Air floating foot for zero-gravity unfolding verification of space antenna

Abstract

The utility model relates to an air floatation unloading structure, in particular to an air floatation foot for space antenna zero-gravity unfolding verification, which solves the problem of how to enable a space antenna to be in a suspension state like an outer space environment in the ground unfolding verification process, and comprises a body, a connecting seat and a butt joint assembly, an air inlet hole is formed in the body and used for being connected with a high-pressure gas pipeline; the connecting seat is arranged in the center of the top of the body, a plurality of throttling holes are formed in the bottom of the body and communicated with the air inlet hole through an air cavity in the body, one end of the butt joint assembly is used for being connected with a space antenna, the other end of the butt joint assembly is connected with the connecting seat, and high-pressure air in the high-pressure air pipeline enters from the air inlet hole and flows out from the throttling holes. The acting force generated by the high-pressure gas enables the space antenna to be in a suspended state.

Description

Technical Field

[0001] The utility model relates to an air floating unloading structure, in particular to an air floating foot used for zero-gravity deployment verification of a space antenna. Background Art

[0002] Space antennas are the main equipment used by in-orbit spacecraft to receive and send signals. In order to facilitate the launch of spacecraft, space antennas are usually designed as folding structures. They are folded and stored inside the spacecraft during launch. When the spacecraft enters the predetermined orbit, they will unfold to facilitate the reception and transmission of signals.

[0003] Since the working environment of the space antenna is outer space, which is in a zero-gravity state, when designing and manufacturing the space antenna, it is necessary to simulate the on-orbit deployment function of the space antenna in a zero-gravity state, and then verify the performance of the space antenna. However, the zero-gravity deployment verification of the space antenna is limited by a series of factors such as cost and technology, so it can only be carried out on the ground. However, when conducting ground verification, the space antenna will be affected by gravity, and the friction caused by gravity will hinder the zero-gravity deployment verification of the space antenna. Therefore, during the verification process, it is necessary to make the space antenna in a suspended state like the outer space environment to ensure that it will not be affected by the friction caused by gravity. Utility Model Content

[0004] The utility model aims to solve the problem of how to make a space antenna in a suspended state like an outer space environment during ground deployment verification, and provides an air floating foot for zero-gravity deployment verification of a space antenna.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] An air floating foot for zero-gravity deployment verification of a space antenna, which is special in that it includes a body, a connection seat and a docking assembly;

[0007] The main body is provided with an air inlet hole for connecting a high-pressure gas pipeline, and the connecting seat is arranged at the top center of the main body;

[0008] A plurality of throttle holes are provided at the bottom of the body, and the throttle holes are connected with the air inlet holes through the air cavity inside the body;

[0009] One end of the docking assembly is used to connect with the space antenna, and the other end is connected with the connecting seat.

[0010] Furthermore, there are two air inlet holes and they are symmetrically arranged on the main body on both sides of the connecting seat. There are eight throttling holes, including four vertex throttling holes and four side throttling holes. The four vertex throttling holes are arranged in a rectangular distribution. The four side throttling holes are respectively located on the center line of two adjacent vertex throttling holes and at the midpoint of the corresponding center line.

[0011] Furthermore, a pressure equalizing groove is provided between adjacent edge throttle holes and vertex throttle holes.

[0012] Furthermore, the docking assembly includes a force sensor, which has an S-shaped structure. A U-shaped groove is respectively opened at the upper and lower parts of the force sensor, and the openings of the two U-shaped grooves are facing opposite directions. A threaded hole is opened in the vertical direction on the lower side wall of the lower U-shaped groove, and a support rod is arranged in the threaded hole. One end of the support rod is connected to the force sensor through the threaded hole, and the other end is connected to the connecting seat, and the space antenna is connected to the top of the force sensor.

[0013] Furthermore, the docking assembly also includes an adjustment assembly arranged at the top of the force sensor, the adjustment assembly includes an adapter plate, an adjustment plate, an adjustment screw and an adjustment nut, the adjustment screw is connected to the top surface of the force sensor, two adjustment nuts are provided and are both screwed on the adjustment screw, the adjustment plate is sleeved on the adjustment screw and located between the two adjustment nuts, the adapter plate is located above the top of the adjustment screw, the adapter plate and the adjustment plate are connected by bolts, and the space antenna is connected to the adapter plate.

[0014] Furthermore, a through hole is provided in the center of the connecting seat, and an accommodating cavity is provided at the bottom of the connecting seat corresponding to the position of the through hole, a hemispherical ball joint head is arranged in the accommodating cavity, and a groove matching the shape of the outer wall of the ball joint head is provided on the main body, the ball joint head is located in the groove, and the other end of the support rod is connected to the ball joint head after passing through the through hole.

[0015] Furthermore, an annular groove is provided at the top of the accommodating cavity, an anti-rotation rubber ring is arranged in the annular groove, the outer wall of the anti-rotation rubber ring abuts against the inner wall of the annular groove, and the inner wall abuts against the outer wall of the support rod.

[0016] Furthermore, the body is an aluminum alloy body, and the connecting seat is an aluminum alloy connecting seat.

[0017] Compared with the prior art, the beneficial effects of the utility model are:

[0018] (1) The utility model provides an air floating foot for zero-gravity deployment verification of a space antenna. An air inlet is provided on the main body, and the air inlet is connected to a high-pressure gas pipeline. A plurality of throttle holes are opened at the bottom of the main body. The throttle holes and the air inlet are connected through an air cavity inside the main body. In this way, after the high-pressure gas enters from the air inlet, it will flow out from the throttle holes. The force generated by the high-pressure gas puts the entire air floating foot in a suspended state. One end of the docking assembly is connected to the space antenna, and the other end is connected to the connecting seat. In this way, the space antenna will also be in a suspended state like the outer space environment. The overall structure is simple.

[0019] (2) The utility model provides an air flotation foot for zero-gravity deployment verification of a space antenna, wherein a pressure equalizing groove is provided between adjacent edge throttle holes and vertex throttle holes, so that the high-pressure area of ​​the air flotation foot is distributed on the periphery, and the air pressure distribution inside is uniform, thereby having good load-bearing capacity and air film stiffness.

[0020] (3) The utility model provides an air-floating foot for zero-gravity deployment verification of a space antenna, wherein the support rod and the ball joint head form a ball joint connection, which can be used to adapt to platforms with different inclination angles and will not generate additional torque on the space antenna, thereby ensuring the verification effect.

[0021] (4) The utility model provides an air-floating foot for zero-gravity deployment verification of a space antenna, which prevents the body from rotating around a support rod by means of an anti-rotation rubber ring, and has a simple structure and low processing cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the connection structure between the main body and the connection seat of the air-floating foot used for zero-gravity deployment verification of a space antenna in the utility model;

[0023] Figure 2 This is a schematic diagram of the structure of the bottom of the body in the embodiment of the utility model;

[0024] Figure 3 This is a schematic diagram of the connection between the main body, the connecting seat and the docking assembly in the embodiment of the utility model;

[0025] Figure 4 It is a schematic diagram of the connection between the support rod and the ball joint head in the embodiment of the utility model.

[0026] The following are the descriptions of the reference numerals:

[0027] 1-main body, 101-apex throttle hole, 102-edge throttle hole, 103-pressure equalizing groove, 104-air inlet; 2-connecting seat, 3-force sensor, 31-U-shaped groove; 4-support rod, 5-adapter plate, 6-adjusting plate, 7-adjusting screw, 8-adjusting nut, 9-ball joint, 10-anti-rotation rubber ring. DETAILED DESCRIPTION

[0028] The utility model is further described below in conjunction with the accompanying drawings and specific embodiments.

[0029] Reference Figure 1-Figure 4 The utility model is a kind of air floating foot for zero gravity deployment verification of space antenna, which includes a body 1, a connecting seat 2 and a docking assembly. The structure of the body 1 is as follows: Figure 1 As shown, it is a rectangular structure. In order to reduce its own weight and improve its strength, the entire body 1 is made of aluminum alloy. Arc chamfers are also provided around the body 1 to prevent the edges from hurting the operator or other facilities. A connecting seat 2 is connected to the top center of the body 1 by bolts. It is also a rectangular structure. The connecting seat 2 is also made of aluminum alloy to reduce its own weight and improve its strength. The connecting seat 2 is connected to the body 1 by bolts. In this way, if one part is damaged, it does not need to be discarded as a whole. The corresponding part can be replaced, which saves the cost of use.

[0030] In order to make the air-floating foot suspended, an air inlet hole 104 is provided. There are two air inlet holes 104 and they are symmetrically arranged on the main body 1 on both sides of the connecting seat 2. Eight throttling holes are provided at the bottom of the main body 1. The eight throttling holes are connected to the air inlet hole 104 through the air cavity inside the main body 1. The throttling holes include four vertex throttling holes 101 and four sideline throttling holes 102. The four vertex throttling holes 101 are arranged in a rectangular distribution. The four sideline throttling holes 102 are respectively located on the center line connecting two adjacent vertex throttling holes 101 and are located at the midpoint position of the corresponding center line. In this way, when the eight throttling holes spray high-pressure gas outward, the entire air-floating foot is evenly stressed and is not easy to tilt. And a pressure equalizing groove 103 is provided between the adjacent sideline throttling holes 102 and the vertex throttling holes 101. The air-floating foot of this structure belongs to a rectangular air-floating foot with a peripheral one-shaped pressure equalizing groove. The high-pressure area of ​​the air-floating foot is distributed on the periphery, and the air pressure inside is evenly distributed, which has good bearing capacity and air film stiffness.

[0031] In order to better connect with the space antenna, a docking assembly is also provided, which includes a force sensor 3 and an adjustment assembly connected to the force sensor 3. The force sensor 3 can detect the bearing capacity of the air floating foot, and the adjustment assembly is used to adapt to space antennas of different heights. The adjustment assembly includes an adapter plate 5, an adjustment plate 6, an adjustment screw 7 and an adjustment nut 8. The adjustment screw 7 is connected to the top surface of the force sensor 3. Two adjustment nuts 8 are provided and are both screwed on the adjustment screw 7. The adjustment plate 6 is sleeved on the adjustment screw 7 and located between the two adjustment nuts 8. The adapter plate 5 is located above the top of the adjustment screw 7. Four threaded holes are arranged on the adapter plate 5 in a rectangular distribution. The space antenna is connected to the adapter plate 5 through the four threaded holes. The adapter plate 5 is connected to the adjustment plate 6 through two bolts. When adjusting the height of the adapter plate 5, the height is adjusted through the adjustment nut 8 below the adjustment plate 6, and the adjustment nut 8 above is used for locking, thereby avoiding the influence of the thread return error on the height adjustment.

[0032] The force sensor 3 is an S-shaped structure, with a U-shaped groove 31 provided at the upper and lower parts respectively. The openings of the two U-shaped grooves 31 face opposite directions. A threaded hole is provided on the lower side wall of the lower U-shaped groove 31 in the vertical direction. A support rod 4 is screwed into the threaded hole. One end of the support rod 4 is connected to the force sensor 3 through the threaded hole, and the other end is connected to the connecting seat 2.

[0033] Because the air-floating foot is generally used on a platform, but the surface of the platform is generally not horizontal due to processing and long-term deformation, but has a certain inclination angle. If the support rod 4 is rigidly connected to the connecting seat 2, the air-floating foot will be affected by these inclination angles when moving on the platform, which will generate additional torque on the space antenna and affect the verification effect. Therefore, in this embodiment, the force sensor 3 and the connecting seat 2 are connected by a ball joint. Specifically, a through hole is opened in the center of the connecting seat 2, and a receiving cavity is opened at the bottom of the connecting seat 2 corresponding to the position of the through hole. A hemispherical ball joint head 9 is arranged in the receiving cavity, and a groove matching the shape of the outer wall of the ball joint head 9 is opened on the main body 1. The ball joint head 9 is located in the groove, and the other end of the support rod 4 is connected to the ball joint head 9 after passing through the through hole. Because a ball joint connection is adopted, the main body 1 may rotate around the support rod 4. Therefore, an annular groove is opened at the top of the accommodating cavity, and an anti-rotation rubber ring 10 is arranged in the annular groove. The outer wall of the anti-rotation rubber ring 10 abuts against the inner wall of the annular groove, and the inner wall abuts against the outer wall of the support rod 4. The friction between the anti-rotation rubber ring 10 and the inner wall of the annular groove will limit the rotation of the main body 1.

[0034] When in use, first adjust the adjustment nut 8 to make the adapter plate 5 and the space antenna highly adaptable, then connect the adapter plate 5 and the space antenna together through bolts, and then introduce high-pressure gas into the high-pressure gas pipeline. The high-pressure gas enters from the air inlet 104 on the main body 1 and flows out from the throttle hole at the bottom of the main body 1. The force generated by the high-pressure gas makes the entire air-floating foot suspended, and the air-floating foot has no contact with the platform. In theory, there is no friction when the air-floating foot moves on the platform. At this time, the space antenna is in a suspended state, thereby completing the unloading of the gravity load of the space antenna, and the space antenna will not be affected by gravity during the deployment verification.

[0035] The embodiments described above are merely descriptions of the specific implementation methods of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. An air-floating foot for zero-gravity deployment verification of a space antenna, characterized in that: It comprises a main body (1), a connecting seat (2) and a docking assembly; The body (1) is provided with an air inlet hole (104) for connecting a high-pressure gas pipeline, and the connecting seat (2) is arranged at the top center of the body (1); A plurality of throttle holes are provided at the bottom of the body (1), and the throttle holes are connected to the air inlet (104) through an air cavity inside the body (1); One end of the docking assembly is used to connect to the space antenna, and the other end is connected to the connecting seat (2).

2. The air floating foot for zero gravity deployment verification of a space antenna according to claim 1, characterized in that: There are two air inlet holes (104) symmetrically arranged on the body (1) on both sides of the connecting seat (2); there are eight throttle holes, including four vertex throttle holes (101) and four sideline throttle holes (102); the four vertex throttle holes (101) are arranged in a rectangular distribution; the four sideline throttle holes (102) are respectively located on the center line connecting two adjacent vertex throttle holes (101) and at the midpoint position of the corresponding center line.

3. The air floating foot for zero gravity deployment verification of a space antenna according to claim 2, characterized in that: A pressure equalizing groove (103) is provided between adjacent edge throttle holes (102) and vertex throttle holes (101).

4. The air floating foot for zero gravity deployment verification of a space antenna according to claim 3, characterized in that: The docking assembly comprises a force sensor (3), the force sensor (3) is an S-shaped structure, a U-shaped groove (31) is respectively provided at the upper part and the lower part of the force sensor (3), the openings of the two U-shaped grooves (31) are oriented in opposite directions, a threaded hole is provided on the lower side wall of the U-shaped groove (31) at the lower part in the vertical direction, a support rod (4) is provided in the threaded hole, one end of the support rod (4) is connected to the force sensor (3) through the threaded hole, and the other end is connected to the connecting seat (2), and the space antenna is connected to the top end of the force sensor (3).

5. The air-floating foot for zero-gravity deployment verification of a space antenna according to claim 4, characterized in that: The docking assembly also includes an adjustment assembly arranged at the top end of the force sensor (3), the adjustment assembly including an adapter plate (5), an adjustment plate (6), an adjustment screw (7) and an adjustment nut (8), the adjustment screw (7) being connected to the top end surface of the force sensor (3), two adjustment nuts (8) being provided and both being screwed onto the adjustment screw (7), the adjustment plate (6) being sleeved on the adjustment screw (7) and being located between the two adjustment nuts (8), the adapter plate (5) being located above the top end of the adjustment screw (7), the adapter plate (5) being connected to the adjustment plate (6) by bolts, and the space antenna being connected to the adapter plate (5).

6. The air-floating foot for zero-gravity deployment verification of a space antenna according to claim 5, characterized in that: A through hole is provided at the center of the connection seat (2), and a receiving cavity is provided at the bottom of the connection seat (2) corresponding to the position of the through hole. A hemispherical ball joint (9) is provided in the receiving cavity, and a groove matching the shape of the outer wall of the ball joint (9) is provided on the body (1). The ball joint (9) is located in the groove, and the other end of the support rod (4) passes through the through hole and is connected to the ball joint (9).

7. The air floating foot for zero gravity deployment verification of a space antenna according to claim 6, characterized in that: An annular groove is provided at the top of the accommodating cavity, an anti-rotation rubber ring (10) is arranged in the annular groove, the outer wall of the anti-rotation rubber ring (10) abuts against the inner wall of the annular groove, and the inner wall abuts against the outer wall of the support rod (4).

8. The air floating foot for zero gravity deployment verification of a space antenna according to claim 1, characterized in that: The body (1) is an aluminum alloy body, and the connection seat (2) is an aluminum alloy connection seat.

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