CN105022318A - Wireless control system for ignition drop-test of initiating explosive device - Google Patents
Wireless control system for ignition drop-test of initiating explosive device Download PDFInfo
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- CN105022318A CN105022318A CN201510373400.1A CN201510373400A CN105022318A CN 105022318 A CN105022318 A CN 105022318A CN 201510373400 A CN201510373400 A CN 201510373400A CN 105022318 A CN105022318 A CN 105022318A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
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Abstract
The invention relates to a wireless control system for ignition drop-test of an initiating explosive device. Control display modules send instructions to an ignition control module, receive instruction from the ignition control module and execute and display feedback signals; the ignition control module controls the initiating explosive device to ignite and cut off a lifting rope, so that a spacecraft model moves according to a set movement track; a synchronous triggering module of a high-speed camera records the movement track of the spacecraft model within set time, and controls the high-speed camera to transmit movement track data of the spacecraft model to a data storage module; and the data storage module receives a shooting triggering signal of the ignition control module and stores shooting data of the high-speed camera. According to the system, the ignition control module is used to intelligently control ignition of the initiating explosive device, state information is downloaded and displayed in real time via radio, and ignition of the initiating explosive device is intelligently controlled. In addition, the system is provided with emergency intervention schemes, so that the flexibility and safety of the system are improved.
Description
Technical field
The present invention relates to spacecraft testing control field, particularly a kind of priming system igniting drop-test wireless control system.
Background technology
Spacecraft model drop-test is intended to the various attitudes that ground is come when Simulated Spacecraft lands by high tower fixed point drop-test model, to verify that can it land with security and stability in all kinds of celestial body surface such as ground surface, lunar surface, Mars, and when testing its landing, whether various performance parameters meets predetermined design.Therefore require under the control of controlling test equipment, test model should be able to Simulated Spacecraft land time the parameters such as acceleration of gravity, landing speed, attitude, position, angle.To require that opertaing device can the gesture stability of implementation model and parameter measurement for this reason.
Traditional spacecraft high tower drop-test control system adopts priming system igniting to realize throwing in control, but ignition control method comparatively backwardness.Realized the Control on Communication of high tower upper and lower mould interblock during test by the long and wire cable of heaviness, therefore all need be set up by testing crew and remove receipts cable carrying out each test.Simultaneously controlling test equipment cannot pass under the information of voltage being positioned at the priming system ignition battery of high tower, therefore testing crew all needs to climb up high tower and measures cell voltage and whether meet next testing requirements when often completing single test, greatly add the workload of testing crew, the more important thing is that traditional input opertaing device is non intelligent IGNITION CONTROL, during test by operating personnel visually spacecraft model throw in the position and the target that fall and whether overlap and control each road priming system and light a fire, therefore in each test, all there is artificial uncertain difference on the opportunity of igniting, the consistance of test findings state is poor.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, provides a kind of by controlling the igniting of ignition module Based Intelligent Control priming system, and status information is passed down by radio and the priming system igniting drop-test wireless control system of display in real time.
Technical solution of the present invention is: a kind of priming system igniting drop-test wireless control system, comprise control display module, control ignition module, height takes the photograph synchronous trigger module, data memory module, wherein
Control display module, produce and send the instruction of high tower voltage request to controlling ignition module, receive the high tower voltage status value controlling ignition module transmission and show; Sending the 1st road priming system pre-ignition instruction, the 1st road priming system firing command to controlling ignition module, receiving the 1st road priming system pre-ignition settling signal of control ignition module transmission, the 1st road priming system igniting settling signal and all the other each road priming system igniting settling signals and showing; When controlling in ignition module ignition process, when spacecraft model attitude occurring abnormal, producing and sending and removing firing command to controlling ignition module, show after instruction and the releasing that reception control ignition module sends has been lighted a fire; After each road priming system has been lighted a fire, produce and send igniting reset instruction to controlling ignition module, receive the igniting reset settling signal of control ignition module transmission and show, wherein, transmission or the reception of instruction, signal all adopt wireless mode;
Control ignition module, receive the high tower voltage request instruction controlling display module and send, gather high tower voltage status value, and be sent to control display module; Receive the 1st road priming system pre-ignition instruction controlling display module, connect the 1st road priming system pre-ignition circuit, and send the 1st road priming system pre-ignition settling signal to controlling display module; Receive the 1st road priming system firing command, connect the 1st road priming system firing circuit to the 1st road priming system igniting, cut off the lifting rope is connected with the 1st road priming system, and send the 1st road priming system igniting settling signal extremely control display module take the photograph synchronous trigger module with height; After 1st road priming system has been lighted a fire, successively all the other priming systems being lighted a fire according to igniting sequential, and after each road priming system has been lighted a fire, cut off the lifting rope that this road priming system connects, sending this road priming system igniting settling signal to controlling display module simultaneously; Reception controls the releasing firing command that display module sends, and stops the priming system igniting to not lighting a fire, and produces and send releasing igniting to complete instruction to controlling display module; After receiving the igniting reset instruction controlling display module transmission, 1st road priming system pre-ignition circuit, the 1st road priming system firing circuit and all the other each road priming system firing circuits are disconnected, produce and send igniting reset settling signal to controlling display module, wherein, controlling ignition module is placed on high tower, and high tower is powered to control ignition module, spacecraft model hangs on high tower by least two lifting ropes, corresponding lifting rope can be cut off during the priming system igniting of every road, lifting rope is separated with high tower, and transmission or the reception of instruction, signal all adopt wireless mode; Described igniting sequential is after the 1st road priming system of pre-stored has been lighted a fire, the sequential of all the other each road priming system igniting; Being wound around appears in the abnormal lifting rope for hanging spacecraft model of described attitude;
Height takes the photograph synchronous trigger module, comprise at least two video cameras, video camera to be laid in respectively near spacecraft model and can to cover all movement locus of spacecraft model, spacecraft model motion trace data in the video camera shooting record fixed time is controlled after receiving the 1st road priming system igniting settling signal or all the other road priming system igniting settling signals controlling ignition module transmission, produce and store trigger pip to data memory module, and control video camera spacecraft model motion trace data is transferred to data memory module, wherein, all movement locus of spacecraft model are the movement locus after lifting rope is cut off, instruction, transmission or the reception of signal all adopt wireless mode,
Data memory module, after receiving the storage trigger pip of video camera transmission, the spacecraft model motion trace data receiving video camera transmission also stores, and the reception of instruction, data all adopts wireless mode.
Described collection high tower voltage status value is for gather by voltage compare Acquisition Circuit, and voltage compare Acquisition Circuit comprises LDO power supply voltage stabilizing chip, series connection divider resistance, divider resistance in parallel, voltage comparator; LDO power supply voltage stabilizing chip input end, series connection divider resistance one end are connected with the power supply of high tower respectively, LDO power supply voltage stabilizing chip output is connected with the positive input of voltage comparator, the series connection divider resistance other end, divider resistance one end in parallel are connected with the negative input of voltage comparator respectively, LDO power supply voltage stabilizing chip ground end, divider resistance other end ground connection in parallel, voltage comparator output terminal exports high tower voltage status value.
Described lifting rope has 6.
The height of described high tower is 100 meters.
The described fixed time is 2s.
The present invention's advantage is compared with prior art:
(1) wireless control system of the present invention overcomes the deficiencies in the prior art, by controlling the igniting of ignition module Based Intelligent Control priming system, and by status information by passing under radio and showing in real time, while realizing intelligentized control method, also be provided with emergence environment prediction scheme, when occurring that in test lifting rope such as to harass and disturb at the emergency case, emergency termination test, drastically increases dirigibility and the security of system;
(2) wireless control system of the present invention adopts wireless mode to control each functional module, compares wired control mode, eliminate high tower and set up length up and down and the cable of heaviness, and the installation position of each module device also will be more flexible;
(3) information such as action executing state, supplying cell voltage being placed in the control ignition module of high tower wirelessly can be reached down control display module by wireless control system of the present invention, facilitates testing crew to control the status information of each equipment in real time;
(4) wireless control system employing pre-ignition of the present invention, dual command serial control mode of lighting a fire realize the 1st priming system IGNITION CONTROL jointly, effectively prevent from starting drop-test because of a maloperation, enhance the security of control system, adopt the whole ignition process of igniting sequential Based Intelligent Control in test simultaneously, non-burst situation can complete whole test without the need to human interaction, and it is convenient flexibly to use;
(5) wireless control system of the present invention is provided with the intervention interface under emergency case, when finding that lifting rope harasses and disturbs situations such as causing test model attitude exception, " removing igniting " instruction can be launched by control display module and carry out emergency termination test, loss is down to minimum;
(6) wireless control system of the present invention carrys out cut-off point ignition circuit by wireless remote control igniting reset instruction, continue to occur Short-Circuit High Current state after effectively preventing igniting, more traditional priming system firing circuit series limiting resistor method, measure the work of current-limiting resistance resistance after avoiding each igniting, greatly improve test efficiency.
Accompanying drawing explanation
Fig. 1 is a kind of priming system igniting of the present invention drop-test wireless control system structural drawing;
Fig. 2 is that the present invention controls display module circuit diagram;
Fig. 3 is that the present invention controls display module workflow diagram;
Fig. 4 is that the present invention controls igniting modular circuit schematic diagram;
Fig. 5 is that the present invention controls igniting module work process flow diagram;
To be that the present invention is high take the photograph synchronous trigger module circuit diagram to Fig. 6;
To be that the present invention is high take the photograph synchronous trigger module workflow diagram to Fig. 7.
Embodiment
The present invention proposes a kind of priming system igniting drop-test wireless control system, spacecraft testing model hangs on 100 meters of high towers by lifting rope (lifting rope quantity is 6) as shown in Figure 1, controls by present system the input cutting off lifting rope implementation model.Present system comprises and controls display module, controls ignition module, height and take the photograph synchronous trigger module, data memory module.Control display module during test, height takes the photograph synchronous trigger module, data memory module is all placed in ground; Control display module to be used for controlling the complete feedback signal of instruction of ignition module to control ignition module transmission instruction, reception and showing; Height takes the photograph synchronous trigger module, spacecraft model motion trace data in the high-speed camera shooting record fixed time is controlled after receiving the 1st road priming system igniting settling signal or all the other road priming system igniting settling signals controlling ignition module transmission, produce and store trigger pip to data memory module, and control high-speed camera spacecraft model motion trace data is transferred to data memory module; Data memory module receives the shooting trigger pip controlling ignition module, the camera data of storing high-speed video camera; Control ignition module and be then placed in high tower, for controlling 6 road priming system igniting, driving firer's cutter action corresponding with it, cutting off lifting rope, make spacecraft model according to the movement locus motion of setting.Be described in detail below in conjunction with accompanying drawing, as shown in Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7:
Control display module, comprise the first master control display unit, the first wireless transmit/receive units as shown in Figure 2, be illustrated in figure 3 the execution flow process controlling display module, wherein, the first wireless transmit/receive units to be lighted a fire the Signal transmissions of intermodule for completing the first master control display unit and master control.First master control display unit, produce high tower voltage request useful signal, receive (high level is effective) by the IO1 mouth of Programmable Logic Device CPLD, and be encoded to " 01010000 ", transfer to the first wireless transmit/receive units through bus interface such as RS485 and launch; The feedback signal controlling ignition module and send is received by the first wireless transmit/receive units, interpretation data " if XXXX0001 " after decoding, control battery capacity indication lamp by IO6 mouth output low level to send out a warning, if " XXXX1111 ", export battery capacity indication lamp by IO7 mouth and give a green light.Produce the 1st road priming system pre-ignition instruction, the 1st road priming system firing command, received (high level is effective) by IO2, IO3 of CPLD, be encoded to respectively " 01010010 " and " 01010100 ", be sent to the first wireless transmit/receive units by I/O port successively and send; The feedback signal of ignition controller output is received by the first wireless transmit/receive units, decoded data interpretation, " if XXXX0011 ", then control the 1st road priming system pre-ignition pilot lamp by IO8 mouth output low level bright, " if XXXX0101 ", then control the 1st road priming system ignition light by IO9 mouth output low level bright.If be respectively " XXXX1010 ~ XXXX1110 ", then by IO12, IO13 ... IO15 port respectively corresponding output low level, controls the 2nd ~ 6th road priming system pilot lamp of having lighted a fire bright.If control ignition module to occur that in ignition process spacecraft model lifting rope harasses and disturbs emergency case such as causing attitude extremely, produce and remove firing command, receive (high level is effective) by IO4, be encoded to " 01011000 ", sent by the first wireless transmit/receive units; By the feedback signal that the first wireless transmit/receive units reception ignition controller sends, interpretation after decoding, if " XXXX1001 ", it is bright that control IO11 output low level control releasing igniting completes pilot lamp.After the priming system igniting of each road, produce igniting reset instruction, receive (high level is effective) by IO5, be encoded to " 01010110 ", sent by the first wireless transmit/receive units; The feedback signal that ignition controller exports is received, if interpretation " XXXX0111 " control IO10 output low level controls igniting reset to complete pilot lamp bright after decoding by the first wireless transmit/receive units.
Control ignition module, comprise the second master control igniting unit, the second wireless transmit/receive units as shown in Figure 4, if Fig. 5 is that the control program controlling ignition module performs flow process, wherein, second wireless transmit/receive units receives the wireless data that master control display module sends, and transfers to the second master control igniting unit by RS485 bus interface; Receive the action that this bus interface receives the second master control igniting unit and complete feedback signal, by being wirelessly transmitted to master control display module.Second master control igniting unit, the data that receipt decoding interpretation second wireless transmit/receive units send, if high tower voltage request instruction " XXXX0000 ", the high tower voltage status value gathered is received by the IO12 of Programmable Logic Device CPLD, be 1 to be encoded to " 01000001 ", be 0 to be encoded to " 01001111 ", be sent to control display module by the second wireless transmit/receive units; If pre-ignition instruction " XXXX0010 ", then IO2 mouth output low level is controlled the 1st road priming system pre-ignition circuit ON, IO1 mouth receives and interpretation level state, if high level, then be encoded to " 01000011 " (the 1st road priming system pre-ignition settling signal), send through the second wireless transmit/receive units; If firing command " XXXX0100 ", then IO4 mouth output low level is controlled the 1st road priming system firing circuit to connect, realize the 1st road priming system igniting, firer's cutter is driven to cut off the 1st lifting rope, IO3 mouth receives and interpretation level state simultaneously, if high level, be then encoded to " 01000101 " (the 1st road priming system igniting settling signal), send through the second wireless transmit/receive units; IO6, IO8, IO10,1O12, IO14 output low level is controlled follow-up 2nd ~ 6 road priming system firing circuits and connects by program automatically successively, realize 2nd ~ 6 road priming system igniting, corresponding firer's cutter is driven to cut off 2nd ~ 6 lifting ropes, with the level state judging IO5, IO7, IO9,1O11, IO13 port successively, for low level is then encoded to 2nd ~ 6 priming system igniting settling signal " 01001010 " ~ " 01001110 ", road respectively, send through the second wireless transmit/receive units; Automatically perform in follow-up 2 ~ 6 road priming system ignition processes in program, firing command " XXXX1000 " is removed if receive, then represent and occur emergency case, default automatic ignition program will be jumped out, stop the priming system igniting of not lighting a fire to follow-up, and be encoded to " 01001001 " and launch through the second wireless transmit/receive units; If igniting reset instruction " XXXX0110 ", then IO2, IO4, IO6, IO8, IO10,1O12, IO14 are exported high level, cut off priming system firing circuit, and be encoded to " 01000111 ", send through the second wireless transmit/receive units.Wherein, described collection high tower voltage status value is for gather by voltage compare Acquisition Circuit, and voltage compare Acquisition Circuit comprises LDO power supply voltage stabilizing chip, series connection divider resistance, divider resistance in parallel, voltage comparator; LDO power supply voltage stabilizing chip input end, series connection divider resistance one end are connected with high tower power supply respectively, LDO power supply voltage stabilizing chip output is connected with the positive input of voltage comparator, the series connection divider resistance other end, divider resistance one end in parallel are connected with the negative input of voltage comparator respectively, LDO power supply voltage stabilizing chip ground end, divider resistance other end ground connection in parallel, voltage comparator output terminal exports high tower voltage status value.
Height takes the photograph synchronous trigger module, as shown in Figure 6, need at the trial to configure at least two high-speed cameras, be laid in spacecraft model respectively to throw near place and all movement locus that can cover spacecraft model, this module comprises the 3rd master control image unit, 3rd wireless transmit/receive units, be illustrated in figure 7 height and take the photograph synchronous trigger module workflow, the wireless signal controlling ignition module and send is received by the 3rd wireless transmit/receive units, be sent to the 3rd master control image unit to carry out decoding and data interpretation, if the 1st road priming system igniting settling signal " XXXX0101 ", then IO1 is set to low level, control the 1st tunnel shooting trigger relay to close, output switch amount signal, if the second road priming system igniting settling signal " XXXX1010 ", be then set to low level by IO2, control the 2nd tunnel shooting trigger relay and close, output switch amount signal, the like, the output of trigger pip of making a video recording after completing totally 6 road priming system igniting.
Data memory module, under the shooting store clock signal function that high-speed camera sends, the spacecraft motion trace data that reception high-speed camera records also stores.
Wherein, after the program initialization of above-mentioned first master control display unit, the second master control igniting unit, the 3rd master control image unit, the I/O port being defined as output function is all set to high level; Each main control unit receives and in decoded data, high four figures all represents binary data 0 or 1 according to " XXXX " each, does not judge in program to high four.First wireless transmit/receive units, the second wireless transmit/receive units are to the priority of the priority of reception of wireless signals higher than wireless signal transmission, when namely carrying out wireless signal transmission, first need judge that whether reception of wireless signals status indicator is invalid, just signal can be launched enable being set to effectively time invalid, carry out wireless signal transmission.
The content be not described in detail in instructions of the present invention belongs to the known technology of those skilled in the art.
Claims (5)
1. a priming system igniting drop-test wireless control system, it is characterized in that comprising control display module, control ignition module, height takes the photograph synchronous trigger module, data memory module, wherein
Control display module, produce and send the instruction of high tower voltage request to controlling ignition module, receive the high tower voltage status value controlling ignition module transmission and show; Sending the 1st road priming system pre-ignition instruction, the 1st road priming system firing command to controlling ignition module, receiving the 1st road priming system pre-ignition settling signal of control ignition module transmission, the 1st road priming system igniting settling signal and all the other each road priming system igniting settling signals and showing; When controlling in ignition module ignition process, when spacecraft model attitude occurring abnormal, producing and sending and removing firing command to controlling ignition module, show after instruction and the releasing that reception control ignition module sends has been lighted a fire; After each road priming system has been lighted a fire, produce and send igniting reset instruction to controlling ignition module, receive the igniting reset settling signal of control ignition module transmission and show, wherein, transmission or the reception of instruction, signal all adopt wireless mode;
Control ignition module, receive the high tower voltage request instruction controlling display module and send, gather high tower voltage status value, and be sent to control display module; Receive the 1st road priming system pre-ignition instruction controlling display module, connect the 1st road priming system pre-ignition circuit, and send the 1st road priming system pre-ignition settling signal to controlling display module; Receive the 1st road priming system firing command, connect the 1st road priming system firing circuit to the 1st road priming system igniting, cut off the lifting rope is connected with the 1st road priming system, and send the 1st road priming system igniting settling signal extremely control display module take the photograph synchronous trigger module with height; After 1st road priming system has been lighted a fire, successively all the other priming systems being lighted a fire according to igniting sequential, and after each road priming system has been lighted a fire, cut off the lifting rope that this road priming system connects, sending this road priming system igniting settling signal to controlling display module simultaneously; Reception controls the releasing firing command that display module sends, and stops the priming system igniting to not lighting a fire, and produces and send releasing igniting to complete instruction to controlling display module; After receiving the igniting reset instruction controlling display module transmission, 1st road priming system pre-ignition circuit, the 1st road priming system firing circuit and all the other each road priming system firing circuits are disconnected, produce and send igniting reset settling signal to controlling display module, wherein, controlling ignition module is placed on high tower, and high tower is powered to control ignition module, spacecraft model hangs on high tower by least two lifting ropes, corresponding lifting rope can be cut off during the priming system igniting of every road, lifting rope is separated with high tower, and transmission or the reception of instruction, signal all adopt wireless mode; Described igniting sequential is after the 1st road priming system of pre-stored has been lighted a fire, the sequential of all the other each road priming system igniting; Being wound around appears in the abnormal lifting rope for hanging spacecraft model of described attitude;
Height takes the photograph synchronous trigger module, comprise at least two video cameras, video camera to be laid in respectively near spacecraft model and can to cover all movement locus of spacecraft model, spacecraft model motion trace data in the video camera shooting record fixed time is controlled after receiving the 1st road priming system igniting settling signal or all the other road priming system igniting settling signals controlling ignition module transmission, produce and store trigger pip to data memory module, and control video camera spacecraft model motion trace data is transferred to data memory module, wherein, all movement locus of spacecraft model are the movement locus after lifting rope is cut off, instruction, transmission or the reception of signal all adopt wireless mode,
Data memory module, after receiving the storage trigger pip of video camera transmission, the spacecraft model motion trace data receiving video camera transmission also stores, and the reception of instruction, data all adopts wireless mode.
2. a kind of priming system igniting drop-test wireless control system according to claim 1, it is characterized in that: described collection high tower voltage status value is for gather by voltage compare Acquisition Circuit, and voltage compare Acquisition Circuit comprises LDO power supply voltage stabilizing chip, series connection divider resistance, divider resistance in parallel, voltage comparator; LDO power supply voltage stabilizing chip input end, series connection divider resistance one end are connected with the power supply of high tower respectively, LDO power supply voltage stabilizing chip output is connected with the positive input of voltage comparator, the series connection divider resistance other end, divider resistance one end in parallel are connected with the negative input of voltage comparator respectively, LDO power supply voltage stabilizing chip ground end, divider resistance other end ground connection in parallel, voltage comparator output terminal exports high tower voltage status value.
3. a kind of priming system igniting drop-test wireless control system according to claim 1 and 2, is characterized in that: described lifting rope has 6.
4. a kind of priming system igniting drop-test wireless control system according to claim 1 and 2, is characterized in that: the height of described high tower is 100 meters.
5. a kind of priming system igniting drop-test wireless control system according to claim 1 and 2, is characterized in that: the described fixed time is 2s.
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| CN201510373400.1A CN105022318B (en) | 2015-06-30 | 2015-06-30 | A kind of priming system igniting drop-test wireless control system |
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| CN201510373400.1A CN105022318B (en) | 2015-06-30 | 2015-06-30 | A kind of priming system igniting drop-test wireless control system |
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| CN105022318B (en) | 2017-09-29 |
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