Truss type resource cabin

Abstract

The invention provides a truss type resource cabin, which comprises a propulsion module, a plurality of functional cabin sections and a control module, the sun orientation device is provided with a first end and a second end which are opposite to each other, and the first end of the sun orientation device is connected with the propelling module; the truss structure is connected with the second end of the sun orientation device; the driving mechanism is arranged on the side surface of the truss mechanism and is provided with a rotating output end; the solar cell wing can be folded and unfolded and is connected with the rotating output end of the driving mechanism; and the track control engine is arranged on the truss structure. The requirement for high in-orbit power generation capacity of the solar cell wing is met, the thrust utilization rate of orbit control power is increased, and the structural mass is reduced.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and more specifically, to a truss-type resource module. Background Technology

[0002] With the continuous advancement of aerospace technology and the evolving needs of on-orbit missions, spacecraft, especially the modules of space stations capable of long-term on-orbit missions, have seen significant improvements in both size and weight. At the same time, the high energy consumption of the equipment carried by these modules poses a significant challenge to the power supply capabilities of the power systems.

[0003] The two existing space station modules employ single-degree-of-freedom solar-orientation for their solar panels, meaning the angle of sunlight incidence cannot always be optimal. Furthermore, mutual shading between modules severely limits the solar panel's power generation capacity. While another type of space station module uses a dual-degree-of-freedom solar panel solar-orientation system to improve power generation, it lacks independent flight capability, relies on the Space Shuttle for launch, and incurs high construction costs. Another type of space station consists of modules with independent autonomous flight capabilities. The experimental module uses a dual-degree-of-freedom solar array solar orientation system to improve power generation. However, this system is located at the rear of the resource module, while the orbital control engine is located on the resource module wall with its nozzle pointing towards the rear. This results in a large structural weight for the resource module, susceptibility of the dual-degree-of-freedom solar array solar orientation system to the plume of the orbital control engine, and low thrust utilization of the engine. This indirectly leads to the need to carry more propellant. In addition, the solar array is installed across three modules, making it difficult to ensure installation accuracy. The configuration and equipment layout of the resource module are not conducive to reducing the weight of the spacecraft in order to carry more test equipment and other payloads within the limited launch vehicle carrying capacity.

[0004] In summary, under the limited carrying capacity of launch vehicles and the limited space constraints of fairings, how to optimize the configuration and equipment layout of the resource module to reduce its weight, improve the space utilization of the launch fairing and the on-orbit power generation capacity of the solar panels, avoid the impact of orbital control engine plumes on onboard products and improve the thrust utilization of orbital control engines, and reduce the installation difficulty and ensure accuracy on the solar panel module are the problems that need to be solved in the configuration and equipment layout of the space station's constituent modules. To address this, the present invention provides a truss-type resource cabin that makes full use of the limited space of the fairing, reduces structural weight, meets the high on-orbit power generation requirements of the solar array, avoids the impact of the orbital control engine plume on the products on the cabin, improves the thrust utilization rate of the orbital control engine, and reduces the difficulty of installing the solar array. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a resource module that reduces structural weight, meets the high on-orbit power generation requirements of solar arrays, and improves the utilization rate of orbit control engine thrust.

[0006] The truss-type resource compartment provided by this invention includes: The propulsion module is capable of connecting to functional modules; A sun-oriented device having a first end and a second end opposite to each other, the first end of the sun-oriented device being connected to the propulsion module; A truss structure, which is connected to the second end of the sun-oriented device; A drive mechanism, located on the side of the truss mechanism, has a rotation output end; The solar cell fins are retractable and deployable, and are connected to the rotational output end of the drive mechanism. The track-controlled engine is mounted on the truss structure.

[0007] Furthermore, the first end of the sun-aligning device is a fixed end, and the second end of the sun-aligning device is a rotating end, wherein the rotating end is capable of rotating about the axis of the fixed end.

[0008] Preferably, a conductive slip ring is provided between the fixed end and the rotating end, and the conductive slip ring is electrically connected to the solar cell fin.

[0009] Furthermore, it also includes a pipeline disconnector, which is installed on the sun orientation device and is connected to the propulsion module and the track control engine respectively through conduits.

[0010] Furthermore, the pipeline disconnector includes an active end and a passive end. The active end is located at the fixed end and is connected to the propulsion module via a conduit. The passive end is located at the rotating end and is connected to the track control engine via a conduit.

[0011] Preferably, when the track control engine is working, the active end and the passive end are connected, and the rotating end is restricted from rotating relative to the fixed end; after the track control engine finishes working, the active end and the passive end are disconnected, and the rotating end is able to rotate relative to the fixed end.

[0012] Preferably, the truss structure is made of low-density material, and the shape of the truss structure is one of rectangle, square, or cylinder.

[0013] Preferably, the track control engine is located at the rear of the truss structure.

[0014] Preferably, the thrust shaft of the orbital control engine is parallel to the flight direction of the aircraft.

[0015] Preferably, the circumferential dimensions of the propulsion module, the solar orientation device, and the truss structure decrease sequentially.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. The truss-type resource module of the present invention, through the cooperation of the sun-orienting device and the pipeline disconnector, realizes the alternation of the operation of the resource module's orbital control engine and the sun-orienting of the solar cell wings, thereby meeting the needs of flight trajectory change and high-power power generation.

[0017] 2. This invention adopts a truss structure to achieve lightweighting of the resource compartment structure; the solar cell wings are installed as a whole on the truss structure, reducing the precision requirements caused by the installation of large solar cell wings across compartment sections.

[0018] 3. The present invention adopts a configuration in which the circumferential dimensions of the propulsion module, the sun-oriented device, and the truss structure decrease sequentially, which meets the space constraints of the von Kármán curve segment of the launch vehicle fairing.

[0019] 4. This invention arranges the orbital control engine along the axial direction of the aircraft at the tail of the truss structure, which reduces the impact of the engine plume on the products on the resource compartment, improves the engine thrust utilization rate, and reduces the amount of propellant carried. Attached Figure Description

[0020] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the truss-type resource compartment according to an embodiment of the present invention; Figure 2 This is an exploded view of the truss-type resource compartment according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the solar cell wing deployment according to an embodiment of the present invention; Figure 4 This is a front view of the truss-type resource compartment according to an embodiment of the present invention.

[0021] Among them, 1-propulsion module, 1a-propulsion module flange, 1b-propulsion module circumferential envelope, 2-pipe disconnector, 2a-active end, 2b-passive end, 3-solar orientation device, 3a-fixed end, 3b-rotating end, 3c-conductive slip ring, 3d-solar orientation device rotation direction, 3e-solar orientation device circumferential envelope, 4-truss structure, 4a-truss structure side, 4b-truss structure interface, 4c-truss structure tail, 4d-truss structure circumferential envelope, 5-orbit control engine, 5a-thrust shaft, 6-solar cell wing, 6a-solar cell wing deployment structure, 7-drive mechanism, 7a-drive mechanism rotation direction, 8-duct, 9-cable, 10-flight direction, 11-fairing curve segment. Detailed Implementation

[0022] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0023] This invention provides a truss-type resource module. Under the limited carrying capacity of the launch vehicle and the limited space of the fairing, by optimizing the configuration and equipment layout of the resource module, the weight of the resource module is reduced, the space utilization rate of the launch fairing and the on-orbit power generation capacity of the solar cell wing are improved, the impact of the orbital control engine plume on the products on the module is avoided and the thrust utilization rate of the orbital control engine is improved, and the installation difficulty on the solar cell wing module is reduced while ensuring accuracy.

[0024] like Figure 1 , Figure 2 As shown, the truss-type resource module of this embodiment includes a propulsion module 1, a solar orientation device 3, a truss structure 4, an orbital control engine 5, solar arrays 6, and a drive mechanism 7. The solar orientation device 3 is mounted on the propulsion module 1, the truss structure 4 is connected to one end of the solar orientation device 3, the orbital control engine 5 is mounted on the truss structure 4, the drive mechanism 7 is mounted on the truss structure 4, and the solar arrays 6 are mounted to the drive mechanism 7. The solar orientation device 3 can rotate, driving the truss structure 4 to rotate as a whole; the drive mechanism 7 can drive the solar arrays 6 to rotate. Under both rotation modes, the solar arrays 6 are oriented towards the sun, ensuring that the angle of sunlight incidence is at the optimal position.

[0025] Specifically, the propulsion module 1 has a propulsion module flange 1a for connecting with other functional modules; the sun-orienting device 3 is located at the end away from the propulsion module flange 1a.

[0026] The sun-oriented device 3 is provided with a fixed end 3a connected to the propulsion module 1 and a rotating end 3b connected to the truss structure 4. The rotating end 3b can rotate around the axis of the fixed end 3a, thus realizing the rotation of the entire truss structure 4.

[0027] To control the rotation of the rotating end 3b of the sun-orienting device 3, this embodiment also includes a pipeline disconnector 2. The pipeline disconnector 2 includes an active end 2a and a passive end 2b. The active end 2a is installed on the fixed end 3a of the sun-orienting device 3 and is connected to the propulsion module 1 through the lower conduit 8. The passive end 2b is installed on the rotating end 3b of the sun-orienting device and is connected to the track control engine 5 through the upper conduit 8.

[0028] When the track control engine 5 is working, the active end 2a and the passive end 2b of the pipeline disconnector 2 are connected, and the rotation of the rotating end 3b relative to the fixed end 3a is restricted, i.e., it stops rotating; when the track control engine 5 stops working, the active end 2a and the passive end 2b of the pipeline disconnector 2 are disconnected, and the rotating end 3b is allowed to rotate relative to the fixed end 3a.

[0029] A conductive slip ring 3c is also provided between the fixed end 3a and the rotating end 3b of the solar orientation device 3. The conductive slip ring 3c is connected to the solar cell wing 6 via a cable 9. The conductive slip ring 3c is also electrically connected to other functional modules, so that the electrical energy converted by the solar cell wing 6 can be transmitted to each functional module.

[0030] One end of the truss structure 4 is connected to the rotating end 3b of the sun-aligning device 3, so that it can rotate together with the rotating end 3b. The side 4a of the truss structure is provided with a truss structure interface 4b for connecting the drive mechanism 7; the truss structure interface 4b can be made accurate through combination processing or drilling jig process.

[0031] Truss structure 4 uses low-density materials, such as composite materials and aluminum alloys, and has high specific stiffness; the shape of truss structure 4 can be rectangular, square or cylindrical.

[0032] The orbit control engine 5 is installed at position 4c at the tail of the truss structure, and its thrust shaft 5a is parallel to the flight direction 10 of the aircraft. This can reduce the impact of the engine plume on the products on the resource compartment, improve the thrust utilization rate of the orbit control engine 5, and reduce the amount of propellant carried.

[0033] The solar array 6 can be folded and deployed. During the launch phase, it is in the folded state; after launch and entry into orbit, the solar array 6 can be deployed.

[0034] The drive mechanism 7 is fixed to the truss structure 4 through the truss structure interface 4b. The drive mechanism 7 has a rotation output end, which is connected to the solar cell wing 6 to realize the rotation of the solar cell wing 6.

[0035] like Figure 3 As shown, the solar cell wing 6 unfolds after entering orbit, forming the solar cell wing unfolding structure 6a. Driven by the drive mechanism 7, the solar cell wing unfolding structure 6a can rotate around the rotation direction 7a of the drive mechanism; under the rotation of the truss structure 4, it can rotate around the rotation direction 3d of the sun-oriented device to achieve sun-oriented orientation and ensure that the angle of sunlight incidence is at the optimal position.

[0036] like Figure 4 As shown, the circumferential envelope 1b of the propulsion module, the circumferential envelope 3e of the solar orientation device, and the circumferential envelope 4d of the truss structure are successively reduced to adapt to the shape of the fairing curve segment 11 and meet the spatial constraints of the von Kármán curve segment.

[0037] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A truss-type resource compartment, characterized in that, include: The propulsion module is capable of connecting to functional modules; A sun-oriented device having a first end and a second end opposite to each other, the first end of the sun-oriented device being connected to the propulsion module; A truss structure, which is connected to the second end of the sun-oriented device; A drive mechanism, located on the side of the truss mechanism, has a rotation output end; The solar cell fins are retractable and deployable, and are connected to the rotational output end of the drive mechanism. The track-controlled engine is mounted on the truss structure.

2. The truss-type resource compartment according to claim 1, characterized in that, The first end of the sun-aligning device is a fixed end, and the second end of the sun-aligning device is a rotating end, which can rotate about the axis of the fixed end.

3. The truss-type resource compartment according to claim 2, characterized in that, A conductive slip ring is provided between the fixed end and the rotating end, and the conductive slip ring is electrically connected to the solar cell fin.

4. The truss-type resource compartment according to claim 2, characterized in that, It also includes a pipeline disconnector, which is installed on the sun orientation device and is connected to the propulsion module and the track control engine through conduits.

5. The truss-type resource compartment according to claim 4, characterized in that, The pipeline disconnector includes an active end and a passive end. The active end is located at the fixed end and is connected to the propulsion module through a conduit. The passive end is located at the rotating end and is connected to the track control engine through a conduit.

6. The truss-type resource compartment according to claim 5, characterized in that, When the track control engine is working, the active end and the passive end are connected, and the rotating end is restricted from rotating relative to the fixed end; After the track control engine finishes working, the active end and the passive end are disconnected, and the rotating end can rotate relative to the fixed end.

7. The truss-type resource compartment according to claim 1, characterized in that, The truss structure is made of low-density material, and the shape of the truss structure is one of rectangle, square, or cylinder.

8. The truss-type resource compartment according to claim 1, characterized in that, The track control engine is located at the rear of the truss structure.

9. The truss-type resource compartment according to claim 8, characterized in that, The thrust shaft of the orbital control engine is parallel to the flight direction of the aircraft.

10. The truss-type resource compartment according to claim 1, characterized in that, The circumferential dimensions of the propulsion module, the solar orientation device, and the truss structure decrease sequentially.

Images