Space engine thermal control structure and space engine

Abstract

This invention discloses a thermal control structure and a space engine, relating to the field of thermal control device technology, to solve the problem of excessive heat consumption caused by uneven heating. The space engine thermal control structure includes: a first dual-loop heater and a second dual-loop heater, both mounted on the injection plate and arranged opposite to each other; the first dual-loop heater has a first heating wire and a second heating wire, and the second dual-loop heater has a third heating wire and a fourth heating wire; a first single-loop heater and a second single-loop heater are both mounted on a flange, both closely attached to the oxidizer control valve; a first series branch formed by the first single-loop heater and the first heating wire is connected in parallel with the third heating wire to form a main heating loop; a second series branch formed by the second single-loop heater and the fourth heating wire is connected in series with the second heating wire to form a backup heating loop. Both the main and backup heating loops ensure that the entire injection plate and control valve are heated evenly and at a uniform temperature, saving heating power consumption.

Description

Technical Field

[0001] This invention relates to the field of thermal control device technology, specifically to a thermal control structure for a space engine and a space engine. Background Technology

[0002] The bicomponent space engine uses a nitrogen tetroxide / methylhydrazine combination propellant. The freezing point of the methylhydrazine fuel is -52.5℃, and that of the nitrogen tetroxide oxidizer is -13.6℃. Because the space engine operates in a cryogenic environment, the propellant's freezing point significantly affects its operation. During engine startup, the propellant entering the engine head exchanges heat with the cryogenic metal structure, rapidly cooling down. If the propellant temperature drops to or below its freezing point, it can cause localized freezing or icing, leading to blockages in the propellant flow channels or injection holes. This can result in decreased thrust, localized flow deviations, or even functional failures such as engine body ablation. To prevent malfunctions caused by excessively low temperatures, an electric heater is used to actively heat the engine head. A thermistor monitors the head temperature and controls the heater's on / off state, ensuring the engine head temperature remains within the reliable operating range for the propellant.

[0003] In addition, during the heat recovery process after the engine is ignited and shut down for a long time, the high temperature of the body is conducted to the low temperature of the head. Therefore, the engine head needs to adopt a heat insulation frame structure to increase the thermal resistance between the injection plate (which is connected to the body) and the flange (which is connected to the solenoid valve), so as to avoid the non-metallic parts inside the solenoid valve from being deformed at high temperature due to the heat recovery of the engine, which would cause its function to fail.

[0004] Current active thermal control structures for space engines typically employ two heating circuits, a primary and a backup, to provide a degree of fault redundancy. Each circuit uses only one electric heater, positioned on either side of the nozzle injector plate (requiring intensive temperature control) and on the outer wall of the oxidizer control valve on the flange, serving as backups for each other. In this structure, when the primary heating circuit is energized, the heater on the nozzle plate only heats the heater on one side of the primary circuit, while the heater on the other side (for the backup circuit) remains inactive. This results in a significant temperature gradient between the two sides of the nozzle plate and between the nozzle plate and the flange structure, leading to uneven heating. To ensure reliable temperature control in the lowest temperature region of the propellant flow channel, the electric heater power needs to be significantly increased, resulting in excessively high actual thermal control power consumption. Summary of the Invention

[0005] The purpose of this invention is to provide a thermal control structure and a space engine for improving the uniformity of heating temperature at the head flange structure of a space engine.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] In a first aspect, the present invention provides a thermal control structure for a space engine, comprising: a first dual-loop heater, a second dual-loop heater, a first single-loop heater, and a second single-loop heater;

[0008] The first dual-circuit heater and the second dual-circuit heater are both located on the side of the injection plate near the flange and are arranged opposite to each other. The first dual-circuit heater is provided with a first heating wire and a second heating wire, and the second dual-circuit heater is provided with a third heating wire and a fourth heating wire.

[0009] Both the first and second single-loop heaters are mounted on the flange and are in close contact with the outer wall of the oxidant control valve.

[0010] The first single-loop heater is connected in series with the first heating wire to form the first series branch, and the first series branch is connected in parallel with the third heating wire to form the main heating circuit;

[0011] The second single-loop heater is connected in series with the fourth heating wire to form a second series branch, and the second series branch is connected in parallel with the second heating wire to form a backup heating circuit, or the second single-loop heater is connected in series with the second heating wire to form a second series branch, and the second series branch is connected in parallel with the fourth heating wire to form a backup heating circuit.

[0012] Optionally, in the above-mentioned space engine thermal control structure, the first dual-loop heater includes:

[0013] The first housing is in close contact with the injection plate. The first heating wire and the second heating wire are both disposed inside the first housing, and the first heating wire and the second heating wire are surrounded by thermally conductive material.

[0014] The first main circuit port is disposed on the first housing. The first main circuit port is connected to the first heating wire circuit. The first heating wire is connected in series with the first single circuit heater through the first main circuit port to form a first series branch.

[0015] The first backup circuit port is located on the first housing and is connected to the second heating wire circuit. The second heating wire is connected in series with the second single-circuit heater through the first backup circuit port to form a second series branch.

[0016] Optionally, in the above-mentioned space engine thermal control structure, the first housing and the injection disk are fixed by a first fastening component, or the first housing and the injection disk are bonded together, or the first housing and the injection disk are welded together as an integral structure.

[0017] Optionally, in the above-mentioned space engine thermal control structure, the second dual-loop heater includes:

[0018] The second housing is in close contact with the injection plate. The third and fourth heating wires are both located inside the second housing, and the third and fourth heating wires are surrounded by thermally conductive material.

[0019] The second main circuit port is located on the second housing and is connected to the third heating wire circuit. The third heating wire is connected in parallel with the first series branch through the second main circuit port.

[0020] The second backup circuit port is located on the second housing and is connected to the fourth heating wire circuit. The fourth heating wire is connected in parallel with the second series branch through the second backup circuit port.

[0021] Optionally, in the above-mentioned space engine thermal control structure, the second housing and the injection disk are fixed by a second fastening component, or the second housing and the injection disk are bonded together, or the second housing and the injection disk are welded together as an integral structure.

[0022] Optionally, the above-mentioned space engine thermal control structure also includes a temperature sensing component, with one or more temperature sensing components disposed between the first dual-loop heater and the second dual-loop heater for monitoring the temperature of the first dual-loop heater and the second dual-loop heater.

[0023] Optionally, in the above-mentioned space engine thermal control structure, the temperature sensing component is a thermistor or a thermocouple.

[0024] Optionally, in the above-mentioned space engine thermal control structure, both the second dual-loop heater and the first dual-loop heater are semi-encircled by the heat insulation frame, and the second dual-loop heater and the first dual-loop heater are symmetrically placed relative to the heat insulation frame.

[0025] Optionally, in the above-mentioned space engine thermal control structure, both the primary heating circuit and the backup heating circuit include: leads, pins, and sockets;

[0026] The main heating circuit and the backup heating circuit are connected by leads;

[0027] The pins are soldered to the leads;

[0028] The socket is soldered onto the lead wire, and the socket and pin are engaged to connect adjacent leads.

[0029] In a second aspect, the present invention also provides a space engine, comprising an engine body, an engine head, and a thermal control structure, wherein the thermal control structure is any of the aforementioned space engine thermal control structures.

[0030] Compared with the prior art, when the above technical solution is adopted, the first dual-circuit heater and the second dual-circuit heater are both set on the injection plate and are arranged opposite to each other. The first single-circuit heater and the second single-circuit heater are set on the flange and close to the outer wall of the oxidant control valve. They are connected by circuit to form the main heating circuit and the backup heating circuit. The two heating circuits are independent of each other and do not interfere with each other. Because the space engine needs to be in orbit for extended periods, operating in a cryogenic environment, after connecting the primary and backup heating circuits, the primary heating circuit is first energized. The first dual-circuit heater, the second dual-circuit heater, and the first single-circuit heater on the primary heating circuit all heat up, simultaneously providing heat to the entire injection plate and flange. When the primary heating circuit malfunctions and the heating temperature provided by the primary heating circuit cannot meet the operational requirements of the space engine, the system switches to the backup heating circuit. The backup heating circuit is then energized, and at this time, the first dual-circuit heater, the second dual-circuit heater, and the second single-circuit heater on the backup heating circuit also heat up. Both the primary and backup heating circuits can achieve uniform heating of the entire injection plate and the oxidizer control valve on the flange, improving the uniformity of thermal control temperature and saving thermal control power consumption. Attached Figure Description

[0031] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0032] Figure 1 This is a schematic diagram of the thermal control structure of the space engine in an embodiment of the present invention;

[0033] Figure 2 This is a schematic diagram of the first dual-loop heater structure in an embodiment of the present invention;

[0034] Figure 3 This is a schematic diagram of the series-parallel connection structure of the main heating circuit in an embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of the series-parallel connection structure of the main heating circuit in an embodiment of the present invention.

[0036] Figure label:

[0037] 1-First dual-circuit heater; 11-Lead wire; 12-Pin; 13-Socket; 14-Sleeve; 101-First heating wire; 102-Second heating wire; 103-First housing; 104-First main circuit port; 105-First backup circuit port; 106-First fastening component; 2-Second dual-circuit heater; 203-Second housing; 204-Second main circuit port; 205-Second backup circuit port; 206-Second fastener; 3-First single-circuit heater; 4-Second single-circuit heater; 5-Injection plate; 6-Flange; 7-Oxidant control valve; 8-Temperature sensing component; 9-Insulation frame. Detailed Implementation

[0038] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0039] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0040] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0041] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0042] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0043] like Figures 1-4 As shown, an embodiment of the present invention provides a space engine thermal control structure including: a first dual-loop heater 1, a second dual-loop heater 2, a first single-loop heater 3, and a second single-loop heater 4.

[0044] The first dual-loop heater 1 and the second dual-loop heater 2 are both located on the injection plate 5 near the flange 6 and are arranged opposite each other. The first dual-loop heater 1 is provided with a first heating wire 101 and a second heating wire 102, and the second dual-loop heater 2 is provided with a third heating wire and a fourth heating wire. The first single-loop heater 3 and the second single-loop heater 4 are both located on the flange 6 and are in close contact with the outer wall of the oxidant control valve 7. The first single-loop heater 3 and the first heating wire 101 are connected in series to form a first series branch, and the first series branch and the third heating wire are connected in parallel to form a main heating circuit. The second single-loop heater 4 and the fourth heating wire are connected in series to form a second series branch, and the second series branch and the second heating wire 102 are connected in parallel to form a backup heating circuit, or the second single-loop heater 4 and the second heating wire 102 are connected in series to form a second series branch, and the second series branch and the fourth heating wire are connected in parallel to form a backup heating circuit.

[0045] like Figure 1As shown, in specific implementation, the first dual-loop heater 1 and the second dual-loop heater 2 are both set on the injection plate 5 and are arranged opposite to each other. The first single-loop heater 3 and the second single-loop heater 4 are set on the flange 6 and are close to the outer wall of the oxidant control valve 7. They are connected by circuit to form the main heating circuit and the backup heating circuit. The two heating circuits are independent of each other and do not interfere with each other. In operation, the main heating circuit is energized. The main heating circuit has two connection methods: First, the first heating wire 101 on the first dual-circuit heater 1 is connected in series with the first single-circuit heater 3 to form a first series branch. The main heating circuit formed by this first series branch and the third heating wire on the second dual-circuit heater 2 in parallel is energized. Alternatively, the third heating wire on the second dual-circuit heater 2 is connected in series with the first single-circuit heater 3 to form a first series branch. The main heating circuit formed by this first series branch and the first heating wire 101 on the first dual-circuit heater 1 in parallel is energized. Both connection methods allow the first dual-circuit heater 1, the second dual-circuit heater 2, and the first single-circuit heater 3 on the main heating circuit to heat up, simultaneously providing heat to the entire injection plate 5 and flange 6. When the main heating circuit malfunctions, it cannot provide the space engine with the required heating temperature. Switch to the backup heating circuit and then energize it. The backup circuit has two connection methods: the second heating wire 102 on the first dual-circuit heater 1 is connected in series with the second single-circuit heater 4 to form a second series branch, and the backup heating circuit formed by the second series branch and the fourth heating wire of the second dual-circuit heater 2 in parallel is energized; or the fourth heating wire on the second dual-circuit heater 2 is connected in series with the second single-circuit heater 4 to form a second series branch, and the backup heating circuit formed by the second series branch and the second heating wire 102 of the first dual-circuit heater 1 in parallel is energized. Both connection methods can make the first dual-circuit heater 1, the second dual-circuit heater 2 and the second single-circuit heater 4 on the backup heating circuit also heat up. Both the main heating circuit and the backup heating circuit can achieve uniform heating of the entire injection plate 5 and heating of the oxidant control valve 7 on the flange 6.

[0046] Compared to traditional single-sided heating structures where the main heating circuit and backup heating circuit, when energized individually, can only heat a portion (e.g., only half) of the injection disk 5, the space engine thermal control structure of this application, without changing the spatial structure, allows for simultaneous temperature control of both parts of the injection disk 5 by arranging the first dual-circuit heater 1 and the second dual-circuit heater 2 relative to each other. Furthermore, both the main and backup heating circuits are complete heating circuits, and energizing each complete heating circuit simultaneously and uniformly heats both parts of the injection disk 5 and the oxidizer control valve 7 on the flange 6. Specifically, when the main heating circuit is energized, the first dual-circuit heater 1, the second dual-circuit heater 2, and the first single-circuit heater 3 on the main heating circuit all generate heat, simultaneously providing heat to both sides of the injection disk 5 and the flange 6. When the backup heating circuit is energized, the first dual-circuit heater 1, the second dual-circuit heater 2, and the second single-circuit heater 4 on the backup heating circuit also generate heat, improving the uniformity of the thermal control temperature and saving thermal control power consumption. Thermal control tests show that the symmetrical heating method of this invention saves about 20% of power consumption compared to the traditional single-sided heating method.

[0047] like Figure 3 As shown, in this embodiment, as one possible implementation, the first single-loop heater 3 and the first heating wire 101 of the first double-loop heater 1 on the main heating circuit form a first series branch. In actual heating operation, the total resistance of the first series branch is the same as the resistance of the third heating wire on the second double-loop heater 2, that is, the resistance of the first double-loop heater 1 is different from the resistance of the second double-loop heater 2. The parallel branches on the main heating circuit have the same resistance, and the thermal control areas of the main heating circuit and the backup heating circuit are redundant. The resistance distribution on the backup heating circuit is the same as the distribution of the components in the main heating circuit, which reduces thermal control power consumption and improves resource utilization.

[0048] like Figure 2As shown, specifically in the thermal control structure of the space engine, the first dual-loop heater 1 includes: a first heating wire 101, a second heating wire 102, a first housing 103, a first main circuit port 104, and a first backup circuit port 105. The first housing 103 is in close contact with the injection disk 5. Both the first heating wire 101 and the second heating wire 102 are disposed within the first housing 103, and thermally conductive material is filled around both heating wires 101 and 102. The first main circuit port 104 is disposed on the first housing 103 and is electrically connected to the first heating wire 101. The first heating wire 101 is connected in series with the first single-loop heater 3 through the first main circuit port 104 to form a first series branch. The first backup circuit port 105 is disposed on the first housing 103 and is electrically connected to the second heating wire 102. The second heating wire 102 is connected in series with the second single-loop heater 4 through the first backup circuit port 105 to form a second series branch. By using a series-parallel circuit connection method, the problem of increasing the number of heating control loops and complicating the hardware and software of the control system when multiple heaters are arranged in multiple areas to implement thermal control of the space engine is solved. The circuit connection method is simplified, making installation and disassembly convenient.

[0049] like Figure 1 As shown, specifically in this embodiment, the first housing 103 and the injection disc 5 are fixed together by a first fastening component 106. The first fastening component 106 can be a bolt or a screw. The bolt secures the first housing 103 to the injection disc 5, or the screw secures the first housing 103 to the injection disc 5. Both bolts and screws provide good stability and high reliability in fixing the first housing 103 to the injection disc 5. The first housing 103 has an arc-shaped profile, with grooves at both ends. The first fastening component 106 passes through these grooves to secure the first housing 103 to the injection disc 5, facilitating disassembly and installation.

[0050] In some embodiments, the first housing 103 is bonded to the injection disk 5, and the first housing 103 and the injection disk 5 are bonded together, which improves the stability of the first housing 103 on the injection disk 5 and makes the overall structure compact.

[0051] In other embodiments, the first housing 103 is welded to the injection disk 5 as an integral structure, which improves the stability of the first housing 103 on the injection disk 5 and makes the overall structure compact.

[0052] Specifically, in the thermal control structure of the space engine, the second dual-loop heater 2 includes: a third heating wire, a fourth heating wire, a second housing 203, a second main circuit port 204, and a second backup circuit port 205. The second housing 203 is in close contact with the injection disk 5. Both the third and fourth heating wires are disposed within the second housing 203, and their surroundings are filled with thermally conductive material. The second main circuit port 204 is located on the second housing 203 and is electrically connected to the third heating wire, which is connected in parallel to the first series branch through the second main circuit port 204. The second backup circuit port 205 is located on the second housing and is electrically connected to the fourth heating wire, which is connected in parallel to the second series branch through the second backup circuit port 205. This series-parallel connection structure allows for continued heating of the engine using the other parallel circuit if a single heater's parallel circuit fails, providing fault redundancy and improving the safety and reliability of the space engine's thermal control structure.

[0053] For example, the thermally conductive materials inside the first and second shells can be magnesium oxide, quartz sand, or other filling materials with good thermal conductivity; no specific limitation is made to the thermally conductive materials here. Magnesium oxide and quartz sand are both electrical insulators and have good thermal conductivity, high stability, and low price, providing good heat conduction for the first heating wire 101, the second heating wire 102, the third heating wire, and the fourth heating wire, extending the service life of the first dual-loop heater 1 and the second dual-loop heater 2, and reducing the usage cost of the space engine thermal control structure.

[0054] like Figure 4 As shown, further in the space engine thermal control structure, the second housing 203 and the injection disk 5 are fixed together by a second fastening component 206. The second fastening component 206 can be a bolt or a screw. Bolts fix the second housing 203 to the injection disk 5, or screws fix the second housing 203 to the injection disk 5. Both bolts and screws provide good stability and high reliability in fixing the second housing 203 to the injection disk 5. The second housing 203 has an arc-shaped profile, symmetrical to the arc-shaped profile of the first housing 103. Grooves are provided at both ends of the arc-shaped profile. The second fastening component 206 passes through these grooves to fix the second housing 203 to the injection disk 5, facilitating disassembly and installation.

[0055] In some embodiments, the second housing 203 is bonded to the injection disk 5, which improves the stability of the second housing 203 on the injection disk 5 and makes the overall structure compact.

[0056] In other embodiments, the second housing 203 is welded to the injection disk 5 as an integral structure, which improves the stability of the second housing 203 on the injection disk 5 and makes the overall structure compact.

[0057] As one possible implementation, the thermal control structure of the space engine also includes a temperature sensing component 8. One or more temperature sensing components 8 are installed between the first dual-loop heater 1 and the second dual-loop heater 2 to monitor the temperature of the first dual-loop heater 1 and the second dual-loop heater 2. When the heating temperature of either the first dual-loop heater 1 or the second dual-loop heater 2 does not meet the operating requirements, the temperature sensing component 8 sends an electrical signal to the control system. The control system then switches the primary heating circuit to the backup heating circuit to continue heating. That is, by monitoring the heating temperature of the engine head through the temperature sensing component 8, when the temperature is too low or too high, the system controls the on / off state of the heater and switches between the primary heating circuit and the backup heating circuit, keeping the engine head temperature within a reliable operating range and improving the safety and reliability of the space engine thermal control structure.

[0058] like Figure 1 As shown, in this embodiment, the temperature sensing component 8 is a thermistor. Thermistors are small in size and low in cost, reducing the cost of the space engine's thermal control structure. They also have advantages such as good stability, strong overload capacity, and high sensitivity in monitoring temperature changes. When the thermistor is placed between the first dual-loop heater 1 and the second dual-loop heater 2, it can quickly detect whether the heating temperature of the first dual-loop heater 1 and the second dual-loop heater 2 meets the working requirements, thus improving the safety, reliability, and sensitivity of the space engine's thermal control structure.

[0059] In some embodiments, the temperature sensing component 8 is a thermocouple. Thermocouples offer high measurement accuracy, simple structure, and high efficiency, and can accurately sense temperature changes. When a thermocouple is positioned between the first dual-loop heater 1 and the second dual-loop heater 2, it can quickly detect whether the heating temperatures of the first dual-loop heater 1 and the second dual-loop heater 2 meet operational requirements, improving the safety, reliability, and sensitivity of the space engine's thermal control structure. Furthermore, thermocouples have good stability, are not easily deformed, and can measure a wide temperature range, extending the service life of the space engine's thermal control structure and ensuring its stability and reliability.

[0060] Specifically, in this embodiment, both the second dual-loop heater 2 and the first dual-loop heater 1 are semi-encircling the heat insulation frame 9, and are symmetrically placed relative to the heat insulation frame 9. The symmetrical arrangement of the second dual-loop heater 2 and the first dual-loop heater 1 encircling the heat insulation frame 9 forms a ring-shaped heating area on the injection disk 5. This symmetrical heating area improves the heating uniformity of the space engine's thermal control structure, reduces the actual thermal control power consumption of the space engine's thermal control structure, and improves resource utilization. For example, the semi-encircling form of the heater can adopt a rectangular concave structure or other heater structures that can provide a ring-shaped heating area; the specific structure of the heater is not limited here. The semi-encircling structure increases the area of ​​the heating region, making the entire injection disk 5 more evenly heated.

[0061] like Figure 4 As shown, specifically in this embodiment, both the primary heating circuit and the backup heating circuit include: a lead wire 11, a pin 12, and a socket 13. The lead wire 11 is used for the wiring connection between the primary heating circuit and the backup heating circuit; the pin 12 is soldered to the lead wire 11; the socket 13 is soldered to the lead wire 11, and the insertion and engagement of the socket 13 and the pin 12 are used for the connection between adjacent lead wires 11. The primary heating circuit and the backup heating circuit are electrically connected through the lead wire 11, pin 12, and socket 13, making the overall heating circuit structure compact, facilitating connection, installation, and disassembly, and improving the flexibility of the space engine thermal control structure installation.

[0062] like Figure 4 As shown, specifically in this embodiment, a sleeve 14 needs to be connected to the lead wire 11. The sleeve 14 can provide heat insulation and anti-wear for the lead wire 11, extending its service life. In some embodiments, the sleeve 14 on the main heating circuit and the sleeve 14 on the backup heating circuit are different colors to distinguish between the main heating circuit and the backup heating circuit, facilitating connection and installation and making them easy to identify.

[0063] Meanwhile, the present invention provides a space engine, including an engine body, an engine head, and a thermal control structure. The thermal control structure is any of the aforementioned space engine thermal control structures. The space engine thermal control structure improves the uniformity of thermal control temperature and saves thermal control power consumption.

[0064] Since the space engine adopts the space engine thermal control structure of this application, when the space engine needs to be on orbit for a long time, and the working duration is long and in a cryogenic working environment, the main heating circuit and the backup heating circuit on the space engine thermal control structure can be energized to implement zoned thermal control on the space engine and realize multi-zone balanced temperature control of the space engine.

[0065] In the description of the above embodiments, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0066] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A thermal control structure for a space engine, characterized in that, It includes a first dual-circuit heater, a second dual-circuit heater, a first single-circuit heater, and a second single-circuit heater; The first dual-circuit heater and the second dual-circuit heater are both located on the side of the injection plate near the flange and are arranged opposite each other. The first dual-circuit heater is provided with a first heating wire and a second heating wire, and the second dual-circuit heater is provided with a third heating wire and a fourth heating wire. Both the first single-loop heater and the second single-loop heater are mounted on the flange and are in close contact with the outer wall of the oxidant control valve; The first single-loop heater is connected in series with the first heating wire to form a first series branch, and the first series branch is connected in parallel with the third heating wire to form a main heating circuit; The second single-loop heater is connected in series with the fourth heating wire to form a second series branch, and the second series branch is connected in parallel with the second heating wire to form a backup heating circuit; or the second single-loop heater is connected in series with the second heating wire to form a second series branch, and the second series branch is connected in parallel with the fourth heating wire to form a backup heating circuit.

2. The space engine thermal control structure according to claim 1, characterized in that, The first dual-loop heater includes: A first housing is attached to the injection plate. The first heating wire and the second heating wire are both disposed inside the first housing, and the first heating wire and the second heating wire are surrounded by a thermally conductive material. The first main circuit port is disposed on the first housing. The first main circuit port is connected to the first heating wire circuit. The first heating wire is connected in series with the first single circuit heater through the first main circuit port to form the first series branch. The first backup circuit port is located on the first housing and is connected to the second heating wire circuit. The second heating wire is connected in series with the second single-circuit heater through the first backup circuit port to form the second series branch.

3. The space engine thermal control structure according to claim 2, characterized in that, The first housing is fixed to the injection disc by a first fastening component, or the first housing is bonded to the injection disc, or the first housing is welded to the injection disc.

4. The space engine thermal control structure according to claim 1, characterized in that, The second dual-loop heater includes: The second housing is in close contact with the injection plate. The third heating wire and the fourth heating wire are both disposed inside the second housing, and the third heating wire and the fourth heating wire are surrounded by thermally conductive material. The second main circuit port is disposed on the second housing and is connected to the third heating wire circuit. The third heating wire is connected in parallel with the first series branch through the second main circuit port. The second backup circuit port is located on the second housing and is connected to the fourth heating wire circuit. The fourth heating wire is connected in parallel with the second series branch through the second backup circuit port.

5. The space engine thermal control structure according to claim 4, characterized in that, The second housing is fixed to the injection disc by a second fastening component, or the second housing is bonded to the injection disc, or the second housing is welded to the injection disc.

6. The space engine thermal control structure according to claim 1, characterized in that, It also includes a temperature sensing component, with one or more of the temperature sensing components disposed between the first dual-circuit heater and the second dual-circuit heater, for monitoring the temperature of the first dual-circuit heater and the second dual-circuit heater.

7. The space engine thermal control structure according to claim 6, characterized in that, The temperature sensing component is a thermistor or a thermocouple.

8. The space engine thermal control structure according to claim 1, characterized in that, The second dual-circuit heater and the first dual-circuit heater are both semi-encircled by the heat insulation frame, and the second dual-circuit heater and the first dual-circuit heater are symmetrically placed with respect to the heat insulation frame.

9. The space engine thermal control structure according to claim 1, characterized in that, Both the primary heating circuit and the backup heating circuit include: leads, pins, and sockets; The circuits of the primary heating circuit and the backup heating circuit are connected by the lead wires. The pin is soldered to the lead wire; The socket is soldered to the lead wire, and the socket engages with the pin for connection between adjacent leads.

10. A space engine, comprising an engine body, an engine head, and a thermal control structure, characterized in that, The thermal control structure is the space engine thermal control structure as described in any one of claims 1-9.

Images