CN110749251B - Charging sequence of combustion-driven high-temperature-resistant fire separation device for deep space probe - Google Patents
Charging sequence of combustion-driven high-temperature-resistant fire separation device for deep space probe Download PDFInfo
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- CN110749251B CN110749251B CN201911082693.2A CN201911082693A CN110749251B CN 110749251 B CN110749251 B CN 110749251B CN 201911082693 A CN201911082693 A CN 201911082693A CN 110749251 B CN110749251 B CN 110749251B
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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
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Abstract
The invention discloses a charging sequence of a combustion-driven high-temperature-resistant fire separation device for a deep space probe, which comprises an igniter, a bridge wire, superfine particle magnesium ignition powder, fine particle magnesium ignition powder, potassium borate nitrate, a positioning ring, a fire transfer hole sealing pad, a bidirectional pressure cartridge, an actuating device shell and a gas channel. The superfine particle magnesium ignition powder, the fine particle magnesium ignition powder and the potassium boronitrate form a high-temperature resistant charging sequence at 180-200 ℃, the distance between an igniter and the bidirectional pressure cartridge is 3.15 mm, and the diameters of four fire transfer holes are 1.5 mm. The two sets of igniters are designed redundantly, the igniters, the bidirectional pressure cartridge and the igniters are arranged in the casing of the actuating device with a T-shaped three-way combustion chamber structure in an axis alignment manner, and any one igniter can independently complete a separation task when working normally, 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 fire separation device, which is used for connection-separation of 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 initiating explosive separation device for the deep space detector is a separation device used for connecting and unlocking a point type separation structure on an aircraft. Generally, the device consists of two parts, namely an initiating explosive device (an igniter and a bidirectional pressure medicine cylinder) and an actuating actuator (a connecting and unlocking mechanism). The composition materials generally include initiating agents, metal materials, rubber and the like. The combustion-driven type fire separation device used on the deep space detector is usually 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 aerospace fire separation devices, and therefore design verification of the combustion-driven type point type fire separation device capable of resisting high temperature of 180 ℃ to 200 ℃ and the explosive charge of the combustion-driven type point type fire separation device have important significance.
The charging sequence of the existing combustion driving type initiating explosive device usually contains medicaments such as stevensite lead, black powder, 2/1 camphor and the like. Lead stevensinate is a common bridgewire ignition charge, the 5-second explosion point of the lead stevensinate is 267 ℃, the lead stevensinate 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 phenomena such as thermal decomposition, color change, weight loss, crystal breakage, 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, meanwhile, the lost crystal water can further destroy the stability and structural sealing property of other medicaments in the device, and the stability changes can cause the changes of flame sensitivity and output power; the black powder is a common working powder and has series types of different types, the ignition point is 290 ℃ to 310 ℃, and the problems of low initial reaction temperature (130 ℃), significant weight loss, sensitivity change and the like under the high temperature condition of more than 150 ℃ exist; 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 traditional charging, and brand new design and verification are needed.
Therefore, in order to design a combustion-driven high-temperature-resistant fire separation device for a deep space probe resistant to high temperature of more than 150 ℃, a charge sequence design resistant to more than 180 ℃ is required, and high-temperature-resistant test verification is performed.
Disclosure of Invention
In order to solve the problems that the traditional initiating explosive device lacks a explosive sequence type which can resist the high temperature of more than 180 ℃, the redundant design of an explosive sequence is difficult to realize, the high temperature test verification is difficult and the like, the invention provides two groups of explosive sequences and a bidirectional ignition pressure cartridge structure in a combustion-driving type high temperature resistant initiating explosive device separating device for a deep space detector, the redundant design of the reliable ignition-explosive transfer function is realized, the explosive sequences can resist the high temperature of 180-200 ℃, and the problem that the explosive sequences of the traditional separating device cannot resist the high temperature is solved.
The technical solution of the invention is as follows: the utility model provides a deep space probe is with novel powder charge sequence of burning driving high temperature resistant firer separator, includes: screening high-temperature resistant medicaments and designing a charging sequence.
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 combustion-driven high-temperature-resistant fire separation device of the deep space detector, 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 working capacity of a medicament charging sequence are carried out, medicament charging conditions such as medicament components, proportion, granularity, density, medicament quantity, adhesive and the like suitable for various properties of the medicament charging sequence are determined, energy matching optimization design of flame sensitivity and working 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 cartridge are determined, and the bidirectional pressure medicament cartridge can be reliably ignited by any igniter through the structural design of the bidirectional pressure medicament cartridge, two groups of charging sequence structures of ignition-fire transmission-work application are formed, and the requirements of point type separation structure connection and unlocking on an aircraft, high temperature resistant environment and high reliability can be met.
The superfine particle magnesium ignition powder, the fine particle magnesium ignition powder and the potassium borate nitrate used in the invention are high-temperature resistant medicament schemes obtained by multiple tests of high-temperature stability of 180-200 ℃, and the performances of the high-temperature resistant medicament schemes can meet the requirements of a charging sequence of a combustion-driven high-temperature resistant fire separation device.
The screening of the high-temperature resistant medicament is to screen out a candidate medicament which can meet the requirement that the medicament performance change degree is within a permitted range by comprehensively analyzing physical stability, chemical stability and explosion stability tests of various heat-resistant ignition medicaments and propellants. 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, the three-layer charging sequence with the superfine magnesium ignition powder, the fine magnesium ignition powder and the potassium boronitrate and resisting high temperature of 180-200 ℃ is provided, and the performance of the three-layer charging sequence is proved to meet the requirement of the functional design of the combustion-driven high-temperature-resistant fire separation device for the deep space detector through the 165-180 ℃ high-temperature work test of the whole separation device product.
The invention relates to a high-temperature resistant charging sequence design, which comprises two bridge wire igniters, a bidirectional pressure cartridge and a T-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 powder charge is fine-particle magnesium ignition powder, and also fills the residual cavity of the igniter in a slurry filling mode, and the particle size of the residual cavity is larger so as to have longer output flame duration; after the two layers of slurry-like explosive-filled solvents are dried or aired, coating a thin layer of protective paint on the surface of the magnesium ignition explosive output explosive to play the roles of preventing explosive blocks from falling and preventing moisture; the third layer of charge is potassium nitrate borate, and is filled in the bidirectional pressure cartridge in a press-fitting mode, the pressure of the charge at two ends of the bidirectional pressure cartridge is the same as that of the sealing pads of the fire transmission holes, and the sealing pads are provided with four fire transmission holes with the diameter of 1.5 mm, so that the bidirectional pressure cartridge has a bidirectional ignition function. The igniter and the separating device shell are connected in a threaded mode, the bidirectional pressure cartridge and the separating device shell are bonded through a high-temperature-resistant adhesive, and a fire transfer gap of 3.15 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 to be a redundant structure, namely two igniters and a bidirectional pressure cartridge constitute two groups of independent ignition-fire transfer sequences, any group of normal work can independently complete separation tasks, and the ignition reliability of the separation device is improved.
When the gas-liquid separation device needs to act, the gas-liquid separation device supplies power to the igniter, sequentially ignites the ultrafine particle magnesium ignition powder, the fine particle magnesium ignition powder and the potassium borate nitrate, and generates high-temperature high-pressure gas to drive the piston to complete the separation task.
Compared with the prior art, the invention has the beneficial effects that:
compared with the existing combustion driving type initiating explosive separation device, the novel explosive charging sequence designed by the invention has the following advantages:
1) the charge types used by the invention are obtained by high-temperature test verification and screening at 180-200 ℃, the performance of each medicament can meet the high-temperature environment requirement of the combustion-driven type fire separation 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 cartridge structure has the function of bidirectional ignition, and the charge structure of the T-shaped input end and the output end of the bidirectional pressure cartridge is optimally designed, so that the bidirectional pressure cartridge is ignited by receiving the output flame from any igniter, high-temperature and high-pressure gas can be generated to complete the separation action, and the ignition reliability of the separation 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 structural diagram of a charging sequence of a combustion-driven high-temperature-resistant firer separation device for a deep space probe according to an embodiment of the invention.
Description of reference numerals:
1. a first igniter; 2. a first ultrafine particulate magnesium ignition charge; 3. a first bridge wire; 4. a first fine particle magnesium ignition charge; 5. a first positioning ring; 6. a first fire transfer hole sealing pad; 7. a bi-directional pressure cartridge; 8. potassium boronitrate; 9. a second fire transfer hole sealing pad; 10. a second positioning ring; 11. a second fine particle magnesium ignition charge; 12. a second bridge wire; 13. a second ultrafine particle magnesium ignition powder; 14. a second igniter; 15. a gas channel; 16. a T-shaped actuating device shell.
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 figure 1, the deep space detector is composed of a combustion-driven high-temperature-resistant fire separation device charging sequence and a T-shaped actuating device shell 16, wherein the two-way ignition sequence is composed of two igniters and a bidirectional pressure medicine cylinder. A first igniter 1 shell, a first superfine particle magnesium ignition powder 2, a first bridge wire 3, a first fine particle magnesium ignition powder 4, a first positioning ring 5, a first fire transmission hole sealing pad 6, a bidirectional pressure cartridge 7 and potassium borate nitrate 8 form a fire transmission sequence. A second igniter 14 shell, a second superfine particle magnesium ignition powder 13, a second bridge wire 12, a second fine particle magnesium ignition powder 11, a second positioning ring 10, a second fire transfer hole sealing pad 9, a bidirectional pressure cartridge 7 and potassium borate 8 form another fire transfer sequence. The T-shaped actuating device shell 16 and the fuel gas channel 15 are combined to form two paths of fire transfer channels and a three-way combustion chamber structure, the T-shaped actuating device shell provides a fire transfer channel and a work pressure transfer channel for any one path of fire transfer sequence, the redundant design of a charging sequence with redundant firing function, redundant fire transfer sequence and redundant work output of an igniter is realized, and any one group of charging sequence can independently complete the separated actuating task when working normally. The first igniter 1, the bi-directional pressure cartridge 7 and the second igniter 14 are coaxially mounted in mounting holes in the actuator housing 16. The first igniter 1 and the second igniter 14 both have a non-inductive electric igniter characteristic. The superfine particle magnesium ignition powder, the fine particle magnesium ignition powder and the potassium borate and nitrate all have high temperature resistance, are suitable for high temperature resistant environment for a deep space detector, and can resist the high temperature of 200 ℃ for more than 10 days.
The "T" shaped actuator housing 16 has a three-way combustion chamber configuration with two input and one output flame-transfer passages. The first igniter 1 and the second igniter 14 are fixedly mounted on the actuator housing 16 by means of screw connection. The bi-directional pressure cartridge 7 is bonded to the "T" shaped actuator housing 16 by silicone rubber. The two-way pressure cartridge 7 is provided at both ends thereof with a first positioning ring 5 and a second positioning ring 10, respectively, and the first positioning ring 5 and the second positioning ring 10 are used for fixing the assembling position of the two-way pressure cartridge 7, providing a fire transfer passage, controlling the gap between the first igniter 1 and the two-way pressure cartridge 7, and controlling the gap between the second igniter 14 and the two-way pressure cartridge 7. The first igniter 1, the bi-directional pressure cartridge 7 and the second igniter 14 are on the same axis. The center of the output end of each igniter is aligned with the center of the input end of the bidirectional pressure cartridge 7, and a 3.15 mm gap is reserved between each igniter and the bidirectional pressure cartridge 7. The first fire transfer hole sealing pad 6 and the second fire transfer hole sealing pad 9 are provided with four fire transfer holes with the diameter of 1.5 mm (the first fire transfer hole sealing pad 6 and the second fire transfer hole sealing pad 9 are respectively provided with two fire transfer holes with the diameter of 1.5 mm), any one igniter can normally output and enable the two-way pressure explosive 7 barrel to normally work, and the firing reliability of the separation actuating device can be improved.
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 first igniter 1 and the second igniter 14 are identical in structure and charge. In order to improve the high-temperature stability, the two medicaments are subjected to high-temperature aging pretreatment at 180 ℃ for 1 day before being loaded into an igniter, so that the pre-reaction of the medicaments in a long-term high-temperature environment is reduced. The first ultrafine particle magnesium ignition powder 2 and the second ultrafine particle magnesium ignition powder 13 are coated in a slurry form in an igniter chamber as a first layer charge, are in close contact with the bridge wire, and serve as bridge wire ignition powder. The first fine particle magnesium ignition powder 4 and the second fine particle magnesium ignition powder 11 are used as second layer charging to fill the cavity of the igniter charging chamber in a slurry charging mode and used as output ignition powder, after the slurry charging solvent is dried or aired, a layer of high-temperature-resistant protective paint is coated on the surfaces of the first fine particle magnesium ignition powder 4 and the second fine particle magnesium ignition powder 11, and the functions of fixing and moisture prevention 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 diameters of the first bridge wire 3 and the second bridge wire 12 are more than 60 micrometers, the bridge wires are combined with the superfine particle magnesium ignition powder, the requirements of reliable ignition of 5 amperes, no ignition of 1 ampere and 1 watt for 5 minutes and safety of resisting electrostatic discharge of 25 kilovolt feet and foot shells can be met through the optimized design of the diameters, the lengths and the resistances of the bridge wires and the optimized design matched with the bridge wire sensitivity and the heat transfer property 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 first igniter 1 and the second igniter 14 which are arranged in the same T-shaped actuating device shell 16 are selected through grouping and screening of resistance matching, the smaller the difference between the matching resistances is, the better the difference is, and the difference is generally not more than 2%.
The temperature resistance characteristics of the first ultrafine particle magnesium ignition powder 2, the second ultrafine particle magnesium ignition powder 13, the first fine particle magnesium ignition powder 4 and the second fine particle magnesium ignition powder 11 of the high-temperature resistant igniter are verified by high-temperature tests, a DSC curve has two reaction peaks from normal temperature to 550 ℃, one secondary reaction peak (405 ℃) and one main reaction peak (more than 550 ℃), the two medicaments of the first igniter 1 and the second igniter 14 are subjected to high-temperature aging pretreatment at 180 ℃, the DSC secondary reaction initial reaction temperature of a normal-temperature sample is 390 ℃, the secondary reaction peak temperature is 405 ℃, the initial reaction temperature of the secondary reaction of a high-temperature sample is 388 ℃ (still higher than 200 ℃ by 188 ℃), the secondary reaction peak temperature is 404 ℃, and the secondary reaction peak temperature change amount is-2 ℃ compared with the normal-temperature sample; the weight loss variation of the sample at the high temperature of 200 ℃ for 10 days is-0.094%, the variation of the p-t peak pressure mean value is-8% (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% (18 cm to 22 cm) and the flame duration change rate was-10% (88 ms to 52 ms) for the 10-day high temperature sample at 200 ℃. The ignition powder has better temperature resistance than the common ignition powder, and the temperature resistance parameters show that the two magnesium ignition powders can endure the high-temperature environment of 200 ℃ for 10 days.
The high-temperature resistant bidirectional pressure cartridge 7 is filled with potassium boronitrate 8, and the potassium boronitrate is subjected to high-temperature aging pretreatment at 180 ℃ for 1 day before the potassium boronitrate 8 is filled into the bidirectional pressure cartridge 7 so as to improve the high-temperature stability, so that the pre-reaction of the medicament in a long-term high-temperature environment is reduced. The potassium borate nitrate 8 fills up two-way pressure cartridge case 7 with the pressure medicine mode, and cartridge case both ends are sealed with first fire transmission hole sealing gasket 6 and second fire transmission hole sealing gasket 9, and the powder charge condition at both ends, the structure of spreading a fire are the same completely to be of value to guarantee that the input end structure has higher flame sensitivity and the function of two-way ignition. The potassium borate nitrate 8 has the characteristics of high temperature resistance, impact resistance, high combustion heat value, moderate peak pressure and longer fuel gas pressure duration, and is suitable for being used as the work doing charge of a combustion-driven actuating device. The temperature resistance test of the potassium boronitrate 8 shows that the potassium boronitrate can resist the high-temperature environment of 180 ℃ for more than 10 days. The two ends of the bidirectional pressure cartridge 7 are respectively provided with a first positioning ring 5 and a second positioning ring 10, and the first positioning ring 5 and the second positioning ring 10 are used for fixing the assembling position of the bidirectional pressure cartridge 7, providing a fire transfer channel and controlling the gap between the igniter and the bidirectional pressure cartridge 7. The middle part below design of two-way pressure cartridge case 7 has the hole of transfering a fire, and the hole of transfering a fire aligns with output gas passageway 15 of "T" type actuator casing 16, and the hole of transfering a fire is as the energy output channel of two-way pressure cartridge case 7, has a thin layer aluminium foil gasket that seals between the hole of transfering a fire and potassium borate 8 for medicament structure reinforcement and dampproofing.
The high-temperature resistant pressure medicine potassium borate nitrate 8 is verified to have temperature resistance characteristics through high-temperature tests, a DSC curve has a reaction peak from normal temperature to 550 ℃, the initial reaction temperature of a DSC melting endothermic peak of a normal-temperature sample is 335.0 ℃, the medicament is subjected to high-temperature aging pretreatment at 180 ℃ for improving the long-term high-temperature environment stability, the initial reaction temperature of the melting endothermic peak of the high-temperature sample at 180 ℃ for 5 days is changed into 335.4 ℃ (the temperature is still 155 ℃ higher than 180 ℃), and the temperature variation is-0.4 ℃. The melting endothermic peak reaction peak temperature of the normal temperature sample was 336.0 ℃, 180 ℃, the reaction peak temperature of the 5-day high temperature sample was 336.2 ℃, and the temperature variation was-0.2 ℃. The weight loss change amount of the high-temperature sample at 180 ℃ for 10 days is-1.18 percent, the p-t peak pressure change amount of the high-temperature sample at 180 ℃ for 10 days is 3.34 MPa to 2.29 MPa, and the maximum pressure rise time change amount is 4.05 milliseconds to 4.48 milliseconds. The combustion type charging device has the advantages of good temperature resistance, long combustion time and high energy utilization rate, and is suitable for being used as a combustion driving type separating device. The temperature resistance tests show that the boron potassium nitrate 8 can resist the high-temperature environment of 180 ℃ for 10 days.
The charging sequence consisting of the first ultrafine particle magnesium ignition powder 2, the second ultrafine particle magnesium ignition powder 13, the first fine particle magnesium ignition powder 4, the second fine particle magnesium ignition powder 11 and the potassium borate 8 is suitable for the high-temperature environment for the deep space probe, can resist high temperature of 180-200 ℃ for more than 10 days, and can meet the requirement of a combustion-driven high-temperature-resistant firer separating 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 potassium borate are subjected to the DSC test, the high-temperature test at 180-200 ℃, the thermal weight loss test, the appearance observation, the bridgewire sensitivity test and the work power test of the medicament, so that 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 combustion-driven high-temperature resistant fire separation device for a 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. Deep space detector is with burning driving high temperature resistant firer separator charge sequence, actuates the device casing by two way biography fire sequences and one "T" type and constitutes, and two way biography fire sequences comprise two some firearms, a two-way pressure cartridge case, its characterized in that: the first igniter shell, the first superfine particle magnesium ignition powder, the first bridge wire, the first fine particle magnesium ignition powder, the first positioning ring, the first fire transfer hole sealing pad, the bidirectional pressure cartridge and potassium borate and potassium nitrate filled in the bidirectional pressure cartridge form a fire transfer sequence; the second igniter shell, the second ultrafine particle magnesium ignition powder, the second bridge wire, the second fine particle magnesium ignition powder, the second positioning ring, the second fire transfer hole sealing pad, the bidirectional pressure medicine cylinder and the potassium borate and potassium nitrate filled in the bidirectional pressure medicine cylinder form another fire transfer sequence; the potassium boronitrate is positioned in the bidirectional pressure cartridge; the T-shaped actuating device shell is provided with a three-way combustion chamber structure, the three-way combustion chamber is provided with two paths of input fire transmission channels and one path of output gas channel, and the three-way combustion chamber provides a fire transmission channel and a gas pressure transmission channel for any one path of fire transmission sequence; the first igniter, the bidirectional pressure medicine cylinder and the second igniter are arranged on the same axis and are arranged in the mounting hole on the T-shaped actuating device shell.
2. The deep space detector combustion-driven high-temperature-resistant fire separation device charging sequence for the deep space detector as claimed in claim 1, wherein the T-shaped actuating device shell is of a three-way combustion chamber structure, the three-way combustion chamber is provided with two paths of input fire transfer channels and one path of output fuel gas channel, and the bidirectional pressure cartridge is fixedly mounted with the T-shaped actuating device shell in a silicon rubber bonding mode; the first igniter and the second igniter are connected with the T-shaped actuating device shell in a threaded connection mode; the first igniter, the bidirectional pressure medicine cylinder and the second igniter are positioned on the same axis; the center of the output end of each igniter is aligned with the center of the input end of the bidirectional pressure cartridge; a3.15 mm gap is reserved between each igniter and the bidirectional pressure medicine cylinder, four fire transfer holes with the diameter of 1.5 mm are totally arranged on the sealing gaskets of the two fire transfer holes, and the bidirectional pressure medicine cylinder can work normally when any one igniter outputs normally.
3. The charge sequence of the combustion-driven high-temperature-resistant firer separation device for the deep space probe according to claim 1, wherein the first igniter and the second igniter are both filled with superfine-particle magnesium ignition powder and fine-particle magnesium ignition powder, the particle sizes of the superfine-particle magnesium ignition powder and the fine-particle magnesium ignition powder are 40 micrometers and 100 micrometers respectively, and the two igniters are completely identical in structure and charge; the two medicaments are subjected to high-temperature aging pretreatment at 180 ℃ for 1 day before being loaded into a fire maker; the superfine particle magnesium ignition powder is coated in a slurry-shaped mode in an igniter powder chamber to serve as a first layer of powder charge, is in close contact with the bridge wire and serves as bridge wire ignition powder; and (3) taking the fine particle magnesium ignition powder as a second layer of powder charge, filling the containing cavity of the igniter powder chamber in a slurry state powder charge mode, taking the containing cavity as an output ignition powder, and coating a thin layer of high-temperature-resistant protective paint on the surface of the fine particle magnesium ignition powder after the slurry state powder charge solvent is dried or aired.
4. The combustion-driven high-temperature-resistant fire separation device charging sequence for the deep space probe as claimed in claim 3, wherein the diameter of the bridge wire is more than 60 microns, the bridge wire is combined with the ultrafine particle magnesium ignition powder, and the requirements of reliable ignition at 5 amperes, no ignition at 1 ampere at 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 matched with the bridge wire sensitivity and the heat transfer property of the magnesium ignition powder.
5. The combustion-driven high-temperature-resistant fire separation device charging sequence for the deep space probe as claimed in claim 4, wherein the first igniter and the second igniter which are arranged in the same T-shaped actuating device shell are selected through resistance pairing grouping screening, and the difference between paired resistances is not more than 2%.
6. The charge sequence of the combustion-driven high-temperature-resistant fire separation device for the deep space probe according to claim 1, wherein the bidirectional pressure cartridge is filled with potassium boronitrate, and the potassium boronitrate is subjected to high-temperature aging pretreatment at 180 ℃ for 1 day before being filled into the bidirectional pressure cartridge; the two-way pressure cartridge case is filled with potassium borate nitrate in a pressing mode, two ends of the cartridge case are respectively packaged by a first fire transmission hole sealing pad and a second fire transmission hole sealing pad, and the charging conditions and the fire transmission structures at the two ends are completely the same.
7. The fire-driving type high-temperature-resistant fire separation device charging sequence for the deep space probe as claimed in claim 6, wherein the bidirectional pressure cartridge is provided at both ends thereof with a first positioning ring and a second positioning ring, respectively, for fixing the assembling position of the bidirectional pressure cartridge, providing a fire transfer passage and controlling the gap between the igniter and the bidirectional pressure cartridge.
8. The deep space probe combustion-driven high-temperature-resistant fire separation device charging sequence is characterized in that an output fire transfer hole is designed below the middle part of a bidirectional pressure cartridge, the output fire transfer hole is aligned with an output fuel gas channel of a T-shaped actuating device shell and serves as an energy output channel of the bidirectional pressure cartridge, and a thin-layer aluminum foil sealing gasket is arranged between the output fire transfer hole and potassium boronitrate.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911082693.2A CN110749251B (en) | 2019-11-07 | 2019-11-07 | Charging sequence of combustion-driven high-temperature-resistant fire separation device for deep space probe |
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