Pressing and stabilizing device for lifting structure of solar wing unfolding frame

Abstract

The utility model relates to the technical field of spacecrafts, in particular to a solar wing unfolding frame lifting structure pressing and stabilizing device which comprises a first section rod, a second section rod and a pressure adjusting device. The pressure adjusting device comprises a lifting table, a telescopic rod, a metal block, a spring, an electromagnet, a tensioning wall, a relay block and a triangular pull rod, the lifting table is fixedly arranged at the bottom of an inner cavity of the first section rod, the telescopic rod is fixedly arranged at the front end of the lifting table, the metal block is fixedly arranged at the front end of the telescopic rod, and one end of the spring is connected with the lifting table; according to the tensioning device for the solar wing unfolding frame, the first section rod, the second section rod, the third section rod, the pressure adjusting device and other structures work in a matched mode, the adjusted solar wing unfolding frame can be tensioned, and it can be guaranteed that the structures move relatively, and meanwhile enough repeated positioning accuracy is achieved.

Description

TECHNICAL FIELD

[0001] The utility model belongs to spacecraft technical field especially, it is especially concrete to be related to a solar wing unfolding frame lifting structure compression stabilizing device. BACKGROUND

[0002] In order to verify the performance index of solar wing, need to carry out solar wing ground deployment test for many times in the process of spacecraft development, since solar wing is in zero gravity state in orbit deployment, therefore solar wing deployment frame needs to unload the gravity of solar wing in the test process, with the improvement of spacecraft assembly accuracy, the precision of ground assembly and test process equipment is required higher and higher, the existing solar wing deployment frame has the following problems:

[0003] 1, the solar wing deployment frame currently used, after telescopic adjustment, there is a gap between structures, and the precision of repeated positioning is poor.

[0004] 2, the solar wing deployment frame currently used, after telescopic adjustment and ground test, there is a problem of solar wing deployment frame shaking. SUMMARY

[0005] Therefore, the utility model is made in view of the above problems, and the above purposes are realized through the following technical solutions:

[0006] A solar wing deployment frame lifting structure compression stabilizing device, comprising: first section rod, second section rod, pressure adjusting device, first section rod is connected with second section rod vertically, pressure adjusting device comprises: lifting platform, telescopic rod, metal block, spring, electromagnet, tension wall, relay block, triangular pull rod, the lifting platform is fixedly arranged in the bottom of the first section rod internal cavity, the telescopic rod is fixedly arranged at the front end of lifting platform, the metal block is fixedly arranged at the front end of telescopic rod, one end of spring is connected with lifting platform, the other end is connected with the rear end of tension wall, sensor is arranged at spring, tension wall is fixedly arranged at the opening end of second section rod, electromagnet is fixedly arranged at the bottom of second section rod internal cavity.

[0007] Preferably, the diameter of the metal block is greater than the diameter of the central gap of the tension wall.

[0008] Preferably, the compression stabilizing device further comprises a third section rod, a pressure adjusting device, and a relay block, the first section rod, the second section rod, and the third section rod are connected vertically, and the first section rod, the second section rod, and the third section rod are connected through the relay block.

[0009] Preferably, the pressure adjusting device further comprises a triangular pull rod, and the electromagnet, the tension wall, the metal block, and the spring each have three, and the electromagnet is fixedly arranged at an angle of the relay block and is arranged opposite to the triangular pull rod.

[0010] The preferred triangular pull rod comprises: a telescopic part, a connecting rod, and a tension rod, the telescopic part is a telescopic sleeve structure and is fixedly arranged at one corner of the relay block, the bottom of the telescopic part is made of magnetic material, the connecting rod is three in number, the upper end of the connecting rod is hingedly arranged below the telescopic part at equal intervals, the lower end of the connecting rod is hingedly connected with one end of the tension rod, and the other end of the tension rod is connected with the metal block.

[0011] The beneficial effects of the utility model are as follows:

[0012] 1. The first section rod, the second section rod, the third section rod, the pressure adjusting device and other structures cooperate to pull the solar wing unfolding frame after adjustment, and the relative movement between structures can ensure sufficient repeated positioning accuracy.

[0013] 2. When the solar wing unfolding frame works, the solar wing unfolding frame is prone to stress deformation under the influence of the gravity of the supported satellite and external force in the ground experiment, at this time, the pressure adjusting device in the device is stressed, and after feedback through the sensor, the magnetic force of the electromagnet can be increased to feed back the increased stress in advance, thereby improving the compacting stability. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is a whole schematic view of the utility model embodiment one.

[0015] Figure 2 It is an internal schematic view of the utility model embodiment one.

[0016] Figure 3 It is a whole schematic view of the utility model embodiment two.

[0017] Figure 4 It is an internal schematic view of the utility model embodiment two.

[0018] Figure 5 It is a schematic view of the triangular pull rod of the utility model embodiment two.

[0019] 1. The first section rod; 2. The second section rod; 3. The third section rod; 4. The pressure adjusting device; 41. The lifting platform; 42. The telescopic rod; 43. The metal block; 44. The spring; 45. The tension wall; 46. The electromagnet; 47. The triangular pull rod; 471. The telescopic part; 472. The connecting rod; 473. The tension rod; 5. The relay block. DETAILED DESCRIPTION

[0020] The preferred embodiments of the application will be described in detail with reference to the accompanying drawings, which are easy to realize for those skilled in the art. However, the application can be realized in various forms, and therefore the application is not limited to the embodiments described below.

[0021] Embodiment One

[0022] A solar wing unfolding frame lifting structure compression stabilizing device, two sections of rods are vertically connected, comprising: a first section of rod 1, a second section of rod 2, a pressure adjusting device 4;

[0023] The first section of rod 1 is a section of the solar wing unfolding frame and is connected to the second section of rod 2 straightly;

[0024] The second section of rod 2 is a section of the solar wing unfolding frame and is connected to the first section of rod 1 straightly;

[0025] The first section of rod 1 and the second section of rod 2 are hollow inside, and the first section of rod 1 can be inserted into the second section of rod 2;

[0026] The pressure adjusting device 4 comprises: a lifting platform 41, an extension rod 42, a metal block 43, a spring 44, an electromagnet 46, a tension wall 45, a relay block 5, and a triangular tension rod 47, which are arranged in the first section of rod 1 and the second section of rod 2 respectively;

[0027] The lifting platform 41 is fixedly arranged at the bottom of the cavity inside the first section of rod 1 and can be controlled to lift or lower by a screw rod or an electric control system;

[0028] The extension rod 42 is of a telescopic structure, passes through the center gap of the spring 44 and the tension wall 45, and is fixedly arranged at the front end of the lifting platform 41;

[0029] The metal block 43 is a flat cylinder, which is fixedly arranged at the front end of the extension rod 42, and the diameter of the metal block 43 is greater than that of the center gap of the tension wall 45;

[0030] One end of the spring 44 is connected to the lifting platform 41, and the other end is connected to the rear end of the tension wall 45;

[0031] A sensor is arranged at the spring 44 to reflect the force condition of the spring 44;

[0032] The tension wall 45 is a flat quadrangular prism with a circular gap in the center, and is fixedly arranged at the opening end of the second section of rod 2;

[0033] The electromagnet 46 is fixedly arranged at the bottom of the cavity inside the second section of rod 2;

[0034] Embodiment Two

[0035] As shown in Figures 3-5 A solar wing unfolding frame lifting structure compression stabilizing device, three sections of rods are vertically connected, comprising: a first section of rod 1, a second section of rod 2, a third section of rod 3, a pressure adjusting device 4, a relay block 5;

[0036] The first section 1, the second section 2, and the third section 3 are perpendicular to each other and are connected by the following relay block 5.

[0037] The first section 1, the second section 2, and the third section 3 are hollow inside, and the first section 1, the second section 2, and the third section 3 can be inserted into the following relay block 5.

[0038] The relay block 5 is composed of three hollow prisms perpendicular to each other.

[0039] The pressure adjusting device 4 includes a tension wall 45, a metal block 43, a spring 44, a triangular tension rod 47, and an electromagnet 46, which are respectively arranged in the first section 1, the second section 2, the third section 3, and the relay block 5.

[0040] The tension wall 45 is a flat quadrangular prism with a circular notch in the center, and the tension wall 45 is fixedly arranged at the opening end of the first section 1, the second section 2, and the third section 3.

[0041] The spring 44 is three in number and is fixedly arranged at the bottom of the internal cavity of the first section 1, the second section 2, and the third section 3, and the other end of the spring 44 is connected to the following metal block 43.

[0042] A sensor is arranged at the spring 44 to react to the force acting on the spring 44.

[0043] The triangular tension rod 47 includes a telescopic part 471, a connecting rod 472, and a tension rod 473.

[0044] The telescopic part 471 is a telescopic sleeve structure and is fixedly arranged at an angle inside the relay block 5.

[0045] The bottom of the telescopic part 471 is made of magnetic material.

[0046] The connecting rod 472 is three in number, and the upper end of the connecting rod 472 is hingedly arranged below the telescopic part 471 at equal intervals, and the lower end is hingedly connected to the following tension rod 473.

[0047] The tension rod 473 is three in number, and one end of each tension rod 473 is hingedly connected to the connecting rod 472, and the other end is connected to the following metal block 43.

[0048] The metal block 43 is three in number and is fixedly arranged at the end of each tension rod 473.

[0049] The metal block 43 is a flat cylinder with a diameter greater than the diameter of the central notch of the tension wall 45.

[0050] The electromagnet 46 is fixedly arranged at an angle inside the relay block 5 and opposite to the telescopic part 471.

[0051] The working principle of the present application;

[0052] In use of the present application, first, the telescopic distance of the solar wing unfolding frame is adjusted by the lifting platform 41, then the electromagnet 46 is started to attract the metal block 43, the metal block 43 compresses the tension wall 45 and the spring 44, thereby driving the first section rod 1 to approach the second section rod 2, and the solar wing unfolding frame lifting structure is compressed;

[0053] In use of the present application, the electromagnet 46 is started to repel the bottom of the telescopic part 471, the telescopic part 471 is contracted, the included angle between the connecting rod 472 and the telescopic part 471 is reduced, the tension rod 473 pulls the metal block 43, thereby further pulling the first section rod 1, the second section rod 2 and the tension wall 45 and the spring 44 of the third section rod 3, thereby driving the first section rod 1, the second section rod 2 and the third section rod 3 to contract and approach the relay block 5, and the solar wing unfolding frame lifting structure is compressed;

[0054] When the solar wing unfolding frame works, it will be affected by the gravity of the supported satellite and external force in the ground experiment, thereby leading to the solar wing unfolding frame to have a force deformation tendency, at this time, the spring 44 in the present device is stressed, after feedback through the sensor, the magnetic force of the electromagnet 46 can be increased through control, thereby making an early feedback to the increased stress, thereby improving the compression stability effect.

Claims

1. A solar wing deployment rack lifting structure compact stabilizing device, comprising: The utility model provides a kind of pressure adjusting device, including first section rod (1), second section rod (2), pressure adjusting device (4);Its characterized in that: first section rod (1) is connected perpendicularly with second section rod (2), and pressure adjusting device (4) includes: lifting platform (41), telescopic rod (42), metal block (43), spring (44), electromagnet (46), tension wall (45), relay block (5), triangular pull rod (47), the lifting platform (41) is fixedly arranged in the bottom of the internal cavity of first section rod (1), the telescopic rod (42) is fixedly arranged in the front end of lifting platform (41), metal block (43) is fixedly arranged in the front end of telescopic rod (42), one end of spring (44) is connected with lifting platform (41), the other end is connected with the rear end of tension wall (45), sensor is arranged at spring (44), tension wall (45) is fixedly arranged in the open end of second section rod (2), electromagnet (46) is fixedly arranged in the bottom of the internal cavity of second section rod (2).

2. The compact stabilizing device for a solar wing deployment boom lifting structure according to claim 1, characterized in that: The diameter of the metal block (43) is greater than the diameter of the central gap of the tension wall (45).

3. The compact stabilizing device for a solar wing deployment boom lifting structure of claim 1, wherein: Further comprising: Third section rod (3), pressure adjusting device (4), relay block (5), first section rod (1), second section rod (2), third section rod (3) are connected perpendicularly, and the first section rod (1), second section rod (2) and third section rod (3) are connected by the relay block (5).

4. The compact stabilizing device for a solar wing deployment boom lifting structure of claim 3, wherein: The pressure adjusting device (4) further comprises a triangular pull rod (47), and the electromagnet (46), tension wall (45), metal block (43) and spring (44) each have three, and the electromagnet (46) is fixedly arranged in one corner of the relay block (5) and is arranged opposite to the triangular pull rod (47).

5. A compact stabilizing device for a solar wing deployment boom lifting structure according to claim 4, characterized in that: The triangular pull rod (47) comprises a telescopic part (471), a connecting rod (472) and a tension rod (473), the telescopic part (471) is a telescopic sleeve structure and is fixedly arranged in one corner of the relay block (5), the bottom of the telescopic part (471) is made of magnetic material, the connecting rod (472) has three, the upper end of the connecting rod (472) is hingedly connected to the lower side of the telescopic part (471) at equal intervals, the lower end of the connecting rod (472) is hingedly connected to one end of the tension rod (473), and the other end of the tension rod (473) is connected to the metal block (43).

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