Missile approximation simulation target missile
By designing a missile approach simulation target and using a simulated combustion chamber and light source to simulate missile tail feathers, the problem of wasted infrared decoy flares in helicopter training was solved, achieving low-cost and high-efficiency training results.
Patent Information
- Application Number
- CN202520364631.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-04
- Publication Date
- 2025-12-26
- Estimated Expiration
- 2035-03-04
AI Technical Summary
In existing technologies, the use of infrared decoy flares by helicopters when facing missile threats is not precise enough, resulting in waste and a lack of training equipment, and making it impossible to effectively simulate missile approach scenarios.
Design a missile approach simulation target missile, using a simulated combustion chamber and simulated light source to simulate missile tail feathers, combined with rocket section and tail fins, launched through launch tube, simulating the missile launch process and tail feather light signals.
It achieved low-cost and high-efficiency training results. By modifying retired incendiary bombs, training costs were reduced and the level of combat realism in training was improved.
Smart Images
Figure CN223726968U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the technical field of missile defense training equipment, and particularly relates to a missile approaching simulation target projectile. BACKGROUND
[0002] At present, portable individual air defense missiles have great threat to helicopters and air-to-ground fighter aircraft, and the helicopters are all installed with infrared decoy bombs, and since the pilots cannot feel the threat of the ground missiles, they can only throw a large number of infrared decoy bombs without purpose, which causes waste of the limited number of decoy bombs. In view of this, the helicopters begin to be installed with missile approaching warning devices, and the pilots can wait until the missile approaching warning device alarms to throw a large number of decoy bombs. However, the army does not have such training equipment in daily training, and therefore, a missile approaching simulation target projectile is developed by technical personnel, which is suitable for ground launching and promotes the army's combat-oriented training. CONTENT OF THE UTILITY MODEL
[0003] In order to solve the above problems, the utility model provides a missile approaching simulation target projectile.
[0004] In order to achieve the above purpose, the utility model adopts the following technical scheme:
[0005] A missile approaching simulation target projectile, comprising a rocket part, a tail wing and a simulation combustion chamber for simulating a warhead; a simulation light source electrically connected with the rocket part is arranged in the simulation combustion chamber, for simulating the tail feather of a ground-to-air missile; the rocket part can be connected with the tail part of the simulation combustion chamber, and the tail wing is rotatably connected with the tail part of the rocket part through an elastic element; the simulation combustion chamber, the rocket part and the tail wing can be arranged in a launching barrel, for simulating the launching of a ground-to-air missile.
[0006] Further, the simulation combustion chamber comprises a simulation fuse and a hollow shell, the simulation fuse is arranged at the head of the shell, the simulation light source is arranged in the shell, for simulating the warhead of a ground-to-air missile; a light-emitting hole is arranged on the side wall of the shell, for allowing the simulation light source to radiate light outward.
[0007] Further, an external thread is arranged on the outer circle of the tail part of the simulation fuse, and an internal thread matched with the external thread is arranged on the head of the shell; the simulation light source is connected with the tail part of the simulation fuse, and the tail part of the simulation light source extends to the middle position of the shell.
[0008] Further, the two ends of the shell are conical, and the middle part is cylindrical, and the shell is sequentially divided into a conical section, a cylindrical section and a conical section from front to back; the light-emitting holes are a plurality of holes and are arranged on the cylindrical section of the shell in a spaced manner.
[0009] Further, the light-emitting holes are four rectangular holes, and the four rectangular holes are arranged in a uniformly distributed manner along the circumference of the shell.
[0010] Further, the inner cavity of the shell is sequentially divided into front combustion chamber, middle combustion chamber and rear combustion chamber from front to back, the front combustion chamber and the rear combustion chamber are correspondingly arranged in the inner part of the two end conical sections of the shell, and the middle combustion chamber is correspondingly arranged in the inner part of the cylindrical section of the shell.
[0011] Further, the simulation light source is an infrared flare tube, the spectral range of the infrared flare tube is 660nm-690nm, and the infrared light, ultraviolet light or tail smoke emitted by the ground-to-air missile engine is simulated.
[0012] Further, the elastic element is a torsion spring, and the connecting end of the tail wing is rotationally connected with the side wall of the rocket part through the torsion spring.
[0013] Further, the tail wing is six pieces and is circumferentially arranged at the tail of the rocket part.
[0014] Compared with the prior art, the technical progress achieved by the utility model lies in that:
[0015] The utility model simulates the warhead by the simulation combustion chamber with the simulation light source, simulates the tail feather of the ground-to-air missile by the simulation light source in the simulation combustion chamber, and is launched through the launching tube after the rocket part is assembled with the simulation combustion chamber and the tail wing, for simulating the launching of the ground-to-air missile. The utility model has the advantages of simple and compact structure and low cost, adopts the retired incendiary bomb for reforming, realizes the reuse of retired equipment and ammunition, reduces the training cost, and improves the training effect. BRIEF DESCRIPTION OF DRAWINGS
[0016] The drawings are used to provide further understanding of the utility model, and constitute a part of the specification, are used together with the embodiments of the utility model to explain the utility model, and do not constitute the limitation to the utility model.
[0017] In the drawings:
[0018] Figure 1 The utility model provides a structure schematic diagram of a missile approaching simulation target bomb for the embodiments of the utility model;
[0019] Figure 2 The utility model Figure 1 The structure schematic diagram of the simulation combustion chamber.
[0020] In the drawings:
[0021] 1-simulation combustion chamber, 11-simulation fuze, 12-shell, 13-light emitting hole, 14-jack; 101-front combustion chamber, 102-middle combustion chamber, 103-rear combustion chamber; 2-rocket part; 3-tail wing; 4-simulation light source. DETAILED DESCRIPTION
[0022] The following specific embodiments can be combined with each other, and the same or similar concepts or processes can not be described again in some embodiments. The embodiments of the present application will be described below with reference to the accompanying drawings.
[0023] As shown in Figure 1 A missile approach simulation target missile, comprising a rocket part 2, tail wing 3 and a simulation combustion chamber 1 for simulating warhead; the simulation combustion chamber 1 is provided with a simulation light source 4 electrically connected with the rocket part 2, for simulating the tail of the ground-to-air missile; the rocket part 2 can be connected with the tail of the simulation combustion chamber 1, the tail wing 3 is rotatably connected with the tail of the rocket part 2 through elastic element; the simulation combustion chamber 1, the rocket part 2 and the tail wing 3 can be arranged in the launching tube (not shown in the figure), for simulating the launching of the ground-to-air missile. When specifically manufactured, the simulation combustion chamber is modified from the shell of the retired combustion bomb, and after installing the simulation light source, the length, mass and center of mass are consistent with the original bomb type. After installing the simulation combustion chamber and the tail wing at both ends of the rocket part, the launching tube is put into the launching tube and ignited to realize the launching of the simulation combustion chamber and the starting of the simulation light source, which is convenient for daily training.
[0024] As a preferred structure, as shown in Figure 2 The simulation combustion chamber 1 comprises a simulation fuze 11 and a hollow shell 12, the simulation fuze 11 is arranged at the head of the shell 12, the simulation light source 4 is arranged in the shell 12, for simulating the warhead of the ground-to-air missile; the side wall of the shell 12 is provided with a light emitting hole 13 for the simulation light source 4 to radiate light outward. When installing, one end of the simulation light source 4 is fixed on the simulation fuze 11 through the jackscrew 14. After the simulation combustion chamber 1 is launched, the simulation light source 4 radiates light outward through the light emitting hole 13, which can simulate the infrared light of the portable ground-to-air missile engine tail or the portable ground-to-air missile engine tail smoke.
[0025] When specifically designed, the outer circle of the tail of the simulation fuze 11 is provided with external threads, and the head of the shell 12 is provided with internal threads matched with the external threads; the simulation light source 4 is connected with the tail of the simulation fuze 11, and the tail of the simulation light source 4 extends to the middle position of the shell 12, which facilitates the light emitted by the simulation light source to radiate out of the light emitting hole, and at the same time, the simulation light source makes the center of mass of the simulation combustion chamber the same as the mass and center of mass of the original bomb type.
[0026] Further optimization of the above structure, the two ends of the shell 12 are conical, the middle part is cylindrical, and are sequentially divided into a conical section, a cylindrical section and a conical section from front to back; the light emitting holes 13 are a plurality of and are arranged at intervals on the cylindrical section of the shell 12. Among them, the light emitting holes 13 are four rectangular holes, and the four rectangular holes are uniformly arranged along the circumference of the shell 12. When assembling, the head conical section of the shell is threadedly connected with the simulated fuze, and the tail conical section is threadedly connected with the rocket part. The shell with the structure has the same shape and weight as the original bomb type, is convenient to assemble, and can also ensure the stability of the simulated target bomb during flight.
[0027] In specific production, the inner cavity of the shell 12 is sequentially divided into a front combustion chamber 101, a middle combustion chamber 102 and a rear combustion chamber 103 from front to back, the front combustion chamber 101 and the rear combustion chamber 103 are correspondingly arranged in the inner part of the two end conical sections of the shell 12, and the middle combustion chamber 102 is correspondingly arranged in the inner part of the cylindrical section of the shell 12.
[0028] In the embodiment of the utility model, the simulation light source 4 is infrared flare, infrared flare is equipped with electric ignition head which is parallelly connected with engine ignition device, emits and electrifies to ignite, and the flame of combustion is sprayed from light emitting hole. The spectral range of the infrared flare is 660nm~690nm, and is used for simulating infrared, ultraviolet light or tail smoke which is emitted by ground-to-air missile engine. The duration of the infrared flare is 3S-5S.
[0029] When assembling, the elastic element is a torsion spring, and the connecting end of the tail fin 3 is rotatably connected with the side wall of the rocket part 2 through the torsion spring. Among them, the tail fin 3 is six pieces and is arranged at intervals in the tail part of the rocket part 2.
[0030] In the embodiment of the utility model, the rocket part 2 includes an outer shell 21 and a nozzle 22, the nozzle 22 is arranged at the lower end of the outer shell 21, rocket propellant and a solid propellant plate are arranged in the outer shell 21, the rocket propellant is arranged on the solid propellant plate, an ignition device for igniting the rocket propellant is arranged in the nozzle, the ignition device is electrically connected with the contact in the launching barrel through an electric cable, the launching barrel is wirelessly connected with the remote controller, and the ignition device is started through the remote controller. The rocket part and the launching barrel are all retired equipment, and the structure, launching principle and ignition principle thereof are all prior art, which will not be repeated here. In order to improve the training safety, the rocket part is tested and short-circuited, and the person and the bomb are separated during testing and launching.
[0031] In summary, the utility model has the advantages of simple and compact structure and low cost, can simulate portable ground-to-air missile engine tail infrared / ultraviolet light (or missile tail smoke), improve the training effect, and realize the reuse of retired equipment and ammunition by using the retired incendiary bomb for modification, thereby reducing the training cost.
[0032] It should be explained finally: the above described is only the preferred embodiment of the utility model, and is not used for limiting the utility model, although the utility model is described in detail with reference to the foregoing embodiment, for the person skilled in the art, it still can modify the technical scheme recorded in the foregoing each embodiment, or equivalent replacement is carried out to part of technical features. Any modification, equivalent replacement, improvement etc. that is made within the spirit and principle of the utility model, should be contained in the scope of protection of the utility model claim.
Claims
1. A missile approach simulation target missile, characterized in that: It includes a rocket section, a tail fin, and a simulated combustion chamber for simulating a warhead; the simulated combustion chamber is equipped with a simulated light source electrically connected to the rocket section for simulating the tail feathers of a surface-to-air missile; the rocket section can be connected to the tail of the simulated combustion chamber, and the tail fin is rotatably connected to the tail of the rocket section through an elastic element; the simulated combustion chamber, rocket section, and tail fin can be installed inside a launch tube for simulating the launch of a surface-to-air missile.
2. The missile approach simulation target missile according to claim 1, characterized in that: The simulated combustion chamber includes a simulated fuse and a hollow shell. The simulated fuse is located at the head of the shell, and the simulated light source is located inside the shell to simulate the warhead of a surface-to-air missile. The side wall of the shell is provided with light-emitting holes for the simulated light source to radiate light outward.
3. The missile approach simulation target missile according to claim 2, characterized in that: The simulated seal has an external thread on its outer circumference at the tail, and the head of the housing has an internal thread that mates with it; the simulated light source is connected to the tail of the simulated fuse, and the tail of the simulated light source extends to the middle of the housing.
4. The missile approach simulation target missile according to claim 2, characterized in that: The shell is conical at both ends and cylindrical in the middle, and is divided into conical, cylindrical and conical segments from front to back; there are multiple light-emitting holes, which are spaced apart on the cylindrical segments of the shell.
5. A missile approach simulation target missile according to claim 4, characterized in that: The light-emitting holes are four rectangular holes, which are evenly distributed along the circumference of the shell.
6. The missile approach simulation target missile according to claim 2, characterized in that: The inner cavity of the shell is divided into a front combustion chamber, a middle combustion chamber and a rear combustion chamber from front to back. The front combustion chamber and the rear combustion chamber are located inside the conical sections at both ends of the shell, and the middle combustion chamber is located inside the cylindrical section of the shell.
7. The missile approach simulation target missile according to claim 1, characterized in that: The simulated light source is an infrared tracer tube with a spectral range of 660nm to 690nm, used to simulate the infrared light, ultraviolet light, or exhaust smoke emitted by a surface-to-air missile engine.
8. The missile approach simulation target missile according to claim 1, characterized in that: The elastic element is a torsion spring, and the connecting end of the tail fin is rotatably connected to the side wall of the rocket section through the torsion spring.
9. A missile approach simulation target missile according to claim 8, characterized in that: The tail fin consists of six pieces, which are circumferentially spaced at the tail of the rocket section.