CN115773698A - Multifunctional cabin opening mechanism for rocket - Google Patents
Multifunctional cabin opening mechanism for rocket Download PDFInfo
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- CN115773698A CN115773698A CN202211525997.3A CN202211525997A CN115773698A CN 115773698 A CN115773698 A CN 115773698A CN 202211525997 A CN202211525997 A CN 202211525997A CN 115773698 A CN115773698 A CN 115773698A
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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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- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
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Abstract
The invention 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 explosive cavity is arranged in the connecting bottom close to the first connecting part, a second explosive cavity is arranged in the connecting bottom close to the second connecting part, an cabin opening explosive box arranged towards the first connecting part is arranged in the first explosive cavity, an ignition explosive box arranged towards the second connecting part is arranged in the second explosive cavity, and a security mechanism for igniting the cabin opening explosive box is arranged between the cabin opening explosive box and the ignition explosive box.
Description
Technical Field
The invention relates to the technical field of rocket training bullets, in particular to the technical field of a multifunctional cabin opening mechanism for rocket bullets.
Background
With the progress of science and technology, military facilities and civil facilities are changed greatly. Modern military has high requirements on accurate striking, which can reduce the cost on one hand and damage to innocent people on the other hand. Therefore, the remote sensing, remote measuring, navigation, guidance and internet information technology in modern technology are applied to missile launching. In modern military play, the rocket projectile for laying thunder still plays an important role, and can quickly lay a thunder field in front of the front armor cluster of an enemy. However, to achieve rapid, accurate mine laying, a more preferred mine laying rocket projectile is needed.
For example, the Chinese utility model patent with the publication number of CN205561674U discloses a mine rocket training projectile, which belongs to the technical field of projectiles and arrows. The utility model discloses a cloth thunder rocket training bullet, including hood, thunder cabin, simulation landmine, push pedal subassembly, mechanism of opening the cabin, biography fire medicine box, combustion chamber, propellant powder, spray tube anterior segment, stabilising arrangement, spray tube back end and electrically conductive lid etc.. The capsule opening mode of the training bomb is controlled by the delay fuse, the controllability of the delay fuse is poor, the time control is inconvenient, the safety is low, the capsule opening mode is easy to cause capsule opening in advance due to the fact that the capsule is burnt out in advance in the launching process, and the mine laying effect is easy to influence.
Disclosure of Invention
The invention 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 during cabin opening of the rocket and higher in safety.
In order to achieve the purpose, the invention 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 explosive cavity is arranged in the connecting bottom close to the first connecting part, a second explosive cavity is arranged in the connecting bottom close to the second connecting part, an cabin opening explosive box arranged towards the first connecting part is arranged in the first explosive cavity, an ignition explosive box arranged towards the second connecting part is arranged in the second explosive cavity, a safety mechanism used for igniting the cabin opening explosive box is arranged between the cabin opening explosive box and the ignition explosive box, the safety mechanism comprises a sliding block seat, a seat cavity communicated with the first explosive cavity and the second explosive cavity is arranged in the connecting bottom, a sliding block seat is fixedly arranged in the seat cavity, a push rod part is arranged at one end of the sliding block seat close to the ignition explosive box, a push rod sliding cavity matched with the push rod part is arranged in the sliding block seat, and a linkage control part used for igniting the ignition explosive box and receiving the push rod is further arranged in the sliding block seat.
Preferably, the linkage component comprises a sliding component, one end of the sliding block seat, which is close to the capsule opening box, is provided with a radial sliding cavity which is arranged in the radial direction, the sliding component can be arranged in the radial sliding cavity in a sliding way in the radial direction, and the ignition component comprises a needle detonator arranged on the sliding component and a firing pin component correspondingly arranged on the sliding block seat; the sliding component comprises an ignition position and a safety position in the radial sliding cavity, and a slider spring for driving the sliding component to slide towards the ignition position is arranged in the radial sliding cavity; when the sliding component is located at the ignition position, the acupuncture detonator corresponds to the firing pin component, and when the sliding component is located at the safety position, the acupuncture detonator is staggered with the firing pin component.
Preferably, the firing pin part comprises a pin body and a first ignition head, a firing pin sliding cavity communicated with the radial sliding cavity is arranged in the sliding part, 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 ignition head for driving the firing pin sliding cavity to slide towards the radial sliding cavity.
Preferably, a booster is further arranged between the capsule opening kit and the acupuncture detonator, and when the sliding component is located at the ignition position, the acupuncture detonator corresponds to the booster.
Preferably, the top of the sliding block seat is provided with a pressing plate, and the detonation tube is fixedly arranged in the pressing plate.
Preferably, a cartridge tray is arranged in the first cartridge cavity, a cartridge placing portion matched with the capsule opening portion is arranged on the cartridge tray, the capsule opening portion is arranged in the cartridge placing portion, a cartridge fire passing hole communicated with the cartridge placing portion is formed in the bottom of the cartridge tray, and the cartridge fire passing hole is formed in a position corresponding to the booster tube.
Preferably, a pin body arranged downwards in the axial direction is arranged in the sliding component, a pin hole matched with the pin body is formed between the radial sliding cavity and the push rod sliding cavity, a pushing part matched with the pin hole is arranged on the push rod component, and the sliding component is located 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 communicated with the pin cavity is arranged between the pin cavity and the radial sliding cavity, a steel ball capable of sliding along the ball cavity is arranged in the ball cavity, and a clamping groove matched with the steel ball is arranged on the sliding component; when the short pin is located at the ball cavity, the steel ball is in an engaged position with the clamping groove, 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 microswitch SW1 in control connection with the first ignition head and a second microswitch 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 invention, the ignition take-off and the throwing of the training rocket shell are respectively controlled by arranging the ignition medicine box and the opening medicine box, the position of the sliding part and the position of the acupuncture detonator arranged on the sliding part are limited by arranging the limiting mechanism, the reverse thrust of the ignition medicine box is received to relieve the limitation of the sliding part, so that 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 medicine box is ignited, the opening medicine box can be ensured to be ignited later than the ignition medicine box, the opening medicine box is prevented from being ignited too early, the early opening of the cabin is avoided, the throwing of the training shells such as the fire extinguishing shell, the rainfall shell and the cloth mine is influenced, the training effect is avoided, and the safety is higher.
The features and advantages of the present invention will be described in detail by embodiments in conjunction with the accompanying drawings.
Drawings
FIG. 1 is a front sectional view of a multifunctional cabin opening mechanism for rockets according to the present invention.
Fig. 2 isbase:Sub>A schematic view of the cross-sectional structurebase:Sub>A-base:Sub>A in fig. 1.
Fig. 3 is an enlarged structural schematic diagram of the security mechanism in fig. 2.
Fig. 4 is a schematic front sectional structure view of the security mechanism.
FIG. 5 is a schematic top view of a partial cross-sectional structure of a security mechanism.
Fig. 6 is a schematic view of the present invention when mounted on a rocket projectile.
Wherein:
1-a connecting bottom; 101-a second connection; 102-a second connection; 103-seat cavity; 3-an electronic control board; 5-opening the capsule box; 6-security mechanism; 7-cartridge tray; 8-an ignition cartridge; 61-a platen; 62-a firing pin component; 63-booster tube; 64-a sliding member; 65-a push rod member; 66-a slider seat; 68-short pin; 69-steel balls; 610-a second firing head; 611-a slider spring; 613-needling detonators; 621-needle body; 622 — first ignition head; 641-a pin body; 661-pushrod sliding chamber; 662-radial sliding chambers; 663-pin hole; 664-pin chamber; 665-ball chamber; 666-firing pin sliding chamber; 71-fire hole for medicine box.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples. It should be understood, however, that the description herein of specific embodiments is only intended to illustrate the invention and not to limit the scope of the invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
In the description of the present invention, it should be noted that when an element is referred to as being "fixed" or "disposed" to 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 invention, it should be noted that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships in which the products of the present invention are conventionally placed when used, and are merely used for convenience of describing and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. The meaning of "a number" is one or more unless specifically limited otherwise.
In the description of the present invention, it should also be noted that, unless otherwise explicitly stated or limited, 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; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in a specific case to those of ordinary skill in the art.
The first embodiment is as follows:
referring to fig. 1-6, the multifunctional cabin opening mechanism for the rocket comprises a connecting bottom 1, wherein the upper end and the lower end of the connecting bottom 1 are respectively provided with a first connecting part 101 and a second connecting part 102, and the multifunctional cabin opening mechanism for the rocket is characterized in that: a first explosive cavity is arranged in the connecting bottom 1 close to the first connecting part 101, a second explosive cavity is arranged in the connecting bottom 1 close to the second connecting part 102, a cabin opening medicine box 5 arranged towards the first connecting part 101 is arranged in the first explosive cavity, an ignition medicine box 8 arranged towards the second connecting part 102 is arranged in the second explosive cavity, a security mechanism 6 for igniting the cabin opening medicine box 5 is arranged between the cabin opening medicine box 5 and the ignition medicine box 8, the security mechanism 6 comprises a slider seat 66, a seat cavity 103 for communicating the first explosive cavity with the second explosive cavity is arranged in the connecting bottom 1, a slider seat 66 is fixedly arranged in the seat cavity 103, a radial sliding cavity 662 arranged in a radial direction and a sliding part 64 capable of sliding in the radial sliding cavity 662 are arranged at one end of the slider seat 66 close to the cabin opening medicine box 5, and the ignition part comprises a needle-punched detonator 613 arranged on the sliding part 64 and a firing needle part 62 correspondingly arranged on the slider seat 66; the position of the sliding component 64 in the radial sliding cavity 662 comprises an ignition position and a safety position, and a slider spring 611 for driving the sliding component 64 to slide towards the ignition position is arranged in the radial sliding cavity 662;
when the slide member 64 is in the ignition position, the acupuncture detonator 613 corresponds to the firing pin member 62, and when the slide member 64 is in the safety position, the acupuncture detonator 613 is offset from the firing pin member 62;
the security mechanism 6 further comprises a limiting mechanism for locking the sliding component 64 at the safe position, and the limiting mechanism is used for receiving the reverse thrust of the ignition medicine box 8 so as to release the limitation of the sliding component 64. In this embodiment, take off and shed cloth thunder through setting up the ignition of ignition medicine box 8 and division of cabin medicine box 5 control training rocket projectile respectively, inject sliding part 64 position and set up acupuncture detonator 613 position on sliding part 64 through setting up stop gear, thereby it is spacing to receive 8 thrust of ignition medicine box and remove sliding part 64, make acupuncture detonator 613 and firing pin part 62 can be in the ignition position, only can remove stop gear's spacing after the ignition of ignition medicine box 8, can guarantee that division of cabin medicine box 5 is later than ignition medicine box 8 and light, avoid opening of cabin medicine box 5 and light in the morning, thereby cause and open the cabin in advance, the influence is put out a fire the bullet, the rainfall bullet, the shed of training bullets such as cloth thunder, avoid influencing the training effect, the security is higher.
Referring to fig. 2, 3 and 4, the axial limiting mechanism includes a push rod member 65, the push rod member 65 is disposed at one end of the slider holder 66 close to the ignition medicine box 8, a push rod sliding cavity 661 adapted to the push rod member 65 is disposed in the slider holder 66, the push rod member 65 is axially slidably disposed in the push rod sliding cavity 661, a pin body 641 disposed axially downward is disposed in the sliding member 64, a pin hole 663 matched with the pin body 641 is disposed between the radial sliding cavity 662 and the push rod sliding cavity 661, a pushing portion adapted to the pin hole 663 is disposed on the push rod member 65, and when the pin body 641 is matched with the pin hole 663, the sliding member 64 is located at a safe position. In an unfired state, the sliding component 64 is positioned at a safe position, the pin body 641 is inserted into the pin hole 663, after the ignition medicine box 8 is ignited, the ignition medicine box 8 can ignite propellant in the rocket engine, the reverse thrust generated by the ignition medicine box 8 and the propellant can drive the push rod component 65 to slide towards the end of the capsule opening 5, the push rod component 65 pushes up the pin body 641 so that 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 slider spring 611 to move to an ignition position, the acupuncture detonator 613 corresponds to the firing pin component 62, the firing pin component 62 can fire the acupuncture detonator 613, and the capsule opening 5 is ignited through the acupuncture detonator 613 so as to open the capsule, so that the safety is higher.
Example 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 communicating between the pin cavity 664 and the radial sliding cavity 662 is provided, a steel ball 69 slidable along the ball cavity 665 is provided in 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 located in the ball cavity 665, the steel ball 69 is in an engagement position with the locking groove, and a second ignition head 610 for driving the short pin 68 to slide along the pin cavity 664 is arranged at one end of the pin cavity 664. The steel balls 69 are matched with the clamping grooves on the side edges of the sliding component 64 to limit the sliding component 64, and are matched with the pin bodies 641 to limit the sliding component 64 twice, so that the safety is higher, and the controllability is higher; the sliding component 64 is located at a safe position, the steel ball 69 is clamped with a clamping groove on the side of the sliding component 64, so that the position of the sliding component 64 is limited, the short pin 68 is located at an opening of the ball cavity 665 at the safe position, the ball cavity 665 is blocked, the steel ball 69 cannot move, when the second ignition head 610 is triggered, thrust generated by explosion of the second ignition head 610 can drive the short pin 68 to slide towards a direction away from the second ignition head 610, the opening position of the ball cavity 665 is released, the steel ball 69 can roll into the ball cavity 665 or the pin cavity 664, limitation on the sliding component 64 is relieved, the second ignition head 610 is an electronic ignition head, and the electronic ignition head can be controlled through an electric signal and is more convenient to control, timing triggering can be selected according to requirements, and controllability and safety are improved.
Referring to fig. 3, the firing pin part 62 includes a pin body 621 and a first ignition head 622, a firing pin sliding cavity 666 communicating with the radial sliding cavity 662 is provided in the sliding part 64, the pin body 621 is slidably provided in the firing pin sliding cavity 666, and the end of the firing pin sliding cavity 666 is provided with the first ignition head 622 for driving the firing pin sliding cavity 666 to slide towards the end of the radial sliding cavity 662. The needle body 621 sets up in the daily state and is being close to first ignition head 622 department, and when first ignition head 622 exploded, the impact force of its production can drive needle body 621 and slide to acupuncture detonator 613 direction to percussion acupuncture detonator 613, first ignition head 622 is the electron ignition head, and response speed is fast, and control is convenient.
Referring to fig. 1 and 4, a booster 63 is further disposed between the capsule opening 5 and the booster 613, and when the sliding member 64 is located at the ignition position, the booster 613 corresponds to the booster 63. The booster 63 is used for connecting the acupuncture detonator 613 and the capsule opening 5 to transfer a fire source, the booster 63 can be ignited immediately after the acupuncture detonator 613 is ignited, and the booster 63 can also be ignited immediately after the capsule opening 5 is ignited.
Referring to fig. 1 and 4, a pressure plate 61 is disposed on the top of the slider seat 66, and the detonation tube 63 is fixedly disposed in the pressure plate 61.
Referring to fig. 1, a cartridge tray 7 is arranged in the first cartridge cavity, a cartridge placing portion adapted to the capsule opening 5 is arranged on the cartridge tray 7, the capsule opening 5 is arranged in the cartridge placing portion, a cartridge fire passing hole 71 communicated with the cartridge placing portion is arranged at the bottom of the cartridge tray 7, and the cartridge fire passing hole 71 is arranged at a position corresponding to the squib 63. The medicine box tray 7 is used for fixing the box 5 for opening the cabin and fixing the safety mechanism 6 in the connecting bottom 1 in a limiting way, the medicine box tray 7 can also separate the box 5 for opening the cabin, so that the impact force generated by explosion of the box 5 for opening the cabin can be effectively acted on the action for opening the cabin.
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 connecting bottom 1, and a first microswitch SW1 controlled and connected to the first ignition head 622 and a second microswitch SW2 controlled and connected to 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 the ignition triggered according to the setting time: namely, the electronic capsule opening fuse is opened at regular time, the control device is used for installing and charging the electronic capsule opening fuse, after the installation is confirmed to be correct, an ignition signal is given, the ignition medicine box 8 is ignited, the propellant in the rocket engine of the rocket training projectile is ignited through the ignition medicine box 8, at the moment of ignition, high-temperature high-pressure gas generated by the ignition of the ignition medicine box 8 and the propellant of the training rocket projectile pushes the push rod part 65 to move upwards, the push rod part 65 jacks 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 second microswitch SW2 can start timing due to multiple gravity overload generated by the flight of the rocket projectile in the process of launching, when the timing reaches the preset time, the second microswitch 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 towards the direction far away from the second ignition head 610, and the opening position of the ball cavity 665 is opened, the steel ball 69 can roll into the ball cavity 665 or the pin cavity 664 to release the limit of the sliding component 64, after two limits of the sliding component 64 are released, the sliding block spring 611 can immediately drive the sliding component 64 to move to an ignition position, the acupuncture detonator 613 corresponds to the firing pin component 62, the electronic control board 3 immediately drives the first microswitch SW1 to start timing according to preset time after being triggered by the second microswitch SW2 or immediately drives the first microswitch SW1 to start timing under multiple gravity overload generated by rocket projectile flying, after the time is up, the first microswitch SW1 controls the first firing head 622 to ignite, when the first firing head 622 explodes, impact force generated by the first microswitch SW 621 can drive the acupuncture detonator 621 to slide towards the needle body of the acupuncture detonator 613, so that the acupuncture detonator 613 is fired, the capsule opening 5 is fired through the acupuncture detonator 613 to open the capsule, the aerial action is completed, and the aerial timed capsule opening can be realized; the first microswitch SW1 is triggered before the rocket projectile falls to the ground.
Another usage of this embodiment is triggering by landing: namely, the timing cabin opening, the control device fixes and charges the electronic cabin opening fuse, after the fixing is confirmed to be correct, an ignition signal is given, the ignition medicine box 8 is ignited, the propellant in the rocket engine of the rocket training projectile is ignited through the ignition medicine box 8, at the moment of ignition, high-temperature and high-pressure gas generated by the ignition of the ignition medicine box 8 and the propellant of the training rocket projectile pushes the push rod part 65 to move upwards, the push rod part 65 jacks 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 relieved, the second microswitch SW2 can start timing due to multiple gravity overload generated by the rocket projectile flying in the process of launching, when the timing reaches the preset time, the second microswitch 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 towards the direction far away from the second ignition head 610, the opening position of the ball cavity 665 is released, the steel ball 69 can roll into the ball cavity 665 or the pin cavity 664, the limit of the sliding component 64 is released, after the two limits of the sliding component 64 are released, the sliding component 64 can be driven by the sliding block spring 611 to move to the ignition position at once, the acupuncture detonator 613 corresponds to the firing pin component 62, after the rocket bomb falls to the ground, tens of times or hundreds of times of gravity Ninggong instantaneously generated enables the first microswitch SW1 to be overloaded and triggered, the first microswitch SW1 controls the first ignition head 622 to be ignited, when the first ignition head 622 explodes, impact force generated by the first ignition head 622 can drive the acupuncture detonator 621 to slide towards the acupuncture detonator 613, so that the acupuncture detonator needle body 613 is fired, the cabin opening medicine box 5 is ignited through the acupuncture detonator 613, and the cabin opening is triggered by falling to the ground.
The working process of the invention is as follows:
in the working process of the multifunctional cabin opening mechanism for the rocket, the cabin opening modes of the multifunctional cabin opening mechanism are divided into two types: the method comprises the following steps of triggering ignition according to a set time: namely, the timing cabin opening, the control device fixes and charges the electronic cabin opening fuse, after the fixing is confirmed to be correct, an ignition signal is given, the ignition medicine box 8 is ignited, the propellant in the rocket engine of the rocket training projectile is ignited through the ignition medicine box 8, at the moment of ignition, high-temperature and high-pressure gas generated by the ignition of the ignition medicine box 8 and the propellant of the training rocket projectile pushes the push rod part 65 to move upwards, the push rod part 65 jacks 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 relieved, the second microswitch SW2 can start timing due to multiple gravity overload generated by the flight of the rocket projectile in the launching process, when the timing reaches the preset time, the second microswitch 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 towards the direction far away from the second ignition head 610, and the opening position of the ball cavity 665 is opened, the steel ball 69 can roll into the ball cavity 665 or the pin cavity 664 to release the limit of the sliding component 64, after two limits of the sliding component 64 are released, the sliding block spring 611 can immediately drive the sliding component 64 to move to an ignition position, the acupuncture detonator 613 corresponds to the firing pin component 62, the electronic control board 3 immediately drives the first microswitch SW1 to start timing according to preset time after being triggered by the second microswitch SW2 or immediately drives the first microswitch SW1 to start timing under multiple gravity overload generated by rocket projectile flying, after the time is up, the first microswitch SW1 controls the first firing head 622 to ignite, when the first firing head 622 explodes, impact force generated by the first microswitch SW 621 can drive the acupuncture detonator 621 to slide towards the needle body of the acupuncture detonator 613, so that the acupuncture detonator 613 is fired, the capsule opening 5 is fired through the acupuncture detonator 613 to open the capsule, the aerial action is completed, and the aerial timed capsule opening can be realized; the first microswitch SW1 is triggered before the rocket projectile falls to the ground.
Another usage of this embodiment is triggering by landing: the control device sets and charges an electronic unlocking fuse, after the setting is confirmed to be correct, an ignition signal is given, the ignition medicine box 8 is ignited, propellant in a rocket engine of a rocket training projectile is ignited through the ignition medicine box 8, at the moment of ignition, high-temperature high-pressure gas generated by burning the propellant of the ignition medicine box 8 and the training rocket projectile pushes the push rod part 65 to move upwards, the push rod part 65 jacks up the pin body 641 to enable the pin body 641 to be separated from the pin hole 663, the limit of the pin body 641 of the sliding part 64 is relieved, multiple gravity overload generated by flying of the rocket projectile during launching can enable the second microswitch SW2 to start timing, after timing is finished, the second microswitch SW2 controls the second ignition head 610 to start, 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 ball cavity opening position is opened, the steel ball 69 can roll into the ball cavity 665 or pin cavity 664, the pin cavity cancels the limit of the sliding part 64, after two sliding parts of the sliding part 64 are relieved, the sliding block spring can drive the sliding block 611 to move to the sliding part 613 to enable the first ignition needle 613 to trigger the first ignition needle chamber 613, the first microswitch 64, the first ignition needle to trigger the first micro-pin 613, the first micro-pin 72 to trigger the detonator to trigger the first micro-pin 613, and trigger micro-pin of the detonator capsule 622, and trigger detonator capsule 622, and accordingly, the first micro-firing capsule 622, the first micro-pin 72 can trigger micro-pin 72 to trigger micro-pin to trigger the detonator capsule 622, and trigger the detonator capsule is triggered by the first micro-pin 613, and accordingly, and the first micro-firing capsule 622.
Standard parts used in the application document can be purchased from the market, the specific connection mode of each part adopts conventional means such as mature bolts, rivets, welding and the like in the prior art, the internal parts of the electric sliding rail sliding seat, the air cylinder, the welding machine, the electric telescopic rod and the controller all adopt conventional models in the prior art, the internal structure of the electric sliding rail sliding seat, the air cylinder, the welding machine, the electric telescopic rod and the controller belongs to the structure of the prior art, a worker can complete normal operation of the electric sliding rail sliding seat according to a manual of the prior art, the circuit connection adopts the conventional connection mode in the prior art, and specific description is not made.
It should be noted that, although the above embodiments have been described herein, the invention is not limited thereto. Therefore, based on the innovative concepts of the present invention, the technical solutions of the present invention can be directly or indirectly applied to other related technical fields by making changes and modifications to the embodiments described herein, or by using equivalent structures or equivalent processes performed in the content of the present specification and the attached drawings, which are included in the scope of the present patent.
Claims (8)
1. The utility model provides a rocket is with multi-functional mechanism of opening cabin, is including 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 explosive cavity is arranged in the connecting bottom (1) close to the first connecting part (101), a second explosive cavity is arranged in the connecting bottom (1) close to the second connecting part (102), an opening explosive box (5) arranged towards the first connecting part (101) is arranged in the first explosive cavity, an ignition explosive box (8) arranged towards the second connecting part (102) is arranged in the second explosive cavity, a safety mechanism (6) used for igniting the opening explosive box (5) is arranged between the opening explosive box (5) and the ignition explosive box (8), the safety mechanism (6) comprises a sliding block seat (66), a seat cavity (103) communicated with the first explosive cavity and the second explosive cavity is arranged in the connecting bottom (1), a sliding block seat (66) is fixedly arranged in the seat cavity (103), a radial sliding cavity (662) and a sliding component (64) which can radially slide and is arranged in the radial sliding cavity (662), the sliding component (613) is arranged on the ignition needle component (66), and the ignition needle component (66) is arranged on the corresponding to the ignition needle seat (613); the sliding component (64) comprises an ignition position and a safety position in the radial sliding cavity (662), and a slider spring (611) used for driving the sliding component (64) to slide towards the direction of the ignition position is arranged in the radial sliding cavity (662);
when the sliding member (64) is in the firing position, the needle detonator (613) corresponds to the firing pin member (62), and when the sliding member (64) is in the safety position, the needle detonator (613) is offset from the firing pin member (62);
the safety mechanism (6) further comprises a limiting mechanism for locking the sliding component (64) at the safety position, and the axial limiting mechanism is used for receiving reverse thrust of the ignition medicine box (8) so as to relieve the limitation of the sliding component (64).
2. A multi-functional rocket pod opening mechanism as recited in claim 1, further comprising: the axial limiting mechanism comprises a push rod component (65), one end, close to the ignition medicine box (8), of the slider 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 slider seat (66), the push rod component (65) can be axially and slidably arranged in the push rod sliding cavity (661), a pin body (641) arranged axially downwards 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 portion matched with the pin hole (663) is arranged on the push rod component (65), and when the pin body (641) is matched with the pin hole (663), the sliding component (64) is located at a safe position.
3. A multi-functional rocket pod opening mechanism as recited in claim 2, further comprising: 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 arranged on the sliding part (64); when the short pin (68) is located 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).
4. A multi-functional rocket pod opening mechanism as recited in claim 1, further comprising: needle beating part (62) include needle body (621) and first ignition head (622), be equipped with in sliding part (64) with the smooth chamber (666) of needle beating of radial sliding chamber (662) intercommunication, needle body (621) slidable is located in the smooth chamber (666) of needle beating, the smooth chamber (666) tip of needle beating is equipped with and is used for the drive the smooth chamber (666) of needle beating to the gliding first ignition head (622) of radial sliding chamber (662) end.
5. A multi-functional rocket pod opening mechanism as recited in claim 1, further comprising: a booster (63) is further arranged between the box opening kit (5) and the acupuncture detonator (613), and when the sliding part (64) is located at the ignition position, the acupuncture detonator (613) corresponds to the booster (63).
6. A multi-functional rocket pod opening mechanism as recited in claim 1, further comprising: 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).
7. A multi-functional mechanism for opening a rocket as recited in claim 1, wherein: the powder box is characterized in that a powder box disc (7) is arranged in the first powder cavity, a powder placing portion matched with the bin opening powder box (5) is arranged on the powder box disc (7), the bin opening powder box (5) is arranged in the powder placing portion, a powder box fire passing hole (71) communicated with the powder placing portion is formed in the bottom of the powder box disc (7), and the powder box fire passing hole (71) is formed in a position corresponding to the booster tube (63).
8. A multi-functional rocket pod opening mechanism as recited in claim 1, further comprising: the connecting bottom (1) is internally provided with an electronic control panel (3) electrically connected with the first ignition head (622) and the second ignition head (610), and the electronic control panel (3) is provided with a first microswitch SW1 connected with the first ignition head (622) in a control way and a second microswitch SW2 connected with the second ignition head (610) in a control way.
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 true CN115773698A (en) | 2023-03-10 |
| CN115773698B 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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116464577A (en) * | 2023-04-26 | 2023-07-21 | 浙江省军工集团股份有限公司 | Double-combustion-chamber multipurpose turbine solid rocket engine |
Citations (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 |
| US20050188884A1 (en) * | 2003-04-03 | 2005-09-01 | Amir Levy | 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 |
| CN112344813A (en) * | 2020-10-30 | 2021-02-09 | 湖北三江航天红林探控有限公司 | Time-delay controllable power supply mechanism and method |
| CN213421970U (en) * | 2020-09-09 | 2021-06-11 | 河南北方红阳机电有限公司 | Ground-contact ignition device |
| CN113587749A (en) * | 2021-07-13 | 2021-11-02 | 南京理工大学 | Safety ignition fuse adopting space explosion-proof principle |
-
2022
- 2022-12-01 CN CN202211525997.3A patent/CN115773698B/en active Active
Patent Citations (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 |
| US20050188884A1 (en) * | 2003-04-03 | 2005-09-01 | Amir Levy | 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 |
| CN112344813A (en) * | 2020-10-30 | 2021-02-09 | 湖北三江航天红林探控有限公司 | Time-delay controllable power supply mechanism and method |
| CN113587749A (en) * | 2021-07-13 | 2021-11-02 | 南京理工大学 | Safety ignition fuse adopting space explosion-proof principle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116464577A (en) * | 2023-04-26 | 2023-07-21 | 浙江省军工集团股份有限公司 | Double-combustion-chamber multipurpose turbine solid rocket engine |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN115773698B (en) | 2023-08-04 |
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