CN108945530A - A kind of satellite and the rocket separation Design of Signal and its analogy method - Google Patents
A kind of satellite and the rocket separation Design of Signal and its analogy method Download PDFInfo
- Publication number
- CN108945530A CN108945530A CN201810621262.8A CN201810621262A CN108945530A CN 108945530 A CN108945530 A CN 108945530A CN 201810621262 A CN201810621262 A CN 201810621262A CN 108945530 A CN108945530 A CN 108945530A
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- Prior art keywords
- satellite
- rocket
- signal
- separation
- rocket separation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Abstract
The invention discloses a kind of satellite and the rocket separation Design of Signal and its analogy methods, the 28V satellite busbar voltage that two-way is isolated is divided respectively to the signal of 10V using resistance, plug and socket respectively through two satellite and the rocket separation connectors, it send the user terminal to satellite and the rocket separation signal to do again and separates indication signal with logical operation to get the satellite and the rocket；The satellite and the rocket are separated into signal from satellite and the rocket separation connector and its ground wire leads to ground, the two is shorted by ground relay and realizes simulation satellite and the rocket separation.The present invention, which can solve the problem of safely and reliably to generate after satellite is separated with carrier rocket, carries out the simulation satellite and the rocket separation when satellite and the rocket separate signal and ground test, including the satellite and the rocket divide the discrete analog satellite and the rocket to separate two parts.Implementation method of the present invention is simple, reliable, and improves the safety of satellite and the rocket demultiplexing circuit；Ground test is convenient, and does not reduce the reliability of satellite and the rocket demultiplexing circuit on star.
Description
Technical field
The present invention relates to aerospace electron message area, separation indication signal is generated after especially suitable spacecraft separation,
To meet the needs of safe and reliable generation of spacecraft separates signal.
Background technique
Satellite is transported by carrier rocket powered phase, after reaching planned orbit, need to complete the separation of satellite and carrier rocket.
After the completion of satellite and the rocket separating action, satellite generates the satellite and the rocket and separates signal, send to spaceborne computer.Spaceborne computer is according to this signal solution
Except the power supply locking of priming system, thruster, start the automatic ignition timing of satellite priming system, Satellite attitude and orbit control software starts to eliminate
Attitude of satellite initial deviation, just catch the earth, essence catch earth etc. movement.Therefore the satellite and the rocket separate the safe and reliable generation of signal extremely
It is important, once it exception occurs, it may cause satellite priming system, jet malfunction before satellite and the rocket separation, may be led after satellite and the rocket separation
Cause the key operations such as the capture earth, priming system igniting that cannot normally start.
The satellite and the rocket separation signal power source of part satellite uses active and standby homologous design, is unfavorable for Fault Isolation；Part satellite
Satellite and the rocket separation Design of Signal first directly send busbar voltage to separation connector, then is divided, and satellite voltage exists
Short-circuit risks；When the design of satellites satellite and the rocket separation simulation of part, by relay string in satellite and the rocket separation signal generating circuit, pass through ground
Face controls the disconnection of the relay to simulate satellite and the rocket separation, reduces the reliability of in-orbit satellite and the rocket separation signal, and the method also needs
Star Up Highway UHW voltage is led into ground, there are busbar short-circuit security risks.
Summary of the invention
In order to ensure satellite and the rocket separation signals security, it is reliable generate, when ground test, is easy to carry out to simulate satellite and the rocket separation, and not
The reliability for reducing satellite and the rocket separation, the invention proposes a kind of safe and reliable satellite and the rocket separation signal generation and analogy methods.
The invention is realized by the following technical scheme:
A kind of satellite and the rocket separation Design of Signal and its analogy method, comprising the following steps:
S1, the busbar voltage that satellite two-way is isolated is divided respectively to 10V low voltage signal；
S2,10V low voltage signal and ground wire are sent through cable, separation connector to user terminal；
S3, two paths of signals separate signal by obtaining the satellite and the rocket with logical operation, and high level is before the satellite and the rocket separate, and low level is
After satellite and the rocket separation；
S4, two-way low voltage signal and ground wire are sent to separation connector, by being shorted between separation connector point, are obtained
To two-way simulation satellite and the rocket separation signal and its ground wire；
S5, the connection that the simulation satellite and the rocket separate signal and its ground wire is controlled by ground relay, to realize the simulation satellite and the rocket point
From.
The invention has the following advantages:
1) power supply using the busbar voltage of two-way isolation as satellite and the rocket separation signal reduces satellite and the rocket separation signal power source
The risk of power supply；
2) first busbar voltage is divided to 10V, then sent through cable, separation connector to user terminal, cable and separation electricity
Voltage is lower on connector, improves the safety of system；
3) it is low level that separation front signal, which is after high level, separation, and system rejection to disturbance and fault-tolerant ability are strong, any one point
It is accidentally separated from electric connector, satellite and the rocket separation signal will not be generated；
4) satellite and the rocket need to only be separated signal by the separation of the simulation satellite and the rocket and ground is shorted, easy to operate, and control relay on ground,
The circuit on star is simplified, the reliability in circuit on star is improved；
5) the line packet power supply for controlling relay is provided by ground, and satellite 28V bus will not lead to ground, star power supply it is complete
Isolation, it is ensured that the safety of satellite power supply.
In conclusion there is biggish practical meaning using the satellite and the rocket proposed by the invention separation signal generation and analogy method
Justice.
Detailed description of the invention
Fig. 1 is the generation of satellite and the rocket separation signal and principle of simulation figure in a specific embodiment of the invention.
Specific embodiment
Below in conjunction with the drawings and specific embodiments to the star proposed by the present invention suitable for the real-time continuous monitoring in the space-based whole world
The double cluster network systems in ground are described in further detail.
Referring to Fig.1, a kind of separation signal generation of satellite and the rocket and analogy method of the embodiment of the present invention, includes the following steps:
(1) satellite busbar voltage 28V A is divided through resistance R1, R2 to 10V low voltage signal after diode D1 isolation；
(2) 10V low voltage signal and ground wire are sent by cable to the socket of separation connector (hereinafter referred to as dividing slotting), are inserted
The contact of head and socket corresponds, and it is a and d that the satellite and the rocket, which separate corresponding point of contact for inserting 1 plug of information and ground wire, as shown in Figure 1；
(3) a point a contact for slotting 1 plug is connect by two conducting wires with b, c contact, then passes through two conducting wires for d contact
It is connect with e, f contact；
(4) a point h contact for slotting 2 plugs is connect by two conducting wires with i, j contact, then passes through two conducting wires for k contact
It is connect with l, m contact；
(5) the b contact that point will insert 1 and the i contact for point inserting 2 are respectively led into an anode of diode D2, D4, two diodes
Output directly combining directly obtains the satellite and the rocket separation signal, complete two paths of signals and logical operation；
(6) the e contact for inserting 1 will be divided and the l contact for inserting 2 is divided directly to be combined, as satellite and the rocket separation signal ground；
(7) contact q that point c contact of slotting 1 socket is led to relay J1, will divide the f contact for inserting 1 socket to lead to relay
The r contact of J1；
(8) contact t that point m contact of slotting 2 sockets is led to relay J1, will divide the j contact for inserting 2 sockets to lead to relay
The s contact of J1；
(9) when ground test, q, r of relay J1 is got an electric shock and are shorted, s, t electric shock are shorted, that is, realize simulation satellite and the rocket separation.
Particular embodiments described above, the technical issues of to solution of the invention, technical scheme and beneficial effects carry out
It is further described, it should be understood that the above is only a specific embodiment of the present invention, is not limited to
The present invention, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in this
Within the protection scope of invention.
Claims (5)
1. a kind of satellite and the rocket separation Design of Signal and its analogy method, which comprises the following steps:
S1, the busbar voltage that satellite two-way is isolated is divided respectively to 10V low voltage signal；
S2,10V low voltage signal and ground wire are sent through cable, separation connector to user terminal；
S3, two paths of signals separate signal by obtaining the satellite and the rocket with logical operation；
S4, two-way low voltage signal and ground wire are sent to separation connector, by being shorted between separation connector point, obtain two
Simulate satellite and the rocket separation signal and its ground wire in road；
S5, the connection that the simulation satellite and the rocket separate signal and its ground wire is controlled by ground relay, to realize simulation satellite and the rocket separation.
2. a kind of satellite and the rocket separation Design of Signal as described in claim 1 and its analogy method, which is characterized in that satellite and the rocket separation letter
The source of breath is the satellite busbar voltage of two-way isolation.
3. a kind of satellite and the rocket separation Design of Signal as described in claim 1 and its analogy method, which is characterized in that first by bus electricity
Pressure is divided to lower voltage, then is sent through cable to separation connector.
4. a kind of satellite and the rocket separation Design of Signal as described in claim 1 and its analogy method, which is characterized in that pass through separation electricity
It is shorted between the contact of connector, realizes the branch of satellite and the rocket separation signal, obtain simulation satellite and the rocket separation signal.
5. a kind of satellite and the rocket separation Design of Signal as described in claim 1 and its analogy method, which is characterized in that by ground after
Electric appliance will simulate satellite and the rocket separation signal and be shorted, to realize simulation satellite and the rocket separation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810621262.8A CN108945530B (en) | 2018-06-15 | 2018-06-15 | Satellite-rocket separation signal simulation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810621262.8A CN108945530B (en) | 2018-06-15 | 2018-06-15 | Satellite-rocket separation signal simulation method |
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| Publication Number | Publication Date |
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| CN108945530A true CN108945530A (en) | 2018-12-07 |
| CN108945530B CN108945530B (en) | 2020-10-27 |
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| CN201810621262.8A Active CN108945530B (en) | 2018-06-15 | 2018-06-15 | Satellite-rocket separation signal simulation method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562498A (en) * | 2019-10-08 | 2019-12-13 | 深圳航天东方红海特卫星有限公司 | Star and arrow separation is from last electric circuit |
| CN112520067A (en) * | 2020-12-07 | 2021-03-19 | 山东航天电子技术研究所 | Satellite autonomous power-up circuit after separation of satellite and rocket and control method thereof |
| CN113636111A (en) * | 2021-08-24 | 2021-11-12 | 上海卫星工程研究所 | Spacecraft electromechanical separation signal hybrid use system, method and medium |
| CN113665851A (en) * | 2021-08-31 | 2021-11-19 | 上海卫星工程研究所 | Initiating explosive device separation signal locking circuit for deep space detection |
| CN113682499A (en) * | 2021-08-10 | 2021-11-23 | 北京空间飞行器总体设计部 | Spacecraft multi-space separation method |
| CN115200424A (en) * | 2022-09-08 | 2022-10-18 | 东方空间技术(山东)有限公司 | Ground equivalent separation testing device and method for carrier rocket |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2013104168A (en) * | 2013-01-30 | 2014-08-10 | Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решётнева" | METHOD FOR PRODUCING SPACE VEHICLE |
| KR101459048B1 (en) * | 2010-12-30 | 2014-11-12 | 한국항공우주연구원 | Regulator and driving apparatus of satellite separation device including it |
| CN203951254U (en) * | 2014-03-21 | 2014-11-19 | 北京机电工程研究所 | One comes off to power and disconnects control circuit |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| CN105883011A (en) * | 2015-01-23 | 2016-08-24 | 北京空间飞行器总体设计部 | Platform interface system for parallel running double-platform spacecraft |
-
2018
- 2018-06-15 CN CN201810621262.8A patent/CN108945530B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101459048B1 (en) * | 2010-12-30 | 2014-11-12 | 한국항공우주연구원 | Regulator and driving apparatus of satellite separation device including it |
| RU2013104168A (en) * | 2013-01-30 | 2014-08-10 | Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решётнева" | METHOD FOR PRODUCING SPACE VEHICLE |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| CN203951254U (en) * | 2014-03-21 | 2014-11-19 | 北京机电工程研究所 | One comes off to power and disconnects control circuit |
| CN105883011A (en) * | 2015-01-23 | 2016-08-24 | 北京空间飞行器总体设计部 | Platform interface system for parallel running double-platform spacecraft |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562498A (en) * | 2019-10-08 | 2019-12-13 | 深圳航天东方红海特卫星有限公司 | Star and arrow separation is from last electric circuit |
| CN110562498B (en) * | 2019-10-08 | 2022-04-12 | 深圳航天东方红海特卫星有限公司 | Star and arrow separation is from last electric circuit |
| CN112520067A (en) * | 2020-12-07 | 2021-03-19 | 山东航天电子技术研究所 | Satellite autonomous power-up circuit after separation of satellite and rocket and control method thereof |
| CN113682499A (en) * | 2021-08-10 | 2021-11-23 | 北京空间飞行器总体设计部 | Spacecraft multi-space separation method |
| CN113682499B (en) * | 2021-08-10 | 2023-03-28 | 北京空间飞行器总体设计部 | Spacecraft multi-space separation method |
| CN113636111A (en) * | 2021-08-24 | 2021-11-12 | 上海卫星工程研究所 | Spacecraft electromechanical separation signal hybrid use system, method and medium |
| CN113636111B (en) * | 2021-08-24 | 2023-08-18 | 上海卫星工程研究所 | Spacecraft electromechanical separation signal mixed use system, method and medium |
| CN113665851A (en) * | 2021-08-31 | 2021-11-19 | 上海卫星工程研究所 | Initiating explosive device separation signal locking circuit for deep space detection |
| CN115200424A (en) * | 2022-09-08 | 2022-10-18 | 东方空间技术(山东)有限公司 | Ground equivalent separation testing device and method for carrier rocket |
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|---|---|
| CN108945530B (en) | 2020-10-27 |
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