CN105446181A - Integrated launching console for quick response satellite - Google Patents
Integrated launching console for quick response satellite Download PDFInfo
- Publication number
- CN105446181A CN105446181A CN201510861015.1A CN201510861015A CN105446181A CN 105446181 A CN105446181 A CN 105446181A CN 201510861015 A CN201510861015 A CN 201510861015A CN 105446181 A CN105446181 A CN 105446181A
- Authority
- CN
- China
- Prior art keywords
- satellite
- control module
- module
- wired
- quick response
- 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.)
- Pending
Links
- 230000004044 response Effects 0.000 title claims abstract description 20
- 238000004088 simulation Methods 0.000 claims abstract description 27
- 230000003750 conditioning effect Effects 0.000 claims abstract description 8
- 238000000926 separation method Methods 0.000 claims abstract description 4
- 230000010354 integration Effects 0.000 claims description 16
- 238000012546 transfer Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 abstract 1
- 238000007599 discharging Methods 0.000 abstract 1
- 230000001276 controlling effect Effects 0.000 description 23
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000008485 antagonism Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Selective Calling Equipment (AREA)
Abstract
The invention provides an integrated launching console for a quick response satellite. The integrated launching console for a quick response satellite comprises a control module, a satellite wired signal acquisition module, a satellite wired control module, a signal conditioning board card and a code list card, wherein the satellite wired signal acquisition module, the satellite wired control module and the code list card are connected with the control module; both the satellite wired signal acquisition module and the satellite wired control module are connected with the signal conditioning board card; and the satellite wired signal acquisition module is used for acquisition of impedance of a satellite, bus voltage, bus current, storage battery voltage, discharging switch state, separating plug state, star catalogue plug state and simulated separation state. The integrated launching console for a quick response satellite integrates a simulation array control module, a telemetry and telecontrol transmission module and the satellite wired signal acquisition module in a PXI cabinet to enable a satellite launching control system to be higher in the integrated level, smaller in volume and being more suitable for requirement of vehicle and mobile launching of the quick response satellite.
Description
Technical field
The present invention relates to and respond satellite fast, particularly, relate to a kind of satellite of response fast integration transmitter control station.
Background technology
Quick response satellite is called for short fast sound satellite, is the satellite of a class for the case of emergency such as special type investigation, extraordinary antagonism, the civilian disaster relief, needs to have rapid Design, fast test, rapid fire ability.Therefore, the fast vehicle-mounted motion in the field of the many employings of satellite that rings is launched, and this volume to its launch control equipment, scale are had higher requirement.The transmitter control station of conventional satellite, comprise industrial computer, signal process box and actuator, volume is larger; Meanwhile, tradition is sent out control platform and is only had wire signal collection, has the function of line traffic control, and functional density is low, for the control of solar simulation battle array, the forwarding of remote measuring and controlling, also needs to use miscellaneous equipment to assist.Therefore the launch control equipment that a set of integrated level is higher, function is more comprehensive, volume is smaller and more exquisite is developed, for realizing the fast rapid fire ringing satellite, significant.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of satellite of response fast integration transmitter control station.
According to quick response satellite integration transmitter control station provided by the invention, comprise control module, satellite wire signal acquisition module, the wired control module of satellite, signal condition board and code table card;
Wherein, the wired acquisition module of described satellite, the wired control module of described satellite and described code table link and connect described control module; The wired acquisition module of described satellite is all connected described signal condition board with the wired control module of described satellite;
Described satellite wire signal acquisition module is for gathering impedance, busbar voltage, bus current, accumulator battery voltage, discharge switch state, de-point slotting state, the star catalogue plug state of satellite and simulating released state;
The wired control module of described satellite for realize ground emaciated face independent power source output, send the disconnected control of simulation satellite and the rocket separation signal, star power source discharge switch;
Described signal condition board for complete Satellite Simulation amount, quantity of state information conditioning and Satellite Simulation amount, quantity of state information after conditioning are sent to satellite wire signal acquisition module and gather; There is line control signal to transfer on the satellite of wired for satellite control module, to be sent on star simultaneously;
There is direct instruction code word described code table card inside, is converted to direct instruction code word for direct instruction code name control module sent.
Preferably, described control module comprises satellite wire signal acquisition control module, satellite has line control signal control module and remote measuring and controlling forwarding module;
Wherein, described satellite wire signal acquisition control module connects described satellite wire signal acquisition module; Described satellite has line control signal control module to connect the wired control module of described satellite; Described remote measuring and controlling forwarding module connects described code table card;
When direct instruction code name is sent to code table card by described remote measuring and controlling forwarding module, described code table card generates direct instruction code word according to described direct instruction code name.
Preferably, the first network interface card is also comprised; Described control module also comprises simulation battle array control module;
Wherein, described simulation battle array control module connects described first network interface card, for controlling the solar simulation battle array of satellite and the data acquisition of solar simulation battle array by described first network interface card.
Preferably, the second network interface card is also comprised;
Wherein, described second network interface card connects described remote measuring and controlling forwarding module; Described remote measuring and controlling forwarding module is used for the observing and controlling base band by described second network interface card, described direct instruction code word being sent to satellite, and indirect instruction and note number are directly transmitted to observing and controlling base band and receive the downlink telemetry of observing and controlling base band.
Preferably, described control module adopts PXI industrial computer, and the wired acquisition module of described satellite, the wired control module of described satellite, described signal condition board and described code table card are all inserted in described PXI industrial computer with PXI board form.
Preferably, the wired acquisition module of described satellite adopts digital multimeter module and coordinates multiplexer.
Preferably, the wired control module of described satellite adopts relay switch board.
Compared with prior art, the present invention has following beneficial effect:
1, the present invention is provided with the data acquisition that simulation battle array control module can control solar simulation battle array and solar simulation battle array;
2, the present invention is provided with remote measuring and controlling forwarding module, indirect instruction and note number directly can be transmitted to observing and controlling base band and receive the downlink telemetry of observing and controlling base band;
3, present invention omits actuator, the function i ntegration of signal process box is installed in industrial computer on signal condition board, send out control stage body than tradition and amass reduction 2/3;
4, solar simulation battle array controls by the present invention, remote measuring and controlling forwards, satellite wire signal gathers control integration in a PXI cabinet, make satellite launch control system integration Du Genggao, volume less, be more applicable to that fast response satellite is vehicle-mounted, the needs of Mobile launch.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is structural representation of the present invention.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
In the present embodiment, as shown in Figure 1, quick response satellite integration transmitter control station provided by the invention, comprises control module, satellite wire signal acquisition module, the wired control module of satellite, signal condition board and code table card;
Wherein, the wired acquisition module of described satellite, the wired control module of described satellite and described code table link and connect described control module; The wired acquisition module of described satellite is all connected described signal condition board with the wired control module of described satellite; Described satellite wire signal acquisition module is for gathering impedance, busbar voltage, bus current, accumulator battery voltage, discharge switch state, de-point slotting state, the star catalogue plug state of satellite and simulating released state; The wired control module of described satellite for realize ground emaciated face independent power source output, send the disconnected control of simulation satellite and the rocket separation signal, star power source discharge switch; Described signal condition board for complete Satellite Simulation amount, quantity of state information conditioning and Satellite Simulation amount, quantity of state information after conditioning are sent to satellite wire signal acquisition module and gather; There is line control signal to transfer on the satellite of wired for satellite control module simultaneously, to be sent on star, simultaneously to there being line control signal to transfer, and providing hardware protection switch or manual backup switch to important control signal.Signal regulating panel card size conforms to standard P XI board size, can be installed on PXI slot.There is direct instruction code word described code table card inside, is converted to direct instruction code word for direct instruction code name control module sent.
Described control module comprises satellite wire signal acquisition control module, satellite has line control signal control module and remote measuring and controlling forwarding module; Wherein, described satellite wire signal acquisition control module connects described satellite wire signal acquisition module; Described satellite has line control signal control module to connect the wired control module of described satellite; Described remote measuring and controlling forwarding module connects described code table card; When direct instruction code name is sent to code table card by described remote measuring and controlling forwarding module, described code table card generates direct instruction code word according to described direct instruction code name.
Quick response satellite integration transmitter control station provided by the invention, also comprises the first network interface card; Described control module also comprises simulation battle array control module; Wherein, described simulation battle array control module connects described first network interface card, for controlling the solar simulation battle array of satellite and the data acquisition of solar simulation battle array by described first network interface card.Quick response satellite integration transmitter control station provided by the invention, also comprises the second network interface card; Wherein, described second network interface card connects described remote measuring and controlling forwarding module; Described remote measuring and controlling forwarding module is used for the observing and controlling base band by described second network interface card, described direct instruction code word being sent to satellite, indirect instruction and note number are directly transmitted to observing and controlling base band and receive the downlink telemetry of observing and controlling base band, is transmitted to testing server and resolves.
In the present embodiment, described control module adopts PXI industrial computer, and the wired acquisition module of described satellite, the wired control module of described satellite, described signal condition board and described code table card are all inserted in described PXI industrial computer with PXI board form.The wired acquisition module of described satellite adopts digital multimeter module and coordinates multiplexer.The wired control module of described satellite adopts relay switch board.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (7)
1. respond a satellite integration transmitter control station fast, it is characterized in that, comprise control module, satellite wire signal acquisition module, the wired control module of satellite, signal condition board and code table card;
Wherein, the wired acquisition module of described satellite, the wired control module of described satellite and described code table link and connect described control module; The wired acquisition module of described satellite is all connected described signal condition board with the wired control module of described satellite;
Described satellite wire signal acquisition module is for gathering impedance, busbar voltage, bus current, accumulator battery voltage, discharge switch state, de-point slotting state, the star catalogue plug state of satellite and simulating released state;
The wired control module of described satellite for realize ground emaciated face independent power source output, send the disconnected control of simulation satellite and the rocket separation signal, star power source discharge switch;
Described signal condition board for complete Satellite Simulation amount, quantity of state information conditioning and Satellite Simulation amount, quantity of state information after conditioning are sent to satellite wire signal acquisition module and gather; There is line control signal to transfer on the satellite of wired for satellite control module, to be sent on star simultaneously;
There is direct instruction code word described code table card inside, is converted to direct instruction code word for direct instruction code name control module sent.
2. quick response satellite integration transmitter control station according to claim 1, is characterized in that, described control module comprises satellite wire signal acquisition control module, satellite has line control signal control module and remote measuring and controlling forwarding module;
Wherein, described satellite wire signal acquisition control module connects described satellite wire signal acquisition module; Described satellite has line control signal control module to connect the wired control module of described satellite; Described remote measuring and controlling forwarding module connects described code table card;
When direct instruction code name is sent to code table card by described remote measuring and controlling forwarding module, described code table card generates direct instruction code word according to described direct instruction code name.
3. quick response satellite integration transmitter control station according to claim 2, is characterized in that, also comprise the first network interface card; Described control module also comprises simulation battle array control module;
Wherein, described simulation battle array control module connects described first network interface card, for controlling the solar simulation battle array of satellite and the data acquisition of solar simulation battle array by described first network interface card.
4. quick response satellite integration transmitter control station according to claim 2, is characterized in that, also comprise the second network interface card;
Wherein, described second network interface card connects described remote measuring and controlling forwarding module; Described remote measuring and controlling forwarding module is used for the observing and controlling base band by described second network interface card, described direct instruction code word being sent to satellite, and indirect instruction and note number are directly transmitted to observing and controlling base band and receive the downlink telemetry of observing and controlling base band.
5. quick response satellite integration transmitter control station according to claim 1, it is characterized in that, described control module adopts PXI industrial computer, and the wired acquisition module of described satellite, the wired control module of described satellite, described signal condition board and described code table card are all inserted in described PXI industrial computer with PXI board form.
6. quick response satellite integration transmitter control station according to claim 1, it is characterized in that, the wired acquisition module of described satellite adopts digital multimeter module and coordinates multiplexer.
7. quick response satellite integration transmitter control station according to claim 1, it is characterized in that, the wired control module of described satellite adopts relay switch board.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510861015.1A CN105446181A (en) | 2015-11-30 | 2015-11-30 | Integrated launching console for quick response satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510861015.1A CN105446181A (en) | 2015-11-30 | 2015-11-30 | Integrated launching console for quick response satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105446181A true CN105446181A (en) | 2016-03-30 |
Family
ID=55556513
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510861015.1A Pending CN105446181A (en) | 2015-11-30 | 2015-11-30 | Integrated launching console for quick response satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105446181A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106292636A (en) * | 2016-08-30 | 2017-01-04 | 北京宇航系统工程研究所 | A kind of integrated ground observing and controlling system |
| CN107991621A (en) * | 2017-11-24 | 2018-05-04 | 上海微小卫星工程中心 | It is a kind of can analog satellite accumulator cell charging and discharging curve test device and method |
| CN112947358A (en) * | 2021-01-25 | 2021-06-11 | 航天科工空间工程发展有限公司 | Vehicle-mounted comprehensive test system and method for testing mobile launching satellite |
| CN116395148A (en) * | 2023-03-20 | 2023-07-07 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1982863A (en) * | 2005-12-14 | 2007-06-20 | 上海微小卫星工程中心 | Universal micro-satellite comprehensive testing platform based on PXI system |
| CN102062645A (en) * | 2010-11-01 | 2011-05-18 | 航天东方红卫星有限公司 | Matrix multi-path temperature detection circuit for small satellite platform |
| JP2011237074A (en) * | 2010-05-07 | 2011-11-24 | Mitsubishi Heavy Ind Ltd | Flying body launch system |
| CN102521533A (en) * | 2011-12-01 | 2012-06-27 | 中国空间技术研究院 | Method for verifying remote control command code version |
| CN102724006A (en) * | 2012-06-18 | 2012-10-10 | 上海卫星工程研究所 | Rapid self-checking system and method of satellite comprehensive testing system |
| CN104062930A (en) * | 2013-11-29 | 2014-09-24 | 中国空间技术研究院 | Universal touch-type switch matrix control card for liquid crystal display |
| CN104331035A (en) * | 2014-09-30 | 2015-02-04 | 航天东方红卫星有限公司 | Mini-satellite test remote measurement and remote control monitoring system based on service-oriented architecture and method thereof |
| CN104932358A (en) * | 2015-05-29 | 2015-09-23 | 上海卫星工程研究所 | Large and medium-sized satellite general emission console based on PXI framework |
| CN105044613A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | High-fidelity satellite load scene reproduction device and method |
-
2015
- 2015-11-30 CN CN201510861015.1A patent/CN105446181A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1982863A (en) * | 2005-12-14 | 2007-06-20 | 上海微小卫星工程中心 | Universal micro-satellite comprehensive testing platform based on PXI system |
| JP2011237074A (en) * | 2010-05-07 | 2011-11-24 | Mitsubishi Heavy Ind Ltd | Flying body launch system |
| CN102062645A (en) * | 2010-11-01 | 2011-05-18 | 航天东方红卫星有限公司 | Matrix multi-path temperature detection circuit for small satellite platform |
| CN102521533A (en) * | 2011-12-01 | 2012-06-27 | 中国空间技术研究院 | Method for verifying remote control command code version |
| CN102724006A (en) * | 2012-06-18 | 2012-10-10 | 上海卫星工程研究所 | Rapid self-checking system and method of satellite comprehensive testing system |
| CN104062930A (en) * | 2013-11-29 | 2014-09-24 | 中国空间技术研究院 | Universal touch-type switch matrix control card for liquid crystal display |
| CN104331035A (en) * | 2014-09-30 | 2015-02-04 | 航天东方红卫星有限公司 | Mini-satellite test remote measurement and remote control monitoring system based on service-oriented architecture and method thereof |
| CN104932358A (en) * | 2015-05-29 | 2015-09-23 | 上海卫星工程研究所 | Large and medium-sized satellite general emission console based on PXI framework |
| CN105044613A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | High-fidelity satellite load scene reproduction device and method |
Non-Patent Citations (2)
| Title |
|---|
| 胡卫光: "遥感卫星跟踪天线伺服监控软件研究与实现", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
| 范利娟: "便携式卫星通信控制系统研究与设计", 《中国优秀硕士学位论文全文数据库信息科技辑》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106292636A (en) * | 2016-08-30 | 2017-01-04 | 北京宇航系统工程研究所 | A kind of integrated ground observing and controlling system |
| CN107991621A (en) * | 2017-11-24 | 2018-05-04 | 上海微小卫星工程中心 | It is a kind of can analog satellite accumulator cell charging and discharging curve test device and method |
| CN112947358A (en) * | 2021-01-25 | 2021-06-11 | 航天科工空间工程发展有限公司 | Vehicle-mounted comprehensive test system and method for testing mobile launching satellite |
| CN112947358B (en) * | 2021-01-25 | 2022-09-23 | 航天科工空间工程发展有限公司 | Vehicle-mounted comprehensive test system and method for testing mobile launching satellite |
| CN116395148A (en) * | 2023-03-20 | 2023-07-07 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
| CN116395148B (en) * | 2023-03-20 | 2023-09-15 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system and control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105446181A (en) | Integrated launching console for quick response satellite | |
| CN103956822B (en) | A kind of satellite power system of fast integration | |
| KR101881623B1 (en) | Dynamically reconfigurable electrical interface | |
| CN105375603A (en) | Satellite thermal vacuum test ground power supply system | |
| CN108828281B (en) | General ground of moonlet supplies distribution test cable system | |
| CN107797071A (en) | A kind of anti-strong electromagnetic isolation sample circuit of space lithium-ions battery group | |
| CN104484257B (en) | A kind of general 1553B bus communication emulation test system and method | |
| CN106706998B (en) | Terminal test system and terminal test method | |
| CN103901881A (en) | Device compatible with multiple test states for carrier rocket equivalent device system | |
| CN113612303B (en) | Satellite-ground solar cell array power supply integrated design system and method for satellite | |
| CN111504142B (en) | Universal missile simulator and simulation method | |
| CN205228283U (en) | Rocket firing system | |
| CN103869808B (en) | Carrier rocket simulator system based on distributed computing technology | |
| CN114661029A (en) | Airworthiness identification test system and method for civil aircraft flight control system | |
| CN105655684B (en) | A kind of NFC terminal of compatible metal rear shell and plastics rear shell | |
| CN206114834U (en) | Pressure transmitter's withstand voltage automatic test system | |
| CN203706212U (en) | Communication and navigation simulation system | |
| CN105444618A (en) | Rocket launching control system | |
| CN109031365A (en) | A kind of method and communication terminal of control satellite communication terminal communication | |
| CN201828904U (en) | Function test load simulation device based on network | |
| CN202351993U (en) | Voice alarm system of aviation cockpit | |
| CN204669379U (en) | A kind of CAN network fault simulation equipment | |
| CN221595205U (en) | Battery simulation device, battery simulation system and battery simulator | |
| CN105428742B (en) | The charge control method of highly reliable satellite lithium-ions battery | |
| CN110545119A (en) | Portable communication cloud terminal equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160330 |