Dual-temperature-zone redundant thermal control structure and temperature control method of bi-propellant space engine

Abstract

The application relates to a dual-temperature-zone redundant thermal control structure and a temperature control method of a dual-component space engine, and solves the technical problems of a complex thermal resistance thermal control system, insufficient thermal resistance temperature resistance, low mechanical environment adaptability and large heater power of the dual-component space engine. The dual-temperature-zone redundant thermal control structure of the dual-component space engine comprises a main temperature control mechanism and a backup temperature control mechanism which are redundant to each other; a heating area of the engine comprises a main temperature control zone and a backup temperature control zone; the main temperature control mechanism comprises two main heaters and corresponding main thermal resistances arranged in the main temperature control zone, and the two main heaters are redundant to each other; the backup temperature control mechanism comprises two backup heaters and corresponding backup thermal resistances arranged in the backup temperature control zone, and the two backup heaters are redundant to each other. The temperature control method of the dual-temperature-zone redundant thermal control structure of the dual-component space engine improves the fault diagnosis accuracy of the main heater and the backup main heater.

Description

Technical Field

[0001] This invention specifically relates to a dual-component space engine dual-temperature zone redundant thermal control structure and temperature control method. Background Technology

[0002] The bicomponent space engine uses a nitrogen tetroxide / methylhydrazine combination propellant. The methylhydrazine fuel has a freezing point of -52.5°C, while the nitrogen tetroxide oxidizer has a freezing point of -13.6°C. Due to the cryogenic environment of space, the propellant entering the engine head during startup is rapidly cooled by the cryogenic metal structure. Once the propellant temperature drops to its freezing point, localized freezing or icing can occur, causing blockages in the propellant channels or injection holes, leading to decreased thrust and even functional failures such as engine burn-out. To prevent propellant icing in the engine head cavity due to excessively low temperatures, a heater is used to actively heat the engine head. A thermistor monitors the head temperature and controls the heater's on / off state, maintaining the engine head temperature within a reliable operating range through active thermal control.

[0003] The thermal control structure of a space engine needs to maintain the head temperature slightly above the propellant freezing point during non-operational periods to meet reliable operation requirements, while also withstanding the effects of alternating high and low temperatures and sustained high temperatures during operation. To address faults in heaters or thermistors during long-term on-orbit operation, the thermal control structure requires a certain degree of fault redundancy. Due to the high head temperature within the operational section of a bicomponent space engine, the thermistor placement requires special thermal insulation design due to limitations in the thermistor's high-temperature resistance. Currently, bicomponent space engines use silicone rubber encapsulation for the thermistors in the engine head, a method with insufficient mechanical adaptability. Current bicomponent space engine thermal control employs zoned thermal control, requiring thermistors in different zones to monitor temperatures, resulting in a large number of thermistors and a complex control system. Furthermore, constrained by the engine head structure and installation dimensions, most engines use only one heater for head heating, leading to poor uniformity of temperature distribution and high actual thermal control power.

[0004] Therefore, the thermal control structure of the dual-component space engine needs to solve technical problems such as the complexity of existing thermistor thermal control systems, insufficient temperature resistance of thermistors, low adaptability to mechanical environment, and excessive heater power. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problems of existing thermistor thermal control systems for bicomponent space engines, such as complexity, insufficient temperature resistance of thermistors, low adaptability to mechanical environments, and excessively high heater power. The invention provides a dual-temperature zone redundant thermal control structure and temperature control method for bicomponent space engines.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows:

[0007] A dual-component space engine dual-temperature zone redundant thermal control structure is set in the heating area of ​​the engine. Its special feature is that it includes a main temperature control mechanism and a backup temperature control mechanism that are redundant with each other.

[0008] The heating area of ​​the engine includes a main temperature control area and a backup temperature control area;

[0009] The main temperature control mechanism includes two main heaters and corresponding main thermistors located in the main temperature control zone, with the two main heaters being redundant.

[0010] The backup temperature control mechanism includes two backup heaters and corresponding backup thermistors located in the backup temperature control zone, with the two backup heaters being redundant.

[0011] Two main heaters and two backup heaters are arranged circumferentially in a staggered manner for heating the engine.

[0012] Furthermore, the two main heaters are connected in parallel to form a main heating circuit;

[0013] The two backup heaters are connected in parallel to form a backup heating circuit.

[0014] Furthermore, the main thermistors are mutually redundant;

[0015] The backup thermistors are mutually redundant;

[0016] Both the main thermistor and the backup thermistor are used to monitor the temperature at the docking position of the engine's injectors and control valves with the thrust chamber, and also serve as switch signals for starting and stopping heating for the main heater and the backup heater.

[0017] Furthermore, the main heater includes a heating zone, a first wire connected to the heating zone, and the heating zone is mounted on the engine flange; the first wire is used to connect to an external control system.

[0018] The structure and connection method of the backup heater are the same as those of the main heater.

[0019] The main thermistor includes a temperature sensing area and a second wire connected to the temperature sensing area; the temperature sensing area is installed in the middle ear groove of the heat insulation frame of the engine via a mounting block; the second wire is used to connect to an external control system.

[0020] The structure of the backup thermistor is the same as that of the main thermistor in terms of structure and connection method.

[0021] Both the first and second conductors are provided with lead tubes and sealing components on their exteriors.

[0022] Furthermore, both the main heater and the backup heater are irregularly shaped plate-type armored heaters, and the main heater and the backup heater have the same structure and specifications;

[0023] Both the main thermistor and the backup thermistor are tubular high-temperature resistant armored G2a thermistors, and the main thermistor and the backup thermistor have the same structure and specifications.

[0024] Furthermore, the two main heaters and two backup heaters are staggered and evenly distributed around the circumference.

[0025] Furthermore, the two end wires of the two main heaters are connected in parallel using electrical connector pins;

[0026] The two conductors at both ends of the two backup heaters are connected in parallel using electrical connector pins.

[0027] Meanwhile, this invention provides a temperature control method for the aforementioned dual-temperature-zone redundant thermal control structure of a dual-component space engine, characterized by the following steps:

[0028] 1) Start the two main heaters in the main temperature control mechanism to heat the engine, and use the two main thermistors to collect the engine temperature. Determine whether the temperature collected by the two main thermistors is less than T0. If so, the two main heaters are faulty and proceed to step 2); otherwise, proceed to step 3.

[0029] 2) Start the two backup heaters in the backup temperature control mechanism to heat the engine. Use the two backup thermistors in the backup temperature control mechanism to collect the engine temperature. Monitor the temperature collected by the two backup thermistors. When the temperature collected by the two backup thermistors is greater than or equal to T1, stop the two backup heaters from heating the engine. Then use the two backup thermistors to collect the engine temperature again. When the temperature collected by one of the backup thermistors is less than T0, repeat step 2) to achieve engine temperature control.

[0030] 3) The two main heaters heat the engine simultaneously until the temperature collected by the two main thermistors is greater than or equal to T1. Then, the two main heaters stop heating the engine and the engine temperature is collected by the two main thermistors. When the temperature collected by one of the main thermistors is less than T0, step 3) is repeated to achieve engine temperature control.

[0031] Compared with the prior art, the beneficial effects of the technical solution of the present invention are:

[0032] 1) This invention presents a dual-component space engine with a dual-temperature-zone redundant thermal control structure, featuring multiple redundancy functions. The engine's heating area is divided into a main temperature control zone and a backup temperature control zone, which are mutually redundant. The main temperature control mechanism of the main temperature control zone consists of two main heaters and corresponding main thermistors mounted on the engine flange. The backup temperature control mechanism of the backup temperature control zone consists of two backup heaters and corresponding backup thermistors mounted on the engine flange. In addition to the mutual redundancy between the two temperature control zones, the two main heaters and backup heaters within the same temperature control zone are also redundantly configured, improving the heating efficiency of the main heaters and backup heaters for the engine head.

[0033] 2) In the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention, the two main thermistors or two backup thermistors set in the same temperature control zone can realize their redundancy function. When one of the two main thermistors fails, the other main thermistor with a symmetrical layout can be used for temperature control. The two main heaters and two backup heaters in the same temperature control zone adopt a parallel connection structure. When one of the two main heaters or two backup heaters fails, the other can also complete the engine temperature control function, realizing the second layer of redundancy and improving the heating reliability of the entire dual-component space engine dual-temperature zone redundant thermal control structure.

[0034] 3) In the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention, the main thermistor and the backup thermistor are arranged in the heat insulation frame of the engine, which solves the problem of insufficient high temperature adaptability of the thermistor in the engine working section, and at the same time can meet the temperature monitoring requirements of the injector and control valve docking position of the entire engine in the non-working section of the engine.

[0035] 4) In the dual-component space engine dual-temperature zone redundant thermal control structure of this invention, the main heater and the backup heater are symmetrically distributed within the same temperature control zone. Both the main heater and the backup heater utilize high-power-density, irregularly shaped, armored heaters. The shapes of the main heater and the backup heater can be designed to match the engine mounting position structure, increasing the contact area between the main heater and the backup heater and the engine, further improving the heating efficiency of the main heater and the backup heater on the engine head. The two armored heaters within the same temperature control zone are arranged symmetrically in pairs. This symmetrical arrangement of the armor ensures uniform heating of the engine head by the armored heaters, achieving the goal of saving thermal control power.

[0036] 5) In the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention, the wires of two armored heaters in the same temperature control zone are welded together by the connector pins to form a parallel circuit. This realizes the function of controlling two symmetrically arranged armored heaters with one heating circuit, thereby achieving uniform heating of both sides of the engine head without increasing the number of engine heater channels or changing the control system structure. At the same time, the parallel circuit improves the fault redundancy capability of the armored heater. When a single armored heater fails, the circuit still has the ability to heat one side of the engine head.

[0037] 6) In the temperature control method of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention, a combined thermal control scheme of main heater and backup heater and main thermistor and backup thermistor is used, which improves the compactness of the thermal control structure and has a high degree of integration; the sensing zone and solid seal end of the main thermistor and backup thermistor on the engine adopt a reliable welding method, which improves their mechanical environment adaptability on the engine. Attached Figure Description

[0038] Figure 1 This is a schematic diagram of an embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention;

[0039] Figure 2 This is a schematic diagram showing the arrangement of two main heaters and their corresponding main thermistors, and two backup heaters and their corresponding backup thermistors in an embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention.

[0040] Figure 3 This is a schematic diagram of the irregularly shaped plate armored heater in an embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention;

[0041] Figure 4 This is a schematic diagram of the armored G2a thermistor in an embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention;

[0042] Figure 5 This is a schematic diagram of the ear groove structure of the engine heat insulation frame in an embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention;

[0043] Figure 6 This is a schematic diagram of the installation structure of the armored G2a thermistor and the irregularly shaped plate armored heater in the embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention.

[0044] Figure 7 This is a schematic diagram of the parallel connection structure of two armored heaters in an embodiment of the dual-component space engine dual-temperature zone redundant thermal control structure of the present invention.

[0045] The attached figures are labeled as follows:

[0046] 1-Engine, 11-Insulation frame, 111-Ear groove, 12-Flange, 2-Main heater, 21-Heating zone, 22-First lead pipe, 23-First sealing element, 24-First wire, 20-Backup heater, 3-Main thermistor, 31-Sensing zone, 32-Second lead pipe, 33-Second sealing element, 34-Second wire, 30-Backup thermistor, 4-Main clamp, 5-Backup clamp, 6-Main welding piece, 7-Backup welding piece, 8-Mounting block, 9-Baffle, 10-Electrical connector pin. Detailed Implementation

[0047] like Figure 1 As shown, a dual-temperature zone redundant thermal control structure for a space engine 1 is provided in the heating area of ​​the engine 1. It consists of the engine 1, two main heaters 2, two thermistors, two backup heaters 20, two backup thermistors 30, a main clamp 4, a backup clamp 5, a main welding piece 6, a backup welding piece 7, a baffle 9, the main clamp 4, the backup clamp 5, the main welding piece 6, and the backup welding piece 7.

[0048] The heating area of ​​engine 1 is provided with a main temperature control zone and a backup temperature control zone, which are redundant with each other. The main temperature control mechanism of the main temperature control zone consists of two main heaters 2 and corresponding main thermistors 3 installed on the flange 12 of engine 1. The two main heaters 2 are redundant with each other. The backup temperature control mechanism of the backup temperature control zone consists of two backup heaters 20 and corresponding backup thermistors 30 installed on the flange 12 of engine 1. The two backup heaters 20 are redundant with each other. The two main heaters 2 and the two backup heaters 20 are staggered and evenly distributed around the circumference, and they are all used to heat engine 1.

[0049] In addition to the redundancy between the main temperature control zone and the backup temperature control zone, the two ends of the wires of the two main heaters 2 are connected in parallel to form the main heating circuit; the two ends of the wires of the two backup heaters 20 are connected in parallel to form the backup heating circuit. This makes the two main heaters 2 and the backup heaters 20 in the same temperature control zone redundantly configured. The two main thermistors 3 or the two backup thermistors 30 set in the same temperature control zone can also realize their redundancy function. When any one of the two main thermistors 3 fails, the other main thermistor 3 with a symmetrical layout can be used for temperature control. The two main heaters 2 and the two backup heaters 20 in the same temperature control zone are all connected in parallel. When any one of the two main heaters 2 or the two backup heaters 20 fails, the other can also complete the temperature control function of the engine 1.

[0050] like Figure 2As shown, the main heater 2 and the backup heater 20 use irregularly shaped plate armored heaters with high power density. The shape of the main heater 2 and the backup heater 20 can be designed to match the installation position structure of the engine 1, which increases the contact area between the main heater 2 and the backup heater 20 and the engine 1, thereby improving the heating efficiency of the main heater 2 and the backup heater 20 on the head of the engine 1.

[0051] like Figure 3 , Figure 4 As shown, the main heater 2 includes a heating zone 21 and a first wire 24 connected together; the heating zone 21 is mounted on the flange 12 of the engine 1; the first wire 24 is used to connect to an external control system; the structure of the backup heater 20 is the same as that of the main heater 2 and the connection method is the same; preferably, both the main heater 2 and the backup heater 20 are irregularly shaped plate-type armored heaters. The main thermistor 3 is connected to the temperature sensing zone 31 and the second wire 34; the temperature sensing zone 31 is set in the ear groove 111 in the middle of the heat insulation frame 11 of the engine 1 through the mounting block 8; the second wire 34 is used to connect to an external control system; the structure of the backup thermistor 30 is the same as that of the main thermistor 3 and the connection method is the same; wherein the first wire 24 is provided with a first lead tube 22 and a first sealing member 23 on the outside, and the second wire 34 is provided with a second lead tube 32 and a second sealing member 33 on the outside.

[0052] In this embodiment, both the main thermistor 3 and the backup thermistor 30 are tubular high-temperature resistant armored G2a thermistors. The main thermistor 3 and the backup thermistor 30 have the same structure and specifications. The four armored G2a thermistors are arranged along the axial direction of the engine 1 in the ear groove 111 in the middle of the heat insulation frame 11 of the engine 1. The main thermistor 3 and the backup thermistor 30 are used to monitor the temperature of the injector and control valve of the engine 1 at the docking position with the thrust chamber, and at the same time serve as the switch signals for starting and stopping heating of the main heater 2 and the backup heater 20.

[0053] Both the main heater 2 and the standby heater 20 are irregularly shaped armored heaters, with identical structures and specifications. All four armored heaters are connected and secured to the flange 12 of the engine 1 using bolts and self-locking nuts, ensuring a reliable connection and preventing loosening under alternating hot and cold conditions. Two armored heaters within the same temperature control zone are arranged symmetrically in pairs. This symmetrical arrangement ensures uniform heating of the engine head, thus saving thermal control power.

[0054] The installation positions of the four tubular high-temperature resistant armored G2a thermistors correspond one-to-one with the installation positions of the four irregularly shaped armored heaters. The armored G2a thermistors can monitor the faults of the irregularly shaped armored heaters at the corresponding positions. When the irregularly shaped armored heaters fail, the data from the armored G2a thermistors at the corresponding positions can be used for fault diagnosis, thereby improving the accuracy of fault diagnosis for the irregularly shaped armored heaters.

[0055] like Figure 5 , Figure 6 As shown, the sensing area 31 of the armored G2a thermistor is placed in the ear groove 111 in the middle of the heat insulation frame 11 of the engine 1, and pressed tightly from the outside by the mounting block 8, so that the sensing area 31 of the tubular high-temperature resistant armored G2a thermistor is tightly fitted with the ear groove 111 in the middle of the heat insulation frame 11 of the engine 1. Then, the mounting block 8 is welded to the heat insulation frame 11 of the engine 1 by argon arc welding, and the baffle 9 is welded to the bottom of the mounting block 8, completing the connection and fixation of the sensing area 31 of the armored G2a thermistor. The second lead tube 32 of the armored G2a thermistor is placed in the main clamp 4 or the backup clamp 5 of the engine 1, and pressed tightly by the main welding piece 6 or the backup welding piece 7, so that the second lead tube 32 of the tubular high-temperature resistant armored G2a thermistor is tightly fitted with the main clamp 4 and the backup clamp 5. The main clamp 4 and main welding piece 6, and the backup clamp 5 and backup welding piece 7 are welded together using argon arc welding to complete the connection and fixation of the sealing end of the tubular high-temperature resistant armored G2a thermistor. This welding installation method, along with the installation of the main clamp 4 and main welding piece 6, improves the mechanical environmental adaptability of the armored G2a thermistor on engine 1.

[0056] The heating zone 21 of the irregularly shaped armored heater is installed on the flange 12 of the engine 1 using bolts. After installation, the two are made to fit tightly together, and a self-locking nut is used to apply torque to loosen it. Then, the first lead tube 22 of the irregularly shaped armored heater is inserted into the main clamp 4 or backup clamp 5 of the engine 1, and pressed with the main welding piece 6 or backup welding piece 7 to make the first lead tube 22 of the irregularly shaped armored heater fit tightly with the main clamp 4 and backup clamp 5. Finally, the main clamp 4 and main welding piece 6, and the backup clamp 5 and backup welding piece 7 are welded together by argon arc welding to complete the connection and fixation of the fixed end of the irregularly shaped armored heater. The four armored heaters are connected and fastened to the flange 12 of the engine 1 by bolts and self-locking nuts, ensuring a reliable connection of the armored heaters on the engine 1 and preventing the armored heaters from loosening under alternating hot and cold environments.

[0057] like Figure 7As shown, the wires of two armored heaters in the same temperature control zone are welded together using the connector pin 10 to form a parallel circuit. This enables the control of two symmetrically arranged armored heaters with one heating circuit, achieving the function of uniformly heating both sides of the engine head. At the same time, the parallel circuit improves the fault redundancy capability of the armored heaters. When a single armored heater fails, the circuit still has the ability to heat only one side of the engine head.

[0058] In the space environment, the ambient temperature of engine 1 is low, causing the temperature of space engine 1 to drop. When the temperature of engine 1 is lower than the propellant temperature, engine 1 cannot operate normally. Therefore, in order to ensure reliable operation of engine 1 in the cold space environment, space engine 1 needs to employ a thermal control structure. Thus, this invention also provides a temperature control method for a dual-component space engine 1 with a dual-temperature-zone redundant thermal control structure, comprising the following steps:

[0059] 1) The main temperature control mechanism is used first to control the temperature of engine 1. The external control system issues a command to start the main heating circuit of the main heater 2, and both main heaters 2 simultaneously heat engine 1, causing the temperature of engine 1 and the temperatures of the two main thermistors 3 to continuously rise. When the temperatures collected by the two main thermistors 3 are simultaneously greater than or equal to T1, the external control system issues a command to stop the main heating circuit of the main heater 2, and the two main heaters 2 stop heating engine 1. Due to the cold environment of the space, the temperature of engine 1 will continue to drop until the temperature collected by either of the two main thermistors 3 reaches T0. At this point, the external control system issues a command to start the main heating circuit of the main heater 2, and both main heaters 2 simultaneously heat engine 1. The main temperature control mechanism cycles through heating and stopping engine 1 using the above method.

[0060] 2) When the heater or thermistor of the main temperature control mechanism fails (i.e., the temperature collected by either of the two main thermistors 3 is less than T0), the external control system will activate the backup temperature control mechanism to perform thermal control on engine 1. When the temperature collected by either of the two backup thermistors 30 is T0, the external control system receives a command to start the backup heating circuit of the backup heater 20. Both backup heaters 20 simultaneously heat engine 1, and the temperature of engine 1 and the temperatures of the two backup thermistors 30 continuously rise. When the temperatures collected by both backup thermistors 30 are simultaneously greater than or equal to T1, the external control system issues a command to stop the backup heating circuit of the backup heater 20. The two backup heaters 20 stop heating engine 1. Due to the cold environment of the space, the temperature of engine 1 will continue to drop until the temperature collected by either of the two backup thermistors 30 reaches T0. At this point, the external control system issues a command to start the backup heating circuit of the backup heater 20, and both backup heaters 20 simultaneously heat engine 1. The backup temperature control mechanism cycles through heating and stopping engine 1 in the above manner.

[0061] 3) Diagnose faults in the two main heaters 2 and the two standby heaters 20;

[0062] a) When the external control system issues a start heating command for the main heater 2, if the temperature collected by both main thermistors 3 is less than T0, it means that both main heaters 2 have failed; if the temperature of one of the two main thermistors 3 is less than T0 and the temperature of the other main thermistor 3 is greater than T0, it means that the main heater 2 installed at the position of the main thermistor 3 with the temperature less than T0 has failed.

[0063] b) When the external control system issues a start heating command for the backup heater 20, if the temperature collected by both backup thermistors 30 is less than T0, it means that both backup heaters 20 have failed; if the temperature of one of the two backup thermistors 30 is less than T0 and the temperature of the other backup thermistor 30 is greater than T0, it means that the backup heater 20 installed at the position of the backup thermistor 30 with the temperature less than T0 has failed.

Claims

1. A dual-component space engine dual-temperature zone redundant thermal control structure, disposed in the heating area of ​​engine (1), characterized in that: This includes redundant main temperature control mechanisms and backup temperature control mechanisms; The heating area of ​​the engine (1) includes a main temperature control area and a backup temperature control area; The main temperature control mechanism includes two main heaters (2) and corresponding main thermistors (3) located in the main temperature control zone, with the two main heaters (2) being redundant with each other; The backup temperature control mechanism includes two backup heaters (20) and corresponding backup thermistors (30) set in the backup temperature control zone, and the two backup heaters (20) are redundant with each other; Two main heaters (2) and two backup heaters (20) are arranged circumferentially in a staggered manner for heating the engine (1); The main heater (2) and the backup heater (20) are both irregularly shaped plate armored heaters, and the main heater (2) and the backup heater (20) have the same structure and specifications; The main thermistor (3) and the backup thermistor (30) are both tubular high-temperature armored G2a thermistors, and the main thermistor (3) and the backup thermistor (30) have the same structure and specifications.

2. The dual-component space engine dual-temperature zone redundant thermal control structure according to claim 1, characterized in that: The two main heaters (2) are connected in parallel to form the main heating circuit; The two standby heaters (20) are connected in parallel to form a standby heating circuit.

3. The dual-component space engine dual-temperature zone redundant thermal control structure according to claim 2, characterized in that: The main thermistors (3) are mutually redundant; The prepared thermistors (30) are mutually redundant; The main thermistor (3) and the backup thermistor (30) are both used to monitor the temperature of the injector and control valve of the engine (1) at the docking position with the thrust chamber, and also serve as the switch signals for starting and stopping heating of the main heater (2) and the backup heater (20).

4. The dual-component space engine dual-temperature zone redundant thermal control structure according to claim 3, characterized in that: The main heater (2) includes a heating zone (21) and a first wire (24) connected to the heating zone (21); the heating zone (21) is mounted on the flange (12) of the engine (1); the first wire (24) is used to connect to an external control system; The structure of the backup heater (20) is the same as that of the main heater (2) in terms of structure and connection method; The main thermistor (3) includes a temperature sensing area (31) and a second wire (34) connected to the temperature sensing area (31); the temperature sensing area (31) is set in the ear groove (111) in the middle of the heat insulation frame (11) of the engine (1) by a mounting block (8); the second wire (34) is used to connect to an external control system; The structure of the backup thermistor (30) is the same as that of the main thermistor (3) in terms of structure and connection method; Both the first conductor (24) and the second conductor (34) are provided with lead tubes and sealing components on their exteriors.

5. A dual-component space engine dual-temperature zone redundant thermal control structure according to any one of claims 1-4, characterized in that: The two main heaters (2) and the two backup heaters (20) are staggered and evenly distributed around the circumference.

6. A dual-component space engine dual-temperature zone redundant thermal control structure according to any one of claims 1-4, characterized in that: The two main heaters (2) are connected in parallel by electrical connector pins (10); The two ends of the wires of the two backup heaters (20) are connected in parallel by electrical connector pins (10).

7. A temperature control method for a dual-temperature-zone redundant thermal control structure for a dual-component space engine as described in any one of claims 1-6, characterized in that, Includes the following steps: 1) Start the two main heaters (2) in the main temperature control mechanism to heat the engine (1), and use the two main thermistors (3) to collect the temperature of the engine (1). Determine whether the temperature collected by the two main thermistors (3) is less than T0; if so, the two main heaters (2) have failed, and proceed to step 2); otherwise, proceed to step 3). 2) Start the two backup heaters (20) in the backup temperature control mechanism to heat the engine (1), use the two backup thermistors (30) in the backup temperature control mechanism to collect the temperature of the engine (1), monitor the temperature collected by the two backup thermistors (30), when the temperature collected by the two backup thermistors (30) is greater than or equal to T1, stop the two backup heaters (20) from heating the engine (1), and then use the two backup thermistors (30) to collect the temperature of the engine (1) again. When the temperature collected by one of the backup thermistors (30) is less than T0, repeat step 2) to achieve temperature control of the engine; 3) The two main heaters (2) heat the engine (1) simultaneously until the temperature collected by the two main thermistors (3) is greater than or equal to T1. Then, the two main heaters (2) stop heating the engine (1) and the two main thermistors (3) are used to collect the temperature of the engine (1). When the temperature collected by one of the main thermistors (3) is less than T0, step 3) is repeated to achieve temperature control of the engine.

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