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Full equation heat flux density measurement and control system and measurement and control method for aerospace aircraft test experiment
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A technology for testing experiments and heat flux, which is applied in the direction of testing/monitoring control systems, aircraft component testing, general control systems, etc., can solve the problems of lack of response state, affecting the control accuracy of heat flux, etc., and achieve excellent control accuracy and verification effect Effect
Active Publication Date: 2022-08-02
CHINA AIRPLANT STRENGTH RES INST
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[0004] Theoretical analysis lacks the response state of the tested aircraft under real conditions, so there will be deviations from the heat flow conditions of the aircraft under real flight conditions, which affects the heat flux control accuracy in the actual ground heat intensity simulation test
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Embodiment 1
[0057] This embodiment is a full-equation heat flux density measurement and control system for the aerospace aircraft test experiment, such as figure 1 shown, including:
[0058] An extreme thermal field generator for generating extreme thermal fields with fast time-varying thermal loads,
[0059] A thermal parameter measurement device used to measure the real heat flux density in the extreme thermal field and the real temperature response of the test aircraft. Temperature Sensor,
[0060] The test control device is used to complete the thermal strength test control calculation and system hardware control of the test aircraft. The test control device is electrically connected with the extreme thermal field generation device and the thermal parameter measurement device, and the heat flow meter and temperature sensor are electrically connected with the test control device. The test control device completes the test control calculation of the thermal strength of the test aircra...
Embodiment 2
[0065] This embodiment is a full-equation heat flux density measurement and control method for the aerospace aircraft test experiment based on the full-equation heat flux density measurement and control system of the aerospace aircraft test experiment of Example 1, such as figure 2 shown, including the following steps:
[0066] S1. Construct the experimental control equation
[0067] According to the principle of aerodynamic heating, the experimental control equation of the ground thermal strength simulation test is established. The experimental control equation is:
[0068]
[0069] In the formula, is the enabling factor, is the radiation coefficient, For the command value of heat flow regardless of the response state of the test aircraft, is the temperature enthalpy, , To test the aircraft temperature, For the test aircraft heat loss, For the recovery enthalpy of the test aircraft, is the control target value of heat flux density;
[0070] S2. Establis...
Embodiment 3
[0091] The difference between this embodiment and Embodiment 2 is:
[0092] In step S3, the control period of the test control device is 0.8ms,
[0093] In step S4-1, .
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Abstract
The invention provides a full-equation heat flux density measurement and control system and a measurement and control method for an aerospace aircraft test experiment, and relates to the technical field of aircraft testing. The system includes an extreme thermal field generation device, a thermal parameter measurement device, an experimental control device, and an electric power adjustment device, and the method includes the following steps: S1, constructing an experimental control equation; S2, establishing the enabling coefficient and radiation coefficient of the experimental control equation; S3, based on Test control equation measurement and control test aircraft thermal strength test; S4, close-loop control of heat flux measurement and control system based on heat flux density control target value; S5, test aircraft thermal strength test safety control. The invention solves the problem of deviation between the calculation of heat flow conditions in the heat strength test of the existing aerospace aircraft and the heat flow conditions in the real flight state of the aircraft, and has the advantages of accurate calculation and real simulation.
Description
technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a full-equation heat flux density measurement and control system and a measurement and control method for aerospace aircraft testing experiments. Background technique [0002] In the aircraft thermal strength test, a ground thermal strength simulation test is required. During the test, it is often necessary to divide multiple temperature zones to simulate the thermal field distribution of different structures of the aircraft, and there is usually a coupling interference phenomenon in multiple temperature zones. At the same time, due to the high-speed maneuverability of the aircraft itself, its ground simulation test system needs to have the characteristics of rapid time-varying. [0003] As an important physical parameter that needs to be simulated in the thermal strength test of the test aircraft, the heat flux density directly determines the accuracy and effect of the ...
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