Airborne equipment ground verification method based on situation construction

Abstract

The invention discloses an airborne equipment ground verification method based on situation construction, and belongs to the field of semi-physical simulation testing. The method comprises the following steps: generating situation information of a carrier aircraft and a friend aircraft according to a target motion track; calculating atmospheric transmission characteristics between the target and the airborne equipment in combination with the situation information; based on the influence of the atmospheric transmission characteristics on the target, correcting the actually collected target intrinsic radiation parameter to obtain the target radiation brightness received by the airborne photoelectric equipment; infrared characteristics of the sky background are calculated; quantification and display of infrared radiation; and carrying out semi-physical simulation verification based on the situation data and the infrared scene. According to the method, outfield actual measurement data are fully utilized, situation information is constructed from an airborne equipment use scene, target radiation characteristic collection, motion characteristic modeling and a semi-physical simulation test are organically combined, and a controllable and repeatable ground verification means is provided for airborne equipment on the premise that the simulation confidence is effectively improved.

Description

Technical Field

[0001] The invention belongs to the field of semi-physical simulation testing, and in particular relates to a ground verification method for airborne equipment based on situation construction. Background Art

[0002] With the advancement of optoelectronic detection technology, the application of airborne optoelectronic equipment has developed rapidly. In order to build an aerospace defense system, the detection demand for high-speed targets such as intelligent entities and near-space aircraft is more urgent. However, the particularity of such targets makes it very difficult to conduct flight tests on airborne equipment. Not only does it cost a huge amount of manpower and material resources, but one test cannot cover all situations such as target movement and weather factors, making it impossible to make a comprehensive evaluation of the functions and performance of airborne equipment. Therefore, it is urgent to study a ground test method that can conduct conditionally controllable and repeatable verification of airborne equipment in a laboratory environment.

[0003] The current ground testing method does not consider the impact of atmospheric transmittance, atmospheric path radiation and solar radiation on the test results, which leads to large errors in the test results and makes it impossible to obtain true simulation results. Summary of the invention

[0004] Technical issues to be solved:

[0005] In order to avoid the shortcomings of the prior art, the present invention provides a method for ground verification of airborne equipment based on situation construction. Starting from the indicators of airborne equipment, a situation that meets the needs of target detection, tracking and collaborative positioning is constructed; the situation information is used as the input condition for calculating the atmospheric transmission characteristics, and the intrinsic radiation parameters of the target are corrected by atmospheric transmission to obtain the target radiation brightness received by the airborne equipment; the radiation brightness of the target and the sky background is quantified and gray-mapped, and an infrared sequence image is generated as a video excitation of the airborne equipment, and a semi-physical simulation environment is constructed to carry out ground verification tests. The method of the present invention makes full use of field measured data, and constructs situation information based on the use scenario of the airborne equipment, organically combines the target radiation characteristic acquisition, motion characteristic modeling and semi-physical simulation test, and provides a controllable and repeatable ground verification means for the airborne equipment on the premise of effectively improving the simulation confidence.

[0006] The technical solution of the present invention is: a ground verification method for airborne equipment based on situation construction, the specific steps are as follows:

[0007] Generate simulated situation information of carrier aircraft and friendly aircraft according to target motion trajectory;

[0008] Combined with simulated situation information, theoretical atmospheric transmission characteristics between the target and the airborne equipment are calculated;

[0009] Based on the influence of theoretical atmospheric transmission characteristics on the target, the actual target intrinsic radiation parameters are corrected to obtain the target radiation brightness received by the airborne optoelectronic equipment;

[0010] Calculation of infrared characteristics of sky background;

[0011] Quantification and display of infrared radiation;

[0012] Carry out semi-physical simulation verification based on situation data and infrared scenes.

[0013] A further technical solution of the present invention is: the method for acquiring simulated situation information of the carrier aircraft and the friendly aircraft plans the flight range of the carrier aircraft and the friendly aircraft according to the typical mission mode and motion trajectory of the target, combined with the detection and tracking distance of the airborne equipment; uses dual-aircraft / multi-aircraft collaborative detection as a positioning means, and according to the angular measurement accuracy and tracking accuracy indicators of the airborne equipment, constructs a situation that meets the positioning accuracy requirements of the airborne equipment, and plans the flight trajectory of the carrier aircraft and the friendly aircraft; according to the motion trajectory of the carrier aircraft / friendly aircraft, uses a modeling toolbox to build a six-degree-of-freedom digital model of the aircraft, sets a simulation cycle, and calculates the position and attitude information of the carrier aircraft / friendly aircraft.

[0014] A further technical solution of the present invention is: a method for calculating the theoretical atmospheric transmission characteristics between the target and the airborne equipment, obtaining the distance and relative angle between the carrier aircraft / friendly aircraft and the target according to the simulated situation information, and selecting the corresponding atmospheric mode and time, and meteorological conditions, and using the distance and relative angle between the carrier aircraft / friendly aircraft and the target, the atmospheric mode and time, the meteorological conditions, and the carrier aircraft height, the observed slant range, and the observed zenith angle at each simulation moment as inputs to the atmospheric radiation transmission software, and solving to obtain the theoretical atmospheric transmittance τ corresponding to the mission mode and motion trajectory cal , Theoretical atmospheric radiation L cal and theoretical solar radiation.

[0015] A further technical solution of the present invention is: the calculation method of the target radiation brightness received by the airborne optoelectronic device is:

[0016] Under the measured meteorological conditions, the radiation brightness of the black body at different temperatures was tested by infrared thermal imager, and the measured atmospheric path radiation L under the measured weather conditions was calculated. path and the measured atmospheric transmittance τ path ;

[0017] The observation conditions under the measured meteorological conditions are input into the atmospheric radiation transmission software to calculate the theoretical atmospheric path radiation L under the meteorological conditions. Modtran and theoretical atmospheric transmittance τ Modtran , combined with the measured atmospheric radiation L path and the measured atmospheric transmittance τ path Calculate the atmospheric radiation correction factor C pathand atmospheric transmittance correction factor C τ , for the theoretical atmospheric transmittance τ cal , Theoretical atmospheric radiation L cal make corrections;

[0018] The measured intrinsic radiation parameters of the target are corrected to obtain the target radiation brightness received by the airborne optoelectronic equipment. The calculation formula is as follows:

[0019] L T =C τ ·τ cal ·L 本 +C path ·L cal

[0020] Where, L T represents the target radiation brightness received by the airborne optoelectronic equipment after correction, C τ is the atmospheric transmittance correction coefficient, C path is the atmospheric radiation correction factor, L 本 is the intrinsic radiance of the target.

[0021] A further technical solution of the present invention is: the calculation formula of the measured atmospheric radiation is as follows:

[0022]

[0023] In the formula, DN1 and DN2 are the output values ​​of the infrared thermal imager at different black body temperatures; k is the radiance responsivity of the infrared thermal imager; L1 and L2 are the radiance of the black body at different temperatures; DN0 is the bias value caused by the thermal radiation of the infrared thermal imager itself and the background radiation factors;

[0024] The calculation formula of the measured atmospheric transmittance is as follows:

[0025]

[0026] A further technical solution of the present invention is: the atmospheric path radiation correction coefficient C path and atmospheric transmittance correction factor C τ The calculation formula is as follows:

[0027]

[0028] A further technical solution of the present invention is: the infrared characteristic calculation method of the sky background is:

[0029] Construct a hemispherical sky geometry model;

[0030] The sky radiance under different atmospheric modes, aerosol types, meteorological conditions, zenith angles and sampling altitudes is calculated by atmospheric radiative transfer software;

[0031] Assuming that the sky background infrared image is consistent in the horizontal direction, a sky image matrix is ​​generated according to the size of the simulation scene, and a uniform sky background image under cloudless conditions is generated according to the grayscale mapping relationship of the radiation brightness; the infrared image of the sky is used as a texture mapping on the hemispherical sky geometric model to form a sky infrared scene under a single condition;

[0032] The sky radiation brightness is calculated under different atmospheric modes, aerosol types, meteorological conditions and sampling altitudes to generate a radiation characteristic database. The corresponding radiation value is queried in real time in the database according to the observation altitude and angle of the airborne equipment to obtain an infrared sky background with dynamic effects.

[0033] A further technical solution of the present invention is: the method for quantifying and displaying infrared radiation is to use an open source scene graphics engine to synthesize and render the infrared target and the sky background to generate an 8-bit grayscale image under the observation angle of the airborne optoelectronic device.

[0034] A further technical solution of the present invention is: the semi-physical simulation verification method based on situation data and infrared scenes is to construct a semi-physical simulation test system with a simulation experiment integrated control system, a flight simulation workstation, a flight simulation turntable, a scene simulation workstation and a dynamic target simulator as the main body. The entire simulation environment adopts a reflective memory communication network, uses situation information as test input, and uses dynamic scenes generated by corresponding situation data as video excitation to carry out ground verification tests of airborne equipment.

[0035] A semi-physical simulation test system for ground verification of airborne equipment based on situation construction, including a simulation experiment integrated control system, a flight simulation workstation, a flight simulation turntable, a scenario simulation workstation and a dynamic target simulator. The whole simulation environment adopts a reflective memory communication network;

[0036] The simulation experiment integrated control system is used for the control of all simulation nodes, the sending and receiving of all data, and the record management;

[0037] The flight simulation workstation operates according to the simulated situation information, distributes the situation information to the control consoles of the two flight simulation turntables and the two scenario simulation workstations, simulates the attitude changes of the carrier aircraft or the friendly aircraft through three axes in the flight simulation turntable, simulates the relative position between the target and the carrier aircraft or the friendly aircraft through two axes outside the turntable, and drives the dynamic target simulator installed on the two-axis target table to the direction where the target is located;

[0038] Two sets of airborne optoelectronic equipment are installed at the rotation center of two flight simulation turntables through tooling, and the airborne optoelectronic equipment uses its own data link for communication and interaction;

[0039] The two scene simulation workstations simulate the positions of the carrier aircraft and the friendly aircraft's viewpoints in the scene respectively according to the received situation information, and set the observation direction of the viewpoint according to the angle of the two-axis target station. Real-time rendering is performed according to the airborne equipment ground verification method based on situation construction, and the infrared visual scene that should be observed by the optoelectronic detection equipment mounted on the carrier aircraft and the friendly aircraft is generated. The visual scene is transmitted to the corresponding dynamic target simulator through the video interface. The dynamic target simulator converts the infrared visual scene into an infrared radiation signal and emits it to stimulate the infrared sensor imaging of the airborne optoelectronic equipment.

[0040] Beneficial Effects

[0041] The beneficial effects of the present invention are as follows: the present invention is a ground verification method for airborne equipment based on situation construction, which makes full use of field measured data, and constructs situation information based on the mission usage scenario of the airborne equipment, and organically combines the target radiation characteristic acquisition, motion characteristic modeling and semi-physical simulation test, and provides a controllable and repeatable ground verification means for the airborne equipment under the premise of effectively improving the simulation confidence.

[0042] The present invention makes full use of limited measured target radiation data, conducts mission situation research, calculates atmospheric transmission characteristics and sky background radiation under different situations, and then fuses the target and background after correcting the target radiation, and renders and generates dynamic infrared scenes as video excitation for semi-physical simulation experiments on the ground. The real airborne optoelectronic equipment is introduced into the simulation test loop to form a semi-physical simulation test environment, realize laboratory reproduction of the mission environment, and strongly support the algorithm development, debugging and performance verification of airborne optoelectronic equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 It is a flow chart of a method for ground verification of airborne equipment based on situation construction of the present invention;

[0044] Figure 2 It is a composition diagram of the semi-physical simulation experiment system of the present invention.

[0045] Explanation of the accompanying drawings: 1. Simulation experiment integrated control system, 2. Flight simulation workstation, 3. Flight simulation turntable, 4. Scenario simulation workstation, 5. Dynamic target simulator, 6. Airborne optoelectronic equipment, 7. Flight simulation turntable console, 8. Reflective memory switch. DETAILED DESCRIPTION

[0046] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0047] Based on the fact that the current ground test method does not consider the influence of atmospheric transmittance, atmospheric path radiation and solar radiation on the test results, which leads to large errors in the test results and the problem that the real simulation results cannot be obtained, the present invention provides a ground verification method for airborne equipment based on situation construction, which constructs a situation that meets the needs of target detection, tracking and collaborative positioning based on the indicators of the airborne equipment; uses situation information as the input condition for calculating the atmospheric transmission characteristics, refers to the measured atmospheric transmittance and atmospheric path radiation values, corrects the MODTRAN calculation results, and then superimposes the atmospheric transmission influence on the basis of the target intrinsic radiation parameters to obtain the target radiation brightness received by the airborne equipment; uses the atmospheric model to calculate the atmospheric transmission characteristics of the target, and obtains the target radiation brightness received by the airborne equipment. , aerosol type, meteorological conditions and sampling altitude conditions, calculate the sky radiation brightness as input, generate a radiation characteristic database, query the corresponding radiation value in the database in real time according to the observation height and angle of the airborne equipment, and dynamically generate an infrared sky background; quantify and gray-map the radiation brightness of the target and the sky background, and generate infrared sequence images as video excitation for the airborne equipment; build a semi-physical simulation test system with a simulation experiment integrated control system, a flight simulation workstation, a flight simulation turntable, a scene simulation workstation and a dynamic target simulator as the main body, use situation information as test input, and the dynamic scene generated by the corresponding situation data as video excitation to carry out ground verification tests of airborne equipment.

[0048] The above technical solution is further described below in conjunction with the accompanying drawings:

[0049] parameter Figure 1 As shown, the specific steps of a method for ground verification of airborne equipment based on situation construction in this embodiment are as follows:

[0050] Step 1: Generate simulation situation information

[0051] According to the typical mission mode and motion trajectory of the target, combined with the detection and tracking distance of the airborne equipment, the flight range of the carrier aircraft and friendly aircraft is planned; considering the need for covert detection, dual / multi-aircraft collaborative detection is used as a positioning method, and according to the angular measurement accuracy and tracking accuracy indicators of the airborne equipment, a situation that meets the positioning accuracy requirements of the airborne equipment is constructed to plan the flight trajectory of the carrier aircraft and friendly aircraft; according to the motion trajectory of the carrier aircraft / friendly aircraft, a six-degree-of-freedom digital model of the aircraft is built using Matlab's Simulink toolbox, and the position and attitude information of the carrier aircraft / friendly aircraft is calculated with a simulation cycle of 5ms.

[0052] Step 2: Calculate the atmospheric transmission characteristics between the target and the airborne equipment based on the situation information

[0053] After obtaining the simulated situation information, the atmospheric mode and time are selected according to the distance and relative angle between the carrier aircraft / friendly aircraft and the target, and the corresponding meteorological conditions are input. The carrier aircraft altitude, observation slant range, and observation zenith angle at each simulation moment are used as inputs of the atmospheric radiation transmission software MODTRAN to solve the corresponding theoretical atmospheric transmittance, theoretical atmospheric path radiation, and theoretical solar radiation under the mission path.

[0054] Step 3: Calculate the target radiation brightness before reaching the airborne optoelectronic device

[0055] Under the actual meteorological conditions, the infrared thermal imager is used to test the radiation brightness of the black body under the same meteorological conditions and different temperatures. The actual atmospheric path radiation L under the weather conditions is calculated according to formula (1): path , according to formula (2) to calculate the measured atmospheric transmittance τ path ; Input the same observation conditions into MODTRAN software to calculate the atmospheric radiation L Modtran and atmospheric transmittance τ Modtran , refer to the measured value to correct the calculation result of MODTRAN software; then, according to formula (3), correct the measured target intrinsic radiation parameter to obtain the target radiation brightness received by the airborne optoelectronic equipment.

[0056]

[0057] In the formula: DN1 and DN2 are the output values ​​of the infrared thermal imager at different black body temperatures; k is the radiance responsivity of the infrared thermal imager; L1 and L2 are the radiance of the black body at different temperatures, which can be calculated by Planck's formula; DN0 is the bias value caused by factors such as the infrared thermal imager's own thermal radiation and background radiation.

[0058] L T =C τ ·τ cal ·L 本 +C path ·L cal (3)

[0059] Where: L T is the radiant brightness of the target reaching the lens of the airborne device, τ cal and L cal is the theoretical atmospheric transmittance and theoretical atmospheric path radiation calculated in MODTRAN software according to step 2, L 本 is the intrinsic radiance of the target.

[0060] Step 4: Calculate the infrared characteristics of the sky background

[0061] Firstly, a hemispherical sky geometry model is constructed; then, the sky radiance under different atmospheric modes, aerosol types, meteorological conditions, zenith angles and sampling altitudes is calculated by using MODTRAN software; assuming that the sky background infrared image is consistent in the horizontal direction, a sky image matrix is ​​generated according to the size of the simulation scene, and a uniform sky background image under cloudless conditions is generated according to the grayscale mapping relationship of the radiance; the infrared image of the sky is used as a texture mapping on the three-dimensional hemispherical model of the sky to form an infrared view of the sky under a single condition; the sky radiance is calculated under different atmospheric modes, aerosol types, meteorological conditions and sampling altitudes, and a radiation characteristic database is generated. According to the observation height and angle of the airborne equipment, the corresponding radiation value is queried in real time in the database, and an infrared sky background with dynamic effects can be obtained.

[0062] Step 5: Quantification and Display of Infrared Radiation

[0063] The open source scene graphics engine (OSG) is used to synthesize and render the infrared target and background to generate an 8-bit grayscale image at the observation angle of the airborne optoelectronic equipment.

[0064] Step 6: Conduct semi-physical simulation verification based on situation data and infrared scenes

[0065] A semi-physical simulation test system is constructed with a simulation experiment integrated control system, a flight simulation workstation, a flight simulation turntable, a scenario simulation workstation and a dynamic target simulator as the main components. The entire simulation environment adopts a reflective memory communication network, with situation information as the test input and the dynamic scenes generated by the corresponding situation data as video stimuli to carry out ground verification tests of airborne equipment.

[0066] Reference Figure 2As shown, this embodiment is a semi-physical simulation test system for ground verification of airborne equipment based on situation construction, which uses a semi-physical simulation experiment system composed of a simulation experiment integrated control system, a flight simulation workstation, two flight simulation turntables, two scene simulation workstations and two dynamic target simulators to carry out detection, tracking, positioning and other functions and performance verification of airborne equipment. The whole simulation environment adopts a reflective memory communication network. The two sets of airborne equipment are installed at the rotation centers of the two flight simulation turntables through tooling, and the airborne equipment uses its own data link for communication and interaction. The simulation experiment integrated control system is the core of the entire semi-physical simulation, responsible for the control of all simulation nodes, the sending and receiving of all data, and the record management; the flight simulation workstation runs a real-time system to generate situation information according to step 1, including the position and attitude data of the carrier aircraft and friendly aircraft, as well as the position and attitude data of the target; the situation information is distributed to the control consoles of two flight simulation turntables and two scene simulation workstations. The three axes inside the flight simulation turntable simulate the attitude changes of the carrier aircraft or friendly aircraft, and the two axes outside the turntable simulate the relative position between the target and the carrier aircraft or friendly aircraft, and drive the dynamic target simulator installed on the two-axis target station to the direction of the target; the two scene simulation workstations simulate the position of the carrier aircraft and friendly aircraft viewpoints in the scene according to the received situation information, and set the observation direction of the viewpoint according to the angle of the two-axis target station, and perform real-time rendering according to steps 2 to 5 to generate the infrared scene that the optoelectronic detection equipment mounted on the carrier aircraft and friendly aircraft should observe, and transmit the scene to the corresponding dynamic target simulator through the video interface. The dynamic target simulator converts the infrared scene into an infrared radiation signal and emits it to stimulate the infrared sensor imaging of the airborne optoelectronic equipment.

[0067] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. A method for ground verification of airborne equipment based on situation construction, characterized in that The specific steps are as follows: Generate simulated situation information of carrier aircraft and friendly aircraft according to target motion trajectory; Combined with simulated situation information, the theoretical atmospheric transmission characteristics between the target and the airborne equipment are calculated; Based on the influence of theoretical atmospheric transmission characteristics on the target, the actual target intrinsic radiation parameters are corrected to obtain the target radiation brightness received by the airborne optoelectronic equipment; Calculation of infrared characteristics of sky background; Quantification and display of infrared radiation; Carry out semi-physical simulation verification based on situation data and infrared scenes.

2. The method for ground verification of airborne equipment based on situation construction according to claim 1, characterized in that: The method for acquiring simulated situation information of a carrier aircraft and a friendly aircraft plans the flight range of the carrier aircraft and the friendly aircraft according to the typical mission mode and motion trajectory of the target and the detection and tracking distance of the airborne equipment; uses dual-aircraft / multi-aircraft collaborative detection as a positioning means, and according to the angle measurement accuracy and tracking accuracy indicators of the airborne equipment, constructs a situation that meets the positioning accuracy requirements of the airborne equipment, and plans the flight trajectory of the carrier aircraft and the friendly aircraft; according to the motion trajectory of the carrier aircraft / friendly aircraft, uses a modeling toolbox to build a six-degree-of-freedom digital model of the aircraft, sets a simulation cycle, and calculates the position and attitude information of the carrier aircraft / friendly aircraft.

3. The method for ground verification of airborne equipment based on situation construction according to claim 2, characterized in that: The calculation method of the theoretical atmospheric transmission characteristics between the target and the airborne equipment is to obtain the distance and relative angle between the carrier aircraft / friendly aircraft and the target according to the simulated situation information, and select the corresponding atmospheric mode and time, and meteorological conditions, and use the distance and relative angle between the carrier aircraft / friendly aircraft and the target, the atmospheric mode and time, the meteorological conditions, and the carrier aircraft height, the observed slant range, and the observed zenith angle at each simulation moment as the input of the atmospheric radiation transmission software to solve and obtain the corresponding theoretical atmospheric transmittance τ under the mission mode and motion trajectory cal , Theoretical atmospheric radiation L cal and theoretical solar radiation.

4. The method for ground verification of airborne equipment based on situation construction according to claim 3, characterized in that: The calculation method of the target radiation brightness received by the airborne optoelectronic device is: Under the measured meteorological conditions, the radiation brightness of the black body at different temperatures was tested by infrared thermal imager, and the measured atmospheric path radiation L under the measured weather conditions was calculated. path and the measured atmospheric transmittance τ path ; The observation conditions under the measured meteorological conditions are input into the atmospheric radiation transmission software to calculate the theoretical atmospheric path radiation L under the meteorological conditions. Modtran and theoretical atmospheric transmittance τ Modtran , combined with the measured atmospheric radiation L path and the measured atmospheric transmittance τ path Calculate the atmospheric radiation correction factor C path and atmospheric transmittance correction factor C τ , for the theoretical atmospheric transmittance τ cal , Theoretical atmospheric radiation L cal make corrections; The measured intrinsic radiation parameters of the target are corrected to obtain the target radiation brightness received by the airborne optoelectronic equipment. The calculation formula is as follows: L T =C τ ·t cal ·L 本 +C path ·L cal Where, L T represents the target radiation brightness received by the airborne optoelectronic equipment after correction, C τ is the atmospheric transmittance correction coefficient, C path is the atmospheric radiation correction factor, L 本 is the intrinsic radiance of the target.

5. The method for ground verification of airborne equipment based on situation construction according to claim 4, characterized in that: The calculation formula of the measured atmospheric radiation is as follows: In the formula, DN1 and DN2 are the output values ​​of the infrared thermal imager at different black body temperatures; k is the radiance responsivity of the infrared thermal imager; L1 and L2 are the radiance of the black body at different temperatures; DN0 is the bias value caused by the thermal radiation of the infrared thermal imager itself and the background radiation factors; The calculation formula of the measured atmospheric transmittance is as follows:

6. The method for ground verification of airborne equipment based on situation construction according to claim 5, characterized in that: The atmospheric path radiation correction factor C path and atmospheric transmittance correction factor C τ The calculation formula is as follows:

7. The method for ground verification of airborne equipment based on situation construction according to claim 1, characterized in that: The infrared characteristic calculation method of the sky background is: Construct a hemispherical sky geometry model; The sky radiance under different atmospheric modes, aerosol types, meteorological conditions, zenith angles and sampling altitudes is calculated by atmospheric radiative transfer software; Assuming that the sky background infrared image is consistent in the horizontal direction, a sky image matrix is ​​generated according to the size of the simulation scene, and a uniform sky background image under cloudless conditions is generated according to the grayscale mapping relationship of the radiation brightness; the infrared image of the sky is used as a texture mapping on the hemispherical sky geometric model to form a sky infrared scene under a single condition; The sky radiation brightness is calculated under different atmospheric modes, aerosol types, meteorological conditions and sampling altitudes to generate a radiation characteristic database. The corresponding radiation value is queried in real time in the database according to the observation altitude and angle of the airborne equipment to obtain an infrared sky background with dynamic effects.

8. The method for ground verification of airborne equipment based on situation construction according to claim 7, characterized in that: The infrared radiation quantification and display method is to use an open source scene graphics engine to synthesize and render the infrared target and the sky background to generate an 8-bit grayscale image under the observation angle of the airborne optoelectronic device.

9. The method for ground verification of airborne equipment based on situation construction according to claim 1, characterized in that: The method for conducting semi-physical simulation verification based on situation data and infrared scenes is to construct a semi-physical simulation test system with a simulation experiment integrated control system, a flight simulation workstation, a flight simulation turntable, a scene simulation workstation and a dynamic target simulator as the main body. The whole simulation environment adopts a reflective memory communication network, takes situation information as test input, and uses dynamic scenes generated by corresponding situation data as video excitation to carry out ground verification tests of airborne equipment.

10. A semi-physical simulation test system for ground verification of airborne equipment based on situation construction, used for implementing the ground verification method of airborne equipment based on situation construction according to any one of claims 1 to 9; characterized in that: It includes simulation experiment integrated control system, flight simulation workstation, flight simulation turntable, scenario simulation workstation and dynamic target simulator. The whole simulation environment adopts reflective memory communication network. The simulation experiment integrated control system is used for the control of all simulation nodes, the sending and receiving of all data, and the record management; The flight simulation workstation operates according to the simulated situation information, distributes the situation information to the control consoles of the two flight simulation turntables and the two scenario simulation workstations, simulates the attitude changes of the carrier aircraft or the friendly aircraft through three axes in the flight simulation turntable, simulates the relative position between the target and the carrier aircraft or the friendly aircraft through two axes outside the turntable, and drives the dynamic target simulator installed on the two-axis target table to the direction where the target is located; Two sets of airborne optoelectronic equipment are installed at the rotation center of two flight simulation turntables through tooling, and the airborne optoelectronic equipment uses its own data link for communication and interaction; The two scene simulation workstations simulate the positions of the carrier aircraft and the friendly aircraft's viewpoints in the scene respectively according to the received situation information, and set the observation direction of the viewpoint according to the angle of the two-axis target station. Real-time rendering is performed according to the airborne equipment ground verification method based on situation construction, and the infrared visual scene that should be observed by the optoelectronic detection equipment mounted on the carrier aircraft and the friendly aircraft is generated. The visual scene is transmitted to the corresponding dynamic target simulator through the video interface. The dynamic target simulator converts the infrared visual scene into an infrared radiation signal and emits it to stimulate the infrared sensor imaging of the airborne optoelectronic equipment.

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