Escape main engine

Abstract

The present invention relates to a main escape engine, which includes an engine body and a connecting mechanism, an ignition device and a plurality of nozzles arranged on the engine body; wherein the engine body includes an outer shell, a temperature control liner and a fuel chamber from the outside to the inside, and the temperature control liner is suitable for heating and / or keeping warm / or cooling the fuel chamber. The structure is simple, and the temperature of the engine is controlled by the temperature control liner integrated with the engine, which saves the cost and resource consumption caused by setting a temperature control device on the outside to control the temperature of the engine, is easy to implement, and has a fast temperature control response and a wide range, thereby realizing efficient and stable control of the engine temperature at a low cost.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an escape main engine. Background Art

[0002] With the continuous development of the aerospace industry, cost-oriented integrated design has become an important trend in the development of spacecraft. In order to reduce the construction and maintenance costs of ground facilities during the launch of manned spacecraft, both domestic and foreign countries use the front-end non-fairing escape tower and the outer wall of the spacecraft assembly to replace the original additional fairing part to achieve aerodynamic fairing capability. At present, the technical route with fairing is adopted. During launch, the closed room and air conditioning on the launch tower are needed to control the temperature within a certain range to ensure the engine thrust performance. However, with the development of aerospace technology, the technical difficulty and cost of achieving closed room temperature control on a higher and larger platform of the launch tower are greater, and the non-fairing escape tower and spacecraft assembly cannot achieve full coverage of the internal ventilation temperature control of the escape main engine. Therefore, the use of low-cost, high-reliability, long-term self-controlled temperature escape main engine in future models of manned spacecraft is an important development direction to reduce system complexity and reduce costs.

[0003] In order to start and respond quickly, the escape tower generally uses a solid rocket engine as the escape main engine to achieve the dynamic main thrust, so that the return capsule can quickly escape from the rocket explosion source. For the escape main engine, on the one hand, the need for a fast escape distance from the rocket determines that it needs a large thrust. On the other hand, the escape main engine thrust needs to be as small as possible to reduce the weight of the escape tower return capsule connection structure. In addition, the escape main engine thrust deviation needs to be controlled within a small deviation range as much as possible to achieve precise control. However, the thrust of solid rocket engines is extremely sensitive to the fuel temperature during launch, which is mainly reflected in the following aspects: if the temperature of the escape main engine fuel is too high during launch (taking the annual ambient temperature of Hainan launch site as an example, it can reach 39.1℃), when the escape main engine needs to be started, there may be risks such as failure of escape tower attitude adjustment due to excessive thrust or even breaking of structural parts; if the temperature of the escape main engine fuel is too low during launch (taking the annual ambient temperature of Hainan launch site as an example, it can reach 4.2℃), when the escape main engine needs to be started, it may be unable to leave the explosion range of the rocket within the specified time due to insufficient thrust of the escape tower; if the actual thrust value of the escape main engine deviates too much from the design state, the inaccurate thrust model used as the control input will lead to inaccurate control, and in severe cases, control failure. Therefore, ensuring the temperature of the escape main engine during the standby period plays a decisive role in ensuring the thrust performance of the escape main engine, and therefore it is crucial for the escape tower to meet the design indicators. In the process of escape tower design, it is necessary to focus on analyzing and verifying the engine's ability to control temperature for a long time.

[0004] At present, the launch tower of the CZ-2F escape main engine used by my country's Shenzhou series spacecraft has an enclosed room that encloses the escape tower as a whole. The enclosed room can be air-conditioned to ensure the temperature. If extreme environmental conditions are encountered during the launch mission, the escape tower will be covered with insulation clothing to further control the escape engine fuel temperature. The insulation clothing is connected to the air supply duct. Such a complex and large-scale insulation implementation technology that requires manual operation is no longer suitable for the integrated, low-cost, and intelligent technical requirements of the new generation of manned spacecraft in the manned space field.

[0005] Ensuring that the fuel temperature of the escape main engine is within a certain range can greatly reduce the engine deviation. In tactical missiles, the temperature control of the solid engine is often achieved by using thermal insulation air conditioning in the launch tube. However, in the escape tower in the manned field, with the manufacture of larger rockets in the future, it will become increasingly difficult to achieve closed room and air conditioning temperature control at the top of the launch tower; even if it can be achieved, the cost will far exceed the benefits it brings. Summary of the invention

[0006] In view of this, the present invention aims to propose an escape main engine to solve the above-mentioned problem.

[0007] An embodiment of the present invention provides a main escape engine, which includes an engine body and a connecting mechanism, an ignition device and a plurality of nozzles arranged on the engine body; wherein the engine body includes an outer shell, a temperature control liner and a fuel chamber from the outside to the inside, and the temperature control liner is suitable for heating and / or keeping the fuel chamber warm and / or cooling the fuel chamber.

[0008] Preferably, the temperature control liner includes a foam insulation layer and a carbon fiber layer from the outside to the inside.

[0009] Preferably, the temperature control liner includes a fluid pipeline layer and a steel liner from the outside to the inside.

[0010] Preferably, the temperature control liner includes a fluid pipeline layer, a carbon fiber layer and an aluminum alloy liner from the outside to the inside.

[0011] Preferably, the temperature control inner liner comprises a carbon fiber layer and an aluminum alloy inner liner from the outside to the inside, and at least one electric heating plate is provided between the carbon fiber layer and the aluminum alloy inner liner.

[0012] Preferably, the temperature control inner liner includes a carbon fiber layer, a first layer of aluminum alloy inner liner and a second layer of aluminum alloy inner liner from the outside to the inside, and at least one electric heating plate is provided between the first layer of aluminum alloy inner liner and the second layer of aluminum alloy inner liner.

[0013] Preferably, a foam insulation layer is provided between the fluid pipeline layer and the outer shell.

[0014] Preferably, a foam insulation layer is provided between the carbon fiber layer and the outer shell.

[0015] Preferably, at least one penetration hole is provided between the carbon fiber layer and the outer shell, and the circuit of the electric heating plate is led out through the penetration hole and connected to a power source.

[0016] Preferably, the engine body is further provided with a safety mechanism, which is suitable for cutting off or connecting the connection between the ignition device and the fuel chamber.

[0017] The escape main engine in the embodiment of the present invention has a simple structure, and the temperature of the engine is controlled by a temperature control liner integrated with the engine, thereby eliminating the cost and resource consumption caused by setting an external temperature control device to control the temperature of the engine. In addition, the temperature control response is fast and the range is wide, thereby achieving efficient and stable control of the engine temperature at a low cost. It can solve the problem of excessive initial fuel temperature under a wide range of ambient temperature launch conditions (the temperature difference band can be narrowed to ±5°C), and can balance the problem of the temperature difference band and the required resources (such as the power required for heating and the additional mass of the phase change material), and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 It is a structural schematic diagram of the escape main engine according to an embodiment of the present invention;

[0020] Figure 2 This is a schematic structural diagram of a temperature control liner according to a first embodiment of the present invention;

[0021] Figure 3 It is a schematic structural diagram of a temperature control inner container according to a second embodiment of the present invention;

[0022] Figure 4 It is a schematic structural diagram of a temperature control inner container according to a third embodiment of the present invention;

[0023] Figure 5 It is a schematic structural diagram of a temperature control inner container according to a fourth embodiment of the present invention;

[0024] Figure 6 This is a schematic structural diagram of a temperature control liner according to a fifth embodiment of the present invention;

[0025] Figure 7 This is a schematic structural diagram of a temperature control liner according to a sixth embodiment of the present invention;

[0026] Figure 8 This is a schematic structural diagram of a temperature control liner according to a seventh embodiment of the present invention;

[0027] Fig. 9 This is a schematic structural diagram of a temperature control liner according to an eighth embodiment of the present invention;

[0028] Fig.10 It is a schematic structural diagram of a temperature control inner container according to a ninth embodiment of the present invention;

[0029] Fig.11 Schematic diagram of the arrangement of the electric heating plate according to an embodiment of the present invention. DETAILED DESCRIPTION

[0030] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0031] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0032] like Figure 1 As shown, it is a structural schematic diagram of the escape main engine of an embodiment of the present invention. The escape main engine includes an engine body 1 and a connecting mechanism 2, an ignition device 3 and a plurality of nozzles 4 arranged on the engine body 1. Among them, the engine body 1 includes an outer shell 5, a temperature control liner 6 and a fuel chamber 7 from the outside to the inside, and the temperature control liner 6 is used to heat and / or keep warm / or cool the fuel chamber 7. Among them, the connecting structure 2 is used to connect the escape main engine to the aircraft, which may include conventional parts such as bolts, and the nozzle 4 is detonated by the fuel in the fuel chamber 7 to provide thrust for the escape main engine. The temperature control of the engine is achieved by the temperature control liner 6 that is integrated with the engine, which eliminates the cost and resource consumption caused by the temperature control of the engine by setting a temperature control device externally (for example, by an air conditioning device set on the launch tower of the aircraft), is easy to implement, and the temperature control response is fast and the range is wide, so that the engine temperature is efficiently and stably controlled at low cost.

[0033] like Figure 1As shown, in this embodiment, the escape main engine also includes a safety mechanism 8 arranged on the engine body 1. The safety mechanism 8 can be arranged next to the ignition device 3, and is used to cut off or connect the connection between the ignition device 3 and the fuel chamber 7. For example, in storage, transportation, standby, etc., when the escape main engine does not need to work, the safety mechanism 8 should be locked to prevent the engine from working due to false triggering; when the escape main engine is required to be in an enabled state, the safety mechanism 8 is unlocked, and the engine completes the predetermined function after receiving the working signal. An insulating layer 9 is also provided between the temperature control liner 6 and the fuel chamber 7. Fuel is provided in the fuel chamber 7. The insulating layer 9 is used to isolate the heat generated by the combustion of the fuel and prevent the fuel from burning to the engine casing 5 at the end of the combustion. Optionally, conventional HTPB-based fuel is selected as the fuel, and the insulating layer 9 uses a nitrile insulating layer with good bonding performance with the temperature control liner 6.

[0034] Optionally, the escape main engine of this embodiment adopts the form of a solid rocket engine to increase the initial thrust, so that the escape main engine can quickly carry the spacecraft to escape.

[0035] Optionally, the ignition device 3 is used to ignite the solid rocket engine. If the engine is loaded with a small amount of fuel, the ignition device 3 is used to directly detonate the fuel; if the engine is loaded with a large amount of fuel, the ignition device 3 first detonates the internal small rocket, and the small rocket further detonates the fuel to prevent the ignition device 3 from being insufficient in ignition charge and failing to ignite all the fuel in time.

[0036] Optionally, the ignition device 3 is a remote ignition device, and the ignition adopts an electric explosion transmission system or a non-electric explosion transmission system.

[0037] Optionally, the present embodiment includes four nozzles 4, and the four nozzles 4 are arranged at equal intervals (ie, 90°) along the circumference of the engine body 1 to provide uniform thrust. Figure 1 Only two nozzles 4 are shown for illustration and are not intended to limit the present invention. In actual situations, the number of nozzles 4 (at least two), the arrangement of nozzles 4 (equal intervals or non-equal intervals), and the angle between nozzles 4 and engine body 1 (for adjusting the emission direction and angle) and other parameters can be adjusted according to needs, and will not be described in detail in this embodiment.

[0038] The outer shell 5 of the engine body 1 is used to withstand aerodynamic pressure, and can be made of metal materials, preferably an aluminum outer wall, and the outer coating is heat-resistant paint to achieve the purpose of reducing weight. The thickness of the aluminum outer wall can be designed according to the aerodynamic force to be borne under the worst working conditions (for example, at the maximum dynamic pressure point), and the thickness of the heat-resistant paint and the uniformity of different positions can be designed according to the maximum heat flux density.

[0039] The escape main engine in the embodiment of the present invention has a simple structure, and the temperature of the engine is controlled by a temperature control liner integrated with the engine, thereby eliminating the cost and resource consumption caused by setting an external temperature control device to control the temperature of the engine. In addition, the temperature control response is fast and the range is wide, thereby achieving efficient and stable control of the engine temperature at a low cost. It can solve the problem of excessive initial fuel temperature under a wide range of ambient temperature launch conditions (the temperature difference band can be narrowed to ±5°C), and can balance the problem of the temperature difference band and the required resources (such as the power required for heating and the additional mass of the phase change material), and has broad application prospects.

[0040] The following nine embodiments are used to specifically illustrate the escape main engine of the present invention, and the temperature control liner 6 of each embodiment has a different structure.

[0041] First embodiment

[0042] like Figure 2 , which is a schematic diagram of the structure of the temperature control liner of the escape main engine of the first embodiment of the present invention. The temperature control liner 6 includes a foam insulation layer and a carbon fiber layer from the outside to the inside. The foam insulation layer is used to achieve temperature protection, and the carbon fiber layer has good mechanical properties, which can not only support the pressure generated by fuel combustion, but also produce a good insulation effect.

[0043] This embodiment uses foaming materials to achieve heat preservation. The advantage is that no additional heating system is required, the layout is simple and easy to implement. The disadvantage is that heat preservation can only be achieved within a certain temperature range, the target temperature has a large deviation, it is greatly affected by the target temperature and the ambient temperature, and there is no active temperature control adjustment capability. It is suitable for use in situations where precise temperature control is not required and only the self-circulation temperature range of the engine temperature under ambient temperature changes needs to be reduced to a certain extent.

[0044] Second embodiment

[0045] like Figure 3 , which is a schematic diagram of the structure of the temperature control liner of the escape main engine of the second embodiment of the present invention. The temperature control liner 6 includes a fluid pipeline layer and a steel liner from the outside to the inside. The fluid circuit is in the form of a fluid pipeline, through which a high-temperature liquid can circulate to achieve engine heating, or a low-temperature liquid can circulate to achieve engine cooling. While the steel liner bears the pressure of the combustion chamber 7, it has good heat conduction performance, which can better transfer the heat in the fluid circuit to the fuel in the fuel chamber 7.

[0046] This embodiment can realize engine self-temperature control based on the setting of fluid circuit. The advantage is fast response speed and no extra weight caused by foaming material. The disadvantage is high heat exchange efficiency with the outside world and high energy consumption. It is suitable for use when precise temperature control is required but the weight cost of the system and the energy consumption level do not need to be considered.

[0047] Third embodiment

[0048] like Figure 4 Shown is a schematic diagram of the structure of the temperature control liner of the escape main engine of the third embodiment of the present invention. The temperature control liner 6 includes a fluid pipeline layer, a carbon fiber layer and an aluminum alloy liner from the outside to the inside. The setting and function of the fluid circuit layer are consistent with the second embodiment and will not be repeated here. Compared with the second embodiment, the carbon fiber layer + aluminum alloy liner is used instead of the steel liner, which can effectively reduce the weight. The carbon fiber layer serves as the outer layer that bears the pressure, and the aluminum alloy liner is used for the reactor for fuel solidification and for sealing. However, the carbon fiber layer uses a fiber composite material with poor thermal conductivity, and requires a higher power heating energy source to heat it, and the heating reaction is delayed, and it cannot quickly reach the specified temperature under emergency heating conditions.

[0049] In the second and third embodiments, the fluid pipeline layer is fixedly connected to the steel liner or the aluminum alloy liner by welding. If welding is not possible, the fluid pipeline should be thermally assembled to ensure that the fluid pipeline is tightly pressed against the steel liner or the aluminum alloy liner after cooling, and thermal grease should be applied near the contact area to enhance the heat exchange capacity.

[0050] Fourth embodiment

[0051] like Figure 5 As shown, it is a schematic diagram of the structure of the temperature control liner of the escape main engine of the fourth embodiment of the present invention. The temperature control liner 6 includes a carbon fiber layer and an aluminum alloy liner from the outside to the inside, and at least one electric heating plate is provided between the carbon fiber layer and the aluminum alloy liner. Among them, the aluminum alloy liner serves as a reaction kettle for the solidification of the fuel in the fuel chamber 7, and has a sealing function. It is a non-pressure-bearing component (the minimum can reach 2mm), and occupies a small space and weight. The electric heating plate is attached to the outer surface of the aluminum alloy liner and is connected to an external power source through a heating cable (not shown). The carbon fiber layer is wrapped around the aluminum alloy liner and the electric heating plate. Compared with the traditional metal combustion chamber shell, the carbon fiber layer made of composite material can reduce weight.

[0052] Optionally, an insulating coating may be provided on the inner side of the aluminum alloy liner to prevent accidental ignition of the fuel due to electrical heating.

[0053] Optionally, during processing, the temperature control liner 6 is processed first, processed and assembled from the outside to the inside, and the fuel is filled after the nitrile insulation layer 9 is coated.

[0054] Optionally, the first step in the processing is to paste the electric heating sheet on the outside of the aluminum alloy liner, and silicone rubber can be used as the pasting material. For example, before pasting the electric heating sheet, the silicone rubber material is first applied to the outer wall of the aluminum alloy liner, and the thickness of the silicone rubber coating should be not less than 0.5 mm. The electric heating sheet can be isolated from the insulation layer 9 by the insulating silicone rubber coating.

[0055] Optionally, after the above-mentioned pasting of the electric heating sheet is completed, a layer of silicone rubber is brushed on the outer side thereof for protection.

[0056] In this embodiment, after the electric heating plate is installed in place, carbon fiber material is used to wrap around the outside to form a carbon fiber layer. The carbon fiber material has good mechanical properties and can support the pressure generated by fuel combustion. Due to its winding method, the contact area is small and has good insulation performance.

[0057] It should be noted that in order to reach the target temperature faster, a higher electric heating plate temperature is required. However, excessively high local heating temperature may cause the engine insulation layer or fuel column to debond, thereby affecting the engine safety and reliability. In addition, the temperature control liner 6 itself must meet the pressure generated inside the engine combustion chamber 7 when supporting the combustion of gunpowder and the pressure of the escape tower's own gravity on the outer shell during ground operation in a lying posture.

[0058] This embodiment can realize engine self-temperature control based on the setting of electric heating plate. The advantage is fast response speed and no extra weight caused by foaming material. The disadvantage is high heat exchange efficiency with the outside world and high energy consumption. It is suitable for use when precise temperature control is required but the weight cost of the system and the energy consumption level do not need to be considered.

[0059] Fifth embodiment

[0060] like Figure 6 The figure shows a schematic diagram of the structure of the temperature control liner of the escape main engine of the fifth embodiment of the present invention. The temperature control liner 6 includes a carbon fiber layer, a first aluminum alloy liner and a second aluminum alloy liner from the outside to the inside, and at least one electric heating plate is provided between the first aluminum alloy liner and the second aluminum alloy liner. Compared with the fourth embodiment, a double-layer aluminum alloy liner is used instead of a single-layer aluminum alloy liner, which can avoid damaging the electric heating plate and the electric heating plate cable when the carbon fiber layer is wound, thereby ensuring the installation reliability and the thermal performance reliability of the structure.

[0061] Sixth embodiment

[0062] like Figure 7 , which is a schematic diagram of the structure of the temperature control liner of the escape main engine of the sixth embodiment of the present invention. This embodiment is a structural diagram of the temperature control liner of the escape main engine of the sixth embodiment of the present invention. Figure 3 ), a foam insulation layer is provided between the fluid pipeline layer and the shell 5. Compared with the second embodiment, the foam insulation layer is provided to provide insulation means for the engine. The advantage is that the temperature can be precisely controlled and the energy consumption can be reduced by taking advantage of the low heat exchange efficiency with the external environment. The disadvantage is that the setting of the foam insulation layer increases the weight. When it is suitable to comprehensively balance the temperature control accuracy and the extra cost paid, this embodiment can be adopted to reduce the energy consumption caused by continuous temperature control.

[0063] Seventh embodiment

[0064] like Figure 8 FIG. 1 is a schematic diagram of the structure of the temperature control liner of the escape main engine of the seventh embodiment of the present invention. This embodiment is a structural diagram of the temperature control liner of the escape main engine of the seventh embodiment of the present invention. Figure 4 ), a foam insulation layer is provided between the fluid pipeline layer and the shell 5. Compared with the third embodiment, the foam insulation layer is provided to provide insulation means for the engine. The advantage is that the temperature can be precisely controlled and the energy consumption can be reduced by taking advantage of the low heat exchange efficiency with the external environment. The disadvantage is that the setting of the foam insulation layer increases the weight. When it is suitable to comprehensively balance the temperature control accuracy and the extra cost paid, this embodiment can be adopted to reduce the energy consumption caused by continuous temperature control.

[0065] Eighth embodiment

[0066] like Fig. 9 FIG. 1 is a schematic diagram of the structure of the temperature control liner of the escape main engine of the eighth embodiment of the present invention. This embodiment is based on the fourth embodiment ( Figure 5 ), a foam insulation layer is provided between the carbon fiber layer and the outer shell 5. Compared with the fourth embodiment, the addition of a foam insulation layer provides insulation means for the engine. The advantage is that it can achieve precise temperature control and reduce energy consumption by taking advantage of the low heat exchange efficiency with the external environment. The disadvantage is that the provision of the foam insulation layer increases weight and cannot achieve cooling treatment. It can only be heated by an electric heating plate. Therefore, it is more suitable for launch conditions corresponding to a temperature control point that is higher than the ambient temperature. When it is suitable for comprehensively balancing the temperature control accuracy and the extra cost paid, this embodiment can be adopted to reduce the energy consumption caused by continuous temperature control.

[0067] Ninth embodiment

[0068] like Fig.10 , which is a schematic diagram of the structure of the temperature control liner of the escape main engine of the ninth embodiment of the present invention. This embodiment is based on the fifth embodiment ( Figure 6 ), a foam insulation layer is provided between the carbon fiber layer and the shell 5. Compared with the fifth embodiment, the foam insulation layer is provided to provide insulation means for the engine. The advantage is that the temperature can be precisely controlled and the energy consumption can be reduced by taking advantage of the low heat exchange efficiency with the external environment. The disadvantage is that the setting of the foam insulation layer increases the weight and cannot achieve cooling treatment. It can only be heated by an electric heating plate. When it is suitable for comprehensively balancing the temperature control accuracy and the extra cost paid, this embodiment can be adopted to reduce the energy consumption caused by continuous temperature control.

[0069] In the sixth embodiment, the seventh embodiment, the eighth embodiment and the ninth embodiment, after the carbon fiber material is wound, it is necessary to use customized tooling to fix the prepared carbon fiber layer and the pneumatic outer wall to ensure that their relative positions are in the final state, and then pour the foaming material into the slit between the carbon fiber layer and the pneumatic outer wall. Preferably, the foaming material is made of polyurethane, which can be automatically formed and has certain mechanical properties. The loose and porous structure produced during the foaming process is also conducive to heat preservation. Specifically, after the foaming material is foamed and formed, it is determined that the thermal insulation liner manufacturing process is completely completed. The above-mentioned foaming material can be shaped in advance and attached to the carbon fiber layer, or it can be filled and cured after the pneumatic outer wall is manufactured externally. The process steps can be selected according to actual conditions.

[0070] In the second, third, sixth and seventh embodiments, the fluid circuit is led out to an external fluid input device via a pipeline (not shown), and a fluid input device with a temperature controller can be used to circulate the fluid into the fluid circuit through the fluid pipeline to form the temperature control capability of the fluid circuit. The pipeline wiring of the fluid circuit and the fluid input device are not described in detail in this embodiment.

[0071] In the fourth embodiment, the fifth embodiment, the eighth embodiment and the ninth embodiment, at least one through-hole (not shown) is provided between the carbon fiber layer and the shell 5, and the power supply line of the electric heating plate is led out through the through-hole and connected to the external power supply. If the escape main engine needs to be continuously temperature-controlled during flight, the source of the external power supply is the energy of the spacecraft itself. Preferably, if the escape main engine does not need to be continuously heat-insulated during flight, the source of the external power supply is a ground facility, for example, it can be supplied by a ground launch site through an electrical connector. In addition, a disposable thermal battery can also be used to connect the electrical energy source to the electric heating plate through an insulated cable.

[0072] like Fig.11 The figure shows the arrangement schematic diagram of the electric heating plates of the fourth embodiment, the fifth embodiment, the eighth embodiment and the ninth embodiment of the present invention. The number of electric heating plates is at least two, and the electric heating plates can be arranged horizontally, vertically or horizontally and vertically. The spacing between the electric heating plates can be equal or unequal (i.e., uniform or uneven arrangement). Preferably, the electric power of the electric heating plate should not be too large to avoid damage due to excessive temperature during operation. 0.5W / m 2 The number of electric heating plates should be such that the total power meets the actual working requirements, and it is preferred that multiple heating plates are arranged evenly and at equal intervals.

[0073] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A main escape engine, characterized in that: The escape main engine comprises an engine body (1), a connecting mechanism (2), an ignition device (3) and a plurality of nozzles (4) arranged on the engine body (1); The engine body (1) comprises, from the outside to the inside, an outer shell (5), a temperature control inner shell (6) and a fuel chamber (7), wherein the temperature control inner shell (6) heats and / or keeps the fuel chamber (7) warm and / or cools the fuel chamber (7); The temperature control liner (6) comprises, from the outside to the inside, a fluid pipeline layer and a steel liner; A foam insulation layer is provided between the fluid pipeline layer and the outer shell (5); The engine body (1) is also provided with a safety mechanism (8), and the safety mechanism (8) cuts off or connects the connection between the ignition device (3) and the fuel chamber (7); A heat insulating layer (9) is also provided between the temperature control inner container (6) and the fuel chamber (7).

2. A main escape engine, characterized in that: The escape main engine comprises an engine body (1), a connecting mechanism (2), an ignition device (3) and a plurality of nozzles (4) arranged on the engine body (1); The engine body (1) comprises, from the outside to the inside, an outer shell (5), a temperature control inner shell (6) and a fuel chamber (7), wherein the temperature control inner shell (6) heats and / or keeps the fuel chamber (7) warm and / or cools the fuel chamber (7); The temperature control liner (6) comprises, from the outside to the inside, a fluid pipeline layer, a carbon fiber layer and an aluminum alloy liner; A foam insulation layer is provided between the fluid pipeline layer and the outer shell (5); The engine body (1) is also provided with a safety mechanism (8), and the safety mechanism (8) cuts off or connects the connection between the ignition device (3) and the fuel chamber (7); A heat insulating layer (9) is also provided between the temperature control inner container (6) and the fuel chamber (7).

3. A main escape engine, characterized in that: The escape main engine comprises an engine body (1), a connecting mechanism (2), an ignition device (3) and a plurality of nozzles (4) arranged on the engine body (1); The engine body (1) comprises, from the outside to the inside, an outer shell (5), a temperature control inner shell (6) and a fuel chamber (7), wherein the temperature control inner shell (6) heats and / or keeps the fuel chamber (7) warm and / or cools the fuel chamber (7); The temperature control inner liner (6) comprises, from the outside to the inside, a carbon fiber layer and an aluminum alloy inner liner, and at least one electric heating plate is provided between the carbon fiber layer and the aluminum alloy inner liner; A foam insulation layer is provided between the carbon fiber layer and the outer shell (5); At least one penetration hole is provided between the carbon fiber layer and the outer shell (5), and the circuit of the electric heating plate is led out through the penetration hole and connected to a power source; The engine body (1) is also provided with a safety mechanism (8), and the safety mechanism (8) cuts off or connects the connection between the ignition device (3) and the fuel chamber (7); A heat insulating layer (9) is also provided between the temperature control inner container (6) and the fuel chamber (7).

4. A main escape engine, characterized in that: The escape main engine comprises an engine body (1), a connecting mechanism (2), an ignition device (3) and a plurality of nozzles (4) arranged on the engine body (1); The engine body (1) comprises, from the outside to the inside, an outer shell (5), a temperature control inner shell (6) and a fuel chamber (7), wherein the temperature control inner shell (6) heats and / or keeps the fuel chamber (7) warm and / or cools the fuel chamber (7); The temperature control inner liner (6) comprises, from the outside to the inside, a carbon fiber layer, a first layer of aluminum alloy inner liner, and a second layer of aluminum alloy inner liner, wherein at least one electric heating plate is provided between the first layer of aluminum alloy inner liner and the second layer of aluminum alloy inner liner; A foam insulation layer is provided between the carbon fiber layer and the outer shell (5); At least one penetration hole is provided between the carbon fiber layer and the outer shell (5), and the circuit of the electric heating plate is led out through the penetration hole and connected to a power source; The engine body (1) is also provided with a safety mechanism (8), and the safety mechanism (8) cuts off or connects the connection between the ignition device (3) and the fuel chamber (7); A heat insulating layer (9) is also provided between the temperature control inner container (6) and the fuel chamber (7).

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