An integrated temperature measurement and heating heater suitable for spacecraft and its usage method

Abstract

This invention relates to an integrated temperature measurement and heating heater and its usage method suitable for spacecraft. The heater includes: multiple constantan heating wires and multiple high-resistance patch thermistors, with the constantan heating wires connected in parallel; each high-resistance patch thermistor is connected in parallel to the corresponding constantan heating wire via connecting wires; each constantan heating wire and the corresponding high-resistance patch thermistor are disposed between two insulating films, and the connecting wires extend from the two insulating films and are connected to an onboard computer via an electrical connector. This invention glues the high-resistance patch thermistors, constantan heating wires, and two insulating films together, making the gluing and fixing convenient and achieving double-sided insulation; in the implementation phase, temperature measurement and heating can be completed in a single operation, saving more time compared to traditional processes.

Description

Technical Field

[0001] This invention relates to the field of heater technology for spacecraft, and more particularly to an integrated temperature measurement and heating heater suitable for spacecraft and its usage method. Background Technology

[0002] In all spacecraft systems, the thermal control system ensures that propellants, components, and other parts are within the required operating temperature range to ensure their normal operation.

[0003] Heaters are an essential component for temperature control in spacecraft on orbit. They are generally thin-film devices containing constantan resistance wires. To achieve temperature control for specific targets, temperature measurement sensors are needed in conjunction with heaters to complete closed-loop temperature control.

[0004] In traditional designs, heaters and temperature measurement sensors are each connected to the onboard computer via two cables. Since spacecraft use a large number of heaters and temperature measurement sensors, which are distributed in various locations on the satellite, the heater and temperature measurement sensor cables consume a considerable amount of weight resources.

[0005] To reduce the consumption of the aforementioned cable resources, this invention proposes an integrated temperature measurement and heating heater suitable for spacecraft. By connecting two cables, it achieves both heating and temperature measurement functions, reducing cable usage by 50%. Summary of the Invention

[0006] To address the technical problems existing in the prior art, the present invention aims to provide an integrated temperature measurement and heating heater and its usage method suitable for spacecraft. It uses a high-resistance thermistor as the temperature measuring element, which is integrated in parallel with a constantan wire thin film heater. By utilizing a time-sharing operation of heating and temperature measurement, the integrated temperature measurement and heating is achieved, reducing the use of cables by 50%.

[0007] To achieve the above-mentioned objectives, the present invention provides an integrated temperature measurement and heating heater suitable for spacecraft, comprising:

[0008] Multiple constantan heating wires are connected in parallel.

[0009] Multiple high-resistance surface-mount thermistors, each with its two ends connected in parallel to the two ends of the corresponding constantan heating wire via connecting wires;

[0010] Each constantan heating wire and its corresponding high-resistance patch thermistor are positioned between two insulating films, and the connecting wire extends out of the two insulating films and is connected to the onboard computer via an electrical connector.

[0011] Furthermore, the onboard computer includes a heating circuit, which is connected in series with a programmable switch. The programmable switch and the heating circuit are connected to an electrical connector via a wiring connection.

[0012] Furthermore, the onboard computer also includes a measured circuit, which is connected in parallel with the heating circuit via a line, and the heating circuit is connected in series with the programmable switch.

[0013] Furthermore, the onboard computer also includes a series-connected voltage divider resistor and a temperature measuring circuit, which are connected in parallel with the circuit being measured. During the heating phase, the programmable switch is closed downwards, and the heating circuit supplies power to the constantan heating wire through an electrical connector, causing the constantan heating wire to heat. During the temperature measuring phase, the programmable switch is closed upwards, the heating circuit stops working, and the power supply circuit for the temperature measuring circuit is connected. After passing through the voltage divider resistor, a temperature-related voltage is generated across the high-resistance surface-mount thermistor. After the circuit being measured measures the voltage, the temperature data is calculated. The heating phase and the temperature measuring phase alternate, and the above process can achieve heating and temperature measurement through a single cable.

[0014] Furthermore, the package specifications of the high-resistance surface mount thermistor do not exceed the 0402 specification, and each high-resistance surface mount thermistor and its corresponding constantan heating wire are encapsulated within two insulating films 3.

[0015] Furthermore, the high-resistance surface mount thermistor has a resistance of not less than 30KΩ at room temperature and not less than 5KΩ at 70℃, so that the power consumption of the high-resistance surface mount thermistor does not exceed 0.2W within the operating range of -40℃ to 70℃.

[0016] Furthermore, the insulating film is made of polyimide material.

[0017] This invention provides a method for using an integrated temperature measurement and heating heater suitable for spacecraft, comprising the following steps:

[0018] Step 1: Set the temperature control target to T0 using the onboard computer;

[0019] Step 2: When the onboard computer detects that the temperature of the high-resistance patch thermistor is less than T0, the programmable switch closes downwards for a duration of t.

[0020] Step 3: When the time is up, the programmable switch closes upward to stop heating, and the onboard computer measures the temperature. If the temperature of the high-resistance surface-mount thermistor is greater than T0, heating will stop again. If the temperature of the high-resistance surface-mount thermistor is less than T0, the programmable switch closes downward again to resume heating.

[0021] Step 4: Repeat the above process to keep the temperature of the controlled object at T0.

[0022] Compared with the prior art, the present invention has the following advantages:

[0023] 1. This invention proposes an integrated temperature measurement and heating heater suitable for spacecraft. It integrates a high-resistance patch thermistor, constantan heating wire, and two insulating films, which are easy to fix and achieve double-sided insulation. In the implementation stage, temperature measurement and heating can be completed in one operation, which saves more time compared with traditional processes.

[0024] 2. This invention proposes a method for using an integrated temperature measurement and heating heater suitable for spacecraft. By combining a constantan heating wire and a high-resistance patch thermistor, and employing appropriate heating and temperature measurement methods, a single wire is used to achieve both temperature measurement and heating. Compared with traditional heating and temperature measurement methods, this method can save a single wire, effectively reducing the consumption of spacecraft weight resources. Attached Figure Description

[0025] 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 described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0026] Appendix Figure 1 This is a schematic diagram of an integrated temperature measurement and heating heater suitable for spacecraft.

[0027] Appendix Figure 2 This is a schematic diagram of the circuit principle of an integrated temperature measurement and heating heater suitable for spacecraft.

[0028] In the picture:

[0029] 1. Constantan heating wire; 2. High-resistance surface mount thermistor; 3. Connecting wire; 4. Insulating film; 5. Electrical connector; 6. Onboard computer;

[0030] 61. Heating circuit; 62. Programmable switch; 63. Measured circuit; 64. Voltage divider resistor; 65. Temperature measuring circuit. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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.

[0032] This invention provides an integrated temperature measurement and heating heater suitable for spacecraft, comprising:

[0033] Multiple constantan heating wires 1 are connected in parallel;

[0034] Multiple high-resistance chip thermistors 2, each high-resistance chip thermistor 2 is connected in parallel with the corresponding constantan heating wire 1 through connecting wires 3;

[0035] Each constantan heating wire 1 and its corresponding high-resistance patch thermistor 2 are disposed between two insulating films 4, and the connecting wire 3 extends out of the two insulating films 4 and is connected to the on-board computer 6 through the electrical connector 5.

[0036] This application utilizes a combination of constantan heating wire 1 and high-resistance patch thermistor 2, employing appropriate heating and temperature measurement methods, and employing only two wires to achieve both temperature measurement and heating. Compared to traditional heating and temperature measurement methods, this approach saves two wires, effectively reducing the consumption of spacecraft weight resources.

[0037] This application integrates a high-resistance surface-mount thermistor 2, a constantan heating wire 1, and two insulating films 4, which is easy to fix and achieves double-sided insulation. In the implementation phase, temperature measurement and heating can be completed in one operation, which saves more time compared with traditional processes.

[0038] The on-board computer 6 includes a heating circuit 61, which is connected in series with a programmable switch 62. The programmable switch 62 and the heating circuit 61 are connected to the electrical connector 5 via a line. The on-board computer 6 also includes a measured circuit 63, which is connected in parallel with the heating circuit 61 via a line, and the heating circuit 63 is connected in series with the programmable switch 62. The onboard computer 6 also includes a series-connected voltage divider resistor 64 and a temperature measuring circuit 65, which are connected in parallel with the measured circuit 63. During the heating phase, the programmable switch 62 is closed downwards, and the heating circuit 61 supplies power to the constantan heating wire 1 through the electrical connector 2, causing the constantan heating wire 1 to heat. During the temperature measuring phase, the programmable switch 62 is closed upwards, the heating circuit 61 stops working, and the power supply circuit of the temperature measuring circuit 65 is turned on. After passing through the voltage divider resistor 64, a temperature-related voltage is generated across the high-resistance patch thermistor 2. After the measured circuit 63 measures the voltage, the temperature data is calculated. The heating phase and the temperature measuring phase work alternately, and the above working process can achieve heating and temperature measurement through two cables.

[0039] The high-resistance patch thermistor 2 has a package specification not exceeding 0402. Each high-resistance patch thermistor 2 and its corresponding constantan heating wire 1 are encapsulated within two insulating films 3, so that when temperature measurement is achieved, it has good insulation from spacecraft or related equipment.

[0040] The high-resistance surface mount thermistor 2 has a resistance of not less than 30KΩ at room temperature and not less than 5KΩ at 70℃, so that the power consumption of the high-resistance surface mount thermistor 2 does not exceed 0.2W within the operating range of -40℃ to 70℃.

[0041] The insulating film 3 is made of polyimide material to provide good insulation for the high-resistance chip thermistor 2 and constantan heating wire 1. The insulating film 3 has a thin sheet structure to facilitate adhesive encapsulation.

[0042] In the specific design, based on the specific conditions of the spacecraft, the appropriate resistance value of the constantan heating wire 1 and the size of the insulating film 3 are designed. A vacuum-resistant and high-low temperature-resistant bonding process is adopted to bond and encapsulate the high-resistance chip thermistor 2, constantan heating wire 1, and connecting wire 4 together inside the insulating film 3.

[0043] During the spacecraft thermal control implementation phase, the heater described in this application is attached to the surface of the controlled object (structural panels, equipment, etc.) and connected to the onboard computer 6 via electrical connector 5.

[0044] This invention provides a method for using an integrated temperature measurement and heating heater suitable for spacecraft, comprising the following steps:

[0045] Step 1: Set the temperature control target to T0 using the onboard computer 6;

[0046] Step 2: When the onboard computer 6 detects that the temperature of the high-resistance patch thermistor 2 is less than T0, the programmable switch 62 closes downwards, and the closing time lasts for t.

[0047] Step 3: When the time is up, the programmable switch 62 closes upward to stop heating, and the onboard computer 6 measures the temperature. If the temperature of the high-resistance patch thermistor 2 is greater than T0, heating will continue to stop. If the temperature of the high-resistance patch thermistor 2 is less than T0, the programmable switch 62 closes downward again to resume heating.

[0048] Step 4: Repeat the above process to keep the temperature of the controlled object at T0.

[0049] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.

[0050] Finally, it should be noted that the above description represents a preferred embodiment of the present invention. It should be pointed out that although preferred embodiments have been described, those skilled in the art, once they understand the basic inventive concept of the present invention, can make various improvements and modifications without departing from the principles described herein. These improvements and modifications should also be considered within the scope of protection of the present invention. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the embodiments of the present invention.

Claims

1. An integrated temperature measurement and heating heater suitable for spacecraft, characterized in that, include: Multiple constantan heating wires (1) are connected in parallel; Multiple high-resistance chip thermistors (2), each high-resistance chip thermistor (2) is connected in parallel with the corresponding constantan heating wire (1) through connecting wires (3); The high-resistance chip thermistor (2) has a resistance of not less than 30KΩ at room temperature and not less than 5KΩ at 70℃, so that the power consumption of the high-resistance chip thermistor (2) does not exceed 0.2W within the operating range of -40℃ to 70℃. The package specification of the high resistance chip thermistor (2) does not exceed the 0402 specification. Each constantan heating wire (1) and the corresponding high resistance chip thermistor (2) are disposed between two insulating films (4). The insulating film (4) is made of polyimide material; The connecting wire (3) extends out two insulating films (4) and is connected to the onboard computer (6) via an electrical connector (5).

2. The integrated temperature measurement and heating heater for spacecraft according to claim 1, characterized in that: The onboard computer (6) includes a heating circuit (61), which is connected in series with a programmable switch (62). The programmable switch (62) and the heating circuit (61) are connected to the electrical connector (5) via a line.

3. The integrated temperature measurement and heating heater suitable for spacecraft according to claim 2, characterized in that: The onboard computer (6) also includes a measured circuit (63), which is connected in parallel with the heating circuit (61) via a line and is connected in series with the programmable switch (62).

4. The integrated temperature measurement and heating heater for spacecraft according to claim 3, characterized in that: The onboard computer (6) also includes a series voltage divider resistor (64) and a temperature measuring circuit (65). The series voltage divider resistor (64) and the temperature measuring circuit (65) are connected in parallel with the measured circuit (63). During the heating phase, the programmable switch (62) is closed downwards, and the heating circuit (61) supplies power to the constantan heating wire (1) through the electrical connector (5), and the constantan heating wire (1) is heated. During the temperature measuring phase, the programmable switch (62) is closed upwards, the heating circuit (61) stops working, the power supply circuit of the temperature measuring circuit (65) is turned on, and after passing through the voltage divider resistor (64), a temperature-related voltage is generated across the high-resistance patch thermistor (2). After the measured circuit (63) measures the voltage, the temperature data is calculated.

5. A method of using an integrated temperature measurement and heating heater suitable for spacecraft as described in any one of claims 1 to 4, comprising the following steps: Step 1: Set the temperature control target to T0 using the onboard computer (6); Step 2: When the onboard computer (6) detects that the temperature of the high-resistance patch thermistor (2) is less than T0, the programmable switch (62) closes downwards for a duration of t. Step 3: When the time is reached, the programmable switch (62) closes upward to disconnect the heating, and the onboard computer (6) measures the temperature. At this time, if the temperature of the high-resistance patch thermistor (2) is greater than T0, the heating will continue to stop. When the temperature of the high-resistance patch thermistor (2) is less than T0, the programmable switch (62) closes downward again to resume heating. Step 4: Repeat the above process to keep the temperature of the controlled object at T0.

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