CN113187623B - Temperature excitation type self-starting safety pressure relief device for solid rocket engine - Google Patents
Temperature excitation type self-starting safety pressure relief device for solid rocket engine Download PDFInfo
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- CN113187623B CN113187623B CN202110348558.9A CN202110348558A CN113187623B CN 113187623 B CN113187623 B CN 113187623B CN 202110348558 A CN202110348558 A CN 202110348558A CN 113187623 B CN113187623 B CN 113187623B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/38—Safety devices, e.g. to prevent accidental ignition
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- Portable Nailing Machines And Staplers (AREA)
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Abstract
The invention relates to a temperature-excited self-starting safety pressure relief device for a solid rocket engine, which comprises a temperature trigger unit, an ignition unit and a cutting rope. The temperature trigger unit consists of a shell with fins, a solution and a acting piston, and after the ambient temperature reaches a certain temperature, the solution is gasified to generate starting energy of spontaneous ignition; the ignition unit is connected to the rear end of the temperature trigger unit, consists of a cavity, a locking sheet and a needling detonator and is used for outputting ignition energy under a proper needling sensitivity; the cutting cable is connected with the end of the needle-pricked detonator of the ignition unit, and the cutting cable is detonated by shock waves generated by the needle-pricked detonator to cut the engine shell to form a pressure relief channel. The passive self-starting device can realize the passive self-starting of the fire driving type pressure relief device under a certain environmental temperature condition.
Description
Technical Field
The invention belongs to the technical field of solid rocket engine safety, and relates to a temperature-excited self-starting safety pressure relief device for a solid rocket engine.
Background
For a solid rocket engine, when a large fire disaster occurs around the engine, the propellant/thermal decomposition in the engine generates combustion reaction and even generates explosion phenomenon. The fire driving type pressure relief device is arranged on the surface of the engine, so that the engine shell can be cut before the engine explodes, the internal pressure of the engine is released, the engine is prevented from explosion reaction, and the damage degree of the engine to the surrounding environment and equipment under the condition of large fire is remarkably reduced.
Based on the design requirements of the characteristics and the working reliability of the pressure relief device driven by the fire, the triggering operation of the pressure relief device after being excited by certain environmental temperature is very critical according to the environmental characteristics of a large fire. Most of the prior art adopts environment temperature signals collected by a peripheral judgment temperature sensor, judges the environment temperature signals through an external logic judgment and control system, and starts an initiating explosive drive type pressure relief device to work in an electric ignition mode. Because the solid rocket engine is not allowed to be electrified continuously for a long time in the service process, the use condition of the fire driving type pressure relief device adopting the electric ignition mode is limited.
Disclosure of Invention
The invention solves the technical problems that: the defects of the existing initiating explosive starting temperature control technology are overcome, the temperature excitation type self-starting safety pressure relief device for the solid rocket engine is provided, and the passive self-starting of the initiating explosive driving pressure relief device can be realized under a certain environment temperature condition.
The technical scheme of the invention is as follows:
a temperature excitation type self-starting safety pressure relief device for a solid rocket engine comprises a temperature trigger unit, an ignition unit and a cutting rope;
the temperature trigger unit comprises a shell with fins, a solution and a piston firing pin, wherein the piston firing pin is arranged in the shell with fins, the solution is arranged in an inner cavity formed by the piston firing pin and the shell with fins, and the rear end of the piston firing pin is of a needle-shaped structure; after the environmental temperature reaches the critical temperature of solution gasification, the solution is gasified to generate the starting energy of spontaneous combustion;
the ignition unit comprises a cavity, a locking sheet and a needle-punched detonator; the locking sheet is positioned in the shell with the fins and is used for realizing the limiting locking and sealing of the piston firing pin at the beginning; the cavity is sleeved on the rear part of the shell with the fins in a laser welding mode, the rear part of the cavity is sequentially provided with a needling detonator and a cutting cable from front to back, and the needling detonator is connected with the cutting cable;
the ignition unit is used for outputting ignition energy under a proper needling sensitivity, and the cutting rope is detonated by shock waves generated by the needling detonator to cut the shell of the engine to form a pressure relief channel.
The solution is a mixture ratio solution of water, ethanol and glycol, and the trigger temperature is controlled by adjusting the components of each item.
The piston firing pin is made of hard metal, and the distance between the piston firing pin and the acupuncture detonator is adjusted to control the impact energy, so that safe and reliable ignition is realized.
The material of the locking piece is aluminum.
The acupuncture detonator and the cutting cable are bonded to the rear part of the cavity through epoxy resin glue.
The jet flow surface of the cutting rope is the cutting direction.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, the solution in the temperature trigger unit is gasified, so that the self-starting of the fire driving type safety pressure relief device under the specified temperature condition can be completed;
(2) the starting temperature of the initiating explosive driving type safety pressure relief device can be adjusted by adjusting the component proportion of the solution in the temperature trigger unit;
(3) according to the invention, the environmental adaptability and service convenience of the safety pressure relief device for the initiating explosive device are improved by automatically starting the safety pressure relief device.
Drawings
FIG. 1 is a schematic view of a self-starting safety pressure relief device according to the present invention.
Detailed Description
The invention is further elucidated with reference to the drawing.
The invention discloses a temperature excitation type self-ignition safety device for a solid rocket engine, which comprises the following components in sequence from front to back according to a trigger sequence: the device comprises a temperature trigger unit, an ignition unit and a cutting rope. The temperature trigger unit consists of a shell 1 with fins, a solution 2 and a piston firing pin 3, and after the ambient temperature reaches a certain temperature, the solution is gasified to generate starting energy of spontaneous combustion; the ignition unit is connected to the rear end of the temperature trigger unit, consists of a cavity 5, a locking sheet 4 and a needling detonator 6 and is used for outputting ignition energy under proper needling sensitivity; the cutting cable is connected with the end of the needle-punched detonator of the ignition unit, and the cutting cable is detonated by shock waves generated by the needle-punched detonator to cut the engine shell to form a pressure relief channel.
As shown in fig. 1, the specific connection form is:
a piston firing pin 3 is arranged in the finned shell 1, and a solution 2 is filled in an internal cavity formed by the piston firing pin 3 and the finned shell 1; the rear end of the piston firing pin 3 is in a needle-shaped structure, and the locking sheet 4 is positioned in the shell 1 with fins and is used for realizing the limiting locking and sealing of the piston firing pin 3 at the beginning; the cavity 5 is sleeved on the rear part of the shell 1 with the fins in a laser welding mode, the rear part of the cavity 5 is sequentially provided with the acupuncture detonator 6 and the cutting cable 7 from front to back, and the acupuncture detonator 6 is connected with the cutting cable 7.
The solution 2 is a mixture of water, ethanol and glycol, and the triggering temperature is controlled by adjusting the components of each component.
The piston firing pin 3 is made of hard metal, and the impact energy is controlled by adjusting the distance between the piston firing pin and the acupuncture detonator, so that safe and reliable firing is realized.
The locking sheet 4 is made of aluminum, and the limiting and sealing of the piston firing pin are realized through the locking sheet, so that the pressure build-up of the gas for driving the piston firing pin is ensured.
The needle detonator 6 and the cutting cable 7 are bonded to the rear part of the cavity 5 through epoxy resin glue.
According to the invention, high pressure generated after phase change of water, ethanol and glycol solution in a certain mass ratio at a certain environmental temperature is adopted to drive the piston firing pin cavity to move so as to impact the needle detonator, and the cutting rope is ignited and detonated, so that the ignition and starting of the pressure relief device at a certain temperature are realized. Table 1 is a table of the ratio of water, ethanol and glycol solutions and the unlock temperature.
TABLE 1 water, ethanol and glycol solution ratio and unlocking temperature corresponding table
Taking the case of large fire around a solid rocket engine or fire around a storage building as an example, when the ambient temperature around the engine continuously rises, the shell with fins in the device transmits the ambient heat into the temperature trigger unit, when the temperature reaches the critical temperature of solution gasification, the solution in the temperature trigger unit is gasified, and when the temperature continuously rises to a certain range, the gas breaks through the locking sheet; the position locking of the piston firing pin is released, and the piston firing pin moves at a high speed in the cavity to finally achieve the needle stimulation energy; when the piston firing pin pierces the needling detonator, the needling powder in the needling detonator is combusted, rapidly turns to deflagration, and detonates the lower layer initiating powder in the form of weak shock wave or heat energy, after the initiating powder is detonated, the cutting cable is detonated in the form of strong shock wave, and directional metal jet flow is generated after the cutter is detonated, so that the cutting pressure relief of the solid rocket engine shell is realized, and the response of the engine to explosion and explosion is avoided.
The temperature-excited self-starting safety pressure relief device can be applied to various solid and liquid rocket engines and tactical ammunition systems.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (5)
1. The utility model provides a temperature excitation type self-starting safety pressure relief device for solid rocket engine which characterized in that: comprises a temperature trigger unit, an ignition unit and a cutting rope (7);
the temperature trigger unit comprises a shell (1) with fins, a solution (2) and a piston firing pin (3), wherein the piston firing pin (3) is installed inside the shell (1) with fins, the solution (2) is installed in an internal cavity formed by the piston firing pin (3) and the shell (1) with fins, and the rear end of the piston firing pin (3) is of a needle-shaped structure; after the environmental temperature reaches the critical temperature of solution gasification, the solution is gasified to generate the starting energy of spontaneous combustion;
the ignition unit comprises a cavity (5), a locking sheet (4) and a needle detonator (6); the locking sheet (4) is positioned inside the shell (1) with the fins and is used for realizing the limiting locking and sealing of the piston firing pin (3) at the beginning; the cavity (5) is sleeved on the rear part of the shell (1) with the fins in a laser welding mode, the rear part of the cavity (5) is sequentially provided with a needling detonator (6) and a cutting cable (7) from front to back, and the needling detonator (6) is connected with the cutting cable (7);
the ignition unit is used for outputting ignition energy under a proper needling sensitivity, and a cutting rope is detonated by shock waves generated by a needling detonator to cut the shell of the engine to form a pressure relief channel;
the solution (2) is a mixture ratio solution of water, ethanol and glycol, and the trigger temperature is controlled by adjusting the components of each item.
2. The temperature-activated self-starting safety pressure relief device for a solid rocket engine according to claim 1, wherein: the piston firing pin (3) is made of hard metal, and the impact energy is controlled by adjusting the distance between the piston firing pin and the acupuncture detonator, so that safe and reliable firing is realized.
3. The temperature-activated self-starting safety pressure relief device for a solid rocket engine according to claim 1, wherein: the locking sheet (4) is made of aluminum.
4. The temperature-activated self-starting safety pressure relief device for a solid rocket engine according to claim 1, wherein: the acupuncture detonator (6) and the cutting cable (7) are bonded to the rear part of the cavity (5) through epoxy resin glue.
5. The temperature-activated self-starting safety pressure relief device for a solid rocket engine according to claim 4, wherein: the jet flow surface of the cutting rope (7) is in the cutting direction.
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| CN202110348558.9A CN113187623B (en) | 2021-03-31 | 2021-03-31 | Temperature excitation type self-starting safety pressure relief device for solid rocket engine |
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| CN202110348558.9A CN113187623B (en) | 2021-03-31 | 2021-03-31 | Temperature excitation type self-starting safety pressure relief device for solid rocket engine |
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| CN110761917A (en) * | 2019-11-05 | 2020-02-07 | 西安长峰机电研究所 | Passive temperature sensing starting device |
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| US6640719B1 (en) * | 1999-01-11 | 2003-11-04 | The United States Of America As Represented By The Secretary Of The Army | Fuze explosive train device and method |
| DE102008025218B3 (en) * | 2008-05-27 | 2009-11-12 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh | initiator |
| CN107907016B (en) * | 2017-11-29 | 2019-08-20 | 四川蓝狮科技有限公司 | A kind of thermal starting pressure relief device |
| CN109631694B (en) * | 2018-12-20 | 2021-01-26 | 南京理工大学 | Pressure relief structure of memory alloy type insensitive ammunition |
| CN111023914A (en) * | 2020-01-02 | 2020-04-17 | 四川久安芯电子科技有限公司 | Hot start cutting device |
| CN111622863B (en) * | 2020-06-05 | 2021-04-06 | 湖北三江航天红林探控有限公司 | Thrust termination device of small solid rocket engine |
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| CN110761917A (en) * | 2019-11-05 | 2020-02-07 | 西安长峰机电研究所 | Passive temperature sensing starting device |
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