CN115773698B - Multifunctional cabin opening mechanism for rocket - Google Patents
Multifunctional cabin opening mechanism for rocket Download PDFInfo
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- CN115773698B CN115773698B CN202211525997.3A CN202211525997A CN115773698B CN 115773698 B CN115773698 B CN 115773698B CN 202211525997 A CN202211525997 A CN 202211525997A CN 115773698 B CN115773698 B CN 115773698B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The utility model discloses a multifunctional cabin opening mechanism for a rocket, which comprises a connecting bottom, wherein a first connecting part and a second connecting part are respectively arranged at the upper end and the lower end of the connecting bottom, a first fire powder cavity is arranged in the connecting bottom and close to the first connecting part, a second fire powder cavity is arranged in the connecting bottom and close to the second connecting part, a cabin opening medicine box which is arranged towards the first connecting part is arranged in the first fire powder cavity, an ignition medicine box which is arranged towards the second connecting part is arranged in the second fire powder cavity, and a security mechanism for igniting the cabin opening medicine box is arranged between the cabin opening medicine box and the ignition medicine box.
Description
Technical Field
The utility model relates to the technical field of rocket training shells, in particular to the technical field of multifunctional cabin opening mechanisms for rocket shells.
Background
With advances in science and technology, both military and civilian facilities have changed tremendously. Modern military has high requirements on accurate striking, which can reduce the cost on one hand and reduce the damage to innocent people on the other hand. Therefore, the remote sensing, navigation, guidance and internet information technology in modern technology are applied to missile launching. In modern military performance, mine-laying rocket projectiles still play an important role, and can rapidly lay down a mine field in front of an enemy front armor cluster. However, to achieve fast, accurate mine deployment, a more preferred mine deployment rocket projectile is required.
The utility model discloses a mine-laying rocket training bomb, which belongs to the technical field of rockets, as disclosed in Chinese patent publication No. CN 205561674U. The utility model relates to a mine-spreading rocket training bomb which comprises a hood, a mine cabin, a simulated mine, a push plate assembly, a cabin opening mechanism, a powder box, a combustion chamber, propellant powder, a spray pipe front section, a stabilizing device, a spray pipe rear section, a conductive cover and the like. The training bullet cabin opening mode is controlled by the delayed fuze, the delayed fuze is poor in controllability, inconvenient in time control, low in safety, easy to burn out in advance in the transmitting process to cause early cabin opening, and easy to influence mine distribution effect.
Disclosure of Invention
The utility model aims to solve the problems in the prior art and provides a multifunctional cabin opening mechanism for a rocket, which is more convenient to adjust and control the cabin opening of the rocket and higher in safety.
In order to achieve the above purpose, the utility model provides a multifunctional cabin opening mechanism for a rocket, which comprises a connecting bottom, wherein a first connecting part and a second connecting part are respectively arranged at the upper end and the lower end of the connecting bottom, a first fire medicine cavity is arranged in the connecting bottom and close to the first connecting part, a second fire medicine cavity is arranged in the connecting bottom and close to the second connecting part, a cabin opening medicine box which is arranged towards the first connecting part is arranged in the first fire medicine cavity, an ignition medicine box which is arranged towards the second connecting part is arranged in the second fire medicine cavity, a security mechanism for igniting the cabin opening medicine box is arranged between the cabin opening medicine box and the ignition medicine box, the security mechanism comprises a slide block seat, a seat cavity which is communicated with the first fire medicine cavity and the second fire medicine cavity is arranged in the connecting bottom, a slide block seat is fixedly arranged in the seat, one end, close to the ignition medicine box, which is arranged in the slide block seat, is provided with a push rod cavity which is matched with the push rod part, the ignition part is axially arranged in the slide seat, and the push rod part is arranged in the slide block seat, and the ignition part is used for receiving the push rod part, and the ignition part is also used for controlling the push rod part.
Preferably, the linkage part comprises a sliding part, a radial sliding cavity which is radially arranged is arranged at one end, close to the capsule opening medicine box, in the sliding block seat, the sliding part can be radially arranged in the radial sliding cavity in a sliding way, and the ignition part comprises a needle detonator arranged on the sliding part and a needle beating part correspondingly arranged on the sliding block seat; the sliding part comprises an ignition position and a safety position at the position in the radial sliding cavity, and a sliding block spring for driving the sliding part to slide towards the ignition position is arranged in the radial sliding cavity; when the sliding part is positioned at the ignition position, the needled detonator corresponds to the firing pin part, and when the sliding part is positioned at the safety position, the needled detonator is staggered with the firing pin part.
Preferably, the firing pin component comprises a pin body and a first firing head, a firing pin sliding cavity communicated with the radial sliding cavity is arranged in the sliding component, the pin body is slidably arranged in the firing pin sliding cavity, and the end part of the firing pin sliding cavity is provided with the first firing head for driving the firing pin sliding cavity to slide towards the end of the radial sliding cavity.
Preferably, a booster is further provided between the capsule and the needle detonator, and the needle detonator corresponds to the booster when the sliding member is positioned at the ignition position.
Preferably, a pressing plate is arranged at the top of the sliding block seat, and the detonating tube is fixedly arranged in the pressing plate.
Preferably, a medicine box tray is arranged in the first medicine cavity, a medicine placing part matched with the capsule-opening medicine box is arranged on the medicine box tray, the capsule-opening medicine box is arranged in the medicine placing part, a medicine box fire passing hole communicated with the medicine placing part is formed in the bottom of the medicine box tray, and the medicine box fire passing hole is formed in a position corresponding to the detonating tube.
Preferably, the sliding component is internally provided with a pin body which is axially downwards arranged, a pin hole matched with the pin body is arranged between the radial sliding cavity and the push rod sliding cavity, the push rod component is provided with a pushing part matched with the pin hole, and the sliding component is positioned at a safe position when the pin body is matched with the pin hole.
Preferably, a pin cavity is further arranged beside the radial sliding cavity, a short pin is slidably arranged in the pin cavity, a ball cavity is communicated between the pin cavity and the radial sliding cavity, steel balls capable of sliding along the ball cavity are arranged in the ball cavity, and a clamping groove matched with the steel balls is formed in the sliding part; when the short pin is positioned at the ball cavity, the steel ball and the clamping groove are in an engaged position, and one end of the pin cavity is provided with a second ignition head for driving the short pin to slide along the pin cavity.
Preferably, an electronic control board electrically connected with the first ignition head and the second ignition head is arranged in the connecting bottom, and a first micro switch SW1 in control connection with the first ignition head and a second micro switch SW2 in control connection with the second ignition head are arranged on the electronic control board.
The multifunctional cabin opening mechanism for the rocket has the beneficial effects that: according to the utility model, the ignition and take-off and mine throwing of the training rocket projectile are respectively controlled by arranging the ignition powder box and the cabin opening powder box, the positions of the sliding part and the acupuncture detonator arranged on the sliding part are limited by arranging the limiting mechanism, the thrust of the ignition powder box is received, so that the limitation of the sliding part is relieved, the acupuncture detonator and the firing pin part can be positioned at the ignition position, the limitation of the limiting mechanism can be relieved only after the ignition powder box ignites, the cabin opening powder box can be ensured to ignite later than the ignition powder box, the early ignition of the cabin opening powder box is avoided, the early cabin opening is caused, the throwing of the training projectile such as the fire extinguishing projectile, the rainfall projectile and the mine throwing is influenced, the training effect is avoided, and the safety is higher.
The features and advantages of the present utility model will be described in detail by way of example with reference to the accompanying drawings.
Drawings
Fig. 1 is a front cross-sectional view of a multifunctional cabin opening mechanism for a rocket of the present utility model.
FIG. 2 is a schematic view of the cross-sectional structure A-A in FIG. 1.
Fig. 3 is an enlarged schematic view of the security mechanism in fig. 2.
Fig. 4 is a schematic view of a front view cross-section structure of the security mechanism.
Fig. 5 is a schematic top view partially in cross-section of the security mechanism.
Fig. 6 is a schematic view of the present utility model when mounted to a rocket projectile.
Wherein:
1-connecting the bottom; 101-a second connection; 102-a second connection; 103-a seat cavity; 3-electronic control board; 5-a capsule; 6-a security mechanism; 7-a medicine box tray; 8-ignition cartridge; 61-pressing plate; 62-a striker member; 63-detonating tube; 64-sliding members; 65-a push rod component; 66-a slide block seat; 68-short pins; 69-steel balls; 610-a second ignition head; 611-a slider spring; 613-needling a detonator; 621-needle body; 622—first ignition head; 641-pins; 661-a push rod sliding cavity; 662-radial sliding chamber; 663-pin holes; 664-pin cavity; 665-ball cavity; 666-firing pin slide chamber; 71-passing the medicine box through the fire hole.
Detailed Description
The present utility model will be further described in detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present utility model more apparent. It should be understood that the detailed description and specific examples, while indicating the utility model, are intended for purposes of illustration only and are not intended to limit the scope of the utility model. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present utility model.
In the description of the present utility model, it will be understood that when an element is referred to as being "fixed" or "disposed" on another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
In the description of the present utility model, it should be noted that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships in which the inventive product is conventionally placed in use, are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the apparatus or element to be referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. The meaning of "a number" is one or more than one unless specifically defined otherwise.
In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.
Embodiment one:
referring to fig. 1-6, the multifunctional cabin opening mechanism for rocket of the present utility model includes a connection base 1, wherein a first connection portion 101 and a second connection portion 102 are respectively provided at the upper and lower ends of the connection base 1, and is characterized in that: a first powder cavity is arranged in the connecting bottom 1 near the first connecting part 101, a second powder cavity is arranged near the second connecting part 102, a cabin opening powder box 5 arranged towards the first connecting part 101 is arranged in the first powder cavity, an ignition powder box 8 arranged towards the second connecting part 102 is arranged in the second powder cavity, a security mechanism 6 for igniting the cabin opening powder box 5 is arranged between the cabin opening powder box 5 and the ignition powder box 8, the security mechanism 6 comprises a slide block seat 66, a seat cavity 103 for communicating the first powder cavity with the second powder cavity is arranged in the connecting bottom 1, a slide block seat 66 is fixedly arranged in the seat cavity 103, a radial sliding cavity 662 arranged at one end of the slide block seat 66 near the cabin opening powder box 5 and a sliding part 64 arranged in the radial sliding cavity 662 in a radial sliding manner are arranged, and the ignition part comprises a needle-punched part 66 arranged on the sliding part 64 and a needle-punched part 613 corresponding to the needle-punched part 62 arranged on the needle-punched part 66; the sliding member 64 includes an ignition position and a safety position at a position in the radial sliding chamber 662, and a slider spring 611 for driving the sliding member 64 to slide toward the ignition position is provided in the radial sliding chamber 662;
when the sliding member 64 is positioned at the ignition position, the acupuncture detonator 613 corresponds to the firing pin member 62, and when the sliding member 64 is positioned at the safety position, the acupuncture detonator 613 is staggered from the firing pin member 62;
the security mechanism 6 further comprises a limiting mechanism for locking the sliding member 64 in the safety position, the limiting mechanism being for receiving the reverse thrust of the ignition cartridge 8 to thereby release the limitation of the sliding member 64. In this embodiment, the ignition take-off and the mine throwing of the training rocket projectile are controlled respectively by setting the ignition powder box 8 and the cabin-opening powder box 5, the position of the sliding part 64 and the position of the acupuncture detonator 613 arranged on the sliding part 64 are limited by setting the limiting mechanism, the reverse thrust of the ignition powder box 8 is received to release the limit of the sliding part 64, the acupuncture detonator 613 and the firing pin part 62 can be positioned at the ignition position, the limit of the limiting mechanism can be released only after the ignition powder box 8 ignites, the cabin-opening powder box 5 can be ensured to ignite later than the ignition powder box 8, the early ignition of the cabin-opening powder box 5 is avoided, the early cabin opening is further caused, the throwing of the training projectiles such as the fire extinguishing projectile, the rainfall projectile and the mine throwing are influenced, the training effect is avoided, and the safety is higher.
Referring to fig. 2, 3 and 4, the axial limiting mechanism includes a push rod member 65, one end of the slide block 66 near the ignition cartridge 8 is provided with the push rod member 65, a push rod sliding cavity 661 adapted to the push rod member 65 is provided in the slide block 66, the push rod member 65 is axially slidably provided in the push rod sliding cavity 661, a pin body 641 disposed axially downward is provided in the sliding member 64, a pin hole 663 engaged with the pin body 641 is provided between the radial sliding cavity 662 and the push rod sliding cavity 661, a pushing portion engaged with the pin hole 663 is provided on the push rod member 65, and the sliding member 64 is located at a safe position when the pin body 641 is engaged with the pin hole 663. In the non-ignition state, the sliding component 64 is located at the safe position, the pin body 641 is spliced with the pin hole 663, when the ignition powder box 8 is ignited, the ignition powder box 8 can ignite the propellant powder in the rocket engine, the thrust back generated by the ignition powder box 8 and the propellant powder can drive the push rod component 65 to slide towards the end of the cabin-opening powder box 5, the push rod component 65 pushes up the pin body 641, the pin body 641 is separated from the pin hole 663, the limit of the sliding component 64 is released, the sliding component 64 can be immediately driven by the sliding component 611 to move to the ignition position, the needle detonator 613 corresponds to the needle component 62, and the needle component 62 can fire the needle detonator 613, so that the cabin-opening powder box 5 is ignited by the needle detonator 613, and the safety is higher.
Embodiment two:
referring to fig. 2, 3, 4 and 5, a pin cavity 664 is further provided beside the radial sliding cavity 662, a short pin 68 is slidably provided in the pin cavity 664, a ball cavity 665 is provided between the pin cavity 664 and the radial sliding cavity 662, a steel ball 69 is provided in the ball cavity 665 and is slidable along the ball cavity 665, and a clamping groove adapted to the steel ball 69 is provided on the sliding member 64; when the short pin 68 is positioned at the ball cavity 665, the steel ball 69 and the clamping groove are in an engaged position, and one end of the pin cavity 664 is provided with a second ignition head 610 for driving the short pin 68 to slide along the pin cavity 664. The steel balls 69 are matched with the clamping grooves on the side edges of the sliding parts 64 to limit the sliding parts 64 and are matched with the pin bodies 641 to limit the sliding parts 64 twice, so that the safety is higher and the controllability is higher; the sliding component 64 is in the safe position, the steel balls 69 are clamped with the clamping grooves on the side edges of the sliding component 64, so that the position of the sliding component 64 is limited, the short pin 68 is positioned at the opening of the ball cavity 665 in the safe position, the ball cavity 665 is blocked, the steel balls 69 cannot move, when the second ignition head 610 is triggered, the thrust generated by explosion of the second ignition head 610 can drive the short pin 68 to slide in the direction away from the second ignition head 610, the opening position of the ball cavity 665 is reserved, the steel balls 69 can roll into the ball cavity 665 or the pin cavity 664, the limit on the sliding component 64 is relieved, the second ignition head 610 is an electronic ignition head, the control is more convenient, the timing triggering can be selected according to requirements, and the controllability and the safety are improved.
Referring to fig. 3, the firing pin member 62 includes a pin body 621 and a first firing head 622, a firing pin slide chamber 666 communicating with the radial slide chamber 662 is provided in the slide member 64, the pin body 621 is slidably provided in the firing pin slide chamber 666, and a first firing head 622 for driving the firing pin slide chamber 666 to slide toward the radial slide chamber 662 is provided at an end of the firing pin slide chamber 666. The needle 621 is arranged at the position close to the first ignition head 622 in a daily state, and when the first ignition head 622 explodes, the impact force generated by the first ignition head 622 can drive the needle 621 to slide towards the direction of the needle detonator 613, so that the needle detonator 613 is triggered, the first ignition head 622 is an electronic ignition head, the response speed is high, and the control is convenient.
Referring to fig. 1 and 4, a booster 63 is further disposed between the cabin-opening medicine box 5 and the needle detonator 613, and when the sliding member 64 is located at the ignition position, the needle detonator 613 corresponds to the booster 63. The booster 63 is used for connecting the needle detonator 613 and the capsule-opening medicine box 5, and transmitting a fire source, the booster 63 can be ignited immediately after the needle detonator 613 is ignited, and the booster 63 can also ignite the capsule-opening medicine box 5 immediately.
Referring to fig. 1 and 4, a pressing plate 61 is disposed at the top of the sliding block seat 66, and the detonation tube 63 is fixedly disposed in the pressing plate 61.
Referring to fig. 1, a first powder chamber is provided with a powder box tray 7, the powder box tray 7 is provided with a powder placing part adapted to the capsule powder box 5, the capsule powder box 5 is arranged in the powder placing part, the bottom of the powder box tray 7 is provided with a powder box fire passing hole 71 communicated with the powder placing part, and the powder box fire passing hole 71 is arranged at a position corresponding to the explosion tube 63. The medicine box tray 7 is used for fixing the cabin-opening medicine box 5 and limiting and fixing the security mechanism 6 in the connecting bottom 1, and the medicine box tray 7 can also separate the cabin-opening medicine box 5, so that the impact force of explosion of the cabin-opening medicine box 5 can effectively act on the cabin-opening action.
Referring to fig. 1, an electronic control board 3 electrically connected to the first ignition head 622 and the second ignition head 610 is disposed in the connection base 1, and a first micro switch SW1 in control connection with the first ignition head 622 and a second micro switch SW2 in control connection with the second ignition head 610 are disposed on the electronic control board 3. Various ignition modes can be realized by controlling the first ignition head 622 and the second ignition head 610 through the electronic control board 3, including triggering ignition according to the set time: namely, the capsule is opened at regular time, the control device carries out setting and charging on the electronic capsule fuze, after setting confirmation, an ignition signal is given, the ignition cartridge 8 is ignited, the rocket engine of the rocket training projectile is ignited by the ignition cartridge 8, the ignition instant is that the ignition cartridge 8 and high-temperature high-pressure gas generated by the combustion of the rocket training projectile propellant push the push rod part 65 to move upwards, the push rod part 65 pushes up the pin body 641, the pin body 641 is separated from the pin hole 663, the limit of the pin body 641 of the sliding part 64 is released, multiple gravity overload generated by the rocket projectile flying in the process of launching can start timing of the second micro switch SW2, after timing reaches the preset time, the second micro switch SW2 controls the second ignition head 610 to start, the thrust generated by the explosion of the second ignition head 610 can drive the short pin 68 to slide in the direction away from the second ignition head 610, the opening position of the ball cavity 665 is opened, the steel balls 69 can roll into the ball cavity 665 or the pin cavity 664, limit on the sliding component 64 is relieved, after both limit on the sliding component 64 are relieved, the sliding block spring 611 can immediately drive the sliding component 64 to move to the ignition position, the needle detonator 613 corresponds to the firing pin component 62, the electronic control board 3 immediately drives the first micro switch SW1 to start timing according to preset time after triggering according to the second micro switch SW2 or starts timing under the condition of multiple gravity overload generated by the first micro switch SW1 and rocket flying, the first micro switch SW1 controls the first ignition head 622 to ignite after the time is reached, and when the first ignition head 622 explodes, the generated impact force can drive the needle 621 to slide towards the needle detonator 613, so that the needle detonator 613 is fired, the capsule box 5 is opened through the needle detonator 613 to perform cabin opening, the air action is completed, and the air timing cabin opening can be realized; the first micro switch SW1 is triggered before the rocket projectile lands for a predetermined time.
Another mode of use of this embodiment is floor triggering: namely, the capsule is opened at regular time, the control device carries out setting and charging on the electronic capsule fuze, after setting confirmation, an ignition signal is given, the ignition cartridge 8 is ignited, the rocket engine of the rocket training projectile is ignited by the ignition cartridge 8, the ignition instant is that the ignition cartridge 8 and high-temperature high-pressure gas generated by the combustion of the rocket training projectile propellant push the push rod part 65 to move upwards, the push rod part 65 pushes up the pin body 641, the pin body 641 is separated from the pin hole 663, the limit of the pin body 641 of the sliding part 64 is released, the multiple gravity overload generated by the rocket projectile flying in the process of launching can start timing by the second micro switch SW2, after timing reaches the preset time, the second micro switch SW2 controls the second ignition head 610 to start, the thrust generated by the explosion of the second ignition head 610 can drive the short pin 68 to slide far away from the second ignition head 610, the opening position of the ball cavity 665 is opened, the steel balls 69 can roll into the ball cavity 665 or the pin cavity 664, the limit on the sliding component 64 is released, after the two limit on the sliding component 64 are released, the sliding component 64 can be immediately driven by the sliding component 611 to move to the ignition position, the needle detonator 613 corresponds to the firing pin component 62, after a rocket projectile falls to the ground, the moment-generated tens or hundreds of times of gravity Ninggo causes the overload triggering of the first micro switch SW1, the first micro switch SW1 controls the first ignition head 622 to ignite, and when the first ignition head 622 explodes, the generated impact force can drive the needle 621 to slide towards the needle detonator 613, so that the needle detonator 613 is fired, and the capsule explosive box 5 is ignited by the needle detonator 613 to open the capsule, so that the capsule is triggered to fall to the ground.
The working process of the utility model comprises the following steps:
in the working process of the multifunctional cabin opening mechanism for the rocket, the cabin opening mode of the multifunctional cabin opening mechanism is divided into two modes: comprises the following steps of triggering ignition according to the set time: namely, the capsule is opened at regular time, the control device carries out setting and charging on the electronic capsule fuze, after setting confirmation, an ignition signal is given, the ignition cartridge 8 is ignited, the rocket engine of the rocket training projectile is ignited by the ignition cartridge 8, the ignition instant is that the ignition cartridge 8 and high-temperature high-pressure gas generated by the combustion of the rocket training projectile propellant push the push rod part 65 to move upwards, the push rod part 65 pushes up the pin body 641, the pin body 641 is separated from the pin hole 663, the limit of the pin body 641 of the sliding part 64 is released, multiple gravity overload generated by the rocket projectile flying in the process of launching can start timing of the second micro switch SW2, after timing reaches the preset time, the second micro switch SW2 controls the second ignition head 610 to start, the thrust generated by the explosion of the second ignition head 610 can drive the short pin 68 to slide in the direction away from the second ignition head 610, the opening position of the ball cavity 665 is opened, the steel balls 69 can roll into the ball cavity 665 or the pin cavity 664, limit on the sliding component 64 is relieved, after both limit on the sliding component 64 are relieved, the sliding block spring 611 can immediately drive the sliding component 64 to move to the ignition position, the needle detonator 613 corresponds to the firing pin component 62, the electronic control board 3 immediately drives the first micro switch SW1 to start timing according to preset time after triggering according to the second micro switch SW2 or starts timing under the condition of multiple gravity overload generated by the first micro switch SW1 and rocket flying, the first micro switch SW1 controls the first ignition head 622 to ignite after the time is reached, and when the first ignition head 622 explodes, the generated impact force can drive the needle 621 to slide towards the needle detonator 613, so that the needle detonator 613 is fired, the capsule box 5 is opened through the needle detonator 613 to perform cabin opening, the air action is completed, and the air timing cabin opening can be realized; the first micro switch SW1 is triggered before the rocket projectile lands for a predetermined time.
Another mode of use of this embodiment is floor triggering: namely, the capsule is opened at regular time, the control device carries out setting and charging on the electronic capsule fuze, after setting confirmation, an ignition signal is given, the ignition cartridge 8 is ignited, the rocket engine of the rocket training projectile is ignited by the ignition cartridge 8, the ignition instant is that the ignition cartridge 8 and high-temperature high-pressure gas generated by the combustion of the rocket training projectile propellant push the push rod part 65 to move upwards, the push rod part 65 pushes up the pin body 641, the pin body 641 is separated from the pin hole 663, the limit of the pin body 641 of the sliding part 64 is released, the multiple gravity overload generated by the rocket projectile flying in the process of launching can start timing by the second micro switch SW2, after timing reaches the preset time, the second micro switch SW2 controls the second ignition head 610 to start, the thrust generated by the explosion of the second ignition head 610 can drive the short pin 68 to slide far away from the second ignition head 610, the opening position of the ball cavity 665 is opened, the steel balls 69 can roll into the ball cavity 665 or the pin cavity 664, the limit on the sliding component 64 is released, after the two limit on the sliding component 64 are released, the sliding component 64 can be immediately driven by the sliding component 611 to move to the ignition position, the needle detonator 613 corresponds to the firing pin component 62, after a rocket projectile falls to the ground, the moment-generated tens or hundreds of times of gravity Ninggo causes the overload triggering of the first micro switch SW1, the first micro switch SW1 controls the first ignition head 622 to ignite, and when the first ignition head 622 explodes, the generated impact force can drive the needle 621 to slide towards the needle detonator 613, so that the needle detonator 613 is fired, and the capsule explosive box 5 is ignited by the needle detonator 613 to open the capsule, so that the capsule is triggered to fall to the ground.
Standard parts used in the application file can be purchased from the market, the specific connection mode of each part adopts conventional means such as mature bolts, rivets and welding in the prior art, the electric sliding rail sliding seat, the air cylinder, the welding machine, the electric telescopic rod and the internal parts of the controller all adopt conventional models in the prior art, the internal structure of the electric sliding rail sliding seat belongs to the prior art structure, a worker can complete normal operation of the electric sliding rail sliding seat according to the prior art manual, and the circuit connection adopts the conventional connection mode in the prior art, so that specific description is not made.
It should be noted that, although the foregoing embodiments have been described herein, the scope of the present utility model is not limited thereby. Therefore, based on the innovative concepts of the present utility model, alterations and modifications to the embodiments described herein, or equivalent structures or equivalent flow transformations made by the present description and drawings, apply the above technical solutions directly or indirectly to other relevant technical fields, all of which are included in the scope of protection of the present patent.
Claims (7)
1. The utility model provides a rocket is with multi-functional cabin opening mechanism, includes connecting end (1), both ends are equipped with first connecting portion (101), second connecting portion (102) respectively about connecting end (1), its characterized in that: a first powder cavity is arranged in the connecting bottom (1) near the first connecting part (101), a second powder cavity is arranged near the second connecting part (102), a cabin opening powder box (5) arranged towards the first connecting part (101) is arranged in the first powder cavity, an ignition powder box (8) arranged towards the second connecting part (102) is arranged in the second powder cavity, a security mechanism (6) for igniting the cabin opening powder box (5) is arranged between the cabin opening powder box (5) and the ignition powder box (8), the security mechanism (6) comprises a slide block seat (66), a seat cavity (103) for communicating the first powder cavity with the second powder cavity is arranged in the connecting bottom (1), a slide block seat (66) is fixedly arranged in the seat cavity (103), a radial sliding cavity (662) and a sliding part (64) which can radially slide and is arranged in the sliding part (64) and is arranged in the corresponding to the radial sliding part (662) of the ignition needle (64) are arranged at one end of the cabin opening powder box (5); the sliding part (64) comprises an ignition position and a safety position at the inner position of the radial sliding cavity (662), and a sliding block spring (611) for driving the sliding part (64) to slide towards the ignition position is arranged in the radial sliding cavity (662);
when the sliding component (64) is positioned at the ignition position, the acupuncture detonator (613) corresponds to the firing pin component (62), and when the sliding component (64) is positioned at the safety position, the acupuncture detonator (613) is staggered with the firing pin component (62);
the security mechanism (6) further comprises an axial limiting mechanism for locking the sliding component (64) at the safe position, wherein the axial limiting mechanism is used for receiving the reverse thrust of the ignition cartridge (8) so as to release the limit of the sliding component (64); the axial limiting mechanism comprises a push rod component (65), one end, close to the ignition cartridge (8), of a slide block seat (66) is provided with the push rod component (65), a push rod sliding cavity (661) matched with the push rod component (65) is arranged in the slide block seat (66), the push rod component (65) can axially slide and is arranged in the push rod sliding cavity (661), a pin body (641) which is axially downwards arranged is arranged in the sliding component (64), a pin hole (663) matched with the pin body (641) is arranged between the radial sliding cavity (662) and the push rod sliding cavity (661), a pushing part matched with the pin hole (663) is arranged on the push rod component (65), and the pin body (641) is located at a safe position when the pin hole (663) is matched with the sliding component (64).
2. A multifunctional rocket motor as recited in claim 1, wherein: a pin cavity (664) is further arranged beside the radial sliding cavity (662), a short pin (68) is slidably arranged in the pin cavity (664), a communicated ball cavity (665) is arranged between the pin cavity (664) and the radial sliding cavity (662), a steel ball (69) capable of sliding along the ball cavity (665) is arranged in the ball cavity (665), and a clamping groove matched with the steel ball (69) is formed in the sliding part (64); when the short pin (68) is positioned at the ball cavity (665), the steel ball (69) and the clamping groove are positioned at the meshing position, and one end of the pin cavity (664) is provided with a second ignition head (610) for driving the short pin (68) to slide along the pin cavity (664).
3. A multifunctional rocket motor as recited in claim 2, wherein: the firing pin component (62) comprises a pin body (621) and a first firing head (622), a firing pin sliding cavity (666) communicated with the radial sliding cavity (662) is arranged in the sliding component (64), the pin body (621) is slidably arranged in the firing pin sliding cavity (666), and the end part of the firing pin sliding cavity (666) is provided with the first firing head (622) used for driving the firing pin sliding cavity (666) to slide towards the end of the radial sliding cavity (662).
4. A multifunctional rocket motor as recited in claim 1, wherein: and a booster (63) is further arranged between the cabin-opening medicine box (5) and the needled detonator (613), and the needled detonator (613) corresponds to the booster (63) when the sliding part (64) is positioned at the ignition position.
5. A multifunctional rocket motor as recited in claim 4, wherein: the top of the sliding block seat (66) is provided with a pressing plate (61), and the detonating tube (63) is fixedly arranged in the pressing plate (61).
6. A multifunctional rocket motor as recited in claim 4, wherein: the medicine box is characterized in that a medicine box tray (7) is arranged in the first medicine cavity, a medicine placing part matched with the capsule-opening medicine box (5) is arranged on the medicine box tray (7), the capsule-opening medicine box (5) is arranged in the medicine placing part, a medicine box fire passing hole (71) communicated with the medicine placing part is formed in the bottom of the medicine box tray (7), and the medicine box fire passing hole (71) is formed in a position corresponding to the detonating tube (63).
7. A multifunctional rocket motor as recited in claim 3, wherein: an electronic control board (3) electrically connected with the first ignition head (622) and the second ignition head (610) is arranged in the connecting bottom (1), and a first micro switch SW1 in control connection with the first ignition head (622) and a second micro switch SW2 in control connection with the second ignition head (610) are arranged on the electronic control board (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211525997.3A CN115773698B (en) | 2022-12-01 | 2022-12-01 | Multifunctional cabin opening mechanism for rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211525997.3A CN115773698B (en) | 2022-12-01 | 2022-12-01 | Multifunctional cabin opening mechanism for rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115773698A CN115773698A (en) | 2023-03-10 |
| CN115773698B true CN115773698B (en) | 2023-08-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211525997.3A Active CN115773698B (en) | 2022-12-01 | 2022-12-01 | Multifunctional cabin opening mechanism for rocket |
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| CN (1) | CN115773698B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116464577B (en) * | 2023-04-26 | 2024-04-19 | 浙江省军工集团股份有限公司 | Double-combustion-chamber multipurpose turbine solid rocket engine |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1617674A (en) * | 1926-02-03 | 1927-02-15 | Dieter William | Hydrostatic mine |
| GB685981A (en) * | 1951-06-12 | 1953-01-14 | Schermuly Pistol Rocket App | Improvements in firing mechanism for pyrotechnic devices |
| IL155219A (en) * | 2003-04-03 | 2010-11-30 | Israel Military Ind | Submunition fuze |
| CN205561674U (en) * | 2016-02-02 | 2016-09-07 | 晋西工业集团有限责任公司 | Rocket dummy round of laying mines |
| CN213421970U (en) * | 2020-09-09 | 2021-06-11 | 河南北方红阳机电有限公司 | Ground-contact ignition device |
| CN112344813B (en) * | 2020-10-30 | 2022-08-05 | 湖北三江航天红林探控有限公司 | Time-delay controllable power supply mechanism and method |
| CN113587749B (en) * | 2021-07-13 | 2023-05-30 | 南京理工大学 | Safety ignition fuze adopting space explosion-proof principle |
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