Orbital Transfer Vehicle

Abstract

The present application discloses an orbital transfer aircraft. The orbital transfer aircraft includes: a main body structure, including side walls and a bottom plate, the bottom plate is connected to the second end of the side wall, and the side wall and the bottom plate enclose a cavity; electrical equipment is installed in the cavity, and the electrical equipment includes an electric energy storage module and a control module; a load adapter plate is installed at the first end, and the load transported by the orbital transfer aircraft is installed on the side of the load adapter plate away from the side wall; at least one solar panel is connected to the side wall and installed outside the cavity, and at least one solar panel is connected to the electric energy storage module; at least one propellant tank is connected to the side wall and installed outside the cavity; a rendezvous and docking module is connected to the side wall and installed outside the cavity; at least one attitude control engine group is connected to the side wall and installed outside the cavity; and a change-of-orbit engine is installed on the bottom plate. Thereby, the flexibility of the orbital transfer aircraft is improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace engineering, and more specifically, to an orbital transfer vehicle. Background Art

[0002] An orbit transfer vehicle is a device used to transfer a spacecraft from one orbit to another. It is mainly used in scenarios such as satellite deployment, deep space exploration, and on-orbit services in space missions. For example, it can transfer a satellite from low-Earth orbit to geosynchronous orbit, or perform longer-distance planetary exploration missions. The widespread use of orbit transfer vehicles has promoted the development of global satellite deployment, deep space exploration, and on-orbit services, and will play an important role in more commercial space and scientific exploration missions in the future.

[0003] Current orbital transfer vehicles are mainly used to transfer spacecraft from Earth orbit to higher orbits or further into space. Most of these orbital transfer vehicles are large and heavy, relying on huge propulsion systems and complex structural designs. These orbital transfer vehicles are complex in structure and large in size, and are not suitable for orbital transfer missions of spacecraft such as small satellites.

[0004] Therefore, how to improve the flexibility of orbital transfer vehicles becomes a technical problem that needs to be solved in this field. Summary of the invention

[0005] In view of this, the present application proposes an orbital transfer aircraft to improve the flexibility of the orbital transfer aircraft.

[0006] According to the present application, an orbital transfer aircraft is proposed, which includes: a main body structure, including side walls and a bottom plate, the side wall including a first end and a second end, the bottom plate and the second end are connected, and the side wall and the bottom plate form a cavity; electrical equipment is installed in the cavity, the electrical equipment includes an electric energy storage module and a control module; a load adapter plate is installed at the first end of the side wall, the plane where the load adapter plate is located is perpendicular to the axis of the main body structure, and the load transported by the orbital transfer aircraft is installed on the side of the load adapter plate away from the side wall; at least one solar panel is connected to the side wall and installed outside the cavity, and the at least one solar panel is connected to the electric energy storage module; at least one propellant tank is connected to the side wall and installed Installed outside the cavity, the at least one propellant tank is distributed around the side wall and close to the side of the load adapter plate away from the load; a rendezvous and docking module is connected to the side wall and installed outside the cavity, the rendezvous and docking module is electrically connected to the power storage module and the control module respectively and connected to the propellant tank through a pipeline; at least one attitude control engine group is connected to the side wall and installed outside the cavity, the at least one attitude control engine group is electrically connected to the power storage module and the control module respectively and connected to the propellant tank through a pipeline; and a trajectory change engine is installed on the bottom plate and installed outside the cavity, the trajectory change engine is electrically connected to the power storage module and the control module respectively and connected to the propellant tank through a pipeline.

[0007] Optionally, the orbital transfer vehicle further includes: at least one bracket connected to the side wall, and the at least one solar panel, at least one propellant tank, the rendezvous and docking module, and the at least one attitude control engine group are mounted on the bracket to be connected to the side wall.

[0008] Optionally, the at least one bracket comprises a plurality of brackets, and the plurality of brackets are arranged in sequence around the side wall.

[0009] Optionally, each propellant tank is mounted on two supports.

[0010] Optionally, the center of the bracket is in the same plane as the center of the propellant tank.

[0011] Optionally, the shape of the propellant tank is one of the following: a sphere, an ellipsoid, or a cylinder.

[0012] Optionally, the rendezvous and docking module and the solar panel are installed on different brackets.

[0013] Optionally, the cross-section of the main body structure is circular.

[0014] Optionally, the axis of the trajectory change engine, the axis of the load adapter plate and the axis of the main body structure coincide with each other.

[0015] Optionally, along a direction perpendicular to the load adapter plate, a top view of the load adapter plate has a polygonal shape.

[0016] According to the technical solution of the present application, a main body structure is provided, the electrical equipment is installed in the cavity of the main body structure, the load adapter plate is installed at the first end of the side wall, the solar panels, the propellant tank, the rendezvous and docking module, and the attitude control engine are connected to the side wall of the main body structure, the orbit change engine is installed on the bottom plate, and the propellant tank is distributed around the side wall, so that the distribution of the components included in the orbit transfer aircraft is relatively concentrated, the size of the orbit transfer aircraft is reduced, the miniaturization of the orbit transfer aircraft is achieved, and the flexibility of the orbit transfer aircraft is improved. According to the technical solution of the present application, the components are arranged based on the main body structure, the structure is simple, and the structure of the orbit transfer aircraft is simplified. By simplifying the structure and achieving miniaturization, the orbit transfer aircraft can be applied to the orbit transfer mission of spacecraft such as small satellites, and the application scenarios of the orbit transfer aircraft are expanded. In addition, by miniaturizing the orbit transfer aircraft and improving the flexibility of the orbit transfer aircraft, it is possible to achieve point-to-point transfer of loads for different orbits to different orbits, and realize efficient and flexible orbit transfer of small spacecraft; at the same time, the manufacturing cost and operating cost of the orbit transfer aircraft are reduced. In addition, according to the technical solution of the present application, the components are arranged based on the main body structure, the components are distributed relatively concentratedly, the load adapter plate is installed at the first end of the side wall, and the tanks are distributed around the side wall, thereby realizing the flattening of the entire structure of the orbital transfer vehicle. In this way, more payloads can be carried, multiple payloads can be shared, and transportation efficiency can be improved; the space inside the rocket fairing can also be utilized to the maximum extent.

[0017] Other features and advantages of the present application will be described in detail in the subsequent detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings constituting a part of the present application are used to provide a further understanding of the present application, and the schematic implementation modes and descriptions of the present application are used to explain the present application. In the accompanying drawings:

[0019] Figure 1 It is a schematic diagram of a partial structure of an orbital transfer vehicle according to a preferred embodiment of the present application;

[0020] Figure 2 It is a schematic diagram of a partial structure of an orbital transfer vehicle according to a preferred embodiment of the present application;

[0021] Figure 3It is a front view of the orbit transfer vehicle according to the preferred embodiment of the present application;

[0022] Figure 4 A top view of an orbital transfer vehicle according to a preferred embodiment of the present application;

[0023] Figure 5 A schematic diagram of the structure of an orbital transfer vehicle according to a preferred embodiment of the present application; and

[0024] Figure 6 It is a bottom view of the orbital transfer vehicle according to the preferred embodiment of the present application. DETAILED DESCRIPTION

[0025] The technical solution of the present application will be described in detail below with reference to the accompanying drawings and in combination with the implementation modes.

[0026] Orbital transfer vehicles can be used in satellite deployment and maintenance, deep space exploration, and on-orbit services.

[0027] In terms of satellite deployment and maintenance, orbital transfer vehicles are often used to transfer satellites from their initial orbits during the launch phase to their target operating orbits. With the rise of small satellites and constellation layouts, orbital transfer vehicles can improve launch efficiency at a lower cost. In deep space exploration missions, orbital transfer vehicles help push probes from Earth orbit to more distant planets such as the moon and Mars. In terms of on-orbit services, including equipment repair, maintenance, and garbage removal on orbit, orbital transfer vehicles can assist in transporting equipment or help other spacecraft complete orbital adjustments.

[0028] The core working principle of an orbital transfer vehicle is to use a propulsion system to provide enough kinetic energy to transfer a spacecraft from one orbit to another. This usually includes two major steps. One step is thrust generation. Thrust is provided by chemical propulsion or electric propulsion systems. Chemical propulsion systems provide large instantaneous thrust through fuel combustion, which is used to complete orbit changes in a short time. Electric propulsion systems such as ion engines provide continuous, small thrust by accelerating charged particles, which is suitable for long-term orbit maintenance. The other step is orbit adjustment. Through multiple propulsion operations, the orbital transfer vehicle can gradually change its speed and altitude to eventually reach the target orbit.

[0029] The propulsion system of the orbital transfer vehicle can include chemical propulsion, electric propulsion, ion propulsion, etc. In terms of navigation and attitude control, the orbital transfer vehicle can accurately determine its position through equipment such as spacecraft computers and gyroscopes, and rely on the attitude control engine with precise thrust output to maintain a stable attitude, ensuring that the thrust direction of the thruster is accurate. The orbital transfer vehicle can adopt a modular design, and different propulsion modules and functional modules can be configured according to mission requirements to improve its adaptability and mission execution capabilities.

[0030] The embodiment of the present application provides an orbital transfer vehicle. Specifically, an orbital transfer vehicle is provided for transporting and propulsing payloads such as satellites.

[0031] In an embodiment of the present application, the orbital transfer vehicle includes a main body structure, electrical equipment 20, a payload adapter plate 30, at least one solar panel 40, at least one propellant tank 50, a rendezvous and docking module 60, at least one attitude control engine group, and a trajectory change engine 80.

[0032] The main structure includes a side wall 10 and a bottom plate 11. Figure 1 , Figure 5 and Figure 6 As shown. The side wall 10 includes a first end and a second end, and the bottom plate 11 is connected to the second end, and the side wall 10 and the bottom plate 11 enclose a cavity. Figure 1 As shown, the first end of the side wall 10 is not closed. In the embodiment of the present application, the first end of the side wall 10 may be closed or not. When the first end of the side wall 10 is closed, a plate-like structure may be connected to the first end.

[0033] The bottom plate 11 is a plate-like structure. In the embodiment of the present application, the material of the side wall 10 and the bottom plate 11 can be determined according to the specific situation, and there is no limitation on this. For example, the material of the side wall 10 and the bottom plate 11 can be aluminum alloy, magnesium alloy, non-metal composite material, etc.

[0034] In addition, if Figure 1 As shown, the cross-section of the main structure is circular, the main structure is cylindrical, and the side wall 10 is the cylinder of the cylindrical structure. In addition, the cross-section of the main structure can also be rectangular or square, which is not limited.

[0035] The electrical equipment 20 is installed inside the orbital transfer vehicle and is responsible for managing and distributing power and program control of the orbital transfer vehicle to ensure stable power supply to all parts of the orbital transfer vehicle. The electrical equipment also has a power storage function to cope with the short-term operation of the orbital transfer vehicle in the shadow area.

[0036] In the embodiment of the present application, the electrical equipment 20 is centrally placed in the middle area inside the main body of the orbital transfer vehicle, in the middle surrounded by multiple propellant tanks 50 .

[0037] The electrical device 20 is installed in the cavity, and the electrical device 20 is installed on the inner side of the side wall 10. For example, the electrical device 20 is fixed on the inner side of the side wall 10 by bolt flanges.

[0038] The electrical device 20 includes an energy storage module 21 and a control module 22. In the embodiment of the present application, the energy storage module 21 can be any component that can store electrical energy, for example, Figure 1 As shown, the electric energy storage module 21 may be a battery 210. The control module 22 may be any component capable of issuing control instructions, for example, Figure 1 As shown, the control module 22 may be a satellite computer 220 .

[0039] The electrical device 20 is directly connected to the solar panel 40 for receiving solar power. Specifically, the power storage module 21 is directly connected to the solar panel 40. In addition, the electrical device 20 is also connected to the attitude control engine 70, the orbit change engine 80 and the satellite and other payloads to manage and distribute power so that each module can operate stably.

[0040] It should be noted that in the embodiment of the present application, when connecting to the electrical device 20 , components that need to use electricity or store electricity are connected to the energy storage module 21 , and components that need to be controlled are connected to the control module 22 .

[0041] The load transfer plate 30 is installed at the first end of the side wall 10, and the plane where the load transfer plate 30 is located is perpendicular to the axis of the main body structure. The load transported by the orbital transfer vehicle is installed on the side of the load transfer plate 30 away from the side wall 10. In other words, the load and the side wall 10 are connected to different sides of the load transfer plate 30 respectively. Figure 1 and Figure 2 As shown, the load adapter plate 30 is installed at one end of the side wall 10, and one side of the load adapter plate 30 is connected to one end of the side wall 10. Specifically, the load adapter plate 30 can be connected to one end of the side wall 10 by bolts and flanges. The load adapter plate 30 is an adapter plate used to carry the load transported by the orbital transfer spacecraft. Among them, the adapter plate is a plate-like structure with one end connected to the spacecraft body and the other end connected to the satellite and other payloads to achieve interface transfer. At least one interface group is provided on the load adapter plate 30, and each interface group includes a plurality of interfaces 301. The interface 301 is used to connect the separation mechanism for load connection, and each interface group corresponds to a load. As shown in FIG. Figure 2 As shown, the load adapter plate has 5 interface groups, which can be used to install 5 loads. For each interface group, the shape of the multiple interfaces 301 can be determined according to the specific situation, and there is no limitation on this. Figure 2 or Figure 4 As shown, the multiple interfaces 301 in each interface group form a circle. In addition, the multiple interfaces 301 in each interface group can also form a square, a rectangle or an ellipse, etc.

[0042] The load transfer plate 30 is used to place the satellite or other payloads carried, and the side of the load transfer plate 30 away from the side wall 10 is a carrying space for the payload, etc. Optionally, in the embodiment of the present application, the axis of the load transfer plate 30 may coincide with the axis of the body structure, so that the carrying space is located in the upper part of the central area of ​​the orbit transfer vehicle.

[0043] The payload is connected to the separation mechanism, which is connected to the orbit transfer vehicle via the payload adapter plate 30, so as to realize the payload separation function. The separation mechanism can be connected to the electrical device 20 to control the separation of the satellite.

[0044] Optionally, in the embodiment of the present application, the plane where the load transfer plate 30 is located is perpendicular to the axial direction of the main body structure.

[0045] At least one solar panel 40 is connected to the side wall 10 and is installed outside the cavity. At least one solar panel 40 is connected to the power storage module 21 to store power in the power storage module 21. Figure 1 or Figure 2 As shown, two solar panels 40 are included. In the embodiment of the present application, the number of solar panels 40 can be determined according to the specific situation, and there is no limitation on this. The solar panels 40 are used to provide continuous power energy for the orbital transfer vehicle, and can automatically adjust the angle according to the lighting conditions to maximize the reception of sunlight.

[0046] Optionally, in the embodiment of the present application, the solar panel 40 is mounted on the bracket 90, and the bracket 90 is mounted on the side wall 10, so that the solar panel 40 is connected to the side wall 10, such as Figure 1 The plane where the solar panel 40 is located is parallel to the axis direction of the main structure. In other words, one extension direction of the solar panel 40 is the same as the extension direction of the side wall 10, and the other extension direction is perpendicular to the extension direction of the side wall 10, as shown in FIG. Figure 1 As shown. Figure 1 As shown, the plane where the load transfer plate 30 is located is perpendicular to the axis of the main body structure, and the solar panel 40 is perpendicular to the load transfer plate 30 .

[0047] It should be noted that the plane where the solar panel 40 is located can be parallel to the axis direction of the main body structure, or can be at a certain angle to the axis direction of the main body structure. Then, the plane where the solar panel 40 is located can be perpendicular to the load adapter plate 30, or not perpendicular, but at a certain angle. In the embodiment of the present application, the angle between the plane where the solar panel 40 is located and the load adapter plate 30 can be any angle within the range of 0°~180°.

[0048] By installing the solar panel 40 on the bracket 90, the solar panel 40 can be located on the side of the orbital transfer vehicle, so that the solar panel 40 can receive sunlight to the maximum extent.

[0049] In the embodiment of the present application, a solar panel 40 may be located on one side of the orbital transfer vehicle and installed in the top side area of ​​the orbital transfer vehicle in the form of one-side unfolding.

[0050] In the embodiment of the present application, the solar panel 40 is connected to the bracket 90 through a hinge structure, and can be rotated or unfolded to adjust the angle toward the sun. The solar panel 40 provides continuous power to the energy storage module 21 in the electrical device 20 and is connected to the internal power management system.

[0051] Optionally, in the embodiment of the present application, the plane where the solar panel 40 is located is perpendicular to the plane where the load transfer plate 30 is located. The plane where the solar panel 40 is located is parallel to the axis of the main body structure.

[0052] Optionally, in the embodiment of the present application, the axis of the bracket 90 is perpendicular to the side wall 10 .

[0053] Optionally, in the embodiment of the present application, the length of the bracket 90 may be determined based on the size of the load transfer plate 30 .

[0054] The propellant tank 50 is used to store propellant and provide a thrust source for the orbit transfer vehicle. The propellant tank 50 is made of special materials and has strong pressure resistance and high temperature resistance.

[0055] At least one propellant tank 50 is connected to the side wall 10 and is mounted outside the cavity. At least one propellant tank 50 is distributed around the side wall 10 and close to the side of the load adapter plate 30 away from the load.

[0056] In the embodiment of the present application, the number of the propellant tanks 50 can be determined according to the specific situation and is not limited thereto. Figure 1 As shown, six propellant tanks 50 are included.

[0057] In the embodiment of the present application, the propellant tanks 50 are distributed around the side wall 10. The specific distribution method can be determined according to the specific situation and is not limited to this. For example, the centers of the multiple propellant tanks 50 can be distributed on different planes perpendicular to the side wall 10. Or, as Figure 1 As shown, a plurality of propellant tanks 50 are arranged in sequence around the side wall 10, and the centers of the plurality of propellant tanks 50 are distributed on the same plane perpendicular to the side wall 10. Optionally, in the embodiment of the present application, the line connecting the centers of the plurality of propellant tanks 50 is a polygon. Figure 1As shown, six propellant tanks 50 are included, and the polygon is a regular hexagon.

[0058] In addition, if Figure 1 and Figure 2 As shown, the propellant tanks 50 are distributed on the side of the load adapter plate 30 away from the load. In other words, the propellant tanks 50 are close to the side of the load adapter plate 30 away from the load, that is, the side where no load is installed.

[0059] In the embodiment of the present application, when a plurality of propellant tanks 50 are included, the connection method between the plurality of propellant tanks 50 can be determined according to specific circumstances. For example, when the same fuel is used, the plurality of propellant tanks 50 are connected in series through pipelines, and a main pipeline is extended. When other components are connected to the pipelines of the propellant tanks 50, the pipeline connection with the propellant tanks 50 is achieved by connecting to the main pipeline. For another example, when two different fuels are used, the plurality of propellant tanks 50 are divided into two groups, and the plurality of propellant tanks 50 in each group are connected in series through pipelines, and a main pipeline is extended from each group, and there are two main pipelines in total; when other components are connected to the pipelines of the propellant tanks 50, they are respectively connected to the two main pipelines to achieve the pipeline connection with the propellant tanks 50.

[0060] The rendezvous and docking module 60 is connected to the side wall 10 and is installed outside the cavity. The rendezvous and docking module 60 is electrically connected to the power storage module 21 and the control module 22 respectively and is connected to the propellant tank 50 through a pipeline. The rendezvous and docking module 60 is used to dock and separate with other equipment to be docked (such as satellites, etc.). The rendezvous and docking module 60 is equipped with a safety locking device and a docking positioning device to ensure that the orbital transfer spacecraft can be safely and accurately connected with the satellites and other equipment to be transported. Among them, the safety locking device grabs and locks the other docked spacecraft or satellite through a claw-shaped structure; the docking positioning device is a device that enables the pipelines that need to be connected between two spacecraft to be accurately aligned and determine their positions.

[0061] The rendezvous and docking module 60 is located on one side of the orbital transfer vehicle, facing the satellite or other equipment to be docked, to facilitate the docking operation.

[0062] The rendezvous and docking module 60 may be mounted on the bracket 90. Specifically, the rendezvous and docking module 60 is mounted on the bracket 90 through a bolt flange.

[0063] The rendezvous and docking module 60 can be connected to the bracket 90 through a telescopic device, and can move forward and backward to achieve accurate docking. The rendezvous and docking module 60 is connected to the electrical device 20 (for example, it can be connected to the power storage module 21 and the control module 22 respectively) to receive necessary power and receive instructions, and is connected to the propellant tank 50 through a pipeline, and the propellant liquid can be transported after the connection.

[0064] At least one attitude control engine group is connected to the side wall 10 and is installed outside the cavity. At least one attitude control engine group is electrically connected to the power storage module 21 and the control module 22 respectively and is connected to the propellant tank 50 through a pipeline. An attitude control engine group includes at least one attitude control engine 70. The attitude control engine 70 is mainly used to control the attitude of the orbital transfer vehicle, so that it can perform high-precision attitude adjustment to ensure the stable operation of the orbital transfer vehicle. The attitude control engine group can be installed around the orbital transfer vehicle.

[0065] The orbit change engine 80 is used to adjust the orbit of the orbit transfer vehicle so that it can enter the target orbit according to the mission requirements. The orbit change engine 80 has a strong thrust output capability and can complete the orbit change operation in a short time.

[0066] The track change engine 80 is mounted on the bottom plate 11 and is mounted outside the cavity, such as Figure 5 or Figure 6 The track-changing engine 80 is connected to the base plate 11 by bolts. Specifically, the track-changing engine 80 and the base plate 11 are provided with special bolt holes for connection, and the bolt holes of the two are aligned and connected by bolts.

[0067] The trajectory change engine 80 is electrically connected to the electric energy storage module 21 and the control module 22 respectively, and is connected to the propellant tank 50 through a pipeline.

[0068] The orbit transfer engine 80 is installed at the bottom of the orbit transfer vehicle to provide powerful thrust output to achieve orbit adjustment.

[0069] The orbit change engine 80 can be fixed in the center of the bottom of the orbit transfer vehicle through a mechanical structure, and the axis of the orbit change engine 80 coincides with the axis of the main body structure.

[0070] The orbit change engine 80 is directly connected to the propellant tank 50 through a pipeline, and sufficient propellant is provided through a dedicated pipeline. At the same time, the orbit change engine 80 is connected to the electrical equipment 20 to receive the command and power support of the orbit change.

[0071] Optionally, in the embodiment of the present application, support rods may be used to increase the connection strength between the bottom plate 11 and the side wall 10, thereby increasing the fixed structural strength of the track change engine 80. Figure 5 or Figure 6 As shown, two support rods 111 are provided; one end of each support rod 111 is connected to the side wall 10, and the other end is connected to the bottom plate 11. It should be noted that the number of support rods 111 can be determined according to specific circumstances, and there is no limitation on this. In addition, the connection between the support rod 111 and the side wall 10 and the bottom plate 11 can be connected by flange bolts.

[0072] Optionally, in the embodiment of the present application, each attitude control engine group may include multiple attitude control engines 70. In the case where each attitude control engine group includes multiple attitude control engines 70, the combination of the multiple attitude control engines 70 may be determined according to the specific situation. For example, in the case where each attitude control engine group includes three attitude control engines 70, the axes of any two attitude control engines 70 may be at an angle of 90°; or, it may be as follows: Figure 5 In the case shown, the axes of two attitude control engines 70 are parallel, and the axis of another attitude control engine 70 forms an angle of 90° with the axes of the first two. For another example, when each attitude control engine group includes four attitude control engines 70, the four attitude control engines 70 can be arranged in a cross-shaped pattern, symmetrically in pairs, with the axes of two of them parallel, and the axes of the other two parallel, and the axes of the two of them perpendicular to the axes of the other two. Figure 5 As shown, it includes 4 attitude control engine groups, and each attitude control engine group includes 3 attitude control engines 70. Among them, the axes of two attitude control engines 70 are parallel, and the axis of another attitude control engine 70 forms a 90° angle with the axes of the first two. In the case where each attitude control engine group includes multiple attitude control engines 70, the attitude control can be made more accurate.

[0073] Optionally, in the embodiment of the present application, multiple attitude control engine groups may be included. In the embodiment of the present application, when multiple attitude control engine groups are included, the distribution form of the multiple attitude control engine groups may be determined according to the specific situation. The multiple attitude control engine groups may be distributed around the side wall 10. The multiple attitude control engine groups are distributed around the orbit transfer vehicle. In this way, attitude control in multiple directions may be achieved.

[0074] For example, the centers of multiple attitude control engine groups may be on the same circumference. Figure 5 As shown, it includes 4 attitude control engine groups, the centers of the 4 attitude control engine groups are on the same circumference, and the 4 attitude control engine groups are symmetrically distributed in pairs.

[0075] In the embodiment of the present application, the attitude control engine 70 can be connected to the side wall 10 included in the body structure through the bracket 90, and connected to the propellant tank 50 through the fuel delivery pipeline to obtain the necessary fuel supply. Each attitude control engine 70 is connected to the electrical device 20 to receive the attitude adjustment command and the required power to ensure that the aircraft can be accurately controlled in all directions.

[0076] Optionally, in the embodiment of the present application, the orbital transfer vehicle may further include at least one bracket 90. At least one bracket 90 is connected to the side wall 10, and at least one solar panel 40, at least one propellant tank 50, a rendezvous and docking module 60, and at least one attitude control engine group are installed on the bracket 90 to be connected to the side wall 10.

[0077] like Figure 1 As shown, the solar panel 40 is mounted on the bracket 90, the propellant tank 50 is mounted on the bracket 90, and the rendezvous and docking module 60 is mounted on the bracket 90. Figure 2 As shown, the attitude control motor group is mounted on a bracket 90 .

[0078] In the embodiment of the present application, the bracket 90 may be a plate-like structure that has been designed for weight reduction using topology optimization technology, and is a hollow structure. The material of the bracket 90 may be an aluminum alloy or a magnesium alloy or a non-metallic composite material. The bracket 90 may include four side surfaces, respectively marked as a first side surface, a second side surface, a third side surface and a fourth side surface, wherein the first side surface is opposite to the third side surface, and the second side surface is opposite to the fourth side surface. The first side surface is connected to the side wall 10, and its shape matches the shape of the side wall 10. The third plane may be determined according to the specific circumstances, for example, it may be a plane. The second side surface and the fourth side surface may match the shape of the components connected thereto. For example, as Figure 1 As shown, the second surface and the fourth surface are connected to the propellant tank 50, and the second surface and the fourth surface are cambered surfaces.

[0079] In the embodiment of the present application, when a posture control engine group includes multiple posture control engines, a single posture control engine is connected to the assembly block through a bolt flange to form a posture control engine group. In addition, the posture control engine group can be installed through the connection hole on the assembly block in combination with the bolt flange, for example, installed on the bracket 90.

[0080] In the embodiment of the present application, which component can be installed on which bracket 90 according to the specific situation, and there is no limitation on this. Figure 1 As shown, a certain bracket 90 is equipped with a rendezvous and docking module 60, and the bracket 90 is also connected to a propellant tank 50; a certain bracket 90 is equipped with a solar panel 40, and the bracket 90 is also connected to a propellant tank 50. Figure 5 As shown, a solar panel 40 is installed on a bracket 90, and a propellant tank 50 and an attitude control engine group are also connected. Figure 5 As shown, a certain bracket 90 is connected to the propellant tank 50 and is also equipped with an attitude control engine group.

[0081] In the embodiment of the present application, by using the bracket 90, the space can be better utilized, the utilization rate of the space can be improved, and it is more conducive to the miniaturization of the orbital transfer aircraft.

[0082] In the embodiment of the present application, when a plurality of brackets 90 are included, the distribution of the brackets 90 around the side wall 10 can be determined according to specific circumstances. For example, the centers of the plurality of brackets 90 may be located on different planes perpendicular to the side wall 10; the centers of the plurality of brackets 90 may be located on the same plane perpendicular to the side wall 10; or the plurality of brackets 90 may be grouped, and the centers of the brackets 90 included in each group may be located on the same plane perpendicular to the side wall 10.

[0083] Optionally, in the embodiment of the present application, the at least one bracket 90 includes a plurality of brackets 90, and the plurality of brackets 90 are arranged in sequence around the side wall 10. The centers of the plurality of brackets 90 are located on the same plane perpendicular to the side wall 10. Figure 1 As shown, a total of 6 brackets 90 are included, and the multiple brackets 90 are respectively connected to the side walls 10 , and the multiple brackets 90 are arranged in sequence around the side walls 10 , and the centers of the multiple brackets 90 are located on the same plane perpendicular to the side walls 10 .

[0084] Optionally, in the embodiment of the present application, each propellant tank 50 is mounted on two brackets 90. Figure 1 As shown, a total of 6 propellant tanks 50 are included, and each propellant tank 50 is connected to two brackets 90 and is installed on the two brackets 90. In this way, the stability of the propellant tank 50 can be improved.

[0085] In the embodiment of the present application, multiple propellant tanks 50 may be connected in pairs through brackets 90, forming a circle and finally connected into one body, forming a whole, and located on the outside of the orbit transfer vehicle. A cavity is formed in the middle of the multiple propellant tanks 50 for placing the electrical device 20. The propellant tanks 50 are connected to the attitude control engine 70 and the orbit change engine 80 through a fuel delivery pipeline to provide a continuous fuel supply. In addition, the propellant tanks 50 are connected to the electrical device 20, and its temperature and pressure are monitored by the electrical management system to ensure the stable storage and supply of the propellant.

[0086] Optionally, in the embodiment of the present application, the center of the bracket 90 is on the same plane as the center of the propellant tank 50. In this way, the orbital transfer vehicle can be flatter, and the space can be better utilized, thereby improving the utilization rate of the space.

[0087] In the embodiment of the present application, the shape of the propellant tank 50 can be determined according to the specific situation, and there is no limitation on this. For example, the shape of the propellant tank 50 can be one of the following: a sphere, an ellipsoid, or a cylinder. Alternatively, the shape of the propellant tank 50 can also be a cube or a cuboid.

[0088] Optionally, in the embodiment of the present application, the shape of the bracket 90 can match the shape of the propellant tank 50 to better utilize the space. Figure 1 As shown, the surface where the bracket 90 is connected to the propellant tank 50 is a curved surface, and the curved surface is bent along the propellant tank 50 .

[0089] Optionally, in the embodiment of the present application, the rendezvous and docking module 60 and the solar panel 40 are installed on different brackets 90. Figure 2 or Figure 5 As shown, the rendezvous and docking module 60 and the solar panel 40 are installed on different brackets 90 .

[0090] Optionally, in the embodiment of the present application, the axis of the track change engine 80, the axis of the load adapter plate 30 and the axis of the main body structure coincide with each other.

[0091] Optionally, in the embodiment of the present application, along a direction perpendicular to the load transfer plate 30 , the shape of the top view of the load transfer plate 30 is a polygon.

[0092] If the top view of the load adapter plate 30 is a polygon, it is convenient to install the solar panel 40 so as to make full use of the space.

[0093] Optionally, in the embodiment of the present application, the plane where the solar panel 40 is located is parallel to the side surface of the load transfer plate 30 .

[0094] Optionally, in the embodiments of the present application, the polygon may be a square, a rectangle, a hexagon, etc., and no limitation is imposed on this. Figure 4 As shown, along the direction perpendicular to the load adapter plate 30 , the shape of the load adapter plate 30 in a top view is a regular hexagon.

[0095] Optionally, in the embodiment of the present application, the orbital transfer vehicle may further include a payload, wherein the payload refers to an object transferred by the orbital transfer vehicle, such as a satellite.

[0096] In the embodiment of the present application, the orbit transfer vehicle adopts a modular layout to achieve the independence and easy maintainability of each component. For example, the solar panels 40 are deployed on one side to provide continuous power. The electrical equipment 20 is located in the middle to coordinate the power and data transmission of each module. The rendezvous and docking module 60 is located on one side and is used to connect payloads such as satellites to be docked. Satellites and other payloads are located in the upper part of the core area to ensure the stability and safety of the payload. The propellant tank 50 is placed around the outside to form a polygonal structure to provide fuel support for the attitude control engine 70 and the orbit change engine 80. The attitude control engine 70 can be distributed around the aircraft in the form of a multi-machine combination. The orbit change engine 80 is located at the bottom of the aircraft, and its axis coincides with the axis of the main body structure, which is convenient for realizing orbit changes.

[0097] Through the technical solution provided in the implementation mode of this application, a light and small multifunctional orbital transfer aircraft is provided, which can solve the problems of excessive weight, high energy consumption, high cost and single function. The aircraft can achieve efficient and flexible orbital transfer of small spacecraft through optimized structure, light and small solution design, modular design, and use of universal module interfaces, while having low manufacturing and operating costs. The aircraft is designed to improve the orbital transfer efficiency of small spacecraft, expand its application scenarios, and adapt to the future aerospace field's demand for on-orbit service aircraft.

[0098] The orbital transfer vehicle provided in the implementation mode of the present application adopts a modular design. It not only has energy self-sufficiency, attitude control and orbit change functions, but also can achieve safe docking with satellites, and has high stability and high reliability.

[0099] The orbital transfer vehicle provided in the embodiment of the present application includes a power system, an electrical system and a rendezvous and docking module. The power system (including the orbit change engine, the attitude control engine, the propellant tank, etc.) is the core propulsion device of the orbital transfer vehicle. It provides sufficient thrust for the vehicle by burning chemical fuel to ensure that it can switch between different orbits; at the same time, it is responsible for accurately controlling the acceleration, deceleration and direction adjustment of the vehicle to ensure that the spacecraft can fly according to the predetermined trajectory. The electrical system (including solar panels and electrical equipment) provides the vehicle with comprehensive control capabilities and energy and power management to ensure that the vehicle can continue to operate during operation. The control module plays a central management role in the orbital transfer vehicle, ensuring that the vehicle runs smoothly according to the mission requirements, and coordinating the operation of each subsystem to achieve efficient and stable operation of the vehicle. The solar panels and the power storage module are responsible for powering all subsystems, etc., to ensure the self-sustaining ability of the aircraft in long-term missions. The rendezvous and docking module is a key module for the docking of the aircraft with other spacecraft. Through radar, sensors and automatic control systems, the aircraft can accurately identify the position and speed of the target spacecraft, adjust the relative position, and finally complete the docking process. The rendezvous and docking module usually relies on complex navigation algorithms and real-time communication to ensure the safety and accuracy of the docking process. These functional modules work together to ensure that the orbital transfer vehicle can successfully complete orbit adjustment, energy management, and rendezvous and docking with other spacecraft during complex space missions.

[0100] The orbital transfer vehicle provided in the implementation mode of the present application 1) can realize the entire vehicle to be flat, with space reserved on the upper part for payloads (satellites and other customers); 2) has the ability to change orbits continuously for multiple times and to transport small satellites into different orbits for multiple times; 3) has the ability to fly in orbit for a long time (more than 1 year) and be reusable, with continuous power supply through solar panels and continuous propulsion capability through in-orbit propellant injection; 4) the vehicle has the ability to rendezvous and dock with itself or other spacecraft; 5) the vehicle has extended functions such as installing a robotic arm and upgrading in-orbit capture.

[0101] The preferred embodiments of the present application are described in detail above; however, the present application is not limited to the specific details in the above embodiments. Within the technical concept of the present application, a variety of simple modifications can be made to the technical solution of the present application, and these simple modifications all fall within the protection scope of the present application.

[0102] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this application will not further describe various possible combinations.

[0103] In addition, the various implementation modes of the present application may be arbitrarily combined, and as long as they do not violate the concept of the present application, they should also be regarded as the contents disclosed by the present invention.

Claims

1. An orbit transfer vehicle, characterized in that: The orbital transfer vehicle includes: A body structure, comprising a side wall and a bottom plate, wherein the side wall comprises a first end and a second end, the bottom plate is connected to the second end, and the side wall and the bottom plate enclose a cavity; An electrical device is installed in the cavity, the electrical device comprising an electric energy storage module and a control module; A load adapter plate is installed at the first end of the side wall, the plane where the load adapter plate is located is perpendicular to the axis of the main body structure, and the load transported by the orbital transfer vehicle is installed on a side of the load adapter plate away from the side wall; at least one solar panel connected to the side wall and mounted outside the cavity, the at least one solar panel connected to the electric energy storage module; at least one propellant tank connected to the side wall and mounted outside the cavity, the at least one propellant tank being distributed around the side wall and close to a side of the load adapter plate away from the load; a rendezvous and docking module, connected to the side wall and installed outside the cavity, the rendezvous and docking module being electrically connected to the electric energy storage module and the control module respectively and connected to the propellant tank through a pipeline; at least one attitude control engine group connected to the side wall and installed outside the cavity, the at least one attitude control engine group being electrically connected to the electric energy storage module and the control module respectively and connected to the propellant tank through a pipeline; and A trajectory change engine is installed on the base plate and outside the cavity. The trajectory change engine is electrically connected to the electric energy storage module and the control module respectively and is connected to the propellant tank through a pipeline.

2. The orbit transfer vehicle according to claim 1, characterized in that: The orbital transfer vehicle also includes: At least one bracket is connected to the side wall, and the at least one solar panel, at least one propellant tank, the rendezvous and docking module, and the at least one attitude control engine group are installed on the bracket to be connected to the side wall.

3. The orbit transfer vehicle according to claim 2, characterized in that: The at least one bracket includes a plurality of brackets, and the plurality of brackets are sequentially arranged around the side wall.

4. The orbit transfer vehicle according to claim 3, characterized in that: Each propellant tank is mounted on two brackets.

5. The orbit transfer vehicle according to claim 2, characterized in that: The center of the bracket is in the same plane as the center of the propellant tank.

6. The orbit transfer vehicle according to any one of claims 1 to 5, characterized in that: The shape of the propellant tank is one of the following: sphere, ellipsoid, cylinder.

7. The orbit transfer vehicle according to claim 2, characterized in that: The rendezvous and docking module and the solar panel are installed on different brackets.

8. The orbit transfer vehicle according to claim 1, characterized in that: The cross-section of the main body structure is circular.

9. The orbit transfer vehicle according to claim 1, characterized in that: The axis of the track-changing engine, the axis of the load adapter plate and the axis of the main body structure coincide with each other.

10. The orbit transfer vehicle according to claim 1, characterized in that: Along a direction perpendicular to the load adapter plate, the shape of the top view of the load adapter plate is a polygon.

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