CN206187366U - A vacuum seal device for compensating skew of optical devices precision - Google Patents
A vacuum seal device for compensating skew of optical devices precision Download PDFInfo
- Publication number
- CN206187366U CN206187366U CN201621073874.0U CN201621073874U CN206187366U CN 206187366 U CN206187366 U CN 206187366U CN 201621073874 U CN201621073874 U CN 201621073874U CN 206187366 U CN206187366 U CN 206187366U
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- Prior art keywords
- connecting cylinder
- elastic
- sealed compartment
- outside
- optical devices
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Abstract
The utility model relates to a spacecraft or the manned lunar module of optics equipment accuracy and sealed dual installation requirement, concretely relates to vacuum seal device. A vacuum seal device for compensating skew of optical devices precision, it includes: mounting base, elastic compensation ware and sealed cowling, the mounting base divide into connecting cylinder A, connecting cylinder B, connecting cylinder B's main aspects are used for installing infrared earth sensor, and tip and the butt joint of connecting cylinder A are equipped with nonmetal heat insulating mattress in butt joint department, the elastic compensation ware cup joints in connecting cylinder A's outside, carries out elastic adjusted along with the under -deck pressure oscillation, be equipped with an anti external pressure unstability steel ring inside every layer of elastic compensation ware and between the connecting cylinder A outer wall, the sealed cowling is the throat tubular structure that the big one end of one end is little, and its lateral wall is equipped with mounting flange, the sealed cowling cup joints the outside at connecting cylinder B to be connected boss sealing connection through its tip and connecting cylinder A one end. The utility model discloses the installation problem that no rectification was covered with infrared earth sensor outside the sealed satellite cabin that requires has been solved smoothly.
Description
Technical field
The utility model is related to spacecraft or manned moon landing cabin with optical device precision and the dual installation requirement of sealing,
Specifically related to a kind of vacuum sealing device.
Background technology
Put into practice No. ten scientific experiment satellites and be used exclusively for the research of " Microgravity Science and space life science " Space Experiments
Retrievable satellite, obtaining attitude of satellite information using two infrared earth sensors carries out in-orbit attitude seizure and control.It is red
Outer earth sensor is to widely use indispensable photo electricity collimation theodolite in spacecraft attitude control system, to required precision
Height, its deviation general control could meet the accurate requirement of gesture stability in percent magnitude once, and except infrared earth
Outside sensor itself precision, for the precision that sensor provides the device of installation pedestal is also that satellite is achieved attitude and is precisely controlled
One of key factor.For most of low orbits without seal request or high orbit satellite such as remote sensing satellite, landsat etc.,
Infrared earth sensor is arranged on structural slab, cast aside when radome fairing, satellier injection after, the operating position of sensor is directly open
Exposed to the outer space, working environment is not disturbed by load such as lock pressure changes, is readily available good precision.And put into practice No. ten and defend
The infrared earth sensor of star is mounted in the sealed compartment of seal request out of my cabin, then need to consider following key point：One
It is due to putting into practice during No. ten satellite launchs without radome fairing, being launched as bullet by celestial body outer surface, need to ensure outside satellite
Surface as far as possible without protrusion, therefore need to the side wall of sealed compartment for infrared earth sensor is designed single recessed cabin, Ji Nengwei
Sensor provides a reliable installation pedestal, can isolate with sealed compartment indoor environment again, it is ensured that sensor is exposed to after installing
Vacuum environment, and the sealing property of sealed compartment is not influenceed；Two when being in-orbit sealed compartment inside leave it is big necessary to model task
Atmospheric pressure, and in cabin the temperature alternating hot and cold of gas can make lock pressure produce fluctuating change, cause thin-walled skin structure bulkhead and
Recessed cabin expands or contraction distortion with air pressure fluctuation, influences infrared earth sensor operating accuracy.Therefore need design a kind of
Device, can realize the seal isolation with sealed compartment, it is ensured that the reliable sealing of sealed compartment, can be provided for infrared earth sensor again
Firm installing matrix, moreover it is possible to eliminate the precision offset that lock pressure change brings.
The content of the invention
The purpose of this utility model is：A kind of vacuum sealing device is provided, in-orbit seal request can be met, and can eliminate
Lock pressure change can caused optical accuracy skew.
The technical solution of the utility model is：A kind of vacuum sealing device for compensating Optical devices precision offset, it
Including：Installation pedestal, elastic compensator and seal closure；
Installation pedestal is made up of bolted connecting cylinder A, connecting cylinder B；Connecting cylinder A is provided with the circle of connection boss for two ends
Barrel structure, connecting cylinder B is the ladder barrel structure that three-level is shunk；The maximum end of connecting cylinder B is used to install infrared earth sensor,
Smallest end is used to be docked with connecting cylinder A, and nonmetallic heat insulating mattress is provided with joint；
Elastic compensator uses elastomeric material, with sandwich construction, elastic adjustment is carried out with pressure oscillation in cabin；Elasticity is mended
The outside that device is socketed in connecting cylinder A is repaid, the connection boss with connecting cylinder A two ends is tightly connected；Every layer of elastic compensator inside with
A critical external compressive resistance unstability steel ring is provided between connecting cylinder A outer walls；
Seal closure is the small necking tubular structure in the big one end in one end, and its side wall is provided with mounting flange；Seal closure is socketed in company
The outside of a B is connect, and is tightly connected with the connection boss of connecting cylinder A one end by its small end.
Another technical scheme of the present utility model is：A kind of vacuum sealing for compensating Optical devices precision offset is filled
The installation method put, it is based on a kind of vacuum sealing device for compensating Optical devices precision offset as described above, including
Following steps：
A. seal closure is welded on the default covering flange of sealed compartment bulkhead, by X-ray check and weld joint air-tight inspection,
Ensure that satisfaction uses level weld seam requirement；
B. connecting cylinder A is connected in place out of my cabin with the girder of sealed compartment；Elastic compensator set is attached on connecting cylinder A
It is attached, and critical external compressive resistance unstability steel ring is set, is needed before connection to contact surface purified treatment to ensure sealing；
C. the part of installation in step B is carried out into the assembling in sealed compartment；
D. elastic compensator and seal closure are adjusted and is connected, is needed before connection to contact surface purified treatment to ensure sealing；
E. connecting cylinder B is put into from the open window of sealed compartment bulkhead, and is connected with connecting cylinder A, junction is provided with non-
Metallic insulation pad；
F. infrared earth sensor is put into from the open window of sealed compartment bulkhead, and is installed on connecting cylinder B.
Beneficial effect：(1) the utility model realizes the isolation of extravehicular environment in cabin using seal closure, by means of elastic compensating
Device realizes the sealing of sealed compartment and deformation-compensated function, and the installation of equipment and compensator is realized using installation pedestal, smoothly solves
The installation question of the satellite of seal request infrared earth sensor out of my cabin is covered with without rectification；
(2) elastic compensator is effectively guaranteed this work essence for having high-precision requirement equipment of infrared earth sensor
Degree.Accuracy test before satellite launch before and after ground has carried out sealed compartment nacelle pressurising, the axis precision of sensor is in lock pressure
Variable quantity is controlled in the range of 0.7 '~1.7 ' all the time in two extreme positions of change are interval, meets the normal work of sensor
Make index request, and be much better than the measured precision on sealed compartment after other nonelastic compensator equipment installations.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is scheme of installation of the utility model in sealed compartment.
Specific embodiment
Embodiment 1, a kind of vacuum sealing device for compensating Optical devices precision offset, it includes：Installation pedestal 1,
Elastic compensator 2 and seal closure 3；
Installation pedestal 1 is made up of the connecting cylinder A1-1 and connecting cylinder B1-2 connected by bolt 7；Connecting cylinder A1-1 is two ends
The cylindrical structure of connection boss is provided with, connecting cylinder B1-2 is the ladder barrel structure that three-level is shunk；The maximum end of connecting cylinder B1-2
For installing infrared earth sensor 12, smallest end is used to be docked with connecting cylinder A1-1；The maximum of connecting cylinder A1-1 is outer in this example
Footpath Ф 160mm, match with the maximum outside diameter position of elastic compensator 2；Connecting cylinder A1-1 minimum outer diameter Ф 100mm, with connecting cylinder
B1-2 matches.One end of connecting cylinder A1-1 is connected by connector 4 with girder 9, and the other end is by bolt 7 and connecting cylinder B1-2
It is connected；Because connecting cylinder A1-1 needs to adapt to the connection with girder 9 and connection and the company of connecting cylinder B1-2 of elastic compensator 2
Connect, therefore in addition to the annexation between coordination and three, also need load according to aerial mission phase difference operating mode to part from
The intensity and toughness and bonding strength of body are checked, to determine part basic parameter and tie point quantity.Connecting cylinder B1-2 is most
Small external diameter Ф 100mm, for matching with connecting cylinder A1-1, maximum outside diameter Ф 244mm, to meet infrared earth sensor 12
Installation requirement.Installation pedestal 1 is installed as cantilever design in sealed compartment 10, and infrared earth sensor 12 is arranged on cantilever most
Distal end.Additionally due to the infrared earth sensor put into practice used by No. ten has strict thermal control requirement, the height of gas temperature in cabin
Warm alternation can influence imaging precision, therefore carry out hot biography using nonmetallic heat insulating mattress between connecting cylinder A1-1, connecting cylinder B1-2
The isolation passed.
Elastic compensator 2, as main material, with sandwich construction, elasticity is carried out with pressure oscillation in cabin from nitrile rubber
Adjustment, at the same to meet put into practice No. ten in-orbit space environments of satellite the need for and ensure the reliable sealing of nacelle；Elastic compensator 2
The outside of connecting cylinder A1-1 is socketed in, the connection boss with connecting cylinder A1-1 two ends is tightly connected, the connection boss spacing at two ends
The length dimension of elastic compensator 2 is determined, and then determines the number of plies of elastic compensator 2；In this example, elastic compensator 2
Overall length is 119mm, minimum diameter Ф 120mm, and maximum outside diameter (flange) Ф 160mm, wall thickness is not less than 1.3mm, 6 layers of the number of plies.By
By the external pressure applied from the atmospheric pressure inside sealed compartment when compensator operation on orbit, pressure outside can produce unstability,
Therefore 6 critical external compressive resistance unstability steel ring 2-1 are provided between every layer of inside of elastic compensator 2 and connecting cylinder A1-1 outer walls.
Seal closure 3 is tubular structure of the one end with necking, needs to be welded with cable according to task on its outer circumference surface and wears
The mounting flange 3-1 of cabin socket, ensures sealing using sealing ring between mounting flange 3-1 and seal closure 3；Seal closure 3 is socketed
In the outside of connecting cylinder B1-2, and it is tightly connected with the connection boss of connecting cylinder A1-1 one end by its necking end；It is close in this example
Sealing cover 3 uses 2.5mm thickness 5A06 aluminium sheet roll bending welding formings, external diameter Ф 285mm, for being turned over sealed compartment side wall covering is reserved
It is lateral opening to carry out butt welding, for meeting the Installation And Test space of infrared earth sensor 12, and leave enough observation visuals field；It is close
The necking end external diameter Ф 160mm of sealing cover 3, for being connected with elastic compensator 2, under the premise of structural strength rigidity Design principle is met
Miniaturization Design as far as possible, it is therefore an objective to reduce the sealing part size between seal closure and nacelle, improves sealing reliability.It is whole close
Sealing cover 3 is isolated with sealing cabin, and its inner space is directly external vacuum environment, by means of weld seam and the rubber material of compensator
Matter realizes the sealing between seal closure and sealed compartment.
Seal closure 3 is used as self-existent recessed cabin, its outer surface during whole flight test on the side wall of sealed compartment 10
The external pressure from the internal pressure power effect of sealed compartment cabin can be subject to, therefore external pressure strength check must be carried out after the completion of the design of seal closure 3,
And carry out the water pressure test by water filling in the cabin of sealed compartment 10, received in the inner surface dedicated ground monitoring of tools cover body of seal closure 3
STRESS VARIATION and deformation after power.The configuration and thickness of seal closure 3 used by this example can be used to bear outside 0.5~1 atmospheric pressure
Pressure operating mode.
Vacuum sealing device is installed in the sealed compartment 10 for being provided with girder 9；In the bulkhead of sealed compartment 10 with the opposite face of girder 9
Place is provided with open window, the default covering flange of window edge；The big end of seal closure 3 and window covering flanging welded, connecting cylinder 1-1
It is fixedly connected by connector 4 with girder 9.
Embodiment 2：A kind of installation method for compensating the vacuum sealing device of Optical devices precision offset, it is based on real
A kind of vacuum sealing device for compensating Optical devices precision offset described in example 1 is applied, is comprised the following steps：
A. seal closure 3 is welded on the default covering flange of the bulkhead of sealed compartment 10, is examined by X-ray check and weld joint air-tight
Look into, it is ensured that meet use requirement；
B. connecting cylinder A1-1 is connected in place out of my cabin with the girder 9 of sealed compartment 10；By 2 sets of companies of being attached to of elastic compensator
Connect and be attached on an A1-1, and critical external compressive resistance unstability steel ring 2-1 is set, needed before connection close to ensure to contact surface purified treatment
Envelope；
C. the part of installation in step B is carried out into the assembling in sealed compartment 10；
D. elastic compensator 2 and seal closure 3 are adjusted and is connected, is needed before connection to contact surface purified treatment to ensure sealing；
E. connecting cylinder B1-2 is put into from the open window of the bulkhead of sealed compartment 10, and is connected with connecting cylinder A1-1, connected
Place is provided with nonmetallic heat insulating mattress；
F. infrared earth sensor 12 is put into from the open window of the bulkhead of sealed compartment 10, and is installed to connecting cylinder B1-2
On.
Claims (2)
1. a kind of vacuum sealing device for compensating Optical devices precision offset, it is characterised in that it includes：Installation pedestal
(1), elastic compensator (2) and seal closure (3)；
Connecting cylinder A (1-1), the connecting cylinder B (1-2) that the installation pedestal (1) is connected by bolt (7) are constituted；The connecting cylinder A
(1-1) is provided with the cylindrical structure of connection boss for two ends, and the connecting cylinder B (1-2) is the ladder barrel structure that three-level is shunk；Institute
Stating the maximum end of connecting cylinder B (1-2) is used to install infrared earth sensor (12), and smallest end is used for and the connecting cylinder A (1-1)
Docking, nonmetallic heat insulating mattress is provided with joint；
The elastic compensator (2) uses elastomeric material, with sandwich construction, elastic adjustment is carried out with pressure oscillation in cabin；Institute
The outside that elastic compensator (2) is socketed in the connecting cylinder A (1-1) is stated, the connection boss with connecting cylinder A (1-1) two ends
It is tightly connected；A critical external compressive resistance unstability steel ring is provided between every layer of elastic compensator (2) inside and the connecting cylinder A outer walls
(2-1)；
The seal closure (3) is the small necking tubular structure in the big one end in one end, and its side wall is provided with mounting flange (3-1)；It is described close
Sealing cover (3) is socketed in the outside of connecting cylinder B (1-2), and the connection boss for passing through its small end and described connecting cylinder A (1-1) one end
It is tightly connected.
2. a kind of vacuum sealing device for compensating Optical devices precision offset as claimed in claim 1, it is characterised in that
The vacuum sealing device is installed on and is provided with the sealed compartment (10) of girder (9)；
Open window is provided with the sealed compartment (10) bulkhead with the girder (9) opposite face, the window edge is preset
Covering flange；The big end of the seal closure (3) and the window covering flanging welded, the connecting cylinder A (1-1) and the girder
(9) it is fixedly connected by connector (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621073874.0U CN206187366U (en) | 2016-09-22 | 2016-09-22 | A vacuum seal device for compensating skew of optical devices precision |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621073874.0U CN206187366U (en) | 2016-09-22 | 2016-09-22 | A vacuum seal device for compensating skew of optical devices precision |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206187366U true CN206187366U (en) | 2017-05-24 |
Family
ID=58729735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621073874.0U Withdrawn - After Issue CN206187366U (en) | 2016-09-22 | 2016-09-22 | A vacuum seal device for compensating skew of optical devices precision |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206187366U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394939A (en) * | 2016-09-22 | 2017-02-15 | 北京空间飞行器总体设计部 | Vacuum sealing device for compensating precision deviation of optical device and installation method of vacuum sealing device |
| CN111426448A (en) * | 2020-03-27 | 2020-07-17 | 中国科学院西安光学精密机械研究所 | Optical assembly performance test platform |
-
2016
- 2016-09-22 CN CN201621073874.0U patent/CN206187366U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394939A (en) * | 2016-09-22 | 2017-02-15 | 北京空间飞行器总体设计部 | Vacuum sealing device for compensating precision deviation of optical device and installation method of vacuum sealing device |
| CN111426448A (en) * | 2020-03-27 | 2020-07-17 | 中国科学院西安光学精密机械研究所 | Optical assembly performance test platform |
| CN111426448B (en) * | 2020-03-27 | 2021-06-22 | 中国科学院西安光学精密机械研究所 | Optical assembly performance test platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170524 Effective date of abandoning: 20181116 |
|
| AV01 | Patent right actively abandoned |