CN205942301U - Spacecraft telemetering measurement frame format control system that gathers and edits - Google Patents
Spacecraft telemetering measurement frame format control system that gathers and edits Download PDFInfo
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- CN205942301U CN205942301U CN201620712178.3U CN201620712178U CN205942301U CN 205942301 U CN205942301 U CN 205942301U CN 201620712178 U CN201620712178 U CN 201620712178U CN 205942301 U CN205942301 U CN 205942301U
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Abstract
The utility model discloses a spacecraft telemetering measurement frame format control system that gathers and edits, it includes: frame format control stored ware, power supply circuit, clock circuit and peripheral circuit, wherein, power supply circuit links to each other with frame format control stored ware for provide the power for frame format control stored ware, the clock circuit passes through the peripheral circuit links to each other with frame format control stored ware, and the clock circuit is used for producing the clock pulse of frame format control stored ware, is used for controlling the peripheral circuit simultaneously and produces frame format control signal, prestore has frame format control file in the frame format control stored ware, is used for the basis clock pulse with frame format control signal forms the telemetering measurement frame format of gathering and editing. The utility model discloses a spacecraft telemetering measurement frame format control system that gathers and edits has the advantage that the loss is low, longe -lived, the reliability is high, be able to bear or endure space radiation ability reinforce, can satisfy the high requirement of spacecraft remote supervising system equipment.
Description
Technical field
This utility model is related to space technology field, gathers and edits frame format control system particularly to a kind of spacecraft remote measurement.
Background technology
Spacecraft gathers and edits frame format control system in spacecraft telemetry system, according to system requirements, is formed corresponding
The remote measurement frame data of frame format, main contents include：Synchronous code, specific code, telemetering channel layout etc..
Because spacecraft runs residing spatial environmentss, spacecraft telemetry system equipment is compared with other telemetry system equipment
There is the high requirement of comparison, need to meet that user is many, low-loss, the demand of long-life, high reliability and resistance to space radiation ability by force.
Utility model content
This utility model is directed to above-mentioned problems of the prior art, proposes a kind of spacecraft remote measurement and gathers and edits frame format control
System processed, has the advantages that loss is low, life-span length, reliability are high, resistance to space radiation ability is strong, disclosure satisfy that spacecraft remote measurement system
The high request of system equipment.
For solving above-mentioned technical problem, this utility model is achieved by the following technical solution：
This utility model provides a kind of spacecraft remote measurement to gather and edit frame format control system, and it includes：Frame format controls storage
Device, power circuit, clock circuit and peripheral circuit, wherein,
Described power circuit is connected with described frame format control memory, for providing for described frame format control memory
Power supply；
Described clock circuit is connected with described frame format control memory by described peripheral circuit, and described clock circuit is used
In the clock pulses producing described frame format control memory, it is simultaneously used for controlling described peripheral circuit to produce frame format control letter
Number；
Be previously stored with frame format in described frame format control memory and control file, for according to described clock pulses and
Described frame format control signal is gathered and edited frame format forming remote measurement.
It is preferred that described peripheral circuit includes：Data-latching circuit, cadence signal circuit, frequency dividing circuit and control letter
Number circuit, wherein, described frequency dividing circuit and described cadence signal circuit are used for producing control signal, read described frame format and control
The frame format prestoring in memorizer controls file, then is generated by described data-latching circuit and described control signal circuit
Frame format control signal.
It is preferred that described power circuit includes：Interconnective wave filter and DC/DC transducer, the one of outside input
Secondary voltage inputs described DC/DC transducer after described wave filter, produces the work needed for described frame format control memory
Piezoelectric voltage；Setting DC/DC transducer, can provide all kinds of power supplys for system operation.
It is preferred that described clock circuit includes：Crystal oscillator, enumerator, decoder and nor gate, wherein, crystal oscillator is used for producing
Raw initial clock, then by described nor gate, described enumerator and described decoder shaping and required for generation system after dividing
Clock.
It is preferred that described form controls file to include：Remote measurement frame format control sequential parameter, synchronization character and special word.
It is preferred that described frame format control memory is disposable programmable read only memory (PROM), using anti-in design
The PROM of irradiation, to meet space long-life, high reliability and resistance to space radiation requirement by force, can not change periphery firmly simultaneously
On the premise of part circuit, only modification form controls file content, you can realize the change of control format data content.
Compared to prior art, this utility model has advantages below：
(1) the spacecraft remote measurement that this utility model provides is gathered and edited form control system, using the telemetry system of PCM system,
With low cost, low-power consumption, easily realize, easy extension way achieves telemetry-acquisition data frame format and controls, need not by CPU or
The high integrated processor software programming such as FPGA, only need to control file by changing the form storing in memory, you can realize
Different frame lengths, the remote measurement frame format of different flag of frame, this is outstanding to the space product (as airship, space station etc.) of high reliability request
For important；
(2) spacecraft remote measurement of the present utility model is gathered and edited frame format control system, using pure hardware handles structure, improves
The integrated level of system, reliability and convenience；And on the premise of not changing hardware circuit, can be to frame format length, frame lattice
The contents such as formula layout, synchronization character and special word are modified, and realize different task and require, and further increase its convenience and fit
The property used.
Certainly, implement arbitrary product of the present utility model to it is not absolutely required to reach all the above advantage simultaneously.
Brief description
Below in conjunction with the accompanying drawings embodiment of the present utility model is described further：
Fig. 1 is that spacecraft remote measurement of the present utility model is gathered and edited the schematic diagram of frame format control system；
Fig. 2 is the schematic diagram of the peripheral circuit of embodiment of the present utility model.
Label declaration：1- frame format control memory, 2- power circuit, 3- clock circuit, 4- peripheral circuit.
Specific embodiment
Below embodiment of the present utility model is elaborated, the present embodiment is being front with technical solutions of the utility model
Put and implemented, give detailed embodiment and specific operating process, but protection domain of the present utility model does not limit
In following embodiments.
In conjunction with Fig. 1-Fig. 2, frame format control system that spacecraft remote measurement of the present utility model is gathered and edited is described in detail, such as
Fig. 1 show its schematic diagram, and it includes：Frame format control memory 1, power circuit 2, clock circuit 3 and peripheral circuit 4.
Wherein, power circuit is connected with frame format control memory 1, provides power supply for it；Clock circuit 3 passes through peripheral circuit 4 and frame
Form control memory 1 is connected, and clock circuit 3 is used for producing the clock pulses needed for frame format control memory 1 works, and reads
The form being stored in frame format control memory 1 controls file, generates the control sequential of telemetry framing；It is additionally operable to simultaneously
The signals such as Control peripheral circuit generation time code, beat and sequencing contro, for the formation of remote measurement frame format；Frame format controls deposits
It is previously stored with the form comprising the contents such as remote measurement frame format control sequential parameter, synchronization character and special word in reservoir and control literary composition
Part, controls the content of file, produces telemetry group frame timing according to the clock output format that clock circuit 3 generates；Form control
The content of file processed includes：Remote measurement frame format control sequential parameter, synchronization character and special word etc., can be carried out according to mission requirements
Change, realizes the framing of different remote measurement frame formats.Example, form controls file to include：1024 frame lengths, 3 byte frame swynchronization codes, frame
The content such as format denotation and special word.
In the present embodiment, peripheral circuit includes：Data-latching circuit, cadence signal circuit, frequency dividing circuit and control letter
Number circuit, frequency dividing circuit and cadence signal circuit are used for producing control signal, read in frame format control memory and prestore
Frame format control file, then pass through data-latching circuit and control signal circuit delta frame format control signal, complete remote measurement
Data framing function.The schematic diagram of peripheral circuit as shown in Fig. 2 herein frequency dividing circuit adopt chip 54HC393, cycling circuit is adopted
Use chip 54HC138, data-latching circuit adopts chip 54HC573, and control signal circuit is by interconnective chip 54HC14
With 54HC02 composition.In different embodiments, each circuit may also be employed other chips or chip portfolio to realize corresponding work(
Energy.
In the present embodiment, clock circuit includes：The small scale integrations such as crystal oscillator, enumerator, decoder and nor gate
Composition, crystal oscillator is used for producing initial clock, then by nor gate, enumerator and decoder shaping and needed for generation system after dividing
The clock wanted.
In the present embodiment, power circuit includes：Interconnective wave filter and DC/DC transducer, the one of outside input
Secondary voltage inputs described DC/DC transducer after described wave filter, produces the work needed for described frame format control memory
Piezoelectric voltage.
Disclosed herein is only preferred embodiment of the present utility model, and this specification is chosen and specifically described these enforcements
Example, is to preferably explain principle of the present utility model and practical application, is not to restriction of the present utility model.Any
The modifications and variations that skilled person is done in the range of description, all should fall in the range of this utility model is protected.
Claims (6)
1. a kind of spacecraft remote measurement gathers and edits frame format control system it is characterised in that including：Frame format control memory, power supply
Circuit, clock circuit and peripheral circuit, wherein,
Described power circuit is connected with described frame format control memory, for providing electricity for described frame format control memory
Source；
Described clock circuit is connected with described frame format control memory by described peripheral circuit, and described clock circuit is used for producing
The clock pulses of raw described frame format control memory, is simultaneously used for controlling described peripheral circuit to produce frame format control signal；
It is previously stored with frame format in described frame format control memory and controls file, for according to described clock pulses and described
Frame format control signal is gathered and edited frame format forming remote measurement.
2. spacecraft remote measurement according to claim 1 gathers and edits frame format control system it is characterised in that described peripheral circuit
Including：Data-latching circuit, cadence signal circuit, frequency dividing circuit and control signal circuit, wherein,
Described frequency dividing circuit and described cadence signal circuit are used for producing control signal, read in described frame format control memory
The frame format prestoring controls file, then generates frame format control by described data-latching circuit and described control signal circuit
Signal processed.
3. spacecraft remote measurement according to claim 1 gathers and edits frame format control system it is characterised in that described power circuit
Including：Interconnective wave filter and DC/DC transducer, the primary voltage of outside input inputs institute after described wave filter
State DC/DC transducer, produce the running voltage needed for described frame format control memory.
4. spacecraft remote measurement according to claim 1 gathers and edits frame format control system it is characterised in that described clock circuit
Including：Crystal oscillator, enumerator, decoder and nor gate, wherein,
Crystal oscillator is used for producing initial clock, then after described nor gate, described enumerator and described decoder shaping and frequency dividing
Clock required for generation system.
5. spacecraft remote measurement according to claim 1 gathers and edits frame format control system it is characterised in that described form controls
File includes：Remote measurement frame format control sequential parameter, synchronization character and special word.
6. spacecraft remote measurement according to claim 1 gathers and edits frame format control system it is characterised in that described frame format control
Memorizer processed is disposable programmable read only memory.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620712178.3U CN205942301U (en) | 2016-07-07 | 2016-07-07 | Spacecraft telemetering measurement frame format control system that gathers and edits |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620712178.3U CN205942301U (en) | 2016-07-07 | 2016-07-07 | Spacecraft telemetering measurement frame format control system that gathers and edits |
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| CN205942301U true CN205942301U (en) | 2017-02-08 |
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| CN201620712178.3U Active CN205942301U (en) | 2016-07-07 | 2016-07-07 | Spacecraft telemetering measurement frame format control system that gathers and edits |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112533276A (en) * | 2020-11-27 | 2021-03-19 | 北京宇航系统工程研究所 | Adaptive framing design method and system based on rocket-borne wireless sensor network |
| CN114205407A (en) * | 2021-12-16 | 2022-03-18 | 北京润科通用技术有限公司 | Method and device for analyzing pulse code modulation telemetry data |
-
2016
- 2016-07-07 CN CN201620712178.3U patent/CN205942301U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112533276A (en) * | 2020-11-27 | 2021-03-19 | 北京宇航系统工程研究所 | Adaptive framing design method and system based on rocket-borne wireless sensor network |
| CN112533276B (en) * | 2020-11-27 | 2023-11-10 | 北京宇航系统工程研究所 | Self-adaptive framing design method and system based on arrow-mounted wireless sensor network |
| CN114205407A (en) * | 2021-12-16 | 2022-03-18 | 北京润科通用技术有限公司 | Method and device for analyzing pulse code modulation telemetry data |
| CN114205407B (en) * | 2021-12-16 | 2023-11-10 | 北京润科通用技术有限公司 | Method and device for analyzing pulse code modulation telemetry data |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180129 Address after: 200050 Anhua Road, Shanghai, No. 492, No. Patentee after: SHANGHAI AEROSPACE COMPUTER TECHNOLOGY INSTITUTE Address before: 200080 Shanghai city Hongkou District street Xingang Tianbao Road No. 881 Patentee before: Shanghai Aerospace Measurement Control Communication Institute |
|
| TR01 | Transfer of patent right |