CN201128484Y - Aerospace optical camera door - Google Patents
Aerospace optical camera door Download PDFInfo
- Publication number
- CN201128484Y CN201128484Y CNU2007201902107U CN200720190210U CN201128484Y CN 201128484 Y CN201128484 Y CN 201128484Y CN U2007201902107 U CNU2007201902107 U CN U2007201902107U CN 200720190210 U CN200720190210 U CN 200720190210U CN 201128484 Y CN201128484 Y CN 201128484Y
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- CN
- China
- Prior art keywords
- camera
- cover plate
- optical camera
- springing
- hot topic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a spaceflight optical camera hot door which is fixedly connected with a camera light shield or a camera body. The spaceflight optical camera hot door consists of a cover plate (4), a driving mechanism (1), a driving arm (3) and an elastic device (5). One end of the driving arm (3) is connected with the driving mechanism (1), and the other end is connected with the cover plate (4) to drive the cover plate (4) to be pressed in the light shield (6) or the camera body. The protrudent elastic device (5) is arranged around the light shield (6). The inner surface of the cover plate (4) is provided with a pit at the position opposite to the elastic device (5). An exploder (2) is arranged at one end of the driving arm (3) which is connected with the driving mechanism (1). The hot door can reduce the heat leakage near a window of a high-resolution camera, reduces the influence on camera shooting resolution caused by temperature difference, takes effect of preventing irradiation and improves the camera safeness. The spaceflight optical camera hot door can be widely applied to the precision thermal control and the protective control of a spaceflight high-resolution camera.
Description
Technical field
The utility model belongs to the space flight optical remote sensor technical field, particularly a kind of accurate thermal control and protection hot topic that is applied to space flight optics fine resolution camera.
Background technology
Along with space flight optical camera technology rapid development, optical sensor resolution is more and more higher, and camera thermal control and protection are had higher requirement.Accurate thermal control technology can be according to CALCULATION OF THERMAL, and the thermal control measure of taking the initiative guarantees that temperature field and thermal drop are even; The protection of space flight optical camera can improve the anti-irradiation and the laser resistant ability of electronic devices and components.Hot topic is closed at ordinary times, opens during photograph, is the important means that improves accurate thermal control ability of camera space and protective capacities simultaneously.
At present, domestic still useless in the hot topic report and the utilization of space flight optical camera.The long-focus fine resolution camera of external development all has been equipped with hot topic as U.S. Hubble glass, Ikonos and Quick Bird2 high-resolution satellite, KH-11 satellite etc., helps Thermal Environment Control and to the protection of camera.But do not see that the popular structure of relevant fine resolution mode transmission camera and the relevant civilian i of mechanism offer report.
The utility model content
The purpose of this utility model is: a kind of space flight optical camera hot topic that can reduce the thermal control power consumption, improve high-resolution camera protective capacities is provided; The problem that the utility model further solves provides and a kind ofly breaks down when popular mechanism, in the time of can't opening, and can be according to the high reliability space flight optical camera hot topic of the popular mechanism of instruction jettisoning.
Technical solution of the present utility model is: a kind of space flight optical camera hot topic, be fixedly connected on camera shade or the camera main-body, and form by cover plate, driver train, actuating arm and springing; Actuating arm one end connects driver train, and the other end connects cover plate to drive cover plate and shade or camera main-body pressing; Along the springing of shade circle distribution projection, be provided with pit in the corresponding springing of the inside face position of cover plate.
At actuating arm and driver train bonded assembly one end, exploder is housed.
Described springing is the cylinder of a hollow, and its in-to-in spring supports ⊥ shape movable holddown and stretches out the cylinder upper surface.
Described springing is along shade circumference rectangular distribution, and quantity is 4-8.
" unlatching " of corresponding cover plate reaches " closing " position micro-switch is installed in described driver train.
The utility model beneficial effect compared with prior art is:
1, the hot topic of camera increase can reduce near the leakage heat of fine resolution camera window, improves the temperature homogeneity of camera lens, thereby reduces the influence of the temperature difference to the camera photographic resolution; Reduce the exposure time of space radiation simultaneously, play certain anti-effect of irradiation catadioptre and CCD; The bump influence of minimizing cosmic dust etc. improves the camera safety.
2, at actuating arm and driver train bonded assembly one end, exploder is housed,, can improves the reliability that camera uses according to instruction blast jettisoning cover plate when popular mechanism breaks down can't open the time.
3, play the effect of buffer shock-absorbing along the springing of shade or camera main-body circle distribution projection, prevent when hot topic from closing impact camera system; Inside face relevant position at cover plate is provided with pit, and when compressing, cover plate is pressed on the structural plan.Simultaneously, the projection of springing falls into corresponding pit, has prevented the radial-play of cover plate.
Description of drawings
Fig. 1 is the scheme drawing of space flight optical camera hot topic of the present utility model;
Fig. 2 is the structural representation of springing.
The specific embodiment
The utility model is described in further detail below in conjunction with accompanying drawing.
Among Fig. 1, driver train-1, exploder-2, actuating arm-3, cover plate-4, springing-5, shade-6.Among Fig. 2, movable holddown-51, spring-52.
A kind of space flight optical camera hot topic is fixedly connected on the camera shade 6, is made up of cover plate 4, driver train 1, actuating arm 3 and springing 5; Actuating arm 3 one ends connect driver train 1, and the other end connects cover plate 4, and drive cover plate 4 and shade 6 pressings; Along the springing 5 of 4 projectioies of rectangular distribution on shade 6 circumference, be provided with pit in the position of the corresponding springing 5 of the inside face of cover plate 4.Spring 52 supports movable holddown 51 and stretches out periphery, and when compressing, cover plate 4 is pressed on the structural plan.
At actuating arm 3 and driver train 1 bonded assembly one end, exploder 2 is housed.
After controller received " the popular unlatching " or " hot topic is closed " instruction, controller gave driver train 1 power supply, made driver train 1 by given direction rotation.The actuating arm 3 that is fixed together with the driver train output shaft drives cover plate 4 along with output shaft rotates.When rotating to the position detector switch by pressing, driver train 1 stops operating.By above action, make cover plate 4 open or close, to reach the purpose that allows the camera photograph or be incubated and protect to camera lens.
In addition, two groups of micro-switchs are respectively arranged in the position that " unlatching " reaches " closing " in driver train, the micro-switch of each position be contained in can be spacing insulating base on, prevent the overvoltage of switch stage clip.Micro-switch plays the effect of transmitting signal, plays buffer action again, the mitigation system vibration.
Be connected with two cables on each micro-switch, cable links to each other with controller circuitry.When actuating arm rotated to popular open position, actuating arm touched two groups of micro-switchs, connected the location of controls testing circuit, and controller is controlled the motor stall according to signal.In addition, program controlly send popular motor stall instruction, as put in place the backup of outage of micro-switch according to the time gap that configures.Guarantee during design that signal is reliable, prevent that again the arcing phenomenon produces in the vacuum.
Springing 5 of the present utility model also can be installed on the camera main-body.
Design result of the present utility model is: switch number of times 〉=50000 time; Folding angle＞180 °; Weight≤15kg; Reliability 〉=0.995; Can reducing initiatively, the thermal control power consumption is 83W.
Claims (5)
1, a kind of space flight optical camera hot topic is characterized in that: be fixedly connected on camera shade or the camera main-body, be made up of cover plate (4), driver train (1), actuating arm (3) and springing (5); Actuating arm (3) one ends connect driver train (1), and the other end connects cover plate (4) to drive cover plate (4) and shade (6) or camera main-body pressing; Along the springing (5) of shade (6) circle distribution projection, be provided with pit in the corresponding springing (5) of the inside face position of cover plate (4).
2, according to a kind of space flight optical camera hot topic of claim 1, it is characterized in that:, exploder (2) is housed at actuating arm (3) and driver train (1) bonded assembly one end.
3, according to a kind of space flight optical camera hot topic of claim 1, it is characterized in that: described springing (5) is the cylinder of a hollow, and its in-to-in spring (52) supports ⊥ shape movable holddown (51) and stretches out the cylinder upper surface.
4, according to a kind of space flight optical camera hot topic of claim 1 or 3, it is characterized in that: described springing (5) is along shade circumference rectangular distribution, and quantity is 4-8.
5, according to a kind of space flight optical camera hot topic of claim 1, it is characterized in that: in driver train (1) " unlatching " of corresponding cover plate (4) reach " closing " position micro-switch be installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201902107U CN201128484Y (en) | 2007-11-16 | 2007-11-16 | Aerospace optical camera door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201902107U CN201128484Y (en) | 2007-11-16 | 2007-11-16 | Aerospace optical camera door |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201128484Y true CN201128484Y (en) | 2008-10-08 |
Family
ID=40016317
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007201902107U Expired - Fee Related CN201128484Y (en) | 2007-11-16 | 2007-11-16 | Aerospace optical camera door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201128484Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103412585A (en) * | 2013-07-15 | 2013-11-27 | 航天东方红卫星有限公司 | Satellite camera heat protection door system with active temperature control function |
| CN104460192A (en) * | 2014-12-30 | 2015-03-25 | 中国科学院长春光学精密机械与物理研究所 | Heat-insulating opening and closing mechanism for light entrance of space optics camera |
-
2007
- 2007-11-16 CN CNU2007201902107U patent/CN201128484Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103412585A (en) * | 2013-07-15 | 2013-11-27 | 航天东方红卫星有限公司 | Satellite camera heat protection door system with active temperature control function |
| CN104460192A (en) * | 2014-12-30 | 2015-03-25 | 中国科学院长春光学精密机械与物理研究所 | Heat-insulating opening and closing mechanism for light entrance of space optics camera |
| CN104460192B (en) * | 2014-12-30 | 2017-10-03 | 中国科学院长春光学精密机械与物理研究所 | A kind of heat-insulated open-and-close mechanism of space optical camera light inlet |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20081008 Termination date: 20161116 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |