CN106873705A - A kind of retrievable satellite method of controlling security - Google Patents
A kind of retrievable satellite method of controlling security Download PDFInfo
- Publication number
- CN106873705A CN106873705A CN201611249661.3A CN201611249661A CN106873705A CN 106873705 A CN106873705 A CN 106873705A CN 201611249661 A CN201611249661 A CN 201611249661A CN 106873705 A CN106873705 A CN 106873705A
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- Prior art keywords
- priming system
- negative wire
- instruction
- satellite
- ground
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Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05F—SYSTEMS FOR REGULATING ELECTRIC OR MAGNETIC VARIABLES
- G05F1/00—Automatic systems in which deviations of an electric quantity from one or more predetermined values are detected at the output of the system and fed back to a device within the system to restore the detected quantity to its predetermined value or values, i.e. retroactive systems
- G05F1/10—Regulating voltage or current
- G05F1/625—Regulating voltage or current wherein it is irrelevant whether the variable actually regulated is ac or dc
Abstract
The invention discloses a kind of retrievable satellite method of controlling security, the method devises priming system main track short circuit plug, in transport and test, by the positive and negative end short circuit of priming system, so as to ensure that priming system uses preceding safety.The method devises priming system negative wire and connects plug, is only just connected between priming system negative wire and power supply buses in test and before penetrating, so as to ensure the security before penetrating.The method sets switch of the on/off by order-driven also in the supply line of power supply buses and each Fire load, these switches are that the instruction just sent by ground after transmitting is entered the orbit is connected, so as to ensure that priming system will not be triggered in the ground stage, and cause serious consequence.
Description
Technical field
The present invention relates to security control field, and in particular to a kind of product for jeopardizing safety satellite comprising Fire load etc.
Method of controlling security.
Background technology
Retrievable satellite in order to meet satellite in orbit, load it is in-orbit experiment and return capsule normally return the need for, it is past
Toward the numerous Fire load of installation number is needed, thrown with the bullet for completing antenna house and radiator protective cover, and complete return phase two
Cabin first separation, secondary separation, disconnection device unblock, parachute-opening etc. are acted, it is ensured that the recovery capsule for carrying life class sample is smoothly reclaimed.
If the unexpected detonation of Fire load occur during in test or in orbit or not detonating, gently then cause damage of product, it is heavy then
Cause satellite experiment mission failure, it is impossible to realize its scientific goal, while bringing serious economy and political fallout.
Common method of controlling security design lacks systematicness, and the safety control measures of body are often only derived from from danger
Account for, less is considered to system-level security control side, cause safety control strategy to design and lack comprehensive and systematicness, shadow
The lifting of whole star security control validity and reliability is rung.
The content of the invention
In view of this, the invention provides a kind of retrievable satellite method of controlling security, controlled safely from satellite Fire load
System, two aspects of instruction secure control carry out system security controls strategy design, it is ensured that satellite is from test, in orbit to return
The security control of overall process, comprehensive, system, can effectively lift the validity and reliability of whole star security control.It is especially suitable
In the security control comprising a large amount of Fire loads and the retrievable satellite for having strict implement timing requirements.
In order to solve the above-mentioned technical problem, the present invention is realized in：
A kind of retrievable satellite method of controlling security, including following security control means：
First, increase priming system main track short circuit plug newly and connect plug with priming system negative wire；The priming system main track short circuit plug
Include the positive and negative terminal short circuit circuit of multichannel priming system；
Wherein, during ground test and whole luck are defeated, priming system main track is replaced to insert with priming system main track short circuit plug
Seat is connected on priming system main track plug so that the positive and negative end short circuit of all of priming system igniter；Priming system negative wire is connected and inserted
Head connects negative wire/test jack in ground test, so as to priming system negative wire terminal be connected with power supply terminal；Filled in delivery
Before, priming system main track short circuit plug is removed, connect priming system main track plug and the positive line socket of priming system；Will when preparing before penetrating
Priming system negative wire is connected plug and is connected in negative wire/test jack；
The 2nd, switch of the break-make by order-driven be set on priming system priming supply power supply buses, and the switch enters in satellite
The instruction sent by ground after rail is connected；
3rd, in the supply line between priming system priming supply power supply buses and each Fire load, set break-make by
The switch of order-driven, these switches are that the instruction sent by ground after entering the orbit is connected；
4th, for entering the orbit during influence the key instruction of success or failure, same key instruction entered by least two passages
Row transmission；
The 5th, journey is set on star in software and returns mark, and journey is injected by ground and return instruction unblock；Software performs journey and returns on star
During dependent instruction, first determine whether that journey returns mark, could only be performed when journey is returned and is masked as unblock；
6th, the formal emphasis execution moment T0 to be acted that ground passes through house-keeping instruction, when software performs this on star
Between T0 as significant data preserve；Not yet reached in execution moment T0, and in the case of generation system reset, resetted on star
Significant data recovery is independently carried out afterwards.
Preferably, priming system negative wire protection cap, during whole luck is defeated, priming system negative wire protection cap lid are further increased newly
In negative wire/test jack.
Preferably, emergency cutoff and inside and outside electrical switch are further set, are switched for the power supply of satellite to be originated
It is on star or ground；The emergency cutoff and inside and outside electrical switch are controlled by interior dispatch from foreign news agency conversion instruction and emergency cutoff order
System；Before facing and penetrating, priming system main track is accessed, negative wire has been turned on, in Quan Xingzhuan electricity and it is de- insert come off in the case of, once
There is exception on star, by emergency cutoff order, make the emergency cutoff and inside and outside electrical switch be switched to ground power supply
Power supply.
Preferably, satellite and the rocket separating switch is further set, and the action triggers satellite and the rocket separating switch that satellite with delivery separate connects
It is logical；After satellite and the rocket separating switch is connected, could allow to act autonomous execution on star.
Preferably, further the lock-out state that the journey returns mark is preserved as significant data, and it is multiple in system
Recover automatically behind position.
Preferably, after the method is recovered to perform moment T0 after the reset, and after corresponding actions are performed after the T0 moment reaches,
Postpone setting time independently to repeat once again.
Beneficial effect：
The design of safety satellite control strategy is the important step for ensureing lifetime of satellite cycle overall process safety from top layer,
It is to ensure that satellite can smoothly complete the premise of its mission.According to the characteristics of retrievable satellite, from Fire load security control, refer to
Make the links such as security control carry out system-level method of controlling security to design, whole star safety has been effectively ensured, be other similar boats
The security control design of its device is provided to be used for reference.
(1) present invention devises priming system main track short circuit plug, in transport and test, by the positive and negative end short circuit of priming system,
So as to ensure that priming system uses preceding safety.
(2) present invention devises priming system negative wire and connects plug, is only just connected to priming system negative wire in test and before penetrating
And power supply buses between, so as to ensure the security before penetrating.
(3) present invention sets on/off opening by order-driven in the supply line of power supply buses and each Fire load
Close, these switches are the instruction connections just sent by ground behind heaven, so as to ensure that priming system will not be by the ground stage
Triggering, and cause serious consequence.
(4) present invention by key instruction backup, journey return lock locking/unlocking mark and significant data automatically store with it is extensive
Multiple function, realizes instruction secure control, so as to ensure that the Successful transmissions of key instruction, journey return the normal execution of instruction, Yi Jichong
The preservation and recovery of data are wanted, so as to ensure the safety of priming system.
Brief description of the drawings
Fig. 1 is Fire load ignition control circuit figure.
Fig. 2 is the control program schematic diagram that power supply buses control corresponding Fire load.
Specific embodiment
Develop simultaneously embodiment below in conjunction with the accompanying drawings, and the present invention will be described in detail.
To ensure the correctness of operation on orbit, from retrievable satellite development to transmitting, from in-orbit flight to landing is returned, need
Verified by the test of multiple Major Ground Test.The present invention according to whole star products configuration, whole star mode of operation and workflow,
Self-characteristic, security control factor and the course of work from product enter to the potential link for influenceing whole star safety control strategy design
Row analysis, controls safely to influenceing the Fire load security control of whole star safety, instruction secure to control the two aspects to carry out system
System strategy design, it is ensured that satellite from test, in orbit to return overall process security control, this be satellite ground test and
The important guarantee of rail operation safety, is also the successful premise of test mission.
(1) Fire load security control
The ignition security control design case thinking of Fire load is：For each ignition condition of Fire load, by setting fire
Frock is put main track, Fire load negative wire, 4 security control links of power supply buses control and firing command output and control and realizes fire
Frock puts security control.Fire load is set to light a fire, it is necessary to the circuit for including Fire load is formed loop, and be allowed to detonate
Operating current.Fire load main track represents priming system in itself, and the access of Fire load main track is the premise of Fire load igniting,
Fire load negative wire then connects power supply negative pole, and power supply buses control the break-make of working power, and firing command is then control fire
Frock puts the final tache of detonation.
(1) the security control link of Fire load main track, Fire load negative wire
As shown in figure 1, newly-increased priming system main track short circuit plug 1, priming system negative wire protection cap 2 is connected with priming system negative wire and inserted
First 3.The main track plug 4 and positive line socket 5 of the priming system in figure are existing.Priming system main track short circuit plug 1 includes multichannel
The positive and negative terminal short circuit circuit of priming system.
During whole luck is defeated, priming system main track plug 4 needs to remain off with the positive line socket 5 of priming system, this
Invention priming system main track short circuit plug 1 is connected on priming system main track plug 4 instead of the positive line socket 5 of priming system so that all
Priming system igniter positive and negative end short circuit.Meanwhile, priming system negative wire protection cap 2 is covered in negative wire/test jack 6, to prevent
External disturbance causes the misconnection of priming system negative wire and power supply.Wherein, negative wire/test jack 6 contains negative wire socket and test
Socket, shares same socket.Negative wire/test jack 6 specifically includes priming system ground test terminal, the test of current-limiting resistance resistance
Terminal, negative wire terminal and power supply terminal；Priming system ground test terminal has n, in the man-to-man connection positive line socket 5 of priming system
The n main track of priming system, current-limiting resistance resistance calibrating terminal separates n bar branch roads, and every branch road connects n by a current-limiting resistance
The main track of individual priming system；Negative wire terminal connects the n negative wire of priming system；Power supply terminal is by switching connection priming system priming supply
Power supply buses.
In usually ground test, if test main track, then priming system main track short circuit plug 1 is connected to priming system main track
On plug 4, the positive line socket 5 of priming system connects the priming system simulator for simulating priming system resistance, and priming system negative wire protection cap 2 is gone
Fall, priming system negative wire is connected between the priming system negative wire terminal and power supply terminal that plug 3 accesses negative wire/test jack 6, so that will
The two is connected.Here, priming system negative wire terminal connects the negative wire terminal of each priming system in the positive line socket 5 of priming system.Priming system
Negative wire connects the negative wire socket part that plug 3 only just connects negative wire/test jack 6 in test, to ensure security.
In usually ground test, if test current-limiting resistance, then connected mode is essentially identical with test main track, simply
Priming system simulator need not be connected.Priming system ground test point and current-limiting resistance resistance of the tester from negative wire/test jack 6
Current-limiting resistance test is carried out between test point.
Before filling is delivered, priming system main track short circuit plug 1 is removed, connection priming system main track plug 4 is with priming system just
Line socket 5.Priming system negative wire connection plug 3 is connected when preparing before penetrating, to ensure safety.
(2) power supply buses controlling unit
Fire load priming supply power supply buses are set, the on/off of the bus by order-driven switch.Fill firer
Igniting is put in addition to needing to send firing command, circuit also needs to logical power supply buses, priming system main track plug and socket company on star
Connect, priming system negative wire connects plug connection, this ensure that the security of priming system control.Bus controlling switch in Fig. 1 and
There is display in Fig. 2.Multiple priming systems in Fig. 1 are combined into a Fire load.Fig. 2 is the schematic diagram of multiple Fire loads.
Multiple Fire loads share a power supply buses, set on the bus by on/off by order-driven switch.The switch is being defended
The instruction that star is just sent after entering the orbit by ground is connected.
(3) firing command output and controlling unit
As depicted in figs. 1 and 2, in the supply line between bus and each Fire load, on/off is set and is driven by instruction
Dynamic switch, these switches are the instruction connections just sent by ground after satellier injection.
(4) other switch controls
Emergency cutoff and inside and outside electrical switch are set.
The switch is controlled by interior dispatch from foreign news agency conversion instruction and emergency cutoff order.Before facing and penetrating, changed by interior dispatch from foreign news agency and referred to
It is that battery is self-powered on star to make power switching on star, i.e., full star turns interior electricity.Access in priming system main track, negative wire has been turned on, entirely
Star turn in electricity and it is de- insert come off in the case of, once occurring abnormal on star, can make urgent by emergency cutoff order
Shutdown and inside and outside electrical switch are switched to ground power supply and power, and battery is powered on cut-out star in time.Due to ground power supply
Break-make is controllable, therefore such design can avoid Fire load from detonating by mistake, is reduced as far as possible caused by abnormal conditions
It is dangerous.
Secondly, satellite and the rocket separating switch is set, and satellite and the rocket separating switch is mechanical switch, when satellite is separated with delivery, is passed through
Machinery triggering makes switch connection.After satellite and the rocket separating switch is connected, could allow to act autonomous execution on star.Otherwise, priming system
The action such as control signal, unlocking signal can not uniformly be performed.
Additionally, before satellite is returned, power supply must be sent to instrument by satellite unlock instruction under conditions of respective bus bars connection
Cabin could perform, so as to ensure that Fire load mis-ignition will not be caused due to missing instruction, and cause serious consequence.
(2) instruction secure control
Instruction secure control method includes 3 aspects：(1) for entering the orbit during influence success or failure key instruction, be all provided with
The instruction of meter different type or different passages is mutually backed up；(2) identified by Software for Design locking/released state, be only in
During released state, software could perform corresponding key operations, and the change of status indicator need to be realized by noting instruction on ground；
(3) significant data storage and recovery routine automatically are set, significant data can be independently carried out in the case of resetting, on star extensive
It is multiple.
Specifically：
(1) for entering the orbit during influence success or failure key instruction, same key instruction can by direct instruction,
At least 2 kinds connect in instruction and bus command are transmitted, to realize that different type or the instruction of different passages are mutually backed up.From
And for influenceing the key instruction of success or failure, it is ensured that instruction secure, reliability, so that the priming system that the process that ensures to enter the orbit is used
Successful action.
(2) journey is set on star in software and returns lock locking/unlocking mark.Software performs (noted on autonomous execution or ground) journey on star
, it is necessary to first determine whether that journey returns whether mark locks when returning dependent instruction.When journey returns instruction locking, software is forbidden performing journey on star
Return instruction.Journey returns instruction lock-out state to be needed to be preserved as significant data, and initial value is lock-out state, only when ground is noted
Enter after journey returns instruction unlock instruction, journey returns mark and is changed into unblock, just performs corresponding journey and returns instruction, so as to ensure to be returned to journey related
Priming system safety.
(3) present invention design significant data is stored and recovers function automatically.Before satellite performs important action, ground is in
The execution moment T0 that the formal note respective bus of instruction of being engaged in are instructed, software protects this execution time T0 as significant data on star
Deposit, not yet reached in execution moment T0, and in the case of generation system reset, independently carry out significant data on star after the reset
Recover；Further, after performing the bus command at T0 moment, the instruction is independently repeated again after certain hour is postponed on star
Once.For the instruction for having performed, performing will not have an impact again to control object.For example after ON switch send again and connect
Logical instruction.
In sum, presently preferred embodiments of the present invention is these are only, is not intended to limit the scope of the present invention.
All any modification, equivalent substitution and improvements within the spirit and principles in the present invention, made etc., should be included in of the invention
Within protection domain.
Claims (6)
1. a kind of retrievable satellite method of controlling security, it is characterised in that including following security control means：
First, increase priming system main track short circuit plug (1) newly and plug (3) is connected with priming system negative wire；The priming system main track short circuit is inserted
Head (1) includes the positive and negative terminal short circuit circuit of multichannel priming system；
Wherein, during ground test and whole luck are defeated, the positive line socket of priming system is replaced with priming system main track short circuit plug (1)
(5) it is connected on priming system main track plug (4) so that the positive and negative end short circuit of all of priming system igniter；Priming system negative wire connects
Logical plug (3) connects negative wire/test jack (6) in ground test, so as to priming system negative wire terminal be connected with power supply terminal；
Before filling is delivered, priming system main track short circuit plug (1) is removed, connection priming system main track plug (4) is inserted with priming system main track
Seat (5)；Priming system negative wire is connected into plug (3) when preparing before penetrating to be connected in negative wire/test jack (6)；
The 2nd, switch of the break-make by order-driven be set on priming system priming supply power supply buses, and the switch is after satellier injection
The instruction sent by ground is connected；
3rd, in the supply line between priming system priming supply power supply buses and each Fire load, break-make is set by instructing
The switch of driving, these switches are that the instruction sent by ground after entering the orbit is connected；
4th, for entering the orbit during influence the key instruction of success or failure, same key instruction passed by least two passages
It is defeated；
The 5th, journey is set on star in software and returns mark, and journey is injected by ground and return instruction unblock；Software performs journey and returns correlation on star
During instruction, first determine whether that journey returns mark, could only be performed when journey is returned and is masked as unblock；
6th, the formal emphasis execution moment T0 to be acted that ground passes through house-keeping instruction, this is performed time T0 by software on star
Preserved as significant data；Not yet reached in execution moment T0, and in the case of generation system reset, on star after the reset certainly
Master carries out significant data recovery.
2. retrievable satellite method of controlling security as claimed in claim 1, it is characterised in that further increase priming system negative wire newly
Protection cap (2), during whole luck is defeated, priming system negative wire protection cap (2) is covered in negative wire/test jack (6).
3. retrievable satellite method of controlling security as claimed in claim 1, it is characterised in that further set emergency cutoff with
And inside and outside electrical switch, for the power supply source of satellite to be switched on star or ground；The emergency cutoff and interior dispatch from foreign news agency turn
Switch is changed to be controlled by interior dispatch from foreign news agency conversion instruction and emergency cutoff order；Before facing and penetrating, priming system main track is accessed, negative wire has connect
In logical, Quan Xingzhuan electricity and it is de- insert come off in the case of, once occurring abnormal on star, by emergency cutoff order, order is described
Emergency cutoff and inside and outside electrical switch are switched to ground power supply and power.
4. retrievable satellite method of controlling security as claimed in claim 1, it is characterised in that the satellite and the rocket are further set and are separated
Close, the action triggers satellite and the rocket separating switch that satellite with delivery separate is connected；After satellite and the rocket separating switch is connected, could allow to be moved on star
Make autonomous execution.
5. retrievable satellite method of controlling security as claimed in claim 1, it is characterised in that mark further is returned to the journey
Lock-out state preserved as significant data, and recover automatically after system reset.
6. retrievable satellite method of controlling security as claimed in claim 1, it is characterised in that the method is recovered to hold after the reset
After row moment T0, and after corresponding actions are performed after the T0 moment reaches, postpone setting time and independently repeat once again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611249661.3A CN106873705A (en) | 2016-12-29 | 2016-12-29 | A kind of retrievable satellite method of controlling security |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611249661.3A CN106873705A (en) | 2016-12-29 | 2016-12-29 | A kind of retrievable satellite method of controlling security |
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| Publication Number | Publication Date |
|---|---|
| CN106873705A true CN106873705A (en) | 2017-06-20 |
Family
ID=59164346
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611249661.3A Pending CN106873705A (en) | 2016-12-29 | 2016-12-29 | A kind of retrievable satellite method of controlling security |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753264A (en) * | 2021-09-10 | 2021-12-07 | 上海卫星工程研究所 | Method and system for high-reliability forced unfolding of solar sailboard when separation of star and arrow is abnormal |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202276048U (en) * | 2011-09-22 | 2012-06-13 | 北京机电工程研究所 | Protection plug and socket for initiating explosive device |
| CN103308818A (en) * | 2013-04-17 | 2013-09-18 | 航天东方红卫星有限公司 | Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite |
| CN203240967U (en) * | 2013-04-25 | 2013-10-16 | 北京航天自动控制研究所 | Initiating explosive device short circuit protection circuit |
| CN103399497A (en) * | 2013-07-03 | 2013-11-20 | 上海卫星工程研究所 | Integrated electronic management system for miniature Mars lander |
| CN103499244A (en) * | 2013-09-24 | 2014-01-08 | 中国空间技术研究院 | Firer device detonation control system for control through MOSFET |
| CN103997031A (en) * | 2014-05-16 | 2014-08-20 | 上海微小卫星工程中心 | Initiating explosive device control circuit and controller using same |
| CN204027462U (en) * | 2014-07-25 | 2014-12-17 | 北京航天长征飞行器研究所 | A kind of priming system that improves detonates the safety circuit of wink degree of sending out |
| US9250051B1 (en) * | 2011-03-25 | 2016-02-02 | The Boeing Company | Squib initiation sequencer |
-
2016
- 2016-12-29 CN CN201611249661.3A patent/CN106873705A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9250051B1 (en) * | 2011-03-25 | 2016-02-02 | The Boeing Company | Squib initiation sequencer |
| CN202276048U (en) * | 2011-09-22 | 2012-06-13 | 北京机电工程研究所 | Protection plug and socket for initiating explosive device |
| CN103308818A (en) * | 2013-04-17 | 2013-09-18 | 航天东方红卫星有限公司 | Testing and verifying circuit of plugging state of flying plug of initiating explosive device on satellite |
| CN203240967U (en) * | 2013-04-25 | 2013-10-16 | 北京航天自动控制研究所 | Initiating explosive device short circuit protection circuit |
| CN103399497A (en) * | 2013-07-03 | 2013-11-20 | 上海卫星工程研究所 | Integrated electronic management system for miniature Mars lander |
| CN103499244A (en) * | 2013-09-24 | 2014-01-08 | 中国空间技术研究院 | Firer device detonation control system for control through MOSFET |
| CN103997031A (en) * | 2014-05-16 | 2014-08-20 | 上海微小卫星工程中心 | Initiating explosive device control circuit and controller using same |
| CN204027462U (en) * | 2014-07-25 | 2014-12-17 | 北京航天长征飞行器研究所 | A kind of priming system that improves detonates the safety circuit of wink degree of sending out |
Non-Patent Citations (2)
| Title |
|---|
| 唐伯昶: "卫星安全性设计", 《航天器工程》 * |
| 张金祥等: "小卫星的安全性及可靠性设计", 《哈尔滨工业大学学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753264A (en) * | 2021-09-10 | 2021-12-07 | 上海卫星工程研究所 | Method and system for high-reliability forced unfolding of solar sailboard when separation of star and arrow is abnormal |
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