Topological configuration of ion rocket engine based on carbon fiber composite material

Abstract

The invention relates to the technical field of aerospace propulsion, in particular to an ion rocket engine topological structure based on a carbon fiber composite material, which comprises a grid shell, a discharge shell, a gas circuit shell, a cover plate, a discharge cylinder and a neutralizer outer cover, wherein the grid shell, the discharge shell, the gas circuit shell, the cover plate, the discharge cylinder and the neutralizer outer cover are all prepared based on a carbon fiber composite material; the grid shell is fixedly connected with the front end of the discharge shell; the rear end of the discharge shell is fixedly connected with the front end of the gas circuit shell; the cover plate is fixed at the rear end of the gas circuit shell; the discharge cylinder is arranged in the discharge shell; and the neutralizer outer cover is fixed on the side surface of the discharge shell. The outstanding advantages of good mechanical property, excellent conductivity, small expansion coefficient and low density of the carbon fiber composite material are fully utilized, and the technical problems of high-temperature working reliability, performance level satisfaction and stability of the medium-high power ion rocket engine are solved.

Description

Technical Field

[0001] The present application relates to the field of aerospace propulsion technology, and more specifically, to a topological configuration of an ion rocket engine based on carbon fiber composite materials. Background Art

[0002] Ion rocket engines are widely used in spacecraft attitude control and orbit transfer missions due to their significant advantages of high specific impulse, long life, high reliability, and precisely adjustable thrust. Restricted by the inherent working principle, the engine will generate a lot of heat when working, resulting in a high operating temperature inside and outside the product. The above heat and temperature will increase sharply with the increase of engine caliber and power.

[0003] As a complex mechanical assembly product, the different materials used in the engine will show different thermal expansion effects in high and low temperature environments. The combined cumulative effect will cause asymmetric deformation of the engine geometry, which will cause the ion beam attracted by the grid assembly to shift relative to the center of the engine structure, causing the thrust vector of the satellite propulsion system to be eccentric, thereby affecting the satellite's orbit control direction accuracy. Long-term thrust eccentricity will cause the satellite to produce unnecessary eccentric torque, and in severe cases, unexpected and uncontrollable flipping will occur. At the same time, as a typical electric vacuum device, the engine does not have good heat dissipation conditions during engineering applications. When the internal temperature of the engine is too high, it will cause the components to deform due to high temperature, and in severe cases, it will cause structural failure, and ultimately cause the loss of functionality of the entire machine; when the external temperature of the engine is too high, it will affect the stability of the satellite structure and the normal operation of related units around the engine, seriously endangering the reliability and safety of the satellite's in-orbit operation.

[0004] For this reason, in the engine structure design, only materials with higher temperature resistance can be selected to ensure the integrity and effectiveness of its structure and functions. However, materials with higher temperature resistance often mean higher economic benefit costs and quality control costs. In the process of engine whole-satellite application, only passive thermal control measures such as adding thermal insulation pads can be taken to achieve its installation on the satellite structure. The newly added thermal control parts not only increase the weight of the satellite, but also bring problems with the effectiveness and long-term reliability of the thermal control solution, thereby introducing new technical risks for the satellite's on-orbit flight application.

[0005] Therefore, providing lightweight, highly stable and highly reliable ion rocket engine products has become a problem that must be solved in the engine system integration and manufacturing process. It is also one of the key technologies that must be overcome for ion rocket engines to achieve in-orbit engineering applications. Summary of the invention

[0006] The present application provides an ion rocket engine topology configuration based on carbon fiber composite materials, which solves the technical problems of high-temperature working reliability, performance level satisfaction and stability of medium and high power ion rocket engines, and realizes the lightweight structure of the ion rocket engine itself.

[0007] In order to achieve the above-mentioned objectives, the present application provides an ion rocket engine topology configuration based on carbon fiber composite materials, including a grid shell, a discharge shell, a gas path shell, a cover plate, a discharge tube and a neutralizer cover, wherein: the grid shell, the discharge shell, the gas path shell, the cover plate, the discharge tube and the neutralizer cover are all made based on carbon fiber composite materials; the grid shell is fixedly connected to the front end of the discharge shell; the rear end of the discharge shell is fixedly connected to the front end of the gas path shell; the cover plate is fixed to the rear end of the gas path shell; the discharge tube is arranged inside the discharge shell and fixedly connected to the internal mounting seat of the gas path shell; the neutralizer cover is fixed to the side of the discharge shell.

[0008] Furthermore, a positioning ring and a first mounting ear are provided on the mounting surface of the gate shell, wherein: an offset structure is formed between the upper end face and the lower end face of the positioning ring and the mounting surface of the gate shell; during installation, the gap between the outer side face of the positioning ring and the inner side face of the discharge shell is less than 0.1 mm; 6 first mounting ears are provided, evenly distributed on the outer side face of the mounting surface of the gate shell, and the lower end face of the first mounting ear is flush with the mounting surface of the gate shell; the thickness of the first mounting ear is 2-4 mm; and a fixing through hole is provided on the first mounting ear.

[0009] Furthermore, a second mounting ear is provided on the front outer side of the discharge shell, the upper end surface of the second mounting ear is flush with the mounting surface of the front end of the discharge shell, and the second mounting ear is provided in one-to-one correspondence with the first mounting ear; a nut made of titanium alloy is pre-embedded in the second mounting ear.

[0010] Furthermore, a stainless steel screw is passed through the fixing through hole of the first mounting ear and is matched with a nut inside the second mounting ear to fix the grid housing to the front end of the discharge housing.

[0011] Furthermore, a first annular mounting ring is provided on the outer side surface of the rear end of the discharge shell, and a plurality of mounting holes are evenly distributed on the first annular mounting ring; a second annular mounting ring is provided on the outer side surface of the front end of the gas path shell, and a plurality of mounting holes are evenly distributed on the second annular mounting ring, and the plurality of mounting holes on the second annular mounting ring are arranged correspondingly to the plurality of mounting holes on the first annular mounting ring.

[0012] Furthermore, a nut made of titanium alloy is pre-embedded in the mounting hole, and the rear end of the discharge housing is fixedly connected to the front end of the gas path housing by using stainless steel screws and nuts.

[0013] Furthermore, a support ring is provided between the first annular mounting ring and the second annular mounting ring, and a through hole corresponding to the mounting hole is provided on the support ring.

[0014] Furthermore, the discharge tube includes an inner tube, an outer tube and insulating ceramics, wherein: the outer tube is sleeved on the outside of the inner tube, and the inner tube and the outer tube are coaxially fixed inside the discharge shell; the insulating ceramics are arranged between the inner tube and the outer tube; and the outer tube is fixedly connected to the mounting seat inside the gas path shell.

[0015] Furthermore, the neutralizer outer cover includes a cover body, a cover plate and a cover cap, wherein: the cover body is provided with a mounting hole, which is threadedly connected to the mounting hole on the side of the discharge shell; the cover plate is fixed to the side of the cover body for installing the neutralizer of the ion rocket engine; the cover cap is arranged on the top surface of the cover body; and corresponding connection holes are arranged on the side of the discharge shell, the cover body and the cover plate.

[0016] Furthermore, the cover plate is fixed to the rear end of the gas path housing by means of stainless steel screws and embedded nuts.

[0017] The present application provides an ion rocket engine topology configuration based on carbon fiber composite materials, which has the following beneficial effects:

[0018] This application makes full use of the outstanding advantages of carbon fiber composite materials, such as good mechanical properties, excellent electrical conductivity, small expansion coefficient and low density. Without reducing the performance level of the ion rocket engine and changing its on-orbit application strategy, it optimizes the engine design scheme and improves the connection and fastening methods of parts to solve the technical problems of high-temperature working reliability, performance level satisfaction and stability of medium and high-power ion rocket engines, realizes the lightweight structure of the ion rocket engine itself, and can effectively promote the engineering application of ion rocket engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of this application are used to provide a further understanding of this application, so that other features, purposes and advantages of this application become more obvious. The schematic embodiment drawings and their descriptions of this application are used to explain this application and do not constitute an improper limitation on this application. In the drawings:

[0020] Figure 1 It is a structural diagram of the topological configuration of an ion rocket engine based on a carbon fiber composite material provided in an embodiment of the present application;

[0021] Figure 2 It is an internal cross-sectional view of a topological configuration of an ion rocket engine based on a carbon fiber composite material provided in an embodiment of the present application;

[0022] In the figure: 1-grid housing, 11-positioning ring, 12-first mounting ear, 2-discharge housing, 21-second mounting ear, 22-first annular mounting ring, 3-gas path housing, 31-second annular mounting ring, 4-cover plate, 5-discharge tube, 51-inner tube, 52-outer tube, 53-insulating ceramic, 54-mounting seat, 6-neutralizer outer cover, 61-cover body, 62-cover plate, 63-cover cover, 7-support ring. DETAILED DESCRIPTION

[0023] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0024] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0025] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0026] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0027] In addition, the term "plurality" shall mean two or more.

[0028] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0029] like Figure 1-2 As shown, the present application provides a topological configuration of an ion rocket engine based on carbon fiber composite materials, including a grid shell 1, a discharge shell 2, a gas path shell 3, a cover plate 4, a discharge tube 5 and a neutralizer cover 6, wherein: the grid shell 1, the discharge shell 2, the gas path shell 3, the cover plate 4, the discharge tube 5 and the neutralizer cover 6 are all made based on carbon fiber composite materials; the grid shell 1 is fixedly connected to the front end of the discharge shell 2; the rear end of the discharge shell 2 is fixedly connected to the front end of the gas path shell 3; the cover plate 4 is fixed to the rear end of the gas path shell 3; the discharge tube 5 is arranged inside the discharge shell 2 and is fixedly connected to the internal mounting seat 54 of the gas path shell 3; the neutralizer cover 6 is fixed to the side of the discharge shell 2.

[0030] Specifically, in the topological configuration of the ion rocket engine based on carbon fiber composite materials provided in the embodiment of the present application, except for the components with special functions such as the grid assembly, magnetic circuit structure, hollow cathode and air supply assembly, other components of the ion rocket engine are prepared using carbon fiber composite materials, including the grid shell 1 for placing the grid assembly, the discharge tube 5 and the discharge shell 2 for placing the magnetic circuit structure and the hollow cathode, the gas circuit shell 3 for placing the air supply assembly, the neutralizer cover 6 for placing the engine neutralizer, and the fixed support structures such as the cover plate 4 and the mounting seat 54. That is, the embodiment of the present application is based on carbon fiber composite materials, and uses its advantages of good mechanical properties, excellent electrical conductivity, small expansion coefficient and low density to optimize the connection and fixing methods of the various component structures of the ion rocket engine, so that it can meet the requirements of light weight, high stability and high reliability.

[0031] Furthermore, a positioning ring 11 and a first mounting ear 12 are provided on the mounting surface of the gate housing 1, wherein: an offset structure is formed between the upper end surface and the lower end surface of the positioning ring 11 and the mounting surface of the gate housing 1; during installation, the gap between the outer side surface of the positioning ring 11 and the inner side surface of the discharge housing 2 is less than 0.1 mm; 6 first mounting ears 12 are provided, evenly distributed on the outer side of the mounting surface of the gate housing 1, and the lower end surface of the first mounting ear 12 is flush with the mounting surface of the gate housing 1; the thickness of the first mounting ear 12 is 2-4 mm; and a fixing through hole is provided on the first mounting ear 12.

[0032] Furthermore, a second mounting ear 21 is provided on the outer side surface of the front end of the discharge shell 2, the upper end surface of the second mounting ear 21 is flush with the mounting surface of the front end of the discharge shell 2, and the second mounting ear 21 is provided in a one-to-one correspondence with the first mounting ear 12; a nut made of titanium alloy is pre-embedded in the second mounting ear 21.

[0033] Furthermore, a stainless steel screw is passed through the fixing through hole of the first mounting ear 12 and is connected with a nut inside the second mounting ear 21 to fix the grid housing 1 to the front end of the discharge housing 2 .

[0034] Specifically, the front end of the grid housing 1 and the discharge housing 2 are threadedly connected by stainless steel screws and pre-embedded nuts made of titanium alloy. Six first mounting ears 12 are preferably arranged on the mounting surface of the grid housing 1, and the first mounting ears 12 are provided with fixed through holes for passing screws; the positioning ring 11 is arranged on the mounting surface of the grid housing 1, which plays a positioning role to ensure the stable and accurate connection between the grid housing 1 and the discharge housing 2; six second mounting ears 21 are also preferably arranged on the outer surface of the front end of the discharge housing 2, and the position of the second mounting ears 21 corresponds to the position of the first mounting ears 12, and the second mounting ears 21 are also provided with fixed through holes, and nuts made of titanium alloy are pre-embedded in the through holes. During installation, the stainless steel screws are passed through the fixed through holes of the first mounting ears 12 and fastened with the pre-embedded nuts of the second mounting ears 21, so as to realize the fixed connection between the front end of the grid housing 1 and the discharge housing 2.

[0035] Furthermore, a first annular mounting ring 22 is provided on the outer side surface of the rear end of the discharge shell 2, and a plurality of mounting holes are evenly distributed on the first annular mounting ring 22; a second annular mounting ring 31 is provided on the outer side surface of the front end of the gas circuit shell 3, and a plurality of mounting holes are evenly distributed on the second annular mounting ring 31, and the plurality of mounting holes on the second annular mounting ring 31 are arranged correspondingly to the plurality of mounting holes on the first annular mounting ring 22.

[0036] Furthermore, a nut made of titanium alloy is pre-buried in the mounting hole, and the rear end of the discharge housing 2 is fixedly connected to the front end of the gas path housing 3 by using stainless steel screws and nuts.

[0037] Specifically, the rear end of the discharge housing 2 and the front end of the gas circuit housing 3 are also threadedly fixed by stainless steel screws and pre-embedded titanium alloy nuts. The first annular mounting ring 22 at the rear end of the discharge housing 2 and the second annular mounting ring 31 at the front end of the gas circuit housing 3 are correspondingly arranged, and the stainless steel screws and the titanium alloy nuts pre-embedded in the mounting holes are used to achieve fixed connection between the rear end of the discharge housing 2 and the front end of the gas circuit housing 3.

[0038] Furthermore, a support ring 7 is provided between the first annular mounting ring 22 and the second annular mounting ring 31, and a through hole corresponding to the mounting hole is provided on the support ring 7. In order to ensure connection strength and stability, the support ring 7 is provided between the first annular mounting ring 22 and the second annular mounting ring 31.

[0039] Furthermore, the discharge tube 5 includes an inner tube 51, an outer tube 52 and an insulating ceramic 53, wherein: the outer tube 52 is sleeved outside the inner tube 51, and the inner tube 51 and the outer tube 52 are fixed inside the discharge housing 2 in a coaxial mounting manner; the insulating ceramic 53 is arranged between the inner tube 51 and the outer tube 52; and the outer tube 52 is fixedly connected to the mounting seat 54 inside the gas circuit housing 3. The discharge tube 5 is mainly used to place the magnetic circuit structure of the engine, and is composed of the inner tube 51 and the outer tube 52. The inner tube 51 and the outer tube 52 are centrally and coaxially mounted in an insulating mounting manner; the entire discharge tube 5 is fixed by the mounting seat 54 to match the magnetic circuit structure of the engine.

[0040] Furthermore, the neutralizer outer cover 6 includes a cover body 61, a cover plate 62 and a cover 63, wherein: the cover body 61 is provided with a mounting hole, which is threadedly connected to the mounting hole on the side of the discharge shell 2; the cover plate 62 is fixed to the side of the cover body 61, and is used to install the neutralizer of the ion rocket engine; the cover 63 is arranged on the top surface of the cover body 61; and corresponding connection holes are arranged on the side of the discharge shell 2, the cover body 61 and the cover plate 62. The neutralizer is fixed to the inside of the cover body 61 as a whole through the cover plate 62, and the cover 63 is arranged above the cover body 61 to protect the neutralizer inside the cover body 61. The neutralizer outer cover 6 is fixed to the side of the discharge shell 2 as a whole, and the electrical and gas pipeline channels of the neutralizer are provided through the arranged connection holes.

[0041] Further, the cover plate 4 is fixed to the rear end of the gas circuit housing 3 by means of stainless steel screws and embedded nuts. The cover plate 4 is fixed to the rearmost end of the gas circuit housing 3 by means of threaded connection to ensure the stability and sealing of the internal engine.

[0042] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A topological configuration of an ion rocket engine based on carbon fiber composite material, characterized in that: It includes a grid shell, a discharge shell, a gas path shell, a cover plate, a discharge tube and a neutralizer cover, wherein: The grid housing, the discharge housing, the gas path housing, the cover plate, the discharge tube and the neutralizer cover are all made of carbon fiber composite materials; The grid housing is fixedly connected to the front end of the discharge housing; The rear end of the discharge housing is fixedly connected to the front end of the gas circuit housing; The cover plate is fixed to the rear end of the gas circuit housing; The discharge tube is arranged inside the discharge housing and is fixedly connected to the internal mounting seat of the gas circuit housing; The neutralizer cover is fixed to the side of the discharge shell.

2. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 1 is characterized in that: A positioning ring and a first mounting ear are provided on the mounting surface of the grid housing, wherein: A dislocation structure is formed between the upper end surface and the lower end surface of the positioning ring and the mounting surface of the grid housing; During installation, the gap between the outer side of the positioning ring and the inner side of the discharge shell is less than 0.1 mm; The first mounting ears are provided with 6 pieces, which are evenly distributed on the outside of the mounting surface of the grid housing, and the lower end surface of the first mounting ears is flush with the mounting surface of the grid housing; The thickness of the first mounting ear is 2-4 mm; The first mounting ear is provided with a fixing through hole.

3. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 2 is characterized in that: A second mounting ear is arranged on the outer side surface of the front end of the discharge shell, the upper end surface of the second mounting ear is flush with the mounting surface of the front end of the discharge shell, and the second mounting ear is arranged in one-to-one correspondence with the first mounting ear; a nut made of titanium alloy is pre-embedded in the second mounting ear.

4. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 3 is characterized in that: The grid housing is fixedly connected to the front end of the discharge housing by passing a stainless steel screw through the fixing through hole of the first mounting ear and cooperating with a nut inside the second mounting ear.

5. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 4 is characterized in that: A first annular mounting ring is provided on the outer side surface of the rear end of the discharge shell, and a plurality of mounting holes are evenly distributed on the first annular mounting ring; a second annular mounting ring is provided on the outer side surface of the front end of the gas circuit shell, and a plurality of mounting holes are evenly distributed on the second annular mounting ring, and the plurality of mounting holes on the second annular mounting ring are arranged correspondingly to the plurality of mounting holes on the first annular mounting ring.

6. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 5 is characterized in that: A nut made of titanium alloy is pre-buried in the mounting hole, and the rear end of the discharge housing is fixedly connected to the front end of the gas path housing by using stainless steel screws and nuts.

7. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 6 is characterized in that: A support ring is further arranged between the first annular mounting ring and the second annular mounting ring, and a through hole corresponding to the mounting hole is arranged on the support ring.

8. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 7 is characterized in that: The discharge tube comprises an inner tube, an outer tube and insulating ceramics, wherein: The outer cylinder is sleeved on the outside of the inner cylinder, and the inner cylinder and the outer cylinder are coaxially fixed inside the discharge shell; The insulating ceramic is arranged between the inner cylinder and the outer cylinder; The outer cylinder is fixedly connected to a mounting seat inside the gas circuit housing.

9. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 8 is characterized in that: The neutralizer housing comprises a housing, a housing plate and a housing cover, wherein: The cover body is provided with a mounting hole, which is threadedly connected with the mounting hole on the side of the discharge shell; The cover plate is fixed to the side of the cover body and is used to install the neutralizer of the ion rocket engine; The cover is arranged on the top surface of the cover body; The side surface of the discharge shell, the cover body and the cover plate are provided with corresponding connection holes.

10. The topological configuration of the ion rocket engine based on carbon fiber composite material according to claim 9 is characterized in that: The cover plate is fixed to the rear end of the gas circuit housing by means of stainless steel screws and embedded nuts.

Images