High-precision thrust frame temperature control device based on active heating method

Abstract

The invention relates to the technical field of thrust measurement of a thruster, in particular to a thrust frame temperature high-precision control device based on an active heating method, which comprises a heat shielding case arranged in a vacuum cabin system, and an ion source used for simulating a plume heat load of the thruster is arranged at one end in the heat shielding case. A thrust rack used for testing thrust is arranged at the other end in the heat shielding cover, and the ion source and the thrust rack are oppositely arranged; a heating piece array used for heating is installed on the inner wall of the heat shielding cover, temperature sensor arrays used for monitoring temperature are installed on the heating piece array and the thrust rack respectively, the temperature sensor arrays are electrically connected with a temperature control unit, and the temperature control unit is electrically connected with the heating piece array. According to the invention, the heating sheet array is controlled by the temperature control unit for heating, and the temperature distribution change range of the surface of the thrust rack can be effectively controlled within 0.1 DEG C, so that the accuracy and reliability of thrust measurement are guaranteed.

Description

Technical Field

[0001] This invention relates to the field of thrust measurement technology for thrusters, and in particular to a high-precision temperature control device for a thruster frame based on an active heating method. Background Technology

[0002] In a thrust measurement system for a thruster, the thrust frame is a key component for measuring thrust. During thruster operation, a high-temperature plume is generated, which heats the thrust frame and its thermal protection devices, resulting in uneven temperature distribution on the thrust frame surface. Temperature changes can cause thermal expansion or deformation of the thrust frame, thus affecting the accuracy of thrust measurement. Therefore, temperature control of the thrust frame is necessary to ensure the accuracy of thrust measurement results.

[0003] Currently, existing temperature control methods mainly employ passive thermal protection (such as insulation materials) or simple active temperature control systems (such as active water cooling). Passive thermal protection reduces heat transfer through insulation layers but cannot actively compensate for dynamic heat loads, resulting in insufficient temperature control accuracy. Simple active water cooling control systems introduce active low-frequency mechanical vibration noise, which can severely interfere with the thrust frame measurement accuracy. Furthermore, existing methods lack multi-point temperature monitoring and feedback mechanisms, making it difficult to adjust heating power in real time, leading to large temperature fluctuations. Typically, it is impossible to control the temperature distribution variation on the thrust frame surface within 0.1℃, thus limiting the accuracy and reliability of thrust measurement.

[0004] Therefore, there is an urgent need for a high-precision thrust frame temperature control device based on active heating method, which can control the temperature distribution variation range of the thrust frame surface within 0.1℃ through multi-point temperature monitoring and feedback control, thereby ensuring the accuracy and reliability of thrust measurement. Summary of the Invention

[0005] The purpose of this invention is to provide a high-precision temperature control device for a thrust frame based on an active heating method, so as to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the present invention provides the following solution: a high-precision thrust frame temperature control device based on an active heating method, comprising a heat shield installed within a vacuum chamber system, an ion source for simulating the thermal load of the thruster plume being installed at one end of the heat shield, and a thrust test stand for testing thrust being installed at the other end of the heat shield, the ion source being positioned opposite to the thrust test stand; an array of heating elements for heating is installed on the inner wall of the heat shield, and temperature sensor arrays for monitoring temperature are respectively installed on the heating element array and the thrust test stand, the temperature sensor array being electrically connected to a temperature control unit, and the temperature control unit being electrically connected to the heating element array.

[0007] Preferably, the heating element array includes multiple heating elements with independently controlled temperatures.

[0008] Preferably, a plurality of heating elements are evenly laid on the inner wall of the heat shield to cover the inner wall of the heat shield.

[0009] Preferably, the temperature sensor array includes multiple waterproof thermocouples.

[0010] Preferably, the plurality of waterproof thermocouples on the thrust platform are evenly arranged on the outer wall of the thrust platform.

[0011] Preferably, the waterproof thermocouples on the heating element array are evenly arranged on the end of each heating element away from the heat shield.

[0012] Preferably, the temperature control unit includes a data acquisition module, which is electrically connected to a PID controller.

[0013] Preferably, the PID controller is electrically connected to the heating element.

[0014] Preferably, the data acquisition module is electrically connected to the waterproof thermocouple.

[0015] Preferably, the data acquisition module and the PID controller are located outside the heat shield.

[0016] The present invention discloses the following technical effects: This invention achieves multi-point temperature detection through a heating element array and a temperature sensor array installed on the thrust test platform. At the same time, by controlling the heating element array to heat through the temperature control unit, the temperature distribution variation range on the surface of the thrust test platform can be effectively controlled within 0.1℃, thereby ensuring the accuracy and reliability of thrust measurement. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the internal structure of the heat shield of the present invention; Figure 2 This is a schematic diagram of the heating element array structure of the present invention; Among them, 1. thermal shield; 2. ion source; 3. thrust platform; 4. temperature sensor array; 5. heating element array. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] Reference Figures 1 to 2 The present invention provides a high-precision thruster temperature control device based on an active heating method, including a heat shield 1 installed in a vacuum chamber system, an ion source 2 for simulating the heat load of the thruster plume installed at one end of the heat shield 1, and a thrust test stand 3 for testing thrust installed at the other end of the heat shield 1, with the ion source 2 and the thrust test stand 3 arranged opposite to each other. A heating element array 5 for heating is installed on the inner wall of the heat shield 1. A temperature sensor array 4 for monitoring temperature is installed on the heating element array 5 and the thrust platform 3 respectively. The temperature sensor array 4 is electrically connected to a temperature control unit, and the temperature control unit is electrically connected to the heating element array 5.

[0022] This invention achieves multi-point temperature detection by using a heating element array 5 and a temperature sensor array 4 installed on the thrust test platform 3 for monitoring temperature. At the same time, by controlling the heating element array 5 to heat through the temperature control unit, the temperature distribution variation range on the surface of the thrust test platform 3 can be effectively controlled within 0.1℃, thereby ensuring the accuracy and reliability of thrust measurement.

[0023] Further optimization of the design: heating element array 5 includes multiple heating elements with independently controlled temperatures.

[0024] The design was further optimized by evenly laying multiple heating elements on the inner wall of the heat shield 1 to cover the inner wall of the heat shield 1.

[0025] By covering the inner wall of the heat shield 1 with multiple heating elements, each heating element with independently controlled temperature can heat different areas, effectively controlling the temperature distribution variation range inside the heat shield 1 to within 0.1℃.

[0026] Further optimization of the design includes multiple waterproof thermocouples in the temperature sensor array 4.

[0027] The waterproof thermocouples are Pt100 waterproof thermocouples (model MF6563), with a measurement range of -50 to 200℃ and an accuracy of 0.1℃. They are placed in key positions on the thrust frame and on the heating element.

[0028] To further optimize the design, multiple waterproof thermocouples on the thrust test platform 3 are evenly distributed on the outer wall of the thrust test platform 3. This allows the multiple waterproof thermocouples on the outer wall of the thrust test platform 3 to stably monitor the temperature changes on the surface of the thrust test platform 3.

[0029] To further optimize the design, waterproof thermocouples on the heating element array 5 are evenly distributed on the end of each heating element away from the heat shield 1. This allows the waterproof thermocouples on the end of each heating element away from the heat shield 1 to effectively monitor the temperature.

[0030] The solution has been further optimized. The temperature control unit includes a data acquisition module, which is electrically connected to a PID controller.

[0031] The solution was further optimized by electrically connecting the PID controller to the heating element.

[0032] The solution was further optimized by electrically connecting the data acquisition module to the waterproof thermocouple.

[0033] To further optimize the design, the data acquisition module and PID controller are placed outside the heat shield 1.

[0034] The signal from the waterproof thermocouple is input to the PID controller via the data acquisition module, and the PID controller outputs a signal to adjust the power of the heating element.

[0035] The heat shield 1 is heated by the ion source 2 to simulate the heating effect of a real ion thruster and plume. Temperature compensation is achieved using heating elements, and waterproof thermocouples arranged at different positions on the inner surface of the heat shield 1 measure the temperature distribution at different locations within the heat shield 1. The heating elements, in conjunction with the heating elements, control the uniformity of the temperature distribution on the inner surface of the heat shield 1 to ensure that the temperature change on the surface of the thrust test stand 3 in the actual measurement system is within 0.1℃.

[0036] The waterproof thermocouple uses a Pt100 adhesive waterproof temperature measuring thermocouple patch, model MF6563, with a measurement range of -50 to 200℃ and a measurement accuracy of 0.1℃, to ensure that the temperature change on the surface of the thrust test bench 3 is within the specified range.

[0037] During thrust measurement, the plume heats both the heat shield 1 and the thrust test stand 3, leading to uneven heating on their surfaces and affecting the accuracy of thrust measurement. Therefore, to ensure uniform surface temperature of the thrust test stand 3, multiple waterproof thermocouples are evenly distributed on the inner surface of the heat shield 1 for temperature measurement, and heating elements are placed on the plume and the surface of the heat shield 1 for further heating. The temperature control effect is assessed by observing the temperature changes of the waterproof thermocouples.

[0038] This invention uses closed-loop feedback control to keep the temperature distribution variation range on the surface of the thrust test stand 3 within 0.1℃, which is significantly better than the existing >1℃ method. At the same time, this invention also adopts a combination of array heating and temperature measurement to overcome the limitations of point control and achieve temperature uniformity on the entire surface of the thrust test stand 3. The improved temperature stability directly reduces the impact of thermal deformation on thrust measurement and effectively improves the reliability of measurement data.

[0039] The specific testing steps are as follows: 1) Preparation before the experiment 1. Test status check: Check whether the laboratory environment meets the corresponding requirements according to the test requirements.

[0040] 2. Test condition check: Prepare the test equipment according to the test condition requirements and check whether the test equipment functions normally.

[0041] 2) Installation of heat source and temperature sensor Attach waterproof thermocouples to their respective positions inside the thermal shield 1, place the test system in the vacuum chamber system, turn on the simulated ion source 2, and wait for the system to reach a stable discharge and thermal equilibrium state. Turn on the temperature control unit and adjust the heating power of the heating element through the numerical feedback of the waterproof thermocouples. Then, record the data every 5 minutes for a total of 10 sets. Compare the 10 sets of temperatures, take the maximum and minimum temperatures among all waterproof thermocouples, subtract them, and finally obtain the maximum value of the temperature difference in the all-round thermal environment.

[0042] Since the heat transfer path between the heat shield 1 and the thrust platform 3 is only thermal radiation in the vacuum working environment of a real ion thruster, if the error between the maximum and minimum steady-state temperature of the inner surface of the heat shield 1 is within 0.1℃, it can be considered to meet the technical requirements.

[0043] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0044] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A high-precision temperature control device for a thrust frame based on an active heating method, characterized in that: It includes a heat shield (1) installed in the vacuum chamber system. One end of the heat shield (1) is provided with an ion source (2) for simulating the heat load of the thruster plume, and the other end of the heat shield (1) is provided with a thrust test stand (3) for testing thrust. The ion source (2) and the thrust test stand (3) are arranged opposite to each other. The inner wall of the heat shield (1) is equipped with a heating element array (5) for heating. The heating element array (5) and the thrust platform (3) are respectively equipped with a temperature sensor array (4) for monitoring temperature. The temperature sensor array (4) is electrically connected to a temperature control unit, and the temperature control unit is electrically connected to the heating element array (5).

2. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 1, characterized in that: The heating element array (5) includes multiple heating elements with independently controlled temperatures.

3. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 2, characterized in that: Multiple heating elements are evenly laid on the inner wall of the heat shield (1) to cover the inner wall of the heat shield (1).

4. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 2, characterized in that: The temperature sensor array (4) includes multiple waterproof thermocouples.

5. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 4, characterized in that: The plurality of waterproof thermocouples on the thrust platform (3) are evenly arranged on the outer wall of the thrust platform (3).

6. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 4, characterized in that: The waterproof thermocouples on the heating element array (5) are evenly arranged on one end of each heating element away from the heat shield (1).

7. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 4, characterized in that: The temperature control unit includes a data acquisition module, which is electrically connected to a PID controller.

8. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 7, characterized in that: The PID controller is electrically connected to the heating element.

9. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 7, characterized in that: The data acquisition module is electrically connected to the waterproof thermocouple.

10. The high-precision temperature control device for the thrust frame based on the active heating method according to claim 7, characterized in that: The data acquisition module and the PID controller are located outside the heat shield (1).

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