A new satellite inertia characteristic test platform

Abstract

The utility model relates to a novel satellite inertia characteristic test platform, it includes: base, fixed mounting on the upper surface of base air float base, float setting air float rotor above air float base, fixed mounting above air float rotor adapter flange, the torsion bar of connecting air float rotor and base, fixed in air float base side surface photoelectric sensor and install in air float rotor side surface with photoelectric sensor corresponding trigger, air float base is equipped with the conical air float surface and the ring air float surface of intercommunication, and air float rotor is correspondingly equipped with matched rotor conical surface and rotor ring surface, the utility model discloses scientific and reasonable structure design has solved the problem of traditional torsional pendulum type test equipment manufacturing cost, interference torque is big, test efficiency is low, torsional pendulum system is complex, and the maintenance is inconvenient, and the deficiency of processing efficiency is solved, realizes effectively reducing interference torque, has the advantages that the sensitivity is high, stability is good, reduces the processing and application cost.

Description

Technical Field

[0001] This utility model relates to a testing platform, specifically a novel satellite inertia characteristic testing platform. Background Technology

[0002] The satellite inertia characteristic test platform is a high-precision test device specifically designed to measure the rotational inertia of a satellite around its axis of rotation.

[0003] With the booming development of the commercial satellite industry and the increasing number of satellites produced, the demand for high-precision, high-efficiency, and low-cost satellite inertia characteristic testing equipment is growing daily. Existing satellite inertia testing equipment mainly relies on I-beam air bearings to release the degree of freedom in the rotational direction. However, existing solutions have the following drawbacks:

[0004] 1. The structure of the I-shaped air bearing is relatively complex, with many assembly relationships, and it has a large interference torque;

[0005] 2. I-beam air bearings have many integral parts, resulting in complex machining and assembly processes and high manufacturing costs in terms of both economy and time. Utility Model Content

[0006] The purpose of this invention is to overcome the problems of high manufacturing cost, large interference torque, low testing efficiency, complex torsion pendulum system, and inconvenient maintenance of traditional torsion pendulum testing equipment, and to provide a new type of satellite inertia characteristic testing platform that effectively reduces interference torque, has high sensitivity, good stability, and reduces processing and application costs.

[0007] The technical problem solved by this utility model is achieved through the following technical solution:

[0008] A novel satellite inertia characteristic testing platform includes: a base, an air-bearing base fixedly installed on the upper surface of the base, an air-bearing rotor floating above the air-bearing base, a transfer flange fixedly installed above the air-bearing rotor, a torsion bar connecting the air-bearing rotor and the base, a photoelectric sensor fixedly installed on the side of the air-bearing base, and a trigger installed on the side of the air-bearing rotor corresponding to the photoelectric sensor.

[0009] The air flotation base has interconnected conical air flotation surfaces and annular air flotation surfaces, and the air flotation rotor has corresponding matching rotor conical surfaces and rotor annular surfaces.

[0010] Furthermore, the air flotation base is equipped with:

[0011] Several sets of air passage systems are evenly distributed around the axis, each set including a side air passage and a main air passage connected to the input air passage;

[0012] The side air passage is perpendicular to the conical air float surface, and the outlet end of the side air passage is provided with a throttling plug perpendicular to the conical air float surface;

[0013] The main air passage is perpendicular to the annular air float surface, and a throttling plug perpendicular to the annular air float surface is provided at the outlet end of the main air passage.

[0014] The throttle plug has a central aperture of 0.08 mm and a 0.5 mm gap between its outer end face and the corresponding air flotation surface.

[0015] Furthermore, the base is provided with:

[0016] Two symmetrically arranged base side windows, with window dimensions not less than 1 / 2 of the torsion bar length;

[0017] The bottom of the inner cavity of the base is provided with a torsion bar mounting and positioning groove, and the bottom of the torsion bar is rotatably locked in the positioning groove, the groove depth being 1 / 3 of the diameter of the torsion bar.

[0018] Furthermore, the axial distance between the photoelectric sensor and the trigger is 1mm-1.5mm, and the trigger is a metal foil with a reflectivity >85%.

[0019] Furthermore, the adapter flange is provided with:

[0020] A standardized interface for connection between the lower end and the air-float rotor;

[0021] The upper part is equipped with a satellite adapter quick-change module, which contains an array of connection threaded holes of different specifications.

[0022] Furthermore, the torsion bar is made of beryllium bronze, and its torsional stiffness K=πd 4 G / (32L), where d is the rod diameter, G is the shear modulus, and L is the effective length. The rod diameter tolerance is controlled within ±0.005mm.

[0023] Furthermore, the cone angle of the conical air-float is 45°±5°, and the outer diameter of the annular air-float is 700-800mm.

[0024] The advantages and beneficial effects of this utility model are as follows:

[0025] 1. The novel satellite inertia characteristic testing platform of this utility model innovatively designs an irregular conical air-bearing rotor, which combines a conical surface with a thrust plane. The air-bearing surface of the air-bearing rotor is a combination of a cone and a plane, which can realize single-axis rotation. The air-bearing rotor is a single integral component, avoiding the problems of multiple components and complex processing and assembly processes of traditional I-shaped air-bearing rotors.

[0026] 2. The novel satellite inertia characteristic testing platform of this utility model innovatively designs an air-floating base that cooperates with an irregular conical air-floating rotor. The base adopts an integrated structural design, which can realize the air-floating support combining the conical surface and the plane, which is convenient for processing and assembly, and avoids the fitting error caused by assembly error, thereby reducing the interference torque during the working process of the air-floating base and the air-floating rotor.

[0027] 3. The novel satellite inertia characteristic testing platform of this utility model uses photoelectric sensors to collect the rotor torsional period, which has high sensitivity, good stability, low cost and is easy to maintain.

[0028] 4. The novel satellite inertia characteristic testing platform of this utility model has two windows on both sides of the base, which facilitates the installation and maintenance of the torsion bar and can monitor the working status of the torsion bar.

[0029] 5. The novel satellite inertia characteristic testing platform of this utility model has an adapter flange that facilitates quick connection to different types of satellites, thereby improving testing efficiency.

[0030] 6. The structure of this utility model is scientifically and rationally designed, which solves the problems of high manufacturing cost, large interference torque, low testing efficiency, complex torsion pendulum system and inconvenient maintenance of traditional torsion pendulum testing equipment. It also improves the processing efficiency, effectively reduces interference torque, has high sensitivity and good stability, and reduces processing and application costs. Attached Figure Description

[0031] Figure 1 A schematic diagram of the overall structure of a novel satellite inertia characteristic testing platform provided for an embodiment of this utility model;

[0032] Figure 2 for Figure 1 A sectional view;

[0033] Figure 3 for Figure 2 Enlarged view of section A in the middle;

[0034] Figure 4 This is a schematic diagram of the air-float base structure;

[0035] Figure 5 This is the front view of the air-floating base;

[0036] Figure 6 for Figure 5 Sectional view along axis AA;

[0037] Figure 7 for Figure 6 Enlarged view of section B;

[0038] Figure 8 This is a schematic diagram of the air-float rotor structure;

[0039] Figure 9 This is a schematic diagram of the base structure;

[0040] Figure 10 This is a schematic diagram of a torsion bar.

[0041] Figure 11 This is a schematic diagram of the transition flange.

[0042] Figure 12 This is a schematic diagram of the trigger structure;

[0043] Figure 13 This is a schematic diagram of the data collector.

[0044] Icon labels:

[0045] 10-Base, 11-Base side window, 12-Bottom of inner cavity, 20-Air flotation base, 21-Conical air flotation surface, 22-Annular air flotation surface, 23-Throttle plug, 24-Side air passage, 25-Main air passage, 26-Input air passage, 30-Air flotation rotor, 31-Rotor conical surface, 32-Rotor annular surface, 40-Adapter flange, 50-Torsion bar, 60-Photoelectric sensor, 70-Trigger. Detailed Implementation

[0046] The present invention will be further described in detail below through specific embodiments. The following embodiments are only descriptive and not limiting, and should not be used to limit the protection scope of the present invention.

[0047] A novel satellite inertia characteristic testing platform, such as Figure 1-13 As shown, it includes: a base 10, an air-floating base 20 fixedly installed on the upper surface of the base 10, an air-floating rotor 30 floating above the air-floating base 20, a connecting flange 40 fixedly installed above the air-floating rotor 30, a torsion bar 50 connecting the air-floating rotor 30 and the base 10, a photoelectric sensor 60 fixed on the side of the air-floating base 20, and a trigger 70 installed on the side of the air-floating rotor 30 corresponding to the photoelectric sensor 60.

[0048] The air flotation base 20 has a conical air flotation surface 21 and an annular air flotation surface 22 that are interconnected. The air flotation rotor 30 has a corresponding rotor conical surface 31 and rotor annular surface 32. The air flotation rotor 30 is installed above the air flotation base 20, with the rotor conical surface 31 coinciding with the conical air flotation surface 21 and the rotor annular surface 32 coinciding with the annular air flotation surface 22.

[0049] The air flotation base 20 is provided with a conical air flotation surface 21, an annular air flotation surface 22, a throttle plug 23, a side air passage 24, a main air passage 25, and an input air passage 26.

[0050] The cone angle of the conical air flotation surface 21 is 45°±5°, and the outer diameter of the annular air flotation surface 22 is 700-800mm, which can be set according to actual needs.

[0051] The air flotation base 20 has several sets of air passage systems evenly distributed around its axis. In this embodiment, there are eight sets of air passage systems, and the number of air passage sets can be adjusted according to actual needs. Each set includes a side air passage 24 connected to the input air passage 26 and a main air passage 25. The side air passage 24 is perpendicular to the conical air flotation surface 21, and the outlet end of the side air passage 24 is provided with a throttling plug 23 perpendicular to the conical air flotation surface 21. The main air passage 25 is perpendicular to the annular air flotation surface 22, and the outlet end of the main air passage 25 is provided with a throttling plug 23 perpendicular to the annular air flotation surface 22. The central diameter of the throttling plug 23 is 0.08 mm, and the outer end face maintains a 0.5 mm gap with the corresponding air flotation surface.

[0052] The base 10 is provided with base side windows 11 and inner cavity bottom 12: two base side windows 11 are symmetrically arranged on the side of the base, and the window size is not less than 1 / 2 of the length of the torsion bar 50; the inner cavity bottom 12 of the base is provided with a torsion bar mounting and positioning groove, and the bottom of the torsion bar is rotatably locked in the positioning groove, the groove depth is 1 / 3 of the diameter of the torsion bar.

[0053] The adapter flange 40 is fixedly installed above the air-bearing rotor 30. The adapter flange 40 has a standardized interface at the lower end that connects to the air-bearing rotor 30. The upper end is equipped with a satellite adapter quick-change module, which contains at least three different sizes of connection threaded hole arrays.

[0054] Torsion bar 50 is made of beryllium bronze, and its torsional stiffness is K=πd. 4 G / (32L), where d is the rod diameter, G is the shear modulus, and L is the effective length. The rod diameter tolerance is controlled within ±0.005mm. One end of the torsion bar 50 is fixedly connected to the rotor bottom surface 33 of the air-floating rotor 30, and the other end is rotatably clamped to the positioning groove at the bottom 12 of the base cavity of the base 10.

[0055] The photoelectric sensor 60 is fixedly installed on the side of the air-float base 20. The trigger 70 is fixedly installed on the side of the air-float rotor 30, located above the photoelectric sensor 60, and the distance between the trigger 70 and the photoelectric sensor 60 is controlled within the range of 1mm-1.5mm.

[0056] The axial distance between the photoelectric sensor 60 and the trigger 70 is 1mm-1.5mm, and the trigger 70 is a metal foil with a reflectivity >85%.

[0057] The working process of this novel satellite inertial characteristic testing platform is as follows:

[0058] First, compressed air is introduced into the air flotation base 20. The compressed air enters from the input air passage 26, then flows into the side air passage 24 and the main air passage 25, and is ejected from the throttle plug 23, so that an air film of about 15μm is formed between the air flotation rotor 30 and the air flotation base 20, thereby realizing the single-axis frictionless motion between the air flotation rotor 30 and the air flotation base 20.

[0059] The satellite body 80 to be tested is fixedly mounted above the adapter flange 40. A rotational torque around the vertical axis is artificially applied to the air-bearing rotor 30, causing it to rotate. This causes the trigger 70 and the photoelectric sensor 60 to be just offset, and the torsion bar 50 generates a rotational torque of equal magnitude but opposite direction due to the torsion. At this moment, the artificially applied rotational torque is instantly removed. The satellite body 80, the air-bearing rotor 30, and the adapter flange 40 will repeatedly oscillate, and the photoelectric sensor 60 will be repeatedly triggered. The oscillation period T is measured by the photoelectric sensor 60.

[0060] The overall moment of inertia I can be calculated using the formula.

[0061]

[0062] Where K is the torsional stiffness of the torsion bar.

[0063] Furthermore, the moment of inertia I of the satellite body 80 was calculated. 卫星 =II 附加 .

[0064] Where I 附加 Add inertia to the equipment.

[0065] Although the embodiments and drawings of this utility model have been disclosed for illustrative purposes, those skilled in the art will understand that various substitutions, variations and modifications are possible without departing from the spirit and scope of this utility model and the appended claims. Therefore, the scope of this utility model is not limited to the contents disclosed in the embodiments and drawings.

Claims

1. A novel satellite inertia characteristic testing platform, characterized in that, include: The base (10), the air-floating base (20) fixedly installed on the upper surface of the base (10), the air-floating rotor (30) floating above the air-floating base (20), the adapter flange (40) fixedly installed above the air-floating rotor (30), the torsion bar (50) connecting the air-floating rotor (30) and the base (10), the photoelectric sensor (60) fixed on the side of the air-floating base (20), and the trigger (70) installed on the side of the air-floating rotor (30) corresponding to the photoelectric sensor (60); the air-floating base (20) is provided with a conical air-floating surface (21) and an annular air-floating surface (22) that are interconnected, and the air-floating rotor (30) is provided with a matching rotor conical surface (31) and rotor annular surface (32).

2. The novel satellite inertia characteristic testing platform according to claim 1, characterized in that, The air-floating base (20) is equipped with: Several sets of air passage systems are evenly distributed around the axis, each set including a side air passage (24) and a main air passage (25) connected to the input air passage (26); The side air passage (24) is perpendicular to the conical air float surface (21), and the outlet end of the side air passage (24) is provided with a throttle plug (23) perpendicular to the conical air float surface (21); The main air passage (25) is perpendicular to the annular air float surface (22), and the outlet end of the main air passage (25) is provided with a throttle plug (23) perpendicular to the annular air float surface (22); The throttle plug (23) has a central aperture of 0.08 mm and a 0.5 mm gap between its outer end face and the corresponding air flotation surface.

3. The novel satellite inertia characteristic testing platform according to claim 1, characterized in that, The base (10) is provided with: Two symmetrically arranged base side windows (11) have a window size not less than 1 / 2 of the length of the torsion bar (50); The bottom of the inner cavity of the base (12) is provided with a torsion bar mounting and positioning groove. The bottom of the torsion bar is rotated and locked in the positioning groove, and the groove depth is 1 / 3 of the diameter of the torsion bar.

4. The novel satellite inertia characteristic testing platform according to claim 1, characterized in that, The axial distance between the photoelectric sensor (60) and the trigger (70) is 1mm-1.5mm, and the trigger (70) is a metal foil with a reflectivity of >85%.

5. The novel satellite inertia characteristic testing platform according to claim 1, characterized in that, The transition flange (40) is provided with: A standardized interface for connecting the lower end to the air-float rotor (30); The upper part is equipped with a satellite adapter quick-change module, which contains an array of connection threaded holes of different specifications.

6. The novel satellite inertia characteristic testing platform according to claim 1, characterized in that, The torsion bar (50) is made of beryllium bronze, and its torsional stiffness is K=πd4G / (32L), where d is the bar diameter, G is the shear modulus, L is the effective length, and the bar diameter tolerance is controlled within ±0.005mm.

7. The novel satellite inertia characteristic testing platform according to any one of claims 1-6, characterized in that, The cone angle of the conical air flotation surface (21) is 45°±5°, and the outer diameter of the annular air flotation surface (22) is 700-800mm.

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