CN111392071B - Initiating explosive device detonation control system and testing method thereof - Google Patents
Initiating explosive device detonation control system and testing method thereof Download PDFInfo
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- CN111392071B CN111392071B CN202010185033.3A CN202010185033A CN111392071B CN 111392071 B CN111392071 B CN 111392071B CN 202010185033 A CN202010185033 A CN 202010185033A CN 111392071 B CN111392071 B CN 111392071B
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- 230000000977 initiatory effect Effects 0.000 title claims abstract description 146
- 239000002360 explosive Substances 0.000 title claims abstract description 132
- 238000005474 detonation Methods 0.000 title claims abstract description 59
- 238000012360 testing method Methods 0.000 title claims description 36
- 238000005259 measurement Methods 0.000 claims abstract description 6
- 238000000034 method Methods 0.000 claims description 11
- 239000003999 initiator Substances 0.000 claims 1
- 238000010998 test method Methods 0.000 claims 1
- 238000007599 discharging Methods 0.000 abstract description 5
- 230000005611 electricity Effects 0.000 abstract description 4
- 230000003068 static effect Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 7
- 230000037452 priming Effects 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 230000003044 adaptive effect Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000002265 prevention Effects 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012790 confirmation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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Abstract
The invention discloses an initiating explosive device detonation control system which realizes control of initiating explosive device detonation through three-level control. The control system comprises a control circuit and a protection and measurement system, wherein the control circuit comprises a first relay, a second relay and a third relay which are used for controlling the on-off of a circuit, a current-limiting resistor which is connected with the relays in series, a shell-connected ground and a discharge resistor which is used for discharging static electricity; the protection and measurement system comprises a plurality of star watch sockets, the star watch sockets are connected with protection plugs or emission plugs in an inserting mode, the on-off of the initiating explosive device control circuit can be controlled, and the initiating explosive device initiating loop, the initiating time sequence and the bridge wire resistance value can be measured for many times at any stage.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a priming system and a testing method thereof for initiating explosive devices.
Background
The initiating explosive device is a common sailboard unfolding separation initiation device on the spacecraft, and after the spacecraft is in orbit, initiation action of the sailboard initiating explosive device is needed to be carried out firstly so as to realize mechanism unlocking and solar sailboard unfolding and supply energy to the spacecraft.
Usually, a large sailboard unfolding test is performed before the spacecraft is launched to verify the correctness of the initiating explosive device detonation circuit design. Therefore, the initiating explosive device path design is a key link of the safe and reliable design of the spacecraft, and whether the initiating explosive device is designed reasonably or not and whether the verification is sufficient or not directly influences the success or failure of the launching task.
The existing initiating explosive device detonation control system is limited by test safety and a test field, large-scale double-wing sailboard unfolding operation is difficult to carry out, and single wings need to be unfolded respectively, so that the reliability and the safety of initiating explosive devices need to be improved; in addition, the spacecraft is generally difficult to perform final measurement before being launched into a launching tower, so that the testing of initiating explosive devices is insufficient.
Disclosure of Invention
In view of some or all of the problems of the prior art, an aspect of the present invention provides a priming control system for initiating explosive devices, including:
a control circuit, comprising:
the first relay is connected with the positive electrode of the detonation power supply and controls the on-off of the positive line of the initiating explosive device;
the second relay is connected with the negative electrode of the detonation power supply and controls the on-off of the initiating explosive device loop;
the third relay is connected with the positive electrode of the initiating explosive device bridge wire and used for controlling the initiating explosive device to detonate;
a current limiting resistor connected in series between the first relay and the third relay,
the first bleeder resistor is connected to the positive end of the initiating explosive device bridge wire and connected to the shell ground; and
the second bleeder resistor is connected with the negative end of the initiating explosive device bridging wire and connected with the shell ground; and
protection and measurement system, comprising:
the positive and negative electrodes of the input end of the first star meter socket are respectively and electrically connected with the positive and negative electrodes of the power output port of the detonation power supply of the positive wing sailboard, and the positive and negative electrodes of the output end of the first star meter socket are respectively and electrically connected with the positive and negative electrodes of the initiating explosive device bridge wire;
the positive and negative electrodes of the input end of the second star meter socket are respectively and electrically connected with the positive and negative electrodes of the power output port of the detonation power supply of the negative wing sailboard, and the positive and negative electrodes of the output end of the second star meter socket are respectively and electrically connected with the positive and negative electrodes of the initiating explosive device bridge wire;
the third star watch socket is electrically connected with a ground falling plug, wherein the ground falling plug is electrically connected with the rocket power socket, and the rocket power socket is connected with the initiating explosive device bridge wire in parallel;
the protection plug can be in adaptive connection with the first star watch socket, the second star watch socket and the third star watch socket, and after the protection plug is connected with the first star watch socket or the second star watch socket, the output end of the first star watch socket or the second star watch socket is in short circuit, so that the initiating explosive device bridge wire is powered off; after the protection plug is connected with the third star watch socket, the output end of the third star watch socket is in short circuit, so that the initiating explosive device bridge wire is in short circuit; and
and the transmitting plug can be in adaptive connection with the first star watch socket and the second star watch socket, and after the transmitting plug is connected with the first star watch socket or the second star watch socket, the input end and the output end of the first star watch socket or the second star watch socket are conducted to supply power to the initiating explosive device bridge wire.
Further, the system is used for controlling N initiating explosive devices, wherein each initiating explosive device comprises a main bridge wire and a standby bridge wire.
Furthermore, any main bridge wire and any standby bridge wire are provided with independent priming power supplies.
Furthermore, the cathodes of all the main bridge wires and the standby bridge wires are a common cathode.
Further, the detonation power supply is a storage battery pack.
Further, the second bleeder resistor comprises M resistors connected in parallel.
The invention also provides a testing method of the initiating explosive device detonation control system, which comprises the following steps:
the method comprises the following steps of checking the path and the sequence of initiating explosive devices, connecting initiating explosive device equivalents to a first star watch socket and a second star watch socket to enable the initiating explosive device equivalents and a control circuit to form a power-on loop, sending an instruction, and observing the working state of the initiating explosive device equivalents;
the detonation test is carried out, wherein the launching plug is respectively connected to the first star watch socket and the second star watch socket, and the detonation test is carried out; and
and (3) resistance testing, namely measuring the resistances of the bridge wire resistor and the current-limiting resistor before the detonation experiment and at each stage of the launching field, and if the resistance of the current-limiting resistor changes within 0.5%, indicating that the path is normal.
Further, the initiating explosive device equivalent device comprises an equivalent bridgewire resistor, a light emitting diode connected with the equivalent bridgewire resistor in series and a voltage test port, and if the light emitting diode is bright after a detonation instruction is received, the path is normal.
Further, the resistance value of the equivalent bridge wire resistor is 10 +/-0.5K omega.
According to the initiating explosive device detonation control system, the initiating explosive device detonation is controlled through three-level control, and meanwhile, in order to ensure the reliability of the control system, two groups of power supplies are adopted to respectively supply power to the main bridge wire and the standby bridge wire of the initiating explosive device. In order to prevent the current of the initiating explosive device from exceeding the detonation range and causing short circuit caused by the fact that the bridge wire is fused and the satellite shell is lapped, the current limiting resistor is connected in series in the control circuit of the system, the current limiting resistor can keep stable resistance under a normal state, and once the current exceeds the range, the current limiting resistor can be rapidly burnt. In addition, the control circuit of the system is also provided with a leakage resistor connected with the shell ground, and the leakage resistor is used for preventing the condition that the initiating explosive device fails or is mistakenly exploded due to the fact that static electricity exceeds the withstand voltage index of the bridge wire. Meanwhile, a protective plug or a transmitting plug is inserted in the star watch socket, so that the on-off of the control circuit can be switched at any time, and the functions of short circuit prevention and misoperation prevention are achieved. After multiple verification, the initiating explosive device detonation control system provided by the invention can obviously improve the reliability and safety of initiating explosive device detonation and improve the satellite launching work efficiency.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
FIG. 1 illustrates a control circuit schematic of an initiating explosive device detonation control system according to one embodiment of the invention;
FIG. 2 shows a schematic diagram of a star watch plug of an initiating explosive device detonation control system according to an embodiment of the invention;
FIG. 3 shows a schematic view of the position of the compacting point of the windsurfing board according to an embodiment of the present invention;
FIG. 4 illustrates a schematic diagram of the initiation path of an initiating explosive device initiation control system according to one embodiment of the present invention;
FIG. 5 illustrates a schematic diagram of an initiating explosive device equivalent of an initiating explosive device detonation control system according to an embodiment of the invention; and
fig. 6 is a schematic diagram illustrating the principle of access and timing check of an initiating explosive device detonation control system according to an embodiment of the invention.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
The invention provides an initiating explosive device detonation control system which detonates an initiating explosive device through an unlocking instruction. In one embodiment of the invention, the system is used for controlling N priming sytems, wherein each priming sytems comprises a main bridge wire and a spare bridge wire, any main bridge wire and any spare bridge wire are provided with independent priming power supplies, and the negative electrodes of all the main bridge wires and the spare bridge wires are a common negative electrode. In yet another embodiment of the present invention, the initiation power source is a battery pack.
Fig. 1 shows a control circuit schematic diagram of an initiating explosive device detonation control system according to an embodiment of the invention. As shown in fig. 1, the control circuit includes:
the first relay 111 is connected with the positive electrode of the detonation power supply 104 and used for controlling the on-off of a positive line of the initiating explosive device;
one end of the second relay 112 is connected with the negative electrode of the detonation power supply 104, and the other end of the second relay 112 is connected with the negative electrode of the initiating explosive device bridging filament 105, and is used for controlling the on-off of the initiating explosive device return wire;
the third relay 113 is connected with the positive electrode of the initiating explosive device bridgewire 105 and used for controlling the initiation of the initiating explosive device;
the current-limiting resistor 102 is connected in series between the first relay and the third relay, and the resistance value of the current-limiting resistor is calculated according to the voltage of an initiation power supply and the initiation current of initiating explosive devices;
one end of the first discharge resistor 131 is connected with the anode of the initiating explosive device bridgewire 105, and the other end of the first discharge resistor is connected with the satellite shell and used for discharging static electricity; and
and one end of the second discharging resistor 132 is connected with the negative electrode of the initiating explosive device bridgewire 105, and the other end of the second discharging resistor is connected with the satellite shell and used for discharging static electricity. In an embodiment of the present invention, the second bleeder resistor 132 is M resistors connected in parallel.
The protection and measurement system comprises:
as shown in fig. 2, the positive and negative electrodes of the input end of the first star watch socket 201 are electrically connected to the positive and negative electrodes of the power output port of the detonation power supply of the positive wing sailboard, respectively, and the positive and negative electrodes of the output end are electrically connected to the positive and negative electrodes of the initiating explosive device bridge wire, respectively;
as shown in fig. 2, the positive and negative poles of the input end of the second star watch socket 202 are respectively and electrically connected with the positive and negative poles of the power output port of the priming power supply of the negative wing sailboard, and the positive and negative poles of the output end are respectively and electrically connected with the positive and negative poles of the initiating explosive device bridge wire;
a third star catalogue socket 203, as shown in fig. 2, electrically connected to a ground drop-off plug 001, wherein the ground drop-off plug is electrically connected to the rocket power socket, and the rocket power socket is connected in parallel to the initiating explosive device bridgewire, so that electrostatic protection and testing of the resistance of the initiating explosive device bridgewire can be realized through the third star catalogue socket in a launching site technology area and during transportation to a launching tower;
the protection plug can be in adaptive connection with the first star watch socket, the second star watch socket and the third star watch socket, after the protection plug is connected with the first star watch socket or the second star watch socket, the output end of the first star watch socket or the second star watch socket is in short circuit, so that the bridge wire of the initiating explosive device is powered off, the initiating explosive device cannot be detonated whether an instruction is sent or not in a test process or a transportation process, and the safety of the initiating explosive device before shooting can be ensured; after the protection plug is connected with the third star watch socket, the output end of the third star watch socket is in short circuit, so that the initiating explosive device bridge wire is in short circuit, the initiating explosive device cannot be ignited no matter whether an instruction is sent or not in a test process or a transportation process, and the safety of the initiating explosive device and the solar sailboard before shooting can be ensured; and
and the transmitting plug can be in adaptive connection with the first star watch socket and the second star watch socket, and after the transmitting plug is connected with the first star watch socket or the second star watch socket, the input end and the output end of the first star watch socket or the second star watch socket are conducted to supply power to the initiating explosive device bridge wire, and the state is consistent with the final flight state of a satellite.
In one embodiment of the invention, a switch-on signal is led from the protection plug and/or the transmission plug to the on-board acquisition unit 002 to determine its switch-on state.
In one embodiment of the invention, the control system is applied to high orbit satellites. As shown in fig. 3, four initiating explosive devices are installed on each sailboard of the high orbit satellite, and eight initiating explosive devices are provided in total, wherein each initiating explosive device has a main bridge wire and a backup bridge wire, and two groups of storage battery packs are used for independently supplying power to the main bridge wire and the backup bridge wire of each initiating explosive device respectively. Because of a large number of initiating explosive devices, the control system adopts three star catalogue sockets, as shown in fig. 4, the input end of a first star catalogue socket 401 is electrically connected with the initiation power supply 404 of the front wing sailboard, and the output end of the first star catalogue socket is electrically connected with a first initiating explosive device main bridge wire 11, a first initiating explosive device spare bridge wire, a second initiating explosive device main bridge wire, a second initiating explosive device spare bridge wire, a third initiating explosive device main bridge wire, a third initiating explosive device spare bridge wire, a fourth initiating explosive device main bridge wire and a fourth initiating explosive device spare bridge wire 42 respectively; the input end of the second star catalogue socket 402 is electrically connected with the initiation power supply of the negative wing sailboard, and the output end is respectively electrically connected with the fifth initiating explosive device main bridge wire 51, the fifth initiating explosive device standby bridge wire, the sixth initiating explosive device main bridge wire, the sixth initiating explosive device standby bridge wire, the seventh initiating explosive device main bridge wire, the seventh initiating explosive device standby bridge wire, the eighth initiating explosive device main bridge wire and the eighth initiating explosive device standby bridge wire 82; and a third star watch socket 403 electrically connected to a ground-drop plug 001, wherein the ground-drop plug 001 is electrically connected to a first rocket power socket 003 and a second rocket power socket 004, the first rocket power socket 003 is electrically connected to an output terminal of the first star watch socket 401, and the second rocket power socket 004 is electrically connected to an output terminal of the second star watch socket 402.
When the control system is subjected to the detonation test, the path and the time sequence of initiating explosive devices, the detonation test and the resistance test need to be carried out.
As shown in fig. 5, the initiating explosive device path and the time sequence check include accessing the initiating explosive device equivalent device to the first star catalogue socket, so that the initiating explosive device equivalent device and the control circuit form a power-on loop, sending a command, and observing the working state of the initiating explosive device equivalent device. The initiating explosive device equivalent device comprises an equivalent bridgewire resistor, a light emitting diode and a voltage test port, wherein the light emitting diode is connected with the equivalent bridgewire resistor in series, and if a detonation instruction is received, the light emitting diode is on, and the condition that a path is normal is indicated. In one embodiment of the present invention, the equivalent bridge wire resistor has a resistance of 10 ± 0.5K Ω.
For a high orbit satellite with eight initiating explosive devices, the schematic diagram of the initiating explosive device passage and the timing sequence checking is shown in fig. 6, wherein only the circuit of the initiating explosive device equivalent device 1 for checking each main bridge wire of the initiating explosive device is shown in the diagram, and the circuit of the initiating explosive device equivalent device 2 for checking each standby bridge wire of the initiating explosive device is consistent with the circuit and is not listed. After the initiating explosive device equivalent device is connected, an initiating explosive device loop connection instruction, an initiating explosive device power supply connection instruction, an initiating explosive device 1 detonation instruction and an initiating explosive device 2 detonation instruction are sent respectively, and the numerical values of a light emitting diode and a voltage test port of the initiating explosive device equivalent device are observed. If the light emitting diodes L11, L13, L15 and L17 of the initiating explosive device equivalent device 1 are lighted after the initiating explosive device 1 initiating instruction is received, it indicates that the control paths of the first initiating explosive device, the third initiating explosive device, the fifth initiating explosive device and the seventh initiating explosive device controlled by the initiating explosive device 1 initiating instruction are normal; if the light emitting diodes L12, L14, L16 and L18 of the initiating explosive device equivalent device 1 are lighted after receiving the initiating instruction of the initiating explosive device 2, it indicates that the control paths of the second initiating explosive device, the fourth initiating explosive device, the sixth initiating explosive device and the eighth initiating explosive device controlled by the initiating instruction of the initiating explosive device 2 are normal.
The detonation test comprises the step of connecting the emission plug to the first star watch socket and the second star watch socket respectively to carry out the detonation test. For a high orbit satellite with eight initiating explosive devices, when the single-wing front plate is unfolded in the detonation test, a transmitting plug is inserted into a first star watch socket, a protection plug is inserted into a second star watch socket, and a third star watch socket is vacant; when the single-wing negative plate side of the detonation test is unfolded, the protection plug is inserted into the first star watch socket, the emission plug is inserted into the second star watch socket, and the third star watch socket is vacant.
And testing the resistance value, namely measuring the resistance value of the bridge wire resistor before and after the detonation experiment and at each stage of the launching field, measuring the resistance value of the current limiting resistor before and after the detonation experiment, and if the resistance value change of the current limiting resistor is within 0.5%, indicating that the path is normal.
After the detonation test is completed, before the satellite is launched, launching plugs are inserted into the first star watch socket and the second star watch socket, and a protection plug is inserted into the third star watch socket, so that electrostatic protection can be performed in the processes of satellite cover closing, fairing transfer and tower crane transferring, the safety of initiating explosive devices is effectively improved, the bridge wire resistance of the initiating explosive devices can be measured through the third star watch socket, data comparison and final state confirmation are performed, and the reliability and safety of the initiating explosive device passage are effectively improved.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (7)
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| CN111964542B (en) * | 2020-09-18 | 2023-07-04 | 北京空天高科技有限公司 | Initiating explosive device detonating circuit, stratospheric airship and nondestructive testing method |
| CN112650192B (en) * | 2020-11-05 | 2021-12-07 | 北京电子工程总体研究所 | General explosion simulator for initiating explosive devices |
| CN112986655A (en) * | 2021-02-25 | 2021-06-18 | 航天科工空间工程发展有限公司 | Detection device and method for aircraft initiating explosive device |
| CN113682497A (en) * | 2021-08-25 | 2021-11-23 | 北京微纳星空科技有限公司 | Test method for preventing satellite sailboard from being unfolded mistakenly and power supply circuit |
| CN113856092A (en) * | 2021-09-14 | 2021-12-31 | 淮海工业集团有限公司 | Fire extinguishing bomb data collection launching control device |
| CN113859583B (en) * | 2021-09-17 | 2023-07-14 | 北京控制工程研究所 | A high fault-tolerant explosive control method for Mars landing process |
| CN115579251B (en) * | 2022-11-24 | 2023-03-10 | 上海航天空间技术有限公司 | Working method of travel switch star catalogue system and satellite testing device |
| CN117382917B (en) * | 2023-11-15 | 2024-05-28 | 苏州馥昶空间技术有限公司 | Unfolding mechanism unlocking control circuit and spacecraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH04243698A (en) * | 1991-01-23 | 1992-08-31 | Toshiba Corp | Solar battery circuit |
| CN103997031A (en) * | 2014-05-16 | 2014-08-20 | 上海微小卫星工程中心 | Initiating explosive device control circuit and controller using same |
| CN205506966U (en) * | 2016-03-28 | 2016-08-24 | 北京航天自动控制研究所 | System for detect priming sytem behavior |
| CN106428639B (en) * | 2016-11-08 | 2019-01-08 | 上海宇航系统工程研究所 | A kind of in-orbit Stretching of solar wings device |
| CN112327085B (en) * | 2018-06-19 | 2023-08-25 | 上海微小卫星工程中心 | A method for verifying the passage of pyrotechnics |
| CN109581138B (en) * | 2018-11-28 | 2021-12-07 | 中国空间技术研究院 | Satellite initiating explosive device access testing method |
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