CN205418145U - Spacecraft payload subtracts impact device - Google Patents
Spacecraft payload subtracts impact device Download PDFInfo
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- CN205418145U CN205418145U CN201521040131.9U CN201521040131U CN205418145U CN 205418145 U CN205418145 U CN 205418145U CN 201521040131 U CN201521040131 U CN 201521040131U CN 205418145 U CN205418145 U CN 205418145U
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Abstract
The utility model discloses a spacecraft payload subtracts impact device, its characterized in that includes interior side ring, support ring and outside ring in proper order, from the interior inboard loop mapping hole of the interior side ring threaded holes and of extremely outer circumference evenly distributed respectively, the crisscross distribution in interior side ring threaded holes and inboard loop mapping hole on the interior side ring, circumference evenly distributed outside loop mapping hole and outside ring screw hole are respectively gone up from interior outside to outside ring, the distribution that interlocks of outside loop mapping hole and outside ring screw hole, interior side opening of difference circumference evenly distributed support ring and support ring outside hole outside the support ring follow is interior, support ring and interior side ring fixed connection, support ring and outside ring fixed connection. This device is small, simple structure, and the strong operability, that can satisfy in spacecraft payload subtracts the impact demand to that can regard as other equipment subtracts the impact measure.
Description
Technical field
The present invention relates to impact and slow down technical field, be specifically related to a kind of spacecraft payload impact-reducing device.
Background technology
In space industry, payload (satellite, airship etc.) is by rocket delivery lift-off, and during payload and Separation, impact is the harshest mechanical environment that spacecraft is experienced.The shock environment that payload is stood mainly operationally is produced by various Fire load, such as the unblock etc. during expandable part expansion on satellite and the rocket separation, the separation of satellite capsule section, star.The energy release that these processes cause due to blasting bolt blast, and then produce the adverse circumstances of blast impulse.Although the ofest short duration relative to whole emission process, but the impact of payload be can not be ignored by impact.
Blast impulse in addition to having plastic deformation near explosive source, relatively large bullet (arrow) body structure only transfer elastic ripple, and itself be susceptible to Explosive separation impact impact (except slim-lined construction, frivolous structure and fragile material structure).But, Explosive separation impact produces material stress ripple, overall dimensions can be made to produce the most high-frequency response with wavelength with the miniature electronic chip of magnitude, thus electronic equipment and micromechanical devices are produced harm, particularly to electronic product, frivolous structure, fragile material destruction particularly evident.
For Process of Piggyback Satellite structure, be hit in separation process the impact of stress wave, makes Process of Piggyback Satellite and final vehicle in addition to lengthwise movement, also produces the traversing of respective barycenter and the rotation around respective barycenter, thus cause angle and angular speed to change, even result in collision.Even if the satellite and the rocket complete to separate, if Process of Piggyback Satellite can not depart from adapter smoothly, also planned orbit cannot be entered with correct attitude.Visible, in satellite and the rocket separation process, the impact-reducing measure taking necessity is the most necessary.
The present invention provides a kind of spacecraft payload impact-reducing device, to reduce the impact stress wave loops to payload, the present invention includes three-decker from the inside to the outside, is provided with multiple stress wave transmission interface, and devise viscous damping material, transmit with the energy of at utmost decay stress ripple.
This principle of device is simple, can be as the impact-reducing measure using equipment in spacecraft or other shock environments.
Summary of the invention
The present invention is directed to payload in spacecraft affected by blast impulse in separation process, it is provided that a kind of spacecraft payload impact-reducing device.This device is in payload and supports between support, reduces the blast impulse of support to the propagation of payload.
A kind of spacecraft payload impact-reducing device that the present invention provides, includes interior side ring, support ring and outer side ring successively；Distinguishing side ring screwed hole and hole, interior side ring location in even circumferential distribution on interior side ring from the inside to the outside, interior side ring screwed hole and hole, interior side ring location are interspersed；On outer side ring, outside interior, even circumferential is distributed side ring hole, location and outer side ring screwed hole respectively, and outer side ring hole, location and outer side ring screwed hole are interspersed；Support ring is difference even circumferential distribution support ring inboard aperture and support ring apertura lateralis outside interior；Support ring is fixing with interior side ring to be connected, and support ring is fixing with outer side ring to be connected.
Described spacecraft payload impact-reducing device, also include inner shield ring and outer back-up ring, inner shield ring is inside interior side ring, it is inner side damping layer between inner shield ring and outer side ring, support ring, interior side ring, outside outer back-up ring side ring outside, it is outside damping layer between outer back-up ring and outer side ring, support ring, interior side ring.
Described interior side ring, support ring, outer side ring, inner shield ring, outer back-up ring are circular ring structure.
Described interior side ring hole, location and outer side ring location Kong Weifang trench structure, hole, interior side ring location includes interior side ring interconnecting hole and the outer connecting hole of interior side ring, interior side ring is connected by interior side ring interconnecting hole is fixing with outside bearing bracket, and interior side ring is fixed with support ring be connected by the outer connecting hole of interior side ring and support ring apertura lateralis；Hole, outer side ring location includes the outer connecting hole of outer side ring and outer side ring interconnecting hole, and outer side ring is connected by the outer connecting hole of outer side ring is fixing with external payload, and outer side ring is connected by outer side ring interconnecting hole and support ring inboard aperture are fixing with support ring.
Further, described interior side ring is connected by bottom connecting bolt with outside bearing bracket, and outer side ring is connected by top connecting bolt with external payload, and bottom connecting bolt and top connecting bolt are hexagon-headed bolt, square head bolt, T-slot bolt.
Described inner side damping layer and outside damping layer are viscous damping material.
Further, described inner side damping layer and outside damping layer are butyl rubber, phenolic resin, solidification glue.
Beneficial effects of the present invention is as follows:
The present invention uses inside and outside hierachical structure, and is interspersed by connecting bolt, to increase stress fluctuation propagation path.The present invention also sets up interior outside viscous damping layer, and uses back-up ring to retrain.When being impacted, damping layer can be deformed along with matrix strain, and material internal produces alternation tension and compression stress and strain.According to the Energy Dissipation Mechanism of damping material, structural impact energy can be lost when material produces alternate stress, strain, thus produce the effect of impact-reducing.The structures such as internal-flange bolt of the present invention, increase the transmissive interface of stress wave, farthest reduce and transmit to the shock wave of payload.Top of the present invention connecting bolt is to connect payload, and bottom connecting bolt connects support support, the location structure of connecting bolt, prevents the rotation in screwing process, makes connection procedure the most easily operated.
Volume of the present invention is little, simple in construction, strong operability, can meet the impact-reducing demand of payload in spacecraft, it is possible to as the impact-reducing measure of other equipment.
Accompanying drawing explanation
Fig. 1 is spacecraft payload impact-reducing device front view；
Fig. 2 is spacecraft payload impact-reducing device top view；
Fig. 3 is the interior side ring front view of the present invention；
Fig. 4 is the interior side ring top view of the present invention；
Fig. 5 is the outer side ring bottom view of the present invention；
Fig. 6 is the outer side ring front view of the present invention；
Fig. 7 is the support ring front view of the present invention；
Fig. 8 is the support ring top view of the present invention；
Fig. 9 is embodiments of the invention schematic diagrams.
In outside the outer back-up ring 3-of 1-top connecting bolt 2-, bottom damping layer 5-, in connecting bolt 6-, in side ring 6a-, in side ring screwed hole 6b-, side ring positions hole 6c-, in side ring interconnecting hole 6d-, the outer side ring 7a-of the outer connecting hole 7-of the side ring outer side ring of outer side ring screwed hole 7b-positions damping layer 12-inner shield ring 13-payload 14-bearing bracket inside the outer side ring of the hole 7c-outer side ring interconnecting hole 8-support ring 8a-support ring inboard aperture 8b-support ring apertura lateralis 11-of outer connecting hole 7d-
Detailed description of the invention
With detailed description of the invention, technical scheme is described in further details below in conjunction with the accompanying drawings.Obviously, described embodiment is only a part of embodiment of the present invention rather than whole embodiments.Based on embodiments of the invention, the every other embodiment that those skilled in the art are obtained under not making creative work premise, broadly fall into the scope of protection of present invention.
As shown in Figures 1 to 8, spacecraft payload impact-reducing device of the present invention includes, top connecting bolt 1, outer back-up ring 2, outside damping layer 3, bottom connecting bolt 5, interior side ring 6, outer side ring 7, support ring 8, inner side damping layer 11, inner shield ring 12.Wherein, interior side ring 6 arranges interior side ring screwed hole 6a, interior side ring location hole 6b, interior side ring interconnecting hole 6c, the outer connecting hole 6d of interior side ring.Outer side ring 7 arranges outer side ring screwed hole 7a, outer side ring location hole 7b, outer side ring interconnecting hole 7c, the outer connecting hole 7d of outer side ring.Support ring 8 arranges support ring inboard aperture 8a, support ring apertura lateralis 8b.
The present invention comprises interior side ring 6, outer side ring 7 and the multiple structure of support ring 8 composition.
Interior side ring 6 is circular ring structure, is positioned at inner side, for providing and the interface of outside bearing bracket, is specifically connected as: bottom connecting bolt 5 is connected with outside bearing bracket by interior side ring location hole 6b.The 6b side of being, hole, interior side ring location bathtub construction, bottom connecting bolt 5 can be the forms such as hexagon-headed bolt, square head bolt, T-slot bolt, when its end is placed in the hole 6b of interior side ring location, the rotation of bottom connecting bolt 5 can be limited, such that it is able to side ring 6 and outside bearing bracket in being connected by external nut.
Outer side ring 7 is circular ring structure, is positioned at outermost, for providing the interface with external payload, is specifically connected as: top connecting bolt 1 is connected with external payload by outer side ring location hole 7b.The outer side ring location hole 7b also side's of being bathtub construction, top connecting bolt 1 can be the forms such as hexagon-headed bolt, square head bolt, T-slot bolt, when its end is placed in the hole 7b of outer side ring location, the rotation of top connecting bolt 1 can be limited, such that it is able to connect outer side ring 7 and external payload by external nut.
Support ring 8 is cirque structure, between interior side ring 6 and outer side ring 7.Support ring 8 is connected by inner side connecting bolt with interior side ring 6, is specially inner side connecting bolt and passes the outer side ring interconnecting hole 7d on outer side ring 7, by support ring inboard aperture 8a in support ring 8, is connected with the interior side ring screwed hole 6a on interior side ring 6 through pad.Support ring 8 is connected by outside connecting bolt with outer side ring 7, is specially outside connecting bolt and passes the outer connecting hole 6d of the interior side ring on interior side ring 6, by the support ring apertura lateralis 8b in support ring 8, is connected with the outer side ring screwed hole 7a on outer side ring 7 through pad.
For increasing the propagation distance of stress wave, in interior side ring 6 is distinguished even circumferential distribution from the inside to the outside, side ring screwed hole 6a and interior side ring location hole 6b, interior side ring screwed hole 6a and interior side ring location hole 6b is interspersed；On outer side ring 7, outside interior, even circumferential is distributed side ring location hole 7b and outer side ring screwed hole 7a respectively, and outer side ring positions hole 7b and outer side ring screwed hole 7a and is interspersed.
Outer back-up ring 2 is circular ring structure, is positioned at the outside of outer side ring 7.Outer back-up ring 2 and outer side ring 7, interior side ring 6, is outside damping layer 3 between support ring 8.Outside damping layer 3 is viscous damping material, can be butyl rubber, phenolic resin or solidification glue.
Inner shield ring 12 is circular ring structure, is positioned at the inner side of side ring 6.Inner shield ring 12 and outer side ring 7, interior side ring 6, is inner side damping layer 11 between support ring 8.Inner side damping layer 11 is viscous damping material, can be butyl rubber, phenolic resin or solidification glue.
As it is shown in figure 9, payload, as a example by analog satellite, quality 50kg, it is positioned at top of the present invention, and is connected by external nut and top connecting bolt 1.Bearing bracket is positioned at bottom the present invention, is connected by external nut and bottom connecting bolt 5.After bearing bracket stands blast impulse, stress wave is transferred to bearing bracket top, and by bottom connecting bolt 5, side ring in the linkage interface of bottom connecting bolt 5 with interior side ring 6 enters.During Gai, stress wave produces refraction, reflection, transmission, and energy has been decayed.Stress wave propagates to inner side connecting bolt enter support ring 8 in interior side ring 6, and the interface that this process is passed through includes the thread interface of inner side connecting bolt and the threaded connection interface of interior side ring 6, interior side ring 6 and the linkage interface of pad, pad and the linkage interface of support ring 8, support ring 8 and inner side connecting bolt.Stress wave propagates to outside connecting bolt in support ring 8, and entering outside ring 7, the interface that this process stress ripple passes through includes support ring 8 and the linkage interface of outside connecting bolt, support ring 8 and the linkage interface of pad, pad and the linkage interface of outer side ring 7, outer side ring 7 and the linkage interface of outside connecting bolt.Stress wave propagates to top connecting bolt 1 after entering outer side ring 7, and enter this analog satellite, during this, stress wave have passed through outer side ring 7 and the linkage interface of top connecting bolt 1, outer side ring 7 and the linkage interface of the linkage interface of outer spacer, outer spacer and the linkage interface of this analog satellite, this analog satellite and top connecting bolt 1.
In distinguishing even circumferential distribution on interior side ring 6 from the inside to the outside, side ring screwed hole 6a and interior side ring location hole 6b, interior side ring screwed hole 6a and interior side ring location hole 6b is interspersed；On outer side ring 7, outside interior, even circumferential is distributed side ring location hole 7b and outer side ring screwed hole 7a respectively, and outer side ring positions hole 7b and outer side ring screwed hole 7a and is interspersed.This form being interspersed adds the stress wave propagation distance in longitudinal direction, adds the energy attenuation of stress wave.
Under shock wave, between this analog satellite and bearing bracket, produce displacement so that between interior side ring 6, support ring 7, support ring 8, produce displacement.This displacement will cause the relative changing of the relative positions between interior side ring 6, support ring 7, support ring 8 with outer back-up ring 2, cause the deformation of outside damping layer 3, and the alternate of relative displacement brings the staggered deformation of outside damping layer 3, largely on reduce the energy of stress wave.Equally, interior side ring 6, support ring 7, support ring 8 with between inner shield ring 12 also by the relative changing of the relative positions, cause the alternately deformation of inner side damping layer 11.
Finally, the stress wave of the less energy after overdamping enters this analog satellite.Through the stress wave energy greater attenuation of the present invention, crude shock signal acceleration peak-peak is 1500g, and after impact-reducing of the present invention, system acceleration peak value of response is 107.5g, and decayed 23dB, serves this analog satellite of protection and the effect of critical component thereof.
Described above to the disclosed embodiments, makes professional and technical personnel in the field be capable of or uses the present invention.Multiple amendment to these embodiments is apparent from for the patented technology personnel of this area, and generic principles defined herein can realize without departing from the present invention in other embodiments.Therefore, the present invention is not intended to be limited to the embodiments shown herein, and is to fit to the widest range consistent with principles disclosed herein and features of novelty.
Claims (7)
1. a spacecraft payload impact-reducing device, it is characterised in that include interior side ring, support ring and outer side ring successively；Distinguishing side ring screwed hole and hole, interior side ring location in even circumferential distribution on interior side ring from the inside to the outside, interior side ring screwed hole and hole, interior side ring location are interspersed；Distinguishing even circumferential on outer side ring from the inside to the outside and be distributed outer side ring hole, location and outer side ring screwed hole, outer side ring hole, location and outer side ring screwed hole are interspersed；Support ring distinguishes even circumferential distribution support ring inboard aperture and support ring apertura lateralis from the inside to the outside；Support ring is fixing with interior side ring to be connected, and support ring is fixing with outer side ring to be connected.
Spacecraft payload impact-reducing device the most according to claim 1, it is characterized in that, also include inner shield ring and outer back-up ring, inner shield ring is inside interior side ring, it is inner side damping layer between inner shield ring and outer side ring, support ring, interior side ring, outside outer back-up ring side ring outside, it is outside damping layer between outer back-up ring and outer side ring, support ring, interior side ring.
Spacecraft payload impact-reducing device the most according to claim 1 and 2, it is characterised in that described interior side ring, support ring, outer side ring, inner shield ring, outer back-up ring are circular ring structure.
Spacecraft payload impact-reducing device the most according to claim 3, it is characterized in that, described interior side ring hole, location and outer side ring location Kong Weifang trench structure, hole, interior side ring location includes interior side ring interconnecting hole and the outer connecting hole of interior side ring, interior side ring is connected by interior side ring interconnecting hole is fixing with outside bearing bracket, and interior side ring is fixed with support ring be connected by the outer connecting hole of interior side ring and support ring apertura lateralis；Hole, outer side ring location includes the outer connecting hole of outer side ring and outer side ring interconnecting hole, and outer side ring is connected by the outer connecting hole of outer side ring is fixing with external payload, and outer side ring is connected by outer side ring interconnecting hole and support ring inboard aperture are fixing with support ring.
Spacecraft payload impact-reducing device the most according to claim 4, it is characterized in that, described interior side ring is connected by bottom connecting bolt with outside bearing bracket, outer side ring is connected by top connecting bolt with external payload, and bottom connecting bolt and top connecting bolt are hexagon-headed bolt, square head bolt, T-slot bolt.
Spacecraft payload impact-reducing device the most according to claim 1 and 2, it is characterised in that described inner side damping layer and outside damping layer are viscous damping material.
Spacecraft payload impact-reducing device the most according to claim 6, it is characterised in that described inner side damping layer is butyl rubber or phenolic resin or solidifies glue, described outside damping layer is butyl rubber or phenolic resin or solidifies glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521040131.9U CN205418145U (en) | 2015-12-11 | 2015-12-11 | Spacecraft payload subtracts impact device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521040131.9U CN205418145U (en) | 2015-12-11 | 2015-12-11 | Spacecraft payload subtracts impact device |
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| CN205418145U true CN205418145U (en) | 2016-08-03 |
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| CN201521040131.9U Active CN205418145U (en) | 2015-12-11 | 2015-12-11 | Spacecraft payload subtracts impact device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106864775A (en) * | 2015-12-11 | 2017-06-20 | 天津航天瑞莱科技有限公司 | A kind of spacecraft payload impact-reducing device |
| CN110143296A (en) * | 2019-04-11 | 2019-08-20 | 上海卫星工程研究所 | Supporting structure is rushed suitable for subtracting for the smaller single machine of heat conduction amount demand on spacecraft |
-
2015
- 2015-12-11 CN CN201521040131.9U patent/CN205418145U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106864775A (en) * | 2015-12-11 | 2017-06-20 | 天津航天瑞莱科技有限公司 | A kind of spacecraft payload impact-reducing device |
| CN110143296A (en) * | 2019-04-11 | 2019-08-20 | 上海卫星工程研究所 | Supporting structure is rushed suitable for subtracting for the smaller single machine of heat conduction amount demand on spacecraft |
| CN110143296B (en) * | 2019-04-11 | 2020-11-24 | 上海卫星工程研究所 | Reduce towards supporting structure suitable for less unit of heat conduction quantity demand on spacecraft |
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