CN203859746U - Novel spaceborne measurement and control communication device - Google Patents
Novel spaceborne measurement and control communication device Download PDFInfo
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- CN203859746U CN203859746U CN201420232146.4U CN201420232146U CN203859746U CN 203859746 U CN203859746 U CN 203859746U CN 201420232146 U CN201420232146 U CN 201420232146U CN 203859746 U CN203859746 U CN 203859746U
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Abstract
The utility model discloses a novel spaceborne measurement and control communication device. The device comprises a secondary power supply module and an integrated function combination module. The secondary power supply module is horizontally connected to a satellite platform and supplies power to the integrated function combination module. The secondary power supply module internally comprises a heat consumption element. The heat consumption element is arranged in the bottom part in the secondary power supply module and dissipates heat through the satellite platform. The integrated function combination module is connected to the top part of the secondary power supply module and comprises multiple function modules including a spread spectrum transmitter module and a data transmission transmitter module. The multiple function modules are vertically connected to the secondary power supply module and are arranged close to each other. The spread spectrum transmitter module and the data transmission transmitter module are respectively located at the two ends of the integrated function combination module, and thus the contact area of the spread spectrum transmitter module and the data transmission transmitter module with external space is broadened. According to the utility model, traditional measurement and control communication units are integrated into a whole; and the influences of environment factors, such as impact, vibration, heat dissipation, and electromagnetic interference, from the perspectives of mechanics, calorifics, and electromagnetic compatibility are all taken into account at the same time.
Description
Technical field
The utility model relates to Space TT&C technical field, particularly a kind of spaceborne telemetry communication equipment of integrated structure design.
Background technology
TTC & DT Systems, as the very crucial part of Simulating of Space Countermeasure System integrated electronics platform, is being born the vital task of Orbit, remote control, remote measurement and the payload data transmission of whole spacecraft.Integrated by function synthesized optimization, design height to TTC & DT Systems, topology layout is integrated, realizes lightweight, is just becoming the basic demand of Space Attack maneuver warfare platform.
On traditional space flight applicator platform, telemetry communication equipment is substantially all divided, is developed separately according to function, mainly contain the function unit such as answering machine, number transmission transmitter, remote terminal and telemetry terminal system, no matter these separate devices are in the physical structure such as volume, weight, or on circuit resource and interface mode, there is very large redundancy and numerous and diverse, also make spacecraft platform structure complexity, figure is too fat to move, has increased especially launch cost.Along with the development of space technology, space flight applicator platform will more and more be simplified, systematization, integrated platform device will become main flow, therefore we need to, by rational structural design, be long-pending little, the lightweight comprehensive aircraft platform product of a stage body by traditional discrete telemetry communication integration of equipments.
Utility model content
The utility model, for prior art above shortcomings, provides a kind of Novel satellite borne telemetry communication equipment.The utility model is achieved through the following technical solutions:
A kind of Novel satellite borne telemetry communication equipment, comprising: secondary power supply module, integrated function composite module;
Secondary power supply module is horizontal to be connected on a satellite platform, and in order to integrated function composite module power supply, secondary power supply inside modules comprises hear rate device, and hear rate device is arranged on the bottom in secondary power supply module, in order to platform heat radiation via satellite;
Integrated function composite module, be connected to the top of secondary power supply module, some functional modules including spread spectrum transmitter module and number transmission transmitter module, some functional modules are vertical to be connected in secondary power supply module, between some functional modules, be close to arrangement, spread spectrum transmitter module and number transmission transmitter module lay respectively at the two ends of integrated function composite module, the contact area in order to increase with space outerpace.
Preferably, between the some functional modules in integrated function composite module, be laterally fixed together by bolt, each functional module is bolted to connection respectively the top in secondary power supply module.
Preferably, secondary power supply module is connected on satellite platform by bolt is horizontal.
Preferably, integrated function composite module comprises connection successively: spread spectrum transmitter module, band spread receiver module, intermediate frequency processor module, remote control command module, remote control decoding module, telemetry module, number pass baseband processing module, and number transmission transmitter module.
Preferably, between some functional modules, being close to arrangement comprises: naked connection between the housing of some functional modules.
Preferably, the top of some functional modules is respectively arranged with electric connector.
The Novel satellite borne telemetry communication equipment that the utility model provides, is integrated into by traditional telemetry communication unit the system-level unit product that unified power supply, a function merge, and makes it have superior performance at the aspect such as volume, weight.To solve traditional spaceborne telemetry communication unit function singleness, the wiring problem such as complicated, bulky, take into account the environmental factors such as mechanics, calorifics, electromagnetic compatibility as the impact on complete machine such as shock and vibration, heat radiation and electromagnetic interference simultaneously.
Brief description of the drawings
Shown in Fig. 1 is structural representation of the present utility model.
Embodiment
Below with reference to accompanying drawing of the present utility model; technical scheme in the utility model embodiment is carried out to clear, complete description and discussion; obviously; as described herein is only a part of example of the present utility model; it is not whole examples; based on the embodiment in the utility model, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite of not making creative work, belongs to protection range of the present utility model.
For the ease of the understanding to the utility model embodiment, be further explained as an example of specific embodiment example below in conjunction with accompanying drawing, and each embodiment does not form the restriction to the utility model embodiment.
As shown in Figure 1, Novel satellite borne telemetry communication equipment comprises: secondary power supply module 10, integrated function composite module.
Integrated function composite module comprises 8 functional modules (quantity is determined according to actual conditions, and the utility model does not limit): band spread receiver module 3, spread spectrum transmitter module 2, intermediate frequency processor module 4, remote control command module 5, remote control decoding module 6, telemetry module 7, number pass baseband processing module 8, number transmission transmitter module 9.
Wherein secondary power supply module 10 is horizontal, be positioned at overall bottom, its inside is provided with hear rate device 14, secondary power supply module 10 is mounted on satellite platform by bolt 11, the naked face of housing between each module (2-9) of integrated function composite module joins, be close to placement, by many fastening bolts 12, each module (2-9) is laterally fixed together, it adopts vertical assembled, each module of this integrated function composite module is fixed in secondary power supply module 10 by bolt 13 respectively, powerful hear rate device 14 is positioned at the bottom of secondary power supply module 10, it contacts with satellite platform, heat can be directly via satellite platform distribute, simultaneously, spread spectrum transmitter module 2 and number transmission transmitter module 9 all configure the Microwave Power Amplifier of large hear rate, therefore it is positioned over respectively to the two ends of integrated function composite module, strengthen the contact area in itself and space, improve heat loss through radiation performance, from electromagnetic compatibility angle, so also be conducive to the electromagnetic interference of a decrease radio-frequency module.
The utility model adopts the hybrid splicing structure that vertical type moduleization is assembled and horizontal modularization assemble combines, effectively avoid mechanical shock, the damage of vibration to device and unit, reached the unit heat balance under multiple source of heat releases, multiple radio-frequency module co-operation, the beneficial effect of electromagnetic compatibility.
The above; it is only preferably embodiment of the utility model; but protection range of the present utility model is not limited to this; any be familiar with those skilled in the art the utility model disclose technical scope in; the variation that can expect easily or replacement, within all should being encompassed in protection range of the present utility model.Therefore, protection range of the present utility model should be as the criterion with the protection range of claim.
Claims (6)
1. a Novel satellite borne telemetry communication equipment, is characterized in that, comprising: secondary power supply module, integrated function composite module;
Described secondary power supply module is horizontal to be connected on a satellite platform, with thinking described integrated function composite module power supply, described secondary power supply inside modules comprises hear rate device, and described hear rate device is arranged on the bottom in described secondary power supply module, in order to dispel the heat by described satellite platform;
Described integrated function composite module, be connected to the top of described secondary power supply module, some functional modules including spread spectrum transmitter module and number transmission transmitter module, described some functional modules are vertical to be connected in described secondary power supply module, between described some functional modules, be close to arrangement, described spread spectrum transmitter module and described several transmission transmitter module lay respectively at the two ends of described integrated function composite module, the contact area in order to increase with space outerpace.
2. Novel satellite borne telemetry communication equipment according to claim 1, it is characterized in that, between some functional modules in described integrated function composite module, be laterally fixed together by bolt, each functional module is bolted to connection respectively the top in described secondary power supply module.
3. Novel satellite borne telemetry communication equipment according to claim 1, is characterized in that, described secondary power supply module is connected on described satellite platform by bolt is horizontal.
4. Novel satellite borne telemetry communication equipment according to claim 1, it is characterized in that, described integrated function composite module comprises connection successively: described spread spectrum transmitter module, band spread receiver module, intermediate frequency processor module, remote control command module, remote control decoding module, telemetry module, number pass baseband processing module, and described several transmission transmitter module.
5. Novel satellite borne telemetry communication equipment according to claim 1, is characterized in that, is close to arrange to comprise between described some functional modules: naked connection between the housing of described some functional modules.
6. Novel satellite borne telemetry communication equipment according to claim 1, is characterized in that, the top of described some functional modules is respectively arranged with electric connector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420232146.4U CN203859746U (en) | 2014-05-08 | 2014-05-08 | Novel spaceborne measurement and control communication device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420232146.4U CN203859746U (en) | 2014-05-08 | 2014-05-08 | Novel spaceborne measurement and control communication device |
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| Publication Number | Publication Date |
|---|---|
| CN203859746U true CN203859746U (en) | 2014-10-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420232146.4U Expired - Fee Related CN203859746U (en) | 2014-05-08 | 2014-05-08 | Novel spaceborne measurement and control communication device |
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| CN (1) | CN203859746U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105897328A (en) * | 2016-04-26 | 2016-08-24 | 清华大学深圳研究生院 | Micro-satellite information processing system and communication method thereof |
| CN106428649A (en) * | 2016-10-26 | 2017-02-22 | 中国运载火箭技术研究院 | Automatic support system for reusable carriers |
-
2014
- 2014-05-08 CN CN201420232146.4U patent/CN203859746U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105897328A (en) * | 2016-04-26 | 2016-08-24 | 清华大学深圳研究生院 | Micro-satellite information processing system and communication method thereof |
| CN106428649A (en) * | 2016-10-26 | 2017-02-22 | 中国运载火箭技术研究院 | Automatic support system for reusable carriers |
| CN106428649B (en) * | 2016-10-26 | 2018-12-21 | 中国运载火箭技术研究院 | A kind of Control System for Reusable Launch Vehicle self -support system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160517 Address after: 201200 Shanghai city Pudong New Area jinzang Road No. 258 Building 5 707A Patentee after: Shanghai Aerospace Satellite Applied Co., Ltd. Address before: 200082 Qigihar Road, Shanghai, No. 76, No. Patentee before: Shanghai Aerospace Electronic Communication Equipment Inst. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141001 Termination date: 20180508 |
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| CF01 | Termination of patent right due to non-payment of annual fee |