CN110715582B - Explosive driving type high-temperature-resistant fire-work actuating device explosive charging sequence for deep space detector - Google Patents
Explosive driving type high-temperature-resistant fire-work actuating device explosive charging sequence for deep space detector Download PDFInfo
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- CN110715582B CN110715582B CN201911082722.5A CN201911082722A CN110715582B CN 110715582 B CN110715582 B CN 110715582B CN 201911082722 A CN201911082722 A CN 201911082722A CN 110715582 B CN110715582 B CN 110715582B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
- F42B33/02—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges
- F42B33/025—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges by compacting
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
- F42B33/02—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges
- F42B33/0278—Safety arrangements therefor
Abstract
The invention discloses an explosive driving type high-temperature-resistant fire-work actuating device explosive charging sequence for a deep space detector. The igniter charges ultrafine particle magnesium ignition powder and fine particle magnesium ignition powder, and the bidirectional pressure cartridge charges powder lead azide to form a high-temperature-resistant ignition-work-doing charge sequence at 180-200 ℃. The two sets of igniters and the bidirectional pressure cartridge constitute two independent ignition-fire transmission-work energy transmission redundant designs. The casing of the actuating device is internally provided with a Y-shaped fire transfer hole and a three-way combustion chamber structure, and a fire transfer sequence consisting of two paths of igniters and two-way pressure cartridges is arranged. The charge structures of the input end and the output end of the two bidirectional pressure medicine cylinders are the same, the bidirectional pressure medicine cylinders can receive the flame output by the igniter to ignite, and can also receive the flame output by the other bidirectional pressure medicine cylinder to ignite, so that the functional reliability of ignition-work can be improved.
Description
Technical Field
The invention relates to a high-temperature-resistant point type separation aerospace firer separation device and a charging technology.
Background
The invention discloses a point type separation firer separation device, which is an firer actuating device used for connection-separation between separation parts on various spacecrafts and generally comprises two parts, namely an electric detonator and a connection-separation mechanical device.
The charging technology disclosed by the invention refers to related technologies such as the component characteristics of each medicament, a charging sequence structure, an energy input structure, an energy output structure and a charging process thereof used in a priming device.
The explosion-driven type fire actuating device for the deep space detector is a separating device for unlocking a metal bar, a rope and a cable type connecting structure of an on-board point type separating structure. Generally, the device consists of two parts, namely an initiating explosive device (an igniter and a pressure medicine cylinder) and an actuating actuator (a connecting and unlocking mechanism). The explosion-driven type firer actuating device used on the deep space detector is required to bear very high space environment temperature, such as 130 ℃ to 170 ℃, the lowest temperature of decomposition, spontaneous combustion and melting of explosives and powders is required to be at least 30 ℃ higher than the predicted highest use temperature in consideration of certain safety temperature margin and relevant regulations in general specifications of the aerospace firer device, and therefore design verification that the explosion-driven type firer actuating device can bear 180 ℃ to 200 ℃ high-temperature-resistant point-type separation firer separation device and the explosive charge thereof is necessary.
The charging sequence of the existing explosion-driven type initiating explosive device usually contains medicaments such as stevensite lead, black powder, 2/1 camphor and the like. The lead stevensonate is a common bridge wire ignition powder, the 5-second explosion point of the lead stevensonate is 267 ℃, the lead stevensonate generally contains a crystal water, the crystal water begins to be dehydrated after being heated to 115 ℃ for 16 hours, the crystal water is rapidly dehydrated at 145 ℃ for 3 hours, and the phenomena of thermal decomposition, color change, weight loss, crystal crushing, adhesive melting or decomposition, adhesive migration and the like can also occur, so that the medicament has adverse reaction hidden danger in a high-temperature environment, and meanwhile, the lost crystal water can further damage the stability of other medicaments in the device and the structural sealing property of the actuating device. The black powder is a common working powder and has series types of different types of powder types, the ignition point is 290-310 ℃, and the problems of low initial reaction temperature (130 ℃), significant weight loss, sensitivity change and the like exist under the high temperature condition of more than 150 ℃. 2/1 Cinnamomum camphora is a commonly used working substance, its 5 second explosion point is 237 deg.C, and it is verified by high temperature test that it can be quickly thermally decomposed at 160 deg.C-170 deg.C, even completely failed. Because the existing charging sequence of the initiating explosive device is not resistant to high temperature, and the high-temperature resistant medicament is usually greatly reduced in bridge wire sensitivity, flame sensitivity, burning speed, combustion heat and other performances, the sensitivity, the fire transmission and the work doing characteristics of the high-temperature resistant charging sequence are greatly different from those of the existing charging, and brand new design and verification are needed.
Therefore, to design a high-temperature-resistant fire-work actuating device for a deep space probe with high temperature resistance of more than 150 ℃, a charge sequence design capable of resisting more than 180 ℃ is required, and high-temperature-resistant test verification is carried out.
Disclosure of Invention
In order to solve the problems that the traditional initiating explosive device lacks a charging sequence type with high temperature resistance of more than 180 ℃, the redundant design of a fire transfer sequence is difficult to realize, the high-temperature test verification is difficult to carry out and the like, the invention provides two groups of independent charging sequences and a bidirectional pressure cartridge structure in an explosion-driven high-temperature-resistant initiating explosive device for a deep space detector, the redundant design of reliable ignition-fire transfer functions is realized, the charging sequence can also resist the temperature of 180-200 ℃, and the problem that the charging sequence of the traditional actuating device cannot resist the high temperature (180-200 ℃) is solved.
The technical solution of the invention is as follows: aiming at the requirements of small-size design, redundancy design and temperature resistance design of the deep space detector explosion-driven high-temperature-resistant fire-work actuating device, high-temperature stability test verification of various alternative medicaments is firstly carried out, ignition medicaments and working medicament types suitable for high temperature resistance are screened out, matching design and test verification of electric ignition sensitivity, flame sensitivity and work capacity of a medicament charging sequence are carried out, medicament charging conditions such as medicament components, proportion, granularity, density, medicament quantity and adhesive suitable for various properties of the medicament charging sequence are determined, energy matching optimization design of flame sensitivity and work capacity is carried out according to power supply conditions and connection and unlocking conditions on the deep space detector, the medicament charging sequence, energy input and output structures of an electric igniter and a bidirectional pressure medicament cylinder are determined, and the ignition of any bidirectional pressure medicament cylinder can reliably ignite the other bidirectional pressure medicament cylinder through the structural design of the bidirectional pressure medicament cylinder, two groups of independent charging sequence structures of ignition, fire transmission and work doing are formed, and the requirements of connection and unlocking of metal bar, rope and cable type point type separation structures on the aircraft, high temperature resistant environment and high reliability are met.
The invention provides an explosive driving type high-temperature-resistant fire-work actuating device explosive charging sequence for a deep space detector, which comprises the following components: screening high-temperature resistant medicaments and designing a charging sequence.
The screening of the high-temperature resistant medicament is to carry out comprehensive analysis through physical stability, chemical stability and explosion stability tests of various medicaments, and screen out alternative medicaments of which all stability analysis items can meet the requirement of medicament performance change degree in a permitted range. The method can be implemented by firstly carrying out primary selection according to the fact that the reaction peak temperature of the DSC analysis medicament is higher than the using temperature, and then carrying out comprehensive demonstration according to other thermal analysis methods and explosion performance analysis methods. The stability change and the change degree of the medicament are evaluated through test items such as DSC analysis, TG analysis, constant high-temperature heat loss gravity analysis, appearance analysis, hot wire sensitivity test, output power test and the like of the medicament, the high-temperature stability of the medicament is comprehensively evaluated, and the usable high-temperature resistant medicament is screened.
The design of the charging sequence is based on the comprehensive analysis method for analyzing various stability and optimizing parameter design, and provides a three-layer charging sequence which is formed by using superfine particle magnesium ignition powder, fine particle magnesium ignition powder and powder lead azide and resists high temperature of 180 ℃ to 200 ℃, and the three-layer charging sequence performance is proved to meet the requirement of the charging sequence design of an explosion-driven high-temperature-resistant fire-work actuating device for a deep space detector through 165 ℃ to 180 ℃ high-temperature work test verification of an actuating device complete machine product.
The invention relates to a high-temperature-resistant charging sequence design, which comprises two bridge wire igniters, two bidirectional pressure cartridges and a Y-shaped actuating device shell. The igniter has two layers of powder charges, the first layer of powder charge is superfine granular magnesium ignition powder, the superfine granular magnesium ignition powder is coated in the igniter in a slurry filling mode and is in close contact with the bridge wire, and the design idea of selecting the superfine granular magnesium ignition powder is to improve the thermal inductance of the bridge wire; the second layer of charge is a coarser particle magnesium ignition powder and also fills the remaining cavity of the igniter in a slurry filling manner, and the larger particle size of the second layer of charge is for longer output flame duration; after the two layers of slurry-like charging solvents are dried or aired, coating a thin layer of protective paint on the surface of the output magnesium ignition powder charge to play the roles of preventing powder falling and preventing moisture; the third layer powder charge is powder lead azide, the selection of its granularity and density uses the flame sensitivity higher as the standard, load in two-way pressure cartridge case with the pressure equipment mode, the powder charge type and the pressure of two-way pressure cartridge case both ends are the same, there are fire transfer hole and sealing pad at cartridge case tube both ends, the selection purpose of sealing pad is that the encapsulation medicament is with easily being penetrated by flame, the input end structure of two-way pressure cartridge case and the powder charge condition of output, the fire transfer structure is completely the same, guarantee the input, output structural design has higher flame sensitivity, make two-way pressure cartridge case have two-way ignition function. The igniter is connected with the actuating device shell in a threaded mode, the bidirectional pressure cartridge is bonded with the actuating device shell through high-temperature-resistant adhesive, and a fire transfer gap of 1.2 mm is reserved between the igniter and the bidirectional pressure cartridge. In order to prevent single-point ignition failure and improve ignition reliability, the charge sequence is designed into a redundant structure, two groups of igniters and bidirectional pressure cartridges are adopted to form two independent fire transfer sequences, and any one group of charge sequence can reliably complete an actuating task after being successfully ignited; the charge sequence mounting hole in the shell of the actuating device is Y-shaped, the bidirectional pressure cartridge has a better bidirectional ignition function through the optimized design of a Y-shaped included angle and the size of a tee joint structure, the bidirectional pressure cartridge can not only receive flame output by an igniter to ignite, but also receive flame output by another bidirectional pressure cartridge to ignite, and the functional reliability of the actuating device can be obviously improved.
When the ignition device needs to act, the ignition device is powered on, superfine particle magnesium ignition powder, coarser particle magnesium ignition powder and powder lead azide are ignited in sequence, and narrow-pulse high-temperature high-pressure gas is generated to drive the piston to complete an action task.
Compared with the prior art, the invention has the beneficial effects that:
compared with the existing explosive loading of the initiating explosive device, the explosive loading sequence designed by the invention has the following advantages:
1) the high-temperature-resistant screening test of the charge types used by the invention at the high temperature of 180-200 ℃ verifies that the performance of each medicament can meet the long-term high-temperature-resistant environmental requirement of the explosion-driven type fire-work actuating device for the deep space probe, and the problem that the existing charge sequence cannot resist the high temperature of more than 130 ℃ is solved.
2) The adopted bidirectional pressure medicine cartridge structure has a bidirectional ignition function, and the bidirectional pressure medicine cartridges can be ignited by receiving the output flame from an igniter or another bidirectional pressure medicine cartridge by optimally designing the Y-shaped included angle and the output end charging structure of the two bidirectional pressure medicine cartridges, so that the functional reliability of the actuating device can be obviously improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
Fig. 1 is a block diagram of a charging sequence for an explosion-driven high temperature resistant firer action device for a deep space probe according to an embodiment of the present invention.
Description of reference numerals:
1. a first igniter; 2. a first bridge wire; 3. a first ultrafine particulate magnesium ignition charge; 4. a first fine particle magnesium ignition charge; 5. a first protective paint; 6. a first powder of lead azide; 7. a first bi-directional pressure cartridge; 8. a second igniter; 9. a second bridge wire; 10. a second ultrafine particle magnesium ignition powder; 11. a second fine particle magnesium ignition charge; 12. a second protective paint; 13. a second powder of lead azide; 14. a second bi-directional pressure cartridge; 15. a Y-shaped actuator housing.
Detailed Description
In order to make the technical solutions of the present invention better understood, those skilled in the art will now describe the present invention in further detail with reference to the accompanying drawings.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal. Without further limitation, an element defined by the phrases "comprising … …" or "comprising … …" does not exclude the presence of additional elements in a process, method, article, or terminal that comprises the element. Further, herein, "greater than," "less than," "more than," and the like are understood to exclude the present numbers; the terms "above", "below", "within" and the like are to be understood as including the number.
As shown in fig. 1, the explosive driving type high temperature resistant fire-working actuating device charging sequence for the deep space probe consists of two paths of fire transfer sequences and a Y-shaped actuating device shell 15, wherein the two paths of fire transfer sequences consist of two igniters and two bidirectional pressure cartridges, wherein the first igniter 1 shell, a first bridge wire 2, a first ultrafine particle magnesium ignition powder 3, a first fine particle magnesium ignition powder 4, a first protective paint 5, a first powder lead azide 6 and a first bidirectional pressure cartridge 7 form one path of fire transfer sequences; and a shell of the second igniter 8, a second bridge wire 9, a second superfine particle magnesium ignition powder 10, a second fine particle magnesium ignition powder 11, a second protective paint 12, a second powder lead azide 13 and a second bidirectional pressure medicine cylinder 14 form another path of fire transfer sequence. The Y-shaped actuating device shell 15 is provided with two paths of fire transmission channels and a three-way combustion chamber structure, provides a fire transmission channel and a work pressure transmission channel for any one path of fire transmission sequence, simultaneously forms a three-way structure that the combustion energy of the two paths of fire transmission channels is gathered in one combustion chamber, and provides a two-way ignition function for the two paths of fire transmission channels, namely, any one path of fire transmission sequence can be ignited to another path of fire transmission sequence through the three-way structure, so that the redundant design of a charge sequence with the fire transmission function redundancy, the fire transmission sequence redundancy, the two-way ignition redundancy and the work output redundancy from an igniter is realized, and any one group of charge sequences can independently complete the actuating task when working normally. The superfine particle magnesium ignition powder, the fine particle magnesium ignition powder and the powder lead azide all have high temperature resistance, and the igniter has the characteristic of a passive induction electric igniter.
The Y-shaped actuating device shell 15 is provided with a three-way combustion chamber structure, the three-way combustion chamber is provided with two input fire transfer channels and one output fire transfer channel, the input fire transfer channels are provided with two mounting holes with different diameters to form a step for mounting and positioning the bidirectional pressure cartridge and bearing the pressure when the igniter outputs flame. The first igniter 1, the second igniter 8, the first bidirectional pressure cartridge 7 and the second bidirectional pressure cartridge 14 are sequentially arranged in the input fire transfer channel, and the included angle of the two input fire transfer channels is 65 degrees. The output fire transfer channel is aligned with the piston type actuating device, and the Y-shaped three-way area has the functions of fire transfer energy convergence, work pressure improvement and charge energy utilization rate improvement and also has the function of bidirectional ignition. The center of the output end of the first igniter 1 is aligned with the center of the input end of the first bidirectional pressure cartridge 7, and a 1.2 mm gap is reserved between the center of the output end of the first igniter and the center of the input end of the first bidirectional pressure cartridge 7; a gap of 1.2 mm is provided between the second igniter 2 and the second bi-directional pressure cartridge 14 to improve the assembling workability and the ignition reliability. The igniter and the bidirectional pressure cartridge are subjected to fire transmission distance margin test verification, and the fire transmission distance between the fine-particle magnesium ignition powder and the powder lead azide obtained by the test can reach more than 100 millimeters, so that the igniter and the bidirectional pressure cartridge have good fire transmission distance margin. The output end of one bidirectional pressure cartridge is communicated with the output end of the other bidirectional pressure cartridge through a three-way structure, and the nearest gap distance is 1-2 mm, so that one bidirectional pressure cartridge can be easily ignited by the output flame of the other bidirectional pressure cartridge. The first igniter 1 and the second igniter 8 are identical in structure and size, are fixedly installed with a large-diameter hole in a Y-shaped actuating device shell in a threaded mode, and form sealing of an input end combustion chamber pressure-bearing structure together with the Y-shaped actuating device shell. The two bidirectional pressure medicine cylinders have the same structure and size and are fixedly installed with a small-diameter hole in the shell of the Y-shaped actuating device in a silicon rubber bonding mode. The input end pipe shells of the two bidirectional pressure cartridge cases are provided with flanges, so that the installation and positioning, the bearing and the gluing fixation are convenient, and the output ends of the bidirectional pressure cartridge cases are aligned to the end faces of the pistons of the actuating devices.
Two igniters of the high-temperature-resistant fire work actuating device are respectively filled with superfine particle magnesium ignition powder and fine particle magnesium ignition powder, and the particle sizes of the superfine particle magnesium ignition powder and the fine particle magnesium ignition powder are 40 micrometers and 100 micrometers respectively. The structure and the size of the first igniter 1 and the second igniter 8 are completely the same, and the high-temperature aging pretreatment of the two medicaments at 180 ℃ for 1 day is carried out before the two medicaments are loaded into the igniters for improving the high-temperature stability so as to reduce the pre-reaction of the medicaments in the long-term high-temperature environment. The superfine particle magnesium ignition powder with fine particle size is coated in a slurry-shaped powder mode in a powder chamber of an igniter to serve as first layer powder charge, is in close contact with a bridge wire and serves as bridge wire ignition powder. The fine particle magnesium ignition powder is filled in the containing cavity of the igniter powder chamber in a slurry state powder mode as second-layer powder charging, and is used as output ignition powder, after the slurry state powder charging solvent is dried or aired, a thin-layer high-temperature-resistant protective paint is coated on the surface of the fine particle magnesium ignition powder, and the functions of fixing and moisture proofing are achieved. The magnesium ignition powder has the characteristics of high temperature resistance, good bridge wire sensitivity and flame sensitivity, high instantaneous degree, high combustion heat value and long flame duration, and is suitable for serving as bridge wire ignition powder and high-energy output ignition powder. The diameter of the bridge wire is more than 60 microns, the bridge wire is combined with the ultrafine particle magnesium ignition powder, the requirements of reliable ignition at 5 amperes, no ignition at 1 ampere for 1 watt for 5 minutes and safety in resisting electrostatic discharge of a foot and a foot shell of 25 kilovolts can be met through the optimized design of the diameter, the length and the resistance of the bridge wire and the optimized design of matching of the sensitivity and the heat transfer performance of the bridge wire of the magnesium ignition powder, and the bridge wire sensitivity variation of a high-temperature sample is 9.9% (the average value is changed from 1.307 amperes to 1.437 amperes). The selection of the first igniter 1 and the second igniter 8 which are arranged in the same Y-shaped actuating device shell needs to be subjected to grouping screening of resistance pairing, the smaller the difference between paired resistances is, the better the difference is, and the difference is generally not more than 2%.
The temperature resistance characteristics of the superfine particle magnesium ignition powder and the fine particle magnesium ignition powder of the high-temperature resistant igniter are verified by high-temperature tests, wherein two reaction peaks, a secondary reaction peak (405 ℃) and a main reaction peak (more than 550 ℃) exist in a DSC curve in the range from normal temperature to 550 ℃. In order to improve the stability of the high-temperature environment, two medicaments of an igniter are subjected to high-temperature aging pretreatment at 180 ℃ to reduce the pre-reaction of the medicaments in the long-term high-temperature environment, the initial reaction temperature of DSC time reaction of a normal-temperature sample is 390 ℃, the peak temperature of the time reaction is 405 ℃, the initial reaction temperature of 200 ℃, the initial reaction temperature of 10 days of the time reaction of the high-temperature sample is 388 ℃ (still higher than 200 ℃ by 188 ℃), the peak temperature of the time reaction is 404 ℃, and the peak temperature change amount of the time reaction is-2 ℃ compared with that of the normal-temperature sample. The weight loss change amount of the sample at the high temperature of 200 ℃ for 10 days is-0.094%, the change amount of the p-t peak pressure mean value is-8% (changed from 1.61 MPa to 1.48 MPa), and the maximum pressure rise time is 0.20 milliseconds to 1.20 milliseconds. The flame length change rate was 22% (from 18 cm to 22 cm) and the flame duration change rate was-10% (from 88 ms to 52 ms) for the 10-day high temperature sample at 200 ℃. The ignition powder has better temperature resistance than the existing ignition powder, and the temperature resistance parameters show that the two magnesium ignition powders can endure the high-temperature environment of more than 200 ℃ for 10 days.
The two bidirectional pressure medicine cylinders of the high-temperature-resistant fire-work actuating device are filled with powder lead azide, and the first bidirectional pressure medicine cylinder 7 and the second bidirectional pressure medicine cylinder 14 are identical in structure and size. In order to improve the high temperature stability, the powder lead azide is subjected to a high temperature aging pretreatment at 180 ℃ for 1 day before being filled into the first and second two- way pressure cartridges 7 and 14, so as to reduce the pre-reaction of the medicament in a long-term high temperature environment. The powder lead azide fills the first bidirectional pressure cartridge 7 and the second bidirectional pressure cartridge 14 in a pressing mode, the fire transfer holes at two ends of the first bidirectional pressure cartridge 7 and the fire transfer holes at two ends of the second bidirectional pressure cartridge 14 are all packaged by silk mats to ensure the charging structural strength and high flame sensitivity at the fire transfer holes, and the powder lead azide has the characteristics of high temperature resistance, good flame sensitivity, large gas production, high peak pressure, short maximum pressure rise time and small energy loss in a work process and is suitable for charging and doing work of an explosion-driven work device.
The high-temperature resistant characteristic obtained by verifying the high-temperature test of the high-temperature resistant bidirectional pressure cartridge powder lead azide is that a DSC curve has a reaction peak in the range from normal temperature to 550 ℃, the DSC initial reaction peak temperature of a normal-temperature sample is 324 ℃, the medicament is subjected to high-temperature aging pretreatment at 180 ℃, the initial reaction temperature of the high-temperature sample at 180 ℃ for 10 days is changed to 322 ℃ (still higher than 180 ℃ by 142 ℃), and the reaction temperature change is-2 ℃ compared with that of the normal-temperature sample. The reaction peak temperature of the normal temperature sample is 330 ℃, the reaction peak temperature of the high temperature sample is 328 ℃ after 180 ℃ and 10 days, and the reaction temperature variation is-2 ℃; the weight loss change of the high-temperature sample is-0.432%, the p-t peak pressure change is-2% (changing from 3.18 MPa to 3.11 MPa), and the maximum pressure rise time is 0.21-0.25 millisecond. Compared with the common working agent, the working agent has the advantages of good temperature resistance, high output pressure, short maximum pressure rise time, quick combustion, small heat loss and high energy utilization rate, has the working characteristics of explosion-driven high-pressure narrow pulse and is suitable for being used as an explosion-driven working device. The temperature resistance tests show that the powder lead azide can resist the high-temperature environment of 180 ℃ for 10 days.
The charging sequence consisting of the first ultrafine particle magnesium ignition powder 3, the second ultrafine particle magnesium ignition powder 10, the first fine particle magnesium ignition powder 4, the second fine particle magnesium ignition powder 11, the first powder lead azide 6 and the second powder lead azide 13 is suitable for the high-temperature environment for the deep space probe, can resist the high temperature of 180-200 ℃ for more than 10 days, and can meet the requirements of the explosion-driven high-temperature-resistant fire work actuating device for the deep space probe.
The screening method of the high-temperature resistant medicament used by the invention is that the superfine particle magnesium ignition powder, the fine particle magnesium ignition powder and the powder lead azide pass the DSC test, the high-temperature 180-200 ℃ test, the thermal weight loss test, the appearance observation, the bridge wire sensitivity test and the work power test of the medicament, the high-temperature stability of the medicament is comprehensively evaluated to be good, and the performance meets the requirements of the charging sequence of the explosion-driven high-temperature resistant fire power actuating device for the deep space probe.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (8)
1. The utility model provides a deep space detector is with explosion drive type high temperature resistant firer actuates device charging sequence, actuates the device casing by two way biography fire sequences and one "Y" type and constitutes, and two way biography fire sequences comprise two some firearms, two-way pressure cartridge cases, its characterized in that: the first igniter shell, the first bridge wire, the first superfine particle magnesium ignition powder, the first fine particle magnesium ignition powder, the first protective paint, the first powder lead azide and the first bidirectional pressure cartridge form a fire transfer sequence; a second igniter shell, a second bridge wire, a second superfine particle magnesium ignition powder, a second fine particle magnesium ignition powder, a second protective paint, second powder lead azide and a second bidirectional pressure cartridge form another path of fire transfer sequence; the Y-shaped actuating device shell is provided with a three-way combustion chamber structure, the three-way combustion chamber structure is provided with two input fire transfer channels and one output fire transfer channel, the three-way combustion chamber structure provides a fire transfer channel and a work pressure transfer channel for any one fire transfer sequence, and combustion energy of two fire transfer channels formed at the same time is gathered in the three-way combustion chamber structure to provide a bidirectional ignition function for the two fire transfer channels.
2. The explosive drive type high temperature resistant firer's actuator charging sequence for deep space probe of claim 1, wherein said "Y" shaped actuator housing has a three-way combustion chamber structure with two input fire-transmitting channels and one output fire-transmitting channel, each input fire-transmitting channel having two mounting holes with different diameters, forming a step; the input fire transfer channel is sequentially provided with a first igniter, a second igniter, a first bidirectional pressure cartridge and a second bidirectional pressure cartridge, and the included angle of the two input fire transfer channels is 65 degrees; the output fire transfer channel is aligned with the end surface of the piston of the actuating device; the center of the output end of the first igniter aligns to the center of the input end of the first bidirectional pressure cartridge, and a 1.2 mm gap is reserved between the center of the output end of the first igniter and the center of the input end of the first bidirectional pressure cartridge; the center of the output end of the second igniter is aligned with the center of the input end of the second bidirectional pressure cartridge, and a 1.2 mm gap is reserved between the center of the output end of the second igniter and the center of the input end of the second bidirectional pressure cartridge; the output end of the first bidirectional pressure cartridge is communicated with the output end of the second bidirectional pressure cartridge through a three-way combustion chamber structure, and the nearest gap between the output end of the first bidirectional pressure cartridge and the output end of the second bidirectional pressure cartridge is 1-2 mm.
3. The explosive driving type high temperature resistant fire-work actuating device charging sequence for the deep space probe according to claim 2, wherein the first igniter and the second igniter are identical in structure and size, are fixedly installed in the Y-shaped actuating device shell in a threaded mode, and form a seal of an input end combustion chamber pressure-bearing structure together with the Y-shaped actuating device shell.
4. The deep space detector explosive drive type high temperature resistant firer action device charging sequence according to claim 3, wherein the first bidirectional pressure cartridge and the second bidirectional pressure cartridge have the same structure and size, and are fixedly mounted with the Y-shaped action device shell in a silicon rubber bonding mode, and the input end pipe shell of the first bidirectional pressure cartridge and the input end pipe shell of the second bidirectional pressure cartridge are both provided with flanges.
5. The explosive driving type high temperature resistant firer actuating device charging sequence for the deep space probe according to claim 1, wherein the first igniter and the second igniter are respectively provided with superfine particle magnesium ignition powder and fine particle magnesium ignition powder, and the particle sizes of the superfine particle magnesium ignition powder and the fine particle magnesium ignition powder are 40 microns and 100 microns respectively; the first igniter and the second igniter are completely the same in structure and size; the two medicaments of the superfine particle magnesium ignition powder and the fine particle magnesium ignition powder are subjected to high-temperature aging pretreatment at 180 ℃ for 1 day before being loaded into an igniter; superfine particle magnesium ignition powder with fine particle size is coated in a slurry-shaped mode in a powder chamber of an igniter to serve as first layer powder charge, is in close contact with a bridge wire and serves as bridge wire ignition powder; and the fine particle magnesium ignition powder is used as a second layer of powder charge to fill the containing cavity of the igniter powder chamber in a slurry state powder charge mode, and is used as output ignition powder, and after the slurry state powder solvent is dried or aired, a thin layer of high-temperature-resistant protective paint is coated on the surface of the fine particle magnesium ignition powder.
6. The explosive driving type high temperature resistant firer actuating device explosive charging sequence for the deep space probe according to claim 5, wherein the diameter of the bridge wire is more than 60 microns, the bridge wire is combined with the superfine particle magnesium ignition powder, and the requirements of reliable ignition at 5 amperes, no ignition at 1 ampere for 1 watt for 5 minutes and safety in resisting electrostatic discharge of 25 kilovolt feet and foot shells can be met through the optimized design of the diameter, the bridge length and the resistance of the bridge wire and the optimized design of matching the sensitivity and the heat transfer performance of the bridge wire of the magnesium ignition powder.
7. The explosive drive type high temperature resistant firer's actuator charging sequence according to claim 6, wherein the first igniter and the second igniter installed in the same "Y" shaped actuator casing are selected by resistance pairing grouping screening, and the difference between the paired resistances is not more than 2%.
8. The deep space probe explosive drive type high temperature resistant firer's actuator charging sequence of claim 1, wherein the first and second cartridge charges are each powdered lead azide; the powdery lead azide is subjected to high-temperature aging pretreatment at 180 ℃ for 1 day before being filled into a first bidirectional pressure cartridge and a second bidirectional pressure cartridge; the powder lead azide fills the first bidirectional pressure cartridge and the second bidirectional pressure cartridge in a pressing mode, the fire transfer holes at the two ends of the first bidirectional pressure cartridge and the fire transfer holes at the two ends of the second bidirectional pressure cartridge are both packaged by silk mats, and the input end structure and the charging condition and the fire transfer structure of the output end of the first bidirectional pressure cartridge and the second bidirectional pressure cartridge are completely the same.
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| CN112985200A (en) * | 2021-02-24 | 2021-06-18 | 南京理工大学 | Detonator with same-end axial needling flame redundant input |
| CN113979821A (en) * | 2021-11-01 | 2022-01-28 | 中国船舶重工集团公司第七一八研究所 | High-reliability multistage ignition mode |
| CN114151233B (en) * | 2021-12-01 | 2023-06-06 | 北京航天动力研究所 | Igniter fixing device for realizing reliable ignition process of liquid rocket engine |
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| US5445077A (en) * | 1992-12-18 | 1995-08-29 | Giat Industries | Initiation device for a pyrotechnic system |
| CN1125981A (en) * | 1994-07-28 | 1996-07-03 | 旭化成工业株式会社 | Electronic delayed ignitor and electric detonator |
| US7574960B1 (en) * | 2005-11-29 | 2009-08-18 | The United States Of America As Represented By The Secretary Of The Navy | Ignition element |
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