Attitude control cabin and carrier of space launch vehicle

Abstract

The present invention provides an attitude control cabin of a space vehicle, comprising: a cylindrical attitude control cabin, wherein four quadrants of the attitude control cabin are respectively provided with a forward thrust attitude control engine and two lateral thrust attitude control engines, wherein the forward thrust attitude control engine is provided at the lower half of the cabin wall along the first axial direction of the attitude control cabin, and the two lateral thrust attitude control engines are provided at the upper half of the cabin wall of the attitude control cabin and are located at both sides above the forward thrust attitude control engine. The attitude control cabin can make good use of the space of the attitude control cabin and meet the layout requirements of the attitude control cabin.

Description

Technical Field

[0001] The present invention relates to the field of space vehicle structure layout, and in particular to an attitude control cabin of a space vehicle and a vehicle. Background Art

[0002] In order to complete the orbit entry and attitude control, the last stage of the space vehicle needs to set up a power system in the attitude control cabin to perform three-channel auxiliary control of the pitch, yaw and roll of the space vehicle. The existing power system layout cannot fully utilize the space in the attitude control cabin. For the attitude control engine with a larger appearance, there is no suitable layout solution for installing it in the small diameter attitude control cabin. The layout method of the attitude control engine in the existing technology cannot guarantee the control arm of the attitude control engine and cannot fully utilize the space in the attitude control cabin.

[0003] In view of this, there is an urgent need to design an attitude control cabin and a carrier of a space vehicle that can fully utilize the space of the attitude control cabin and can ensure the control arm of the attitude control engine. Summary of the invention

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and to provide an attitude control cabin of a space vehicle and a vehicle.

[0005] The present invention provides an attitude control cabin of a space vehicle, comprising: a cylindrical attitude control cabin, wherein four quadrants of the attitude control cabin are respectively provided with a forward thrust attitude control engine and two lateral thrust attitude control engines, the forward thrust attitude control engine is arranged at the lower half of the cabin wall along the first axial direction of the attitude control cabin, and the two lateral thrust attitude control engines are arranged at the upper half of the cabin wall of the attitude control cabin and are located on both sides above the forward thrust attitude control engine.

[0006] According to one embodiment of the present invention, the two side thrust attitude control engines are staggered in the first direction.

[0007] According to one embodiment of the present invention, the orthographic projections of the two thrust attitude control engines partially overlap in the first direction.

[0008] According to one embodiment of the present invention, the two side thrust attitude control engines face opposite directions and the thrust chambers of the engines face the outside of the bulkhead.

[0009] According to one embodiment of the present invention, a sleeve is provided outside the thrust chamber of the two side thrust attitude control engines, and the sleeve extends to the through hole of the bulkhead.

[0010] According to one embodiment of the present invention, the bulkhead through hole of the attitude control cabin is arranged to be elliptical in the direction corresponding to the thrust chamber of each of the side thrust attitude control engines.

[0011] According to one embodiment of the present invention, the thrust chamber of the forward thrust attitude control engine faces the lower port of the attitude control cabin.

[0012] According to one embodiment of the present invention, the minimum distance between the axis of the side thrust attitude control engine and the axis of the attitude control cabin is a first distance, the maximum distance between the axis of the side thrust attitude control engine and the bulkhead of the attitude control cabin in the quadrant is a second distance, and the first distance is greater than the second distance.

[0013] According to one embodiment of the present invention, the propellant pipelines of the forward thrust attitude control engine and the side thrust engine are arranged in a ring along the bulkhead of the attitude control cabin and avoid other engines.

[0014] On the other hand, the present invention provides a space vehicle, characterized in that it includes the attitude control cabin of the above-mentioned space vehicle.

[0015] The attitude control cabin of the space vehicle of the present invention adopts a layout in which a forward thrust attitude control engine is arranged in the lower half of the cabin wall along the first axial direction of the attitude control cabin, and two side thrust attitude control engines are arranged in the upper half of the cabin wall of the attitude control cabin and are located on both sides above the forward thrust attitude control engine. This layout can better utilize the space of the attitude control cabin and meet the layout requirements of the attitude control cabin to save space and ensure the control arm. There is no need to increase the diameter of the attitude control cabin, thereby avoiding an increase in the weight of the attitude control cabin.

[0016] It should be understood that the above general description and the following detailed description are merely exemplary and illustrative and are not intended to limit the scope of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The following drawings are a part of the specification of the present invention, and illustrate exemplary embodiments of the present invention. Together with the description of the specification, the accompanying drawings are used to explain the principles of the invention.

[0018] Figure 1 is a schematic diagram of an attitude control cabin of a space vehicle according to an embodiment of the present invention;

[0019] Figure 2 yes Figure 1 Top view of the .

[0020] Reference numerals:

[0021] 100-attitude control cabin, 101-through hole, 200-forward thrust attitude control engine, 300-lateral thrust attitude control engine. DETAILED DESCRIPTION

[0022] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and are used to illustrate the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the sizes of some structural components or areas in the drawings may be enlarged for other structural components or areas to help understand the embodiments of the present invention.

[0023] The directional words appearing in the following description are all 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 "installation", "connection" and "connection" 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 ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0024] In addition, the terms "include", "comprise", "have" or any other variations thereof are intended to cover non-exclusive inclusion, so that a structure or component including a series of elements includes not only those elements, but also other mechanical elements that are not explicitly listed or inherent in the structure or component. In the absence of more restrictions, the elements defined by the sentence "include..." do not exclude the existence of other identical elements in the article or device including the elements.

[0025] Spatially related terms such as "below", "beneath", "under", "low", "above", "on", "high", etc. are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device in addition to orientations different from those shown in the figures. In addition, for example, "one element is above / below another element" can mean that the two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first", "second", etc. are also used to describe various elements, regions, parts, etc., and should not be regarded as limiting. Similar terms represent similar elements throughout the description.

[0026] 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 intended to provide a better understanding of the present invention by showing examples of the present invention.

[0027] Figure 1 is a schematic diagram of an attitude control cabin of a space vehicle according to an embodiment of the present invention; Figure 2 yes Figure 1 Top view of the .

[0028] like Figure 1 and 2 As shown, the present invention provides an attitude control cabin of a space vehicle, comprising: a cylindrical attitude control cabin 100, wherein four quadrants of the attitude control cabin 100 are respectively provided with a forward thrust attitude control engine 200 and two lateral thrust attitude control engines 300, the forward thrust attitude control engine 200 is arranged at the lower half of the cabin wall along the first axial direction of the attitude control cabin 100, and the two lateral thrust attitude control engines 300 are arranged at the upper half of the cabin wall of the attitude control cabin 100 and are located on both sides above the forward thrust attitude control engine 200.

[0029] Specifically, the last stage of the solid-propellant carrier rocket in the space launch vehicle has a power system arranged in the attitude control cabin 100 due to the need for orbital accuracy and attitude control. The layout of the power system of this embodiment in the attitude control cabin 100 adopts an "8+4" attitude control engine nozzle scheme, that is, eight side thrust attitude control engines 300 and four forward thrust attitude control engines 200 are arranged on the cabin wall of the attitude control cabin 100, and the eight side thrust attitude control engines 300 form four pairs, two by two, arranged in four quadrants.

[0030] The first direction is the axial direction of the attitude control cabin 100, the forward thrust attitude control engine 200 is arranged in the lower half of the bulkhead along the first direction, and the two side thrust attitude control engines 300 are arranged in the upper half of the bulkhead of the attitude control cabin 100 and are located on both sides above the forward thrust attitude control engine 200. In the present application, the upper half and lower half of the bulkhead of the attitude control cabin 100 refer to the orientation of the space vehicle during launch or flight, that is, the upper and lower orientations corresponding to the space vehicle (for example, a launch vehicle) standing at the launch site with its head facing up and its tail facing down, and the position of the attitude control engine is not affected by other placement methods of the attitude control cabin 100.

[0031] As the requirements for the final stage control capability of solid-propellant carrier rockets or weapon systems in space launch vehicles increase, the thrust of the side-thrust attitude control engine 300 needs to be increased, while the solid-propellant carrier rockets or weapon systems have the requirement for miniaturization of the final stage, resulting in the existing attitude control cabin 100 layout scheme being increasingly unable to meet the layout requirements of large side-thrust attitude control engines 300 and compact small-diameter attitude control cabins 100.

[0032] The layout of the attitude control cabin 100 in the embodiment of the present invention can meet the layout requirements of the large side thrust attitude control engine 300 in the compact small-diameter attitude control cabin 100, which not only avoids the significant increase in the difficulty of development caused by reducing the volume of the attitude control engine, but also meets the requirements of the compact attitude control cabin 100 for small diameter design, thereby realizing the miniaturization of the solid carrier rocket last stage or the weapon system last stage of the space launch vehicle.

[0033] like Figure 2As shown, according to one embodiment of the present invention, two side thrust attitude control engines 300 are staggered in the first direction.

[0034] According to one embodiment of the present invention, the orthographic projections of the two thruster attitude control engines 300 in the first direction partially overlap, for example, the orthographic projections of the heads of the two thruster attitude control engines in the first direction partially overlap.

[0035] Specifically, for the layout of the nozzles of the large thruster attitude control engines 300 in the small diameter attitude control cabin 100, if a pair of thruster attitude control engines 300 do not adopt the layout method of staggered and overlapping in the first direction, in order to meet the space for their relative layout, the nozzle axes of the thruster attitude control engines 300 in the quadrant can only be moved away from the attitude control cabin wall to leave space for accommodating the pair of thruster attitude control engines 300. However, this will greatly shorten the rolling channel force arm, reduce the control efficiency, and even make the layout impossible due to structural interference.

[0036] According to the size of the thruster attitude control engine 300, the diameter of the attitude control cabin 100, and the convenience of the pipeline layout, the distance between the pair of thruster attitude control engines 300 in the quadrant can be staggered up and down in the axial direction of the attitude control cabin 100, i.e., in the first direction, and the range of the orthographic projection overlap of the two thruster attitude control engines 300 in the first direction can be changed and adjusted. Any one of the pair of thruster attitude control engines 300 in this embodiment can make full use of the space of the attitude control cabin 100 body, and is no longer restricted by the total length being too long when the pair of thruster attitude control engines 300 are arranged oppositely and the insufficient space in the attitude control cabin 100, so as to save space and ensure the control lever arm.

[0037] Among them, the larger the side thrust attitude control engine 300 is arranged in the smaller diameter attitude control cabin 100, the staggered distance of a pair of side thrust attitude control engines 300 in the quadrant in the axial direction of the attitude control cabin 100 can be appropriately increased, and at the same time, the overlapping range of the positive projections of the two side thrust attitude control engines 300 in the first direction can be increased to meet the requirements of spatial layout, ensure the distance between the axis of the side thrust attitude control engine 300 and the axis of the attitude control cabin 100, and ensure the control efficiency of the rolling channel.

[0038] According to one embodiment of the present invention, the two thrust attitude control engines 300 face opposite directions and the thrust chambers of the engines face the outside of the bulkhead.

[0039] According to one embodiment of the present invention, sleeves are provided outside the thrust chambers of the two thrust attitude control engines 300, and the sleeves extend to the through holes 101 of the bulkhead.

[0040] According to one embodiment of the present invention, the bulkhead through hole 101 of the attitude control cabin 100 corresponds to the thrust chamber orientation direction of each thruster attitude control engine 300 and is arranged in an elliptical shape.

[0041] Specifically, the two side thrust attitude control engines 300 face oppositely in the quadrants and the thrust chambers of the engines face the outside of the cabin wall. The nozzles of a pair of attitude control engines on each quadrant face opposite directions. The three-channel control of the final stage pitch, yaw and roll of the space vehicle is achieved through different combinations of opening and closing of the side thrust attitude control engines 300.

[0042] In order to protect the thrust chamber of the thrust attitude control engine 300 and prevent its operation from affecting the attitude control cabin 100, a sleeve is provided outside the thrust chamber of the thrust attitude control engine 300, and the sleeve extends to the through hole 101 of the bulkhead, and the thrust attitude control engine 300 is installed in a closed manner in the sleeve. According to the layout of each pair of thrust attitude control engines 300, the through hole 101 of the bulkhead of the attitude control cabin 100 is arranged to be elliptical in the direction of the thrust chamber of each thrust attitude control engine 300, and the sleeve is extended to the through hole 101 to achieve closed installation.

[0043] The present invention is suitable for the layout of a large thrust attitude control engine 300 and a compact small-diameter attitude control cabin 100, and realizes three-channel control of the pitch, yaw and roll of the last stage of the space vehicle through different combinations of opening and closing the thrust attitude control engine 300. No major adjustment is required to the existing mature attitude control algorithm and control logic, and the invention has good inheritance and engineering feasibility.

[0044] According to one embodiment of the present invention, the thrust chamber of the forward thrust attitude control engine 200 faces the lower port of the attitude control cabin 100. The forward thrust attitude control engine 200 provides power to achieve forward propulsion of the space vehicle, so the thrust chamber of the forward thrust attitude control engine 200 faces the lower port of the attitude control cabin 100, realizing the layout of the engine in the compact small-diameter attitude control cabin 100.

[0045] According to one embodiment of the present invention, the minimum distance between the axis of the side thrust attitude control engine 300 and the axis of the attitude control cabin 100 is a first distance, and the maximum distance between the axis of the side thrust attitude control engine 300 and the wall of the attitude control cabin 100 in the quadrant is a second distance, and the first distance is greater than the second distance.

[0046] Specifically, the minimum distance between the axis of the thrust attitude control engine 300 and the axis of the attitude control cabin 100 is the first distance, that is, the vertical distance between the middle position of a pair of thrust attitude control engines 300 overlapping and the axis of the attitude control cabin 100; the maximum distance between the axis of the thrust attitude control engine 300 and the wall of the attitude control cabin 100 in the quadrant is the second distance, that is, the vertical distance between the middle position of a pair of thrust attitude control engines 300 overlapping and the wall of the attitude control cabin 100; wherein the first distance is greater than the second distance. This layout can greatly reduce the distance between the axis of the thrust attitude control engine 300 and the wall of the attitude control cabin 100, increase the distance between the axis of the thrust attitude control engine 300 and the axis of the attitude control cabin 100, improve the control efficiency of the rolling channel, and provide a layout solution for the attitude control cabin 100, especially for situations where the layout cannot be arranged due to structural interference.

[0047] According to one embodiment of the present invention, the propellant pipelines of the forward thrust attitude control engine 200 and the side thrust engine are arranged in a ring along the bulkhead of the attitude control cabin 100 and avoid other engines.

[0048] Specifically, the propellants of the forward thrust attitude control engine 200 and the lateral thrust engine are liquid propellants, wherein the propellant pipelines of the forward thrust attitude control engine 200 and the lateral thrust engine are arranged in a ring along the inner wall of the attitude control cabin 100 and avoid other engines. The forward thrust attitude control engine 200, the lateral thrust attitude control engine 300 and their propellant pipelines constitute a liquid auxiliary power system, which can meet the layout requirements of the small-diameter attitude control cabin 100.

[0049] The above embodiments can be combined with each other and have corresponding technical effects.

[0050] On the other hand, the present invention provides a space vehicle, characterized in that it includes the above-mentioned attitude control cabin 100 of the space vehicle. The space vehicle in this embodiment includes the above-mentioned attitude control cabin 100 of the space vehicle, and its technical effects are not described in detail here.

[0051] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An attitude control cabin of a space vehicle, characterized in that: include: A cylindrical attitude control cabin, wherein four quadrants of the attitude control cabin are respectively provided with a forward thrust attitude control engine and two lateral thrust attitude control engines, the forward thrust attitude control engine is arranged at the lower half of the bulkhead along the first axial direction of the attitude control cabin, and the two lateral thrust attitude control engines are arranged at the upper half of the bulkhead of the attitude control cabin and are located on both sides above the forward thrust attitude control engine; The two side thrust attitude control engines are staggered in the first direction; and the orthographic projections of the two side thrust attitude control engines in the first direction partially overlap.

2. The attitude control cabin of a space vehicle according to claim 1, characterized in that: The two side thrust attitude control engines face oppositely and the thrust chambers of the engines face the outside of the bulkhead.

3. The attitude control cabin of a space vehicle according to claim 2, characterized in that: A sleeve is arranged on the outer side of the thrust chamber of the two side thrust attitude control engines, and the sleeve extends to the through hole of the bulkhead.

4. The attitude control cabin of a space vehicle according to claim 3, characterized in that: The through hole in the bulkhead of the attitude control cabin corresponds to the direction of the thrust chamber of each of the side thrust attitude control engines and is arranged in an elliptical shape.

5. The attitude control cabin of a space vehicle according to claim 1, characterized in that: The thrust chamber of the forward thrust attitude control engine faces the lower port of the attitude control cabin.

6. The attitude control cabin of a space vehicle according to claim 1, characterized in that: The minimum distance between the axis of the side thrust attitude control engine and the axis of the attitude control cabin is a first distance, and the maximum distance between the axis of the side thrust attitude control engine and the bulkhead of the attitude control cabin in the quadrant is a second distance, and the first distance is greater than the second distance.

7. The attitude control cabin of a space vehicle according to claim 1, characterized in that: The propellant pipelines of the forward thrust attitude control engine and the side thrust attitude control engine are arranged in a ring along the bulkhead of the attitude control cabin and avoid other engines.

8. A space launch vehicle, characterized in that: Comprising an attitude control cabin of a space vehicle as described in any one of claims 1-7.

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