CN112032245A - Vibration reduction system for satellite-borne accelerometer combination - Google Patents
Vibration reduction system for satellite-borne accelerometer combination Download PDFInfo
- Publication number
- CN112032245A CN112032245A CN202010952421.XA CN202010952421A CN112032245A CN 112032245 A CN112032245 A CN 112032245A CN 202010952421 A CN202010952421 A CN 202010952421A CN 112032245 A CN112032245 A CN 112032245A
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- Prior art keywords
- accelerometer
- vibration
- mounting bracket
- satellite
- shock absorber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
- G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
Abstract
The invention discloses a vibration reduction system used by an accelerometer combination, which relates to the technical field of satellite attitude control, and can effectively reduce the impact and vibration caused by the separation of a satellite and an arrow, the shutdown of an engine, various actions on the satellite (or an aircraft) and a spacecraft under the normal and emergency landing conditions, and improve the reliability and the service life of the accelerometer combination. The vibration reduction system comprises a plurality of vibration reducers, an accelerometer mounting bracket and an accelerometer combined base, wherein the impact and vibration received by a satellite are transmitted to the accelerometer combined base through a mounting cabin plate and then transmitted to the accelerometer mounting bracket through the plurality of vibration reducers. The shock absorber can dissipate most of the impact and vibration energy, so that electronic components inside the accelerometer mounting bracket are protected. The vibration reduction system also has a heat dissipation function, so that the related electronic components can be ensured to be at a lower working temperature. The materials used by the damping system are all mature products, and can meet the aerospace requirement.
Description
Technical Field
The invention relates to the technical field of satellite single machine structures, and belongs to a vibration reduction system of an accelerometer combination in a satellite attitude trajectory control system.
Background
The accelerometer combination is an independent single machine on the satellite and is used for an attitude sensitive system on the satellite, and after the satellite is started, the three-axis acceleration information of the satellite can be measured and provided for a superior system. The on-board accelerometers need to be confronted with impacts and vibrations from satellite-to-satellite separations, engine shutdowns, various actions on the satellite (or on the aircraft) and spacecraft during normal and emergency landing conditions, which can negatively affect the accuracy and lifetime of the on-board accelerometers.
The main function of the vibration reduction system of the satellite-borne accelerometer combination is to dissipate impact and random vibration energy caused by satellite and rocket running conditions. The energy transmission of the vibration reduction system is utilized to reduce a large amount of shock and vibration born by the accelerometer in the actual working process, improve the working environment of the accelerometer and improve the reliability of the accelerometer. Conventional damping system solutions have a number of disadvantages:
1. the traditional vibration reduction system layout mode usually adopts an eight-point vibration reduction mode, the four-point vibration reduction mode mostly adopts a structural lug mode to install the vibration reducer, the size of the vibration reduction system is larger, and the vibration reducer of the vibration reduction system adopts an embedded structure, so that the size of the vibration reduction system is favorably reduced;
2. the traditional layout form of the vibration damping system has higher requirements on the machining precision of the mounting structure, particularly form and position tolerance, and is not beneficial to cost control and cycle control of structural member machining;
3. the traditional vibration reduction system usually adopts a metal rubber vibration reducer, and the heat dissipation of rubber is poor, so that the thermal performance in a product is reduced to some extent, and the normal operation of an electronic device is not facilitated;
4. the traditional vibration reduction system usually adopts a metal rubber vibration reducer, a series of potential failure modes such as rubber aging exist, and the reliability and the service life of the vibration reduction system can be reduced;
5. the traditional vibration reduction system is usually fixedly connected to the side wall of a product, but not directly fixedly connected to a mounting bottom plate of the product, so that the heat dissipation of the position of the accelerometer support is not facilitated;
6. in a traditional complete machine level plane four-point layout vibration reduction system, a vibration reducer is usually directly installed on a lug structure of a complete machine, and because the centroid position of the complete machine is not coincident with the centroid position of the complete machine, the linear angular vibration coupling condition exists, and the speed information output of an accelerometer is not facilitated.
Aiming at the technical defects of the prior art, the invention provides a vibration reduction system for a satellite-borne accelerometer combination, which can solve the problems of overlarge size of a vibration reducer, short service life of the vibration reducer and poor heat dissipation and can effectively improve the reliability of the use of the accelerometer in a large-impact environment.
Disclosure of Invention
The invention aims to solve the problem that an accelerometer cannot bear large-magnitude impact and vibration. The vibration reduction system provided by the invention optimizes the traditional vibration reduction system, solves the technical defects of the traditional vibration reduction system, and improves the overall performance of the vibration reduction system for the satellite-borne accelerometer combination.
The invention provides a vibration reduction system for a satellite-borne accelerometer combination, which comprises a plurality of vibration reducers, an accelerometer mounting bracket and an accelerometer combination base, wherein the vibration reducers are arranged on the accelerometer mounting bracket; each shock absorber comprises an upper shock absorber and a lower shock absorber, the top end of each lower shock absorber is fixedly connected with the accelerometer mounting bracket, and the bottom end of each lower shock absorber is fixedly connected with the accelerometer combination base; the bottom end of each upper-layer shock absorber is fixedly connected with the accelerometer mounting bracket; the vibration energy of the accelerometer combination base fixedly connected to the satellite mounting deck plate is transmitted to the accelerometer combination base through the satellite mounting deck plate, then transmitted to the vibration damper and dissipated through the vibration damper.
A plurality of the shock absorbers in the scheme can effectively attenuate a large number of levels of shock and vibration transmitted to the accelerometer combination base in a satellite working environment, so that the influence of the shock and vibration on the accelerometer mounting bracket is reduced.
The accelerometer mounting bracket in the vibration damping system is provided with a lug structure specially used for mounting the vibration damper through the layout optimization of the vibration damper, the lug structure is provided with a groove used for embedding the vibration damper therein and fixedly connecting the vibration damper by using a screw, and the design of the structure is favorable for reducing the volume of the vibration damping system.
The vibration dampers are fixed on the accelerometer combination base bottom through threaded connection, the number of the vibration dampers is 4, and a planar four-point vibration damping layout structure is adopted.
In the preferred embodiment, after the accelerometer mounting bracket is mounted, an accelerometer, an electronic element and the like need to be mounted in the bracket, which results in the position of the center of mass of the bracket in front of and behind the whole bracket. In order to overcome the problem that the displacement of the mass center seriously affects the vibration reduction efficiency of a vibration reduction system, for example, the problem of linear-angular vibration coupling can be generated, the accuracy of information output of the accelerometer is also affected, the support needs to be subjected to counterweight after the accelerometer and the electronic element are installed, and the positions of the front mass center and the rear mass center of the accelerometer installation support and the positions of the front mass center and the rear mass center of the internally installed device are adjusted to be consistent through the counterweight.
The shock absorber is made of heat-conducting metal, and heat generated by the work of the accelerometer and the electronic element in the accelerometer mounting bracket can be transferred to the accelerometer combination base in a heat conduction mode and then transferred to the satellite mounting cabin plate.
The vibration reduction system further comprises a shell, wherein the shell is fixed on the accelerometer combination base, and the vibration reducers and the accelerometer installation support are wrapped in the shell.
The vibration reduction layout form of the system can reduce the requirement on the machining precision of the accelerometer combination base, thereby reducing the machining cost.
Compared with the traditional scheme of the vibration damping system, the vibration damping system has the advantages and beneficial effects that:
the vibration reduction layout is optimized, and the overall volume and quality of the product are reduced; the metal vibration damper integrates vibration damping and heat dissipation; the vibration damping system can adjust the center of mass of the bracket to be consistent with the vibration damping center, thereby effectively solving the problem of linear-angular vibration coupling; the invention has less requirement on the machining precision of the mounting base of the shock absorber, can effectively reduce the machining cost and the machining period, adopts mature materials, and is beneficial to cost control and production period control.
Drawings
FIG. 1 is a side view of a damping system design of the present invention;
FIG. 2 is a top plan view of the damping system design of the present invention;
fig. 3 is a schematic diagram of the damping system of the present invention.
Detailed Description
The vibration reduction system for the combination of the satellite-borne accelerometer provided by the invention is further described in detail with reference to the attached drawings and the detailed description. The advantages and features of the present invention will become more apparent from the following description. It is to be noted that the drawings are in a very simplified form and are all used in a non-precise scale for the purpose of facilitating and distinctly aiding in the description of the embodiments of the present invention. To make the objects, features and advantages of the present invention comprehensible, reference is made to the accompanying drawings. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the implementation conditions of the present invention, so that the present invention has no technical significance, and any structural modification, ratio relationship change or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention.
Fig. 1 shows a side view of the inventive damping system and fig. 2 shows a top view of the inventive damping system. As shown in fig. 1 and 2, the invention provides a vibration reduction system for a satellite-borne accelerometer combination, and the vibration reduction system for the satellite-borne accelerometer combination comprises a plurality of vibration absorbers 1, an accelerometer mounting bracket 2 and an accelerometer combination base 3; each shock absorber 1 comprises an upper layer shock absorber and a lower layer shock absorber, the top end of each lower layer shock absorber is fixedly connected with an accelerometer mounting bracket 2, and the bottom end of each lower layer shock absorber is fixedly connected with an accelerometer combination base 3; the bottom end of each upper-layer shock absorber is fixedly connected with the accelerometer mounting bracket 2; and the accelerometer combined base 3 is fixedly connected to the satellite mounting cabin plate.
In order to better describe the operation of the damping system, fig. 3 shows a flow chart of the damping mode of the damping system according to the present invention. As shown in fig. 3, large-magnitude shock and vibration on the satellite are firstly transmitted to the accelerometer combination base 3 through the satellite mounting deck, then the shock and vibration on the accelerometer combination base 3 are transmitted to the accelerometer mounting bracket 2 through the plurality of shock absorbers 1 mounted on the accelerometer combination base 3, and in the process, the energy of the shock and vibration is mostly dissipated after passing through the plurality of shock absorbers 1, so that the shock and vibration energy finally transmitted to the electronic element on the accelerometer mounting bracket 2 is greatly reduced, and the shock absorption effect is effectively achieved.
Preferably, the number of the shock absorbers 1 is 4, a planar four-point shock absorption layout structure is adopted, a lug structure specially used for mounting the shock absorbers is arranged on the accelerometer mounting bracket 2, grooves are formed in the lug structure and used for embedding the shock absorbers 1 into the lug structure and fixedly connecting the shock absorbers with screws, and the design of the structure is favorable for reducing the volume of a shock absorption system.
In the preferred embodiment, after the accelerometer mounting bracket is mounted, an accelerometer, an electronic component, and the like need to be mounted on the accelerometer mounting bracket 2, which causes the position of the center of mass of the accelerometer mounting bracket to change. The deviation of the mass center seriously influences the vibration damping efficiency of the vibration damping system, for example, the linear angular vibration coupling problem is generated, and the accuracy of the information output of the accelerometer is also influenced. In order to overcome the problem, the support needs to be weighted after the accelerometer and the electronic component are installed, and the front and back mass center positions of the accelerometer installing support 2 are kept consistent through weight adjustment.
Preferably, the plurality of shock absorbers 1 are made of heat conducting metal, heat generated by the work of electronic components in the accelerometer mounting support 2 is transmitted to the plurality of shock absorbers 1 through the accelerometer mounting support 2 in a heat conduction mode, then transmitted to the accelerometer combination base 3 through the plurality of shock absorbers 1 and finally transmitted to a mounting cabin plate of the whole satellite, and therefore the electronic components are guaranteed to be in a lower working temperature range.
The vibration damping system further comprises a shell, wherein the shell is fixed on the accelerometer combination base 3, and the plurality of vibration dampers 1 and the accelerometer mounting bracket 2 are wrapped in the shell.
Preferably, the accelerometer combination base has low requirements on processing precision, and processing cost and period can be effectively reduced.
The materials used in the invention are all mature products so as to meet the space navigation requirements.
The invention adopts a layout scheme of plane four-point vibration reduction and adopts an embedded structure for the installation angle of the vibration absorber, thereby solving the problems of larger volume of a vibration reduction system and the like caused by the layout of the traditional eight-point vibration reduction mode. Compared with the traditional vibration damping system, the vibration damping system has smaller volume, has good heat dissipation, replaces the traditional metal rubber with the metal vibration damper, further enhances the heat conduction effect and prolongs the service life of the system.
The invention has less requirement on the machining precision of the mounting base of the shock absorber, can effectively reduce the machining cost and the machining period, adopts mature materials, and is beneficial to controlling the cost and the production period.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (9)
1. A vibration reduction system for a combination of on-board accelerometers, comprising: the accelerometer comprises a plurality of shock absorbers (1), an accelerometer mounting bracket (2) and an accelerometer combined base (3);
each shock absorber (1) comprises an upper layer shock absorber and a lower layer shock absorber; the top end of each lower layer shock absorber is fixedly connected with an accelerometer mounting bracket (2), and the bottom end of each lower layer shock absorber is fixedly connected with the accelerometer combination base (3); the bottom end of each upper-layer shock absorber is fixedly connected with an accelerometer mounting bracket (2);
the accelerometer combination base (3) is fixedly connected to the satellite mounting cabin plate;
the vibration energy is transferred to the accelerometer assembly base (3) through the satellite deck and then to the damper (1) and dissipated via the damper (1).
2. Damping system according to claim 1, characterized in that the accelerometer assembly base (3) is fixed to the satellite mounting deck by screws; the accelerometer mounting bracket (2) is fixedly connected with each lower-layer shock absorber and each upper-layer shock absorber through screws.
3. Damping system according to claim 2, characterized in that the accelerometer mounting bracket (2) is provided with a lug structure for screw fixation.
4. Damping system according to claim 3, characterized in that the lug structure is provided with a recess for mounting the damper, into which recess the damper (1) is inserted and screwed in fixed connection.
5. Damping system according to claim 1, characterized in that the number of said dampers (1) is 4, in a planar four-point damping layout.
6. The vibration damping system according to claim 1, wherein the mounting on the accelerometer mounting bracket (2) comprises: an accelerometer, and an electronic component.
7. Damping system according to claim 6, characterized in that after the accelerometer mounting bracket (2) has been mounted with the components including accelerometer and electronics, the accelerometer mounting bracket is weighted to ensure a consistent front-to-back mass center.
8. The vibration damping system according to claim 1, wherein the plurality of vibration dampers (1) are made of heat conductive metal, and heat generated by the operation of the accelerometer and the electronic components inside the accelerometer mounting bracket (2) is transferred to the accelerometer assembly base (3) and further transferred to the satellite mounting deck by a heat conduction manner.
9. The vibration damping system according to claim 1, further comprising a housing fixed to the accelerometer assembly base (3) and enclosing the plurality of vibration dampers (1) and the accelerometer mounting bracket (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010952421.XA CN112032245A (en) | 2020-09-11 | 2020-09-11 | Vibration reduction system for satellite-borne accelerometer combination |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010952421.XA CN112032245A (en) | 2020-09-11 | 2020-09-11 | Vibration reduction system for satellite-borne accelerometer combination |
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| CN112032245A true CN112032245A (en) | 2020-12-04 |
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| CN202010952421.XA Pending CN112032245A (en) | 2020-09-11 | 2020-09-11 | Vibration reduction system for satellite-borne accelerometer combination |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114413886A (en) * | 2021-12-24 | 2022-04-29 | 上海航天控制技术研究所 | Zero compensation method for combination of satellite-borne accelerometers |
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2020
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114413886A (en) * | 2021-12-24 | 2022-04-29 | 上海航天控制技术研究所 | Zero compensation method for combination of satellite-borne accelerometers |
| CN114413886B (en) * | 2021-12-24 | 2024-01-02 | 上海航天控制技术研究所 | Combined zero compensation method for satellite-borne accelerometer |
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