Spacecraft thermal vacuum test method

Abstract

The application discloses a spacecraft thermal vacuum test method, one, completes infrared heating device preliminary heating partition design, builds the whole star thermal analysis model under the test state; two, establishes infrared heating device-cabin plate closed loop temperature control; the whole star thermal analysis model under the test state is used, and the temperature feedback point temperature control target value under the low-temperature working condition of thermal vacuum is determined by iterative analysis with the requirement of the on-board equipment participating in the whole star thermal vacuum test as the target; three, the whole star thermal analysis model under the test state, the temperature control target value of high and low temperature working conditions of thermal vacuum, predicts the thermal vacuum test process; the implementation requirement and control requirement of the temperature control point are proposed; four, temperature sensors are pasted on the corresponding positions on the surface of the outer cabin plate, the infrared heating device is arranged, and the infrared heating device-whole star temperature closed loop temperature control system is established; the application can carry out partition design on the infrared heating device according to the equipment layout, weaken the interference influence between the partitions, and accurately control the temperature of the whole star equipment.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of spacecraft thermal test, and particularly relates to a spacecraft thermal vacuum test method. BACKGROUND

[0002] The spacecraft thermal control system task is to ensure that all instruments and equipment on the satellite meet the temperature index requirements under the conditions of the determined orbit, attitude and working mode. In order to verify the overall function of the spacecraft in the space environment and ensure the reliable operation of the spacecraft in orbit, all spacecrafts must be subjected to vacuum thermal test during the ground development stage, and the most important, most complex and longest test is the whole satellite vacuum thermal test in the space environment simulation equipment. The thermal vacuum test is to examine the ability of the instruments and equipment on the satellite to withstand high and low temperatures and temperature alternation under vacuum conditions, and to expose the defects of the single machine, raw materials, components and process on the satellite in advance.

[0003] The whole satellite thermal vacuum test needs to pull the high and low temperature of the whole satellite equipment, and the temperature of the equipment on the satellite is controlled to be 5-10 DEG C higher (or lower) than the high and low temperature value obtained during the thermal balance test, and not more than the highest or lowest test temperature of the equipment acceptance level. The method for adjusting the temperature of the whole satellite during the test is to adjust the external heat flow of each aspect to the whole satellite through the infrared heating device-heat flow meter system, and then adjust the temperature of the whole satellite.

[0004] The existing thermal vacuum test method has the following disadvantages:

[0005] 1) There is mutual interference between each partition of the infrared heating device, which easily leads to that when most of the equipment does not reach the thermal vacuum temperature, the temperature of individual equipment has exceeded the acceptance temperature.

[0006] 2) The target temperature of the heat flow meter can only realize the control of the external heat flow of the whole satellite, indirectly controls the temperature of the equipment in the cabin, cannot realize the closed loop control of the infrared heating device and the temperature of the whole satellite, and is easy to appear the risk of out-of-control of the temperature of the whole satellite caused by over-regulation of the external heat flow.

[0007] 3) Open loop control, low test automation degree, low test efficiency and long test cycle. SUMMARY

[0008] Therefore, the application provides a spacecraft thermal vacuum test method, which can be designed according to the equipment layout, the corresponding relationship between the infrared heating device and the equipment is clear, the interference between the partitions is weakened, and the temperature of the whole satellite equipment can be accurately controlled.

[0009] The technical scheme of the application is as follows:

[0010] A spacecraft thermal vacuum test method comprises the following steps:

[0011] Step one, according to the corresponding relationship between the heat dissipation surface of each outer cabin plate of the satellite and the equipment in the cabin, arranging infrared heating devices outside each heat dissipation surface, completing the preliminary heating partition design of the infrared heating device, and building the whole satellite thermal analysis model under the test state;

[0012] Step two, according to the preliminary partition of the infrared heating device, selecting the outer cabin plate corresponding to the partition as the temperature feedback point, establishing the infrared heating device-cabin plate closed-loop temperature control, and using the whole satellite thermal analysis model under the test state, taking the requirement of the on-orbit equipment participating in the whole satellite thermal vacuum test as the target, performing iterative analysis to determine the temperature feedback point control target value under the thermal vacuum low-temperature working condition;

[0013] Step three, using the whole satellite thermal analysis model under the test state and the high-low temperature working condition temperature control target value, predicting the thermal vacuum test process through thermal analysis; according to the number, position and target control temperature of the temperature control points given in step two, the implementation requirements and control requirements of the temperature control points are proposed;

[0014] Step four, according to step three, pasting temperature sensors on the corresponding positions on the outer cabin plate surface and arranging infrared heating devices to establish an infrared heating device-whole satellite temperature closed-loop temperature control system, and in the thermal vacuum test, the temperature control target value of each outer cabin plate is applied according to the working condition.

[0015] Further, according to the layout of the whole satellite equipment and the distribution of the heat dissipation surface, the corresponding relationship between the heat dissipation surface of each outer cabin plate of the satellite and the equipment in the cabin is obtained.

[0016] Further, in step one, the infrared heating devices are arranged at a distance of 150-300mm from each outer cabin plate.

[0017] Further, in step two, the requirement of the on-orbit equipment participating in the whole satellite thermal vacuum test is that: in the thermal vacuum high-temperature working condition, the temperature of more than 80% of the passive temperature-controlled electronic equipment inside the satellite is 5-10℃ higher than the maximum temperature of the heat balance test, and the temperature of all single-machine equipment inside the satellite does not exceed the corresponding upper limit of the acceptance temperature; in the thermal vacuum low-temperature working condition, the temperature of more than 80% of the passive temperature-controlled electronic equipment inside the satellite is 5-10℃ lower than the minimum temperature of the heat balance test, and the temperature of all single-machine equipment inside the satellite does not exceed the corresponding lower limit of the acceptance temperature.

[0018] Further, in step three, in order to speed up the thermal vacuum test process, increase the design power of the infrared heating device, and shorten the time from the thermal vacuum low-temperature to the thermal vacuum high-temperature.

[0019] Beneficial effects:

[0020] 1. The method of the present application can realize precise control of the temperature deviation of the whole satellite equipment.

[0021] 2, The present application utilizes the infrared heating device-cabin plate closed loop temperature control system, improves the degree of automation, reduces the risk of thermal vacuum test temperature out of control, improves the test efficiency, and saves the test cost.

[0022] 3, The method of the present application can accurately predict the thermal vacuum test process and result through the whole satellite thermal analysis model under the test state. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 The present application is a method flowchart. DETAILED DESCRIPTION

[0024] The present application will be described in detail below with reference to the accompanying drawings and examples.

[0025] As Figure 1 The working flowchart of the present application is shown, including the following steps:

[0026] Step 1: According to the satellite configuration layout, the corresponding relationship between the satellite each outer cabin plate heat dissipation surface and the equipment in the cabin is established, on this basis, the infrared heating device is arranged at a distance of 150-300mm from each outer cabin plate, according to the equipment layout, heat dissipation surface distribution, the preliminary zoning design of each infrared heating device is completed, and the zoning of the infrared heating device and the corresponding relationship of the equipment are established;

[0027] Step 2: According to the satellite configuration layout, the thermal characteristics of the on-board equipment, the satellite thermal design state, the thermal vacuum working condition satellite working mode, the infrared heating device layout, the vacuum tank, and the test support, the whole satellite thermal analysis model under the test state is established;

[0028] Step 3: According to the preliminary zoning of the infrared heating device, the outer cabin plate corresponding to the zoning is selected as the temperature feedback point, and the infrared heating device-cabin plate closed loop temperature control is established.

[0029] Step 4: Using the whole satellite thermal analysis model under the test state, taking the requirement of on-board equipment participating in the whole satellite thermal vacuum test as the target, iterative analysis is carried out, specifically as follows: the thermal analysis target of the thermal vacuum high temperature working condition is that the temperature of more than 80% of the passive temperature controlled electronic equipment inside the satellite is 5-10℃ higher than the maximum temperature of the heat balance test, and the temperature of all single machine equipment inside the satellite does not exceed the corresponding upper limit of the acceptance temperature. According to the thermal vacuum high temperature working condition analysis target, iterative analysis is carried out to determine the temperature feedback point representing the average temperature in the cabin, the infrared heating device power, and the temperature feedback point control target value under the thermal vacuum high temperature working condition; the thermal analysis target of the thermal vacuum low temperature working condition is that the temperature of more than 80% of the passive temperature controlled electronic equipment inside the satellite is 5-10℃ lower than the minimum temperature of the heat balance test, and the temperature of all single machine equipment inside the satellite does not exceed the corresponding lower limit of the acceptance temperature. According to the thermal vacuum low temperature working condition analysis target, iterative analysis is carried out to determine the temperature feedback point control target value under the thermal vacuum low temperature working condition.

[0030] Step 5: using the whole satellite thermal analysis model in the test state, the thermal vacuum high and low temperature working condition temperature control target value, through thermal analysis, the thermal vacuum test process is predicted, in order to speed up the test process, the design power of the infrared heating device can be increased, and the time from the thermal vacuum low temperature to the thermal vacuum high temperature is shortened.

[0031] Step 6: according to steps 3 and 4, the number, position and target control temperature of the thermal vacuum test temperature control point are given, and the temperature control point implementation requirements and control requirements are proposed;

[0032] Step 7: according to step 6, the thermal vacuum test temperature control point and the infrared heating device thermal control implementation requirements and control requirements are proposed, the temperature sensor is pasted on the corresponding position of the outer cabin plate surface, the infrared heating device is arranged, the infrared heating device-whole satellite temperature closed loop temperature control system is established, and in the thermal vacuum test, the target value of each outer cabin plate temperature control is applied according to the working condition.

[0033] In summary, the above is only a preferred embodiment of the present application, and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A spacecraft hot vacuum test method, characterized by, The method comprises the following steps: Step one, according to the corresponding relationship between the heat dissipation surface of each outer cabin plate and the equipment inside the cabin, arranging infrared heating devices outside each heat dissipation surface, completing the preliminary heating partition design of the infrared heating device, and building the whole satellite thermal analysis model under the test state; Step two, according to the preliminary partition of the infrared heating device, selecting the outer cabin plate corresponding to the partition as the temperature feedback point, and establishing the infrared heating device-cabin plate closed-loop temperature control; Using the whole satellite thermal analysis model under the test state, taking the requirement of the equipment on the satellite participating in the whole satellite thermal vacuum test as the target, performing iterative analysis, and determining the temperature feedback point control target value under the thermal vacuum low-temperature working condition; Step three, using the whole satellite thermal analysis model under the test state and the high-low temperature working condition temperature control target value, predicting the thermal vacuum test process through thermal analysis; according to step two, the number, position and target control temperature of the thermal vacuum test temperature control points are given, and the implementation requirement and control requirement of the temperature control points are proposed; Step four, according to step three, pasting temperature sensors on the corresponding positions of the outer cabin plate surface, arranging infrared heating devices, establishing the infrared heating device-whole satellite temperature closed-loop temperature control system, and applying the temperature control target value of each outer cabin plate according to the working condition during the thermal vacuum test.

2. The spacecraft hot vacuum test method of claim 1, wherein, According to the whole satellite equipment layout and the heat dissipation surface distribution, the corresponding relationship between the heat dissipation surface of each outer cabin plate and the equipment inside the cabin is obtained.

3. The spacecraft hot vacuum test method of claim 1, wherein, In step one, the infrared heating devices are arranged at a distance of 150-300 mm from each outer cabin plate.

4. The spacecraft hot vacuum test method of claim 1 or 3, wherein, In step two, the requirement of the equipment on the satellite participating in the whole satellite thermal vacuum test is as follows: in the thermal vacuum high-temperature working condition, the temperature of more than 80% of the passive temperature-controlled electronic equipment inside the satellite is 5-10℃ higher than the maximum temperature of the thermal balance test, and the temperature of all single-machine equipment inside the satellite does not exceed the corresponding upper limit of the acceptance temperature; In the thermal vacuum low-temperature working condition, the temperature of more than 80% of the passive temperature-controlled electronic equipment inside the satellite is 5-10℃ lower than the minimum temperature of the thermal balance test, and the temperature of all single-machine equipment inside the satellite does not exceed the corresponding lower limit of the acceptance temperature.

5. The spacecraft hot vacuum test method of claim 4, wherein, In step three, in order to speed up the thermal vacuum test process, increase the design power of the infrared heating device, and shorten the time from the thermal vacuum low-temperature to the thermal vacuum high-temperature,

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