CN111981899B - High-speed target missile for simulating air-defense missile to intercept target - Google Patents
High-speed target missile for simulating air-defense missile to intercept target Download PDFInfo
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- CN111981899B CN111981899B CN202010871379.9A CN202010871379A CN111981899B CN 111981899 B CN111981899 B CN 111981899B CN 202010871379 A CN202010871379 A CN 202010871379A CN 111981899 B CN111981899 B CN 111981899B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A33/00—Adaptations for training; Gun simulators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention discloses a high-speed target missile for simulating an anti-aircraft missile to intercept a target, which relates to the technical field of army training simulation light sources and comprises a simulation fuse part, a simulation warhead part, a simulation endurance engine, a simulation connecting part, a take-off engine, a tail wing and a spray pipe which are sequentially connected, wherein the take-off engine, the tail wing and the spray pipe are used for providing flight power to simulate the appearance of the high-speed target missile; the inside of the shell of the simulated warhead is provided with a simulated light source and an ignition device, and the simulated light source is arranged above and/or below the window; the ignition device is connected with an external launcher through a pulling mechanism; the pneumatic shell of the simulated fuse part is matched with the front end pneumatic shape of the simulated warhead part. The ignition device and the simulation light source are ignited by the pulling and sending mechanism connected with the external launching rack, infrared light and visible light emitted by the simulation light source are emitted out through a window in the middle of the shell, detection by a detection instrument is facilitated, and the effect of accurate training is achieved; meanwhile, the takeoff engine provides flight power, and stable flight is ensured by means of the tail fin and the spray pipe.
Description
Technical Field
The invention relates to the technical field of army training equipment, in particular to a high-speed target missile for simulating an air-defense missile intercepting target.
Background
At present, the high-speed target missile is few in types, strict in use environment requirement, complex in operation and high in cost, and cannot meet the requirement of large-scale training of portable air defense missiles. The existing portable air defense missile training mostly adopts a target drone. In view of cost, one target drone is high in cost, and the price is between one hundred thousand and several hundred thousand yuan; from the practical consideration, the maximum speed of the existing target drone is 150m/s, and the training requirement of the portable air defense missile on the high-speed target cannot be met at all.
The existing high-speed target projectiles are of two types: one type of the missile simulator is a target missile which rotates at a high speed, has a small volume, simulates a weaker infrared light source, is only limited to be used in the early morning or in the evening, has short flight time and is not suitable for training a portable air defense missile; the other type is an external hanging type infrared light source, only frame type emission can be adopted, the storage and turnover cost is high, and the emission operation is complicated. The two types of target missiles have high cost, certain difficulty in large-scale training and use of the portable air defense missiles and poor applicability. And the imported target bomb product not only has high purchase cost, but also has higher later use and maintenance cost.
Disclosure of Invention
The invention provides a high-speed target missile for simulating an air-defense missile to intercept a target, and aims to solve the technical problems that in the prior art, the high-speed target missile simulates an infrared light source with weak light intensity, adopts frame type launching, has overhigh target missile speed and overhigh cost, and the high-speed target missile simulates the infrared light source with weak light intensity, adopts frame type launching, has overhigh target missile speed and overhigh cost.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
a high-speed target missile for simulating an air-defense missile to intercept a target comprises a simulation fuse part, a simulation warhead part, a simulation endurance engine, a simulation connecting part, a take-off engine, a tail wing and a spray pipe which are sequentially connected, wherein the take-off engine, the tail wing and the spray pipe are used for providing flight power; the ignition device is connected with an external launcher through a pulling mechanism and is used for igniting the ignition device; the simulation fuse part is provided with a pneumatic shell suitable for flying and used for being matched with the front end pneumatic shape of the simulation warhead.
Preferably, the hair-pulling mechanism comprises a hair-pulling rope, a firing cylinder, an upper detonating cord and an upper explosion-expanding device, one end of the hair-pulling rope is connected with the launcher, the front end of the firing cylinder at the other end of the hair-pulling rope is connected, the rear end of the firing cylinder is connected with one end of the upper explosion-expanding device through the upper detonating cord, and the other end of the upper explosion-expanding device is connected with the ignition device; the impact needle cylinder, the upper detonating cord and the upper detonating extension device are all arranged in a pneumatic shell of the analog fuse part, and the lower end of the analog fuse part is movably connected with the upper end of the shell; the side wall of the needle striking cylinder is fixed in the analog fuse part through a connecting piece, and the tail end of the hair pulling rope penetrates through the side wall of the analog fuse part and is connected with an external launching rack; the lower end of the simulation fuse part is open, and the lower end of the upper detonating fuse and the upper detonating extension device penetrate through the lower end opening of the simulation fuse part and extend into the shell.
Preferably, the number of the simulation light sources is two, and the simulation light sources are respectively an infrared light source and a visible light source; the light source burning support is arranged in the shell and comprises an upper connecting sleeve, a lower connecting sleeve and more than two connecting rods, the upper end and the lower end of each connecting rod are respectively connected with the upper connecting sleeve and the lower connecting sleeve, gaps among the connecting rods correspond to the windows, and the upper connecting sleeve and the lower connecting sleeve are respectively arranged above and below the windows; the infrared light source and the visible light source are respectively arranged in the upper connecting sleeve and the lower connecting sleeve, and the charge ends of the infrared light source and the visible light source are oppositely arranged at intervals of windows; the upper end of the ignition device is connected with the hair pulling mechanism through an upper connecting sleeve, and the lower end of the ignition device is connected with the visible light source and used for igniting the visible light source.
Preferably, the top of the upper connecting sleeve is provided with a top plate, the bottom of the upper connecting sleeve is provided with an upper connecting plate, and the infrared light source is arranged between the top plate and the upper connecting plate; the top of the lower connecting sleeve is provided with a lower connecting plate, the bottom of the lower connecting sleeve is provided with a bottom plate, and the visible light source is arranged between the lower connecting plate and the bottom plate; the middle parts of the upper connecting plate and the lower connecting plate are respectively provided with a through hole for enabling the charge ends of the infrared light source and the visible light source to be oppositely arranged; the both ends of connecting rod link to each other with upper junction plate and lower connecting plate respectively, and many connecting rods set up along the edge equipartition of upper junction plate and lower connecting plate.
Preferably, the number of the connecting rods is four, and four windows are correspondingly arranged on the outer wall of the shell.
Preferably, the ignition device comprises a lower explosion expanding device, a lower detonating cord, an igniter, a medicine box and a mounting seat, the lower explosion expanding device is connected with the upper explosion expanding device, the lower explosion expanding device is connected with the igniter through the lower detonating cord, the igniter is connected with the medicine box, the lower end of the igniter extends into the medicine box, the medicine box is fixed on the mounting seat, the mounting seat is connected with a lower connecting plate, and the middle part of the mounting seat is provided with a through hole corresponding to the lower connecting plate and used for enabling the medicine charging end of the visible light source to be abutted to the medicine box; the upper end of the lower detonating cord is connected with the lower explosion expanding device through an upper connecting sleeve.
Preferably, the inner wall of the upper connecting sleeve is provided with a guide groove used for being matched with the lower detonating cord.
Preferably, a balancing weight is further arranged in the shell and fixed at the top of the lower connecting sleeve, and the balancing weight and the medicine box are respectively arranged on the upper surface and the lower surface of the lower connecting plate.
Preferably, the infrared light source is a HWY-2-60A flare and the visible light source is a Y50H flare.
Preferably, the simulation endurance engine, the simulation connecting part and the tail wing are all hollow pipe bodies; a plurality of fins are radially and uniformly distributed on the excircle of the empennage; the take-off engine is a solid rocket engine and is used for providing power for target projectile flying; three spray holes are uniformly distributed at the tail part of the spray pipe.
Adopt the produced beneficial effect of above-mentioned technical scheme to lie in: compared with the prior art, the appearance of the high-speed target projectile is simulated through the simulation fuse part, the simulation warhead part, the simulation endurance engine, the simulation connecting part, the take-off engine, the tail wing and the spray pipe which are sequentially connected, the simulation light source and the ignition device are arranged in the shell, the ignition device is ignited through the drawing mechanism connected with the external launching frame, and then the simulation light source is ignited, infrared light and visible light emitted by the simulation light source can be emitted through the window in the middle of the shell, so that the detection of a detection instrument on the ground is facilitated, and the effect of accurate training is achieved; meanwhile, the takeoff engine provides flight power, and stable flight is ensured by means of the tail fin and the spray pipe. The invention has the following beneficial effects:
(1) by means of the simulated light source capable of emitting infrared light and visible light, the light emitting intensity and duration are enhanced, and the requirements of the infrared simulated light source on the light source intensity and the light emitting intensity under the high-speed flight load condition are met;
(2) the system launching mechanism is adopted for launching, the muzzle automatic ignition function can be realized by utilizing the pulling mechanism and the ignition device, compared with the ground manual ignition, the operation is simple and convenient, the use is more convenient, and the problem of rapid small target guarantee under the actual combat condition of the air defense under the field combat condition is solved;
(3) the invention has simple and compact structure, convenient manufacture, low cost, simple and convenient operation and short preparation time, can adapt to various complex exercise environments, and has performance and practicability far higher than those of other target bombs or target drone.
Drawings
FIG. 1 is a schematic external view of a high-speed target projectile for simulating an air defense missile intercepting target according to an embodiment of the invention;
FIG. 2 is a schematic view of the installation of the hair-pulling mechanism in an embodiment of the present invention;
FIG. 3 is a schematic view of the housing of the simulated warhead of FIG. 1;
FIG. 4 is a schematic view of the internal structure of the housing of FIG. 3;
FIG. 5 is a schematic structural view of the light source burning rack of FIG. 4;
FIG. 6 is a schematic view showing the construction of an ignition device in the embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a simulated endurance engine in an embodiment of the present invention;
FIG. 8 is a schematic diagram of a simulated connection in one embodiment of the invention;
FIG. 9 is a schematic illustration of the mating of a takeoff engine and tail wing in one embodiment of the present invention;
FIG. 10 is a schematic view of the construction of a nozzle in accordance with an embodiment of the present invention;
in the figure: 1-simulating a fuse part, 2-simulating a warhead part, 3-simulating a endurance engine, 4-simulating a connecting part, 5-taking-off engine, 6-empennage and 7-spray pipe; 8-a hair-pulling mechanism, 9-a hair-pulling rope, 10-a needle cylinder, 11-an upper detonating cord, 12-an upper expanding device and 13-a window; 14-lower explosion expanding device, 15-lower detonating cord, 16-igniter, 17-medicine box, 18-mounting seat; 19-a simulated light source, 20-a top plate, 21-an upper connecting sleeve, 22-an upper connecting plate, 23-a connecting rod, 24-a lower connecting plate, 25-a balancing weight, 26-a lower connecting sleeve and 27-a bottom plate.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly and completely understood, the technical solutions in the embodiments of the present invention are described below with reference to the accompanying drawings and specific embodiments, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1 and 4, the high-speed target projectile for simulating the interception target of an air-defense missile provided by the embodiment of the invention comprises a simulation fuse part 1, a simulation warhead part 2, a simulation endurance engine 3, a simulation connecting part 4, a takeoff engine 5 for providing flight power, a tail wing 6 and a spray pipe 7 which are connected in sequence, wherein the simulation warhead part 2 comprises a shell with a light-transmitting window 13, a simulation light source 19 capable of emitting infrared light and visible light and an ignition device for igniting the simulation light source 19 are arranged in the shell, and the simulation light source 19 is arranged above and/or below the window 13; the ignition device is connected with an external launcher through a pulling mechanism 8 and is used for igniting the ignition device; the simulation fuse part 1 is provided with a pneumatic shell suitable for flying and is used for matching with the front end pneumatic shape of the simulation warhead part 2. Wherein, split type structure can be selected for use to the casing, can set up the window in the top of lower half, and threaded connection or joint structural connection are fixed can be adopted to the first half and the lower half of casing. During specific manufacturing, the abandoned explosion-killing grenades can be selected for transformation, the decommissioning equipment can be recycled, the manufacturing cost is reduced, the reliability is high, and the period is short.
In one embodiment of the present invention, as shown in fig. 2, the firing mechanism 8 includes a firing rope 9, a firing pin barrel 10, an upper detonating cord 11 and an upper explosion-expanding device 12, one end of the firing rope 9 is connected to the launcher, the other end is connected to the front end of the firing pin barrel 10, the rear end of the firing pin barrel 10 is connected to one end of the upper explosion-expanding device 12 through the upper detonating cord 11, and the other end of the upper explosion-expanding device 12 is connected to the ignition device; the needle striking cylinder 10, the upper detonating cord 11 and the upper detonation expanding device 12 are all arranged in a pneumatic shell of the simulation fuse part 1, and the lower end of the simulation fuse part 1 is movably connected with the upper end of a shell of the simulation warhead part 2; the side wall of the needle striking cylinder 10 is fixed in the analog fuse part 1 through a connecting piece, and the tail end of the hair pulling rope 9 penetrates through the side wall of the analog fuse part 1 to be connected with an external launching frame; the lower end of the analog fuse part 1 is open, and the lower end of the upper detonating cord 11 and the upper detonating extension device 12 penetrate through the lower end opening of the analog fuse part 1 and extend into the shell of the analog warhead 2. After the target projectile is launched, the launching rope is drawn by the launching rack, and can drive the detonation transfer series actions of the needle striking cylinder, the upper detonating cord and the upper detonating device, so that the ignition device is detonated, and the target projectile can be automatically ignited at the projectile outlet.
The combined type pulling and firing mechanism can connect the pulling and firing rope with the standard launcher, completes the automatic pulling and firing ignition of the pulling and firing mechanism at the gun outlet through the motion of the target projectile after firing, and has the advantages of small volume, high reliability, simple and convenient assembly, high productivity and low manufacturing cost. Simulation fuse portion also can be with the preparation of the abandonment ammunition fuse of removing the powder charge, will draw and send out the mechanism setting in the simulation fuse, at the cylindric space of simulation fuse internal design, conveniently will draw and send out the mechanism and pack into in the cylindric space to install the screw additional in the lateral wall symmetry of simulation fuse, with the locating hole cooperation on the firing pin section of thick bamboo lateral wall, realize drawing and send out the cooperation installation of mechanism in simulation fuse portion.
In one embodiment of the present invention, as shown in fig. 4 and 5, there are two analog light sources 19, which are an infrared light source and a visible light source; a light source burning support is arranged in the shell and comprises an upper connecting sleeve 21, a lower connecting sleeve 26 and more than two connecting rods 23, the upper end and the lower end of each connecting rod 23 are respectively connected with the upper connecting sleeve 21 and the lower connecting sleeve 26, a gap between the connecting rods 23 corresponds to the window 13, and the upper connecting sleeve 221 and the lower connecting sleeve 26 are respectively arranged above and below the window 13; the infrared light source and the visible light source are respectively arranged in the upper connecting sleeve 21 and the lower connecting sleeve 26, and the charge ends of the infrared light source and the visible light source are oppositely arranged at intervals of the window 13; the upper end of the ignition device is connected with the drawing mechanism 8 through an upper connecting sleeve 21, and the lower end of the ignition device is connected with the visible light source and used for igniting the visible light source. The infrared light source is HWY-2-60A tracing pipe, and the visible light source is Y50H tracing pipe. After the ignition device is ignited by the pulling mechanism, the visible light source is ignited firstly, and the combustion brightness of the visible light source can be radiated out from the window; subsequently, the flame of the visible light source ignites the charge end of the infrared light source, infrared light emitted by the infrared light source is radiated out from the window, the infrared light source and the visible light source are installed in the simulated warhead, a standard emission mechanism can be adopted, the operation is simple and convenient in transferring and emission, and the practicability is high. The structure has two light sources of infrared light and visible light, and is high in luminous intensity, practical and reliable.
Specifically, when manufacturing the light source burning bracket, as shown in fig. 4 and 5, the top of the upper connecting sleeve 21 is provided with a top plate 20, the bottom is provided with an upper connecting plate 22, and the infrared light source is arranged between the top plate 20 and the upper connecting plate 22; the top of the lower connecting sleeve 26 is provided with a lower connecting plate 24, the bottom of the lower connecting sleeve is provided with a bottom plate 27, and the visible light source is arranged between the lower connecting plate 24 and the bottom plate 27; the middle parts of the upper connecting plate 22 and the lower connecting plate 24 are respectively provided with a through hole for enabling the charge ends of the infrared light source and the visible light source to be oppositely arranged; the both ends of connecting rod 23 link to each other with upper junction plate 22 and lower connecting plate 24 respectively, and many connecting rods 23 set up along the edge equipartition of upper junction plate 22 with lower connecting plate 24. Both ends of the connecting rod 23 are respectively provided with threads, and the connecting rod is fixed by nuts after penetrating through the upper connecting plate 22 and the lower connecting plate 24. And the infrared light source for simulation and the visible light source are respectively arranged in the upper connecting sleeve and the lower connecting sleeve to be matched and fixed. The visible light source and the infrared light source are adopted to emit light together, the brightness intensity is high, the visible light can reach 5 kilometers, the duration is long, and the infrared and visible light sources are provided, so that the infrared and visible light source is practical and reliable.
In one embodiment of the present invention, as shown in fig. 5, the number of the connecting rods 23 is four, and four windows 13 are correspondingly formed on the outer wall of the case of the simulated warhead. The window is symmetrically arranged along the circumference of the side wall of the shell, and the side edge of the window is connected with the outer wall of the shell. This structural design can guarantee that structure uniformity and casing are at the intensity of high overload, and light source intensity is high, ensures 5 kilometers and visualizes, and simple structure is with low costs, and is compatible with standard transmission platform.
In one embodiment of the present invention, as shown in fig. 4 and 6, the ignition device includes a lower explosion expanding device 14, a lower explosion-conducting wire 15, an igniter 16, a medicine box 17 and a mounting seat 18, the lower explosion expanding device 14 is connected to the upper explosion expanding device 12, the lower explosion expanding device 14 is connected to the igniter 16 through the lower explosion-conducting wire 15, the igniter 16 is connected to the medicine box 17, and the lower end of the igniter extends into the medicine box 17, the medicine box 17 is fixed on the mounting seat 18, the mounting seat 18 is connected to a lower connecting plate 24, a through hole corresponding to the lower connecting plate 24 is provided in the middle of the mounting seat 18 for enabling the medicine charging end of the visible light source to abut against the medicine box 17; the upper end of the lower detonating cord 15 is connected with the lower detonating device 14 through an upper connecting sleeve 21. The middle part of the medicine box is provided with a threaded hole, and the lower end of the ignition tool is in threaded connection with the threaded hole in the middle part of the medicine box. After the ignition mechanism is ignited, the lower explosion expanding device, the lower detonating cord, the igniter and the medicine box are sequentially ignited from top to bottom, and then the visible light source in the lower connecting sleeve is ignited; then the visible light source ignites the infrared light source to form the automatic ignition system of the simulation light source.
Further optimizing the above technical solution, as shown in fig. 4, the inner wall of the upper connecting sleeve 21 is provided with a guide groove for matching with the lower detonating cord 15. Wherein, the guide way also can be designed on the outer wall of the upper connecting sleeve. With the structure, the ignition devices are respectively installed, and rapid assembly can be realized.
In an embodiment of the present invention, as shown in fig. 4, a weight 25 is further disposed in the housing, the weight 25 is fixed to the top of the lower connection sleeve 26, and the weight 25 and the medicine box 17 are disposed on the upper surface and the lower surface of the lower connection plate 24, respectively. During the concrete preparation, can weld the balancing weight suit on the outer wall of lower adapter sleeve, also can welded fastening at the top of lower adapter sleeve.
As shown in fig. 7 and 8, during specific manufacturing, the simulation endurance engine, the simulation connecting part and the tail fin are all designed into hollow pipe bodies, so that the overall weight of the target projectile can be reduced; the take-off engine is a solid rocket engine and is used for providing power for target projectile flying; as shown in fig. 9, a plurality of fins are radially and uniformly distributed on the outer circle of the tail wing 6 to ensure the stability in the flight process; as shown in fig. 10, three spray holes are uniformly distributed at the tail part of the spray pipe 7, and the initial speed of the target when the target is shot out of the muzzle can be ensured by adopting the design of the 3-hole spray pipe, so that the requirement of the troops on exercise training can be met.
In addition, the simulation fuze 1 is preferably designed by an arrow-4 fuze modification, is a 122mm I-type detonation-killing grenade original-matched fuze and is connected with the simulation warhead 2 through threads; the simulated warhead 2 and the simulated endurance engine 3 are screwed together through threads; the simulated endurance engine 3, the simulated connecting part 4 and the takeoff engine 5 are connected in turn through threads; the takeoff engine 5, the tail wing 6 and the spray pipe 7 are sequentially screwed together through threads. The structure is simple and convenient to operate and easy to assemble, and completely meets the speed requirement of the portable air defense missile on the target. Meanwhile, the target projectile can be integrally lengthened, the flight trajectory is stabilized, the bearing capacity is high, the aerodynamic appearance is good, the structure is simple, the material is single, the assembly workload is small, and the cost is low.
The working principle of the invention is as follows: the high-speed target projectile is designed into a scheme of a single-stage solid rocket engine and a built-in simulation light source, the solid rocket engine is in a boosting stage, the working time is short, the solid rocket engine is mainly used for providing kinetic energy (ascending section) for target projectile flight, the simulation light source is automatically ignited through a drawing mechanism and an ignition device when the boosting stage works, then stable flight (level flight section) is realized through the self structure of the target projectile, the target projectile descends (descending section) under the action of gravity until falling to the ground, and the simulation light source is extinguished. The target bomb mainly meets the corresponding tactical exercise requirements in a plane flight section and a descending section. The flying speed of the high-speed target projectile is 200-300 m/s, the flying speed is 200-1500 m, the reliability is about 0.85, the design of the built-in simulation light source is larger than that of the existing target projectile, the light intensity of the simulation light source is high, the system transportation and emission system is adopted for emission and transportation, the operation is simple and convenient, the high-speed target projectile can adapt to various exercise complex environments, and the performance and the practicability are far higher than those of other domestic target projectiles or target drone. The target bomb can be reformed by using an I type detonation grenade with the retired 122mm, is not influenced by factors such as foreign export restriction and the like, and has high reliability, short period and low cost.
The specific working process of the invention is as follows:
the launching rope is hung on the launching cradle in advance, and when the launching is carried out, the take-off engine starts to provide power for the target projectile to fly; the pulling force produced by the movement of the target bomb pulls the firing pin in the firing cylinder to fire the fire cap, the upper detonating cord is ignited, the upper detonating device of the upper detonating cord ignites the lower detonating cord and the lower detonating cord, the lower detonating cord ignites the igniter, the igniter ignites the medicine box again, thereby igniting the visible light source, and then the infrared light source with residual heat completes the automatic ignition of the infrared simulation light source during the firing. The invention completely breaks away from the operation of manual ignition, realizes full-automatic ignition, adopts a standard launching platform, has simple and convenient transportation and launching operation and short time consumption, and can meet the requirements of rapidness and diversification of troops.
The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (9)
1. A high-speed target missile for simulating an air defense missile to intercept a target is characterized in that: the aircraft comprises a simulation fuse part, a simulation warhead part, a simulation endurance engine, a simulation connecting part, a take-off engine for providing flight power, a tail wing and a spray pipe which are sequentially connected, wherein the simulation warhead part comprises a shell with a light-transmitting window, a simulation light source capable of emitting infrared light and visible light and an ignition device for igniting the simulation light source are arranged in the shell, and the simulation light source is arranged above and/or below the window; the ignition device is connected with an external launcher through a pulling mechanism and is used for igniting the ignition device; the simulation fuse part is provided with a pneumatic shell suitable for flying and is used for matching with the front end pneumatic shape of the simulation warhead; the hair-pulling mechanism comprises a hair-pulling rope, a needle striking cylinder, an upper detonating cord and an upper explosion expanding device, one end of the hair-pulling rope is connected with the launcher, the front end of the needle striking cylinder at the other end of the hair-pulling rope is connected, the rear end of the needle striking cylinder is connected with one end of the upper explosion expanding device through the upper detonating cord, and the other end of the upper explosion expanding device is connected with the ignition device; the impact needle cylinder, the upper detonating cord and the upper detonating extension device are all arranged in the simulation fuse part, and the lower end of the simulation fuse part is movably connected with the upper end of the shell; the side wall of the needle striking cylinder is fixed in the analog fuse part through a connecting piece, and the tail end of the hair pulling rope penetrates through the side wall of the analog fuse part and is connected with an external launching rack; the lower end of the simulation fuse part is open, and the lower end of the upper detonating fuse and the upper detonating extension device penetrate through the lower end opening of the simulation fuse part and extend into the shell.
2. The high-speed target projectile for simulating an air defense missile interception target according to claim 1, wherein: the number of the simulation light sources is two, and the simulation light sources are respectively an infrared light source and a visible light source; the light source burning support is arranged in the shell and comprises an upper connecting sleeve, a lower connecting sleeve and more than two connecting rods, the upper end and the lower end of each connecting rod are respectively connected with the upper connecting sleeve and the lower connecting sleeve, gaps among the connecting rods correspond to the windows, and the upper connecting sleeve and the lower connecting sleeve are respectively arranged above and below the windows; the infrared light source and the visible light source are respectively arranged in the upper connecting sleeve and the lower connecting sleeve, and the charge ends of the infrared light source and the visible light source are oppositely arranged at intervals of windows; the upper end of the ignition device is connected with the drawing mechanism through an upper connecting sleeve, and the lower end of the ignition device is connected with the visible light source and used for igniting the visible light source.
3. The high-speed target projectile for simulating an air defense missile interception target according to claim 2, wherein: the top of the upper connecting sleeve is provided with a top plate, the bottom of the upper connecting sleeve is provided with an upper connecting plate, and the infrared light source is arranged between the top plate and the upper connecting plate; the top of the lower connecting sleeve is provided with a lower connecting plate, the bottom of the lower connecting sleeve is provided with a bottom plate, and the visible light source is arranged between the lower connecting plate and the bottom plate; the middle parts of the upper connecting plate and the lower connecting plate are respectively provided with a through hole for enabling the charge ends of the infrared light source and the visible light source to be oppositely arranged; the both ends of connecting rod link to each other with upper junction plate and lower connecting plate respectively, and many connecting rods set up along the edge equipartition of upper junction plate and lower connecting plate.
4. The high-speed target projectile for simulating an air defense missile interception target according to claim 2, wherein: the connecting rods are four, and four windows are correspondingly arranged on the outer wall of the shell.
5. The high-speed target projectile for simulating an air defense missile interception target according to claim 3, wherein: the ignition device comprises a lower explosion expanding device, a lower detonating cord, an igniter, a medicine box and a mounting seat, the lower explosion expanding device is connected with the upper explosion expanding device, the lower explosion expanding device is connected with the igniter through the lower detonating cord, the igniter is connected with the medicine box, the lower end of the igniter extends into the medicine box, the medicine box is fixed on the mounting seat, the mounting seat is connected with a lower connecting plate, and the middle part of the mounting seat is provided with a through hole corresponding to the lower connecting plate and used for enabling a medicine charging end of the visible light source to be abutted against the medicine box; the upper end of the lower detonating cord is connected with the lower explosion expanding device through an upper connecting sleeve.
6. The high-speed target projectile for simulating an air defense missile interception target according to claim 5, wherein: and the inner wall of the upper connecting sleeve is provided with a guide groove matched with the lower detonating cord.
7. The high-speed target projectile for simulating an air defense missile interception target according to claim 2, wherein: the casing is also internally provided with a balancing weight which is fixed at the top of the lower connecting sleeve, and the balancing weight and the medicine box are respectively arranged on the upper surface and the lower surface of the lower connecting plate.
8. The high-speed target projectile for simulating an air defense missile interception target according to claim 2, wherein: the infrared light source is HWY-2-60A flare and the visible light source is Y50H flare.
9. The high-speed target projectile for simulating air defense missile interception targets according to any one of claims 1 to 8, wherein: the simulation endurance engine, the simulation connecting part and the tail wing are all hollow pipe bodies; a plurality of fins are radially and uniformly distributed on the excircle of the empennage; the take-off engine is a solid rocket engine and is used for providing power for target projectile flying; three spray holes are uniformly distributed at the tail part of the spray pipe.
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| CN102155878A (en) * | 2010-12-20 | 2011-08-17 | 吉林保利科技中试有限公司 | 130 mm PL59A type base bleed and rocket composite range-enhanced high explosive projectile of howitzer |
| CN202013147U (en) * | 2011-05-05 | 2011-10-19 | 吉林保利科技中试有限公司 | 130mm rocket target missile |
| CN107529370B (en) * | 2011-03-31 | 2014-04-30 | 北京理工大学 | A kind of extreme low-altitude supersonic cruise target missile |
| CN111727791A (en) * | 2020-07-20 | 2020-10-02 | 成都信息工程大学 | Weather modification catalytic operation device and control system and control method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102155878A (en) * | 2010-12-20 | 2011-08-17 | 吉林保利科技中试有限公司 | 130 mm PL59A type base bleed and rocket composite range-enhanced high explosive projectile of howitzer |
| CN107529370B (en) * | 2011-03-31 | 2014-04-30 | 北京理工大学 | A kind of extreme low-altitude supersonic cruise target missile |
| CN202013147U (en) * | 2011-05-05 | 2011-10-19 | 吉林保利科技中试有限公司 | 130mm rocket target missile |
| CN111727791A (en) * | 2020-07-20 | 2020-10-02 | 成都信息工程大学 | Weather modification catalytic operation device and control system and control method thereof |
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