of the control mechanism, the visual unit and the audio unit, so that the high-load flight simulator pilot operates the control mechanism (flight control) to form a simulated flight state, and the simulated flight state is adapted to the actual psychological and physiological parameter values ​​(visual, auditory and proprioceptive stimulation) generated by the simulator acting on the simulator pilot and the corresponding actual psychological and physiological parameter values ​​under the actual flight state. The simulator realizes simulated continuous load flight according to the modified flight parameters, the visual unit displays the simulated scene, and the audio unit plays the simulated sound.

[0071] The large number of empirical aerodynamic parameters include more than 60 groups of parameters such as drag coefficient, lift coefficient, moment coefficient, aerodynamic derivative, etc., preferably more than 80 groups of parameters.

[0072] The longitudinal aerodynamic coefficient and the lateral aerodynamic coefficient of the high-load simulation aerodynamic equation respectively include:

[0073] Longitudinal aerodynamic coefficients, including drag coefficient in the stable coordinate system , lift coefficient and the pitch moment coefficient in the body coordinate system , the calculation formula is as follows:

[0074] in, Zero lift drag coefficient, Induced drag coefficient, Reynolds number variation The correction amount, The drag coefficient correction amount caused by the damping plate, The additional drag coefficient correction amount caused by external attachments, Predictive control to correct the drag coefficient, The correction amount of the drag coefficient according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model;

[0075] in, The lift coefficient at zero angle of attack is The elasticity of the aircraft structure The influence coefficient of Lift coefficient parameters, Angle of attack, Aeroelastic correction factor for lift coefficient slope, The derivative of the lift coefficient with respect to the horizontal tail deviation angle, Fully moving horizontal tail deflection angle, Predictive control to lift coefficient correction, The correction amount of lift coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0076]

[0077] in, Aeroelastic correction factor for lift coefficient slope, Fully moving horizontal tail control derivative, Fully moving horizontal tail deflection angle, The relative position of the aircraft mass on the mean aerodynamic chord of the wing, The relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, The correction amount of the relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, Dimensionless longitudinal damping derivative, Dimensionless wash flow time derivative, The dimensionless angular velocity of the aircraft about its body axis, The relative position of the lift angle of attack, Predictive control correction of pitch moment coefficient, The correction amount of the pitch moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0078] Lateral aerodynamic coefficients, calculation of the side force coefficients in the stable coordinate system and the rolling moment in the body coordinate system , Yaw moment coefficient , the calculation formula is as follows:

[0079]

[0080] in , The side force coefficient generated by a 1° sideslip angle is Aircraft structural elasticity The incremental impact of Side slip angle, Aircraft structural elasticity The influence coefficient of The side force coefficient generated by a 1° rudder deflection is, Rudder, Predictive control of the lateral force coefficient correction, The correction amount of the lateral force coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0081]

[0082] in, Heading stability, Aircraft structural elasticity The incremental impact of Aileron deflection 1° produces , Ailerons (flaperons), Machine structure elasticity The incremental impact of Rudder efficiency, Rudder, Dimensionless cross derivatives on the lateral side, , Dimensionless lateral damping derivative, Yaw angular velocity, , The total moving tail deflection 1° produces , Tail differential, , The correction amount of the yaw moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values;

[0083]

[0084] in, Lateral static stability, Aileron efficiency, Ailerons (flaperons), Transverse dimensionless damping derivative, , Dimensionless cross derivatives on the lateral side, Yaw angular velocity, Aircraft structural elasticity The influence coefficient of The total moving tail deflection 1° produces , Tail differential, Predictive control for the correction of the rolling moment coefficient, The roll moment coefficient correction amount is made according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model.

[0085] In the correction equations of the above parameters, except for the correction of each parameter by predictive control and the correction amounts in the human body comprehensive perception model based on the differences between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values, the other items are conventional calculation items of the existing high-load simulator.

[0086] The correction quantities of predictive control are the correction quantities caused by the difference between the control of the simulator and the control of the actual flight, because the control of the simulator is not a pulse quantity but a smooth quantity.

[0087] For example, this embodiment is to change the F of a certain force F n-1 , F n-2 ……F n-5 Items are compared to determine their trend, whether it is rising, falling, or a turning point. Then, according to the trend, F n+1 , F n+2 ……F n+5 For example, if the trend is rising, the current and voltage of F are increased or doubled, and vice versa if it is falling. The correction amount of predictive control is different for different aircraft models and different flight states.

[0088] In this embodiment, the correction amount in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​is calculated by the mental ability parameter P q For example, when a pilot at sea actually flies a certain type of aircraft, although low-altitude flying is beneficial for avoiding radar, it is very difficult to control. Therefore, it is necessary to simulate the state of low-altitude flying over the sea. In the low-altitude flying state, the closer to the low altitude, the more tense the mind and muscles are. q Therefore, for the safety of flight, the mental ability P q Need to meet the requirements of the job. Figure 3The curves of the mental ability of sea flight and simulated flight change with the altitude (simulated altitude) S. The mental ability P has been obtained based on the empirical aerodynamic parameters of low-altitude flight and medical and animal experimental data. q The curve of the change with height, that is, the actual psychological and physiological parameter value curve, is the upper curve in the figure - the actual P q The corresponding relationship between the altitude parameter S and the low-altitude flight state, and S can correspond to the flight control parameter, that is, the other aerodynamic parameters can be related to the mental ability parameter P by the same logic. q The relationship between the actual flight state and the actual psychological and physiological parameters is established for a large number of aerodynamic parameters; the simulated psychological and physiological parameter values ​​of the pilot under the corresponding flight state simulated on the high-load flight simulator are collected by sensors, and the lower curve - simulated P q The corresponding relationship with the actual low-altitude flight state S, that is, the simulated P q The corresponding relationship with the simulated flight state is obtained according to the two curves. The control of the high load simulator control system can be corrected to adjust the simulated flight state so that the simulated P q Achieved and actual P q Adaptation; further, the association of other aerodynamic parameters with psychological and physiological parameters can have more corrections, conduct comprehensive evaluation, and obtain more accurate corrections: , , , , , thereby achieving a high degree of simulation of the low-altitude flight state.

[0089] The high-load flight simulation system of the present invention has a basic structure similar to that of an existing simulator, including a cockpit, a load-bearing base and a power system. The cockpit includes a control mechanism, a visual unit and an audio unit. The operating parameters in the simulated flight status information, including displacement parameters and rod force parameters, are generated by manipulating the control mechanism, and the operating parameters are transmitted to the main control computer module through a signal acquisition and communication system. Then, the signal acquisition and communication system also receives the flight parameters, simulated scenes and simulated sounds, and simulates continuous load flight according to the flight parameters. The visual unit displays the simulated scenes, and the audio unit plays the simulated sounds.

[0090] like Figure 4 As shown, the flexible wearable wireless sensor includes: a flexible substrate material 1, a plurality of signal electrodes 2, a signal amplifier 3, a filter circuit 4, an analog-to-digital converter 5 and a wireless transmission module 6;

[0091] The flexible substrate material 1 provides stable support and enables the sensor to fit closely to the skin;

[0092] The signal electrodes 2 are arranged on the flexible base material, and include a forehead electrode 21, an eye electrode 22 and a jaw electrode 23 respectively contacting corresponding parts of the face, wherein the forehead electrode 21 is used to collect brain electrical signals, the eye electrode 22 is used to collect eye movement signals, and the jaw electrode 23 is used to collect mandibular electromyographic signals;

[0093] The signal amplifier 3 is connected to the signal electrode 2 and is used to amplify the signal data collected by the signal electrode;

[0094] The filtering circuit 4 is connected to the signal amplifier 3 and is used to remove noise and interference in the signal data;

[0095] The analog-to-digital converter 5 is connected to the filter circuit 4 and is used to convert the filtered signal data into a digital signal;

[0096] The wireless transmission module 6 is connected to the analog-to-digital converter 5 and is used to transmit the digital signal to a receiving device.

[0097] Specifically, the eye electrode 22 includes an upper eyelid electrode 221 and a lower eyelid electrode 222 that contact corresponding parts of the eye respectively, measure the potential change generated by eye movement to collect eye movement signals, and evaluate eye movement by analyzing the eye movement signals.

[0098] The jaw electrode 23 includes a temporalis electrode 231 and a mandibular electrode 232 which are respectively in contact with corresponding parts of the jaw, and measures the electrical activity of the mandibular muscles to collect mandibular myoelectric signals.

[0099] The wireless transmission module 6 uses WiFi or Bluetooth transmission to transmit data.

[0100] The flexible base material 1 may preferably be made of polyimide or silicone.

[0101] The flexible base material 1 is provided with various specifications according to the body shapes of different people, and has stickiness on the side that needs to contact with the skin.

[0102] like Figure 2 As shown, according to the experiment, the overlap between the actual flight curve and the prototype flight curve is very high, exceeding 80%, which can realize high-load flight simulation and solve the technical problem of the present invention.

[0103] It should be noted that the above-described specific implementations can enable those skilled in the art to more fully understand the invention, but do not limit the invention in any way. Therefore, although this specification has described the invention in detail with reference to the drawings and embodiments, those skilled in the art should understand that the invention can still be modified or replaced by equivalents. In short, all technical solutions and improvements that do not deviate from the spirit and scope of the invention should be included in the protection scope of the patent for the invention.

Claims

1. A high-load flight simulation method, characterized in that: Correlate a large number of existing empirical aerodynamic parameters with the actual psychological and physiological parameters of pilots during flight, and establish the corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight status; Collecting the simulated psychological and physiological data of the pilot in the simulated flight state simulated for the actual flight state of the actual flight on the high-load flight simulator through sensors to obtain simulated psychological and physiological parameter values, correcting the control of the high-load flight simulator control system according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values, adjusting the simulated flight state information of the high-load flight simulator, so that the further detected simulated psychological and physiological parameter values ​​are adapted to the actual psychological and physiological parameter values, so that the corresponding relationship between the simulated psychological and physiological parameter values ​​and the simulated flight state is adapted to the corresponding relationship between the actual psychological and physiological parameter values ​​and the actual flight state, the simulated flight state information including displacement parameters and rod force parameters for driving the high-load flight simulator control mechanism; The correction of the control of the high-load flight simulator control system refers to correcting the high-load simulation aerodynamic equation parameters of the high-load flight simulator according to the difference to obtain a correction amount, wherein the high-load simulation aerodynamic equation parameters include a longitudinal aerodynamic coefficient and a lateral aerodynamic coefficient, and the longitudinal aerodynamic coefficient and the lateral aerodynamic coefficient include the correction amount; The longitudinal aerodynamic coefficient and the lateral aerodynamic coefficient of the high-load simulation aerodynamic equation respectively include: Longitudinal aerodynamic coefficients, including drag coefficient in the stable coordinate system , lift coefficient and the pitch moment coefficient in the body coordinate system , the calculation formula is as follows: in, Zero lift drag coefficient, Induced drag coefficient, Reynolds number variation The correction amount, The drag coefficient correction amount caused by the damping plate, The additional drag coefficient correction amount caused by external attachments, Predictive control to correct the drag coefficient, The correction amount of the drag coefficient according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model; in, The lift coefficient at zero angle of attack is The elasticity of the aircraft structure The influence coefficient of Lift coefficient parameters, Angle of attack, Aeroelastic correction factor for lift coefficient slope, The derivative of the lift coefficient with respect to the horizontal tail deviation angle, Fully moving horizontal tail deflection angle, Predictive control to lift coefficient correction, The correction amount of lift coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; in, Aeroelastic correction factor for lift coefficient slope, Fully moving horizontal tail control derivative, Fully moving horizontal tail deflection angle, The relative position of the aircraft mass on the mean aerodynamic chord of the wing, The relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, The correction amount of the relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, Dimensionless longitudinal damping derivative, Dimensionless wash flow time derivative, The dimensionless angular velocity of the aircraft about its body axis, The relative position of the lift angle of attack, Predictive control to the pitch moment coefficient correction, The correction amount of the pitch moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; Lateral aerodynamic coefficients, including side force coefficients in the stable coordinate system and the rolling moment in the body coordinate system , Yaw moment coefficient , the calculation formula is as follows: in , is the side force coefficient generated by a sideslip angle of 1°, Aircraft structural elasticity The incremental impact of is the sideslip angle, Aircraft structural elasticity The influence coefficient of The side force coefficient generated by a 1° rudder deflection is Rudder, Predictive control of the lateral force coefficient correction, The correction amount of the lateral force coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; in, Heading stability, Aircraft structural elasticity The incremental impact of Aileron deflection 1° produces , aileron, Machine structure elasticity The incremental impact of Rudder efficiency, Rudder, Dimensionless cross derivatives on the lateral side, , Dimensionless lateral damping derivative, Yaw angular velocity, , The total moving tail deflection 1° produces , Tail differential, , The correction amount of the yaw moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; Lateral static stability, Aileron efficiency, aileron, Transverse dimensionless damping derivative, , Dimensionless cross derivatives on the lateral side, Yaw angular velocity, Aircraft structural elasticity The influence coefficient of The total moving tail deflection 1° produces , Tail differential, , The roll moment coefficient correction amount is made according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model.

2. The method according to claim 1, characterized in that The actual flight state and the simulated flight state both include at least one of boundary flight, entering and recovering from a stall, and entering and recovering from a spin, and the large number of subjects is more than sixty.

3. The method according to claim 2, characterized in that The correction of the control of the high-load flight simulator control system refers to correcting the high-load simulation aerodynamic equation parameters of the high-load flight simulator according to the difference to obtain a correction amount, and forming new simulated flight state information, and then correcting the action of the high-load flight simulator control system so that the simulator pilot obtains a comprehensive feeling of the operation of the control mechanism that is adapted to the operation of the actual flight state; the high-load simulation aerodynamic equation parameters include longitudinal aerodynamic coefficients and lateral aerodynamic coefficients, the longitudinal aerodynamic coefficients and lateral aerodynamic coefficients include the correction amount, and the actual psychological and physiological parameters include existing empirical parameters of aviation medicine and animal experiments.

4. The method according to claim 3, characterized in that The actual psychological and physiological parameter values ​​and simulated psychological and physiological parameter values ​​collected by the sensor are obtained by substituting the psychological and physiological data collected by the sensor fitted on the pilot's head and face into the psychological and physiological parameters.

5. A high-load flight simulation system, characterized in that It includes high-load flight simulation module, human perception processing module and main control computer module. The high-load flight simulation module is a device that provides flight load, flight attitude adjustment, flight control, simulated scene and simulated sound, and includes a cockpit, a load-bearing base, a power system, and a signal acquisition and communication system. The cockpit includes a control mechanism, a visual unit and an audio unit. The signal acquisition and communication system collects information from the control mechanism, the visual unit and the audio unit and transmits it to the main control computer module, and receives control information from the main control computer module to control the device. The human perception processing module includes a flexible wearable wireless sensor for detecting the pilot's psychology and physiology, a signal receiving module and a processing module. The signal receiving module receives the simulated psychological and physiological parameter values ​​collected by the flexible wearable wireless sensor and inputs them into the processing module. The processing module stores a human comprehensive perception model. The human comprehensive perception model stores the correspondence between the actual psychological and physiological parameter values ​​and the actual flight state established by associating a large number of existing empirical aerodynamic parameters with the actual psychological and physiological parameter values ​​of the pilot during flight, and the high-load simulation aerodynamic equation from the main control computer module. The processing module compares the simulated psychological and physiological parameter values ​​with the actual psychological and physiological parameter values, and corrects the high-load simulation aerodynamic equation parameters according to the difference between the two, so as to obtain the correction amount of the human comprehensive perception model to the high-load simulation aerodynamic equation parameters, and transmits the correction amount to the main control computer module; The main control computer module establishes a high-load simulation aerodynamic equation according to the aircraft aerodynamic mathematical model, wherein the parameters of the high-load simulation aerodynamic equation include longitudinal aerodynamic coefficient and lateral aerodynamic coefficient, wherein the longitudinal aerodynamic coefficient and lateral aerodynamic coefficient include corrections made by the human body comprehensive perception model to the parameters of the high-load simulation aerodynamic equation; at the same time, generates control information combined with the corrections, including corresponding flight parameters, simulated scenes, simulated sounds and other information, and transmits the information to the high-load flight simulation module; the high-load flight simulation module forms simulated flight state information according to the control information, i.e., new parameter values ​​of corresponding parameters of the control mechanism, the visual unit and the audio unit, so that the simulated flight state formed by the high-load flight simulator pilot operating the control mechanism and the simulated psychological and physiological parameter values ​​generated by the simulator pilot are adapted to the actual psychological and physiological parameter values ​​under the corresponding actual flight state; The longitudinal aerodynamic coefficient and the lateral aerodynamic coefficient of the high-load simulation aerodynamic equation respectively include: Longitudinal aerodynamic coefficients, including drag coefficient in the stable coordinate system , lift coefficient and the pitch moment coefficient in the body coordinate system , the calculation formula is as follows: in, Zero lift drag coefficient, Induced drag coefficient, Reynolds number variation The correction amount, The drag coefficient correction amount caused by the damping plate, The additional drag coefficient correction amount caused by external attachments, Predictive control to correct the drag coefficient, The correction amount of the drag coefficient according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model; in, The lift coefficient at zero angle of attack is The elasticity of the aircraft structure The influence coefficient of Lift coefficient parameters, Angle of attack, Aeroelastic correction factor for lift coefficient slope, The derivative of the lift coefficient with respect to the horizontal tail deviation angle, Fully moving horizontal tail deflection angle, Predictive control to lift coefficient correction, The correction amount of lift coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; in, Aeroelastic correction factor for lift coefficient slope, Fully moving horizontal tail control derivative, Fully moving horizontal tail deflection angle, The relative position of the aircraft mass on the mean aerodynamic chord of the wing, The relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, The correction amount of the relative position of the focus of the whole aircraft on the average aerodynamic chord of the wing, Dimensionless longitudinal damping derivative, Dimensionless wash flow time derivative, The dimensionless angular velocity of the aircraft about its body axis, The relative position of the lift angle of attack, Predictive control to the pitch moment coefficient correction, The correction amount of the pitch moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; Lateral aerodynamic coefficients, including side force coefficients in the stable coordinate system and the rolling moment in the body coordinate system , Yaw moment coefficient , the calculation formula is as follows: in , is the side force coefficient generated by a sideslip angle of 1°, Aircraft structural elasticity The incremental impact of is the sideslip angle, Aircraft structural elasticity The influence coefficient of The side force coefficient generated by a 1° rudder deflection is Rudder, Predictive control of the lateral force coefficient correction, The correction amount of the lateral force coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; in, Heading stability, Aircraft structural elasticity The incremental impact of Aileron deflection 1° produces , aileron, Machine structure elasticity The incremental impact of Rudder efficiency, Rudder, Dimensionless cross derivatives on the lateral side, , Dimensionless lateral damping derivative, Yaw angular velocity, , The total moving tail deflection 1° produces , Tail differential, , The correction amount of the yaw moment coefficient in the human body comprehensive perception model according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values; Lateral static stability, Aileron efficiency, aileron, Transverse dimensionless damping derivative, , Dimensionless cross derivatives on the lateral side, Yaw angular velocity, Aircraft structural elasticity The influence coefficient of The total moving tail deflection 1° produces , Tail differential, , The roll moment coefficient correction amount is made according to the difference between the actual psychological and physiological parameter values ​​and the simulated psychological and physiological parameter values ​​in the human body comprehensive perception model.

6. The simulation system according to claim 5, characterized in that The flexible wearable wireless sensor comprises: a flexible substrate material, a plurality of signal electrodes, a signal amplifier, a filter circuit, an analog-to-digital converter and a wireless transmission module; The flexible substrate material provides stable support and enables the sensor to fit snugly against the skin; The signal electrodes are arranged on the flexible base material, including forehead electrodes, eye electrodes and jaw electrodes respectively contacting corresponding parts of the head and face, the forehead electrodes are used to collect brain electrical signals, the eye electrodes are used to collect eye movement signals, and the jaw electrodes are used to collect mandibular electromyographic signals; The signal amplifier is connected to the signal electrode and is used to amplify the signal data collected by the signal electrode; The filtering circuit is connected to the signal amplifier and is used to remove noise and interference in the signal data; The analog-to-digital converter is connected to the filtering circuit and is used to convert the filtered signal into a digital signal; The wireless transmission module is connected to the analog-to-digital converter and is used to transmit the digital signal to a receiving device.

7. The simulation system according to claim 6, characterized in that: The eye electrodes include an upper eyelid electrode and a lower eyelid electrode that contact corresponding parts of the eye respectively, measure the potential changes caused by eye movement to collect eye movement signals, and evaluate eye movement by analyzing the eye movement signals.

8. The simulation system according to claim 7, characterized in that: The jaw electrodes include a temporalis electrode and a mandibular electrode respectively contacting corresponding parts of the jaw, and measure the electrical activity of the mandibular muscles to collect mandibular electromyographic signals.

9. The simulation system according to claim 8, characterized in that: The wireless transmission module uses WiFi or Bluetooth transmission to transmit data, and the flexible substrate material is made of polyimide or silicone.

Images