CN104895700A - Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion - Google Patents
Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion Download PDFInfo
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Abstract
In a low delay ignition confirmation system and confirmation method applied to rocket ground information infusion, a comprehensive detection and control apparatus of a ground test launch control system receives an initial ignition signal sent by a central display and control station; after ladder diagram and logical calculation and signal conditioning, a timing system zero point signal is output; a flight control computer determines whether each one-chip microcomputers on the rocket work normally according to time synchronization after receiving the timing system zero point signal; a flight control procedure is started upon normal work and a determining result is fed back to a central computer; the flight control procedure is stopped upon abnormal work and a determining result is fed back to the central computer and ground post processing is expected; the central computer receives the rocket results; for the normal work signal, an intermediate ignition signal is output to the comprehensive detection and control apparatus; a final ignition signal is output by the comprehensive detection and control apparatus after receiving the intermediate ignition signal; and an initiating explosive device is detonated by a second launch control conditioning plate, so the rocket and the ground are reliably separated.
Description
Technical field
The present invention relates to the low time delay ignition confirming system and method for a kind of arrow ground information fusion, belong to vehicle launch control technique field.
Background technique
Fire signal is the key signal in emission control technology, for ignite igniting fire-working article be separated with realizing arrow, also as flight control computer on arrow time system zero point, for enter flight control solver.
As shown in Figure 1, in traditional approach, after " the initial ignition signal " of synthesis observe and control device receiving center indication control board, after carrying out logical operation and signal condition, export " final fire signal " and " time system zero signal ", respectively drive ignition fire-working article and start flight control solver simultaneously.There is following problem in traditional design scheme: if while drive ignition fire-working article on arrow equipment or application state abnormal, normally do not enter flight control program, fire-working article of meanwhile lighting a fire detonates, and rocket body takes off, and will inevitably cause launch mission failure.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide the low time delay ignition confirming system and method for a kind of arrow ground information fusion, by arrow ground information fusion technology, state on arrow before monitoring rocket takes off, coordinate and validation of information in igniting process, with carrying out arrow, improve the reliability of rocket launching.
Technical solution of the present invention is:
The low time delay ignition confirming system of a kind of arrow ground information fusion comprises: flight control computer on ground launch vehicle measurement and arrow; Ground launch vehicle measurement comprises again synthesis observe and control device, center indication control board and central computer;
Center indication control board is User Interface, provides " initial ignition " signal to synthesis observe and control device;
Synthesis observe and control device, receives " initial ignition " signal that center indication control board sends, and after carrying out ladder diagram logical operation and signal condition, exports flight control computer on " time system zero point " signal to arrow; After synthesis observe and control device receives " middle igniting " instruction of central computer simultaneously, carry out ladder diagram logical operation process, output " finally igniting " control signal ignites igniting fire-working article and output " bus control signal " disconnects bus-controlled switching.
Central computer, the whether normal court verdict of each stand-alone device work on the arrow that on collection arrow, flight control computer feeds back, and when stand-alone device normally works, send " lighting a fire in centre " instruction to synthesis observe and control device;
Flight control computer on arrow, after receiving " time system zero point " signal, reset the time on current arrow, and other stand-alone device sends time of implementation simultaneously operating instruction on arrow; Simultaneously, the time synchronization situation that on arrow, flight control computer is fed back by each stand-alone device received, judge that on arrow, whether crucial unit is working properly, and by the result feedback of judgement to the central computer of ground launch vehicle measurement, on arrow, flight control computer starts flight control algorithm under each stand-alone device normal operation simultaneously.
Synthesis observe and control device comprises PLC, first control conditioning circuit and second control conditioning circuit;
First control conditioning circuit comprises again relay K 11, K12; Second control conditioning circuit comprises again relay K dh1, Kdh2, Kdh3 and Kdh4;
The line bag of relay K 11, K12 is in parallel; The contact K12A of contact K11A and the K12 of relay K 11 is in parallel, and contact K11B and K12B is in parallel, mutually connects after parallel connection again;
The line bag of relay K dh1, Kdh2, Kdh3 and Kdh4 is in parallel; The contact Kdh2A of contact Kdh1A and the Kdh2 of relay K dh1 is in parallel, and contact Kdh1B and Kdh2B is in parallel, mutually connects after parallel connection again; The contact Kdh4A of contact Kdh3A and the Kdh4 of relay K dh3 is in parallel, and contact Kdh3B and Kdh4B is in parallel, mutually connects after parallel connection again;
The output terminal of PLC connects relay K 11, the line bag of K12, Kdh1, Kdh2, Kdh3 and Kdh4 and bus-controlled switching respectively.
The present invention also comprises: electromagnetic relay Kyx1, Kyx2, Kzdh1 and Kzdh2;
The contact Kzdh2A of contact Kzdh1A and the Kzdh2 of relay K zdh1 is in parallel, and contact Kzdh1B and Kzdh2B is in parallel, mutually connects after parallel connection again, that the input of this series connection connects all contacts of relay K dh1, Kdh2 and output of connecting;
The contact Kyx2A of contact Kyx1A and the Kyx2 of relay K yx1 is in parallel, and contact Kyx1B and Kyx2B is in parallel, mutually connects after parallel connection again, and the input of this series connection connects all contacts of Kzdh1 and Kzdh2 and the output of series connection.
Sending out in synthesis observe and control device is controlled conditioning circuit and can be expanded to N number of according to demand, and N number of control conditioning circuit specific implementation realizes according to concrete function.
Central computer comprises CPU, 1553B bus interface module, switching value output module; Switching value output module comprises again solid state relay 1, solid state relay 2, solid state relay 3, solid state relay 4, solid state relay 5, solid state relay 6;
CPU passes through 1553B bus interface module, the whether normal court verdict of each stand-alone device work on the arrow of collection flight control computer feedback, and when stand-alone device normally works, relay closes output " lighting a fire in the centre " instruction in control switch amount output module;
Solid state relay 1 and solid state relay 2 are connected, solid state relay 3 and solid state relay 4 is connected, solid state relay 5 and solid state relay 6 are connected, and then output parallel with one another.
A confirmation method for the low time delay ignition confirming system of arrow ground information fusion, comprises step as follows:
(1) synthesis observe and control device of ground launch vehicle measurement receives " initial ignition " signal that center indication control board sends, and after carrying out ladder diagram logical operation and signal condition, exports flight control computer on " time system zero point " signal to arrow;
(2) after on arrow, flight control computer receives " time system zero point " signal by optocoupler, the time on current arrow is reset, and other stand-alone device send time of implementation simultaneously operating instruction on arrow; Simultaneously, the time synchronization situation that on arrow, flight control computer is fed back by each stand-alone device received, judge that on arrow, whether crucial unit is working properly, and by the result feedback of judgement to the central computer of ground launch vehicle measurement, on arrow, flight control computer starts flight control algorithm under each stand-alone device normal operation simultaneously;
(3) after central computer receives the court verdict that on arrow, each stand-alone device is working properly, " middle igniting " instruction is sent to synthesis observe and control device;
(4) after synthesis observe and control device receives " middle igniting " instruction, carry out ladder diagram logical operation process, output " finally igniting " control signal ignites igniting fire-working article and output " bus control signal " disconnects bus-controlled switching.
The specific implementation step of step (1) is as follows:
(1a) PLC in synthesis observe and control device, to three tunnels " initial ignition " signal received from center indication control board, carries out ladder diagram logical operation, exports two-way " time system zero point PLC " signal to the control conditioning circuit of first in synthesis observe and control device;
(1b) first control conditioning circuit in synthesis observe and control device, carry out signal condition to the received signal: first control conditioning circuit receives " time system zero point PLC " signal, first generates relay K 11, the K12 line band electricity of controlling conditioning circuit, all make contact of K11, K12, and series connection exports " time system zero point " signal to flight control computer on arrow.
The specific implementation step of step (4) is as follows:
(4a) PLC in synthesis observe and control device carries out ladder diagram logical operation process after receiving " middle igniting " instruction of central computer, exports six tunnels " finally light a fire PLC " signal and disconnects bus-controlled switching to the control conditioning circuit of second in synthesis observe and control device and output one tunnel " bus control signal ";
(4b) second control conditioning circuit, carry out signal condition to the received signal: second control conditioning circuit carries out three get two process to receiving " finally light a fire PLC " signal, then Kdh1, Kdh2, Kdh3, Kdh4 tetra-electromagnetic relay line bags are driven, the all contacts of Kdh1, Kdh2 also series connection make igniting fire-working article positive bus-bar charged, and all contacts of Kdh3, Kdh4 also series connection make the negative busbar of igniting fire-working article charged.
The present invention's beneficial effect is compared with prior art:
(1) the present invention by the mode of time synchronization carry out detection that on arrow, whether stand-alone device working properly and ground launch vehicle measurement receive " each stand-alone device is working properly " that control system on arrow returns return order after just ignite igniting fire-working article, ensure that the fusion of arrow ground information, and then monitoring rocket take off before arrow on state, coordinate and validation of information in igniting process, with carrying out arrow, the transmitting risk that hardware and software failure on arrow brings can be avoided, strengthen the guarantee of igniting process, improve the reliability of launching.
(2) central computer of the present invention adopts the arrow ground information fusion mode of 1553B bus+solid state relay interface, shortens the ignition confirming time, and before guaranteeing to take off, software and hardware is working properly, ensures the Security of emission control, substantially increases working efficiency.
(3) the present invention does not change the basis of hardware, and achieved the Reliability Assurance of rocket launching by rational arrow ground information fusion mode, therefore highly versatile of the present invention, does not increase device, and hardware cost is low, and reliability is high, is beneficial to and applies.
(4) central computer of the present invention adopts the form of 6 solid state relays to realize data communication, solid state relay has the advantages that switching speed is fast, functional reliability is high, six solid state relays to be connected between two mode more in parallel, improve reliability and the Security of firing circuit.
Accompanying drawing explanation
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.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is further described in detail.
, in the prior art, be all generally that directly light a fire, present the present invention needs ground and arrow meet ignition condition simultaneously, can improve reliability and the Security of igniting after ground launch vehicle measurement judges to meet ignition condition.
As shown in Figure 2,3, the low time delay ignition confirming system of a kind of arrow ground information fusion comprises: flight control computer on ground launch vehicle measurement and arrow; Ground launch vehicle measurement comprises again synthesis observe and control device, center indication control board and central computer;
Center indication control board is User Interface, provides " initial ignition " signal to synthesis observe and control device;
Synthesis observe and control device, receives " initial ignition " signal that center indication control board sends, and after carrying out ladder diagram logical operation and signal condition, exports flight control computer on " time system zero point " signal to arrow; After synthesis observe and control device receives " middle igniting " instruction of central computer simultaneously, carry out ladder diagram logical operation process, output " finally igniting " control signal ignites igniting fire-working article and output " bus control signal " disconnects bus-controlled switching.
Synthesis observe and control device comprises PLC, first control conditioning circuit and second control conditioning circuit;
First control conditioning circuit comprises again relay K 11, K12; Second control conditioning circuit comprises again relay K dh1, Kdh2, Kdh3 and Kdh4;
The line bag of relay K 11, K12 is in parallel; The contact K12A of contact K11A and the K12 of relay K 11 is in parallel, and contact K11B and K12B is in parallel, mutually connects after parallel connection again;
The line bag of relay K dh1, Kdh2, Kdh3 and Kdh4 is in parallel; The contact Kdh2A of contact Kdh1A and the Kdh2 of relay K dh1 is in parallel, and contact Kdh1B and Kdh2B is in parallel, mutually connects after parallel connection again; The contact Kdh4A of contact Kdh3A and the Kdh4 of relay K dh3 is in parallel, and contact Kdh3B and Kdh4B is in parallel, mutually connects after parallel connection again;
The output terminal of PLC connects relay K 11, the line bag of K12, Kdh1, Kdh2, Kdh3 and Kdh4 and bus-controlled switching respectively.
Sending out in synthesis observe and control device is controlled conditioning circuit and can be expanded to N number of according to demand, and native system only uses first control conditioning circuit, second control conditioning circuit, and other control conditioning circuits are according to concrete function specific implementation.
Central computer, the whether normal court verdict of each stand-alone device work on the arrow that on collection arrow, flight control computer feeds back, and when stand-alone device normally works, send " lighting a fire in centre " instruction to synthesis observe and control device; On arrow, each stand-alone device comprises control combination, inertial instruments, servo-drive subsystem and measures combination etc.
Central computer comprises CPU, 1553B bus interface module, switching value output module; Switching value output module comprises again solid state relay 1, solid state relay 2, solid state relay 3, solid state relay 4, solid state relay 5, solid state relay 6;
CPU passes through 1553B bus interface module, the whether normal court verdict of each stand-alone device work on the arrow of collection flight control computer feedback, and when stand-alone device normally works, relay closes output " lighting a fire in the centre " instruction in control switch amount output module;
Solid state relay 1 and solid state relay 2 are connected, solid state relay 3 and solid state relay 4 is connected, solid state relay 5 and solid state relay 6 are connected, and then output parallel with one another.Solid state relay has the advantages that switching speed is fast, functional reliability is high, and mode in parallel again of being connected between two by six solid state relays, improves reliability and the Security of firing circuit.
Flight control computer on arrow, after receiving " time system zero point " signal, reset the time on current arrow, and other stand-alone device sends time of implementation simultaneously operating instruction on arrow by optocoupler; Simultaneously, the time synchronization situation that on arrow, flight control computer is fed back by each stand-alone device received, judge that on arrow, whether crucial unit is working properly, and by the result feedback of judgement to the central computer of ground launch vehicle measurement, on arrow, flight control computer starts flight control algorithm under each stand-alone device normal operation simultaneously.
In order to the installation of detonating is reliable, the present invention also comprises electromagnetic relay Kyx1, Kyx2, Kzdh1 and Kzdh2;
The contact Kzdh2A of contact Kzdh1A and the Kzdh2 of relay K zdh1 is in parallel, and contact Kzdh1B and Kzdh2B is in parallel, mutually connects after parallel connection again, that the input of this series connection connects all contacts of relay K dh1, Kdh2 and output of connecting;
The contact Kyx2A of contact Kyx1A and the Kyx2 of relay K yx1 is in parallel, and contact Kyx1B and Kyx2B is in parallel, mutually connects after parallel connection again, and the input of this series connection connects all contacts of Kzdh1 and Kzdh2 and the output of series connection.
A confirmation method for the low time delay ignition confirming system of arrow ground information fusion, comprises step as follows:
(1) synthesis observe and control device of ground launch vehicle measurement receives " initial ignition " signal that center indication control board sends, and after carrying out ladder diagram logical operation and signal condition, exports flight control computer on " time system zero point " signal to arrow;
The specific implementation step of step (1) is as follows:
(1a) PLC in synthesis observe and control device, to three tunnels " initial ignition " signal received from center indication control board, carries out ladder diagram logical operation, exports two-way " time system zero point " signal to the control conditioning circuit of first in synthesis observe and control device;
After artificially judging that launch vehicle measurement meets ignition condition according to a survey flow control journey implementation status, for pressing center indication control board SB1 switch, SB1 switch closes, and positive bus-bar voltage+M3 delivers to the input end of PLC.
(1b) first control conditioning circuit in synthesis observe and control device, carry out signal condition to the received signal: first control conditioning circuit receives " time system zero point PLC " signal, positive bus-bar voltage is connected to two relay K 11 in parallel, K12 lines and wraps, first generates relay K 11, the K12 line band electricity of controlling conditioning circuit, all make contact (K11A, K12A, K11B, K12B) of K11, K12, through and outputs of connecting " time unite zero point " to flight control computer on arrow.
(2) after on arrow, flight control computer receives " time system zero point " signal by optocoupler, the time on current arrow is reset, and other stand-alone device send time of implementation simultaneously operating instruction on arrow, simultaneously, the time synchronization situation that on arrow, flight control computer is fed back by each stand-alone device received, judge that whether crucial unit on arrow is working properly (the confirmation of synchronization value of the time synchronization operational order of transmission with each stand-alone device returned to be compared, if each stand-alone device confirmation of synchronization value whole retaking of a year or grade success is also identical with the simultaneously operating director data that flight control computer on arrow sends respectively, then think that stand-alone device is working properly), and the result judged is passed through 1553B bus feedback to the central computer of ground launch vehicle measurement, on arrow, flight control computer starts flight control algorithm under each stand-alone device normal operation simultaneously, if each stand-alone device malfunction, on arrow, flight control computer does not restart flight control program, wait for follow-up floor treatment, adopt 1553B bus to carry out arrow ground communication, make arrow ground information fusion process not increase device, reduce costs,
(3) after central computer receives the court verdict that on arrow, each stand-alone device is working properly, " middle igniting " instruction is sent to synthesis observe and control device;
Central computer CPU is by 1553B bus interface module, the whether normal court verdict of each stand-alone device work on the arrow of collection flight control computer feedback, and when stand-alone device normally works, solid state relay 1 ~ solid state relay 6 action in control switch amount output module, connect again Parallel opertation " middle igniting " instruction between two in solid state relay 1 ~ solid state relay 6 contact, solid state relay has the fast characteristic of switching speed, for the low delay character of arrow ground information fusion provides guarantee.
(4) after synthesis observe and control device receives " middle igniting " instruction, carry out ladder diagram logical operation process, output " finally igniting " control signal ignites igniting fire-working article and output " bus control signal " disconnects bus-controlled switching.
Specific implementation step in step (4) is as follows:
(4a) PLC in synthesis observe and control device carries out ladder diagram logical operation process after receiving " middle igniting " instruction of central computer, exports six tunnels " finally light a fire PLC " signal and disconnects bus-controlled switching to the control conditioning circuit of second in synthesis observe and control device and output one tunnel " bus control signal "; Bus control signal has following effect: export " bus control signal " and disconnect 1553B bus switch, cut off the 1553B bus run of launch vehicle measurement and flight control computer, build-out resistor is accessed terminal bus on arrow, realize the separation of arrow ground bus, guarantee the communication quality of 1553B bus run on arrow after taking off.
(4b) second control conditioning circuit, carry out signal condition to the received signal: second control conditioning circuit carries out three get two process to receiving " igniting " signal, then Kdh1, Kdh2, Kdh3, Kdh4 tetra-electromagnetic relay line bags are driven, the all contacts of Kdh1, Kdh2 (Kdh1A, Kdh2A, Kdh1B, Kdh2B) and series connection make igniting fire-working article positive bus-bar charged, all contacts of Kdh3, Kdh4 (Kdh3A, Kdh4A, Kdh3B, Kdh4B) and series connection make the negative busbar of igniting fire-working article charged.
For improving the Security that fire-working article controls, following restrictive condition of connecting in IGNITION CONTROL passage: also connect in Kyx1, Kyx2 electromagnetic relay contact, also connect in Kzdh1, Kzh2 electromagnetic relay contact, ensures to complete igniting in the interval allowing igniting.Be implemented as follows: the contact Kzdh2A of contact Kzdh1A and the Kzdh2 of relay K zdh1 is in parallel, contact Kzdh1B and Kzdh2B is in parallel, mutually connects after parallel connection again, that the input of this series connection connects all contacts of relay K dh1, Kdh2 and output of connecting.The contact Kyx2A of contact Kyx1A and the Kyx2 of relay K yx1 is in parallel, and contact Kyx1B and Kyx2B is in parallel, mutually connects after parallel connection again, and the input of this series connection connects all contacts of Kzdh1 and Kzdh2 and the output of series connection.
Each make contact in ignition channel, M3 busbar voltage is added to igniting fire-working article two ends through current-limiting resistance, and fire-working article is ignited, and rocket body takes off after firing.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (8)
1. a low time delay ignition confirming system for arrow ground information fusion, is characterized in that comprising: flight control computer on ground launch vehicle measurement and arrow; Ground launch vehicle measurement comprises again synthesis observe and control device, center indication control board and central computer;
Center indication control board is User Interface, provides " initial ignition " signal to synthesis observe and control device.
Synthesis observe and control device, receives " initial ignition " signal that center indication control board sends, and after carrying out ladder diagram logical operation and signal condition, exports flight control computer on " time system zero point " signal to arrow; After synthesis observe and control device receives " middle igniting " instruction of central computer simultaneously, carry out ladder diagram logical operation process, output " finally igniting " control signal ignites igniting fire-working article and output " bus control signal " disconnects bus-controlled switching.
Central computer, the whether normal court verdict of each stand-alone device work on the arrow that on collection arrow, flight control computer feeds back, and when stand-alone device normally works, send " lighting a fire in centre " instruction to synthesis observe and control device.
Flight control computer on arrow, after receiving " time system zero point " signal, reset the time on current arrow, and other stand-alone device sends time of implementation simultaneously operating instruction on arrow; Simultaneously, the time synchronization situation that on arrow, flight control computer is fed back by each stand-alone device received, judge that on arrow, whether crucial unit is working properly, and by the result feedback of judgement to the central computer of ground launch vehicle measurement, on arrow, flight control computer starts flight control algorithm under each stand-alone device normal operation simultaneously.
2. the low time delay ignition confirming system of a kind of arrow ground according to claim 1 information fusion, is characterized in that: described synthesis observe and control device comprises PLC, first control conditioning circuit and second control conditioning circuit;
First control conditioning circuit comprises again relay K 11, K12; Second control conditioning circuit comprises again relay K dh1, Kdh2, Kdh3 and Kdh4;
The line bag of relay K 11, K12 is in parallel; The contact K12A of contact K11A and the K12 of relay K 11 is in parallel, and contact K11B and K12B is in parallel, mutually connects after parallel connection again;
The line bag of relay K dh1, Kdh2, Kdh3 and Kdh4 is in parallel; The contact Kdh2A of contact Kdh1A and the Kdh2 of relay K dh1 is in parallel, and contact Kdh1B and Kdh2B is in parallel, mutually connects after parallel connection again; The contact Kdh4A of contact Kdh3A and the Kdh4 of relay K dh3 is in parallel, and contact Kdh3B and Kdh4B is in parallel, mutually connects after parallel connection again;
The output terminal of PLC connects relay K 11, the line bag of K12, Kdh1, Kdh2, Kdh3 and Kdh4 and bus-controlled switching respectively.
3. the low time delay ignition confirming system of a kind of arrow ground according to claim 2 information fusion, characterized by further comprising: electromagnetic relay Kyx1, Kyx2, Kzdh1 and Kzdh2;
The contact Kzdh2A of contact Kzdh1A and the Kzdh2 of relay K zdh1 is in parallel, and contact Kzdh1B and Kzdh2B is in parallel, mutually connects after parallel connection again, that the input of this series connection connects all contacts of relay K dh1, Kdh2 and output of connecting;
The contact Kyx2A of contact Kyx1A and the Kyx2 of relay K yx1 is in parallel, and contact Kyx1B and Kyx2B is in parallel, mutually connects after parallel connection again, and the input of this series connection connects all contacts of Kzdh1 and Kzdh2 and the output of series connection.
4. the low time delay ignition confirming system of a kind of arrow ground according to claim 2 information fusion, be further characterized in that: sending out in described synthesis observe and control device is controlled conditioning circuit and can be expanded to N number of according to demand, native system only uses first control conditioning circuit, second control conditioning circuit, and the specific implementation of other control conditioning circuits designs according to concrete function.
5. the low time delay ignition confirming system of a kind of arrow ground according to claim 1 information fusion, is characterized in that: described central computer comprises CPU, 1553B bus interface module, switching value output module; Switching value output module comprises again solid state relay 1, solid state relay 2, solid state relay 3, solid state relay 4, solid state relay 5, solid state relay 6;
CPU passes through 1553B bus interface module, the whether normal court verdict of each stand-alone device work on the arrow of collection flight control computer feedback, and when stand-alone device normally works, relay closes output " lighting a fire in the centre " instruction in control switch amount output module;
Solid state relay 1 and solid state relay 2 are connected, solid state relay 3 and solid state relay 4 is connected, solid state relay 5 and solid state relay 6 are connected, and then output parallel with one another.
6., based on a confirmation method for the low time delay ignition confirming system of arrow ground according to claim 5 information fusion, it is characterized in that comprising step as follows:
(1) synthesis observe and control device of ground launch vehicle measurement receives " initial ignition " signal that center indication control board sends, and after carrying out ladder diagram logical operation and signal condition, exports flight control computer on " time system zero point " signal to arrow;
(2) after on arrow, flight control computer receives " time system zero point " signal by optocoupler, the time on current arrow is reset, and other stand-alone device send time of implementation simultaneously operating instruction on arrow; Simultaneously, the time synchronization situation that on arrow, flight control computer is fed back by each stand-alone device received, judge that on arrow, whether crucial unit is working properly, and by the result feedback of judgement to the central computer of ground launch vehicle measurement, on arrow, flight control computer starts flight control algorithm under each stand-alone device normal operation simultaneously;
(3) after central computer receives the court verdict that on arrow, each stand-alone device is working properly, " middle igniting " instruction is sent to synthesis observe and control device;
(4) after synthesis observe and control device receives " middle igniting " instruction, carry out ladder diagram logical operation process, output " finally igniting " control signal ignites igniting fire-working article and output " bus control signal " disconnects bus-controlled switching.
7. the low time delay ignition confirming method of a kind of arrow ground according to claim 6 information fusion, is characterized in that: the specific implementation step of described step (1) is as follows:
(1a) PLC in synthesis observe and control device, to three tunnels " initial ignition " signal received from center indication control board, carries out ladder diagram logical operation, exports two-way " time system zero point PLC " signal to the control conditioning circuit of first in synthesis observe and control device;
(1b) first control conditioning circuit in synthesis observe and control device, carry out signal condition to the received signal: first control conditioning circuit receives " time system zero point PLC ", first generates relay K 11, the K12 line band electricity of controlling conditioning circuit, all make contact of K11, K12, through and outputs of connecting " time unite zero point " signal to flight control computer on arrow.
8. the low time delay ignition confirming method of a kind of arrow ground according to claim 6 information fusion, is characterized in that: the specific implementation step of described step (4) is as follows:
(4a) PLC in synthesis observe and control device carries out ladder diagram logical operation process after receiving " middle igniting " instruction of central computer, exports six tunnels " finally light a fire PLC " signal and disconnects bus-controlled switching to the control conditioning circuit of second in synthesis observe and control device and output one tunnel " bus control signal ";
(4b) second control conditioning circuit, carry out signal condition to the received signal: second control conditioning circuit carries out three get two process to receiving " finally light a fire PLC " signal, then Kdh1, Kdh2, Kdh3, Kdh4 tetra-electromagnetic relay line bags are driven, the all contacts of Kdh1, Kdh2 also series connection make igniting fire-working article positive bus-bar charged, and all contacts of Kdh3, Kdh4 also series connection make the negative busbar of igniting fire-working article charged.
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| CN112130505B (en) * | 2020-09-27 | 2024-05-31 | 山东航天电子技术研究所 | Initiating explosive device ignition control circuit and method thereof |
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