Switching tool for 180-degree unfolding test of solar wing of moonlet

Abstract

The utility model provides a switching tool for a 180-degree unfolding test of a solar wing of a moonlet. The switching tool comprises a switching platform and a switching ring, two circles of small satellite interfaces are symmetrically arranged on the switching platform; an operation hole is formed in the center of the switching platform; a plurality of through holes are evenly distributed in the upper end face and the lower end face of the adapter ring in the circumferential direction, and the adapter ring is connected with the adapter platform through the through hole in the lower portion and in butt joint with the moonlet through the through hole in the upper portion. When the switching tool is installed on the existing two-shaft rotary table, the requirement that no interference exists in the 180-degree unfolding range of the solar wing wall plate during the 180-degree unfolding test of the solar wing can be met.

Description

Technical Field

[0001] The utility model belongs to the technical field of small satellite assembly equipment, and in particular relates to a switching tool used for a 180-degree unfolding test of a small satellite solar wing. Background Art

[0002] When a small satellite conducts a solar panel deployment test, the satellite usually has two states: vertical and horizontal. The vertical state only requires the small satellite to be placed on a horizontal parking bracket, while the horizontal state requires a two-axis turntable to flip the small satellite into a horizontal state for the test.

[0003] When a small satellite uses a two-axis turntable to conduct a solar wing deployment test, the deployed state of the small satellite's solar wing panels is usually 90 degrees perpendicular to the satellite's side panels. In this way, when the solar wing is deployed, it is only necessary to ensure that there is no interference within the 90-degree deployment range of the solar wing panels.

[0004] However, with the development and changes of small satellites, the unfolded state of the solar wing panels of some small satellites is 180 degrees parallel to the satellite side panels. During the unfolding process, the solar wing panels will unfold 180 degrees. Therefore, when the solar wing is unfolded, it is necessary to ensure that there is no interference within the 180-degree unfolding range of the solar wing panels. However, when the existing two-axis turntable is in the flipped state, its support frame will interfere with the 180-degree unfolded state of the solar wing panels, which does not meet the requirements of the solar wing unfolding test. Utility Model Content

[0005] The technical problem solved by the utility model is: to overcome the shortcomings of the prior art and provide a transfer fixture for a small satellite solar wing 180-degree deployment test. The transfer fixture is installed on an existing two-axis turntable to meet the requirement that there is no interference within the 180-degree deployment range of the solar wing wall panel when the solar wing is subjected to a 180-degree deployment test.

[0006] The technical solution of the utility model is: a transfer tooling for a 180-degree deployment test of a small satellite solar wing, comprising a transfer platform and a transfer ring;

[0007] Two circles of small satellite interfaces are symmetrically arranged on the transfer platform; an operation hole is arranged at the center of the transfer platform;

[0008] The upper and lower end surfaces of the adapter ring are respectively provided with a plurality of through holes evenly distributed along the circumferential direction. The adapter ring is connected to the adapter platform through the lower through holes and docked with the small satellite through the upper through holes.

[0009] Furthermore, the middle part of the transfer platform is a rectangular plate, and the two sides are semicircular plates, and the diameter of the semicircular plate is the side of the middle rectangular plate; the two circles of small satellite interfaces are through holes, which are distributed circumferentially with the center of the semicircular plates on both sides as the center.

[0010] Furthermore, the center distance of the pitch circles of the two circles of small satellite interfaces is adjusted according to the interference between the small satellite solar panels and the two-axis turntable.

[0011] Furthermore, the height of the adapter ring is adjusted according to the size of the small satellite.

[0012] Furthermore, the adapter tooling for the 180-degree deployment test of a small satellite solar wing also includes eye screws, which are symmetrically distributed on the surface of the adapter platform.

[0013] The advantages of the utility model compared with the prior art are:

[0014] The utility model provides a transfer tool for a small satellite solar wing 180-degree deployment test, which creates conditions for a small satellite solar wing to perform a 180-degree deployment test. By installing the transfer tool on an existing two-axis turntable, the requirement of no interference within the 180-degree deployment range of the solar wing wall panel can be met when the solar wing performs a 180-degree deployment test. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is the structural front view of the utility model;

[0016] Figure 2 It is a top view of the structure of the utility model;

[0017] Figure 3 It is a left view of the structure of the utility model;

[0018] Figure 4 It is a structural oblique view of the utility model.

[0019] In the figure: 1. Adapter platform; 2. Adapter ring; 3. Eyebolt; 4. Two-axis turntable interface; 5. Satellite interface. DETAILED DESCRIPTION

[0020] The utility model is described in detail below in conjunction with the accompanying drawings. The following embodiments will help those skilled in the art to further understand the utility model, but do not limit the utility model in any form. It should be pointed out that for those of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the utility model. These all belong to the protection scope of the utility model.

[0021] The utility model discloses a transfer tool for a 180-degree unfolding test of a small satellite solar wing. The transfer tool is installed on an existing two-axis turntable to meet the 180-degree unfolding test requirement of a small satellite solar wing wall panel.

[0022] like Figure 1As shown, the utility model is a transfer tool for a 180-degree deployment test of a small satellite solar wing, which mainly includes a transfer platform 1, a transfer ring 2, and eyebolts 3. The transfer platform 1 and the transfer ring 2 are fixed together with 32 M5 screws and nuts, and the four eyebolts 3 are symmetrically distributed on the surface of the transfer platform 1 and are mainly used for the lifting of the transfer tool.

[0023] like Figure 2 As shown, the upper end surface of the adapter ring 2 is equipped with a small satellite interface 5, which is mainly composed of 32 through holes with a diameter of 6 mm and 8 through holes with a diameter of 20 mm, and is used to connect with the satellite. The adapter platform 1 is equipped with a small satellite interface 4, which is connected to the two-axis turntable with 32 M5mm screws and nuts.

[0024] The center distance of the two circles of small satellite interfaces 4 on the transfer platform 1 is 150 mm, which solves the problem of interference between the existing two-axis turntable support frame and the 180-degree unfolded state of the solar wing wall panel.

[0025] When the transfer tooling for the 180-degree deployment test of the small satellite solar wing of the utility model is docked with the existing two-axis turntable, the following steps are implemented:

[0026] 1. Connect the universal lifting strap to the four lifting eye screws on the adapter tooling.

[0027] 2. Move the crane hook to a suitable position above the transfer tooling.

[0028] 3. Connect the main lifting ring of the universal lifting strap to the hook of the crane.

[0029] 4. Command the crane to lift and hoist the transfer tooling to the docking surface with the existing two-axis turntable, and use 32 M5 screws to reliably connect the transfer tooling to the two-axis turntable.

[0030] 5. Disconnect the connection between the universal lifting strap and the four lifting eye screws of the adapter tooling.

[0031] 6. Remove the universal sling.

[0032] 7. Hoist the small satellite onto the satellite docking surface of the adapter ring 1 of the adapter tooling, and use 32 M5mm screws and nuts to securely fix the small satellite on the satellite docking surface of the adapter tooling.

[0033] Example

[0034] A transfer tooling for a 180-degree deployment test of a small satellite solar wing is mainly composed of a transfer platform 1, a transfer ring 2, and a lifting eye screw 3. The transfer platform 1 is in an oblong shape with a thickness of 30 mm. Two circles of small satellite 937 interfaces are provided on the end face of the platform. Each circle of small satellite 937 interfaces consists of 32 evenly distributed through holes with a diameter of 6 mm. The center distance of the two circles of small satellite 937 interfaces is 150 mm. This distance can be adaptively adjusted according to the interference between the small satellite solar wing and the two-axis turntable. A 400 mm diameter operating hole is provided in the middle of the transfer platform 1 for the installation of the transfer tooling and the two-axis turntable docking screws.

[0035] The adapter ring 2 is 250mm high, and the height can be adjusted according to the actual situation of the small satellite. The upper and lower end surfaces of the adapter ring 2 are equipped with small satellite 937 interfaces. The lower interface is connected to the adapter platform 1 with 32 M5mm screws and nuts, and the upper interface is connected to the small satellite.

[0036] The utility model provides a transfer tool for a small satellite solar wing 180-degree deployment test, which creates conditions for a small satellite solar wing to carry out a 180-degree deployment test. The transfer tool is installed on an existing two-axis turntable to meet the requirements for a small satellite solar wing wall panel 180-degree deployment test.

[0037] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various modifications or variations within the scope of the claims, which does not affect the essence of the present invention.

[0038] The parts of the present invention that are not described in detail belong to the well-known technologies for those skilled in the art.

Claims

1. A transfer tool for a 180-degree deployment test of a small satellite solar wing, characterized in that: It comprises a transfer platform (1) and a transfer ring (2); Two circles of small satellite interfaces are symmetrically arranged on the transfer platform (1); an operation hole is arranged at the center of the transfer platform (1); The upper and lower end surfaces of the adapter ring (2) are respectively provided with a plurality of through holes evenly distributed along the circumferential direction; the adapter ring (2) is connected to the adapter platform (1) through the lower through holes and docked with the small satellite through the upper through holes.

2. The adapter tool for a 180-degree deployment test of a small satellite solar wing according to claim 1, characterized in that: The middle part of the transfer platform (1) is a rectangular plate, and the two sides are semicircular plates, the diameter of the semicircular plate is the side of the middle rectangular plate; the two circles of small satellite interfaces are through holes, which are distributed around the circumference with the center of the semicircular plates on the two sides as the center.

3. The adapter tool for a 180-degree deployment test of a small satellite solar wing according to claim 1, characterized in that: The center distance of the pitch circles of the two circles of small satellite interfaces is adjusted according to the interference between the small satellite solar panels and the two-axis turntable.

4. The adapter tool for a 180-degree deployment test of a small satellite solar wing according to claim 1, characterized in that: The height of the adapter ring (2) is adjusted according to the size of the small satellite.

5. The adapter tool for a 180-degree deployment test of a small satellite solar wing according to claim 1, characterized in that: It also comprises eye screws (3), wherein the eye screws (3) are symmetrically distributed on the surface of the transfer platform (1).

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