Rocket engines and launch vehicles

Abstract

The embodiment of the present application provides a rocket engine and a launch vehicle. The rocket engine includes: an assembly, at least two groups of thrust chambers and valves. Each group of thrust chambers includes at least two thrust chambers that are angled to each other. The angles of different groups of thrust chambers are different. One end of each thrust chamber is fixedly connected to the assembly and is in line. Each thrust chamber is connected to at least one valve through an assembly, and the valve is used to control the flow of propellant flowing into the thrust chamber. The rocket engine in the embodiment of the present application has a simple overall structure, is easy to install, has a high degree of integration, occupies a relatively concentrated space inside the launch vehicle, is easy to maintain, and can reduce system risks on the basis of achieving diversified control torque.

Description

Technical Field

[0001] The present application relates to the field of propulsion technology for launch vehicles, and more specifically, to a rocket engine and a launch vehicle. Background Art

[0002] Rocket engines are the main power source for launch vehicles, which need to adjust their flight status according to different missions during flight. To meet the attitude adjustment requirements of launch vehicles, the rocket's power system generally includes multiple thrust chambers with different orientations, which control the working status of each thrust chamber and thus control the rocket's pitch, yaw, roll and other attitudes.

[0003] In the related art, the installation position of the thrust chamber in the internal space of the rocket is relatively scattered, and there are many installation structures, which leads to the overall structure of the rocket engine being relatively complex and occupying a large space. Summary of the invention

[0004] In view of the shortcomings of the existing methods, the present application proposes a rocket engine and a carrier rocket to solve the technical problems in the prior art that the overall structure of the rocket engine is relatively complex or occupies a large space.

[0005] In a first aspect, an embodiment of the present application provides a rocket engine, comprising: an assembly, at least two sets of thrust chambers and valves.

[0006] Each group of thrust chambers includes at least two thrust chambers that are angled to each other. Different groups of thrust chambers have different angles. One end of each thrust chamber is fixedly connected to the assembly and is collinear.

[0007] Each thrust chamber is connected to at least one valve through an assembly, and the valve is used to control the flow rate of the propellant flowing into the thrust chamber.

[0008] Optionally, the at least two groups of thrust chambers include: a first group of thrust chambers and a second group of thrust chambers.

[0009] The first group of thrust chambers includes a first thrust chamber and a second thrust chamber which form a first angle with each other.

[0010] The second group of thrust chambers includes a third thrust chamber and a fourth thrust chamber which form a second angle with each other.

[0011] The first group of thrust chambers is located between the third thrust chamber and the fourth thrust chamber, and the first included angle is smaller than the second included angle.

[0012] Optionally, the rocket engine further includes: a first liquid inlet and a second liquid inlet.

[0013] The first liquid inlet and the second liquid inlet are both connected to each thrust chamber through a valve.

[0014] Optionally, the two valves connected to each thrust chamber are symmetrically arranged.

[0015] The connecting line between each thrust chamber and the valve connected to the first liquid inlet is parallel to the straight line formed by each thrust chamber and one end of the assembly connected thereto.

[0016] The connecting line between each thrust chamber and the valve connected to the second liquid inlet is parallel to the straight line formed by each thrust chamber and one end connected to the assembly.

[0017] Optionally, the assembly includes: a mounting portion, a first supporting portion and a second supporting portion.

[0018] The number of the mounting parts is consistent with the number of the thrust chambers, and one end of each thrust chamber is mounted on the mounting part.

[0019] The mounting portion is located between the first supporting portion and the second supporting portion which are oppositely arranged.

[0020] Optionally, a first hole structure corresponding to the thrust chambers is formed on the first support portion, and a second hole structure corresponding to the thrust chambers is formed on the second support portion.

[0021] The valves connected to the first liquid inlet are all connected to the first hole structure, and the valves connected to the second liquid inlet are all connected to the second hole structure.

[0022] The installation part is provided with a flow channel communicating with each thrust chamber and the corresponding first hole structure and second hole structure.

[0023] Optionally, the rocket engine also includes: a first pipeline and a second pipeline.

[0024] The first pipeline connects the first liquid inlet and the valve, and the second pipeline connects the second liquid inlet and the valve.

[0025] Optionally, the first pipeline and the second pipeline each include a main pipeline and a branch pipeline that are interconnected.

[0026] The main line of the first pipeline is connected to the first liquid inlet, and the main line of the second pipeline is connected to the second liquid inlet.

[0027] The main path of the first pipeline and the main path of the second pipeline are both parallel to a straight line formed by one end of each thrust chamber connected to the assembly.

[0028] The branches are connected to the valves in a one-to-one correspondence.

[0029] Optionally, the rocket engine also includes: a first tank and a second tank.

[0030] The first storage tank is connected to the first liquid inlet, and the second storage tank is connected to the second liquid inlet.

[0031] In a second aspect, an embodiment of the present application provides a launch vehicle, comprising: a rocket engine as provided in the first aspect above.

[0032] The beneficial technical effects brought about by the technical solution provided in the embodiments of the present application include: at least two groups of thrust chambers are assembled together through an assembly, and multiple thrust chambers in each group of thrust chambers are arranged at angles to each other. The angles of each group of thrust chambers are different, which can provide thrust in all directions and thus provide different control torques. The rocket engine has a simple overall structure, easy installation, high integration, and a relatively concentrated space inside the launch vehicle. It is easy to maintain and can reduce system risks on the basis of achieving diversified control torques.

[0033] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0035] Figure 1 A schematic diagram of the structure of a rocket engine provided in an embodiment of the present application from a top-down perspective;

[0036] Figure 2 A schematic diagram of the structure of a rocket engine provided in an embodiment of the present application from a main perspective;

[0037] Figure 3 A schematic structural diagram of an assembly of rocket engines provided in an embodiment of the present application;

[0038] Figure 4 A schematic diagram of the structure of a launch vehicle provided in an embodiment of the present application. Description of the drawings:

[0040] 100 - rocket engine;

[0041] 11-assembly; 111-mounting portion; 112-first supporting portion; 113-second supporting portion; 1130-second hole structure;

[0042] 12-thrust chamber; 121-first thrust chamber; 122-second thrust chamber; 123-third thrust chamber; 124-fourth thrust chamber;

[0043] 13-valve; 14-first liquid inlet; 15-second liquid inlet;

[0044] 16-first pipeline; 161-main pipeline of the first pipeline 16; 162-branch pipeline of the first pipeline 16;

[0045] 17-second pipeline; 171-main line of the second pipeline 17; 172-branch line of the second pipeline 17;

[0046] α-first angle; β-second angle;

[0047] 200-Launch vehicle body. DETAILED DESCRIPTION

[0048] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0049] Those skilled in the art will appreciate that, unless expressly stated, the singular forms "one", "an", "said" and "the" used herein may also include plural forms. It should be further understood that the term "comprising" used in the specification of the present application refers to the presence of the features, integers, elements and / or components, but does not exclude the implementation of other features, information, data, elements, components and / or combinations thereof supported by the technical field. It should be understood that when we refer to an element as being "connected" or "coupled" to another element, the one element may be directly connected or coupled to the other element, or may refer to the one element and the other element establishing a connection relationship through an intermediate element. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0050] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0051] In the relevant technology, the power system of a launch vehicle includes multiple rocket engines, each of which is independently arranged inside the rocket, and the installation positions are relatively scattered. Each engine needs to be equipped with a thrust chamber, a control system and other components, and each needs to occupy a certain space and reserve a certain working space. This leads to a large number of rocket engine installation structures, a more complex structure, a larger overall space occupation, and a greater system risk.

[0052] The rocket engine and launch vehicle provided in this application are intended to solve the above technical problems of the prior art.

[0053] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0054] The present application embodiment provides a rocket engine 100, the structural schematic diagram of the rocket engine 100 is as follows Figure 1 and Figure 2 As shown, it includes: an assembly 11, at least two groups of thrust chambers 12 and a valve 13.

[0055] Each group of thrust chambers 12 includes at least two thrust chambers 12 that are angled with each other. The angles of different groups of thrust chambers 12 are different. One end of each thrust chamber 12 is fixedly connected to the assembly 11 and is collinear.

[0056] Each thrust chamber 12 is connected to at least one valve 13 via an assembly 11 , and the valve 13 is used to control the flow rate of the propellant flowing into the thrust chamber 12 .

[0057] In this embodiment, the rocket engine 100 includes a plurality of thrust chambers 12, at least two thrust chambers 12 form a group, and at least two groups of thrust chambers 12 are assembled together by an assembly 11. The plurality of thrust chambers 12 in each group of thrust chambers 12 are arranged at angles to each other, and the angles of each group of thrust chambers 12 are different, so that thrust in various directions can be provided, thereby providing different control torques. The rocket engine 100 has a simple overall structure and is easy to install. One end of each thrust chamber 12 is fixedly connected to the assembly 11 and is in the same line. The thrust chambers 12 are arranged horizontally with a high degree of integration. The space occupied inside the launch vehicle is relatively concentrated, and maintenance is easy. The system risk can be reduced on the basis of achieving diversified control torques.

[0058] It can be understood that one ends of the thrust chambers 12 are collinear, that is, the center points of one ends of the thrust chambers are collinear.

[0059] Optionally, in this embodiment, multiple groups of thrust chambers 12 are combined into a combined attitude and orbit control engine, and the power system of the rocket can include multiple combined attitude and orbit control engines, which are arranged inside the launch vehicle as needed.

[0060] Optionally, the propellant includes an oxidizer and a fuel, and the valve 13 can control the flow into the combustion chamber of the thrust chamber 12 , thereby controlling the combustion state of the oxidizer and the fuel, and thereby controlling the torque generated by the thrust chamber 12 .

[0061] The oxidant may be green nitrogen tetroxide; the fuel may be monomethylhydrazine. The present embodiment does not limit the specific types of the oxidant and the fuel, and they may be selected according to actual needs.

[0062] Optionally, when the number of thrust chambers 12 in each group is greater than two, adjacent thrust chambers 12 also form an angle with each other, so as to generate thrusts in different directions. Then, as required, the operation of each thrust chamber 12 or the magnitude of the thrust generated is controlled, so that the entire rocket engine 100 generates the thrust required by the launch vehicle, thereby adjusting the flight attitude.

[0063] Optionally, there are multiple valves 13, and each thrust chamber 12 is connected to at least one valve 13. The structures and functions of all valves 13 are similar, and no distinction is made between them here.

[0064] For some possible implementations, please refer to Figure 1 and Figure 2 , at least two groups of thrust chambers 12 include: a first group of thrust chambers 12 and a second group of thrust chambers 12 .

[0065] The first group of thrust chambers 12 includes a first thrust chamber 121 and a second thrust chamber 122 which form a first angle α with each other.

[0066] The second group of thrust chambers 12 includes a third thrust chamber 123 and a fourth thrust chamber 124 which form a second angle β with each other.

[0067] The first group of thrust chambers 12 is located between the third thrust chamber 123 and the fourth thrust chamber 124 , and the first angle α is smaller than the second angle β.

[0068] In this embodiment, each group of thrust chambers 12 includes two thrust chambers 12, and an angle is formed between the two thrust chambers 12 to form a "V" shape. The two groups of thrust chambers 12 can form two "V" shapes. The two groups of thrust chambers 12 in this embodiment can form a double "V" layout scheme, and four engines in the related art (one thrust chamber 12 includes one engine) are combined into a combined engine, that is, the combined engine includes four thrust chambers 12, the third thrust chamber 123, the first thrust chamber 121, the second thrust chamber 122 and the fourth thrust chamber 124 are arranged in sequence, and the third thrust chamber 123 and the first thrust chamber 121 can be arranged in parallel or have a very small angle, which is determined according to the thrust direction required by the thrust chamber 12. The combined engine in this embodiment has a compact layout, and the assembly 11 combines and fixes the four thrust chambers 12 together, and can also reduce material and weight.

[0069] Optionally, the first angle α can range from 30 degrees to 180 degrees, and the second angle β can also range from 30 degrees to 180 degrees. For example, the first angle α is 60 degrees and the second angle β is 90 degrees. No specific limitation is made here and it can be set according to actual needs.

[0070] In the layout of the thrust chamber 12 of the rocket engine 100 provided in this embodiment, a variety of control schemes can be implemented. For example, the third thrust chamber 123 works alone, the fourth thrust chamber 124 works alone, the third thrust chamber 123 and the first thrust chamber 121 work together, or the second thrust chamber 122 and the fourth thrust chamber 124 work together, all of which can provide rolling or yaw torques, thereby changing the attitude or orbit of the launch vehicle. For another example, the first thrust chamber 121 works alone, the second thrust chamber 122 works alone, the first thrust chamber 121 and the second thrust chamber 122 work together, or the third thrust chamber 123 and the fourth thrust chamber 124 work together, which can provide yaw and pitch torques, thereby changing the attitude or orbit of the launch vehicle. Therefore, when a single thrust chamber 12 works alone or multiple thrust chambers 12 work together, the resultant forces generated are different, thereby realizing a variety of torque control schemes.

[0071] In the related art, each thrust chamber 12 has two liquid inlets for injecting oxidizer and fuel. When a rocket engine 100 includes multiple thrust chambers 12, each thrust chamber 12 must be connected to an oxidizer tank and a fuel tank, and the connecting pipelines are relatively complicated. Therefore, in some possible implementations, please refer to Figure 1 The rocket engine 100 also includes: a first liquid inlet 14 and a second liquid inlet 15.

[0072] The first liquid inlet 14 and the second liquid inlet 15 are both connected to the thrust chambers 12 via valves 13 .

[0073] In this embodiment, the oxidizer inlet of each rocket engine 100 is integrated into a first inlet 14, and the fuel inlet of each rocket engine 100 is integrated into a second inlet 15. The first inlet 14 and the second inlet 15 are respectively connected to the inlet of the valve 13, so that the oxidizer can flow from the first inlet 14 through the valve 13 into the assembly 11 and then into the thrust chamber 12, and the fuel can flow from the second inlet 15 through the valve 13 into the assembly 11 and then into the thrust chamber 12. In this embodiment, no additional propellant pipeline is required, which simplifies the structure and improves the integration.

[0074] Optionally, the axes of the first liquid inlet 14 and the second liquid inlet 15 are consistent with the length direction of the assembly 11, and there is a certain distance between the first liquid inlet 14 and the second liquid inlet 15 and they are independent of each other, avoiding interference caused by the pipelines being too close, which can reduce the complexity of the structure.

[0075] For some possible implementations, please refer to Figure 1 The two valves 13 connected to each thrust chamber 12 are symmetrically arranged.

[0076] The connecting line between each thrust chamber 12 and the valve 13 connected to the first liquid inlet 14 is parallel to the straight line formed by one end of each thrust chamber 12 connected to the assembly 11 .

[0077] The connecting line between each thrust chamber 12 and the valve 13 connected to the second liquid inlet 15 is parallel to the straight line formed by one end of each thrust chamber 12 connected to the assembly 11 .

[0078] In this embodiment, each thrust chamber 12 corresponds to two valves 13, and the two valves 13 are relatively arranged on both sides of the thrust chamber 12. The connection line of the valves 13 is perpendicular to the arrangement direction of the thrust chambers 12, with a reasonable layout and high space utilization.

[0079] For some possible implementations, please refer to Figure 1 and Figure 3 The assembly 11 includes: a mounting portion 111 , a first supporting portion 112 and a second supporting portion 113 .

[0080] The number of the mounting portions 111 is consistent with the number of the thrust chambers 12 , and one end of each thrust chamber 12 is mounted on the mounting portion 111 .

[0081] The mounting portion 111 is located between the first supporting portion 112 and the second supporting portion 113 which are oppositely disposed.

[0082] In this embodiment, the assembly 11 can be regarded as a long strip, the first support portion 112 and the second support portion 113 are both arranged along the length direction of the assembly 11, and the mounting portion 111 is connected between the first support portion 112 and the second support portion 113, and is used to mount and fix the thrust chamber 12. Therefore, one end of each thrust chamber 12 is arranged along the length direction of the first support portion 112 (or the second support portion 113), and this appearance structure of the assembly 11 is convenient for installation inside the rocket, and the working space and accommodation space required for the combined engine provided in this embodiment are convenient for division, and are also convenient for reservation inside the rocket.

[0083] Optionally, the assembly 11 can be made of metal materials such as aluminum.

[0084] Optionally, the number of mounting portions 111 of the assembly 11 corresponds to the number of thrust chambers 12 , and there are hollow spaces between the mounting portions 111 , which can separate the mounting portions 111 , thereby separating the thrust chambers 12 and avoiding impact between the thrust chambers 12 during operation.

[0085] Optionally, the assembly 11 can separate the thrust chamber 12 and the valve 13 , and can provide heat insulation to prevent the valve 13 from being damaged by high heat.

[0086] Optionally, the valve 13 is a solenoid valve.

[0087] Optionally, the assembly 11 may be cast in one piece to facilitate manufacturing.

[0088] For some possible implementations, please refer to Figure 1 and Figure 3 The first support portion 112 is provided with a first hole structure (not shown) corresponding to the thrust chamber 12 . The second support portion 113 is provided with a second hole structure 1130 corresponding to the thrust chamber 12 .

[0089] The valves 13 connected to the first liquid inlet 14 are all connected to the first hole structure (not shown in the figure), and the valves 13 connected to the second liquid inlet 15 are all connected to the second hole structure 1130 .

[0090] The mounting portion 111 has a flow channel (not shown in the figure) in communication with each thrust chamber 12 and the corresponding first hole structure (not shown in the figure) and the second hole structure 1130 .

[0091] In this embodiment, the valve 13, the hole structure on the first support part 112, the mounting part 111 and the oxidant liquid inlet of the thrust chamber 12 are connected in sequence, and the valve 13 can control the amount of oxidant flowing to the hole structure of the first support part 112. The valve 13, the hole structure on the second support part 113, the mounting part 111 and the fuel liquid inlet of the thrust chamber 12 are connected in sequence, and the valve 13 can control the amount of fuel flowing to the hole structure of the second support part 113. The assembly 11 can not only integrate and install the thrust chambers 12 in one body, but also circulate the propellant inside, further reducing the structural complexity of the engine and the number of engine components.

[0092] Optionally, the structures of the first support portion 112 and the second support portion 113 are similar or even identical and can be manufactured simultaneously. The structures of the first hole structure and the second hole structure 1130 are also identical, and the specifications of the valves used in the rocket engine are consistent, which facilitates manufacturing and installation.

[0093] For some possible implementations, please refer to Figure 1 The rocket engine 100 also includes: a first pipeline 16 and a second pipeline 17.

[0094] The first pipeline 16 connects the first liquid inlet 14 and the valve 13 , and the second pipeline 17 connects the second liquid inlet 15 and the valve 13 .

[0095] In this embodiment, each liquid inlet is connected to the valve 13 via a pipeline.

[0096] For some possible implementations, please refer to Figure 1 The first pipeline 16 and the second pipeline 17 each include a main pipeline and a branch pipeline that are interconnected.

[0097] The main path 161 of the first pipeline 16 is connected to the first liquid inlet 14 , and the main path 171 of the second pipeline 17 is connected to the second liquid inlet 15 .

[0098] The main passage 161 of the first pipeline 16 and the main passage 171 of the second pipeline 17 are both parallel to the straight line formed by one end connecting each thrust chamber 12 and the assembly 11 .

[0099] The branches are connected to the valves 13 in a one-to-one correspondence.

[0100] In this embodiment, both the first pipeline 16 and the second pipeline 17 can be hard pipelines with certain stability. The main pipeline 161 of the first pipeline 16 is arranged along the length direction of the assembly 11, and the main pipeline 171 of the second pipeline 17 is also arranged along the length direction of the assembly 11. The branches separated from the main pipeline can be directly connected to the corresponding valve 13, and the layout is compact and reasonable.

[0101] In this embodiment, the branch 162 of the first pipeline 16 is connected to the oxidant liquid inlet of the thrust chamber 12 through a valve, and the branch 172 of the second pipeline 17 is connected to the fuel liquid inlet of the thrust chamber 12 through a valve.

[0102] In some possible implementations, the rocket engine 100 further includes: a first tank and a second tank.

[0103] The first storage tank is connected to the first liquid inlet 14 , and the second storage tank is connected to the second liquid inlet 15 .

[0104] In this embodiment, the first tank is an oxidant tank, and the second tank is a fuel tank, which provide oxidant and fuel to the engine respectively. The combustion in the thrust chamber 12 generates high-temperature and high-pressure gas, which is ejected from the large nozzle to generate thrust.

[0105] Based on the same inventive concept, an embodiment of the present application provides a launch vehicle, including: any rocket engine 100 provided in the above embodiments.

[0106] In this embodiment, the launch vehicle includes any rocket engine 100 provided in the above embodiments, and its implementation principle and specific structure are similar, which will not be described in detail here. Figure 4 As shown, at least one rocket engine 100 may be installed inside the launch vehicle body 200 to perform attitude and orbit control of the launch vehicle.

[0107] By applying the embodiments of the present application, at least the following beneficial effects can be achieved:

[0108] 1. In some embodiments, the rocket engine 100 includes a plurality of thrust chambers 12, at least two thrust chambers 12 form a group, and at least two groups of thrust chambers 12 are assembled together by an assembly 11. The plurality of thrust chambers 12 in each group of thrust chambers 12 are arranged at angles to each other, and the angles of the thrust chambers 12 in each group are different, so that thrusts in various directions can be provided, thereby providing different control torques. The rocket engine 100 has a simple overall structure and is easy to install. One end of each thrust chamber 12 is fixedly connected to the assembly 11 and is collinear. The thrust chambers 12 are arranged horizontally, with a high degree of integration, and the space occupied inside the launch vehicle is relatively concentrated, thereby reducing system risks on the basis of achieving diversified control torques.

[0109] 2. In some embodiments, each group of thrust chambers 12 includes two thrust chambers 12, and an angle is formed between the two thrust chambers 12 to form a "V" shape. The two groups of thrust chambers 12 can form two "V" shapes. The two groups of thrust chambers 12 in this embodiment can form a double "V" layout scheme, and four engines in the related art (one thrust chamber 12 includes one engine) are combined into a combined engine, that is, the combined engine includes four thrust chambers 12, the third thrust chamber 123, the first thrust chamber 121, the second thrust chamber 122 and the fourth thrust chamber 124 are arranged in sequence, and the third thrust chamber 123 and the first thrust chamber 121 can be arranged in parallel or have a very small angle, which is determined according to the thrust direction required by the thrust chamber 12. The combined engine in this embodiment has a compact layout, and the assembly 11 combines and fixes the four thrust chambers 12 together, and can also reduce material and weight.

[0110] 3. In some embodiments, the oxidizer inlet of each rocket engine 100 is integrated into a first inlet 14, and the fuel inlet of each rocket engine 100 is integrated into a second inlet 15. The first inlet 14 and the second inlet 15 are respectively connected to the inlet of the valve 13, so that the oxidizer can flow from the first inlet 14 through the valve 13 into the assembly 11 and then into the thrust chamber 12, and the fuel can flow from the second inlet 15 through the valve 13 into the assembly 11 and then into the thrust chamber 12. In this embodiment, there is no need to set up an additional propellant pipeline, which simplifies the structure and improves the integration.

[0111] 4. In some embodiments, each thrust chamber 12 corresponds to two valves 13, and the two valves 13 are relatively arranged on both sides of the thrust chamber 12. The connecting line of the valves 13 is perpendicular to the arrangement direction of the thrust chambers 12, with a reasonable layout and high space utilization.

[0112] 5. In some embodiments, the assembly 11 can be regarded as a long strip, the first support portion 112 and the second support portion 113 are both arranged along the length direction of the assembly 11, and the mounting portion 111 is connected between the first support portion 112 and the second support portion 113, and is used to mount and fix the thrust chamber 12. Therefore, one end of each thrust chamber 12 is arranged along the length direction of the first support portion 112 (or the second support portion 113), and this appearance structure of the assembly 11 is convenient for installation inside the rocket, and the working space and accommodation space required for the combined engine provided in this embodiment are convenient for division, and are also convenient for reservation inside the rocket.

[0113] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0114] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0115] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0116] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0117] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A rocket engine, characterized in that: include: Assembled pieces; At least two groups of thrust chambers, each group of thrust chambers includes at least two thrust chambers that are angled with each other; the angles of thrust chambers in different groups are different; one end of each thrust chamber is fixedly connected to the assembly and is in a collinear line; each thrust chamber is arranged transversely; Valve, each of the thrust chambers is connected to at least one of the valves through the assembly, and the valve is used to control the flow of the propellant flowing into the thrust chamber.

2. The rocket engine according to claim 1, characterized in that: The at least two groups of thrust chambers include: a first group of thrust chambers and a second group of thrust chambers; The first group of thrust chambers includes a first thrust chamber and a second thrust chamber that form a first angle with each other; The second group of thrust chambers includes a third thrust chamber and a fourth thrust chamber which form a second angle with each other; The first group of thrust chambers is located between the third thrust chamber and the fourth thrust chamber, and the first angle is smaller than the second angle.

3. The rocket engine according to claim 2, characterized in that: Also includes: a first liquid inlet and a second liquid inlet; The first liquid inlet and the second liquid inlet are both connected to the respective thrust chambers through the valves.

4. The rocket engine according to claim 3, characterized in that: The two valves connected to each thrust chamber are symmetrically arranged; A connecting line between each of the thrust chambers and the valve connected to the first liquid inlet is parallel to a straight line formed by one end of each of the thrust chambers connected to the assembly; A connecting line between each of the thrust chambers and the valve connected to the second liquid inlet is parallel to a straight line formed by one end of each of the thrust chambers connected to the assembly.

5. The rocket engine according to claim 3, characterized in that: The assembly comprises: a mounting portion, a first supporting portion and a second supporting portion; The number of the mounting parts is consistent with the number of the thrust chambers, and one end of each thrust chamber is mounted on the mounting part; The mounting portion is located between the first supporting portion and the second supporting portion which are oppositely arranged.

6. The rocket engine according to claim 5, characterized in that: The first support portion is provided with a first hole structure corresponding to the thrust chamber in a one-to-one manner; the second support portion is provided with a second hole structure corresponding to the thrust chamber in a one-to-one manner; The valves connected to the first liquid inlet are all connected to the first hole structure, and the valves connected to the second liquid inlet are all connected to the second hole structure; The mounting portion has a flow channel in communication with each of the thrust chambers and the correspondingly connected first hole structure and second hole structure.

7. The rocket engine according to claim 3, characterized in that: The rocket engine further comprises: a first pipeline and a second pipeline; The first pipeline connects the first liquid inlet and the valve, and the second pipeline connects the second liquid inlet and the valve.

8. The rocket engine according to claim 7, characterized in that: The first pipeline and the second pipeline each include a main pipeline and a branch pipeline that are interconnected; The main line of the first pipeline is connected to the first liquid inlet, and the main line of the second pipeline is connected to the second liquid inlet; The main path of the first pipeline and the main path of the second pipeline are both parallel to the straight line formed by one end of each thrust chamber connected to the assembly; The branches are connected to the valves in a one-to-one correspondence.

9. The rocket engine according to claim 8, characterized in that: The rocket engine also includes: a first tank and a second tank; The first storage tank is connected to the first liquid inlet, and the second storage tank is connected to the second liquid inlet.

10. A launch vehicle, characterized in that: include: A rocket engine as described in any one of claims 1-9 above.

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