CN204223195U - Discrete point type satellite adapter - Google Patents
Discrete point type satellite adapter Download PDFInfo
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- CN204223195U CN204223195U CN201420642943.XU CN201420642943U CN204223195U CN 204223195 U CN204223195 U CN 204223195U CN 201420642943 U CN201420642943 U CN 201420642943U CN 204223195 U CN204223195 U CN 204223195U
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Abstract
A kind of discrete point type satellite adapter.In order to overcome the complex structure that existing satellite adapter exists, can not meet the deficiency of the non-centrosymmetry point type interface requirements of specific middle-size and small-size satellite, 4 coaming plates of the present utility model surround a rectangle, and coaming plate is fixedly connected with by column with coaming plate; Column is made up of top board, base plate and cross riser, and cross riser is axially supported in the middle of base plate and top board; Column is axially divided into 4 regions by cross riser, and wherein 2 diagonal zones are fixedly connected with coaming plate respectively, and the column inner clip angular zone between 2 coaming plates is for installing release spring; Column outer clip angular zone dividing plate horizontal subdivision between 2 coaming plates is upper and lower 2 districts, is respectively used to install low impact disengagement gear and release travel switch.Its beneficial effect is: structure is simple, rationally distributed, compact conformation, is convenient to install and operation; Size and the riser inclination angle of column regional can be adjusted according to satellite size.
Description
Technical field
The utility model relates to a kind of satellite adapter, especially relates to a kind of discrete point type satellite adapter, is applicable to and has point type interface satellite and be connected with the installation of rocket body support.
Background technology
Satellite adapter is the vitals connecting satellite and rocket body structure in space industry, is applied to dynamic changes process between satellite and carrier rocket.The skin stringer formula that the is mostly satellite adapter of current use, Chinese invention patent application " shell type adapter " (publication number CN2010254971) disclosed in 14 days March in 2012, this adapter is a truncated cone shape assembly, the riveted joint of truncated cone shape assembly top has a upper end frame, upper end frame forms satellite and the rocket burbling area and fixture block contact surface respectively, and it is provided with the mounting interface for satellite or delivery travel switch; The riveted joint of truncated cone shape assembly bottom has a lower end frame, the support that this lower end frame transports in order to provide satellite, parks; Upper end frame and this lower end frame are combined into an entirety by a covering through riveted joint, and covering passes to the Main Load of satellite in order to carry carrier rocket, due to complex structure, truncated cone shape can not meet the non-centrosymmetry point type interface requirements of certain specific middle-size and small-size satellite.The satellite adapter of composite material also has similar problem, and valuable product.
Utility model content
In order to overcome the complex structure that existing satellite adapter exists, can not meet the deficiency of the non-centrosymmetry point type interface requirements of specific middle-size and small-size satellite, the utility model provides a kind of discrete point type satellite adapter.
The utility model solves the technical scheme that its technical matters adopts: the coaming plate quantity of discrete point type satellite adapter is 4, and 4 coaming plates surround a rectangle, and coaming plate is fixedly connected with by column with coaming plate; Column is made up of top board, base plate and cross riser, and cross riser is axially supported in the middle of base plate and top board; Column is axially divided into 4 regions by cross riser, and wherein 2 diagonal zones are fixedly connected with coaming plate respectively, and the column inner clip angular zone between 2 coaming plates is for installing release spring; Column outer clip angular zone dividing plate horizontal subdivision between 2 coaming plates is upper and lower 2 districts, is respectively used to install low impact disengagement gear and release travel switch.Every 2 coaming plates are installed as one group in opposite directions, and wherein one group of coaming plate is vertically arranged straight coaming plate, and another group is the oblique coaming plate tilting to install; Oblique coaming plate is tilted to rectangle from the bottom to top; The angle of oblique coaming plate and perpendicular line is 12-18 °.
Column quantity is 4, and comprise 2 columns I and II, 2 the column I diagonal angles installations of 2 columns, 2 column II diagonal angles are installed; Column I is identical with the angle of inclination of oblique coaming plate for the cross riser plate face fixedly mounting oblique coaming plate with on column II, and top board 6 interface of column upper end is non-centrosymmetry, symmetrical centered by base plate 7 interface of column lower end.The plate face of straight coaming plate, tiltedly coaming plate is provided with ripple, the plane between ripple and ripple has the mounting hole of installing cables or instrument.
The beneficial effects of the utility model are, structure is simple, rationally distributed, compact conformation, are convenient to install and operation; Can adjust size and the riser inclination angle of column regional according to satellite size, the use for all parts provides good intensity and toughness environment.
Accompanying drawing explanation
Fig. 1 is the utility model discrete point type satellite adapter structure schematic diagram.
In figure: 1. column I, 2. straight coaming plate, 3. oblique coaming plate, 4. column II, 5. cross riser, 6. top board, 7. base plate, 8. column inner clip angular zone, 9. column outer clip angular zone.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail.But those skilled in the art should know, the invention is not restricted to listed detailed description of the invention, as long as spirit according to the invention, all should be included in protection scope of the present invention.
With reference to accompanying drawing.The utility model discrete point type satellite adapter comprises coaming plate, column, and the quantity of coaming plate is 4, and 4 coaming plates surround a rectangle, and coaming plate is fixedly connected with by column with coaming plate, keeps the integraty of satellite adapter element.4 every 2 of coaming plates are installed as one group in opposite directions, and wherein one group of coaming plate is vertically arranged straight coaming plate 2, and another group is the oblique coaming plate 3 tilting to install; Oblique coaming plate 3 is tilted to rectangle from the bottom to top, and oblique coaming plate 3 is 12-18 ° with the angle of perpendicular line, and usual angle is 15 °.
Column is the radical function of adapter is power transmission and carrying.Column is made up of top board 6, base plate 7 and cross riser 5, and cross riser 5 is axially supported in cross bracing shape in the middle of base plate 7 and top board 6, and usual column is formed in one.Column is axially divided into 4 regions by cross riser 5, and the function in each region is different.Wherein 2 diagonal zones are fixedly connected with coaming plate respectively, and the column inner clip angular zone 8 between 2 coaming plates is for installing release spring; Column outer clip angular zone 9 between 2 coaming plates is upper and lower 2 districts with dividing plate horizontal subdivision, is respectively used to install low impact disengagement gear and release travel switch.
Column comprises 2 columns I 1 and 2 columns, II 4,2 column I 1 diagonal angles are installed, and 2 column II 4 diagonal angles are installed; Column I 1 is identical with the angle of inclination of oblique coaming plate 3 for the cross riser 5 plate face fixedly mounting oblique coaming plate 3 with on column II 4.The top board 6 interface distribution of column is non-centrosymmetry along with celestial body butt hole, base plate 7 times interfaces are centrosymmetric with distributing box distribution, therefore the upright coaming plate in both sides during connection column, the oblique coaming plate in another both sides, to meet the requirement of satellite adapter global sections gradual change.
The plate face of straight coaming plate 2, tiltedly coaming plate 3 is provided with ripple, and be corrugated by metal plate punching usually, to increase the rigidity of coaming plate, the version of thin plate panel beating can meet lighting requirement.Plane between coaming plate ripple and ripple has the mounting hole of installing cables or instrument, will not stress or stressed very little instrument cable is arranged on coaming plate, convenient operation is implemented.
The utility model discrete point type satellite adapter is different from traditional cylindrical (or truncated cone shape) satellite and the rocket interface, interface for certain type satellite is the non-centrosymmetrical four-point distribution interface of rotational symmetry, satellite distributor will can be good at carrying discrete point type concentrated force, limit by height, selected 4 uniform columns as carrying main structure; Adopt vertical coaming plate and oblique coaming plate conbined usage, ensure the globality of adapter.Make full use of the usage space of carrying column, satellite and rocket rocket body connecting interface are provided, release spring mounting interface, low impact disengagement gear mounting interface are provided, transmit celestial body and rocket body load, and instrument cable installing space and interface etc., good economy performance.
The utility model adopts quadrangle column Brattice type satellite adapter design scheme, meets connection and the carrying needs of grapefruit satellite point type discrete type interface; Multifunctional column and ripple coaming plate, meet the demand of adapter separation and power transmission transition, Fabric utilization is high; The structure design of column ripple coaming plate can well solve the connectivity problem of satellite point type interface, is easy to the commercialization of structure, normalisation.
It should be noted that above-described embodiment is example and unrestricted the present invention, those skilled in the art can design a lot of alternate embodiment and not depart from the right of this patent.
Claims (5)
1. a discrete point type satellite adapter, comprises coaming plate, it is characterized in that: the quantity of described coaming plate is 4, and 4 coaming plates surround a rectangle, and coaming plate is fixedly connected with by column with coaming plate;
Described column is made up of top board (6), base plate (7) and cross riser (5), and cross riser (5) is axially supported in the middle of base plate (7) and top board (6); Column is axially divided into 4 regions by cross riser (5), and wherein 2 diagonal zones are fixedly connected with coaming plate respectively, and the column inner clip angular zone (8) between 2 coaming plates is for installing release spring; Column outer clip angular zone (9) between 2 coaming plates is upper and lower 2 districts with dividing plate horizontal subdivision, is respectively used to install low impact disengagement gear and release travel switch.
2. discrete point type satellite adapter according to claim 1, it is characterized in that: every 2 of described coaming plate is installed as one group in opposite directions, wherein one group of coaming plate is vertically arranged straight coaming plate (2), the oblique coaming plate (3) of another group for tilting to install; Oblique coaming plate (3) is tilted to rectangle from the bottom to top.
3. discrete point type satellite adapter according to claim 2, is characterized in that: described oblique coaming plate (3) is 12-18 ° with the angle of perpendicular line.
4. discrete point type satellite adapter according to claim 3, it is characterized in that: described column quantity is 4, comprise 2 columns, I (1) and 2 column II (4), 2 column I (1) diagonal angles are installed, and 2 column II (4) diagonal angles are installed; Column I (1) is identical with the angle of inclination of oblique coaming plate (3) for cross riser (5) the plate face fixedly mounting oblique coaming plate (3) with on column II (4); Top board (6) interface of column upper end is non-centrosymmetry, symmetrical centered by the base plate (7) of column lower end.
5. discrete point type satellite adapter according to claim 4, is characterized in that: the plate face of described straight coaming plate (2), tiltedly coaming plate (3) is provided with ripple, the plane between ripple and ripple has the mounting hole of installing cables or instrument.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420642943.XU CN204223195U (en) | 2014-10-31 | 2014-10-31 | Discrete point type satellite adapter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420642943.XU CN204223195U (en) | 2014-10-31 | 2014-10-31 | Discrete point type satellite adapter |
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| CN204223195U true CN204223195U (en) | 2015-03-25 |
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| CN201420642943.XU Active CN204223195U (en) | 2014-10-31 | 2014-10-31 | Discrete point type satellite adapter |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628252A (en) * | 2016-10-11 | 2017-05-10 | 北京宇航系统工程研究所 | In-orbit aircraft structure of effective load adapter based on parallel arrangement |
| CN108177799A (en) * | 2017-11-20 | 2018-06-19 | 首都航天机械公司 | A kind of discrete point type carries rimless structure satellite adapter and its assembly method |
| CN111409875A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Composite material bearing structure suitable for space vehicle separation cabin section |
| CN112135777A (en) * | 2018-05-24 | 2020-12-25 | 欧盟委员会 | Efficient satellite architecture model for single launch or stacked multiple launches |
-
2014
- 2014-10-31 CN CN201420642943.XU patent/CN204223195U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628252A (en) * | 2016-10-11 | 2017-05-10 | 北京宇航系统工程研究所 | In-orbit aircraft structure of effective load adapter based on parallel arrangement |
| CN106628252B (en) * | 2016-10-11 | 2018-11-02 | 北京宇航系统工程研究所 | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter |
| CN108177799A (en) * | 2017-11-20 | 2018-06-19 | 首都航天机械公司 | A kind of discrete point type carries rimless structure satellite adapter and its assembly method |
| CN108177799B (en) * | 2017-11-20 | 2020-08-21 | 首都航天机械公司 | Discrete point type bearing frameless structure satellite adapter and assembling method thereof |
| CN112135777A (en) * | 2018-05-24 | 2020-12-25 | 欧盟委员会 | Efficient satellite architecture model for single launch or stacked multiple launches |
| CN111409875A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Composite material bearing structure suitable for space vehicle separation cabin section |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |