CN104895700B - A kind of low time delay ignition confirming system and confirmation method of arrow ground information fusion - Google Patents
A kind of low time delay ignition confirming system and confirmation method of arrow ground information fusion Download PDFInfo
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Abstract
A kind of arrow ground low time delay ignition confirming system of information fusion and the comprehensive control device of confirmation method ground launch vehicle measurement receive " initial ignition " signal that center indication control board sends, after carrying out ladder diagram logical operation and signal condition, output " when unite zero point " signal；Flight control computer receives " when unite zero point " signal and judges whether each unit is working properly on arrow by time synchronized；If working properly, start flight control program, and will determine that result feeds back to central computer, otherwise do not start flight control program, will determine that result feeds back to central computer, and wait ground subsequent treatment；Central computer receives result on arrow, if normal output " middle igniting " signal is to comprehensive control device；After comprehensive control device receives " middle igniting " signal, output " final to light a fire " signal, second control conditioning plate of Jing ignite priming system, make the safe and reliable separation in arrow ground.
Description
Technical field
The present invention relates to a kind of low time delay ignition confirming system and method for arrow ground information fusion, belongs to vehicle launch control
Technical field processed.
Background technology
Ignition signal is the key signal in emission control technology, is separated with realizing arrow for igniting igniting priming system,
As on arrow flight control computer when unite zero point, for entering flight control solver.
As shown in figure 1, in traditional approach, comprehensive control device receives " the initial ignition signal " of center indication control board
Afterwards, after carrying out logical operation and signal condition, while output " final ignition signal " and " when unite zero signal ", drive respectively
Igniting priming system and startup flight control solver.There is problems with traditional design scheme：If drive ignition priming system
While arrow on equipment or application state exception, do not normally enter flight control program, at the same time light a fire priming system detonate,
Rocket body takes off, and launch mission will necessarily be caused to fail.
The content of the invention
The present invention technology solve problem be：Overcome the deficiencies in the prior art, there is provided a kind of arrow ground information fusion it is low
Time delay ignition confirming system and method, by arrow ground information fusion technology, monitors state on the arrow before rocket takes off, was lighting a fire
Coordinate and validation of information while arrow is carried out in journey, improve the reliability of rocket launching.
The present invention technical solution be：
A kind of low time delay ignition confirming system of arrow ground information fusion includes：Fly control to calculate on ground launch vehicle measurement and arrow
Machine；Ground launch vehicle measurement includes comprehensive control device, center indication control board and central computer again；
Center indication control board, is User Interface, provides " initial ignition " signal to comprehensive control device；
Comprehensive control device, receives " initial ignition " signal that center indication control board sends, carry out ladder diagram logical operation with
And after signal condition, output " when unite zero point " signal is to flight control computer on arrow；Comprehensive control device receives middle scheming simultaneously
After " middle igniting " instruction of calculation machine, ladder diagram logical operation process is carried out, output " final to light a fire " control signal ignites igniting
Priming system and output " bus control signal " disconnect bus-controlled switching.
Central computer, gathers on arrow whether each stand-alone device work normally adjudicates knot on the arrow of flight control computer feedback
Really, and when stand-alone device normal work, " middle igniting " instruction is sent to comprehensive control device；
Flight control computer on arrow, after receiving " when unite zero point " signal, the time on current arrow is reset, and other lists on arrow
Machine equipment sends and performs time synchronized operational order；Meanwhile, on arrow, flight control computer is fed back by each stand-alone device for receiving
Time synchronized situation, judge on arrow whether crucial unit working properly, and the result that will determine that feed back to ground and surveys and sends out control system
The central computer of system, while flight control computer starts flight control computing under each stand-alone device normal operation on arrow.
Comprehensive control device includes PLC, first control modulate circuit and second control modulate circuit；
First control modulate circuit includes relay K11, K12 again；Second control modulate circuit again include relay Kdh1,
Kdh2, Kdh3 and Kdh4；
The line bag of relay K11, K12 is in parallel；The contact K12A of the contact K11A and K12 of relay K11 is in parallel, contact
K11B and K12B is in parallel, is serially connected after parallel connection again；
The line bag of relay Kdh1, Kdh2, Kdh3 and Kdh4 is in parallel；The contact Kdh1A's and Kdh2 of relay Kdh1 touches
Point Kdh2A is in parallel, and contact Kdh1B and Kdh2B are in parallel, is serially connected after parallel connection again；The contact Kdh3A and Kdh4 of relay Kdh3
Contact Kdh4A it is in parallel, contact Kdh3B and Kdh4B are in parallel, parallel connection after be serially connected again；
The output end of PLC connects the line bag and total line traffic control of relay K11, K12, Kdh1, Kdh2, Kdh3 and Kdh4 respectively
System switch.
Present invention additionally comprises：Electromagnetic relay Kyx1, Kyx2, Kzdh1 and Kzdh2；
The contact Kzdh2A of the contact Kzdh1A and Kzdh2 of relay Kzdh1 is in parallel, and contact Kzdh1B and Kzdh2B are simultaneously
Connection, is serially connected after parallel connection again, all contacts of input connection relay Kdh1, Kdh2 and output of connecting of the series connection；
The contact Kyx2A of the contact Kyx1A and Kyx2 of relay Kyx1 is in parallel, and contact Kyx1B and Kyx2B are in parallel, in parallel
It is serially connected again afterwards, the input of the series connection connects all contacts of Kzdh1 and Kzdh2 the output connected.
Sending out a control modulate circuit and can expand to N number of according to demand in comprehensive control device, N number of control modulate circuit is specifically real
Now according to concrete function realizing.
Central computer includes CPU, 1553B bus interface module, switching value output module；Switching value output module is wrapped again
Include solid-state relay 1, solid-state relay 2, solid-state relay 3, solid-state relay 4, solid-state relay 5, solid-state relay 6；
By 1553B bus interface modules, CPU gathers whether just each stand-alone device on the arrow of flight control computer feedback works
Normal court verdict, and when stand-alone device normal work, the relay closure output in controlling switch amount output module is " middle
Igniting " instruction；
Solid-state relay 1 and solid-state relay 2 are connected, solid-state relay 3 and solid-state relay 4 are connected, solid-state relay 5
Connect with solid-state relay 6, then output parallel with one another again.
A kind of confirmation method of the low time delay ignition confirming system of arrow ground information fusion, including step is as follows：
(1) the comprehensive control device of ground launch vehicle measurement receives " initial ignition " signal that center indication control board sends, and enters
After the logical operation of row ladder diagram and signal condition, output " when unite zero point " signal is to flight control computer on arrow；
(2) on arrow, flight control computer, after optocoupler receives " when unite zero point " signal, the time on current arrow is reset, and to
On arrow, other stand-alone devices send and perform time synchronized operational order；Meanwhile, on arrow, flight control computer passes through each list for receiving
The time synchronized situation of machine equipment feedback, judges whether crucial unit is working properly on arrow, and the result that will determine that feeds back to ground
The central computer of face launch vehicle measurement, while flight control computer starts flight under each stand-alone device normal operation on arrow
Control computing；
(3) after central computer receives the court verdict working properly of each stand-alone device on arrow, fill to comprehensive control
Put transmission " middle igniting " instruction；
(4) after comprehensive control device receives " middle igniting " instruction, ladder diagram logical operation process is carried out, output is " most
Terminal fire " control signal ignites igniting priming system and output " bus control signal " disconnects bus-controlled switching.
Step (1) to implement step as follows：
(1a) PLC in comprehensive control device enters to receiving three tunnels " initial ignition " signal from center indication control board
Row ladder diagram logical operation, exports two-way " when unite zero point PLC " signal to first control modulate circuit in comprehensive control device；
(1b) first control modulate circuit in comprehensive control device, the signal to receiving carry out signal condition：First
Send out control modulate circuit and receive " when unite zero point PLC " signal, first generates relay K11, K12 line band electricity of control modulate circuit,
All closings of contact of K11, K12, and " when unite zero point " signal of connecting and export is to flight control computer on arrow.
Step (4) to implement step as follows：
(4a) PLC in comprehensive control device carries out ladder diagram logic after receiving " middle igniting " instruction of central computer
Calculation process, exports six tunnels " finally light a fire PLC " signal to second control modulate circuit in comprehensive control device and output
" bus control signal " disconnects bus-controlled switching all the way；
(4b) second control modulate circuit, the signal to receiving carry out signal condition：Second control modulate circuit docking
Receiving " finally light a fire PLC " signal carries out two from three process, then drives tetra- electromagnetic relays of Kdh1, Kdh2, Kdh3, Kdh4
Line bag, all contacts of Kdh1, Kdh2 and series connection make igniting priming system positive bus-bar powered, all contacts of Kdh3, Kdh4 and connect make
The negative busbar of igniting priming system is powered.
Compared with the prior art, the invention has the advantages that：
(1) present invention carries out stand-alone device detection whether working properly and ground on arrow by way of time synchronized
Launch vehicle measurement is received and just ignite igniting priming system after time order of " each stand-alone device is working properly " of control system return on arrow,
Ensure that arrow ground information fusion, and then monitor rocket take off before arrow on state, coordinate with carrying out arrow in ignition process with
Validation of information, can avoid the transmitting risk that hardware and software failure brings on arrow, strengthen the guarantee of ignition process, improve transmitting
Reliability.
(2) arrow ground information fusion mode of the central computer of the present invention using 1553B buses+solid-state relay interface, contracting
The short ignition confirming time, it is ensured that software and hardware is working properly before taking off, it is ensured that the security of emission control, substantially increases work
Efficiency.
(3) present invention does not change the basis of hardware, realizes rocket launching by rational arrow ground information fusion mode
Reliability Assurance, therefore highly versatile of the present invention do not increase device, and hardware cost is low, and reliability is high, beneficial to popularization and application.
(4) central computer of the invention realizes data communication, solid-state relay tool in the form of 6 solid-state relays
There is the characteristics of switching speed is fast, functional reliability is high, the mode of parallel connection again that six solid-state relays are connected two-by-two improves a little
The reliability and security of ignition circuit.
Description of the drawings
Fig. 1 is prior art systems schematic diagram；
Fig. 2 is present system schematic diagram；
Fig. 3 is particular circuit configurations schematic diagram of the present invention.
Specific embodiment
Below in conjunction with the accompanying drawings the specific embodiment of the present invention is further described in detail.
In the prior art, typically all directly lighted a fire after ground launch vehicle measurement judges to meet ignition condition,
Now the present invention is to need on ground and arrow while meet ignition condition, to improve the reliability and security of igniting.
As shown in Figure 2,3, a kind of low time delay ignition confirming system of arrow ground information fusion includes：Ground launch vehicle measurement and
Flight control computer on arrow；Ground launch vehicle measurement includes comprehensive control device, center indication control board and central computer again；
Center indication control board, is User Interface, provides " initial ignition " signal to comprehensive control device；
Comprehensive control device, receives " initial ignition " signal that center indication control board sends, carry out ladder diagram logical operation with
And after signal condition, output " when unite zero point " signal is to flight control computer on arrow；Comprehensive control device receives middle scheming simultaneously
After " middle igniting " instruction of calculation machine, ladder diagram logical operation process is carried out, output " final to light a fire " control signal ignites igniting
Priming system and output " bus control signal " disconnect bus-controlled switching.
Comprehensive control device includes PLC, first control modulate circuit and second control modulate circuit；
First control modulate circuit includes relay K11, K12 again；Second control modulate circuit again include relay Kdh1,
Kdh2, Kdh3 and Kdh4；
The line bag of relay K11, K12 is in parallel；The contact K12A of the contact K11A and K12 of relay K11 is in parallel, contact
K11B and K12B is in parallel, is serially connected after parallel connection again；
The line bag of relay Kdh1, Kdh2, Kdh3 and Kdh4 is in parallel；The contact Kdh1A's and Kdh2 of relay Kdh1 touches
Point Kdh2A is in parallel, and contact Kdh1B and Kdh2B are in parallel, is serially connected after parallel connection again；The contact Kdh3A and Kdh4 of relay Kdh3
Contact Kdh4A it is in parallel, contact Kdh3B and Kdh4B are in parallel, parallel connection after be serially connected again；
The output end of PLC connects the line bag and total line traffic control of relay K11, K12, Kdh1, Kdh2, Kdh3 and Kdh4 respectively
System switch.
Sending out a control modulate circuit and can expand to N number of according to demand in comprehensive control device, the system only uses first control
Modulate circuit, second control modulate circuit, other control modulate circuits are implemented according to concrete function.
Central computer, gathers on arrow whether each stand-alone device work normally adjudicates knot on the arrow of flight control computer feedback
Really, and when stand-alone device normal work, " middle igniting " instruction is sent to comprehensive control device；On arrow, each stand-alone device includes
Control combination, inertial instruments, servo-drive subsystem and measurement combination etc..
Central computer includes CPU, 1553B bus interface module, switching value output module；Switching value output module is wrapped again
Include solid-state relay 1, solid-state relay 2, solid-state relay 3, solid-state relay 4, solid-state relay 5, solid-state relay 6；
By 1553B bus interface modules, CPU gathers whether just each stand-alone device on the arrow of flight control computer feedback works
Normal court verdict, and when stand-alone device normal work, the relay closure output in controlling switch amount output module is " middle
Igniting " instruction；
Solid-state relay 1 and solid-state relay 2 are connected, solid-state relay 3 and solid-state relay 4 are connected, solid-state relay
5 and solid-state relay 6 connect, then output parallel with one another again.Solid-state relay has that switching speed is fast, functional reliability is high
Feature, the mode of parallel connection again that six solid-state relays are connected two-by-two, improves the reliability and security of firing circuit.
Flight control computer on arrow, after optocoupler receives " when unite zero point " signal, the time on current arrow is reset, and to arrow
Upper other stand-alone devices send and perform time synchronized operational order；Meanwhile, on arrow, flight control computer passes through each unit for receiving
The time synchronized situation of equipment feedback, judges whether crucial unit is working properly on arrow, and the result that will determine that feeds back to ground
The central computer of launch vehicle measurement, while flight control computer starts flight control under each stand-alone device normal operation on arrow
Computing processed.
For the installation reliability of detonation, present invention additionally comprises electromagnetic relay Kyx1, Kyx2, Kzdh1 and Kzdh2；
The contact Kzdh2A of the contact Kzdh1A and Kzdh2 of relay Kzdh1 is in parallel, and contact Kzdh1B and Kzdh2B are simultaneously
Connection, is serially connected after parallel connection again, all contacts of input connection relay Kdh1, Kdh2 and output of connecting of the series connection；
The contact Kyx2A of the contact Kyx1A and Kyx2 of relay Kyx1 is in parallel, and contact Kyx1B and Kyx2B are in parallel, in parallel
It is serially connected again afterwards, the input of the series connection connects all contacts of Kzdh1 and Kzdh2 the output connected.
A kind of confirmation method of the low time delay ignition confirming system of arrow ground information fusion, including step is as follows：
(1) the comprehensive control device of ground launch vehicle measurement receives " initial ignition " signal that center indication control board sends, and enters
After the logical operation of row ladder diagram and signal condition, output " when unite zero point " signal is to flight control computer on arrow；
Step (1) to implement step as follows：
(1a) PLC in comprehensive control device enters to receiving three tunnels " initial ignition " signal from center indication control board
Row ladder diagram logical operation, exports two-way " when unite zero point " signal to first control modulate circuit in comprehensive control device；
Artificially judge that launch vehicle measurement is met after ignition condition according to a flow control journey implementation status is surveyed, for the center of pressing
Indication control board SB1 is switched, and SB1 switch closures, positive pole line voltage+M3 deliver to the input of PLC.
(1b) first control modulate circuit in comprehensive control device, the signal to receiving carry out signal condition：First
Send out control modulate circuit and receive " when unite zero point PLC " signal, positive pole line voltage is connected to two relay K11, K12 lines in parallel
Wrap, first generate control modulate circuit relay K11, K12 line band electricity, K11, K12 all closings of contact (K11A, K12A,
K11B, K12B), Jing output of connecting " when unite zero point " are to flight control computer on arrow.
(2) on arrow, flight control computer, after optocoupler receives " when unite zero point " signal, the time on current arrow is reset, and to
On arrow, other stand-alone devices send and perform time synchronized operational order；Meanwhile, on arrow, flight control computer passes through each list for receiving
The time synchronized situation of machine equipment feedback, judges on arrow whether crucial unit is working properly and (operates the time synchronized of transmission and refer to
The confirmation of synchronization value with each stand-alone device for returning is made to be compared, if the whole retaking of a year or grade success of each stand-alone device confirmation of synchronization value
And it is identical with the simultaneously operating director data that flight control computer on arrow sends respectively, then it is assumed that stand-alone device is working properly), and will
The result of judgement passes through central computer of the 1553B bus feedbacks to ground launch vehicle measurement, while flight control computer exists on arrow
Start flight control computing under each stand-alone device normal operation, if each stand-alone device irregular working, fly control on arrow and calculate
Machine does not restart flight control program, waits follow-up floor treatment；Communicated with carrying out arrow using 1553B buses, make arrow ground information
Fusion process does not increase device, reduces cost；
(3) after central computer receives the court verdict working properly of each stand-alone device on arrow, fill to comprehensive control
Put transmission " middle igniting " instruction；
Central computer CPU gathers each stand-alone device on the arrow of flight control computer feedback by 1553B bus interface modules
The whether normal court verdict of work, and the solid relay when stand-alone device normal work, in controlling switch amount output module
1～solid-state relay of device, 6 action, 1～solid-state relay of solid-state relay, 6 contact is connected again Parallel opertation " middle igniting " two-by-two
Instruction, solid-state relay have the fast characteristic of switching speed, and the low delay character for arrow ground information fusion provides guarantee.
(4) after comprehensive control device receives " middle igniting " instruction, ladder diagram logical operation process is carried out, output is " most
Terminal fire " control signal ignites igniting priming system and output " bus control signal " disconnects bus-controlled switching.
In step (4) to implement step as follows：
(4a) PLC in comprehensive control device carries out ladder diagram logic after receiving " middle igniting " instruction of central computer
Calculation process, exports six tunnels " finally light a fire PLC " signal to second control modulate circuit in comprehensive control device and output
" bus control signal " disconnects bus-controlled switching all the way；Bus control signal has following effect：Output " bus control signal "
1553B bus switch is disconnected, the 1553B bus runs of launch vehicle measurement and flight control computer is cut off, build-out resistor is accessed into arrow
Upper terminal bus, realize arrow ground bus separation, it is ensured that after taking off on arrow 1553B bus runs communication quality.
(4b) second control modulate circuit, the signal to receiving carry out signal condition：Second control modulate circuit docking
Receiving " igniting " signal carries out two from three process, then drives tetra- electromagnetic relay line bags of Kdh1, Kdh2, Kdh3, Kdh4,
The all contacts of Kdh1, Kdh2 (Kdh1A, Kdh2A, Kdh1B, Kdh2B) and series connection make igniting priming system positive bus-bar powered, Kdh3,
The all contacts of Kdh4 (Kdh3A, Kdh4A, Kdh3B, Kdh4B) and series connection make the negative busbar of igniting priming system powered.
To improve the security of priming system control, following restrictive condition of connecting in IGNITION CONTROL passage：Kyx1, Kyx2 are electric
Magnetic relay contact is simultaneously connected, and Kzdh1, Kzh2 electromagnetic relay contact is simultaneously connected, it is ensured that complete in the interval for allowing igniting
Igniting.It is implemented as follows：The contact Kzdh2A of the contact Kzdh1A and Kzdh2 of relay Kzdh1 is in parallel, contact Kzdh1B and
Kzdh2B is in parallel, is serially connected after parallel connection again, and the series connection all contacts of input connection relay Kdh1, Kdh2 is simultaneously connected defeated
Go out.The contact Kyx2A of the contact Kyx1A and Kyx2 of relay Kyx1 is in parallel, and contact Kyx1B and Kyx2B are in parallel, phase again after parallel connection
Mutually connect, the input of the series connection connects all contacts of Kzdh1 and Kzdh2 the output connected.
Each closing of contact in ignition channel, M3 busbar voltage Jing current-limiting resistances are added to igniting priming system two ends, and priming system draws
Quick-fried, rocket body is taken off after firing.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (8)
1. the low time delay ignition confirming system of a kind of arrow ground information fusion, including：Fly control to calculate on ground launch vehicle measurement and arrow
Machine；Ground launch vehicle measurement includes comprehensive control device, center indication control board and central computer again；Center indication control board, is user
Interactive interface, provides " initial ignition " signal to comprehensive control device, it is characterised in that：
Comprehensive control device, receives " initial ignition " signal that center indication control board sends, carries out ladder diagram logical operation and letter
After number conditioning, output " when unite zero point " signal is to flight control computer on arrow；Comprehensive control device receives central computer simultaneously
" middle igniting " instruction after, carry out ladder diagram logical operation process, output " final to light a fire " control signal ignites igniting firer
Product and output " bus control signal " disconnect bus-controlled switching；
Central computer, gathers on arrow the whether normal court verdict of each stand-alone device work on the arrow of flight control computer feedback,
And when stand-alone device normal work, " middle igniting " instruction is sent to comprehensive control device；
Flight control computer on arrow, after receiving " when unite zero point " signal, is reset, and other units sets on arrow the time on current arrow
Preparation send execution time synchronized operational order；Meanwhile, on arrow flight control computer by each stand-alone device feedback that receives when
Between synchronous situation, judge on arrow whether crucial unit working properly, and the result that will determine that feed back to ground launch vehicle measurement
Central computer, while flight control computer starts flight control computing under each stand-alone device normal operation on arrow.
2. the low time delay ignition confirming system of a kind of arrow ground according to claim 1 information fusion, it is characterised in that：It is described
Comprehensive control device includes PLC, first control modulate circuit and second control modulate circuit；
First control modulate circuit includes relay K11, K12 again；Second control modulate circuit again include relay Kdh1,
Kdh2, Kdh3 and Kdh4；
The line bag of relay K11, K12 is in parallel；The contact K12A of the contact K11A and K12 of relay K11 is in parallel, contact K11B and
K12B is in parallel, is serially connected after parallel connection again；
The line bag of relay Kdh1, Kdh2, Kdh3 and Kdh4 is in parallel；The contact of the contact Kdh1A and Kdh2 of relay Kdh1
Kdh2A is in parallel, and contact Kdh1B and Kdh2B are in parallel, is serially connected after parallel connection again；The contact Kdh3A's and Kdh4 of relay Kdh3
Contact Kdh4A is in parallel, and contact Kdh3B and Kdh4B are in parallel, is serially connected after parallel connection again；
The output end of PLC connects the line bag and bus marco of relay K11, K12, Kdh1, Kdh2, Kdh3 and Kdh4 respectively and opens
Close.
3. the low time delay ignition confirming system of a kind of arrow ground according to claim 2 information fusion, it is characterised in that also wrap
Include：Electromagnetic relay Kyx1, Kyx2, Kzdh1 and Kzdh2；
The contact Kzdh2A of the contact Kzdh1A and Kzdh2 of relay Kzdh1 is in parallel, and contact Kzdh1B and Kzdh2B are in parallel, and
It is serially connected after connection again, the Parallel opertation of the input connecting terminal Kdh1A and contact Kdh2A of the series connection；
The contact Kyx2A of the contact Kyx1A and Kyx2 of relay Kyx1 is in parallel, and contact Kyx1B and Kyx2B are in parallel, after parallel connection again
It is serially connected, the Parallel opertation of the input connecting terminal kzdh1A and contact Kzdh2A of the series connection.
4. a kind of low time delay ignition confirming system of arrow ground information fusion according to claim 2, is further characterized in that：Institute
State in comprehensive control device send out control a modulate circuit can expand to according to demand it is N number of, the system only use first generate control conditioning electricity
Road, second control modulate circuit, implementing for other control modulate circuits are designed according to concrete function.
5. the low time delay ignition confirming system of a kind of arrow ground according to claim 1 information fusion, it is characterised in that：It is described
Central computer includes CPU, 1553B bus interface module, switching value output module；Switching value output module again include solid after
Electrical equipment 1, solid-state relay 2, solid-state relay 3, solid-state relay 4, solid-state relay 5, solid-state relay 6；
Whether normal CPU gathers each stand-alone device work on the arrow of flight control computer feedback by 1553B bus interface modules
Court verdict, and the relay closure output " intermediate point when stand-alone device normal work, in controlling switch amount output module
Fire " instruction；
Solid-state relay 1 and solid-state relay 2 are connected, solid-state relay 3 and solid-state relay 4 are connected, solid-state relay 5 and solid
Body relay 6 is connected, then output parallel with one another again.
6. a kind of confirmation method of the low time delay ignition confirming system of the arrow ground information fusion based on described in claim 5, which is special
Levy is to include that step is as follows：
(1) the comprehensive control device of ground launch vehicle measurement receives " initial ignition " signal that center indication control board sends, and carries out ladder
After the logical operation of shape figure and signal condition, output " when unite zero point " signal is to flight control computer on arrow；
(2) on arrow, flight control computer, after optocoupler receives " when unite zero point " signal, the time on current arrow is reset, and on arrow
Other stand-alone devices send and perform time synchronized operational order；Meanwhile, on arrow, flight control computer is set by each unit for receiving
The time synchronized situation of standby feedback, judges whether crucial unit is working properly on arrow, and the result that will determine that feeds back to ground survey
The central computer of launching control system, while flight control computer starts flight control under each stand-alone device normal operation on arrow
Computing；
(3) after central computer receives the court verdict working properly of each stand-alone device on arrow, send out to comprehensive control device
Send " middle igniting " instruction；
(4), after comprehensive control device receives " middle igniting " instruction, ladder diagram logical operation process is carried out, " maximal end point is exported
Fire " control signal ignites igniting priming system and output " bus control signal " disconnects bus-controlled switching.
7. the low time delay ignition confirming of a kind of arrow ground information fusion based on described in claim 5 according to claim 6
The confirmation method of system, it is characterised in that：The step (1) to implement step as follows：
(1a) PLC in comprehensive control device carries out ladder to receiving three tunnels " initial ignition " signal from center indication control board
Shape figure logical operation, exports two-way " when unite zero point PLC " signal to first control modulate circuit in comprehensive control device；
(1b) first control modulate circuit in comprehensive control device, the signal to receiving carry out signal condition：First control
Modulate circuit receives " when unite zero point PLC ", and first generates relay K11, K12 line band electricity of control modulate circuit, K11, K12's
All closings of contact, Jing connecting export " when unite zero point " signal to flight control computer on arrow.
8. the low time delay ignition confirming of a kind of arrow ground information fusion based on described in claim 5 according to claim 6
The confirmation method of system, it is characterised in that：The step (4) to implement step as follows：
(4a) PLC in comprehensive control device carries out ladder diagram logical operation after receiving " middle igniting " instruction of central computer
Process, six tunnels " finally light a fire PLC " signal is exported to second control modulate circuit in comprehensive control device and exported all the way
" bus control signal " disconnects bus-controlled switching；
(4b) second control modulate circuit, the signal to receiving carry out signal condition：Second control modulate circuit is to receiving
" finally light a fire PLC " signal carries out two from three process, then drives tetra- electromagnetic relay lines of Kdh1, Kdh2, Kdh3, Kdh4
Bag, all contacts of Kdh1, Kdh2 and connect make igniting priming system positive bus-bar powered, all contacts of Kdh3, Kdh4 and connect make a little
The negative busbar of fiery priming system is powered.
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| CN201510178331.9A CN104895700B (en) | 2015-04-15 | 2015-04-15 | A kind of low time delay ignition confirming system and confirmation method of arrow ground information fusion |
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| CN107797467A (en) * | 2017-09-15 | 2018-03-13 | 江西洪都航空工业集团有限责任公司 | System Zero magnitude control device during a kind of generalization |
| CN110297481B (en) * | 2019-07-01 | 2024-03-15 | 中国航天空气动力技术研究院 | High-precision time system method of interstage separation flight control system |
| CN110632944B (en) * | 2019-10-28 | 2022-12-13 | 北京空间机电研究所 | Parafoil autonomous homing control system for rocket booster recovery |
| CN111396215B (en) * | 2020-04-21 | 2021-05-14 | 北京中科宇航技术有限公司 | Ignition safety system of multistage rocket engine and detection method thereof |
| CN111911318A (en) * | 2020-06-28 | 2020-11-10 | 南京云睿航天科技有限公司 | Solid engine ignition circuit with feedback |
| CN111854543A (en) * | 2020-07-07 | 2020-10-30 | 深圳零壹空间电子有限公司 | Rocket control device |
| CN112012851B (en) * | 2020-08-31 | 2023-05-16 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle cluster boosting rocket ignition control system and working method thereof |
| CN112130505A (en) * | 2020-09-27 | 2020-12-25 | 山东航天电子技术研究所 | Initiating explosive device ignition control circuit and method thereof |
| CN114459284A (en) * | 2021-12-24 | 2022-05-10 | 宜昌测试技术研究所 | Communication and transmission safety interlocking control method and system |
| CN114517749B (en) * | 2021-12-29 | 2023-12-12 | 中国航天系统科学与工程研究院 | Automatic ignition control system of carrier rocket |
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| CH621230B (en) * | 1975-11-25 | Mefina Sa | ELECTRONIC IGNITION DEVICE FOR PROJECTILE ROCKET. | |
| JPS6229599U (en) * | 1985-08-06 | 1987-02-23 | ||
| JPH02127994U (en) * | 1989-03-27 | 1990-10-22 | ||
| CN101776028B (en) * | 2009-12-30 | 2011-12-21 | 北京宇航系统工程研究所 | Hold-down and release simulation data source system |
| CN104454240B (en) * | 2014-11-24 | 2016-04-20 | 江西洪都航空工业集团有限责任公司 | A kind of booster rocket ignition control circuit of aircraft |
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