CN210862400U - Aeronautical training bomb with infrared target - Google Patents
Aeronautical training bomb with infrared target Download PDFInfo
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- CN210862400U CN210862400U CN201921071038.2U CN201921071038U CN210862400U CN 210862400 U CN210862400 U CN 210862400U CN 201921071038 U CN201921071038 U CN 201921071038U CN 210862400 U CN210862400 U CN 210862400U
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Abstract
The patent discloses an aviation training bullet with infrared target, including rotor pin, projectile body, cigarette light pipe, fin, infrared target source and insurance mechanism. The rotor blade firing pin is arranged at the foremost end of the aeronautical training bomb and is connected with the bomb body through a pin shaft; the smoke tube is arranged inside the bomb body; the tail fin is welded on the conical surface of the tail part of the projectile body; the infrared target source is fixed at the tail of the projectile body through a pin shaft; one end of the safety mechanism is inserted into the rotor blade, the other end of the safety mechanism is inserted into the infrared target source, and an installation interface fixedly connected with the carrier is reserved at the other end of the safety mechanism; the outer surface of the aerobat is coated with an infrared coating. The beneficial effect of this patent is: by additionally arranging the infrared target source, the practical combat training requirement of a user all day time and especially under complex environmental conditions can be met; the all-steel design is adopted, the manufacturing precision is high, and the aerodynamic shape with stable streamline and low resistance is realized; the process is mature, the cost is low, and the method is suitable for mass production.
Description
Technical Field
The patent relates to an aviation training bullet, especially relates to an aviation training bullet of taking infrared target.
Background
Assault to the ground (sea) is the core military capability of the soldier aviation, and assault to the ground (sea) training is the important content of the soldiers aviation daily training and the main way of generating the fighting power. Under the situation background that the actual combat training is widely carried out by the current army, the ground (sea) assault training which is mainly focused on marine direction, complex environment, limit condition and night combat night training is the primary task of the actual combat training of aviation soldiers.
The training of the assault of the aviation soldier to the ground (sea) is mainly to throw the aviation training bomb and accurately obtain the bomb impact information of each bomb under different conditions, so as to evaluate the impact effect, judge the operational capability, provide improvement measures and strengthen operational construction. The aviation standard bullet that current aviation soldier army used equips the army early, and live time is long, has that the design theory falls behind, training quality is imitated not high scheduling problem, can't satisfy actual combat ization training requirement, consequently necessarily adopts brand-new technical system to research and develop novel aviation standard bullet, solves above-mentioned problem pertinence.
Disclosure of Invention
In view of the above analysis, this patent proposes an aeronautical training bullet with infrared target. The technical scheme of this patent is as follows:
an aeronautical training bomb with an infrared target comprises a rotor pin, a bomb body, a smoke tube, an empennage, an infrared target source and a safety mechanism. The method is characterized in that: the rotor blade firing pin is arranged at the foremost end of the aeronautical training bomb and is connected with the bomb body through a pin shaft; the projectile body is a main body of the aviation training projectile, the head part is in an arc shape, and the tail part is in a conical shape; the smoke tube is arranged inside the bomb body; the tail fin is welded on the conical surface of the tail part of the projectile body; the infrared target source is fixed at the tail of the projectile body through a pin shaft; one end of the safety mechanism is inserted into the rotor blade, the other end of the safety mechanism is inserted into the infrared source, and an installation interface fixedly connected with the carrier is reserved at one end of the safety mechanism; the outer surface of the aerobat is coated with an infrared coating.
Furthermore, the rotor blade includes a wind wheel, a blade seat, a blade cover, a bolt and a nut. The wind wheel is in threaded connection with the striker base, and when the wind wheel rotates, the striker base generates linear motion; the needle striking cover is connected with the rotor needle striking base through threads and is prevented from loosening through spot welding; the bolt penetrates through the center of the wind wheel, and the head of the bolt is fixedly connected with the wind wheel in a spot welding manner; the nut is screwed on the tail of the bolt and is prevented from loosening by spot welding.
Furthermore, the projectile body comprises a projectile head, a projectile body, a tail cone, a projectile ear, a central tube and concrete. The warhead is arc-shaped and is welded at one end of the warbody; the tail cone is conical and is welded at the other end of the bullet body; the bullet lug is directly welded on the bullet body; the central tube penetrates through the interior of the projectile body, one end of the central tube is fixedly connected with the warhead in a welding mode, and the other end of the central tube is fixedly connected with the tail cone in a welding mode; the concrete is poured into a cavity formed by the bullet body and the central tube.
Further, the smoke tube is a tubular smoke generating device.
Further, the tail comprises a wing and a tail ring. The number of the fins is four, and the fins are symmetrically distributed around the central axis of the tail ring; the fins and the tail wing ring are connected in a welding mode.
Further, the infrared target source is a chemical reaction type infrared source and comprises a cutting component, a chemical reaction component and an infrared radiation component.
Furthermore, the safety mechanism comprises a first safety steel bar, a second safety steel bar, a third safety steel bar and a safety steel ring. One side of the first insurance steel bar is inserted into the rotor blade firing pin, and the other side of the first insurance steel bar is connected with the insurance steel ring; one side of the second steel bar is inserted into the infrared source, and the other side of the second steel bar is connected with the steel ring; and one side of the third steel bar is connected with the steel ring, and one side of the third steel bar is provided with a mounting interface fixedly connected with the carrier.
Further, the aviation training bomb with the infrared target comprises the following working method: after the aerial carrier is thrown, the aviation training bomb is separated from the aerial carrier and falls freely, and a first insurance steel bar and a second insurance steel bar of the insurance mechanism are respectively pulled away from the interior of the rotor blade and the infrared target source. On one hand, due to the pulling-out of the steel bumper, the cutting component inside the infrared target source cuts the capsule body of the chemical reaction component, the chemical reaction is triggered, and a large amount of heat is rapidly released outwards for the ground system to capture and track; on one hand, the wind wheel starts to rotate, the striker cover (together with the striker base) moves backwards along the axial direction until the striker cover butts against the smoke light tube in the bomb body, and after the aviation training is bounced to the ground, the impact of the landing makes the striker puncture the smoke light tube to generate gray smoke, so as to assist a ground system in judging the aviation training bomb landing point.
Compared with the prior art, the beneficial effect of this patent is:
(1) the aerial training bomb with the infrared target can meet the requirements of actual combat training of users by additionally arranging an infrared target source, particularly training in marine directions, complex environments, night combat and night; (2) the aerotrain projectile is designed by adopting an all-steel system, has high manufacturing precision, stable streamline low-resistance aerodynamic shape and stable trajectory during flying; (3) the aerotrain bomb has mature process and low cost, and is suitable for mass production.
Drawings
FIG. 1 is a schematic view of an airborne training missile with an infrared target; numbering in the figures: the device comprises a rotor blade firing pin 1, a projectile body 2, a smoke light pipe 3, a tail wing 4, an infrared target source 5 and a safety mechanism 6.
FIG. 2 is an isometric view of an aerotrain projectile with an infrared target.
Detailed Description
The following detailed description of the patent refers to the accompanying drawings that form a part hereof, and in which is shown by way of illustration specific embodiments in which the patent may be practiced. It is obvious that the described embodiments are only a part of the embodiments of the patent, not all embodiments.
Referring to fig. 1 and 2, the patent provides an aeronautical training bomb with an infrared target, which comprises a rotor pin 1, a bomb body 2, a smoke tube 3, a tail fin 4, an infrared source 5, a safety mechanism 6 and the like. The rotor blade firing pin 1 is arranged at the foremost end of the aeronautical training bomb and is connected with the bomb body through a pin shaft; the projectile body 2 is a main body of a flight training projectile; the smoke tube 3 is arranged inside the bomb body; the tail fin 4 is welded on the conical surface of the tail part of the projectile body; the infrared target source 5 is fixed at the tail of the projectile body; one end of the safety mechanism 6 is inserted into the rotor blade, the other end of the safety mechanism is inserted into the infrared source, and an installation interface fixedly connected with the carrier is reserved at one end of the safety mechanism.
The rotor blade firing pin 1 comprises a wind wheel, a firing pin base, a firing pin cover, a bolt and a nut. The wind wheel is in threaded connection with the striker base, and when the wind wheel rotates windward, the striker base generates linear motion; the striking pin cover is connected with the striking pin base through threads and is prevented from loosening through spot welding; the bolt penetrates through the center of the wind wheel, and the head of the bolt is fixedly connected with the wind wheel in a spot welding manner; the nut is screwed on the tail part of the bolt and is prevented from loosening by spot welding. The combined use of the bolt and the nut plays a role in centering and limiting.
The projectile body 2 comprises a projectile head, a projectile body, a tail cone, a projectile ear, a central tube and concrete. The warhead is an assembly part and comprises a warhead ring part and a warhead column part, wherein the warhead ring part is formed by stretching a plate and then punching the center of the plate, and the warhead column part is formed by turning a bar; the warhead is circular-arc, and is welded at one end of the body of the bullet. The bullet body is formed by curling a plate and then welding seams, and the bullet body is further rolled to ensure the roundness of the bullet body after being formed. The tail cone is conical, is formed by secondary drawing of a plate and then center punching, and is welded at the other end of the bullet body. The bullet ear is drawn by the round steel and then is bent system and form, and the beading is in the bullet body, and the location is accurate and can effectively guarantee the aviation training bullet pneumatic appearance. The central tube adopts a standard tube and penetrates through the interior of the projectile body, one end of the central tube is fixedly connected with the warhead in a welding way, and the other end of the central tube is fixedly connected with the tail cone in a welding way; the concrete is poured into a cavity formed by the bullet body and the central tube, and the weight of the concrete needs to be accurately calculated.
The smoke tube 3 is a tubular smoke generating device. The rotor blade breaks down and releases a large amount of gray smoke.
The tail 4 comprises fins and a tail ring. The wing pieces are stamping parts, the outer sides of the wing pieces are flanged, and meanwhile, ruffles are pressed at the centers of the wing pieces to increase the rigidity of the wing pieces; the number of the wing pieces is four, and the wing pieces are symmetrically distributed around the central axis of the tail wing ring. The tail wing ring is made of steel plates by rolling, and the seam is welded. The wing panel and the tail wing ring adopt a welding connection mode.
The infrared target source 5 includes a cutting part, a chemical reaction part, an infrared radiation part. The cutting assembly is connected with a second steel bumper bar of the safety mechanism. The chemical reaction device comprises a nano material A and a nano material B which are respectively arranged in respective capsules. The infrared radiation member is used to radiate heat.
The safety mechanism 6 includes a first safety steel bar, a second safety steel bar, a third safety steel bar, and a safety steel ring. One side of the first insurance steel bar is inserted into the rotor blade firing pin, and the other side of the first insurance steel bar is connected with the insurance steel ring; one side of the second steel bar is inserted into the infrared source and connected with the cutting part, and the other side of the second steel bar is connected with the steel ring; one side of the third steel bar is fixedly connected with the loader, and the other side of the third steel bar is connected with the steel ring. After the flight training cartridge is separated from the carrier, the safety mechanism is still hung on the carrier.
The aerotrain projectile with the infrared target has the total weight of 50kg and the full projectile length (without a rotor blade) of 968mm, and particularly has a streamline aerodynamic shape which is strictly matched with the weight and the size. The whole body of the aeronautical training bomb is coated with a high-emissivity infrared coating so as to improve the emissivity of the whole bomb.
The patent provides an aviation training bullet with an infrared target, and the working method comprises the following steps: after the aerial carrier is thrown, the aviation training bomb is separated from the aerial carrier and falls freely, and a first insurance steel bar and a second insurance steel bar of the insurance mechanism are simultaneously pulled away from the interior of the rotor blade and the infrared source. On one hand, the second steel bumper strip drives the cutting assembly to cut a capsule body of a chemical reaction part in the infrared target source, the nano material A and the nano material B are mixed to carry out chemical reaction, and a large amount of heat is rapidly released outwards to be captured and tracked by a ground system; on one hand, the wind wheel starts to rotate, the striker moves backwards along the axial direction until the striker props against the smoke light tube in the bomb body, and after the aviation training is landed, the impact of landing makes the striker break through the smoke light tube to generate gray smoke, so as to assist a ground system in judging the aviation training bomb landing point.
The above description is given for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the present invention, but rather as the description is given by way of illustration and description of the preferred embodiments of the present invention.
Claims (7)
1. The utility model provides a take aviation training bullet of infrared target, includes rotor firing pin (1), projectile body (2), cigarette light pipe (3), fin (4), infrared target source (5) and safety mechanism (6), its characterized in that:
the rotor blade firing pin (1) is arranged at the foremost end of the aeronautical training bomb and is connected with the bomb body (2) through a pin shaft; the smoke light pipe (3) is arranged inside the bomb body; the tail wing (4) is welded on the conical surface of the tail part of the projectile body; the infrared target source (5) is fixed at the tail of the projectile body through a pin shaft; one end of the safety mechanism (6) is inserted into the rotor blade firing pin, the other end of the safety mechanism is inserted into the infrared target source, and an installation interface fixedly connected with the carrier is reserved at the other end of the safety mechanism; the outer surface of the aeronautical training bomb is coated with an infrared coating.
2. The aeronautical training cartridge with infrared target according to claim 1, characterized in that: the rotor blade firing pin (1) comprises a wind wheel, a firing pin base, a firing pin cover, a bolt and a nut; the wind wheel is in threaded connection with the striker base, and when the wind wheel rotates, the striker base generates linear motion; the striking pin cover is connected with the striking pin base through threads and is prevented from loosening through spot welding; the bolt penetrates through the center of the wind wheel, and the head of the bolt is fixedly connected with the wind wheel in a spot welding manner; the nut is screwed on the tail of the bolt and is prevented from loosening by spot welding.
3. The aeronautical training cartridge with infrared target according to claim 1, characterized in that: the projectile body (2) comprises a projectile head, a projectile body, a tail cone, a projectile lug, a central tube and concrete; the warhead is arc-shaped and is welded at one end of the warbody; the tail cone is conical and is welded at the other end of the bullet body; the bullet lug is directly welded on the bullet body; the central tube penetrates through the interior of the projectile body, one end of the central tube is fixedly connected with the warhead in a welding mode, and the other end of the central tube is fixedly connected with the tail cone in a welding mode; the concrete is poured into a cavity formed by the bullet body and the central tube.
4. The aeronautical training cartridge with infrared target according to claim 1, characterized in that: the smoke light pipe (3) is a tubular smoke generating device.
5. The aeronautical training cartridge with infrared target according to claim 1, characterized in that: the tail wing (4) comprises four wing pieces and a tail wing ring, and the four wing pieces are symmetrically distributed around the central shaft of the tail wing ring; the fins and the tail wing ring are connected in a welding mode.
6. The aeronautical training cartridge with infrared target according to claim 1, characterized in that: the infrared target source (5) is a chemical reaction type infrared source and comprises a cutting component, a chemical reaction component and an infrared radiation component.
7. The aeronautical training cartridge with infrared target according to claim 1, characterized in that: the safety mechanism (6) comprises a first safety steel bar, a second safety steel bar, a third safety steel bar and a safety steel ring; one side of the first insurance steel bar is inserted into the rotor blade firing pin, and the other side of the first insurance steel bar is connected with the insurance steel ring; one side of the second steel bar is inserted into the infrared source, and the other side of the second steel bar is connected with the steel ring; and one side of the third steel bar is connected with the steel ring, and one side of the third steel bar is provided with a mounting interface fixedly connected with the carrier.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921071038.2U CN210862400U (en) | 2019-07-10 | 2019-07-10 | Aeronautical training bomb with infrared target |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921071038.2U CN210862400U (en) | 2019-07-10 | 2019-07-10 | Aeronautical training bomb with infrared target |
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| Publication Number | Publication Date |
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| CN210862400U true CN210862400U (en) | 2020-06-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921071038.2U Active CN210862400U (en) | 2019-07-10 | 2019-07-10 | Aeronautical training bomb with infrared target |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110398185A (en) * | 2019-07-10 | 2019-11-01 | 中国科学院上海技术物理研究所 | A kind of Areonautic exercise bobm with infrared target |
-
2019
- 2019-07-10 CN CN201921071038.2U patent/CN210862400U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110398185A (en) * | 2019-07-10 | 2019-11-01 | 中国科学院上海技术物理研究所 | A kind of Areonautic exercise bobm with infrared target |
| CN110398185B (en) * | 2019-07-10 | 2023-07-04 | 中国科学院上海技术物理研究所 | Aviation training bullet with infrared target |
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