Engine mounting assembly and space propeller

Abstract

The embodiment of the utility model relates to the technical field of space propulsion, and discloses an engine mounting assembly and a space propeller. The engine installation assembly comprises an installation support and a plurality of switch valves. The mounting bracket comprises a plurality of mounting plates, each mounting plate is provided with an outlet, a switch hole is formed in the position, close to each outlet, of the mounting bracket, the switch hole is communicated with an inlet, a plurality of sections of circulating hole channels are formed between the inlet and the outlets, and fluid flows in through the inlets, flows to the switch holes through the circulating hole channels and then flows out through the corresponding outlets; the plurality of switch valves are arranged in the corresponding switch holes one by one to control connection or disconnection between the switch holes and the outlet; and the plurality of mounting plates are staggered on different planes and are used for mounting the engine in different directions. According to the engine mounting assembly and the space propeller, the size of a space propelling system can be reduced, and the requirement for multi-direction propelling is met.

Description

Technical Field

[0001] The present application relates to the field of space propulsion technology, and in particular to an engine mounting assembly and a space thruster. Background Art

[0002] As human beings continue to explore space, the demand for propulsion systems is also growing. As a practical propulsion system, space propulsion technology has received extensive attention and research internationally. Especially in the field of commercial aerospace, such as satellite orbit transfer, space attitude adjustment, and rocket precision orbit entry, space propulsion technology has great application prospects. Commercial aerospace is based on communications, navigation, and remote sensing, and is based on the principles of "agility, speed, low price, reliability, platform sharing, and extreme focus". This requires commercial aerospace to use small satellite propulsion systems with low cost, light weight, small size, short cycle, and high performance (the generalized small satellite weight is less than 500kg). As small satellites gradually carry part of the tasks of the original large satellites, the requirements for propulsion systems are also constantly increasing. For example, some tasks require high specific impulse and long life, and can provide precise micro-thrust and precise and adjustable thrust.

[0003] High-pressure cold gas propulsion is a space propulsion technology that can achieve extremely fast thrust response, but long-term storage of high-pressure gas may cause leakage risks, and the specific impulse and storage density are not high. Although increasing the pressure can increase the storage density, after the pressure rises to a certain level, the gas no longer satisfies the ideal gas state equation. Continuing to increase the pressure will cause the pressure to rise sharply while the inflation mass increment is small. In fuel propulsion technology, the propellant is stored in liquid form and ejected in gaseous form after being ignited by the engine, which increases the storage density, eliminates the storage risk of high-pressure gas, and also improves the engine specific impulse.

[0004] In existing fuel propulsion systems, single-propellant engines are mostly arranged side by side with large spacing between the engines. The propulsion direction is single and the space occupied is also large. Utility Model Content

[0005] The purpose of the embodiments of the present application is to provide an engine mounting assembly and a space thruster that can reduce the volume of the space propulsion system and meet the needs of multi-directional propulsion.

[0006] In order to solve the above technical problems, the embodiment of the present application provides an engine mounting assembly, which includes a mounting bracket and a plurality of switch valves. The mounting bracket includes a plurality of mounting plates, each of which is provided with an outlet, and a switch hole is provided near each outlet on the mounting bracket, and the switch hole is connected to an inlet, and a plurality of flow channels are provided between the inlet and the plurality of outlets, and the fluid flows in through the inlet, flows through the flow channels to the switch hole, and then flows out from the corresponding outlet; the plurality of switch valves are arranged one by one in the corresponding switch holes to control the connection or disconnection between the switch hole and the outlet; the plurality of mounting plates are staggered on different planes to install the engine in different directions.

[0007] In addition, an embodiment of the present application further provides a space thruster, which includes the above-mentioned engine mounting assembly, multiple mounting plates are connected to the engine, and the inlet is connected to the storage box.

[0008] The engine mounting assembly and space thruster provided by the embodiments of the present application stagger multiple mounting plates for mounting engines in space, so that the engines are staggered in different directions in space, providing power in different directions for the propulsion of the spacecraft. The volume of the space propulsion system can be reduced to meet the needs of multi-directional propulsion.

[0009] In some embodiments, there are three mounting plates, and the three mounting plates are perpendicular to each other in space.

[0010] In some embodiments, the mounting bracket further includes a main bracket, which is located between two mounting plates. The main bracket is provided with a joint hole for fixing the main bracket on the cabin section.

[0011] In some embodiments, there are two inlets, which are respectively disposed at two ends of the main support.

[0012] In some embodiments, auxiliary brackets are respectively disposed on one side of both ends of the main bracket facing away from the inlet, and both auxiliary brackets are connected to another mounting plate.

[0013] In some embodiments, both auxiliary stents are hollow tubular structures, and flow channels are formed inside both auxiliary stents.

[0014] In some embodiments, a through hole is provided in the middle of the main support.

[0015] In some embodiments, a support rod is disposed between a middle position of the through hole and another mounting plate.

[0016] In some embodiments, the mounting bracket has an integrally formed structure, and the flow channel is disposed inside the mounting bracket. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] One or more embodiments are exemplarily described by pictures in the corresponding drawings, and these exemplified descriptions do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings represent similar elements, and unless otherwise stated, the figures in the drawings do not constitute proportional limitations.

[0018] Figure 1 is a schematic diagram of the three-dimensional structure of an engine mounting assembly provided in some embodiments of the present application when the engine is mounted;

[0019] Figure 2 is a schematic diagram of a three-dimensional structure of a mounting bracket in an engine mounting assembly provided in some embodiments of the present application;

[0020] Figure 3 The engine mounting assembly provided by some embodiments of the present application is relative to Figure 2 Schematic diagram of the three-dimensional structure of the mounting bracket on the back;

[0021] Figure 4 The engine mounting assembly provided by some embodiments of the present application Figure 1 Schematic diagram of the cross-sectional structure along the entrance perpendicular to the main support direction.

[0022] Explanation of the reference numerals: 11-mounting bracket; 111-mounting plate; 112-outlet; 113-switch hole; 114-inlet; 115-circulation channel; 116-main bracket; 1161-connector hole; 1162-through hole; 117-auxiliary bracket; 118-support rod; 12-switch valve; 13-engine. DETAILED DESCRIPTION

[0023] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, each embodiment of the present application will be described in detail below in conjunction with the accompanying drawings. However, it will be appreciated by those skilled in the art that in each embodiment of the present application, many technical details are proposed in order to enable the reader to better understand the present application. However, even without these technical details and various changes and modifications based on the following embodiments, the technical scheme claimed in the present application can also be implemented. The division of the following embodiments is for the convenience of description, and the specific implementation of the present application should not constitute any limitation, and the various embodiments can be combined with each other and referenced to each other without contradiction.

[0024] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0025] In the description of the embodiments of the present application, the technical terms "first", "second", etc. are only used to distinguish different objects, and cannot be understood as indicating or implying relative importance or implicitly indicating the number, specific order or primary and secondary relationship of the indicated technical features. In the description of the embodiments of the present application, the meaning of "multiple" is more than two, unless otherwise clearly and specifically defined.

[0026] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installed", "connected", "connected" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0027] As human beings continue to explore space, the demand for propulsion systems is also growing. As a practical propulsion system, space propulsion technology has received extensive attention and research internationally. Especially in the field of commercial aerospace, such as satellite orbit transfer, space attitude adjustment, and rocket precision orbit entry, space propulsion technology has great application prospects. Commercial aerospace is based on communications, navigation, and remote sensing, and is based on the principles of "agility, speed, low price, reliability, platform sharing, and extreme focus". This requires commercial aerospace to use small satellite propulsion systems with low cost, light weight, small size, short cycle, and high performance (the generalized small satellite weight is less than 500kg). As small satellites gradually carry part of the tasks of the original large satellites, the requirements for propulsion systems are also constantly increasing. For example, some tasks require high specific impulse and long life, and can provide precise micro-thrust and precise and adjustable thrust.

[0028] High-pressure cold gas propulsion is a space propulsion technology that can achieve extremely fast thrust response, but long-term storage of high-pressure gas may cause leakage risks, and the specific impulse and storage density are not high. Although increasing the pressure can increase the storage density, after the pressure rises to a certain level, the gas no longer satisfies the ideal gas state equation. Continuing to increase the pressure will cause the pressure to rise sharply while the inflation mass increment is small. In fuel propulsion technology, the propellant is stored in liquid form and ejected in gaseous form after being ignited by the engine, which increases the storage density, eliminates the storage risk of high-pressure gas, and also improves the engine specific impulse.

[0029] In existing fuel propulsion systems, single-propellant engines are mostly arranged side by side with large spacing between the engines. The propulsion direction is single and the space occupied is also large.

[0030] The engine mounting assembly provided in the embodiment of the present application staggers multiple mounting plates for mounting engines in space, so that the engines are staggered in different directions in space, providing power in different directions for the propulsion of the spacecraft, which can reduce the volume of the space propulsion system and meet the needs of multi-directional propulsion.

[0031] Combine the following Figure 1 , Figure 2 , Figure 3 as well as Figure 4 The engine 13 mounting assembly provided in some embodiments of the present application is described.

[0032] like Figure 1 As shown, the engine 13 mounting assembly provided by some embodiments of the present application includes a mounting bracket 11 and a plurality of switch valves 12. The mounting bracket 11 includes a plurality of mounting plates 111, each of which is provided with an outlet 112, and a switch hole 113 is provided near each outlet 112 on the mounting bracket 11, and the switch hole 113 is connected with an inlet 114, and a plurality of flow channels 115 are provided between the inlet 114 and the plurality of outlets 112, and the fluid flows in through the inlet 114, flows to the switch hole 113 through the flow channels 115, and then flows out from the corresponding outlet 112; the plurality of switch valves 12 are arranged one by one in the corresponding switch holes 113, and control the connection or disconnection between the switch hole 113 and the outlet 112; the plurality of mounting plates 111 are staggered with each other on different planes, and are used to mount the engine 13 in different directions.

[0033] It should be noted that the mounting plate 111 can be a plate-like structure made of titanium alloy and having a certain thickness, and is provided with a plurality of holes for mounting the engine 13. The engine 13 is mounted and fixed by screws, and the outlet 112 on the mounting plate 111 is aligned with the opening of the engine 13, and a sealing component is used to seal the interface between the mounting plate 111 and the engine 13. The propellant flows from the inlet 114 of the mounting bracket 11 to the outlet 112 through the flow channel 115, and then flows into the engine 13 to provide power for the engine 13. The switch valve 12 can be an electromagnetic valve and is controlled by a control module, which controls which switch valve 12 is closed and which switch valve 12 is started. The switch valve 12 is sealed and installed in the switch hole 113 through a sealing component such as a sealing ring and a sealing gasket. The internal channel of the switch valve 12 is connected to the flow channel 115. The switch of the electromagnetic control valve controls the connection and disconnection between the corresponding flow channel 115 and the outlet 112, and further controls the corresponding engine 13 to be turned on or off. The mounting plate 111 can be installed on the body of the mounting bracket 11 separately, or it can be integrally formed together with the body of the mounting bracket 11, the inlet 114, the outlet 112, the switch hole 113, and the flow channel 115 through three-dimensional printing or mold casting to form an integral mounting bracket 11.

[0034] Specifically, Figure 2 As shown, the mounting plate 111 is a double-layer plate-like structure with a certain thickness. One layer is a nearly quadrilateral plate-like structure with four protrusions, a switch hole 113 is provided in the middle, and the four protrusions respectively have mounting holes for mounting the switch valve 12. The other layer is a plate-like structure with three protrusions similar to the shape of fan blades, an outlet 112 is provided in the middle, and the three protrusions respectively have mounting holes for mounting the engine 13. Figure 3 is from Figure 2 The view obtained from the rear perspective clearly shows another layer structure of the mounting plate 111 that is approximately in the shape of a fan blade.

[0035] In addition, multiple mounting plates 111 are arranged on different planes and at different angles to each other as needed. The engine 13 can be installed in different directions so that the aircraft is subjected to thrust in different directions, and the direction of the aircraft's flight can be adjusted to achieve precise control of the flight direction. Since the engine 13 generates high temperature when working, and its control unit cannot work in a high temperature environment for a long time, the existing parallel-arranged engines 13 must be spaced relatively large in order to prevent the influence of high temperature, which leads to a larger outer size, and the pipeline has a minimum bend radius, which makes it impossible to reduce it to a certain size. The engine 13 mounting assembly provided in the embodiment of the present application is staggered through multiple mounting plates 111, so that the arrangement direction of the engine 13 is staggered, avoiding the high temperature area, shortening the safety distance, and reducing the required axial space. Moreover, the circulation channel 115 is integrally formed with the mounting bracket 11, avoiding the influence of the pipeline bend radius, and further reducing the volume of the space propulsion system.

[0036] The engine 13 mounting assembly provided in the embodiment of the present application staggers multiple mounting plates 111 for mounting the engines 13 in space, so that the engines 13 are staggered in different directions in space, providing power in different directions for the propulsion of the spacecraft, which can reduce the volume of the space propulsion system and meet the needs of multi-directional propulsion.

[0037] In some embodiments of the present application, there are three mounting plates 111 , and the three mounting plates 111 are perpendicular to each other in space.

[0038] It should be noted that the number of mounting plates 111 can be two, three, four or more as needed. Three mounting plates 111 are distributed perpendicularly to each other in space, which is the preferred number and position of mounting plates 111. The installation axis lines of the three mounting plates 111 can just form three-dimensional X, Y and Z axes, and the engine 13 can provide power in these three directions. The distances between the three mounting plates 111 are equal, and the high temperature of a single engine 13 under long-term operation will not have an adverse effect on each other. When the main flight direction is constant, the flight posture can be adjusted by the momentum output in these three directions to achieve the control target.

[0039] In some embodiments of the present application, the mounting bracket 11 further includes a main bracket 116, which is located between two mounting plates 111. The main bracket 116 is provided with a joint hole 1161 for fixing the main bracket 116 on the cabin section.

[0040] That is, a mounting plate 111 is provided at each end of the main bracket 116. The mounting plate 111 and the main bracket 116 can be separate components connected by welding or other connection methods, or can be integrally formed by three-dimensional printing. The mounting plate 111 is at a certain angle to the main bracket 116. One side of the mounting plate 111 has an outlet 112 for installing the engine 13, and the other side has a switch hole 113 for installing the switch valve 12. The side of the main bracket 116 close to the switch valve 12 is fixed to the cabin section, and the main bracket 116 is firmly installed using bolts through the joint hole 1161.

[0041] In some embodiments of the present application, there are two inlets 114 , and the two inlets 114 are respectively disposed at two ends of the main support 116 .

[0042] It should be noted that the inlet 114 can be one or more. The inlet 114 has two inlets and the inlet 114 is provided at both ends of the main bracket 116, which can reduce the flow resistance generated when the gas propellant flows inside the pipeline. When the resistance along the way is small, the flow rate and flow rate of the propellant at the engine 13 can be guaranteed when the solenoid valve is opened. A connecting joint is generally installed at the inlet 114.

[0043] In some embodiments of the present application, auxiliary brackets 117 are respectively provided on one side of both ends of the main bracket 116 facing away from the inlet 114 , and the two auxiliary brackets 117 are connected to another mounting plate 111 .

[0044] It should be noted that the auxiliary bracket 117 can be an integrated structure with the main bracket 116, and can be made of the same material, and can be integrally formed by three-dimensional printing during the manufacturing process of the mounting bracket 11. The auxiliary bracket 117 plays the role of auxiliary support and connecting the mounting plate 111. The auxiliary bracket 117 is a round rod-shaped structure with a pipe inside, which serves as a flow channel 115, and can guide the propellant to enter the mounting plate 111 and flow from the outlet 112 of the mounting plate 111 to the engine 13.

[0045] In some embodiments of the present application, the two auxiliary supports 117 are both hollow tubular structures, and flow channels 115 are formed inside the two auxiliary supports 117 .

[0046] It should be noted that the two auxiliary brackets 117 and the main bracket 116 are in a triangular shape, and the mounting plates 111 are arranged at the three corners of the triangle, and the structure has strong stability. The auxiliary bracket 117 plays the role of auxiliary support and connecting the mounting plate 111. The auxiliary bracket 117 is a hollow tubular structure, and two flow channels 115 are formed inside, which can guide the propellant to enter the mounting plate 111 and flow from the outlet 112 of the mounting plate 111 to the engine 13. The two flow channels 115 are respectively connected to the two inlets 114, and the two channels flow at the same time, which can reduce the flow resistance generated when the gas propellant flows inside the pipeline. When the resistance along the way is small, the flow rate and flow rate of the propellant at the engine 13 can be guaranteed when the solenoid valve is opened.

[0047] In some embodiments of the present application, a through hole 1162 is provided in the middle of the main support 116 .

[0048] It should be noted that in order to enable the main bracket 116 to provide sufficient support and have the ability to withstand certain vibration and impact, the main bracket 116 has a certain width and thickness, and in order to reduce the weight of the entire engine 13 mounting assembly to the maximum extent, a through hole 1162 is provided in the middle of the main bracket 116. The through hole 1162 should be of appropriate size. If the through hole 1162 is too small, it will not have the effect of reducing the weight, and if the through hole 1162 is too large, it will affect the supporting capacity and impact resistance of the main bracket 116.

[0049] In some embodiments of the present application, a support rod 118 is disposed between a middle position of the through hole 1162 and another mounting plate 111 .

[0050] It should be noted that the support rod 118 can be an integrated structure with the mounting plate 111, and can be formed in one piece by three-dimensional printing during the manufacturing process of the mounting bracket 11. The middle of the support rod 118 can be in a triangular shape, with one end connected to the main bracket 116 and the other end connected to another mounting plate 111 different from the mounting plates 111 at both ends of the main bracket 116, playing a role of fixed support. The middle part of the support rod 118 can also be hollowed out to reduce the weight of the entire structure.

[0051] In some embodiments of the present application, the mounting bracket 11 has an integrally formed structure, and the flow channel 115 is disposed inside the mounting bracket 11 .

[0052] It should be noted that the mounting bracket 11 including the mounting plate 111, the outlet 112, the inlet 114, the switch hole 113, the multi-section flow channel 115, the main bracket 116, the auxiliary bracket 117 and the support rod 118 are all made of titanium alloy material by three-dimensional printing. Since the traditional engine 13 mounting assembly is composed of multiple valves and pipelines, the pipeline joints and the shells of each valve will occupy most of the volume and weight; the pipelines will not be completely linearly adapted, and most of them need to be bent, and the pipelines are complicated; at the same time, there are many valves, which leads to more pipelines that need to be bent, making the assembly and testing process very complicated and inconvenient to install and replace; the whole system has many pipelines and joints, and each joint represents a leak point, which leads to low reliability of the whole system. The highly integrated component designed in the present application, which designs the flow channel 115 inside the mounting bracket 11 and is formed by one-piece molding and printing, has the advantages of small size, light weight, simple installation and replacement of valves, simple pipelines, and high reliability. Figure 4 for Figure 1 The cross-sectional view is a cross-sectional view taken from a top view along the two entrances perpendicular to the direction of the main support 116. Figure 4 Two flow channels 115 connected to the two inlets 114 can be clearly seen.

[0053] Some embodiments of the present application further provide a space thruster, including the above-mentioned engine 13 mounting assembly, wherein a plurality of mounting plates 111 are all connected to the engine 13, and an inlet 114 is connected to a storage box (not shown in the figure).

[0054] It should be noted that the storage box is connected to the inlet 114 of the mounting assembly, and the inlet 114 is connected to the switch hole 113 through the flow channel 115. The switch valve 12 is installed on the switch hole 113, and the switch valve 12 controls the opening or closing of the corresponding outlet 112 through the control module. The switch hole 113 is connected to the outlet 112 of the mounting plate 111, and the outlet 112 of the mounting plate 111 is connected to the engine 13. Liquid fuel is stored inside the storage box. After the liquid fuel flows out of the storage box, it flows through the inlet 114, the flow channel 115, the switch valve 12, another section of the flow channel 115, the mounting plate 111 and the outlet 112 in sequence. When passing through the engine 13, it is catalyzed by the catalyst to produce a self-ignition phenomenon, and is ejected through the nozzle of the engine 13 to generate thrust, providing propulsion for the aircraft. The engine 13 mounting assembly is fixed on the cabin section, and the storage box is also fixed on the cabin section. A connecting joint is provided at the inlet 114 and is connected to the storage box through an external pipeline.

[0055] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present application, and in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present application.

Claims

1. An engine mounting assembly, characterized in that: include: The mounting bracket includes a plurality of mounting plates, each of the mounting plates is provided with an outlet, a switch hole is provided at a position near each of the outlets on the mounting bracket, the switch hole is connected with an inlet, and a plurality of flow channels are provided between the inlet and the plurality of outlets, the fluid flows in through the inlet, flows through the flow channels to the switch hole, and then flows out from the corresponding outlet; A plurality of switch valves are arranged one by one in the corresponding switch holes to control the connection or disconnection between the switch holes and the outlet; The plurality of mounting plates are staggered with each other on different planes and are used for mounting the engine in different directions.

2. The engine mounting assembly according to claim 1, characterized in that: There are three mounting plates, and the three mounting plates are perpendicular to each other in space.

3. The engine mounting assembly according to claim 1, characterized in that: The mounting bracket also includes a main bracket, which is located between two of the mounting plates. The main bracket is provided with a joint hole for fixing the main bracket on the cabin section.

4. The engine mounting assembly according to claim 3, characterized in that: There are two inlets, which are respectively arranged at two ends of the main support.

5. The engine mounting assembly according to claim 4, characterized in that: Auxiliary brackets are respectively arranged on one side of both ends of the main bracket facing away from the inlet, and the two auxiliary brackets are connected to the other mounting plate.

6. The engine mounting assembly according to claim 5, characterized in that: The two auxiliary supports are both hollow tubular structures, and the flow channels are formed inside the two auxiliary supports.

7. The engine mounting assembly according to claim 5, characterized in that: A through hole is arranged in the middle of the main support.

8. The engine mounting assembly according to claim 7, characterized in that: A support rod is arranged between the middle position of the through hole and the other mounting plate.

9. The engine mounting assembly according to claim 1, characterized in that: The mounting bracket has an integrally formed structure, and the flow channel is arranged inside the mounting bracket.

10. A space propulsion device, comprising the engine mounting assembly according to any one of claims 1 to 9, characterized in that: The plurality of mounting plates are all connected to an engine, and the inlet is connected to a storage box.

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