阅读说明：本技术 一种高速巡航式靶弹 (High-speed cruising target bomb ) 是由 李超旺 方丹 文健 施冬梅 崔平 杨岩峰 崔亮 于 2019-11-19 设计创作，主要内容包括：本发明涉及模拟靶弹技术领域,具体为一种高速巡航式靶弹,包括气动外形单元、飞行控制单元、脱离回收单元和动力单元,其中,所述脱离回收单元设置在设备箱中,脱离回收单元包括伞降装置、助推装置、定位装置、数据处理器和脱离控制器；所述伞降装置安装在设备箱的上侧,伞降装置由脱离控制器控制,所述助推装置安装在设备箱的上侧。本发明利用定位装置能够快速的缺点设备箱的位置以便于回收设备箱,定位装置为GPS卫星定位器和北斗卫星定位器,北斗卫星定位器能够在中国境内提供更为精准的定位信息,GPS卫星定位器能够在全世界范围内提供定位信息,能够节约靶弹的制造成本,且能够回收大量的实验数据。(The invention relates to the technical field of simulated target projectiles, in particular to a high-speed cruise type target projectile, which comprises a pneumatic appearance unit, a flight control unit, a separation recovery unit and a power unit, wherein the separation recovery unit is arranged in an equipment box and comprises a parachute landing device, a boosting device, a positioning device, a data processor and a separation controller; the parachute landing device is installed on the upper side of the equipment box and controlled by the separation controller, and the boosting device is installed on the upper side of the equipment box. According to the target projectile recovery device, the position of the equipment box can be quickly determined by the positioning device so as to facilitate recovery of the equipment box, the positioning device comprises a GPS (global positioning system) satellite positioner and a Beidou satellite positioner, the Beidou satellite positioner can provide more accurate positioning information in China, the GPS satellite positioner can provide positioning information in the world, the manufacturing cost of the target projectile can be saved, and a large amount of experimental data can be recovered.)

1. A high-speed cruise target projectile, comprising:

the pneumatic appearance unit comprises a nose cone (11), a projectile body (12), a skin (13), wings (14), a tail wing (15) and a tail cone (16), wherein the projectile body (12) is sequentially connected with the nose cone (11), the wings (14), the tail wing (15) and the tail cone (16), a rectangular notch is formed in the lower portion of the projectile body (12), a square connecting piece (17) is fixedly connected to the inner wall of the rectangular notch, the skin (13) is fixed to the lower portion of the connecting piece (17) through a plurality of locking points, a gunpowder bag (18) is arranged at the locking point of the skin (13) and the connecting piece (17), and an equipment box (19) is fixedly connected to the upper side of the skin (13);

the flight control unit is arranged in an equipment box (19) and comprises a power supply battery (21), a flight controller (22), a radar detector (23) and a data memory (24), wherein the radar detector is installed in a nose cone (11), the power supply battery (21), the flight controller (22) and the data memory (24) are all installed in the equipment box (19), the flight controller (22) is used for controlling a wing (14) and a tail wing (15), the radar detector (23) is used for detecting the position of an intercepted missile, and the data memory (24) is used for storing flight data in the flight controller (22) and detection information of the radar detector (23);

a detachment recovery unit provided in the equipment box (19), the detachment recovery unit including a parachute landing device (31), a boosting device (32), a positioning device (33), a data processor (34), and a detachment controller (35); the device comprises an parachute landing device (31), a boosting device (32), a data processor (34) and a separation controller (35), wherein the parachute landing device (31) is installed on the upper side of an equipment box (19), jet ports of the boosting device (32) are arranged upwards, the boosting device (32) is controlled by the separation controller (35), the positioning device (33) is used for acquiring position information of the equipment box (19), the data processor (34) is used for calculating a flight track of the boosting device and a missile intercepting flight track detected by a radar detector (23), judging whether a target missile intersects with the missile intercepting track, and if the flight track intersects with the missile intercepting flight, transmitting an electronic signal to the separation controller (35);

the power unit is powered by a solid rocket engine (41), the solid rocket engine (41) is installed at the tail of the projectile body (12), the solid rocket engine (41) is isolated from the equipment box (19) through a partition plate of the wing (14), and the head of the solid rocket engine (41) is connected with the partition plate of the wing (14).

2. A high speed cruise target projectile as claimed in claim 1, wherein: the separation and recovery unit further comprises a camera device (36), the camera device (36) is installed on the upper side of the equipment box (19), and the camera device (36) is used for shooting the projectile body (12) and transmitting the shot image to the data storage (24).

3. A high speed cruise target projectile as claimed in claim 1, wherein: the positioning device (33) is a GPS satellite positioner and a Beidou satellite positioner.

4. A high speed cruise target projectile as claimed in claim 1, wherein: the equipment box (19) comprises a box body (191), an upper cover (192) and a lock (193), wherein the box body (191) is fixedly connected with the upper cover (192) through the lock (193).

5. A high speed cruise target projectile as claimed in claim 1, wherein: the flight controller (22) adopts an ARM9+ FPGA embedded hardware circuit.

6. A high speed cruise target projectile as claimed in claim 1, wherein: the solid rocket engine (41) is a single-chamber double-thrust solid rocket engine (41), and the installation mode is end-hanging.

Technical Field

The invention relates to the technical field of simulated target bombs, in particular to a high-speed cruise type target bomb.

Background

At present, because the types of domestic target bombs are few, the target practice in the air defense weapon unit shaping test and military training mostly selects 100-2 aviation bombs, aeromodelling and the like as targets, the difference between the fighting technical indexes and the actual fighting state is large, the aim of training cannot be achieved, and the great waste in the training is caused.

The Chinese patent with the patent application number of 2014208535166 discloses a high-speed cruise target projectile for testing or training an air defense weapon unit, which consists of a pneumatic appearance unit, a flight control unit, a parachute landing unit and a power unit. After ignition and launching, a solid rocket engine of the power unit provides power for the target projectile, the pneumatic appearance unit ensures the flight state of the target projectile, the flight control unit controls the target projectile to enter a set height and a flight path for cruise flight, and in the flight process, the missile-borne data terminal can transmit the flight data of the target projectile to the ground station in real time for ground personnel to monitor and record. The target missile modifies the action and simulates a missile in actual combat, but the target missile still has the following defects: 1. the cost and the cost are high, the target missile can be recovered only under the condition that the intercepted missile is not hit, and if the intercepted missile hits the target missile, the parachute landing unit can be directly hit, so that the target missile cannot be recovered by the parachute landing unit; 2. when the flight data of the target bomb is transmitted to the ground station through the data terminal, long data delay exists, and a plurality of radar vehicles are required to be arranged on the flight path of the target bomb to serve as ground signal relay stations, so that the use is troublesome.

Disclosure of Invention

In order to overcome the defects of the target projectile in the prior art, the invention provides a high-speed cruise target projectile.

The technical problem to be solved by the invention is realized by adopting the following technical scheme:

the invention relates to a high-speed cruise target projectile, which comprises:

the pneumatic appearance unit comprises a nose cone, a projectile body, a skin, wings, an empennage and a tail cone, wherein the projectile body is sequentially connected with the nose cone, the wings, the empennage and the tail cone, a rectangular notch is formed in the lower portion of the projectile body, a square-frame-shaped connecting sheet is fixedly connected to the inner wall of the rectangular notch, the skin is fixed to the lower portion of the connecting sheet through a plurality of locking points, a gunpowder bag is arranged at the locking point of the skin and the connecting sheet, and an equipment box is fixedly connected to the upper side of the skin;

the flight control unit is arranged in the equipment box and comprises a power supply battery, a flight controller, a radar detector and a data memory, the radar detector is installed in a nose cone, the power supply battery, the flight controller and the data memory are all installed in the equipment box, the flight controller is used for controlling wings and empennages, the radar detector is used for detecting the position of an intercepted missile, and the data memory is used for storing flight data in the flight controller and detection information of the radar detector;

the separation recovery unit is arranged in the equipment box and comprises an parachute landing device, a boosting device, a positioning device, a data processor and a separation controller; the parachute landing device is arranged on the upper side of the equipment box and controlled by the separation controller, the boosting device is arranged on the upper side of the equipment box, a jet port of the boosting device is arranged upwards, the boosting device is controlled by the separation controller, the positioning device is used for acquiring position information of the equipment box, the data processor is used for calculating a flight track of the data processor and a flight track of an intercepted missile detected by the radar detector, judging whether a target missile intersects with the track of the intercepted missile, and if the flight track intersects with the flight of the intercepted missile, transmitting an electronic signal to the separation controller;

the power unit is powered by a solid rocket engine, the solid rocket engine is mounted at the tail of the projectile body, the solid rocket engine is isolated from the equipment box through a wing partition plate, and the head of the solid rocket engine is connected with the wing partition plate.

Preferably, the separation and recovery unit further comprises an image pickup device installed at an upper side of the apparatus case, the image pickup device being configured to photograph the projectile and transfer the photographed image to the data storage.

Preferably, the positioning device is a GPS satellite positioner and a Beidou satellite positioner.

Preferably, the equipment box comprises a box body, an upper cover and a lock, and the box body is fixedly connected with the upper cover through the lock.

Preferably, the flight controller adopts an ARM + FPGA embedded hardware circuit.

Preferably, the solid rocket engine is a single-chamber double-thrust solid rocket engine, and the installation mode is an end-hanging type.

Compared with the prior art, the invention has the beneficial effects that: the invention relates to a high-speed cruising type target bomb, which is characterized in that a separation recovery unit is additionally arranged, a power supply battery, a flight controller, a data memory, a parachute landing device, a boosting device, a positioning device, a data processor and a separation controller can be reserved by using an equipment box before an intercepted missile destroys the target bomb, all flight data can be reserved in the data memory, in order to shoot the process that the intercepted missile destroys the target bomb, a camera shooting device for shooting a bomb body is also arranged on the upper side of the equipment box, the camera shooting device transmits the shot image to the data memory, the separation controller controls the parachute landing device to start a parachute, so that the equipment box can safely land, meanwhile, the position of the equipment box can be quickly determined by the positioning device so as to conveniently recover the equipment box, the positioning device is a GPS (global positioning system) satellite positioner and a Beidou satellite positioner, and the Beidou satellite positioner can provide more accurate positioning information in China, the GPS satellite positioner can provide positioning information in the world, can save the manufacturing cost of target bullets, can recover a large amount of experimental data, and can be opened only by using a corresponding key in order to avoid the leakage of the experimental data because the box body of the equipment box is fixedly connected with the upper cover through a lock.

Drawings

FIG. 1 is a schematic structural diagram of a high-speed cruise target projectile according to the present invention;

FIG. 2 is a bottom view of a high speed cruise target projectile according to the present invention;

fig. 3 is a sectional view taken along line a-a of fig. 1.

In the figure:

a nose cone 11, a projectile body 12, a skin 13, wings 14, a tail wing 15, a tail cone 16, a connecting sheet 17, a gunpowder bag 18, an equipment box 19, a box body 191, an upper cover 192 and a lock 193;

a power supply battery 21, a flight controller 22, a radar detector 23, and a data memory 24;

the parachute landing device 31, the boosting device 32, the positioning device 33, the data processor 34, the separation controller 35 and the camera 36;

a solid rocket motor 41.

DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, 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. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-3, a preferred embodiment is provided as follows:

a high-speed cruise target projectile comprising:

the pneumatic appearance unit comprises a nose cone 11, a projectile body 12, a skin 13, wings 14, a tail wing 15 and a tail cone 16, wherein the projectile body 12 is sequentially connected with the nose cone 11, the wings 14, the tail wing 15 and the tail cone 16, the lower part of the projectile body 12 is provided with a rectangular notch, the inner wall of the rectangular notch is fixedly connected with a square connecting sheet 17, the skin 13 is fixed at the lower part of the connecting sheet 17 through a plurality of locking points, a gunpowder bag 18 is arranged at the locking point of the skin 13 and the connecting sheet 17, and the upper side of the skin 13 is fixedly connected with an equipment box 19;

the flight control unit is arranged in the equipment box 19 and comprises a power supply battery 21, a flight controller 22, a radar detector 23 and a data memory 24, the radar detector 23 is installed in the nose cone 11, the power supply battery 21, the flight controller 22 and the data memory 24 are all installed in the equipment box 19, the flight controller 22 adopts an ARM9+ FPGA classic embedded hardware circuit, the flight controller 22 is used for controlling the wings 14 and the empennage 15 to realize the maneuvering of the target missile and the adjustment of the flight track, the radar detector 23 is used for detecting the position of the intercepted missile so as to obtain the flight track of the intercepted missile, the data memory 24 is used for storing the flight data in the flight controller 22 and the detection information of the radar detector 23, and the power supply battery 21 supplies power to all electronic components needing power in the target missile;

a separation recovery unit which is arranged in the equipment box 19 and comprises an umbrella falling device 31, a boosting device 32, a positioning device 33, a data processor 34 and a separation controller 35; the parachute landing device 31 is installed on the upper side of the equipment box 19, the parachute landing device 31 is controlled by a separation controller 35, the boosting device 32 is installed on the upper side of the equipment box 19, a jet port of the boosting device 32 is arranged upwards, the boosting device 32 is controlled by the separation controller 35, the positioning device 33 is used for obtaining position information of the equipment box 19, the data processor 34 is used for calculating a flight track of the parachute detected by the radar detector 23 and a flight track of an intercepted missile, judging whether a target missile intersects with the track of the intercepted missile or not, if the flight track intersects with the flight of the intercepted missile, an electronic signal is transmitted to the separation controller 35, and the separation controller 35 controls the propellant package 18 through a lead;

when the device works, the data processor 34 acquires the position information of the intercepted missile through the radar detector 23, calculates the running track of the intercepted missile through the position information of the intercepted missile, compares the running track with the self flying track in the flying controller 22, judges whether the intercepted missile has a junction point, sets a threshold value in the separation recovery unit after the intercepted missile has the junction point with the self target missile, the threshold value is the distance for intercepting the missile explosion and is a fixed value, the fixed value is the time reserved for the separation recovery unit to work, when the distance for intercepting the missile and the target missile monitored by the radar enters a preset threshold value, the separation controller 35 ignites the explosive charge 18 through a lead at the moment, the explosive charge 18 generates explosion to crack the locking point of the skin 13 and the connecting sheet 17, so that the skin 13 is separated from the connecting sheet 17, the separation controller 35 controls the boosting device 32 to rapidly push the equipment box down, the boosting device 32 can be a high-pressure air booster or a rocket booster, the boosting device 32 can tear off a connecting line to completely separate the equipment box 19 from the projectile body 12, then the intercepted missile can explode, and the target projectile is destroyed through the exploded fragments, the power supply battery 21, the flight controller 22, the data memory 24, the parachute landing device 31, the boosting device 32, the positioning device 33, the data processor 34 and the separation controller 35 in the equipment box 19 can be reserved, all flight data can also be reserved in the data memory 24, in order to shoot the process of intercepting the missile and destroying the target projectile, the upper side of the equipment box 19 is also provided with a camera 36 for shooting the projectile body 12, the camera 36 transmits the shot image to the data memory 24, the separation controller 35 controls the parachute landing device 31 to start the parachute, so that the equipment box 19 can safely land, utilize simultaneously the position of shortcoming equipment box 19 that positioner 33 can be quick so that recovery plant box 19, positioner 33 is GPS satellite positioning ware and big dipper satellite positioning ware, big dipper satellite positioning ware can provide more accurate locating information in china, GPS satellite positioning ware can provide locating information in the world wide, can practice thrift the manufacturing cost of target bullet, and can retrieve a large amount of experimental data, avoid experimental data to be leaked, through tool to lock 193 fixed connection between equipment box 19's box 191 and upper cover 192, need just can open with the key that corresponds.

The power unit is powered by a solid rocket engine 41, the solid rocket engine 41 is installed at the tail of the projectile body 12, the solid rocket engine 41 is isolated from the equipment box 19 through a wing 14 partition, the head of the solid rocket engine 41 is connected with the wing 14 partition, the solid rocket engine 41 is a single-chamber double-thrust solid rocket engine 41, and the installation mode is end-hanging.

It should be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in a data store (24) and executed by a suitable instruction execution unit. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are well known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

While the invention has been described above with reference to an embodiment, various modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In particular, the various features of the embodiments disclosed herein may be used in any combination, provided that there is no structural conflict, and the combinations are not exhaustively described in this specification merely for the sake of brevity and conservation of resources. Therefore, it is intended that the invention not be limited to the particular embodiments disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.