Open circulation liquid oxygen kerosene rocket engine structure

Abstract

The invention belongs to the field of rocket engines, and particularly relates to an open circulation liquid oxygen kerosene rocket engine structure. Comprising five or seven engines. The engine comprises a thrust chamber and a turbine pump mounted on the thrust chamber; wherein one engine serves as a middle extension, and a thrust chamber of the engine is installed in the middle of the outer rack; the other engines serve as edge extension sets, and thrust chambers of the edge extension sets are evenly installed on the outer rack in the circumferential direction with the axis of the thrust chamber of the middle extension set as the center; a thrust chamber of each engine is connected with a servo driving end of an external servo mechanism; the turbine pump of the middle extension is located between any two adjacent edge extensions in the circumferential direction, and the distances between the axis of the turbine pump and the axes of the two adjacent edge extensions are equal. According to the invention, a 3.35 m rocket body diameter five-aircraft layout can be realized, the take-off thrust of the rocket is increased by 25% compared with an original four-aircraft layout, and the method can be suitable for a 3.8 m rocket body seven-aircraft layout.

Description

Technical Field

[0001] The invention relates to a rocket engine, in particular to an open cycle liquid oxygen-kerosene rocket engine structure. Background Art

[0002] The open-cycle liquid oxygen-kerosene rocket engine has the advantages of simple system, low working pressure of the post-pump components, high thrust-to-weight ratio, non-toxic and pollution-free, and reusable.

[0003] See also Figure 1 The first-stage rocket engine usually uses four engines in parallel to provide flight power for the rocket. Specifically, the thrust chambers 1 of the four engines are evenly installed on the external frame 02 along the circumferential direction, the turbo pump 22 is installed on the thrust chamber 1, and the servo drive end of the external servo mechanism 01 is connected to the thrust chamber 1. Each engine is driven by the external servo mechanism 01 to swing and combine to provide flight control force for the rocket.

[0004] However, with the continuous development of the aerospace industry, the thrust requirements for rockets are becoming higher and higher. The existing four-engine parallel engine layout has been unable to meet the needs of large-thrust rockets due to the small number of engines and low thrust. Therefore, it is urgent to install more engines within a certain rocket body diameter to further enhance the rocket's carrying capacity and application range. Summary of the invention

[0005] The purpose of the present invention is to solve the technical problem that the existing four-engine parallel engine layout structure has a small thrust and is difficult to meet the needs of large-thrust rockets, and to provide an open-cycle liquid oxygen-kerosene rocket engine structure.

[0006] To achieve the above purpose, the technical solution adopted by the present invention is:

[0007] An open cycle liquid oxygen-kerosene rocket engine structure, which is special in that:

[0008] The invention comprises five or seven engines; the engines comprise a thrust chamber and a turbo pump mounted on the thrust chamber;

[0009] One of the engines is used as a middle extension, and its thrust chamber is installed in the middle position of the outer frame;

[0010] The remaining engines are all used as edge extensions, and their thrust chambers are evenly mounted on the outer frame along the circumferential direction with the axis of the thrust chamber of the middle extension as the center;

[0011] The thrust chambers of each engine are respectively connected to the servo drive end of the external servo mechanism, each edge extension is used to swing tangentially along a respective set swing plane under the drive of the external servo mechanism, and the middle extension is used to swing along a set direction under the drive of the external servo mechanism;

[0012] Define the virtual circle enclosed by the axes of all edge extension thrust chambers as the installation circle, and the tangent plane between the axial mid-section of each edge extension thrust chamber and the installation circle is the respective set swing plane;

[0013] The axis of each of the edge branch turbine pumps is located in the corresponding swing plane, and the turbine pumps of each edge branch are located on the same side of the corresponding thrust chamber along the circumferential direction;

[0014] The turbine pump of the middle branch is located between any two edge branches adjacent to each other in the circumferential direction, and the axis of the turbine pump is equidistant from the axes of the two adjacent edge branches.

[0015] Further, the engine also includes an oxidant main valve, a fuel main valve, a fuel isolation valve, a gimbal, a heat exchanger, an exhaust pipe, an oxygen swing hose and a fuel swing hose;

[0016] The turbo pump comprises an oxidant pump, a fuel pump and a turbine which are connected in sequence in a coaxial form;

[0017] The turbo pump is mounted on one side of the thrust chamber via a pump mounting frame, and the connection between the servo drive end of the external servo mechanism and the thrust chamber is located on the other side of the thrust chamber opposite to the turbo pump;

[0018] The inlet of the oxidant pump is connected to the rocket body delivery pipeline through an oxygen swing hose, and the outlet of the oxidant pump is connected to the oxidant main valve through an oxygen main conduit. The oxidant main valve is installed on the top of the thrust chamber through a bearing seat; the gimbal is installed on the top of the bearing seat, and is used to connect with the external frame to transmit the swing thrust during swinging;

[0019] The inlet of the fuel pump is connected to the rocket fuel pipeline through the S transition pipe, the fuel swing hose, and the fuel isolation valve in sequence; the outlet of the fuel pump is connected to the thrust chamber through the fuel pump rear pipeline 1, the fuel main valve, and the fuel pump rear pipeline 2 in sequence, and the fuel main valve is installed on the pump mounting frame;

[0020] The heat exchanger is installed on the outlet ring of the turbine, and the exhaust pipe is installed at the outlet of the heat exchanger.

[0021] Further, the axis of the fuel swing hose passes through the swing center of the gimbal;

[0022] There is a 90° angle between the inlet and outlet of the oxidant main valve, the first pipeline after the fuel pump is provided with a 90° bend, and the second pipeline after the fuel pump is S-shaped.

[0023] Furthermore, the exhaust pipe is a Laval pipe.

[0024] Furthermore, an angle of 5° to 10°, preferably 7°, is set between the axial direction of the exhaust pipe and the axial direction of the thrust chamber.

[0025] Further, the engine also includes a gas generator, an oxidant auxiliary valve, an oxygen auxiliary check valve, a fuel auxiliary valve, a control electric gas valve, a blow-off electric gas valve, a thrust chamber igniter, a generator igniter and a gunpowder starter;

[0026] The gas generator is vertically mounted on the intake ring of the turbine, the fuel auxiliary valve is mounted on the top of the gas generator, and the fuel auxiliary valve is connected to the rear pipeline of the fuel pump through the fuel auxiliary conduit and the fuel auxiliary throttling assembly in sequence;

[0027] The oxygen auxiliary check valve is installed on the top of the gas generator, the oxidant auxiliary valve is installed on the oxygen main conduit, and the oxygen auxiliary check valve is connected to the oxidant auxiliary valve through the oxygen auxiliary conduit and the oxygen auxiliary throttling assembly in sequence;

[0028] The thrust chamber igniter is vertically fixed on the body of the thrust chamber, the generator igniter is installed on the top of the gas generator, and the gunpowder starter is installed on the intake ring of the turbine; the control electric gas valve and the blow-off electric gas valve are installed on the pump mounting frame, the control electric gas valve is respectively connected to the oxidant main valve, the fuel main valve, the oxidant auxiliary valve and the fuel auxiliary valve, and the blow-off electric gas valve is respectively connected to the gas generator and the thrust chamber head.

[0029] Furthermore, the main oxygen conduit is a π-shaped conduit.

[0030] The beneficial effects of the present invention are:

[0031] 1. The present invention can realize a 5-engine layout with a 3.35m rocket body diameter, which increases the take-off thrust of the rocket by 25% compared with the original 4-engine layout, so that the carrying capacity of the second-stage rocket covers the carrying capacity of the original three-stage rocket. In addition, the engine can adapt to the 7-engine layout of the 3.8m rocket body. The engine has multiple starts and continuously variable thrust functions, can realize the vertical landing and recovery of a sub-stage, and has the ability to be reused.

[0032] 2. The layout structure of the present invention has the advantages of fewer system components, small envelope space and good processability. The oxygen auxiliary system does not need to be precooled, eliminating the oxygen auxiliary precooling return pipeline. The ignition conduit is arranged after the fuel main valve, eliminating the one-way valve with high opening pressure difference and the ignition path purge valve. The oxygen main conduit is π-shaped, the conduit is easy to file and repair, and has strong adaptability to the assembly position. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a schematic diagram of the structure of the first-stage rocket engine with an existing four-engine layout;

[0034] Figure 2 is a schematic diagram of the structure of a five-machine layout in an embodiment of the present invention;

[0035] Figure 3 is a schematic diagram of the structure of the seven-machine layout in an embodiment of the present invention;

[0036] Figure 4 is a schematic structural diagram of an engine in an embodiment of the present invention;

[0037] Figure 5 yes Figure 4 Top view of the .

[0038] In the figure:

[0039] 01-servo mechanism, 02-frame;

[0040] 1-thrust chamber, 2-gas generator, 3-oxidizer pump, 4-fuel pump, 5-turbine, 6-oxidizer main valve, 7-oxidizer sub-valve, 8-oxygen sub-check valve, 9-fuel main valve, 10-fuel sub-valve, 11-fuel isolation valve, 12-control electric gas valve, 13-purge electric gas valve, 14-thrust chamber igniter, 15-generator igniter, 16-propellant starter, 17-heat exchanger, 18-oxygen swing hose, 19-fuel swing hose, 20-level seat, 21-exhaust pipe, 22-turbine pump, 23-S transition pipe, 24-load bearing seat, 25-oxygen main pipe, 26-fuel pump rear pipeline 1, 27-fuel pump rear pipeline 2, 28-fuel sub-pipe, 29-fuel sub-throttle assembly, 30-oxygen sub-pipe, 31-oxygen sub-throttle assembly. DETAILED DESCRIPTION

[0041] In order to make the purpose, advantages and features of the present invention clearer, the structure of an open-cycle liquid oxygen-kerosene rocket engine proposed by the present invention is further described in detail below in combination with the accompanying drawings and specific embodiments. According to the following specific implementation methods, the advantages and features of the present invention will be clearer. It should be noted that: the drawings are all in a very simplified form and are not in precise proportions, which are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention; secondly, the structure shown in the drawings is often a part of the actual structure.

[0042] See also Figure 2 and Figure 3 , this embodiment is an open cycle liquid oxygen-kerosene rocket engine structure, including five or seven engines.

[0043] For details, see Figure 4 and Figure 5The engine mainly includes a thrust chamber 1, an oxidizer pump 3, a fuel pump 4, a turbine 5, an oxidizer main valve 6, a fuel main valve 9, a fuel isolation valve 11, a gimbal 20, a heat exchanger 17, an exhaust pipe 21, an oxygen swing hose 18, a fuel swing hose 19, a gas generator 2, an oxidizer auxiliary valve 7, an oxygen auxiliary check valve 8, a fuel auxiliary valve 10, a fuel isolation valve 11, a control electric gas valve 12, a blow-off electric gas valve 13, a thrust chamber igniter 14, a generator igniter 15 and a gunpowder starter 16, etc.

[0044] Among them, the oxidant pump 3, the fuel pump 4 and the turbine 5 are connected in sequence in a coaxial form to form a turbine pump 22.

[0045] The turbopump 22 is installed on one side of the thrust chamber 1 through a pump mounting frame, and the connection between the servo drive end of the external servo mechanism 01 and the thrust chamber 1 is located on the other side of the thrust chamber 1 opposite to the turbopump 22, so that the thrust chamber 1 (i.e., the engine) is driven to swing through the servo drive end, thereby realizing the flight control of the rocket.

[0046] The inlet of the oxidizer pump 3 is connected to the rocket body delivery pipeline through the oxygen swing hose 18. The connection between the oxygen swing hose 18 and the rocket body delivery pipeline is rigidly fixed to prevent the rocket body delivery pipeline and the engine pipeline from generating force and displacement interference. After the rocket is filled with liquid oxygen, the oxygen circuit precooling begins. The outlet of the oxidizer pump 3 is connected to the oxidizer main valve 6 through the oxygen main conduit 25. The oxidizer main valve 6 is installed on the top of the thrust chamber 1 through the bearing seat 24. There is a 90° angle between the inlet and outlet of the oxidizer main valve 6; the gimbal 20 is installed on the top of the bearing seat 24 and connected to the external frame 02 to achieve thrust transmission, thereby meeting the swing requirements between the thrust chamber 1 and the frame 02.

[0047] The inlet of the fuel pump 4 is connected to the rocket fuel pipeline in sequence through the S transition pipe 23, the fuel swing hose 19, and the fuel isolation valve 11. The axis of the fuel swing hose 19 passes through the swing center of the gimbal 20, so that the fuel swing hose 19 only needs to compensate for the angular displacement, and the fuel isolation valve 11 can isolate the fuel path of the engine and the rocket. The outlet of the fuel pump 4 is connected to the thrust chamber 1 in sequence through the fuel pump rear pipeline 1 26, the fuel main valve 9, and the fuel pump rear pipeline 2 27. The fuel main valve 9 is installed on the pump mounting frame. The fuel pump rear pipeline 1 26 is provided with a 90° bend, and the fuel pump rear pipeline 2 27 is S-shaped.

[0048] The heat exchanger 17 and the exhaust pipe 21 constitute an exhaust unit, wherein the heat exchanger 17 is mounted on the outlet ring of the turbine 5, and the exhaust pipe 21 is mounted at the outlet of the heat exchanger 17. The exhaust pipe 21 is a Laval tube, so that the work of the turbine 5 is not affected by the atmospheric altitude. At the same time, an angle of about 5° to 10° is set between the axial direction of the exhaust pipe 21 and the axial direction of the thrust chamber 1. In the present embodiment, the angle is specifically 7°. The exhaust gas of the turbine 5 is directly discharged to the outside, and the exhaust device has a simple structure.

[0049] The gas generator 2 is vertically mounted on the intake ring of the turbine 5, and the fuel auxiliary valve 10 is mounted on the top of the gas generator 2. The fuel auxiliary valve 10 is connected to the fuel pump rear pipeline 26 through the fuel auxiliary conduit 28 and the fuel auxiliary throttling assembly 29.

[0050] The oxygen auxiliary check valve 8 is installed on the top of the gas generator 2, and the oxidant auxiliary valve 7 is installed on the oxygen main conduit 25. The oxygen main conduit 25 is π-shaped and is pre-cooled through the main line. There is no need to set up a pre-cooling return line. The oxygen auxiliary check valve 8 is connected to the oxidant auxiliary valve 7 through the oxygen auxiliary conduit 30 and the oxygen auxiliary throttling assembly 31.

[0051] The thrust chamber igniter 14 is vertically fixed on the body of the thrust chamber 1 to shorten the length of the igniter pipeline. The generator igniter 15 is installed on the top of the gas generator 2 in a vertical layout. The gunpowder starter 16 is installed on the intake ring of the turbine 5. The control electric gas valve 12 and the blow-off electric gas valve 13 are installed on the pump mounting frame. The control electric gas valve 12 is respectively connected to the oxidant main valve 6, the fuel main valve 9, the oxidant sub-valve 7 and the fuel sub-valve 10, and the blow-off electric gas valve 13 is respectively connected to the gas generator 2 and the head of the thrust chamber 1.

[0052] One of the engines is used as a middle extension, and its thrust chamber 1 is installed in the middle position of the external frame 02; the remaining engines are used as edge extensions, and their thrust chambers 1 are evenly installed on the external frame 02 along the circumferential direction with the axis of the middle extension thrust chamber 1 as the center, and the axis of the middle extension is equidistant from the axes of the two adjacent edge extensions.

[0053] The thrust chamber 1 of each engine is connected to the servo drive end of the external servo mechanism 01, and each edge extension performs tangential swing along its own preset swing plane under the drive of the servo mechanism 01. The virtual circle surrounded by the axes of all edge extension thrust chambers 1 is defined as the installation circle, and the tangent plane between the axial mid-section of each edge extension thrust chamber 1 and the installation circle is the set swing plane; the axis of the oxygen swing hose 18 in the edge extension is located in the swing plane.

[0054] The middle extension swings along the set direction under the drive of the external servo mechanism 01. Specifically, the middle extension swings in the quadrant plane. The quadrant plane here refers to the Figure 2 or Figure 3In the example, the axis of the middle extension is taken as the center origin, the line connecting any two edge extensions through the center origin is taken as the X axis, and the straight line passing through the center origin and perpendicular to the X axis is taken as the Y axis. At this time, the X axis and Y axis are about to Figure 2 and Figure 3 The plane is divided into four quadrants, and the middle extension swings within the four quadrants.

[0055] The axis of each edge extension turbine pump 22 is located in the corresponding swing plane, and the turbine pump 22 of each edge extension is located on the same side of the respective thrust chamber 1 along the circumferential direction; the turbine pump 22 of the middle extension is located between any two edge extensions adjacent to each other along the circumferential direction, and the flight control force can be provided for the rocket by swinging the edge extension and the middle extension.

Claims

1. An open cycle liquid oxygen-kerosene rocket engine structure, characterized in that: The invention comprises five or seven engines; the engines comprise a thrust chamber (1) and a turbine pump (22) mounted on the thrust chamber (1); One of the engines is used as a middle extension, and its thrust chamber (1) is installed in the middle position of the outer frame (02); The remaining engines are all used as edge extensions, and their thrust chambers (1) are evenly mounted on the outer frame (02) along the circumferential direction with the axis of the middle extension thrust chamber (1) as the center; The thrust chambers (1) of each engine are respectively connected to the servo drive end of the external servo mechanism (01), each edge extension is used to swing tangentially along a respective set swing plane under the drive of the external servo mechanism (01), and the middle extension is used to swing along a set direction under the drive of the external servo mechanism (01); The virtual circle enclosed by the axes of all the edge extension thrust chambers (1) is defined as the installation circle, and the tangent plane between the axial mid-section of each edge extension thrust chamber (1) and the installation circle is the respective set swing plane; The axis of each of the edge branch turbine pumps (22) is located in a corresponding swing plane, and the turbine pumps (22) of each edge branch are located on the same side of the corresponding thrust chamber (1) along the circumferential direction; The turbine pump (22) of the middle branch is located between any two edge branches adjacent to each other in the circumferential direction, and its axis is equidistant from the axes of the two adjacent edge branches.

2. The open cycle liquid oxygen-kerosene rocket engine structure according to claim 1, characterized in that: The turbine pump (22) is installed on one side of the thrust chamber (1) via a pump mounting frame, and the connection between the servo drive end of the external servo mechanism (01) and the thrust chamber (1) is located on the other side of the thrust chamber (1) opposite to the turbine pump (22); The engine further comprises an oxidant main valve (6), a fuel main valve (9), a fuel isolation valve (11), a gimbal (20), a heat exchanger (17), an exhaust pipe (21), an oxygen swing hose (18) and a fuel swing hose (19); The turbo pump (22) comprises an oxidant pump (3), a fuel pump (4) and a turbine (5) which are coaxially connected in sequence; The inlet of the oxidant pump (3) is connected to the arrow body delivery pipeline through the oxygen swing hose (18), and the outlet of the oxidant pump (3) is connected to the oxidant main valve (6) through the oxygen main conduit (25). The oxidant main valve (6) is installed on the top of the thrust chamber (1) through the bearing seat (24); the gimbal (20) is installed on the top of the bearing seat (24) and is used to connect with the external frame (02) to transmit the swing thrust during swinging; The inlet of the fuel pump (4) is connected to the rocket fuel pipeline in sequence through the S transition pipe (23), the fuel swing hose (19), and the fuel isolation valve (11); the outlet of the fuel pump (4) is connected to the thrust chamber (1) in sequence through the fuel pump rear pipeline 1 (26), the fuel main valve (9), and the fuel pump rear pipeline 2 (27), and the fuel main valve (9) is installed on the pump mounting frame; The heat exchanger (17) is installed on the outlet ring of the turbine (5), and the exhaust pipe (21) is installed at the outlet of the heat exchanger (17).

3. The open cycle liquid oxygen-kerosene rocket engine structure according to claim 2, characterized in that: The axis of the fuel swing hose (19) passes through the swing center of the gimbal (20); The inlet and outlet of the oxidant main valve (6) have an angle of 90°, the fuel pump rear pipeline (26) is provided with a 90° bend, and the fuel pump rear pipeline (27) is S-shaped.

4. The open cycle liquid oxygen-kerosene rocket engine structure according to claim 3, characterized in that: The exhaust pipe (21) is a Laval pipe.

5. The open cycle liquid oxygen-kerosene rocket engine structure according to claim 4, characterized in that: An included angle of 5° to 10° is set between the axial direction of the exhaust pipe (21) and the axial direction of the thrust chamber (1).

6. The open cycle liquid oxygen-kerosene rocket engine structure according to claim 5, characterized in that: An included angle of 7° is set between the axial direction of the exhaust pipe (21) and the axial direction of the thrust chamber (1).

7. An open cycle liquid oxygen-kerosene rocket engine structure according to claim 6, characterized in that: The engine further comprises a gas generator (2), an oxidant auxiliary valve (7), an oxygen auxiliary check valve (8), a fuel auxiliary valve (10), a control electric gas valve (12), a blow-off electric gas valve (13), a thrust chamber igniter (14), a generator igniter (15) and a gunpowder starter (16); The gas generator (2) is vertically mounted on the intake ring of the turbine (5), the fuel auxiliary valve (10) is mounted on the top of the gas generator (2), and the fuel auxiliary valve (10) is connected to the fuel pump rear pipeline 1 (26) through the fuel auxiliary conduit (28) and the fuel auxiliary throttle assembly (29) in sequence; The oxygen auxiliary check valve (8) is installed on the top of the gas generator (2), the oxidant auxiliary valve (7) is installed on the oxygen main conduit (25), and the oxygen auxiliary check valve (8) is connected to the oxidant auxiliary valve (7) in sequence through the oxygen auxiliary conduit (30) and the oxygen auxiliary throttling assembly (31); The thrust chamber igniter (14) is vertically fixed to the body of the thrust chamber (1), the generator igniter (15) is installed on the top of the gas generator (2), and the gunpowder starter (16) is installed on the intake ring of the turbine (5); the control electric gas valve (12) and the blow-off electric gas valve (13) are installed on the pump mounting frame, the control electric gas valve (12) is respectively connected to the oxidant main valve (6), the fuel main valve (9), the oxidant auxiliary valve (7) and the fuel auxiliary valve (10), and the blow-off electric gas valve (13) is respectively connected to the gas generator (2) and the head of the thrust chamber (1).

8. The open cycle liquid oxygen-kerosene rocket engine structure according to claim 7, characterized in that: The main oxygen conduit (25) is a π-shaped conduit.

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