A torsional load loading device for spacecraft vibration test

Abstract

A spacecraft vibration test torsional load loading device, the gantry is used as a support; bearing bracket is installed on the gantry, a pair of bearing grooves are arranged on the bearing bracket, and one bearing is installed in each bearing groove; a recess is arranged on the rotating disc, the rotating disc is installed in the middle of the bearing shaft, the two ends of the bearing shaft pass through one bearing respectively; the bearing pin is used for being connected with the tested piece; the pull rope assembly is divided into two sections, the two ends of the first section of the pull rope assembly are connected with the bearing pin and the tension spring respectively, one end of the second section of the pull rope assembly is connected with the tension spring, the other end of the second section of the pull rope assembly is connected with the pull rod tray after winding around the rotating disc, and the counterweight is arranged on the pull rod tray; the recess is arranged on the rotating disc, so that the second section of the pull rope assembly can stably wind around; the height and the position of the gantry are adjusted, so that the upper end recess of the rotating disc, the bearing pin and the mass center of the tested piece are all located on the same horizontal plane, and the bearing pin, the first section of the pull rope assembly, the tension spring, the local of the second section of the pull rope assembly and the upper end recess of the rotating disc are in a straight line state.

Description

Technical Field

[0001] This invention relates to a torsional load loading device for spacecraft vibration testing, used for loading torsional loads under vibration tests on spacecraft such as satellites, modules, and large payloads that are subjected to torsional loads during flight. Background Technology

[0002] Some spacecraft are subjected to continuous torsional loads during launch, and the spacecraft experiences a series of mechanical environmental conditions, including vibration, during launch. It is necessary to apply torsional loads in spacecraft vibration tests to verify the impact of torsional loads on the spacecraft's vibration conditions.

[0003] Currently, torsional loads are applied during spacecraft vibration testing primarily by adding counterweights to the spacecraft, causing its center of mass to deviate from its geometric center. During vibration, the torsional load is generated by the inertial force of this center-of-mass shift. However, with this method, the magnitude of the torsional load varies with the vibration magnitude, making it uncontrollable and inconsistent. Some spacecraft experience continuous and stable torsional loads during launch, and existing methods cannot provide such continuous and stable torsional loads for vibration testing. Summary of the Invention

[0004] The technical problem to be solved by this invention is to overcome the shortcomings of the prior art and meet the loading requirements of torsional load in spacecraft vibration tests, with the torsional load being adjustable, sustainable, stable and feasible.

[0005] The objective of this invention is achieved through the following technical solutions:

[0006] A torsional load loading device for spacecraft vibration testing includes a load-bearing pin, a rope assembly, a tension spring, a turntable, a load-bearing shaft, a bearing bracket, a bearing, a tie rod tray, a counterweight, and a gantry frame.

[0007] The gantry serves as a support component; the bearing bracket is installed on the gantry, and the bearing bracket has a pair of bearing slots, with one bearing installed in each bearing slot; the turntable has a groove, and the turntable is installed in the middle of the load-bearing shaft, with a bearing passing through each end of the load-bearing shaft;

[0008] The load-bearing pin is used to connect with the test piece; the pull rope assembly is divided into two sections. The two ends of the first pull rope assembly are connected to the load-bearing pin and the tension spring, respectively. One end of the second pull rope assembly is connected to the tension spring, and the other end is connected to the pull rod tray after passing around the turntable. The counterweight is placed on the pull rod tray.

[0009] The groove on the turntable facilitates the stable passage of the second section of the pull rope assembly. By adjusting the height and orientation of the gantry, the groove at the top of the turntable, the load-bearing pin, and the center of gravity of the test piece are all on the same horizontal plane, and the load-bearing pin, the first section of the pull rope assembly, the tension spring, parts of the second section of the pull rope assembly, and the groove at the top of the turntable are in a straight line.

[0010] In one embodiment of the present invention, the lower end of the load-bearing pin has a square flange that connects to the test piece, and the upper end is provided with a groove for connecting the rope sleeve of the pull rope assembly and an anti-slip cap for the rope sleeve to prevent slippage.

[0011] In one embodiment of the present invention, the rope assembly includes a steel wire rope and anti-loosening rings; the steel wire rope has annular loops at both ends, and the anti-loosening rings are used to crimp the annular loops.

[0012] In one embodiment of the present invention, the turntable has a circular opening in the middle and a circular groove structure on the outer circle, and the inner and outer sides are connected by six evenly distributed spokes.

[0013] In one embodiment of the present invention, during the low-frequency phase of the vibration test, the loading device provides a continuous and stable tension through a counterweight, and during the high-frequency phase, the loading device provides a continuous and stable tension through a tension spring.

[0014] In one embodiment of the present invention, different torsional loads are achieved by loading the test specimen in different directions.

[0015] In one embodiment of the present invention, the bearing bracket is provided with a flange for installation with the gantry frame, and is structurally reinforced by a web and reinforcing ribs.

[0016] In one embodiment of the present invention, the loading device connects the tension spring and the counterweight together in series via a pull rope assembly, and the tension value is adjusted by the counterweight block.

[0017] A torsional load loading system for spacecraft vibration testing employing an upper loading device, wherein there are two sets of loading devices, which are symmetrically distributed with respect to the test specimen and are used together to apply torsional loads to the test specimen.

[0018] In one embodiment of the present invention, the torsional load applied to the test specimen is changed by adjusting the counterweight.

[0019] Compared with the prior art, the present invention has the following advantages:

[0020] (1) Adjustable torsional load: The torsional load loading device for spacecraft vibration test connects the tension spring and the counterweight in series through the rope assembly, and the tension value can be adjusted by the counterweight.

[0021] (2) Wide range of applications: It can adapt to both low-frequency and high-frequency vibration tests. During the low-frequency stage of spacecraft vibration tests, the frequency is small and the amplitude is large. The continuous and stable tension is mainly achieved by the lifting and lowering of the counterweight. During the high-frequency stage, the frequency is large and the amplitude is small. The continuous and stable tension is mainly provided by the tension spring.

[0022] (3) Simultaneous loading in multiple directions: During vibration, loading can be performed simultaneously in different directions.

[0023] (4) Simple operation: The torsional load loading device has a simple structure, is easy to install and operate, and can be used in multiple scenarios. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the two sets of spacecraft vibration test torsional load loading devices of the present invention, symmetrically distributed in operation;

[0025] Figure 2 This is a schematic diagram of a spacecraft vibration test torsional load loading device according to the present invention;

[0026] Figure 3 This is a schematic diagram of a load-bearing pin structure;

[0027] Figure 4 This is a schematic diagram of the pull rope assembly structure;

[0028] Figure 5 This is a schematic diagram of the turntable structure;

[0029] Figure 6 This is a schematic diagram of the bearing support structure;

[0030] Figure 7 This is a schematic diagram of a pallet with a handle. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0032] A torsional load loading device for spacecraft vibration testing, the device comprising a load-bearing pin 1, a rope assembly 2, a tension spring 3, a turntable 4, a load-bearing shaft 5, a bearing bracket 6, a bearing 7, a tie rod tray 8, a counterweight 9, and a gantry frame 10.

[0033] Two sets of spacecraft vibration test torsional load loading devices are centrally symmetrically distributed to form a loading system.

[0034] For a spacecraft vibration test torsional load loading device, the load-bearing pin is installed on the outside of the spacecraft, at the same level as the spacecraft's center of mass. One end of a pull rope assembly is fitted into the groove of the load-bearing pin, and the other end is fitted onto the hook of the tension spring. Another pull rope assembly has one end fitted onto the hook at the other end of the tension spring. The pull rope assembly passes through the turntable, and after turning, the other end is fitted onto the drag bar of the rod tray. An appropriate amount of counterweight is placed on the tray. The upper load-bearing pin, pull rope assembly, tension spring, and upper groove of the turntable are in a straight line. The turntable is fixed in the middle of the load-bearing shaft. A set of bearing brackets and bearing assemblies are arranged on each side of the load-bearing shaft, and the bearings are embedded in the bearing grooves of the bearing brackets. The two sets of bearing brackets and bearing assemblies are symmetrically installed on the gantry.

[0035] Furthermore, the lower end of the load-bearing pin has a square flap that connects to the spacecraft, and the upper end has a groove for placing the rope sleeve of the pull rope assembly and an anti-slip cap to prevent the rope sleeve from slipping off.

[0036] Furthermore, the pull rope assembly consists of a steel wire rope and anti-loosening rings; there are circular rope loops at both ends of the pull rope, and the ends of the rope loops are fixed by bending the rope head three times and crimping the anti-loosening rings.

[0037] Furthermore, the turntable has a circular opening in the center and a circular groove structure on the outer circumference, with the inner and outer sides connected by six evenly distributed spokes.

[0038] Furthermore, the upper end of the bearing bracket is provided with a bearing groove, and the lower end is a flange for installation with the gantry frame. The upper and lower ends are connected by a web and reinforcing ribs.

[0039] Furthermore, the pallet with a handle consists of a handle and a pallet, with a notched circular connecting ring at the upper end of the handle.

[0040] An assembly and testing method for a spacecraft vibration testing torsional load loading system includes:

[0041] Assemble a gantry crane. Install a bearing bracket on the gantry crane, and install a bearing in the bearing groove of the bearing bracket. Install another bearing in the bearing groove of another bearing bracket. Install and fix the turntable in the middle of the load-bearing shaft. One end of the turntable and load-bearing shaft assembly passes through the bearing bracket and bearing assembly not yet installed on the gantry crane. After assembly, install the assembly on the other side of the gantry crane. The other end of the load-bearing shaft passes through the middle hole of the bearing bracket and bearing assembly already installed on the gantry crane. Adjust the assembly and fix it on the gantry crane. Adjust the height and orientation of the gantry crane so that the groove at the top of the turntable is at the same level as the spacecraft's center of mass.

[0042] The load-bearing pin is installed on the outside of the spacecraft, at the same level as the spacecraft's center of mass. One end of a pull rope assembly is fitted into the groove of the load-bearing pin, and the other end is fitted onto the hook of the tension spring. Another pull rope assembly has one end fitted onto the hook at the other end of the tension spring. The pull rope assemblies pass through the turntable, and the load-bearing pin, pull rope assemblies, tension spring, and the groove at the upper end of the turntable are in a straight line. After turning, the other end is fitted onto the trailing rod of the pallet with a rod, and an appropriate amount of counterweight is placed on the pallet.

[0043] Two symmetrical spacecraft vibration test torsional load loading devices continuously provide symmetrical tensile force to apply torsional load. The magnitude of the torsional load can be adjusted by adjusting the weight of the counterweight. It has the advantages of adjustable torsional load, sustainability, stability and strong feasibility.

[0044] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0045] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A torsional load loading device for spacecraft vibration testing, characterized in that, Includes load-bearing pins, rope assemblies, tension springs, turntables, load-bearing shafts, bearing brackets, bearings, tie rod trays, counterweights, and gantry frames; The gantry serves as a support component; the bearing bracket is installed on the gantry, and the bearing bracket has a pair of bearing slots, with one bearing installed in each bearing slot; the turntable has a groove, and the turntable is installed in the middle of the load-bearing shaft, with a bearing passing through each end of the load-bearing shaft; The load-bearing pin is used to connect to the test piece; the pull rope assembly is divided into two sections. The two ends of the first section are connected to the load-bearing pin and the tension spring, respectively. One end of the second section is connected to the tension spring, and the other end is connected to the pull rod tray after passing around the turntable. The counterweight is placed on the pull rod tray. This loading device connects the tension spring and the counterweight together in series through the pull rope assembly, and the tension value is adjusted by the counterweight. The groove on the turntable facilitates the stable passage of the second section of the pull rope assembly. By adjusting the height and orientation of the gantry, the groove at the top of the turntable, the load-bearing pin, and the center of gravity of the test piece are all on the same horizontal plane, and the load-bearing pin, the first section of the pull rope assembly, the tension spring, parts of the second section of the pull rope assembly, and the groove at the top of the turntable are in a straight line. During the low-frequency phase of the vibration test, the loading device provides a continuous and stable tension through a counterweight. During the high-frequency phase, the loading device provides a continuous and stable tension through a tension spring.

2. The loading device according to claim 1, characterized in that, The lower end of the load-bearing pin has a square flange that connects to the test piece, and the upper end has a groove for connecting the rope sleeve of the pull rope assembly and an anti-slip cap to prevent the rope sleeve from slipping off.

3. The loading device according to claim 1, characterized in that, The rope assembly includes a steel wire rope and anti-loosening rings; the steel wire rope has loops at both ends, and the loops are crimped together using anti-loosening rings.

4. The loading device according to claim 1, characterized in that, The turntable has a circular opening in the middle and a circular groove on the outer circumference. The inner and outer sides are connected by six evenly distributed spokes.

5. The loading device according to claim 1, characterized in that, Different torsional loads are achieved by loading the test specimen in different directions.

6. The loading device according to claim 1, characterized in that, The bearing bracket is equipped with flanges for installation on the gantry frame and is structurally reinforced by web plates and reinforcing ribs.

7. A spacecraft vibration test torsional load loading system employing the loading device according to any one of claims 1 to 6, characterized in that, There are two sets of loading devices, which are symmetrically distributed with respect to the center of the test specimen and are used together to apply torsional loads to the test specimen.

8. The loading system according to claim 7, characterized in that, The torsional load applied to the test specimen is changed by adjusting the counterweight.

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