Two-component five-unit combination power system

Abstract

The application provides a dual-component five-machine combined power system, which comprises a mounting block, an oxidant inlet, a fuel inlet, an oxidant collecting groove, a fuel collecting groove, an oxidant flow channel, a fuel flow channel, an attitude control engine oxidant flow channel, an attitude control engine fuel flow channel, a track control engine oxidant flow channel and a track control engine fuel flow channel; an attitude control thrust chamber is mounted on the mounting block, the attitude control engine oxidant flow channel is connected between the attitude control thrust chamber and the oxidant collecting groove, and the attitude control engine fuel flow channel is connected between the fuel collecting groove and the attitude control thrust chamber; a track control thrust chamber is mounted on the mounting block, the track control engine oxidant flow channel is connected between the oxidant collecting groove and the track control thrust chamber, and the track control engine fuel flow channel is connected between the fuel collecting groove and the track control thrust chamber. The structure is free of pipelines and joints, compact, small in weight, high in reliability, small in space occupation and convenient to install and maintain.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of power equipment, in particular to a dual-element five-engine combined power system. BACKGROUND

[0002] At present, with the vigorous development of space industry, micro flying vehicles are widely used in the field of space. The dual-element attitude and orbit control power system has the advantages of high precision, high specific impulse, multiple start, wide thrust range, etc., and is widely used in micro flying vehicles.

[0003] In the prior art, the engines of the micro-thrust power system at home and abroad are mostly fixed by installing supports and delivering propellants through pipelines, which results in a complex system, low reliability, more structural parts, large space occupation, and inconvenient installation and maintenance. SUMMARY

[0004] The main purpose of the present application is to provide a dual-element five-engine combined power system to solve the problem of complex structure and low reliability of the dual-element five-engine combined power system in the prior art.

[0005] In order to achieve the above-mentioned purpose, the present application provides a dual-element five-engine combined power system, comprising: a mounting block, the mounting block is provided with an oxidizer inlet, a fuel inlet, an oxidizer collection tank, a fuel collection tank, an oxidizer flow channel, a fuel flow channel, an attitude control engine oxidizer flow channel, an attitude control engine fuel flow channel, an orbit control engine oxidizer flow channel, and an orbit control engine fuel flow channel, wherein the oxidizer flow channel is connected between the oxidizer inlet and the oxidizer collection tank, and the fuel flow channel is connected between the fuel inlet and the fuel collection tank; an attitude control thrust chamber, the attitude control thrust chamber is installed on the mounting block, the attitude control engine oxidizer flow channel is connected between the attitude control thrust chamber and the oxidizer collection tank, and the attitude control engine fuel flow channel is connected between the fuel collection tank and the attitude control thrust chamber; an orbit control thrust chamber, the orbit control thrust chamber is installed on the mounting block, the orbit control engine oxidizer flow channel is connected between the oxidizer collection tank and the orbit control thrust chamber, and the orbit control engine fuel flow channel is connected between the fuel collection tank and the orbit control thrust chamber.

[0006] Further, the oxidizer inlet and the fuel inlet are located on the same plane or different planes of the mounting block, and the oxidizer inlet and the fuel inlet are communicated with the outside through a conduit.

[0007] Further, the oxidizer collection tank and the fuel collection tank are arranged in a circular or curved or linear shape, and the cross section of the oxidizer collection tank and the fuel collection tank is circular or elliptical or polygonal.

[0008] Further, the oxidizer collection groove, the fuel collection groove, the oxidizer flow channel, the fuel flow channel, the attitude control engine oxidizer flow channel, the attitude control engine fuel flow channel, the orbit control engine oxidizer flow channel and the orbit control engine fuel flow channel are arranged in a straight line or a curve.

[0009] Further, the mounting block is a prismatic block, and the attitude control thrust chambers are four, which are respectively mounted on the outer circumferential surface of the prismatic block.

[0010] Further, the orbit control thrust chamber is mounted on the end surface of the prismatic block.

[0011] Further, the dual-propellant five-engine combined power system further comprises a control valve for controlling the fuel and the oxidizer entering the attitude control thrust chamber and the orbit control thrust chamber.

[0012] Further, the control valve is an electromagnetic valve.

[0013] Further, the control valve, the attitude control thrust chamber and the orbit control thrust chamber are all sealingly connected to the mounting block.

[0014] By applying the technical scheme of the present application, the oxidizer inlet, the fuel inlet, the oxidizer collection groove, the fuel collection groove, the oxidizer flow channel, the fuel flow channel, the attitude control engine oxidizer flow channel, the attitude control engine fuel flow channel, the orbit control engine oxidizer flow channel, the orbit control engine fuel flow channel, the orbit control thrust chamber and the attitude control thrust chamber in the dual-propellant five-engine combined power system of the present application are all collected on the mounting block, and the structure is free of pipelines and joints, compact, light in weight, high in reliability, occupies less space, and is convenient to install and maintain.

[0015] In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0016] The drawings constituting a part of the specification of the present application are used to provide further understanding of the present application, and the schematic embodiments of the present application and the description thereof are used to explain the present application, and do not constitute improper limitation on the present application. In the drawings:

[0017] Fig. 1 The front view of the mounting block of the present application is schematically shown;

[0018] Fig. 2 The top view of the mounting block of the present application is schematically shown;

[0019] Fig. 3 The sectional view of the mounting block of the present application at the oxidizer flow channel and the fuel flow channel is schematically shown.

[0020] Fig. 4 schematically shows a sectional view of the mounting block of the present application at the oxidizer manifold or fuel manifold position;

[0021] Fig. 5 schematically shows a sectional view of the mounting block of the present application at the attitude control engine oxidizer flow passage and attitude control engine fuel flow passage position;

[0022] Fig. 6 schematically shows a perspective view of the dual propellant five-engine combined power system of the present application.

[0023] Wherein, the above-mentioned drawings include the following reference signs:

[0024] 10, mounting block; 11, oxidizer inlet; 12, fuel inlet; 13, oxidizer manifold; 14, fuel manifold; 15, oxidizer flow passage; 16, fuel flow passage; 17, attitude control engine oxidizer flow passage; 18, attitude control engine fuel flow passage; 19, orbit control engine oxidizer flow passage; 110, orbit control engine fuel flow passage; 20, attitude control thrust chamber; 30, orbit control thrust chamber; 40, control valve. DETAILED DESCRIPTION

[0025] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0026] In order to make the personnel in the technical field better understand the present application scheme, the technical scheme in the embodiments of the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by the personnel in the field without creative labor should belong to the protection scope of the present application.

[0027] It should be noted that the terms "first", "second" and the like in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, not necessarily to describe a specific order or sequence. It should be understood that the terms thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device including a series of steps or units does not necessarily limit to those steps or units clearly listed, but can include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0028] It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and / or "comprising," when used in this specification, specify the presence of stated features, steps, operations, elements, components, and / or groups thereof, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and / or groups thereof.

[0029] Referring to Figs. 1 to 6 As shown, according to the embodiment of the present application, a dual-element five-machine combined power system is provided, which comprises a mounting block 10, an attitude control thrust chamber 20 and a trajectory control thrust chamber 30.

[0030] The mounting block 10 is provided with an oxidizer inlet 11, a fuel inlet 12, an oxidizer collecting groove 13, a fuel collecting groove 14, an oxidizer flow channel 15, a fuel flow channel 16, an attitude control engine oxidizer flow channel 17, an attitude control engine fuel flow channel 18, a trajectory control engine oxidizer flow channel 19 and a trajectory control engine fuel flow channel 110. The oxidizer flow channel 15 is connected between the oxidizer inlet 11 and the oxidizer collecting groove 13, facilitating the delivery of the oxidizer entering from the oxidizer inlet 11 into the oxidizer collecting groove 13. The fuel flow channel 16 is connected between the fuel inlet 12 and the fuel collecting groove 14, facilitating the delivery of the fuel entering from the fuel inlet 12 into the fuel collecting groove 14. The attitude control engine oxidizer flow channel 17 and the attitude control engine fuel flow channel 18 are connected with the oxidizer collecting groove 13 and the fuel collecting groove 14 respectively. The attitude control thrust chamber 20 is mounted on the mounting block 10. The attitude control engine oxidizer flow channel 17 and the attitude control engine fuel flow channel 18 are in communication with the attitude control thrust chamber 20, facilitating the delivery of the oxidizer in the oxidizer collecting groove 13 and the fuel in the fuel collecting groove 14 into the attitude control thrust chamber 20. Correspondingly, the trajectory control thrust chamber 30 is mounted on the mounting block 10. The trajectory control engine oxidizer flow channel 19 and the trajectory control engine fuel flow channel 110 are connected with the oxidizer collecting groove 13 and the fuel collecting groove 14 respectively. The trajectory control engine oxidizer flow channel 19 and the trajectory control engine fuel flow channel 110 are in communication with the trajectory control thrust chamber 30, facilitating the delivery of the oxidizer in the oxidizer collecting groove 13 and the fuel in the fuel collecting groove 14 into the trajectory control thrust chamber 30.

[0031] According to the above structure, it can be known that the oxidant inlet 11, the fuel inlet 12, the oxidant collection groove 13, the fuel collection groove 14, the oxidant flow channel 15, the fuel flow channel 16, the attitude control engine oxidant flow channel 17, the attitude control engine fuel flow channel 18, the orbit control engine oxidant flow channel 19, the orbit control engine fuel flow channel 110, the orbit control thrust chamber 30 and the attitude control thrust chamber 20 in the dual-component five-machine combined power system of the application are all collected on the mounting block 10, the structure has no pipeline and joint, is compact in structure, small in weight, high in reliability, small in occupied space and convenient to install and maintain.

[0032] In an embodiment of the application, the oxidant inlet 11 and the fuel inlet 12 are arranged on the same plane of the mounting block 10, and the oxidant inlet 11 and the fuel inlet 12 are communicated with the outside through the pipes. Of course, in other embodiments of the application, the oxidant inlet 11 and the fuel inlet 12 can also be arranged on different planes of the mounting block 10, respectively.

[0033] In actual processing, the oxidant collection groove 13 and the fuel collection groove 14 in the embodiment can be arranged in a circular shape, or in a curved or straight line shape, and the cross section of the oxidant collection groove 13 and the fuel collection groove 14 can be circular, or can be arranged in an elliptical or polygonal shape, or other special-shaped structures, as long as other deformation modes under the concept of the application are within the protection scope of the application.

[0034] Preferably, the oxidant collection groove 13, the fuel collection groove 14, the oxidant flow channel 15, the fuel flow channel 16, the attitude control engine oxidant flow channel 17, the attitude control engine fuel flow channel 18, the orbit control engine oxidant flow channel 19 and the orbit control engine fuel flow channel 110 in the embodiment are arranged in a straight line or a curved line, and can also be arranged in a broken line, as long as other deformation modes under the concept of the application are within the protection scope of the application.

[0035] Again referring to Figs. 1 to 6 It is shown that the mounting block 10 in the embodiment is a prismatic block, and the four attitude control thrust chambers 20 are installed on the four outer circumferential surfaces of the prismatic block, respectively. Of course, in other embodiments of the application, the mounting block 10 can also be arranged as a cylindrical block or other special-shaped block structure, as long as other deformation modes under the concept of the application are within the protection scope of the application.

[0036] Referring to Figs. 1 to 4 It is shown that the mounting block 10 in the embodiment has six planes on the outside, and the four attitude control thrust chambers 20 are installed on the four planes, respectively, which can be arranged oppositely or continuously, as long as other deformation modes under the concept of the application are within the protection scope of the application.

[0037] The track control thrust chamber 30 is installed on the end face of the prism block, while the four attitude control thrust chambers 20 are installed on the outer periphery of the mounting block 10. This can greatly reduce the overall volume and weight of the entire dual-component five-machine combined power system, making it compact, highly reliable, space-saving, and easy to install and maintain.

[0038] The dual-component five-engine combined propulsion system in this embodiment also includes a control valve 40, which is used to control the fuel and oxidizer entering the attitude control thrust chamber 20 and the orbit control thrust chamber 30. Preferably, the control valve 40 in this embodiment is a solenoid valve, which has a simple structure and is easy to implement. The solenoid valve controls the oxidizer and fuel in the oxidizer collection tank 13 and the fuel collection tank 14 to enter the attitude control thrust chamber 20 and the orbit control thrust chamber 30, where the propellant burns and generates thrust.

[0039] Preferably, in this embodiment, the control valve 40, attitude control thrust chamber 20, and track control thrust chamber 30 are all sealed and connected to the mounting block 10, resulting in a stable and reliable structure. During actual installation, the control valve 40, attitude control thrust chamber 20, and track control thrust chamber 30 are sealed and connected to the mounting block 10 using O-ring seals.

[0040] As can be seen from the above description, the embodiments of the present invention achieve the following technical effects:

[0041] The bicomponent five-engine combined power system of this invention integrates the inlets, channels, collection tanks, solenoid valves, and thrust chambers for both oxidizer and fuel, eliminating the need for piping and joints. This results in a more compact layout, effectively reduced weight, significantly increased reliability, and excellent applicability to bicomponent liquid attitude and trajectory control engines.

[0042] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0043] For purposes of the description hereinafter, the orientations in the various drawings will be described as they are depicted in the drawings. However, it is to be understood that these orientations are depicted and described only for purposes of illustrating the embodiments, and that other orientations of the described embodiments are possible. Therefore, the following description is not intended to limit the scope of the application. The terms "front," "back," "top," "bottom" and the like as used in this description should not be construed as limiting the present application in any manner. The terms "first," "second," "third," etc. as used in this description should not be construed as limiting the present application in any manner. The terms "including," "containing," "having," and the like as used herein are understood to be open-ended, i.e., meaning "including but not limited to." The terms "coupled" and "connected" as used herein, are intended to mean a direct connection to or between entities. These terms are not intended to mean that an electrical or magnetic coupling or path occurs between entities.

[0044] In the description of the present application, it is to be understood that the orientation words such as "front, back, up, down, left, right," "transverse, vertical, perpendicular, horizontal," and "top, bottom," etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, only for the convenience of describing the present application and simplifying the description, these orientation words do not indicate and imply that the devices or elements referred to must have a particular orientation or be constructed and operated in a particular orientation, therefore, cannot be understood as limiting the scope of protection of the present application; the orientation words "inner, outer" refer to the inner and outer relative to the contour of each component.

[0045] The above only describes the preferred embodiments of the present application, and is not intended to limit the present application. For those skilled in the art, the present application can have various modifications and changes. 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 two-component five-mechanism combination power system characterized by, The application relates to a dual-propellant five-engine combined power system, which comprises the following components: a mounting block (10) which is a prismatic block, wherein an oxidant inlet (11), a fuel inlet (12), an oxidant collecting groove (13), a fuel collecting groove (14), an oxidant flow channel (15), a fuel flow channel (16), an attitude control engine oxidant flow channel (17), an attitude control engine fuel flow channel (18), an orbit control engine oxidant flow channel (19) and an orbit control engine fuel flow channel (110) are arranged on the mounting block (10), wherein the oxidant flow channel (15) is connected between the oxidant inlet (11) and the oxidant collecting groove (13), and the fuel flow channel (16) is connected between the fuel inlet (12) and the fuel collecting groove (14); four attitude control thrust chambers (20) which are arranged on four outer circumferential surfaces of the prismatic block respectively, wherein the attitude control engine oxidant flow channel (17) is connected between the attitude control thrust chamber (20) and the oxidant collecting groove (13), and the attitude control engine fuel flow channel (18) is connected between the fuel collecting groove (14) and the attitude control thrust chamber (20); an orbit control thrust chamber (30) which is arranged on an end surface of the prismatic block, wherein the orbit control engine oxidant flow channel (19) is connected between the oxidant collecting groove (13) and the orbit control thrust chamber (30), and the orbit control engine fuel flow channel (110) is connected between the fuel collecting groove (14) and the orbit control thrust chamber (30).

2. The two-component five-engine hybrid powertrain system of claim 1, wherein, The oxidant inlet (11) and the fuel inlet (12) are arranged on the same plane or different planes of the mounting block (10), and are communicated with the outside through pipes.

3. The two-component five-engine hybrid powertrain system of claim 1, wherein, The oxidant collecting groove (13) and the fuel collecting groove (14) are arranged in a circular, curved or linear mode, and the cross sections of the oxidant collecting groove (13) and the fuel collecting groove (14) are circular, elliptical or polygonal.

4. The two-component five-engine hybrid powertrain system of claim 1, wherein, The oxidant collecting groove (13), the fuel collecting groove (14), the oxidant flow channel (15), the fuel flow channel (16), the attitude control engine oxidant flow channel (17), the attitude control engine fuel flow channel (18), the orbit control engine oxidant flow channel (19) and the orbit control engine fuel flow channel (110) are arranged in a linear or curved mode.

5. The two-component five-engine hybrid powertrain system of claim 1, wherein, The dual-propellant five-engine combined power system further comprises a control valve (40) which is used for controlling the fuel and the oxidant entering the attitude control thrust chamber (20) and the orbit control thrust chamber (30).

6. The two-component five-engine hybrid powertrain system of claim 5, wherein, The control valve (40) is an electromagnetic valve.

7. The two-component five-engine hybrid powertrain system of claim 5, wherein, The control valve (40), the attitude control thrust chamber (20) and the orbit control thrust chamber (30) are all sealingly connected to the mounting block (10).

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