CN106864775A - A kind of spacecraft payload impact-reducing device - Google Patents
A kind of spacecraft payload impact-reducing device Download PDFInfo
- Publication number
- CN106864775A CN106864775A CN201510924831.2A CN201510924831A CN106864775A CN 106864775 A CN106864775 A CN 106864775A CN 201510924831 A CN201510924831 A CN 201510924831A CN 106864775 A CN106864775 A CN 106864775A
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- ring
- side ring
- outer side
- interior side
- interior
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- 238000009826 distribution Methods 0.000 claims abstract description 12
- 238000013016 damping Methods 0.000 claims description 31
- 239000000463 material Substances 0.000 claims description 11
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 4
- 229920005549 butyl rubber Polymers 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims description 4
- 229920001568 phenolic resin Polymers 0.000 claims description 4
- 239000005011 phenolic resin Substances 0.000 claims description 4
- 238000007711 solidification Methods 0.000 claims description 4
- 230000008023 solidification Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 9
- 238000000926 separation method Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 6
- 238000010276 construction Methods 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000002360 explosive Substances 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a kind of spacecraft payload impact-reducing device, it is characterised in that successively including interior side ring, support ring and outer side ring；Side ring screwed hole and interior side ring location hole in even circumferential distribution are distinguished on interior side ring from the inside to the outside, interior side ring screwed hole and interior side ring location hole are interspersed；On outer side ring outside interior even circumferential distribution outer side ring location hole and outer side ring screwed hole respectively, outer side ring location hole and outer side ring screwed hole are interspersed；Support ring even circumferential distribution support ring inboard aperture and support ring apertura lateralis respectively outside interior；Support ring is fixedly connected with interior side ring, and support ring is fixedly connected with outer side ring.Present apparatus small volume, simple structure, strong operability can meet the impact-reducing demand of payload in spacecraft, it is possible to as the impact-reducing measure of other equipment.
Description
Technical field
Slow down technical field the present invention relates to impact, and in particular to a kind of spacecraft payload impact-reducing device.
Background technology
In space industry, payload (satellite, airship etc.) is delivered by rocket and gone up to the air, in payload and Separation process
In, impact is the more harsh mechanical environment that spacecraft is experienced.The shock environment that payload is undergone is mainly by various
What Fire load was operationally produced, the unblock during such as the satellite and the rocket are separated, satellite bay section is separated, expandable part launches on star.
The energy release that these processes trigger due to blasting bolt blast, and then produce the adverse circumstances of blast impulse.Although relative to whole
Individual emission process is more of short duration, but influence of the impact to payload can not be ignored.
Blast impulse except there is plastic deformation outer near explosive source, relatively large bullet (arrow) body structure only transfer elastic ripple, and in itself
It is difficult to be influenceed (except slim-lined construction, frivolous structure and fragile material structure) by Explosive separation impact.But, Explosive separation punching
Generation material stress ripple is hit, appearance and size can be made to produce very high-frequency response with the miniature electronic chip of magnitude with wavelength, from
And electronic equipment and micromechanical devices are produced with harm, particularly to electronic product, frivolous structure, fragile material destruction
It is particularly evident.
For Process of Piggyback Satellite structure, the influence of the stress wave that is hit in separation process makes Process of Piggyback Satellite and final vehicle except longitudinal fortune
Outside dynamic, the traversing of respective barycenter and the rotation around respective barycenter are also produced, so as to cause angle and angular speed to change, very
To cause collision.Even if the satellite and the rocket complete to separate, if Process of Piggyback Satellite can not smoothly depart from adapter, cannot also be entered with correct attitude
Enter planned orbit.It can be seen that, in satellite and the rocket separation process, take necessary impact-reducing measure very necessary.
The present invention provides a kind of spacecraft payload impact-reducing device, is transmitted with the Shock stress Wave reduced to payload, this
Invention includes three-decker from the inside to the outside, there is provided multiple stress wave transmission interfaces, and viscous damping material is devised, with maximum
The energy transmission of degree decay stress ripple.
The principle of device is simple, can be used as the impact-reducing measure in spacecraft or other shock environments using equipment.
The content of the invention
The present invention is influenceed in separation process for payload in spacecraft by blast impulse, there is provided a kind of spacecraft is effective
Load impact-reducing device.The device is located between payload and supporting support, reduces the blast impulse of support to payload
Propagate.
A kind of spacecraft payload impact-reducing device that the present invention is provided, successively including interior side ring, support ring and outer side ring；It is interior
Side ring screwed hole and interior side ring location hole in even circumferential distribution are distinguished on side ring from the inside to the outside, interior side ring screwed hole and interior side ring are fixed
Position hole is interspersed；On outer side ring outside interior even circumferential distribution outer side ring location hole and outer side ring screwed hole, outer side ring respectively
Location hole and outer side ring screwed hole are interspersed；Support ring even circumferential distribution support ring inboard aperture and support ring respectively outside interior
Apertura lateralis；Support ring is fixedly connected with interior side ring, and support ring is fixedly connected with outer side ring.
Described spacecraft payload impact-reducing device, also including inner shield ring and outer back-up ring, inner shield ring is interior inside interior side ring
Be inner side damping layer between back-up ring and outer side ring, support ring, interior side ring, outer back-up ring outside outer side ring, outer back-up ring and outer side ring,
It is outside damping layer between support ring, interior side ring.
The interior side ring, support ring, outer side ring, inner shield ring, outer back-up ring are circular ring structure.
The interior side ring location hole and outer side ring location hole are square trench structure, interior side ring location hole include interior side ring interconnecting hole and
The outer connecting hole of interior side ring, interior side ring is fixedly connected by interior side ring interconnecting hole with outside bearing bracket, and interior side ring leads to support ring
The outer connecting hole of interior side ring is crossed to be fixedly connected with support ring apertura lateralis；Outer side ring location hole is included in outer side ring outer connecting hole and outer side ring
Connecting hole, outer side ring is fixedly connected by the outer connecting hole of outer side ring with external payload, and outer side ring passes through outer side ring with support ring
Interconnecting hole is fixedly connected with support ring inboard aperture.
Further, the interior side ring is connected with outside bearing bracket by bottom connecting bolt, outer side ring and external payload
Connected by top connecting bolt, bottom connecting bolt and top connecting bolt are hexagon-headed bolt, square head bolt, T-slot use
Bolt.
The inner side damping layer and outside damping layer are viscous damping material.
Further, the inner side damping layer and outside damping layer are butyl rubber, phenolic resin, solidification glue.
Beneficial effects of the present invention are as follows：
Be interspersed for connecting bolt using inside and outside hierachical structure by the present invention, to increase stress fluctuation propagation path.This hair
It is bright to also set up interior outside viscous damping layer, and using back-up ring constraint.When being impacted, damping layer can be produced as matrix is strained
Deformation, material internal produces alternation tension and compression stress and strain.According to the Energy Dissipation Mechanism of damping material, when material produce alternate stress,
Structural impact energy can be lost during strain, so as to produce the effect of impact-reducing.The structures such as internal-flange bolt of the present invention, increase stress wave
Transmissive interface, farthest reduce to payload shock wave transmit.Top connecting bolt of the invention is effectively carried with connecting
Lotus, bottom connecting bolt connection supporting support, the location structure of connecting bolt prevents the rotation in screwing process, makes company
Termination process is simply easily operated.
Small volume of the present invention, simple structure, strong operability can meet the impact-reducing demand of payload in spacecraft, and can
As the impact-reducing measure of other equipment.
Brief description of the drawings
Fig. 1 is spacecraft payload impact-reducing device front view；
Fig. 2 is spacecraft payload impact-reducing device top view；
Fig. 3 is interior side ring front view of the invention；
Fig. 4 is interior side ring top view of the invention；
Fig. 5 is outer side ring bottom view of the invention；
Fig. 6 is outer side ring front view of the invention；
Fig. 7 is support ring front view of the invention；
Fig. 8 is support ring top view of the invention；
Fig. 9 is embodiments of the invention schematic diagram.
Side ring screwed hole in side ring 6a- in damping layer 5- bottoms connecting bolt 6- on the outside of the outer back-up ring 3- of 1- tops connecting bolt 2-
Outer side ring screwed hole 7b- of the outer side ring 7a- of the outer connecting hole 7- of side ring in side ring interconnecting hole 6d- in side ring location hole 6c- in 6b-
The outer side ring interconnecting hole 8- support ring 8a- support ring inboard aperture 8b- branch of the outer connecting hole 7d- of the outer side rings of outer side ring location hole 7c-
Pushing out ring apertura lateralis 11- inner sides damping layer 12- inner shield ring 13- payload 14- bearing brackets
Specific embodiment
Technical scheme is described in further details with reference to the accompanying drawings and detailed description.Obviously, it is described
Embodiment is only a part of embodiment of the invention, rather than whole embodiments.Based on embodiments of the invention, this area
The every other embodiment that technical staff is obtained under the premise of creative work is not made, belongs to claimed
Scope.
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 sets interior side ring screwed hole 6a, interior side ring location hole 6b, interior side ring interconnecting hole 6c, interior side ring
Outer connecting hole 6d.Outer side ring 7 sets outer side ring screwed hole 7a, outer side ring location hole 7b, outer side ring interconnecting hole 7c, outside
The outer connecting hole 7d of ring.Support ring 8 sets support ring inboard aperture 8a, support ring apertura lateralis 8b.
Sandwich construction of the present invention comprising interior side ring 6, outer side ring 7 and support ring 8 composition.
Interior side ring 6 is circular ring structure, positioned at most inner side, for providing the interface with outside bearing bracket, is specifically connected as：Bottom
Portion's connecting bolt 5 is connected by interior side ring location hole 6b with outside bearing bracket.Interior side ring location hole 6b is square bathtub construction,
Bottom connecting bolt 5 can be the forms such as hexagon-headed bolt, square head bolt, T-slot bolt, and its end is placed in interior side ring and determines
When in the hole 6b of position, the rotation of bottom connecting bolt 5 can be limited, be held such that it is able to pass through side ring 6 and outside in external nut connection
Power support.
Outer side ring 7 is circular ring structure, positioned at outermost, for providing the interface with external payload, is specifically connected as：Top
Portion's connecting bolt 1 is connected by outer side ring location hole 7b with external payload.Outer side ring location hole 7b is also square bathtub construction,
Top connecting bolt 1 can be the forms such as hexagon-headed bolt, square head bolt, T-slot bolt, and its end is placed in outer side ring and determines
When in the hole 7b of position, the rotation of top connecting bolt 1 can be limited, had such that it is able to pass through the outer side ring 7 of external nut connection and outside
Effect load.
Support ring 8 is cirque structure, between interior side ring 6 and outer side ring 7.Support ring 8 passes through inner side with interior side ring 6
Connecting bolt is connected, and specially inner side connecting bolt passes through the outer side ring interconnecting hole 7d on outer side ring 7, by support ring 8
Support ring inboard aperture 8a, be connected with the interior side ring screwed hole 6a on interior side ring 6 by pad.Support ring 8 and outer side ring 7
Connected by outside connecting bolt, specially outside connecting bolt passes through the outer connecting hole 6d of the interior side ring on interior side ring 6, by branch
Support ring apertura lateralis 8b on pushing out ring 8, is connected by pad with the outer side ring screwed hole 7a on outer side ring 7.
It is the propagation distance for increasing stress wave, distinguishes side ring screwed hole 6a and interior in even circumferential distribution on interior side ring 6 from the inside to the outside
Side ring location hole 6b, interior side ring screwed hole 6a and interior side ring location hole 6b are interspersed；Justify respectively outside interior on outer side ring 7
It is uniformly distributed outer side ring location hole 7b and outer side ring screwed hole 7a, outer side ring location hole 7b week and outer side ring screwed hole 7a interlocks
Distribution.
Outer back-up ring 2 is circular ring structure, positioned at the outside of outer side ring 7.Outer back-up ring 2 and outer side ring 7, interior side ring 6, support ring 8
Between be outside damping layer 3.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, positioned at the inner side of interior side ring 6.Inner shield ring 12 and outer side ring 7, interior side ring 6, support ring
It is inner side damping layer 11 between 8.Inner side damping layer 11 is viscous damping material, can be butyl rubber, phenolic resin or solidification
Glue.
As shown in figure 9, payload, by taking analog satellite as an example, quality 50kg, positioned at present invention top, and by external spiral shell
Female and top connecting bolt 1 is connected.Bearing bracket is located at bottom of the present invention, is connected by external nut and bottom connecting bolt 5.
After bearing bracket undergoes blast impulse, stress wave is transferred to bearing bracket top, and by bottom connecting bolt 5, connects through bottom
Connecting bolt 5 enters interior side ring with the linkage interface of interior side ring 6.During being somebody's turn to do, stress wave produces refraction, reflection, transmission, energy
Amount has decayed.Stress wave propagates to inner side connecting bolt in interior side ring 6 and enters support ring 8, the interface that the process passes through
The linkage interface of threaded connection interface, interior side ring 6 including inner side connecting bolt and interior side ring 6 and pad, pad and support ring
The thread interface of 8 linkage interface, support ring 8 and inner side connecting bolt.Stress wave propagates to outside connection in support ring 8
Bolt, and enter outside ring 7, linkage interface of the interface that the process stress ripple passes through including support ring 8 and outside connecting bolt,
The connection of the linkage interface of the linkage interface of support ring 8 and pad, pad and outer side ring 7, outer side ring 7 and outside connecting bolt
Interface.Stress wave enters the analog satellite into propagating to top connecting bolt 1 after outer side ring 7, during this, should
Reeb have passed through linkage interface, the outside of outer side ring 7 and the linkage interface, outer side ring 7 and outer spacer of top connecting bolt 1
The linkage interface of the linkage interface, the analog satellite and top connecting bolt 1 of pad and the analog satellite.
Side ring screwed hole 6a and interior side ring location hole 6b, interior side ring spiral shell in even circumferential distribution are distinguished on interior side ring 6 from the inside to the outside
Pit 6a and interior side ring location hole 6b are interspersed；Even circumferential is distributed outer side ring location hole respectively outside interior on outer side ring 7
7b and outer side ring screwed hole 7a, outer side ring location hole 7b and outer side ring screwed hole 7a are interspersed.The form that this is interspersed increases
Add stress wave in the propagation distance of longitudinal direction, increased the energy attenuation of stress wave.
Under shock wave, displacement is produced between the analog satellite and bearing bracket so that interior side ring 6, support ring 7, support ring
Displacement is produced between 8.The displacement will cause interior side ring 6, support ring 7, support ring 8 and the relative changing of the relative positions between outer back-up ring 2, cause
The deformation of outside damping layer 3, and the change of the alternating of relative displacement brings the staggeredly deformation of outside damping layer 3, largely drops
The low energy of stress wave.Equally, interior side ring 6, support ring 7, support ring 8 with, also by the relative changing of the relative positions, led between inner shield ring 12
Cause the alternating deformation of inner side damping layer 11.
Finally, the analog satellite is entered through the stress wave of the smaller energy after overdamping.It is larger by stress wave energy of the invention
Decay, crude shock signal acceleration peak-peak is 1500g, and system acceleration peak value of response is after impact-reducing of the present invention
107.5g, decayed 23dB, serves the effect for protecting the analog satellite and its critical component.
The foregoing description of the disclosed embodiments, enables professional and technical personnel in the field to realize or uses the present invention.To these
Various modifications of embodiment are it will be apparent that generic principles defined herein can for the patented technology personnel of this area
Without departing from the present invention, to realize in other embodiments.Therefore, the present invention is not intended to be limited to herein
These shown embodiments, and it is to fit to the widest range consistent with principles disclosed herein and features of novelty.
Claims (7)
1. a kind of spacecraft payload impact-reducing device, it is characterised in that successively including interior side ring, support ring and outer side ring；
Side ring screwed hole and interior side ring location hole, interior side ring screwed hole and interior side ring in even circumferential distribution are distinguished on interior side ring from the inside to the outside
Location hole is interspersed；On outer side ring outside interior even circumferential distribution outer side ring location hole and outer side ring screwed hole, outside respectively
Ring location hole and outer side ring screwed hole are interspersed；Support ring even circumferential distribution support ring inboard aperture and support respectively outside interior
Ring apertura lateralis；Support ring is fixedly connected with interior side ring, and support ring is fixedly connected with outer side ring.
2. spacecraft payload impact-reducing device according to claim 1, it is characterised in that also including inner shield ring and outer
Back-up ring, inner shield ring is inner side damping layer, outer back-up ring inside interior side ring, between inner shield ring and outer side ring, support ring, interior side ring
It is outside damping layer outside outer side ring, between outer back-up ring and outer side ring, support ring, interior side ring.
3. spacecraft payload impact-reducing device according to claim 1 and 2, it is characterised in that the interior side ring,
Support ring, outer side ring, inner shield ring, outer back-up ring are circular ring structure.
4. spacecraft payload impact-reducing device according to claim 3, it is characterised in that the interior side ring location hole
It is square trench structure with outer side ring location hole, interior side ring location hole includes interior side ring interconnecting hole and the outer connecting hole of interior side ring, inner side
Ring is fixedly connected by interior side ring interconnecting hole with outside bearing bracket, and interior side ring is with support ring by the outer connecting hole of interior side ring and branch
Pushing out ring apertura lateralis is fixedly connected；Outer side ring location hole includes the outer connecting hole of outer side ring and outer side ring interconnecting hole, and outer side ring is by outer
The outer connecting hole of side ring is fixedly connected with external payload, and outer side ring is with support ring by outer side ring interconnecting hole and support ring inner side
Hole is fixedly connected.
5. spacecraft payload impact-reducing device according to claim 4, it is characterised in that the interior side ring with it is outside
Bearing bracket is connected by bottom connecting bolt, and outer side ring is connected with external payload by top connecting bolt, bottom connection
Bolt and top connecting bolt are hexagon-headed bolt, square head bolt, T-slot bolt.
6. spacecraft payload impact-reducing device according to claim 1 and 2, it is characterised in that the inner side damping
Layer and outside damping layer are viscous damping material.
7. spacecraft payload impact-reducing device according to claim 6, it is characterised in that the inner side damping layer and
Outside damping layer is butyl rubber, phenolic resin, solidification glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510924831.2A CN106864775A (en) | 2015-12-11 | 2015-12-11 | A kind of spacecraft payload impact-reducing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510924831.2A CN106864775A (en) | 2015-12-11 | 2015-12-11 | A kind of spacecraft payload impact-reducing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106864775A true CN106864775A (en) | 2017-06-20 |
Family
ID=59177550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510924831.2A Pending CN106864775A (en) | 2015-12-11 | 2015-12-11 | A kind of spacecraft payload impact-reducing device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110285176A (en) * | 2019-07-19 | 2019-09-27 | 厦门大学 | Firer based on anti-wavelength characteristic separates drop percussion mechanism and its preparation process |
| CN112706948A (en) * | 2021-03-26 | 2021-04-27 | 北京中科宇航技术有限公司 | Inertial measurement unit support and inertial measurement unit assembly |
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| US5878980A (en) * | 1997-02-05 | 1999-03-09 | Hughes Electronics Corporation | Attenuation ring |
| CN1253898A (en) * | 1998-11-18 | 2000-05-24 | 建筑航空股份有限公司 | System for changing rigidity and damping property of structural connecting piece |
| US6202961B1 (en) * | 2000-03-21 | 2001-03-20 | Csa Engineering | Passive, multi-axis, highly damped, shock isolation mounts for spacecraft |
| US20020109277A1 (en) * | 2001-02-09 | 2002-08-15 | Stewart Correll | Shock and vibration absorption system |
| CN101392808A (en) * | 2008-10-17 | 2009-03-25 | 华中科技大学 | Vibration isolator for space precision electronic equipment |
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| CN205418145U (en) * | 2015-12-11 | 2016-08-03 | 天津航天瑞莱科技有限公司 | Spacecraft payload subtracts impact device |
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|---|---|---|---|---|
| US5878980A (en) * | 1997-02-05 | 1999-03-09 | Hughes Electronics Corporation | Attenuation ring |
| CN1253898A (en) * | 1998-11-18 | 2000-05-24 | 建筑航空股份有限公司 | System for changing rigidity and damping property of structural connecting piece |
| US6202961B1 (en) * | 2000-03-21 | 2001-03-20 | Csa Engineering | Passive, multi-axis, highly damped, shock isolation mounts for spacecraft |
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| CN110285176A (en) * | 2019-07-19 | 2019-09-27 | 厦门大学 | Firer based on anti-wavelength characteristic separates drop percussion mechanism and its preparation process |
| CN112706948A (en) * | 2021-03-26 | 2021-04-27 | 北京中科宇航技术有限公司 | Inertial measurement unit support and inertial measurement unit assembly |
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Application publication date: 20170620 |