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Construction method of multi-section spreading arm for space-borne mesh antenna

A construction method and a technology for deploying arms, which are applied in the field of satellite antennas, can solve problems such as the mismatch between the reflector and the focus, and achieve the effect of perfectly matching the focus position of the reflector.

Active Publication Date: 2021-09-21
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, more spread arms introduce more spread joints with gaps, which can easily lead to misalignment of reflective surfaces and focal points

Method used

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  • Construction method of multi-section spreading arm for space-borne mesh antenna
  • Construction method of multi-section spreading arm for space-borne mesh antenna
  • Construction method of multi-section spreading arm for space-borne mesh antenna

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0062] Embodiment 1: as figure 1 , figure 2 , image 3 , Figure 4 As shown, a construction method of a multi-section spread arm of a spaceborne mesh antenna, including

[0063] Step 1, given the focal length f and aperture D of the mesh antenna reflector, set up the standard reflector under the global coordinate system (X, Y, Z) whose coordinate origin is point O, in the global coordinate system (X, The X axis of the (XOZ) plane of Y, Z) takes the cylindrical axis D with the offset distance d′ a , in the D a A cylinder is generated with a radius of D / 2, and the intersecting line between the cylinder and the standard reflection surface generates the offset reflection surface of the mesh antenna.

[0064] Step 2, according to described standard reflection surface and offset reflection surface, under the global coordinate system, determine the coordinates of the key nodes A and B of mesh antenna mesh surface, and calculate the height H of mesh antenna mesh surface up , th...

Embodiment 2

[0108] Embodiment 2: the same as Embodiment 1, the difference is that it also includes the height H of the upper surface of the mesh antenna calculated in the step 2 up Integrity verification step of : according to the key nodes A and B on the surface of the mesh antenna, take the cylinder axis D with the offset distance d′ a With the intersection point o of the line segment AB, the tangent direction and the normal direction of this point are the axial direction of the local coordinate system x and z, establish the local coordinate system (x, y, z) of the offset reflection surface, and make the described The projections of the upper surface and the lower surface on the (xoy) plane in the local coordinate system are completely coincident to ensure the integrity of the mesh antenna.

Embodiment 3

[0109] Embodiment 3: as Figure 5 As shown, it is the same as Embodiment 1, the difference is that the multi-section deployment arm of the present invention locks the deployment arm joints through a locking mechanism, and the deployment arm joints refer to two single-section arms of the deployment arm. The hinge 6 provided between 8, the locking mechanism includes a card slot 61 on the hinge 6, and also includes a connecting rod 7, one end of the connecting rod 7 is connected to the deployment arm, and the connecting rod 7 The other end is provided with a cross bar 71 perpendicular to the connecting rod 7. When the hinge 6 of the unfolding arm is free to rotate, the connecting rod 7 and the hinge 6 do not form a constraint relationship. k , the crossbar 71 falls into the slot 61 to lock the hinge 6. In the prior art, there are multiple structures for locking the deployment arm, and the locking structure provided by the present invention is simpler and more practical than the ...

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Abstract

The invention belongs to the technical field of satellite antennas, in particular to a method for constructing a multi-section deployment arm of a space-borne mesh antenna. The minimum length is the goal, combined with the position constraints of the mesh antenna reflector and the deployment arm, the number N and arm length L of the multi-section deployment arms are constructed. i and an optimized model under the global coordinate system, according to the model, the joints of the deployment arm are locked to complete the construction of the deployment arm; the invention ensures that the envelope requirements of the carrying fairing can be met when the multi-section deployment arms are closed; After the segment deployment arm is unfolded and locked in place, the antenna feed and the reflector focal position of the mesh antenna are perfectly matched.

Description

technical field [0001] The invention belongs to the technical field of satellite antennas, in particular to a method for constructing a mesh expandable antenna arm. Background technique [0002] Mesh deployable antennas are more and more widely used due to their wide application range, large storage rate, and light weight. Signal, improve communication efficiency, and reduce the size of the ground terminal, there are higher requirements for the on-orbit gain and pointing accuracy of the spaceborne mesh deployable antenna. As the key equipment connecting the mesh antenna and the satellite body, the deployment arm is the main part to support and fix the large-scale spaceborne mesh reflector antenna. Whether its design is reasonable is crucial to the success of the rocket transportation and space deployment of the antenna. role. [0003] However, due to the limitation of the effective carrying space of the spacecraft, the large-scale space-borne mesh deployable antenna is fix...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H01Q1/12H01Q1/10H01Q1/28H01Q1/50H01Q15/14H01Q19/10G06F30/20
CPCG06F30/20H01Q1/103H01Q1/1235H01Q1/288H01Q1/50H01Q15/14H01Q19/10
Inventor 宗亚雳张铎王杰吕昂
Owner NORTHWESTERN POLYTECHNICAL UNIV
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