CN105173125A - Adjustable air flotation device for satellite eccentric expandable accessories and using method of adjustable air flotation device - Google Patents
Adjustable air flotation device for satellite eccentric expandable accessories and using method of adjustable air flotation device Download PDFInfo
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- CN105173125A CN105173125A CN201510466033.XA CN201510466033A CN105173125A CN 105173125 A CN105173125 A CN 105173125A CN 201510466033 A CN201510466033 A CN 201510466033A CN 105173125 A CN105173125 A CN 105173125A
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Abstract
The invention provides an adjustable air flotation device for satellite eccentric expandable accessories and a using method of the adjustable air flotation device. The adjustable air flotation device comprises a bearing cross beam, a self-aligning cross beam, a supporting vertical beam, a cross four-foot chassis, air flotation discs, air flotation disc air inlets and air distributing pipes. According to the adjustable air flotation device, based on a traditional air flotation device of the satellite expandable accessories, the function of adapting to eccentricity and the adjustable function thereof are improved according to application requirements; the expandable accessories can be borne reliably and safely so that an in-orbit weightless environment can be simulated, and meanwhile test failures caused by friction, tumble and the like on account of eccentricity can be prevented effectively; it is reliably guaranteed that a ground deployment test of the satellite eccentric expandable accessories can be completed effectively and smoothly.
Description
Technical field
The invention belongs to the field of the ground spreading test air-floating apparatus of the deployable annex of satellite, be specifically related to a kind of adjustable air-floating apparatus for the eccentric deployable annex of satellite.
Background technology
Satellite launches annex (as sun battle array, aerial system etc.) and occurs increasing eccentric nature along with technical development, namely the barycenter launching annex can not ensure on the joint face of air-floating apparatus with expansion annex, so, then certainly existing bias makes annex quality laterally act on air-floating apparatus, cause the generation of friction and affect test validity, even there will be under serious conditions and launch toppling over of annex.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of adjustable air-floating apparatus for the eccentric deployable annex of satellite,
According to a kind of adjustable air-floating apparatus for the eccentric deployable annex of satellite provided by the invention, comprising: bearing beam, aligning crossbeam, support vertical beam, cross four sole dish, air supporting dish, gas-distributing pipe;
Bearing beam is articulated with the end of aligning crossbeam, and can turn at the first plane internal rotation around the axis by hinge-point A; Wherein, hinge-point A refers to the hinge-point between bearing beam and aligning crossbeam;
The middle part of aligning crossbeam is articulated with the upper end supporting vertical beam, and can turn at the second plane internal rotation around the axis by hinge-point B; Wherein, hinge-point B refers to the hinge-point between aligning crossbeam and support vertical beam; Second plane parallel is in the first plane;
The lower end supporting vertical beam is fastenedly connected on cross four sole dish;
Four underfooting of cross four sole dish are respectively arranged with an air supporting dish; Spatial destribution between air supporting dish presents 90 degree of circle distribution;
The admission port of air supporting dish connects gas-distributing pipe;
Gas-distributing pipe, for accepting source of the gas and the admission port giving air supporting dish produces air film for air supporting dish, unloads the gravity of eccentric deployable annex;
Bearing beam is used for being spirally connected with the deployable annex of bias, and the interface of bearing beam arranges through hole.
Preferably: hinged by screw between bearing beam and aligning crossbeam, screw tightens from bottom to top, namely bearing beam is provided with the tapped bore with screw mates, the positioning through hole that screw is greater than screw maximum outside diameter through the aperture of aligning crossbeam one end screws in tapped bore.
Preferably: hinged by screw between aligning crossbeam and support vertical beam, screw tightens from top to bottom, namely support on vertical beam and be provided with the tapped bore with screw mates, the positioning through hole that screw is greater than screw maximum outside diameter through the aperture in the middle part of aligning crossbeam screws in tapped bore.
Preferably: bearing beam can, around aligning crossbeam in the first plane internal rotation three-sixth turn, make eccentric carrying scope be in 360 degree of regions that positioning through hole axis rotates on aligning crossbeam.
Preferably: aligning crossbeam can, around support vertical beam in the second plane internal rotation three-sixth turn, make eccentric carrying scope be around supporting in 360 degree of regions that on vertical beam, positioning through hole axis rotates.
Preferably: multiple positioning through hole aligning crossbeam existing certain intervals, the hole count of positioning through hole is 14.
According to the using method of a kind of above-mentioned adjustable air-floating apparatus for the eccentric deployable annex of satellite provided by the invention, comprise the steps:
The first step, according to bias deployable annex barycenter test value, computing value or discreet value, first adjust within the scope of 360 degree that support vertical beam at aligning crossbeam, make bearing beam adjust within the scope of 360 degree of aligning crossbeam more as required, make support vertical beam by or basically by the deployable annex barycenter of bias;
Second step, is spirally connected bearing beam and the deployable annex of bias, is stabilized on platform by the air supporting dish under cross four sole dish, ensures that four air supporting dishes all fit tightly with platform;
3rd step, connects source of the gas to gas-distributing pipe, then is connected by the admission port of gas-distributing pipe with air supporting dish, ensure that source of the gas is supplied in air supporting dish and inflates.
All screws of eccentric adjustable air-floating apparatus connect, and comprise being spirally connected between bearing beam and aligning crossbeam, aligning crossbeam and support vertical beam etc., all should be fastenedly connected before device place in operation.
Compared with prior art, the present invention has following beneficial effect:
1, the present invention is on the basis that satellite launches annex tradition air-floating apparatus, improve according to application needs and adapt to eccentric and adjustable function, launch accessory weight and simulate in-orbit while weightlessness to reach can reliable and secure carry, the friction effectively preventing from producing because of eccentric, topple etc. causes test failure, reliably ensures that ground spreading that satellite bias launches annex is tested and effectively, successfully completes.
2, the design configuration that has of this device of the present invention is simple, there is good design flexibility, realize economy and assembly process process, possess the features such as extensibility is strong, economy and durability, reliability are high, it is convenient, easy to use to assemble, applied range, various satellite can be applied to and launch in the ground spreading test of annex.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the perspective view of apparatus of the present invention.
Fig. 2 is the schematic diagram of the test application of apparatus of the present invention and side, end face corresponding relation.
Fig. 3, Fig. 4 are the principle schematic of apparatus of the present invention.
In figure: 1-bearing beam; 2-aligning crossbeam; 3-supports vertical beam; 4-cross four sole dish; 5-air supporting dish; 6-air supporting dish admission port; 7-gas-distributing pipe; 8-positioning through hole; 9-tracheae.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
Shown in accompanying drawing 1, Fig. 2 and Fig. 3, a kind of using method of the adjustable air-floating apparatus for the eccentric deployable annex of satellite, concrete steps are as follows:
The first step, according to annex barycenter test value, computing value or discreet value, first adjust within the scope of 360 degree that support vertical beam 3 at aligning crossbeam 2, bearing beam 1 is made to adjust within the scope of 360 degree of aligning crossbeam 2 more as required, make to support vertical beam 3 approximately through annex barycenter, and cross four sole dish 4 is firm.
Second step, being placed on by the described adjustable air-floating apparatus for the eccentric deployable annex of satellite launches in the middle of annex and marble platform, then bearing beam 1 and annex are spirally connected, cross four sole dish 4 and air supporting dish 5 thereof are stabilized in marble platform, ensure four air supporting dishes 5 all with the fitting tightly of marble platform.
3rd step, connects source of the gas to gas-distributing pipe 7, then is connected with air supporting dish 5 admission port by gas-distributing pipe 7, ensure the smooth supply air supporting dish 5 of source of the gas.
Wherein, the described adjustable air-floating apparatus for the eccentric deployable annex of satellite, comprising: bearing beam, aligning crossbeam, support vertical beam, cross four sole dish, air supporting dish, gas-distributing pipe;
Bearing beam is articulated with the end of aligning crossbeam, and can turn at the first plane internal rotation around the axis by hinge-point A; Wherein, hinge-point A refers to the hinge-point between bearing beam and aligning crossbeam;
The middle part of aligning crossbeam is articulated with the upper end supporting vertical beam, and can turn at the second plane internal rotation around the axis by hinge-point B; Wherein, hinge-point B refers to the hinge-point between aligning crossbeam and support vertical beam; Second plane parallel is in the first plane;
The lower end supporting vertical beam is fastenedly connected on cross four sole dish;
Four underfooting of cross four sole dish are respectively arranged with an air supporting dish; Spatial destribution between air supporting dish presents 90 degree of circle distribution;
The admission port of air supporting dish connects gas-distributing pipe;
Gas-distributing pipe, for accepting source of the gas and the admission port giving air supporting dish produces air film for air supporting dish, unloads the gravity of eccentric deployable annex;
Bearing beam is used for being spirally connected with the deployable annex of bias, and the interface of bearing beam arranges through hole.
Preferably: hinged by screw between bearing beam and aligning crossbeam, screw tightens from bottom to top, namely bearing beam is provided with the tapped bore with screw mates, the positioning through hole that screw is greater than screw maximum outside diameter through the aperture of aligning crossbeam one end screws in tapped bore.
Preferably: hinged by screw between aligning crossbeam and support vertical beam, screw tightens from top to bottom, namely support on vertical beam and be provided with the tapped bore with screw mates, the positioning through hole that screw is greater than screw maximum outside diameter through the aperture in the middle part of aligning crossbeam screws in tapped bore.
Preferably: bearing beam can, around aligning crossbeam in the first plane internal rotation three-sixth turn, make eccentric carrying scope be in 360 degree of regions that positioning through hole axis rotates on aligning crossbeam.
Preferably: aligning crossbeam can, around support vertical beam in the second plane internal rotation three-sixth turn, make eccentric carrying scope be around supporting in 360 degree of regions that on vertical beam, positioning through hole axis rotates.
Preferably: multiple positioning through hole aligning crossbeam existing certain intervals, the hole count of positioning through hole is 14.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (7)
1. the adjustable air-floating apparatus for the eccentric deployable annex of satellite, it is characterized in that, comprising: bearing beam (1), aligning crossbeam (2), support vertical beam (3), cross four sole dish (4), air supporting dish (5), gas-distributing pipe (7);
Bearing beam (1) is articulated with the end of aligning crossbeam (2), and can turn at the first plane internal rotation around the axis by hinge-point A; Wherein, hinge-point A refers to the hinge-point between bearing beam (1) and aligning crossbeam (2);
The middle part of aligning crossbeam (2) is articulated with the upper end supporting vertical beam (3), and can turn at the second plane internal rotation around the axis by hinge-point B; Wherein, hinge-point B refers to the hinge-point between aligning crossbeam (2) and support vertical beam (3); Second plane parallel is in the first plane;
The lower end supporting vertical beam (3) is fastenedly connected on cross four sole dish (4);
Four underfooting of cross four sole dish (4) are respectively arranged with an air supporting dish (5); Spatial destribution between air supporting dish (5) presents 90 degree of circle distribution;
The admission port of air supporting dish (5) connects gas-distributing pipe (7);
Gas-distributing pipe (7), for accepting source of the gas and the admission port giving air supporting dish (5) produces air film for air supporting dish (5), unloads the gravity of eccentric deployable annex;
Bearing beam (1), for being spirally connected with the deployable annex of bias, the interface of bearing beam (1) arranges through hole.
2. the adjustable air-floating apparatus for the eccentric deployable annex of satellite according to claim 1, it is characterized in that: hinged by screw between bearing beam (1) and aligning crossbeam (2), screw tightens from bottom to top, namely bearing beam (1) is provided with the tapped bore with screw mates, the positioning through hole that screw is greater than screw maximum outside diameter through the aperture of aligning crossbeam (2) one end screws in tapped bore.
3. the adjustable air-floating apparatus for the eccentric deployable annex of satellite according to claim 1, it is characterized in that: hinged by screw between aligning crossbeam (2) and support vertical beam (3), screw tightens from top to bottom, namely support on vertical beam (3) and be provided with the tapped bore with screw mates, the positioning through hole that screw is greater than screw maximum outside diameter through the aperture in the middle part of aligning crossbeam (2) screws in tapped bore.
4. the adjustable air-floating apparatus for the eccentric deployable annex of satellite according to claim 2, it is characterized in that: bearing beam (1) can, around aligning crossbeam (2) in the first plane internal rotation three-sixth turn, make eccentric carrying scope be in 360 degree of regions that the upper positioning through hole axis of aligning crossbeam (2) rotates.
5. the adjustable air-floating apparatus for the eccentric deployable annex of satellite according to claim 3, it is characterized in that: aligning crossbeam (2) can, around support vertical beam (3) in the second plane internal rotation three-sixth turn, make eccentric carrying scope be in the 360 degree of regions supporting the upper positioning through hole axis rotation of vertical beam (3).
6. the adjustable air-floating apparatus for the eccentric deployable annex of satellite according to claim 4, it is characterized in that: multiple positioning through hole aligning crossbeam (2) existing certain intervals, the hole count of positioning through hole is 14.
7. a using method for the adjustable air-floating apparatus for the eccentric deployable annex of satellite according to any one of claim 1 to 6, is characterized in that, comprise the steps:
The first step, according to bias deployable annex barycenter test value, computing value or discreet value, first in aligning crossbeam (2) adjustment within the scope of 360 degree that support vertical beam (3), make bearing beam (1) adjust within the scope of 360 degree of aligning crossbeam (2) more as required, make support vertical beam (3) by or basically by the deployable annex barycenter of bias;
Second step, is spirally connected bearing beam (1) and the deployable annex of bias, is stabilized on platform, ensures that four air supporting dishes (5) all fit tightly with platform by the air supporting dish (5) under cross four sole dish (4);
3rd step, connects source of the gas to gas-distributing pipe (7), then is connected by the admission port of gas-distributing pipe (7) with air supporting dish (5), ensure that source of the gas is supplied in air supporting dish (5) and inflates.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510466033.XA CN105173125B (en) | 2015-07-31 | 2015-07-31 | Scalable air-floating apparatus for the eccentric deployable adnexa of satellite and its using method |
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| CN201510466033.XA CN105173125B (en) | 2015-07-31 | 2015-07-31 | Scalable air-floating apparatus for the eccentric deployable adnexa of satellite and its using method |
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| CN105173125B CN105173125B (en) | 2017-03-08 |
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Cited By (4)
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| CN106918462A (en) * | 2015-12-24 | 2017-07-04 | 中国科学院沈阳自动化研究所 | A kind of mass inertia simulating piece structure based on given frequency constraint |
| CN106921026A (en) * | 2015-12-24 | 2017-07-04 | 中国科学院沈阳自动化研究所 | A kind of orthogonal satellite antenna drive mechanism ground air supporting gravity unloading mechanism of two axles |
| CN108897012A (en) * | 2018-06-15 | 2018-11-27 | 上海卫星工程研究所 | A kind of adjustable suspension apparatus and its application for satellite bias expansion attachment |
| CN109188648A (en) * | 2018-09-11 | 2019-01-11 | 中国科学院长春光学精密机械与物理研究所 | A kind of floating support device for the unloading of space optics load ground gravity |
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| CN108897012A (en) * | 2018-06-15 | 2018-11-27 | 上海卫星工程研究所 | A kind of adjustable suspension apparatus and its application for satellite bias expansion attachment |
| CN109188648A (en) * | 2018-09-11 | 2019-01-11 | 中国科学院长春光学精密机械与物理研究所 | A kind of floating support device for the unloading of space optics load ground gravity |
| CN109188648B (en) * | 2018-09-11 | 2020-05-15 | 中国科学院长春光学精密机械与物理研究所 | Floating support device for unloading space optical load ground gravity |
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