Multi-truss system of space station

Abstract

The invention discloses a space station multi-truss system. The space station multi-truss system is characterized by comprising a truss module and a sun orientation mechanism a; each truss module comprises a truss structure, an unfolding mechanism, a flexible solar wing, a connection unlocking mechanism, an electromechanical adaptive interface and a sun orientation mechanism b, and a plurality of truss modules are installed in parallel through the connection unlocking mechanisms to form a multi-truss system; during unfolding, the truss structure and the spacecraft are sequentially connected into an axial series system through the unfolding mechanism. According to the space station multi-truss system disclosed by the invention, a carrying launching envelope space is fully and reasonably utilized, and a solar wing capable of infinitely expanding the area and an installation space are provided, so that the increasing requirements of on-orbit power generation and power supply power of a large spacecraft are met.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace overall design, and in particular relates to a multi-truss system for a space station. Background Art

[0002] Space stations or large spacecraft, such as the Mir Space Station, the International Space Station, and my country's Tiangong Space Station, have an extra-large main structure, a strict astronaut environmental control and life support system, and a large number of platform equipment and experimental equipment, and have large energy requirements and equipment installation requirements.

[0003] Solar energy is currently the most widely used clean energy for spacecraft. Therefore, large spacecraft often need to be equipped with large solar panels. In the past, conventional spacecraft could only carry and install two large solar panels at a time, and the launch efficiency was often relatively low. For example, the International Space Station took many launches to build the current 2,500m 2 Therefore, it is of great significance to study how to reasonably utilize the carrier envelope, improve the launch efficiency of solar wings in a single launch, and increase the area and number of solar wings. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a multi-truss system for a space station, the system comprising a truss module and a sun-orientation mechanism a;

[0005] The truss module includes a truss structure, an unfolding mechanism, a flexible solar wing, a connection unlocking mechanism, an electromechanical adaptation interface, and a sun-orienting mechanism b. Multiple truss modules are installed in parallel through the connection unlocking mechanism to form a multi-truss system;

[0006] The solar orientation mechanism a is used for connecting the spacecraft and the truss structure;

[0007] The flexible solar wing is symmetrically mounted on the front and rear sides of the truss structure, and is connected to the root of the flexible solar wing through the sun-orientation mechanism b;

[0008] The connection unlocking mechanism is symmetrically installed on the left and right sides of the truss structure;

[0009] The deployment structure is installed on the left and right sides of two adjacent truss structures. When deployed, the deployment mechanism sequentially connects the truss structures with the spacecraft to form an axial series system;

[0010] The upper top surface and the lower bottom surface of the truss structure are provided with electromechanical adapter interfaces. After the unfolding mechanism is unfolded, each of the truss structures forms a series system through the electromechanical adapter interfaces.

[0011] Furthermore, the truss structure is a polyhedron having six or more joint surfaces.

[0012] Furthermore, the solar orientation mechanisms b correspond one-to-one to the flexible solar wings, and each truss module has two solar orientation mechanisms b and two flexible solar wings.

[0013] Furthermore, the number of truss modules increases with the increase in the size requirements of the flexible solar wing. The truss module fixedly connected to the solar orientation mechanism a is truss module 1, and truss module 1 is the reference module. When the multi-truss system is launched, the truss modules are arranged in a left-right symmetrical parallel configuration with truss module 1 as the center.

[0014] Furthermore, after the truss modules are launched into orbit, the space station robotic arm is used to rearrange the symmetrical truss modules, and an unfolding mechanism is used to unfold and dock them.

[0015] Furthermore, the deployment mechanisms are alternately arranged at the upper right corner and the lower right corner of the truss structure starting from the truss module 1 .

[0016] Furthermore, the axial series system is composed of truss modules that are rotated and deployed. The rearranged truss modules utilize an deployment mechanism, and the undeployed module rotates 90° relative to the truss module 1 to form an inverted triangle offset configuration. Thereafter, the undeployed module rotates 90° relative to the deployed part to form a straight series configuration, and the process is repeated in sequence.

[0017] Furthermore, platforms and space experimental equipment can be installed inside and outside the truss module.

[0018] Furthermore, the truss module can be installed at any part of the spacecraft or launched independently if the launch envelope allows.

[0019] Furthermore, after the truss modules are put into orbit, a robotic arm is used to transfer all truss modules to the left or right side of the truss module 1, and then the unfolding mechanism is used to rotate, unfold and dock them in sequence to form a linear series configuration.

[0020] The present invention has the following advantages:

[0021] The present invention provides a multi-truss system with expandable quantity and changeable configuration. The total area of ​​the solar wing power generation array and the number of trusses depend on the power demand for on-orbit power generation and power supply. It can make full use of the carrying envelope space during launch and multiply the power generation, power supply and carrying capacity of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the prior art descriptions. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. It should be noted that for the sake of clarity and ease of description, the drawings are not necessarily drawn to scale.

[0023] Figure 1 is a schematic diagram of a truss module 1 of the present invention;

[0024] Figure 2 is a schematic diagram of a truss module 2 of the present invention;

[0025] Figure 3 is a schematic diagram of a truss module 3 of the present invention;

[0026] Figure 4 It is a schematic diagram of the first stage configuration change process of the multi-truss system of the present invention;

[0027] Figure 5 It is a schematic diagram of the second stage configuration change process of the multi-truss system of the present invention;

[0028] Figure 6 It is a schematic diagram of the third stage configuration change process of the multi-truss system of the present invention;

[0029] Markings in the figure:

[0030] 1-truss module 1, 101-truss structure, 102-electromechanical adaptation interface, 103-unfolding mechanism 1, 104-front sun-facing orientation mechanism b, 105-right connection unlocking mechanism, 106-front solar wing, 107-sun-facing orientation mechanism a, 108-left connection unlocking mechanism, 109-rear solar wing, 110-rear sun-facing orientation mechanism b;

[0031] 2-truss module 2, 201-truss structure, 202-upper electromechanical adapter interface, 203-front sun-facing orientation mechanism b, 204-right connection unlocking mechanism, 205-front solar wing, 206-unfolding mechanism 2, 207-lower electromechanical adapter interface, 208-left connection unlocking mechanism, 209-rear solar wing, 210-rear sun-facing orientation mechanism b;

[0032] 3-truss module 3, 301-truss structure, 302-upper electromechanical adapter interface, 303-unfolding mechanism 3, 304-front sun-facing orientation mechanism b, 305-right connection unlocking mechanism, 306-front solar wing, 307-lower electromechanical adapter interface, 308-left connection unlocking mechanism, 309-rear solar wing, 310-rear sun-facing orientation mechanism b.

[0033] Specific implementation methods

[0034] The present invention will be further described below in conjunction with the accompanying drawings.

[0035] In this embodiment, the principle and content of the present invention are described in detail by taking a launch carrying three truss modules as an example.

[0036] The structure of the truss module 1 is as follows Figure 1 As shown, the truss module 1 is defined as a reference module, including a truss structure 101, an unfolding mechanism 103, located at the upper right corner of the module, two connection unlocking mechanisms: a left connection unlocking mechanism 108 and a right connection unlocking mechanism 105, respectively, for connection and unlocking with other truss modules, an electromechanical adaptation interface 102, for mechanical connection with other trusses and connection and transmission of electrical power and signals, a solar orientation mechanism a107, for connecting the truss structure 101 with the spacecraft and realizing rotational solar orientation, and two flexible solar wings: a front solar wing 106 and a rear solar wing 109, respectively, corresponding to two solar orientation mechanisms b: a front solar orientation mechanism b104 and a rear solar orientation mechanism b110, respectively;

[0037] The structure of the truss module 2 is as follows Figure 2 As shown, it includes a truss structure 201, an unfolding mechanism 206 located at the lower right corner of the module, two connection unlocking mechanisms: a left connection unlocking mechanism 208 and a right connection unlocking mechanism 204, two electromechanical adaptation interfaces: an upper electromechanical adaptation interface 202 and a lower electromechanical adaptation interface 207, two flexible solar wings: a front solar wing 205 and a rear solar wing 209, corresponding to two sun-facing orientation mechanisms b: a front sun-facing orientation mechanism b203 and a rear sun-facing orientation mechanism b210;

[0038] The structure of the truss module 3 is as follows Figure 3 As shown, it includes a truss structure 301, an unfolding mechanism 303, located at the upper right corner of the module, two connection unlocking mechanisms: a left connection unlocking mechanism 308 and a right connection unlocking mechanism 305, two electromechanical adaptation interfaces: an upper electromechanical adaptation interface 302 and a lower electromechanical adaptation interface 307, two flexible solar wings: a front solar wing 306 and a rear solar wing 309, corresponding to two sun-facing orientation mechanisms b: a front sun-facing orientation mechanism b304 and a rear sun-facing orientation mechanism b310;

[0039] The truss structures 101, 201, 301 are all polyhedrons, having six or more butt joint surfaces;

[0040] Preferably, the truss is in the shape of a cuboid, wherein the front and rear sides are provided with solar wings, and the left and right sides are provided with other trusses through a connection unlocking mechanism, and are used for being installed in parallel with other trusses during launch, and a single truss can be connected with at most two other trusses;

[0041] like Figure 4 As shown in the schematic diagram of the first stage configuration change process of the multi-truss system, during launch, truss module 1 is in the center, with truss module 2 on the right and truss module 3 on the left. The truss system is a bilaterally symmetrical parallel configuration, with the sequence numbers 3-1-2 from left to right. After entering orbit, the robotic arm grabs module 3 on the left, then the connection unlocking mechanism between truss module 1 and truss module 3 is unlocked, and the robotic arm transfers module 3 to the far right, the connection unlocking mechanism between modules 2 and 3 is locked, and the deployment mechanism between modules 2 and 3 is locked, forming an offset parallel configuration, with the sequence numbers 1-2-3 from left to right.

[0042] like Figure 5 As shown in the schematic diagram of the second stage configuration change process of the multi-truss system, the connection unlocking mechanism between truss module 1 and truss module 2 is unlocked, and the assembly of truss modules 2-3 is rotated 90° to 180° around truss module 1 by using the unfolding mechanism 1, and the electromechanical adapter interfaces of modules 1 and 2 are docked and locked to form an inverted triangle offset configuration;

[0043] like Figure 6 As shown in the schematic diagram of the third stage of the multi-truss system configuration change process, the connection unlocking mechanism between truss module 2 and truss module 3 is unlocked, and the unfolding mechanism 2 is used to rotate truss module 3 around truss module 2 by 90° to 180°, and the electromechanical adapter interfaces of modules 2 and 3 are docked and locked to form the final form of the linear series configuration;

[0044] Preferably, the truss module can continue to install truss modules 4 and truss modules 5 on the left and right sides to the required number under the premise that the carrying envelope allows, and after entering the track, all truss modules are transferred to one side (left or right) of the truss module 1 by using a mechanical arm, and then rotated and unfolded by using an unfolding mechanism in turn to dock into a linear series configuration;

[0045] Preferably, the truss module can be installed in other parts of the spacecraft, including but not limited to the outside or inside of the spacecraft, the outside or inside of other spacecraft, and the separate launch of the truss module, etc. After entering orbit, all truss modules are transferred to the left or right side of the truss module 1 by using a robotic arm, and then rotated and deployed in sequence by using an deployment mechanism to dock into a linear series configuration;

[0046] Preferably, the configuration change process can be simplified to directly utilize the principle of building blocks, with the help of a robotic arm, an on-orbit robot or astronauts to install and dock into a linear series configuration.

[0047] Although the present invention has been disclosed as a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the above disclosed methods and technical contents without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention. The contents not described in detail in the specification of the present invention belong to the known technology of professional and technical personnel in this field.

Claims

1. A multi-truss system for a space station, characterized in that: The system includes a truss module and a sun-orientation mechanism a. The truss module includes a truss structure, an unfolding mechanism, a flexible solar wing, a connection unlocking mechanism, an electromechanical adaptation interface, and a sun-orienting mechanism b. Multiple truss modules are installed in parallel through the connection unlocking mechanism to form a multi-truss system; The solar orientation mechanism a is used for connecting the spacecraft and the truss structure; The flexible solar wing is symmetrically mounted on the front and rear sides of the truss structure, and is connected to the root of the flexible solar wing through the sun-orientation mechanism b; The connection unlocking mechanism is symmetrically installed on the left and right sides of the truss structure; The deployment structure is installed on the left and right sides of two adjacent truss structures. When deployed, the deployment mechanism sequentially connects the truss structures with the spacecraft to form an axial series system; The upper top surface and the lower bottom surface of the truss structure are provided with electromechanical adapter interfaces. After the unfolding mechanism is unfolded, each of the truss structures forms a series system through the electromechanical adapter interfaces.

2. A space station multi-truss system as claimed in claim 1, characterized in that: The truss structure is a polyhedron and is provided with six or more butt joint surfaces.

3. A space station multi-truss system according to claim 1, characterized in that: The solar orientation mechanisms b correspond one-to-one to the flexible solar wings, and each truss module has two solar orientation mechanisms b and two flexible solar wings.

4. A space station multi-truss system according to claim 1, characterized in that: The number of truss modules increases as the size requirements of the flexible solar wing increase. The truss module fixedly connected to the solar orientation mechanism a is truss module 1, and truss module 1 is the reference module. When the multi-truss system is launched, the truss modules are arranged in a left-right symmetrical parallel configuration with truss module 1 as the center.

5. A space station multi-truss system according to claim 4, characterized in that: After the truss modules are launched into orbit, the space station robotic arm is used to rearrange the symmetrical truss modules, and an unfolding mechanism is used to unfold and dock them.

6. A space station multi-truss system according to claim 4 or 5, characterized in that: The deployment mechanisms are arranged alternately at the upper right corner and the lower right corner of the truss structure starting from the truss module 1 .

7. A space station multi-truss system according to claim 1, characterized in that: The truss modules are rotated and unfolded. The rearranged truss modules use an unfolding mechanism. The unfolded module is rotated 90° to the truss module 1 to form an inverted triangle offset configuration. Then the unfolded module is rotated 90° to the unfolded part to form a straight series configuration, which is carried out in sequence.

8. A space station multi-truss system according to claim 1, characterized in that: Platforms and space experimental equipment can be installed inside and outside the truss module.

9. A space station multi-truss system according to claim 1, characterized in that: The truss module can be installed at any part of the spacecraft or launched separately if the launch envelope allows.

10. A space station multi-truss system according to claim 4 or 9, characterized in that: After the truss modules are put into orbit, the robot arm is used to transfer all the truss modules to the left or right side of the truss module 1, and then the unfolding mechanism is used to rotate, unfold and dock them in sequence to form a linear series configuration.

Images