A pneumatically extendable spaceborne monocone deployable antenna and its deployment method

Abstract

This invention discloses a pneumatically extendable spaceborne single-cone deployable antenna and its deployment method. In the telescopic mechanism of this invention, sleeves one, two, three, four, and five, and a cylindrical column are nested sequentially to form a telescopic rod. Locking elements one, two, three, four, and five are respectively installed inside sleeves two, three, four, and the cylindrical column. An airbag is placed inside the telescopic rod. In the tensioning mechanism, an adjusting bolt is located inside the cylindrical column, and the bottom end of the adjusting bolt forms a rotating pair with a limiting block. A tensioning disc is connected to the adjusting bolt through a threaded hole. This invention allows the antenna cone to be folded before entering space, reducing its volume and achieving a higher spatial convergence rate while saving rocket payload space. After entering space, the expansion of the airbag causes the telescopic rod to extend, thereby deploying the antenna cone.

Description

Technical Field

[0001] This invention belongs to the field of spaceborne antenna technology, specifically relating to an aerodynamically extendable spaceborne single-cone deployable antenna and its deployment method. Background Technology

[0002] In order to make efficient use of the rocket's payload capacity, onboard antennas, solar panels, and other equipment need to be kept in a folded position during launch and then unfolded and put into working condition after the satellite enters orbit.

[0003] The single-cone antenna in spaceborne antennas has non-frequency-varying characteristics and has the advantages of simple structure and light weight, which can effectively reduce the mass of rockets. However, there is currently no spaceborne single-cone deployable antenna. The single-cone antenna occupies a large space in the rocket's storage space. Therefore, it is necessary to design a single-cone deployable antenna suitable for spaceborne conditions, which can improve the space convergence rate, save rocket launch space, and ensure the accuracy of the antenna profile. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and to propose an aerodynamically extendable spaceborne monocone deployable antenna and its deployment method.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] The present invention discloses a pneumatically extendable spaceborne single-cone deployable antenna, comprising a telescopic mechanism, a tensioning mechanism, an antenna cone, a fixed base, and an air source device.

[0007] The telescopic mechanism includes sleeve 1, sleeve 2, sleeve 3, sleeve 4, sleeve 5, a column, an airbag, and an end cap; the diameters of sleeve 1, sleeve 2, sleeve 3, sleeve 4, sleeve 5, and the column decrease sequentially, and sleeve 1, sleeve 2, sleeve 3, sleeve 4, sleeve 5, and the column are nested sequentially to form a telescopic rod; the upper end of the inner wall of sleeve 1, the lower end of the inner wall of the column, and both ends of the inner walls of sleeve 2, sleeve 3, sleeve 4, and sleeve 5 are each provided with n column holes arranged equidistantly along the circumference, where n≥2; locking elements 1, 2, 3, 4, and 5 are respectively fixed at the lower column holes in sleeve 2, sleeve 3, sleeve 4, sleeve 5, and the column. Locking components one, two, three, four, and five are all elastic annular pieces, and each annular piece has n integrally formed cylindrical pins arranged equidistantly along its outer edge. Each cylindrical pin on locking components one, two, three, four, and five is embedded in a cylindrical hole at the lower end of sleeve two, sleeve three, sleeve four, sleeve five, and cylindrical tube, forming a sliding pair with the corresponding cylindrical hole. The outer end of each cylindrical pin has an integrally formed ball head. The end cap is fixed to the lower end of sleeve one. The airbag is placed in the inner cavity of the telescopic rod, and the upper end of the airbag is fixed to the lower end of the cylindrical tube. The inflation tube at the lower end of the airbag passes through the circular hole on the end cap and is connected to the air source device.

[0008] The tensioning mechanism includes a limiting block, an adjusting bolt, a tensioning disc, and a positioning pin. The adjusting bolt is located inside the column, and its bottom end forms a rotating pair with the limiting block. The tensioning disc is connected to the adjusting bolt through a threaded hole. The integrally formed column at the bottom of the tensioning disc is embedded in the inner cavity of the column, forming a sliding pair with the column. The integrally formed ring at the top of the tensioning disc has multiple sets of holes arranged equidistantly along the circumference. Each set of holes consists of two opposite holes. The adjusting bolt has a waist-shaped groove, and the positioning pin passes through the waist-shaped groove and one of the sets of holes.

[0009] The antenna cone is funnel-shaped, with its upper end fixed to the tensioning disc and its lower end fixed to the upper end of a cylindrical frustum integrally formed on the sleeve; the fixed base is fixed to the lower end of the cylindrical frustum integrally formed on the sleeve.

[0010] Among them, the integrally formed column of sleeve 2, sleeve 3, sleeve 4, sleeve 5, column and tensioning plate are all prisms, the inner cavity of sleeve 1, sleeve 2, sleeve 3, sleeve 4, sleeve 5 and column are all prisms, and the antenna cone is formed by woven metal wire.

[0011] Preferably, the gas source device includes a compressed gas cylinder, a pressure reducing valve, a solenoid valve, and a gas delivery pipe. The outlet of the compressed gas cylinder is connected to the inlet of the pressure reducing valve, the outlet of the pressure reducing valve is connected to the inlet of the solenoid valve, the outlet of the solenoid valve is connected to the inlet of the gas delivery pipe, and the outlet of the gas delivery pipe is connected to the inflation pipe of the air bag. The compressed gas cylinder is filled with inert gas.

[0012] Preferably, the limiting block includes a limiting body one and a limiting body two, which are fixed inside the column cylinder. The grooves on the limiting body one and the limiting body two are combined to form a stepped hole, and the bolt head of the adjusting bolt is placed in the stepped hole.

[0013] The present invention discloses a method for deploying a pneumatically extendable spaceborne monocone antenna, as detailed below:

[0014] In the initial state, the airbag, telescopic rod, and antenna cone are in a folded state, and locking parts one, two, three, four, and five are all in a compressed state. The ball heads integrally formed on the cylindrical pins of locking parts one, two, three, four, and five respectively abut against the inner sidewalls of sleeve one, two, three, four, and five.

[0015] After the satellite enters its space orbit, the gas supply device inflates the airbag. The airbag expands, which in turn moves the cylindrical tube upward, extending the telescopic rod. This extension, along with the tensioning disc, causes the antenna cone to unfold upward until the telescopic rod is fully extended and locked. Each cylindrical pin on locking component one, two, three, four, and five is embedded in a cylindrical hole at the upper end of sleeve one, two, three, four, and five, respectively. The antenna cone is fully extended and in a tensioned state.

[0016] Preferably, before satellite launch, the antenna cone is first adjusted to its tensioned state after deployment via a tensioning mechanism, and then compressed back to its initial state. The specific process is as follows:

[0017] Manually remove the positioning pin and turn the adjusting bolt clockwise. The tensioning disc moves downward to the lowest position. Then, the air source device inflates the airbag. The airbag expands, which in turn drives the column to move upward. The telescopic rod extends and drives the antenna cone upward through the tensioning disc until the telescopic rod is fully extended and locked. At this time, the antenna cone is not fully extended. Then, turn the adjusting bolt counterclockwise. The tensioning disc drives the antenna cone to continue to extend upward until the antenna cone is in a tensioned state. Insert the positioning pin into the waist-shaped groove and the set of holes opposite the waist-shaped groove. Finally, turn off the air source device and compress the telescopic rod to the initial state.

[0018] The beneficial effects of the present invention are as follows:

[0019] This invention reduces the size of the antenna cone by folding the telescopic rod before launch, thereby improving the space folding efficiency and saving rocket payload space. Once in orbit, an air supply device inflates the airbag, which inflates and simultaneously extends and locks the telescopic rod, thus deploying the antenna cone and ensuring a stable deployment. Furthermore, the invention utilizes a tensioning mechanism pre-adjusted before launch to prevent the antenna cone from becoming too loose or too tight after deployment, maintaining good surface accuracy and minimizing damage. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 This is a cross-sectional view of the telescopic mechanism, tensioning mechanism, antenna cone, and fixed base in this invention;

[0022] Figure 3 This is a cross-sectional view of the telescopic mechanism in the extended state in this invention;

[0023] Figure 4 This is a cross-sectional view of the telescopic mechanism in the present invention in its folded state;

[0024] Figure 5 This is a cross-sectional view of the tensioning mechanism in this invention;

[0025] Figure 6 This is a cross-sectional view of the antenna cone in this invention;

[0026] Figure 7 This is a schematic diagram of the structure of the fixed base in this invention;

[0027] Figure 8 This is a schematic diagram of the gas source device in this invention. Detailed Implementation

[0028] The present invention will now be further described with reference to the accompanying drawings.

[0029] like Figure 1 and Figure 2 As shown, the present invention provides a pneumatically extendable spaceborne single-cone deployable antenna, comprising a telescopic mechanism 1, a tensioning mechanism 2, an antenna cone 3, a fixed base 4, and an air source device 5.

[0030] like Figure 3 and Figure 4As shown, the telescopic mechanism 1 includes sleeve 1-1, sleeve 2-2, sleeve 3-3, sleeve 4-4, sleeve 5-5, column 1-6, airbag 1-12, and end cap 1-13; the diameters of the vertically arranged sleeve 1-1, sleeve 2-2, sleeve 3-3, sleeve 4-4, sleeve 5-5, and column 1-6 decrease sequentially, and the sleeve 1-1, sleeve 2-2, sleeve 3-3, sleeve 4-4, sleeve 5-5, and column 1-6 are nested sequentially to form a telescopic rod; The upper end of the inner wall of sleeve 1-1, the lower end of the inner wall of column 1-6, and both ends of the inner walls of sleeve 2-2, sleeve 3-3, sleeve 4-4, and sleeve 5-5 are each provided with n column holes arranged equidistantly along the circumference, where n≥2; locking elements 1-7, 2-8, 3-9, 4-10, and 5-1-1 are respectively fixed at the positions of the lower column holes in sleeve 2-2, sleeve 3-3, sleeve 4-4, sleeve 5-5, and column 1-6. 1 (Each locking element is elastically pressed into its corresponding sleeve or cylinder). Locking elements 1-7, 1-8, 1-9, 1-10, and 1-11 are all elastic annular pieces, and each annular piece has n integrally formed cylindrical pins evenly spaced circumferentially along its outer edge. Each cylindrical pin on locking elements 1-7, 1-8, 1-9, 1-10, and 1-11 is respectively embedded in sleeve 2-2, sleeve 3-2, sleeve 4-2, sleeve 5-2, and sleeve 6-3. 3. Sleeves 1-4, 1-5, and 1-6 are located in a column hole at the lower end, forming a sliding pair with the corresponding column hole. The outer end of each cylindrical pin is provided with an integrally formed ball head. End cap 1-13 is fixed to the lower end of sleeve 1-1. Airbag 1-12 is placed in the inner cavity of the telescopic rod, and the upper end of airbag 1-12 is fixed to the lower end of column 1-6. The inflation tube at the lower end of airbag 1-12 passes through the round hole opened on end cap 1-13 and is connected to air source device 5. Air source device 5 provides gas to airbag 1-12.

[0031] like Figure 5As shown, the tensioning mechanism 2 includes a limiting block, an adjusting bolt 2-3, a tensioning disc 2-4, and a positioning pin 2-5. The adjusting bolt 2-3 is vertically placed inside the column 1-6, and the bottom end of the adjusting bolt 2-3 forms a rotating pair with the limiting block. The tensioning disc 2-4 is connected to the adjusting bolt 2-3 through a threaded hole. The integrally formed column at the bottom of the tensioning disc 2-4 is embedded in the inner cavity of the column 1-6, forming a sliding pair with the column 1-6. The integrally formed ring at the top of the tensioning disc 2-4 has multiple sets of holes arranged equidistantly along the circumference. Each set of holes consists of two holes facing each other. The adjusting bolt 2-3 has a waist-shaped groove, and the positioning pin 2-5 passes through the waist-shaped groove and one of the sets of holes. Rotating the adjusting bolt 2-3 can drive the tensioning disc 2-4 to move up and down. The waist-shaped groove ensures that when a certain set of holes aligns with the tensioning disc 2-4 during its up and down movement, the positioning pin 2-5 can pass through the adjusting bolt 2-3.

[0032] like Figure 6 As shown, the antenna cone 3 is funnel-shaped. The upper end of the antenna cone 3 is fixed to the tensioning disc 2-4, and the lower end is fixed to the upper end of the integrally formed circular platform on the sleeve 1-1. Figure 7 As shown, the fixed base 4 is fixed to the lower end of the integrally formed frustum on the sleeve 1-1.

[0033] Among them, the integrally formed columns on sleeve 1-2, sleeve 3-3, sleeve 4-4, sleeve 5-5, column 1-6 and tensioning disc 2-4 are all prismatic, the inner cavities of sleeve 1-1, sleeve 2-2, sleeve 3-3, sleeve 4-4, sleeve 5-5 and column 1-6 are all prismatic, and the antenna cone 3 is formed by braiding metal wire.

[0034] As a preferred embodiment, such as Figure 8 As shown, the gas source device 5 includes a compressed gas cylinder 5-1, a pressure reducing valve 5-2, a solenoid valve 5-3, and a gas delivery pipe 5-4. The outlet of the compressed gas cylinder 5-1 is connected to the inlet of the pressure reducing valve 5-2, the outlet of the pressure reducing valve 5-2 is connected to the inlet of the solenoid valve 5-3, the outlet of the solenoid valve 5-3 is connected to the inlet of the gas delivery pipe 5-4, and the outlet of the gas delivery pipe 5-4 is connected to the inflation pipe of the air bag 1-12. The compressed gas cylinder 5-1 is filled with inert gas, and the pressure reducing valve 5-2 is used to control the output gas pressure of the compressed gas cylinder 5-1.

[0035] In a preferred embodiment, the limiting block includes limiting body 2-1 and limiting body 2-2. Limiting body 2-1 and limiting body 2-2 are fixed inside the column cylinder 1-6, and the grooves opened on limiting body 2-1 and limiting body 2-2 are combined to form a stepped hole. The bolt head of adjusting bolt 2-3 is placed in the stepped hole (but the cross groove of the bolt head is not covered by limiting body 2-1 and limiting body 2-2).

[0036] Both the pressure reducing valve 5-2 and the solenoid valve 5-3 are controlled by the controller.

[0037] The present invention discloses a method for deploying a pneumatically extendable spaceborne monocone antenna, as detailed below:

[0038] In the initial state, the airbag 1-12, telescopic rod and antenna cone 3 are all in a folded state, and locking parts 1-7, 1-8, 1-9, 1-10 and 1-11 are all in a compressed state. The ball heads integrally formed on the cylindrical pins of locking parts 1-7, 1-8, 1-9, 1-10 and 1-11 respectively abut against the inner sidewalls of sleeves 1-1, 1-2, 1-3, 1-4 and 1-5.

[0039] After the satellite enters its space orbit, the gas source device 5 inflates the airbags 1-12. The airbags 1-12 expand, which in turn drives the cylinder 1-6 to move upward. The telescopic rod extends and, through the tensioning disc 2-4, drives the antenna cone 3 to unfold upward until the telescopic rod is fully unfolded and locked. Each cylindrical pin on locking component 1-7, locking component 2-8, locking component 3-9, locking component 4-10, and locking component 5-1-11 is embedded in a cylindrical hole at the upper end of sleeve 1-1, sleeve 2-2, sleeve 3-3, sleeve 4-4, and sleeve 5-5, respectively. The antenna cone 3 is fully unfolded and in a tensioned state.

[0040] Before satellite launch, the antenna cone 3 is first adjusted to its tension state after deployment by the tensioning mechanism 2, and then compressed to its initial state to ensure that the antenna cone 3 is neither too loose nor too tight after entering space orbit and deploying. The specific process is as follows:

[0041] Manually remove the positioning pin 2-5 and rotate the adjusting bolt 2-3 clockwise. The tensioning disc 2-4 moves downward to the lowest position. Then, the air source device 5 inflates the airbag 1-12. The airbag 1-12 expands, which in turn drives the column 1-6 to move upward. The telescopic rod extends and drives the antenna cone 3 to unfold upward through the tensioning disc 2-4 until the telescopic rod is fully unfolded and locked. At this time, the antenna cone 3 is not fully unfolded. Then, rotate the adjusting bolt 2-3 counterclockwise. The tensioning disc 2-4 drives the antenna cone 3 to continue to unfold upward until the antenna cone 3 is in a tensioned state. Insert the positioning pin 2-5 into the waist-shaped groove and a set of holes opposite the waist-shaped groove. Finally, turn off the air source device 5 and compress the telescopic rod to the initial state.

Claims

1. A pneumatically extendable spaceborne single-cone deployable antenna, comprising a telescopic mechanism, an antenna cone, and a fixed base, characterized in that: It also includes a tensioning mechanism and an air source device; the telescopic mechanism includes sleeve one, sleeve two, sleeve three, sleeve four, sleeve five, a column, an air bladder, and an end cap; the diameters of sleeve one, sleeve two, sleeve three, sleeve four, sleeve five, and the column decrease sequentially, and sleeve one, sleeve two, sleeve three, sleeve four, sleeve five, and the column are nested sequentially to form a telescopic rod; the upper end of the inner wall of sleeve one, the lower end of the inner wall of the column, and both ends of the inner walls of sleeve two, sleeve three, sleeve four, and sleeve five are each provided with n column holes arranged equidistantly along the circumference, n≥2; locking element one, locking element two, locking element three, and locking element four are respectively fixed at the position of the lower column hole inside sleeve two, sleeve three, sleeve four, sleeve five, and the column. Locking components one, two, three, four, and five are all elastic annular pieces, and each annular piece has n integrally formed cylindrical pins arranged equidistantly along its outer edge. Each cylindrical pin on locking component one, two, three, four, and five is embedded in a cylindrical hole at the lower end of sleeve two, sleeve three, sleeve four, sleeve five, and cylindrical tube, forming a sliding pair with the corresponding cylindrical hole. The outer end of each cylindrical pin has an integrally formed ball head. The end cap is fixed to the lower end of sleeve one. The airbag is placed in the inner cavity of the telescopic rod, and the upper end of the airbag is fixed to the lower end of the cylindrical tube. The inflation tube at the lower end of the airbag passes through the circular hole on the end cap and is connected to the air source device. The tensioning mechanism includes a limiting block, an adjusting bolt, a tensioning disc, and a positioning pin. The adjusting bolt is located inside the column, and its bottom end forms a rotating pair with the limiting block. The tensioning disc is connected to the adjusting bolt through a threaded hole. The integrally formed column at the bottom of the tensioning disc is embedded in the inner cavity of the column, forming a sliding pair with the column. The integrally formed ring at the top of the tensioning disc has multiple sets of holes arranged equidistantly along the circumference. Each set of holes consists of two opposing holes. The adjusting bolt has a waist-shaped groove, and the positioning pin passes through the waist-shaped groove and one of the sets of holes. The antenna cone is funnel-shaped, with its upper end fixed to the tensioning disc and its lower end fixed to the upper end of a cylindrical frustum integrally formed on the sleeve; the fixed base is fixed to the lower end of the cylindrical frustum integrally formed on the sleeve. Among them, the integrally formed column of sleeve 2, sleeve 3, sleeve 4, sleeve 5, column and tensioning plate are all prisms, the inner cavity of sleeve 1, sleeve 2, sleeve 3, sleeve 4, sleeve 5 and column are all prisms, and the antenna cone is formed by woven metal wire.

2. The aerodynamically extendable spaceborne monocone deployable antenna according to claim 1, characterized in that: The gas source device includes a compressed gas cylinder, a pressure reducing valve, a solenoid valve, and a gas delivery pipe. The outlet of the compressed gas cylinder is connected to the inlet of the pressure reducing valve, the outlet of the pressure reducing valve is connected to the inlet of the solenoid valve, the outlet of the solenoid valve is connected to the inlet of the gas delivery pipe, and the outlet of the gas delivery pipe is connected to the inflation pipe of the air bag. The compressed gas cylinder is filled with inert gas.

3. The aerodynamically extendable spaceborne monocone deployable antenna according to claim 1, characterized in that: The limiting block includes limiting body one and limiting body two, which are fixed inside the column. The grooves on limiting body one and limiting body two are combined to form a stepped hole, and the bolt head of the adjusting bolt is placed in the stepped hole.

4. A method for deploying a pneumatically extendable spaceborne monocone antenna according to any one of claims 1 to 3, characterized in that: Specifically as follows: In the initial state, the airbag, telescopic rod and antenna cone are all in a folded state, and locking parts one, two, three, four and five are all in a compressed state. The ball head integrally formed on each cylindrical pin of locking parts one, two, three, four and five respectively abuts against the inner sidewall of sleeve one, sleeve two, sleeve three, sleeve four and sleeve five. After the satellite enters its space orbit, the gas supply device inflates the airbag. The airbag expands, which in turn moves the cylindrical tube upward, extending the telescopic rod. This extension, along with the tensioning disc, causes the antenna cone to unfold upward until the telescopic rod is fully extended and locked. Each cylindrical pin on locking component one, two, three, four, and five is embedded in a cylindrical hole at the upper end of sleeve one, two, three, four, and five, respectively. The antenna cone is fully extended and in a tensioned state.

5. The deployment method of a pneumatically extendable spaceborne monocone antenna according to claim 4, characterized in that: Before satellite launch, the antenna cone is first adjusted to its tensioned state after deployment via a tensioning mechanism, and then compressed back to its initial state. The specific process is as follows: Manually remove the positioning pin and turn the adjusting bolt clockwise. The tensioning disc moves downward to the lowest position. Then, the air source device inflates the airbag. The airbag expands, which in turn drives the column to move upward. The telescopic rod extends and drives the antenna cone upward through the tensioning disc until the telescopic rod is fully extended and locked. At this time, the antenna cone is not fully extended. Then, turn the adjusting bolt counterclockwise. The tensioning disc drives the antenna cone to continue to extend upward until the antenna cone is in a tensioned state. Insert the positioning pin into the waist-shaped groove and the set of holes opposite the waist-shaped groove. Finally, turn off the air source device and compress the telescopic rod to the initial state.

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