Modular satellite structure arrangement for low cost

Abstract

The application discloses a low-cost modular satellite structure device, a module unit, a body-mounted solar wing and a deployed solar wing, the module unit is several, and every two module units are connected through a pin rod assembly, the body-mounted solar wing is fixedly installed on the front surface of a module satellite composed of the module units, and the deployed solar wing is fixedly installed on the side wall of the module satellite composed of the module units through a width plate assembly; the combination of the pin rod assembly and the module unit is more compact and stable, and the combination precision can be ensured; the modular assembly enables the module units to be quickly assembled, the module unit design can reduce the overall research and development and production manufacturing cost, the identification block is arranged, so that the automatic assembly can be realized in the assembly process; the module unit design enables the module units to be quickly replaced and maintained in limited space, which is convenient and fast.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of satellite structures, in particular to a low-cost modular satellite structure device. BACKGROUND

[0002] With the continuous development of miniaturization and improved operation performance of microelectronic technology, a series of satellite design ideas have emerged, the ability of satellite commercial use is continuously improved, and the functions that can be realized by satellites are more and more, and because the types of satellite payloads are various and space flight tasks are various, the performance indexes of satellites are different, the design and development mode centered on the satellite platform, the development mode relying on physical tests and the management mode of serial work have been difficult to realize the development goals of high performance, short cycle and low cost of satellites, and the commercial value of satellites cannot be maximized. The satellite modular design method has the characteristics of short development cycle and flexible and rapid layout of satellite structures, and is more and more applied to the research and production of satellites. At present, the modular structure is only imagined, and the overall structure design is not specifically designed.

[0003] Therefore, it is necessary to design a low-cost modular satellite structure device with high practicability. SUMMARY

[0004] The application aims to provide a low-cost modular satellite structure device to solve the problems in the background art.

[0005] In order to solve the above technical problems, the application provides the following technical scheme:

[0006] The low-cost modular satellite structure device comprises module units, a body-mounted solar wing and an unfolded solar wing, the module units are a plurality of, and each two module units are connected through a pin rod assembly, the body-mounted solar wing is fixedly installed on the front surface of a module satellite composed of a plurality of module units, and the unfolded solar wing is fixedly installed on the side wall of a module satellite composed of a plurality of module units through a width plate assembly.

[0007] The module unit is a regular hexahedron structure, a rotating dovetail table is integrally formed in the middle part of each face, and a countersunk groove is formed at both ends of the penetrating pin groove.

[0008] The pin rod assembly comprises a connecting pin and a tension nut, the rod body of the connecting pin is integrally formed with a rotating dovetail groove, any end of the connecting pin is provided with a threaded portion, the threaded portion is cut to have a limiting surface, the tension nut is screwed at the threaded portion, and an anti-loosening washer is clamped between the connecting pin and the tension nut.

[0009] According to the above technical scheme, the eight corners of the module unit are provided with embedding grooves, and the embedding grooves are embedded with identification blocks.

[0010] According to the above technical scheme, the pin slot is a semicircle, the rotating dovetail table is a quarter of a ring length, and the rotating dovetail table is symmetrical with the excess on both sides of the pin slot.

[0011] According to the above technical scheme, the rotating dovetail groove is formed by opposite bosses, the diameter of the boss is the same as the diameter of the pin slot, and the ring groove of the rotating dovetail groove is a quarter of the circumference.

[0012] According to the above technical scheme, the pin slot is divided into two sections based on the intersection, and one rotating dovetail table is arranged in each section of the pin slot.

[0013] According to the above technical scheme, the rotating dovetail groove is two, and the position matches the rotating dovetail table.

[0014] According to the above technical scheme, the anti-loose washer includes a ring piece and an embedded body, and the outer diameter of the embedded body is the same as the inner diameter of the pin slot. The lower end and the upper end of the anti-loose washer leave a gap with the upper boss of the rotating dovetail groove.

[0015] According to the above technical scheme, a limiting slot is formed in the middle of the ring piece of the anti-loose washer, and the limiting slot matches the threaded part and the limiting surface thereof.

[0016] According to the above technical scheme, the surface of the module unit is embedded with a standardized port, and the standardized port is not located in the pin slot.

[0017] Compared with the prior art, the beneficial effects achieved by the present application are:

[0018] 1) Through the combination of the pin rod assembly and the module unit, the combination between the module units is more compact and stable, and the combination accuracy can be ensured;

[0019] 2) Through modular assembly, the module units can be quickly assembled, and the modular design can reduce the overall research and production manufacturing cost;

[0020] 3) The identification block is arranged, so that the automatic assembly can be realized during the assembly process, and the assembly speed can be accelerated;

[0021] 4) Through the modular design, the module units can be quickly replaced, and the module units can be quickly repaired in a limited space, which is convenient and fast. BRIEF DESCRIPTION OF DRAWINGS

[0022] The accompanying drawings are used to provide a further understanding of the present application, and constitute a part of the specification. Together with embodiments of the present application, they are used to explain the present application, and do not constitute a limitation on the present application. In the drawings:

[0023] Figure 1 is a schematic diagram of the on-orbit attitude structure of the present application;

[0024] Figure 2 is the schematic diagram of the assembled explosion structure of the module unit of the present application;

[0025] Figure 3 is the schematic diagram of the sectional structure of the pin rod assembly of the present application;

[0026] Figure 4 is the schematic diagram of the combined structure of the pin rod assembly and the module unit of the present application;

[0027] Figure 5 is the schematic diagram of the sectional structure of the lock washer of the present application.

[0028] In the figure: 1, module unit, 2, body-mounted solar wing, 3, unfolded solar wing, 4, pin rod assembly, 41, connecting pin, 42, tension nut, 43, rotating dovetail groove, 44, lock washer, 5, pin-through groove, 6, rotating dovetail table, 7, identification block. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0030] Please refer to Figures 1-5 The present application provides the technical solution: a low-cost modular satellite structure device, a module unit 1, a body-mounted solar wing 2 and an unfolded solar wing 3, the module unit 1 is a plurality of, and every two module units 1 are connected through a pin rod assembly 4, the body-mounted solar wing 2 is fixedly installed on the front surface of the module satellite composed of a plurality of module units 1, and the unfolded solar wing 3 is fixedly installed on the side wall of the module satellite composed of a plurality of module units 1 through a width plate assembly; the module unit 1 is a regular hexahedron structure, and a pin-through groove 5 is formed in the middle of each face, a rotating dovetail table 6 is integrally formed in the pin-through groove 5, and a countersunk groove is formed at both ends of the pin-through groove 5; the pin rod assembly 4 comprises a connecting pin 41 and a tension nut 42, a rotating dovetail groove 43 is integrally formed on the rod body of the connecting pin 41, a threaded portion is formed at either end of the connecting pin 41, and the threaded portion is cut to a limit surface, the tension nut 42 is screwed at the threaded portion, and a lock washer 44 is clamped between the connecting pin 41 and the tension nut 42.

[0031] Module unit 1 is the basic design unit, through milling, sheet metal and punching of aluminum alloy material, constitutes the outer shell, built-in satellite electronic components, pin rod assembly 4 through the connecting pin 41 of its own cooperation with rotating dovetail groove 43, on the rotating dovetail table 6 in the spin slot 5 effective combination limit, in turn through the rotating dovetail table 6 on the module unit 1 tension combination, so as to ensure the tightness of the whole combination, while the rotating dovetail table 6 and rotating dovetail groove 43 cooperate, under the action of tension nut, make the two adhere more tightly, and the lock washer 44 through its own structure, so that the pre-tightening force can be effectively collected, ensure the stability of the tension nut 42 work.

[0032] Specifically, the eight corners of the module unit 1 are provided with embedding grooves, and the embedding grooves are embedded with identification blocks 7.

[0033] By embedding grooves in the module unit 1 and embedding identification blocks 7, the position, orientation and angle of the module unit 1 can be quickly and accurately identified during automatic installation, so as to realize the convenience of the whole.

[0034] Specifically, the spin slot 5 is semicircular, the rotating dovetail table 6 is one fourth of the ring length, and the rotating dovetail table 6 is symmetrical with the excess on both sides of the spin slot 5.

[0035] Through the semicircle of the spin slot 5, it is ensured that when two module units 1 are combined, a complete cylinder structure can be formed, and the structure design of the rotating dovetail table 6 and the spin slot 5 makes the two rotating dovetail tables 6 at the same position after combination can be distributed symmetrically, which can ensure that the pin rod assembly 4 can rotate 90° after combination to ensure the tightness of the combination.

[0036] Specifically, the rotating dovetail groove 43 is composed of opposite bosses, the diameter of the boss is the same as the diameter of the spin slot 5, and the ring groove of the rotating dovetail groove 43 is four times the length.

[0037] It can be effectively used with the rotating dovetail table 6.

[0038] Specifically, the spin slot 5 is divided into two sections based on the intersection, and one rotating dovetail table 6 is arranged in each spin slot 5.

[0039] Through the cross two-section structure and the rotating dovetail table 6 arranged respectively, the uniformity of the force after combination can be ensured, the unilateral force can be avoided, and the stability of the whole structure can be increased.

[0040] Specifically, the rotating dovetail groove 43 is two, and the position matches the rotating dovetail table 6.

[0041] Ensure the accuracy and stability of cooperation.

[0042] Specifically, the anti-loose washer 44 comprises a ring piece and an embedded body, and the outer diameter of the embedded body is the same as the inner diameter of the pin hole 5, and the lower end of the anti-loose washer 44 leaves a clearance gap with the upper boss of the rotating dovetail groove 43.

[0043] Through the embedded anti-loose washer 44, the stability of the combination of the pin rod assembly 4 and the pin hole 5 can be better ensured after being pressed, and the stress structure is also prolonged, so that more load can be carried after being stressed.

[0044] Specifically, a limiting slot is formed in the middle of the ring piece of the anti-loose washer 44, and the limiting slot matches the threaded part and its limiting surface.

[0045] Through the limiting slot, the anti-loose washer 44 can be prevented from rotating synchronously when the lock nut 42 is rotated, so as to affect the anti-loose effect.

[0046] Specifically, the surface of the module unit 1 is embedded with a standardized port, and the standardized port is not located in the pin hole 5.

[0047] Through the setting of the standardized port, the module unit 1 can be electrically connected to each other after assembly, so as to form a complete star body.

[0048] Working principle: in use, based on the prompt of the identification block 7, the adjacent module units 1 are basicly adhered, the pin rod assembly 4 is embedded into the cylinder groove formed by the pin hole 5 after adhesion, and then the rotating dovetail groove 43 on the connecting pin 41 is wedged with the rotating dovetail table 6 through rotation, so as to effectively and fixedly combine the adjacent unit modules, and then the connecting pin 41 is made to go up through the rotation of the lock nut 42, so as to realize the close adhesion of the rotating dovetail groove 43 and the rotating dovetail table 6, and under the action of the anti-loose washer 44, the anti-loose effect is avoided, so as to ensure the close connection.

[0049] It should be noted that in this paper, relationship terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment.

[0050] Finally, it should be noted that the above only describes the preferred embodiments of the present application and is not intended to limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art will appreciate that the technical solutions described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalent ones. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. Modular satellite structure arrangement for low cost, module unit (1), body mounted solar wing (2) and deployed solar wing (3), characterized in that: The module unit (1) is a plurality of, and each two module units (1) are connected by pin rod assembly (4), the body-mounted solar wing (2) is fixedly installed on the front surface of the module satellite composed of a plurality of module units (1), and the unfolded solar wing (3) is fixedly installed on the side wall of the module satellite composed of a plurality of module units (1). The module unit (1) is a regular hexahedron structure, and a through pin slot (5) is formed in the middle of each face, the through pin slot (5) is integrally formed with a rotating dovetail table (6), and the through pin slot (5) is provided with a countersunk groove at both ends. The pin rod assembly (4) comprises a connecting pin (41) and a tension nut (42), the rod body of the connecting pin (41) is integrally formed with a rotating dovetail groove (43), any end of the connecting pin (41) is provided with a threaded portion, and the threaded portion is cut to a limit surface, the tension nut (42) is screwed on the threaded portion, and the connecting pin (41) is clamped with a lock washer (44).

2. The low-cost oriented modular satellite structural arrangement according to claim 1, characterized in that: The eight corners of the module unit (1) are provided with embedding grooves, and the embedding grooves are embedded with identification blocks (7).

3. The low-cost oriented modular satellite structural arrangement according to claim 1, characterized in that: The through pin slot (5) is a semicircle, the rotating dovetail table (6) is a quarter ring length, and the rotating dovetail table (6) is symmetrical with the remaining amount on both sides of the through pin slot (5).

4. The low-cost oriented modular satellite structural arrangement according to claim 1, characterized in that: The rotating dovetail groove (43) is formed by opposite bosses, the diameter of the boss is the same as the diameter of the through pin slot (5), and the ring groove of the rotating dovetail groove (43) is a quarter of the circumference.

5. The low-cost oriented modular satellite structural arrangement according to claim 3, characterized in that: The through pin slot (5) is divided into two sections based on the intersection point, and one rotating dovetail table (6) is arranged in each section of the through pin slot (5).

6. The low-cost oriented modular satellite structural arrangement according to claim 4, characterized in that: The rotating dovetail groove (43) is two, and the position matches the rotating dovetail table (6).

7. The low-cost oriented modular satellite structural arrangement according to claim 1, characterized in that: The lock washer (44) comprises a ring piece and an embedded body, and the outer diameter of the embedded body is the same as the inner diameter of the through pin slot (5), and the lower end and the upper end of the lock washer (44) are provided with a gap between the upper boss of the rotating dovetail groove (43).

8. The low-cost oriented modular satellite structural arrangement according to claim 7, characterized in that: The limit slot in the middle of the ring piece of the lock washer (44) matches the threaded portion and the limit surface thereof.

9. The low-cost oriented modular satellite structural arrangement according to claim 1, characterized in that: The surface of the module unit (1) is embedded with a standardized port, and the standardized port is not located in the through pin slot (5).

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