Final-stage attitude control power system and liquid rocket

Abstract

The utility model provides a final-stage attitude control power system and a liquid rocket. The final-stage attitude control power system at least comprises N attitude control power units symmetrically distributed on the outer surface of a rocket body and an attitude control engine fairing, the attitude control power units are installed on the separation face of the rocket body through supports and do not exceed the separation face, and the attitude control engine fairing is installed on the windward faces of the attitude control power units. The number N and the positions of the attitude control power units can be adjusted according to the attitude control requirement of the rocket body, but it needs to be guaranteed that the attitude control engine units are evenly and symmetrically distributed on the outer surface of the cabin wall of the rocket body, so that the rocket body is prevented from losing stability in the attitude adjusting process. According to the attitude control power system, the moment arm of the attitude control engine arranged on the outer side of the cabin wall of the rocket body is lengthened, the control moment is increased, and the attitude control efficiency of the rocket body is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of space launch vehicles, in particular to a terminal attitude control power system and a liquid rocket. Background Art

[0002] To improve the orbital injection accuracy of a launch vehicle, attitude control engines are generally arranged around the main engine at the terminal stage of the rocket. The main functions of the attitude control engines are as follows: First, during the flight stage of the terminal stage of the rocket, it provides the control force for the roll of the rocket body. If the main engine does not have the functions of pitch and yaw, the attitude control engine also needs to provide the control forces for pitch, yaw, and roll. Second, during the coasting stage of the terminal stage of the rocket, it provides the propellant sedimentation force and the control forces for pitch, yaw, and roll of the rocket body. Third, it corrects the final velocity when the rocket enters the orbit and deactivates the rocket body from the orbit.

[0003] At present, the attitude control engines on launch vehicles are generally arranged on the inner wall of the rocket body. This arrangement structure reduces the protrusions on the rocket body surface, and the rocket body has a good aerodynamic shape during flight. However, there are the following problems: First, since the attitude control engines are arranged on the inner wall of the rocket body, due to the large number of attitude control engines, it occupies the space on the inner wall of the rocket body, resulting in the elongation of the rocket body structure and an increase in the rocket body weight. Second, with the attitude control engines arranged on the inner wall of the rocket body, under the premise of a certain engine thrust, the provided control torque is small and the efficiency is low. Third, since the attitude control engines are arranged on the inner wall of the rocket body, it is necessary to lead the plume of the engine to the outside of the rocket body through a sleeve, resulting in a relatively high temperature of the sleeve and the rocket wall near the sleeve, and strict heat protection treatment is required. Summary of the Utility Model

[0004] To solve the above technical problems, the utility model provides a terminal attitude control power system and a liquid rocket. By arranging the attitude control engines on the outer surface of the rocket body, the length of the rocket body is significantly shortened, the weight of the rocket body is reduced, the heat radiation of the attitude control engines to the rocket body cabin wall is reduced, and the overall structural layout of the rocket body is optimized.

[0005] On the one hand, the utility model provides a terminal attitude control power system, which at least includes: N attitude control power units symmetrically distributed on the outer surface of the rocket body and an attitude control engine fairing; each of the attitude control power units is respectively installed on the separation surface of the rocket body through a bracket and does not exceed the separation surface, and the attitude control engine fairing is installed on the windward side of each of the attitude control power units;

[0006] Wherein, N is an even number and greater than or equal to 4.

[0007] In an embodiment, each of the attitude control power units at least includes: a first side spray attitude control engine, a sedimentation attitude control engine, and a second side spray attitude control engine sequentially arranged on one side of the bracket; the nozzle of the sedimentation attitude control engine is arranged towards the tail of the rocket; the nozzles of the first side spray attitude control engine and the second side spray attitude control engine are respectively arranged towards two tangential directions of the rocket body.

[0008] In one embodiment, looking up at the rocket body, four of the brackets are installed at the positions of the four quadrant lines thereof, and each of the brackets is respectively provided with the attitude control power unit;

[0009] In the clockwise direction along the rocket body, the four attitude control power units include: a first side jet attitude control engine, a first bottom-mounted attitude control engine, a second side jet attitude control engine, a third side jet attitude control engine, a second bottom-mounted attitude control engine, a fourth side jet attitude control engine, a fifth side jet attitude control engine, a third bottom-mounted attitude control engine, a sixth side jet attitude control engine, a seventh side jet attitude control engine, a fourth bottom-mounted attitude control engine, and an eighth side jet attitude control engine;

[0010] The first bottom-mounted attitude control engine, the second bottom-mounted attitude control engine, the third bottom-mounted attitude control engine, and the fourth bottom-mounted attitude control engine are used to provide the propellant sinking force for the sliding section of the rocket's upper stage and the final velocity correction for the rocket to enter and leave the orbit;

[0011] The first side jet attitude control engine, the second side jet attitude control engine, the fifth side jet attitude control engine, and the sixth side jet attitude control engine are used to control the yaw of the rocket body;

[0012] The third side jet attitude control engine, the fourth side jet attitude control engine, the seventh side jet attitude control engine, and the eighth side jet attitude control engine are used to control the pitch of the rocket body;

[0013] The first side jet attitude control engine, the third side jet attitude control engine, the fifth side jet attitude control engine, and the seventh side jet attitude control engine are used to control the clockwise roll of the rocket body;

[0014] The second side jet attitude control engine, the fourth side jet attitude control engine, the sixth side jet attitude control engine, and the eighth side jet attitude control engine are used to control the counterclockwise roll of the rocket body.

[0015] In one embodiment, the attitude control power unit at least includes: a first side jet attitude control engine, a bottom-mounted attitude control engine, and a second side jet attitude control engine that are sequentially arranged on the bracket;

[0016] The nozzle of the bottom-mounted attitude control engine is arranged facing the tail of the rocket; the nozzles of the first side jet attitude control engine and the second side jet attitude control engine are arranged in opposite directions, and the axis of the nozzle of the first side jet attitude control engine forms an angle of X° with the rocket body section where the bottom-mounted attitude control engine is located, and the axis of the nozzle of the second side jet attitude control engine forms an angle of X° with the rocket body section where the bottom-mounted attitude control engine is located;

[0017] Wherein the value range of X is from 13 to 18.

[0018] In the above embodiment, the value of X is 15.

[0019] In one embodiment, the nozzle axis of the bottom-mounted attitude control engine forms an angle of Y° with the rocket body axis;

[0020] wherein the value range of Y is from 9 to 11.

[0021] In the above embodiment, the value of Y is 10.

[0022] In one embodiment, the attitude control engine bracket is formed by 3D printing of titanium alloy.

[0023] In one embodiment, the bracket is provided with weight-reducing holes.

[0024] On the other hand, the present utility model provides a liquid rocket, which at least includes the final-stage attitude control power system described in any one of the above embodiments.

[0025] The final-stage attitude control power system and the liquid rocket provided by the present utility model at least have one of the following beneficial effects:

[0026] First, for the final-stage attitude control power system and the liquid rocket of the present utility model, by arranging each attitude control engine outside the rocket body, the length of the rocket body is effectively shortened and the weight of the rocket body is reduced. After the attitude control engine is arranged outside the rocket body, the force arm becomes longer and the control torque increases, improving the attitude control efficiency of the rocket body.

[0027] Second, for the final-stage attitude control power system and the liquid rocket of the present utility model, the nozzle orientation of each attitude control engine can be adjusted according to the engine thrust and the magnitude of the heat flux, reducing the heat radiation and heat erosion to the rocket body wall surface and making the heat protection work simpler.

[0028] Third, the installation of the final-stage attitude control power system of the present utility model is simple, the overall structural layout is concise, and the later maintenance is more convenient.

[0029] After reading the specific implementation manners and viewing the drawings, those skilled in the art will recognize additional features and advantages. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present utility model, and those of ordinary skill in the art can also obtain other drawings based on these drawings without creative efforts.

[0031] Figure 1 It is a schematic diagram of the overall structure of the attitude control power system according to an embodiment of the present utility model.

[0032] Figure 2 It is a schematic diagram of the outer side of the rocket cabin wall according to an embodiment of the present utility model.

[0033] Figure 3 It is the first structural schematic diagram of the attitude control power unit of the embodiment of the present utility model.

[0034] Figure 4 It is the second structural schematic diagram of the attitude control power unit of the embodiment of the present utility model.

[0035] Figure 5 It is the structural schematic diagram of the bracket of the embodiment of the present utility model.

[0036] Figure 6 It is the structural schematic diagram of the side jet attitude control engine of the embodiment of the present utility model.

[0037] Figure 7 It is the structural schematic diagram of the bottom-mounted attitude control engine of the embodiment of the present utility model.

[0038] Explanation of reference numerals:

[0039] 1. Rocket body; 11. Separation surface; 2. Attitude control power unit; 3. Attitude control engine fairing; 4. Bracket; 41. Weight reduction hole; 42. First mounting hole; 43. Second mounting hole; P1. First side jet attitude control engine; P2. Second side jet attitude control engine; P3. Third side jet attitude control engine; P4. Fourth side jet attitude control engine; P5. Fifth side jet attitude control engine; P6. Sixth side jet attitude control engine; P7. Seventh side jet attitude control engine; P8. Eighth side jet attitude control engine; P10. First bottom-mounted attitude control engine; P11. Second bottom-mounted attitude control engine; P12. Third bottom-mounted attitude control engine; P13. Fourth bottom-mounted attitude control engine. Detailed implementation manners

[0040] The features and exemplary embodiments of various aspects of the present utility model will be described in detail below. In order to make the purpose, technical solutions and advantages of the present utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present utility model, for exemplarily illustrating the principle of the present utility model, and are not configured to limit the present utility model. Additionally, the components in the drawings are not necessarily drawn to scale. For example, the dimensions of some components or regions in the drawings may be enlarged for other components or regions to help understand the embodiments of the present utility model.

[0041] The orientation terms used in the following description are all the directions shown in the figures, and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that unless otherwise specified, the terms "installed", "connected", and "coupled" 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 directly connected, or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0042] In addition, the terms "comprise", "include", "have" or any other variants thereof are intended to cover non-exclusive inclusion, so that a structure, component or assembly including a series of elements not only includes those elements, but also includes other elements that are not explicitly listed or are inherent to the structure, component. Without more limitations, the elements defined by the statement "comprising..." do not exclude the existence of additional identical elements in the article or device including the elements.

[0043] Spatial relationship terms such as "below", "beneath", "under", "lower", "above", "over", "upper" etc. are used to facilitate description to explain the positioning of one element relative to a second element, and these terms are intended to cover different orientations of the device in addition to the orientations different from those shown in the figures. Additionally, for example, "one element is on / under another element" can mean that the two elements are in direct contact, or can also mean that there are other elements between the two elements. Furthermore, terms such as "first", "second" etc. are also used to describe each element, region, part etc., and should not be regarded as limiting. Similar terms indicate similar elements throughout the description.

[0044] For those skilled in the art, the present invention can be implemented without some of these specific details. The following description of the embodiments is only provided to provide a better understanding of the present invention by showing examples of the present invention.

[0045] At the same time, referring to Figure 1 , Figure 2 and Figure 3 , on the one hand, the present invention provides a final-stage attitude control power system, which at least includes N attitude control power units 2 symmetrically distributed on the outer surface of the rocket body 1 and an attitude control engine fairing 3. Each attitude control power unit 2 is respectively installed on the separation surface 11 of the bulkhead of the rocket body 1 through a bracket 4 and does not extend beyond the separation surface 11, and the attitude control engine fairing 3 is installed on the windward surface of each attitude control power unit 2. N in this embodiment is an even number and greater than or equal to 4.

[0046] In this embodiment, by installing a posture control engine fairing 3 on the windward side of the attitude control power unit 2, on the one hand, it provides a good aerodynamic shape for the flight of the rocket body, reducing the flight resistance of the rocket body, and on the other hand, it provides a good working environment for each attitude control engine unit.

[0047] In this embodiment, the number and position of the attitude control power units can be adjusted according to the attitude control requirements of the rocket body, but it is necessary to ensure that the attitude control engine units are evenly and symmetrically distributed on the outer surface of the rocket body cabin wall to prevent the rocket body from becoming unstable during the attitude adjustment process. In the attitude control power system of the present application, the lever arm of the attitude control engine arranged outside the rocket body cabin wall becomes longer, and the control torque increases, improving the attitude control efficiency of the rocket body.

[0048] In addition, for the attitude control power system of the last stage of this embodiment, by installing the axial position of the attitude control engine at the separation surface of the rocket body and not exceeding the separation surface, on the one hand, it can prevent the rocket body from hitting the attitude control engine during separation, and on the other hand, it can reduce the influence of the plume heat radiation of the bottom-mounted engine in each attitude control engine unit on the rocket wall.

[0049] In one embodiment, each attitude control power unit 2 at least includes a first side spray attitude control engine P1, a first bottom spray attitude control engine P10, and a second side spray attitude control engine P2 that are sequentially arranged on the bracket 4. The nozzle of the first bottom spray attitude control engine P10 is arranged facing the tail of the rocket, and the nozzles of the first side spray attitude control engine P1 and the second side spray attitude control engine P2 are respectively arranged facing the two tangential directions of the rocket body.

[0050] For the attitude control power system of the last stage of this embodiment, by installing three attitude control engines (one bottom spray and two side sprays) on the bracket, the structural efficiency of the bracket and the overall assembly efficiency are improved, the number of protrusions is reduced, and the rocket body structure is made more concise and compact.

[0051] See Figure 1 , in one embodiment, looking up at the rocket body, four brackets are installed at the positions of its four quadrant lines, and an attitude control power unit 2 is respectively arranged on each bracket. Specifically, in the clockwise direction along the rocket body ( Figure 1In the direction indicated by the arrow in the figure, the four attitude control power units include: the first side jet attitude control engine P1, the first bottom-mounted attitude control engine P10, the second side jet attitude control engine P2, the third side jet attitude control engine P3, the second bottom-mounted attitude control engine P11, the fourth side jet attitude control engine P4, the fifth side jet attitude control engine P5, the third bottom-mounted attitude control engine P12, the sixth side jet attitude control engine P6, the seventh side jet attitude control engine P7, the fourth bottom-mounted attitude control engine P13, and the eighth side jet attitude control engine P8. Among them, the first bottom-mounted attitude control engine P10, the second bottom-mounted attitude control engine P11, the third bottom-mounted attitude control engine P12, and the fourth bottom-mounted attitude control engine P13 are used to provide the propellant sinking force for the rocket's upper stage glide section and the final velocity correction for the rocket's orbit insertion and orbit departure; the first side jet attitude control engine P1, the second side jet attitude control engine P2, the fifth side jet attitude control engine P5, and the sixth side jet attitude control engine P6 are used to control the yaw of the rocket body; the third side jet attitude control engine P3, the fourth side jet attitude control engine P4, the seventh side jet attitude control engine P7, and the eighth side jet attitude control engine P8 are used to control the pitch of the rocket body; the first side jet attitude control engine P1, the third side jet attitude control engine P3, the fifth side jet attitude control engine P5, and the seventh side jet attitude control engine P7 are used to control the clockwise roll of the rocket body; the second side jet attitude control engine P2, the fourth side jet attitude control engine P4, the sixth side jet attitude control engine P6, and the eighth side jet attitude control engine P8 are used to control the counterclockwise roll of the rocket body.

[0052] Furthermore, in the above embodiment, side jet attitude control engines can be added according to the attitude control requirements of the rocket body, and their positions can be adjusted according to the structure of the rocket body. Also, the number of bottom-mounted attitude control engines can be increased or decreased according to the attitude control requirements of the rocket body, but it is necessary to ensure the symmetrical distribution of the same type of attitude control engines to avoid the instability of the rocket body during the attitude adjustment process.

[0053] In any of the above embodiments, in order to reduce the thermal radiation of the plume from each attitude control engine to the rocket body wall surface, the angle between the nozzle axis of the bottom-mounted attitude control engine in each attitude control power unit and the rocket body axis can be set, and the nozzle axes of the two side jet attitude control engines can be respectively set to form an angle with the rocket body radius.

[0054] See Figure 4 , for example, each attitude control power unit at least includes: the third side jet attitude control engine P3, the second bottom-mounted attitude control engine P11, and the fourth side jet attitude control engine P4, which are sequentially arranged on the bracket 4.

[0055] Among them, the nozzle of the second bottom-mounted attitude control engine P11 is arranged towards the arrow tail, and the axis of the nozzle of the second bottom-mounted attitude control engine P11 forms an angle of Y° with the axis of the arrow body, and the value range of Y is 9 to 11. The nozzles of the third side-mounted attitude control engine P3 and the fourth side-mounted attitude control engine P4 are arranged in opposite directions, and the axis of the nozzle of the third side-mounted attitude control engine P3 forms an angle of X° with the arrow body section where the second bottom-mounted attitude control engine P11 is located, and the axis of the nozzle of the fourth side-mounted attitude control engine P4 forms an angle of X° with the arrow body section where the second bottom-mounted attitude control engine P11 is located, and the value range of X is 13 to 18.

[0056] For the attitude control power system of the last stage in this embodiment, the nozzle orientation and angle of each attitude control engine can be adjusted according to the engine thrust and heat flux, so that the heat protection of the arrow body wall can be omitted or aluminized films can be pasted at the positions with large heat flux, making the heat protection of the arrow body wall simpler.

[0057] Furthermore, the smaller the values of X and Y in this embodiment, the higher the efficiency of the attitude control engine and the greater the thermal radiation to the arrow body; while the larger the values of X and Y, the smaller the thermal radiation of the attitude control engine to the arrow body, but the lower the efficiency. After multiple tests, the test results are the best when X takes the value of 15 and Y takes the value of 10 in the above embodiment.

[0058] Since the thrust of the attitude control engine is small, the bracket can be 3D printed with high-temperature-resistant titanium alloy, which can not only reduce the heat protection work of the bracket, but also reduce the manufacturing cost and lighten the weight of the bracket.

[0059] See also Figure 5 、 Figure 6 and Figure 7 , in order to further reduce the weight of the bracket 4, a plurality of weight-reducing holes 41 can be arranged at appropriate positions of the bracket 4. In addition, the bracket 4 is provided with two first mounting holes 42 for mounting side-mounted attitude control engines, and a second mounting hole 43 for mounting bottom-mounted attitude control engines is arranged between the two first mounting holes 42. After the bracket 4 is mounted on the outer side of the arrow body cabin wall, the axis of the second mounting hole 43 forms an angle of Y° with the axis of the arrow body, and the axis of the first mounting hole 42 is parallel to the axis of the arrow body. Figure 6 After the side-mounted attitude control engine in is mounted in the two first mounting holes 42, the side jet requirement is realized by using the nozzle orientation of the side-mounted attitude control engine. Figure 7 After the bottom-mounted attitude control engine in is mounted in the second mounting hole 43, the spray direction requirement of the bottom-mounted attitude control engine is realized by using the opening angle of the second mounting hole 43 relative to the axis of the arrow body.

[0060] In this embodiment, Figure 6 is a schematic structural diagram of the side-mounted attitude control engine, Figure 7 is a schematic structural diagram of the bottom-mounted attitude control engine. Therefore, those skilled in the art should understand that according toFigure 6 It is possible to simultaneously understand the specific structures of the first side jet attitude control engine P1, the second side jet attitude control engine P2, the third side jet attitude control engine P3, the fourth side jet attitude control engine P4, the fifth side jet attitude control engine P5, the sixth side jet attitude control engine P6, the seventh side jet attitude control engine P7, and the eighth side jet attitude control engine P8; according to Figure 7 It is possible to simultaneously understand the specific structures of the first bottom-mounted attitude control engine P10, the second bottom-mounted attitude control engine P11, the third bottom-mounted attitude control engine P12, and the fourth bottom-mounted attitude control engine P13.

[0061] The above embodiments can be combined with each other and have corresponding technical effects.

[0062] The present utility model also provides a liquid rocket, which at least includes the end-stage attitude control power system in any one of the above embodiments.

[0063] For the end-stage attitude control power system and the liquid rocket of the present utility model, the end-stage attitude control engines of the rocket body are arranged on the outer wall of the rocket body, without occupying the inner wall space of the rocket body, shortening the length of the rocket body and reducing the weight of the rocket body. In addition, for the end-stage attitude control power system of the present utility model, after arranging the end-stage attitude control engines on the outside of the rocket body, the lever arm becomes longer and the control torque increases, improving the efficiency of rocket body attitude control. Additionally, after the attitude control engines are arranged on the outside of the rocket body and are far from the rocket wall, the rocket body may not need to be heat-protected or only need to be appropriately heat-protected. For medium and large liquid rockets, the flight speed of the rocket body is relatively low, and the requirements for the aerodynamic shape of the rocket body are not high. A fairing can be installed on the windward side of the attitude control engine to reduce the flight resistance of the rocket body and protect the attitude control engine.

[0064] The above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A final-stage attitude control power system, characterized in that, At least including: N attitude control power units and an attitude control engine fairing symmetrically distributed on the outer surface of the rocket body; each of the attitude control power units is respectively mounted on the separation surface of the rocket body through a bracket and does not exceed the separation surface, and the attitude control engine fairing is mounted on the windward side of each of the attitude control power units; wherein, N is an even number and greater than or equal to 4.

2. The final attitude control power system according to claim 1, characterized in that, Each of the attitude control power units at least includes: a first side jet attitude control engine, a bottom-mounted attitude control engine, and a second side jet attitude control engine sequentially arranged on the first side of the bracket; The nozzle of the bottom-mounted attitude control engine is arranged towards the rocket tail; the nozzles of the first side jet attitude control engine and the second side jet attitude control engine are respectively arranged towards two tangential directions of the rocket body.

3. The final attitude control power system according to claim 2, characterized in that, Looking up at the rocket body, 4 of the brackets are installed at the positions of its four quadrant lines, and each of the brackets is respectively provided with the attitude control power unit; In the clockwise direction along the rocket body, the four attitude control power units include: a first side jet attitude control engine, a first bottom-mounted attitude control engine, a second side jet attitude control engine, a third side jet attitude control engine, a second bottom-mounted attitude control engine, a fourth side jet attitude control engine, a fifth side jet attitude control engine, a third bottom-mounted attitude control engine, a sixth side jet attitude control engine, a seventh side jet attitude control engine, a fourth bottom-mounted attitude control engine, and an eighth side jet attitude control engine; The first bottom-mounted attitude control engine, the second bottom-mounted attitude control engine, the third bottom-mounted attitude control engine, and the fourth bottom-mounted attitude control engine are used to provide the propellant bottom force for the sliding section of the rocket's upper stage and the final velocity correction for the rocket to enter and leave the orbit; The first side jet attitude control engine, the second side jet attitude control engine, the fifth side jet attitude control engine, and the sixth side jet attitude control engine are used to control the yaw of the rocket body; The third side jet attitude control engine, the fourth side jet attitude control engine, the seventh side jet attitude control engine, and the eighth side jet attitude control engine are used to control the pitch of the rocket body; The first side jet attitude control engine, the third side jet attitude control engine, the fifth side jet attitude control engine, and the seventh side jet attitude control engine are used to control the clockwise roll of the rocket body; The second side jet attitude control engine, the fourth side jet attitude control engine, the sixth side jet attitude control engine, and the eighth side jet attitude control engine are used to control the counterclockwise roll of the rocket body.

4. The final attitude control power system according to claim 1, characterized in that, Each of the attitude control power units at least includes: a first side jet attitude control engine, a bottom-mounted attitude control engine, and a second side jet attitude control engine sequentially arranged on the first side of the bracket; The nozzle of the bottom-mounted attitude control engine is arranged towards the rocket tail; The nozzles of the first side jet attitude control engine and the second side jet attitude control engine are arranged in opposite directions, and the axis of the nozzle of the first side jet attitude control engine forms an angle of X° with the rocket body section where the bottom-mounted attitude control engine is located, and the axis of the nozzle of the second side jet attitude control engine forms an angle of X° with the rocket body section where the bottom-mounted attitude control engine is located; where the value range of X is 13 to 18.

5. The final attitude control power system according to claim 4, characterized in that, The value of X is 15.

6. The final attitude control power system according to claim 2 or 4, characterized in that, The axis of the nozzle of the bottom-mounted attitude control engine forms an angle of Y° with the axis of the rocket body; where the value range of Y is 9 to 11.

7. The final attitude control power system according to claim 6, wherein The value of Y is 10.

8. The final attitude control power system according to claim 1, characterized in that, The bracket is formed by 3D printing of titanium alloy.

9. The final attitude control power system according to claim 2, characterized in that The bracket is provided with weight reduction holes.

10. A liquid rocket, characterized in that, At least including the upper stage attitude control power system according to any one of claims 1 to 9.

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