CN2708232Y - Simulation cruise missile target drone - Google Patents
Simulation cruise missile target drone Download PDFInfo
- Publication number
- CN2708232Y CN2708232Y CN 200420032097 CN200420032097U CN2708232Y CN 2708232 Y CN2708232 Y CN 2708232Y CN 200420032097 CN200420032097 CN 200420032097 CN 200420032097 U CN200420032097 U CN 200420032097U CN 2708232 Y CN2708232 Y CN 2708232Y
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- target
- control circuit
- cruise missile
- emulation
- parachute
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- Expired - Fee Related
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Abstract
The utility model provides a simulation cruise missile target drone, comprising a simulation missile-shaped casing. The casing is provided with wings, and the wings are provided with steering engines. The inner part of a dynamic force warehouse on the back part of the casing is provided with a rocket motor. The middle part of the casing is provided with a parachute warehouse. The inner part of an equipment warehouse on the front part of the casing is provided with a gyro gps signal receiver and a control circuit board. The control circuit is connected with the steering engines; when the gyro sends out deviation signal, the control circuit can put out regulating signal to the steering engine. A parachute warehouse cover opening circuit is also arranged in the control circuit. The utility model can be ignite and emitted on a launching shoe; the simulation cruise missile target drone can fly towards a predetermined training and guidance area after be emitted, so the simulation cruise missile target drone can be used in air training center. As the simulation cruise missile target drone is provided with the rocket motor, the flying speed is high and the airborne period is long. The flying direction of the simulation cruise missile target drone can be regulated during flight in order to fly towards the predetermined training and guidance area. If the simulation cruise missile target drone is not hit in the training and guidance area, an elastic hook between a parachute warehouse cover and the casing can be detached, in order the make the parachute warehouse cover open and release a parachute. The simulation cruise missile target drone can be recovered and reused safely.
Description
Technical field
The utility model relate to a kind of in military training for ground-to-air missile, but the drone of for target practice analog simulation cruise missile of antiaircraft gun and air-to-air missile, but particularly a kind of engine of drone, flight control assemblies and target retracting device.
Background technology
In military training, present for target practice target selects for use navigate bright bullet or model plane of 100-2 to make target sometimes, this target with compare under battle conditions, authenticity differs greatly, and does not only reach the purpose of training, also causes the significant wastage in the training.Chinese patent ZL 99 2 05920.8 discloses a kind of bullet target for the air-to-air missile attack, and this bullet target has the housing of imitative guided missile shape, and wing is arranged on the housing.During training, be suspended on by special-purpose beam on the universal externally hung beam of aircraft, with aircraft the bullet target that hangs taken to and instruct the spatial domain, cast the bullet target playing target, then aircraft at once heavy grade break off backward and instruct the spatial domain, play target and supply air-to-air missile to impact.This bullet target has following deficiency: 1. playing target does not have engine, and flying speed is little, and airborne period is short, plays target and can only keep 2～3 minutes airborne period aloft, the training of practicing shooting of unfavorable all kinds of antiaircraft weapons; 2. Fei Hang bullet target does not have the heading control device, in short airborne period, as meets unfavorable air-flow, plays target and departs from heading, and influence is practiced shooting; 3. playing target does not have retracting device, and the bullet target that is not hit is the landing crash voluntarily, can not recycling.
Summary of the invention
The purpose of this utility model is in order to overcome above-mentioned deficiency, and it is bigger to propose a kind of flying speed, and airborne period is longer, can control heading, emulation cruise missile target that can recycling.
The utility model is realized with the following method.
Emulation cruise missile target has the housing of imitative guided missile shape, wing is arranged on the housing, the steering wheel that is connected with stepper motor is arranged on the wing, dynamic storehouse, rear portion in the housing, engine is arranged in the power bin, engine is a rocket engine, there is the umbrella storehouse at the housing middle part, umbrella has parachute in the storehouse, parachute hangs on the focus point of emulation cruise missile target, umbrella Cang Gai is arranged at top, umbrella storehouse, flexible hook between umbrella Cang Gai and housing, there is the electrical fuze bomb on the elastic hook side, after the electrical fuze bomb is ignited, umbrella Cang Gai breaks off relations, allow umbrella Cang Gai open, emit parachute, on the emulation cruise missile target target situation sensors is arranged, there is equipment compartment the front portion of housing, the heading control device is arranged in the equipment compartment, the heading control device has gyroscope, gps signal receiver, height inductive head and control circuit board, control circuit is arranged on the control circuit board, control circuit has input and output, gyroscope, gps signal receiver, the output of height inductive head links to each other with the input of control circuit, the output of control circuit links to each other with the stepper motor of steering wheel respectively, at gyroscope, gps signal receiver, the height inductive head is when control circuit input deviation signal, control circuit can be to the steering wheel output regulation signal, in the control circuit, also has umbrella storehouse lid open circuit, the output of target situation sensors links to each other with the input of storehouse lid open circuit, the output of umbrella storehouse lid open circuit links to each other with the lead-in wire of electrical fuze bomb, and storehouse lid open circuit is received exportable detonator signal behind the input signal of target situation sensors, gyroscope in addition in the equipment compartment, gps signal receiver, the height inductive head, the power supply of control circuit and steering wheel stepper motor.
The utility model emission of can on launcher, lighting a fire, after the emission, the utility model flies to predetermined training guidance region direction under the promotion of rocket engine, behind the arrival training guidance zone, available all kinds of antiaircraft weapon aiming is smashed, and is used to check all kinds of antiaircraft weapon target practice usefulness.The utility model is owing to there is rocket engine, and the speed of flight is big, and airborne period is longer; The utility model is owing to there is the heading control device, before flight, predeterminable mission program, when flight, when the utility model departs from heading because of airflow influence, the heading control device can be adjusted heading in real time, and the utility model is kept to predetermined training guidance region direction flight; If the utility model is not hit in the training guidance zone, lid open circuit exportable detonator signal in storehouse is ignited the electrical fuze bomb, and the elastic hook between Cang Gai and housing is thrown off, and allows umbrella Cang Gai open, and emits parachute, and the utility model can be reclaimed by safety.
Below in conjunction with accompanying drawing, the utility model is further described.
Description of drawings
Fig. 1 be the angle between the axis of the axis of engine and emulation cruise missile target be 6 ° 3 ' the main cross-sectional schematic of emulation cruise missile target;
Fig. 2 is the I place enlarged diagram of Fig. 1;
Fig. 3 is the main cross-sectional schematic of the emulation cruise missile target of axis on same straight line of the axis of engine and emulation cruise missile target.
The specific embodiment
Fig. 1, among Fig. 2, emulation cruise missile target has the housing 1 of imitative guided missile shape, wing 2 is arranged on the housing, the steering wheel 3 that is connected with stepper motor is arranged on the wing, dynamic storehouse 4, rear portion in the housing, engine 5 is arranged in the power bin, engine is a rocket engine, rocket engine is propellant and the graphite jet pipe combination technique that adopts same pot to mix, disposablely water the single chamber dual-thrust motor that medicine is produced, the axis 6 of engine has 0 °～7 ° angle with the axis 7 of emulation cruise missile target, there is umbrella storehouse 8 at the housing middle part, parachute 9 is arranged in the umbrella storehouse, parachute hangs on the focus point of emulation cruise missile target, umbrella storehouse lid 10 is arranged at top, umbrella storehouse, flexible hook 11 between umbrella Cang Gai and housing, there is electrical fuze bomb 12 on the elastic hook side, after the electrical fuze bomb is ignited, umbrella Cang Gai breaks off relations, allow umbrella Cang Gai open, emit parachute, target situation sensors 13 is arranged on the rocket engine, the target situation sensors is temperature sensor and/or sound transducer, after rocket engine quits work, the sound of engine operation disappears, when engine temperature reduces, exportable target status signals, there is equipment compartment 14 front portion of housing, equipment compartment lid 15 is arranged at equipment compartment top, the heading control device is arranged in the equipment compartment, the heading control device has gyroscope 16, gps signal receiver 17, height inductive head 18 and control circuit board 19, control circuit is arranged on the control circuit board, control circuit has input and output, gyroscope, gps signal receiver links to each other with the input of control circuit with the output of height inductive head, the output of control circuit links to each other with the stepper motor of steering wheel respectively, at gyroscope, gps signal receiver, the height inductive head is when control circuit input deviation signal, control circuit can be to the steering wheel output regulation signal, in the control circuit, also has umbrella storehouse lid open circuit, the output of target situation sensors links to each other with the input of umbrella storehouse lid open circuit, the output of umbrella storehouse lid open circuit links to each other with the lead-in wire of electrical fuze bomb, also has gyroscope in the equipment compartment, the power supply 20 of control circuit and steering wheel stepper motor.
Target situation sensors on the above-mentioned emulation cruise missile target is temperature sensor and/or sound transducer, and the target situation sensors is the combination of timer or temperature sensor and/or sound transducer and timer also.Timer can be used the clock in the control circuit.Different target situation sensors is set, can be after the flight regular hour or after rocket engine quits work at emulation cruise missile target, output target status signals, or the certain hour of after rocket engine quits work, delaying time, output target status signals, allow umbrella storehouse lid open circuit export detonator signal, emit parachute, the utility model can be reclaimed by safety.
Angle between the axis of the engine of above-mentioned emulation cruise missile target and emulation cruise missile target axis be 6 ° 3 '.In order to increase motive force, the axis of engine and emulation cruise missile target axis can be on same straight lines.Among Fig. 3, the axis of the axis of engine 21 and emulation cruise missile target is on same straight line.
Claims (5)
1. emulation cruise missile target, the housing that imitative guided missile shape is arranged, wing is arranged on the housing, it is characterized in that: the steering wheel that is connected with stepper motor is arranged on the wing, dynamic storehouse, the rear portion of housing, rocket engine is arranged in the power bin, there is the umbrella storehouse at the housing middle part, umbrella has parachute in the storehouse, parachute hangs on the focus point of emulation cruise missile target, umbrella Cang Gai is arranged at top, umbrella storehouse, flexible hook between umbrella Cang Gai and housing, there is the electrical fuze bomb on the elastic hook side, on the emulation cruise missile target target situation sensors is arranged, there is equipment compartment the front portion of housing, the heading control device is arranged in the equipment compartment, the heading control device has gyroscope, gps signal receiver, height inductive head and control circuit board, receive gyroscope on the control circuit board, gps signal receiver, can be after the deviation signal of height inductive head input to the control circuit of steering wheel output regulation signal, control circuit has input and output, gyrostatic output links to each other with the input of control circuit, the output of control circuit links to each other with the stepper motor of steering wheel, in the control circuit, receive the umbrella storehouse lid open circuit of exportable detonator signal behind the input signal of target situation sensors in addition, the output of target situation sensors links to each other with the input of umbrella storehouse lid open circuit, the output of open circuit links to each other with the lead-in wire of electrical fuze bomb, also has gyroscope in the equipment compartment, gps signal receiver, the height inductive head, the power supply of control circuit and steering wheel stepper motor.
2. by the described emulation cruise missile of claim 1 target, it is characterized in that: described target situation sensors is timer, temperature sensor and/or sound transducer, timer is the clock in the control circuit, and temperature sensor and/or sound transducer are installed on the rocket engine.
3. by claim 1 or 2 described emulation cruise missile targets, it is characterized in that: described rocket engine is to adopt propellant that same pot mixes and graphite jet pipe combination technique, disposablely water the single chamber dual-thrust motor that medicine is produced.
4. by the described emulation cruise missile of claim 3 target, it is characterized in that: the angle between the axis of described engine and emulation cruise missile target axis be 6 ° 3 '.
5. by the described emulation cruise missile of claim 3 target, it is characterized in that: the axis of described emulation cruise missile target and the axis of engine are on same straight line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420032097 CN2708232Y (en) | 2004-06-16 | 2004-06-16 | Simulation cruise missile target drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420032097 CN2708232Y (en) | 2004-06-16 | 2004-06-16 | Simulation cruise missile target drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2708232Y true CN2708232Y (en) | 2005-07-06 |
Family
ID=34849948
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420032097 Expired - Fee Related CN2708232Y (en) | 2004-06-16 | 2004-06-16 | Simulation cruise missile target drone |
Country Status (1)
| Country | Link |
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| CN (1) | CN2708232Y (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2442947C1 (en) * | 2010-10-11 | 2012-02-20 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Air target imitator |
| CN103307934A (en) * | 2012-03-07 | 2013-09-18 | 中国人民解放军总参谋部工程兵科研三所 | Large-caliber supersonic target projectile for testing or training |
| CN103307936A (en) * | 2012-03-07 | 2013-09-18 | 中国人民解放军总参谋部工程兵科研三所 | Small-sized rocket projectile capable of being used as cruise missile radar reflection character equivalent target |
| CN104976924A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Airbag canopy jettison mechanism |
| CN105035332A (en) * | 2015-08-19 | 2015-11-11 | 北京航天科颐技术有限公司 | Drone aircraft flight control system and method |
| CN105387771A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Hiding structure for drone aircraft parachute lanyards |
| CN105627838A (en) * | 2016-02-22 | 2016-06-01 | 许昌义 | Express delivery missile |
| CN106205264A (en) * | 2016-08-25 | 2016-12-07 | 程旭德 | A kind of guided missile rear test simulation training method and system |
| CN109798808A (en) * | 2018-12-25 | 2019-05-24 | 中国工程物理研究院总体工程研究所 | A kind of arrow load transmitting folding wings scout missile Tuo San mechanism |
| CN110966898A (en) * | 2019-12-06 | 2020-04-07 | 上海机电工程研究所 | Missile projectile recovery system after examination flight test |
| RU2759973C2 (en) * | 2019-12-04 | 2021-11-19 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-Морского Флота "Военно-морская академия им. Адмирала Флота Советского Союза Н.Г. Кузнецова" | Method for forming target object simulating launch of aerial target in conditions of missile position, airfield, unequipped territory, and device for its implementation |
-
2004
- 2004-06-16 CN CN 200420032097 patent/CN2708232Y/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2442947C1 (en) * | 2010-10-11 | 2012-02-20 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Air target imitator |
| CN103307934A (en) * | 2012-03-07 | 2013-09-18 | 中国人民解放军总参谋部工程兵科研三所 | Large-caliber supersonic target projectile for testing or training |
| CN103307936A (en) * | 2012-03-07 | 2013-09-18 | 中国人民解放军总参谋部工程兵科研三所 | Small-sized rocket projectile capable of being used as cruise missile radar reflection character equivalent target |
| CN104976924A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Airbag canopy jettison mechanism |
| CN105035332A (en) * | 2015-08-19 | 2015-11-11 | 北京航天科颐技术有限公司 | Drone aircraft flight control system and method |
| CN105387771B (en) * | 2015-11-26 | 2018-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of target drone umbrella rope stealth structure |
| CN105387771A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Hiding structure for drone aircraft parachute lanyards |
| CN105627838A (en) * | 2016-02-22 | 2016-06-01 | 许昌义 | Express delivery missile |
| CN106205264A (en) * | 2016-08-25 | 2016-12-07 | 程旭德 | A kind of guided missile rear test simulation training method and system |
| CN109798808A (en) * | 2018-12-25 | 2019-05-24 | 中国工程物理研究院总体工程研究所 | A kind of arrow load transmitting folding wings scout missile Tuo San mechanism |
| CN109798808B (en) * | 2018-12-25 | 2023-09-26 | 中国工程物理研究院总体工程研究所 | Rocket-borne launching folding wing patrol fly bullet parachute-removing mechanism |
| RU2759973C2 (en) * | 2019-12-04 | 2021-11-19 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-Морского Флота "Военно-морская академия им. Адмирала Флота Советского Союза Н.Г. Кузнецова" | Method for forming target object simulating launch of aerial target in conditions of missile position, airfield, unequipped territory, and device for its implementation |
| CN110966898A (en) * | 2019-12-06 | 2020-04-07 | 上海机电工程研究所 | Missile projectile recovery system after examination flight test |
| CN110966898B (en) * | 2019-12-06 | 2022-07-01 | 上海机电工程研究所 | Missile projectile recovery system after completion of assessment flight test |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |