CN203231699U - Gliding drone aircraft - Google Patents
Gliding drone aircraft Download PDFInfo
- Publication number
- CN203231699U CN203231699U CN 201320142125 CN201320142125U CN203231699U CN 203231699 U CN203231699 U CN 203231699U CN 201320142125 CN201320142125 CN 201320142125 CN 201320142125 U CN201320142125 U CN 201320142125U CN 203231699 U CN203231699 U CN 203231699U
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- CN
- China
- Prior art keywords
- cabin
- target
- control
- glider
- middle fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A gliding drone aircraft comprises a head cover, a middle fuselage, a flight control cabin, a stern room and a tail cover which are sequentially connected. The middle fuselage is connected with the flight control cabin through a first disassembly mechanism installed at the back of the middle fuselage, the flight control cabin is connected with the stern room installed at the back of the flight control cabin, a central wing is arranged above the middle fuselage, two sides of the central wings are connected with a wing, an empennage is disposed at the back of the flight control cabin, and a rectification cover plate is fixed above the central wing. According to the gliding drone aircraft, an air-launched unpowered gliding flight mode is adopted, flight performances such as speed and height and target characteristics can meet basic requirements for mid-range air-to-air missile aggressive training, the gliding drone aircraft is high in quality, low in cost and high in cost performance and reliability, and aerial safety and ground safety can be guaranteed.
Description
Technical field
The relevant a kind of glider target of the utility model.
Background technology
Target drone is the expendable training device that air unit's training is used, and it has applicability, economy, security preferably.For a long time, China air unit air-to-air missile training target, be substitute with the bright bullet that navigates, along with the development of Air Force weapon equipment, the target of aerial flare can not satisfy the attack requirement of some new model air-to-air missile always, aerial flare is stored and is seriously exceeded the time limit in addition, functional reliability is poor, and quantity runs out, for this reason, developed the air-to-air missile training with infrared and microwave target signature and used the umbellate form target, satisfied the low coverage air-to-air missile substantially and attacked the demand of training.But along with equipping of middle distance air-to-air missile, its Doppler radar has proposed new requirement again to target speed, target signature etc., so prior art still has necessity of improvement.
Summary of the invention
The utility model provides a kind of glider target, to solve the technical problem that exists in the background technology.
For this reason, a kind of glider target of the present utility model, comprise in turn the nose shell, the middle fuselage that connect, fly to control cabin, deck store and tail fairing, the first disintegration mechanism that described middle fuselage is installed by its rear portion flies to control the cabin and is connected with described, describedly fly to control the second disintegration mechanism of installing by its rear portion in the cabin and be connected with described deck store, described middle fuselage top is provided with central wing, the both sides of described central wing connect wing, the described rear portion that flies to control the cabin is provided with empennage, and described central wing upper fixed has the rectification cover plate.
Wherein, main chute and extractor parachute are installed in the described deck store, the main chute rope of described main chute flies to control the cabin and links to each other with described, and the extractor parachute rope of described extractor parachute links to each other with described deck store.
Wherein, described fly to control be provided with in the cabin for control state of flight flight control system.
Wherein, described deck store links to each other with described tail fairing by three cable wires.
Wherein, described nose shell adopts the glass fibre reinforced plastic structure of female mould forming, and the anterior thickness of described nose shell is 0.6mm, and rear portion thickness is 3mm, and described nose shell connects with bolt and described middle fuselage.
Wherein, described middle fuselage is to be processed by steel pipe, the external diameter 219mm of described middle fuselage.
Wherein, described wing is to adopt steel skeleton also to be connected with the polyurethane foam filler with the fiberglass covering to make.
Wherein, described to fly to control the cabin be the cylinder that forms with the thick steel plate rolling of 2mm, and the described external diameter that flies to control the cabin is 219mm.
Wherein, described empennage is to adopt steel skeleton also to be connected with the polyurethane foam filler with the fiberglass covering to make.
The utility model adopts the empty flying method of formula, unpowered glide of penetrating, and trains basic demand apart from the air-to-air missile aggressiveness during flying quality such as its speed, height and target signature can satisfy.And super quality and competitive price, the cost performance height, good reliability guarantees air security and ground safety.
Description of drawings
Fig. 1 is overall structure schematic diagram of the present utility model;
Fig. 2 is the structural representation after the utility model disintegrates.
Description of reference numerals
Middle fuselage-1; Central wing-11; Wing-12; Rectification cover plate-13; Fly to control cabin-2; Empennage-21; Extractor parachute-22; Main chute-23; Tail fairing-3; Nose shell-4; Deck store-5.
The specific embodiment
For shape of the present utility model, structure and characteristics can be understood better, below will enumerate preferred embodiment and also be elaborated by reference to the accompanying drawings.
Fig. 1 is structural representation of the present utility model, and as shown in Figure 1, the utility model comprises in turn the nose shell 4, the middle fuselage 1 that connect, flies to control cabin 2, deck store 5 and tail fairing 3.Middle fuselage 1 is to be processed by steel pipe, middle fuselage 1 external diameter 219mm, middle fuselage 1 the place ahead junctor head-shield 4.Nose shell 4 adopts the glass fibre reinforced plastic structure of female mould forming, and the front portion is 0.6mm thickness, and the rear portion is 3mm thickness, and connects with bolt and middle fuselage 1.
The rear portion of middle fuselage 1 is equipped with the first disintegration mechanism that first Cylinder lock with ball constitutes.Middle fuselage 1 by first Cylinder lock with ball with fly to control cabin 2 and be connected.Middle fuselage 1 top is provided with central wing 11, and the both sides of central wing 11 connect wing 12.Wing 12 is composite structures that steel skeleton also is formed by connecting with fiberglass covering and polyurethane foam filler.Central wing 11 upper fixed of middle fuselage 1 have rectification cover plate 13, are used for installing the strong point of inclined support bar on hanger and the carrier aircraft hanger.
Flying to control cabin 2 is the cylinders that form with the thick steel plate rolling of 2mm, and external diameter also is 219mm.The rear portion that flies to control cabin 2 is equipped with the second disintegration mechanism that second Cylinder lock with ball constitutes, and flies to control cabin 2 and is connected with deck store 5 by second Cylinder lock with ball.Fly to control in the cabin 2 and be provided with flight control system, with the state of flight of control glider target.The rear portion that flies to control cabin 2 is provided with empennage 21, and empennage 21 is by the steel skeleton of rotating shaft, U-shaped stiffener and the combination of wing root rib, and the composite structure that is formed by connecting with fiberglass covering and polyurethane foam filler.
The utility model adopts the empty flying method of formula, unpowered glide of penetrating, and trains basic demand apart from the air-to-air missile aggressiveness during flying quality such as its speed, height and target signature can satisfy.And super quality and competitive price, the cost performance height, good reliability guarantees air security and ground safety.
More than be illustrative to description of the present utility model; and it is nonrestrictive; those skilled in the art is understood, and can carry out many modifications, variation or equivalence to it within spirit that claim limits and scope, but they will fall in the protection domain of the present utility model all.
Claims (9)
1. glider target, it is characterized in that, comprise in turn the nose shell, the middle fuselage that connect, fly to control cabin, deck store and tail fairing, the first disintegration mechanism that described middle fuselage is installed by its rear portion flies to control the cabin and is connected with described, describedly fly to control the second disintegration mechanism of installing by its rear portion in the cabin and is connected with described deck store, be provided with central wing above the described middle fuselage, the both sides connection wing of described central wing, the described rear portion that flies to control the cabin is provided with empennage, and described central wing upper fixed has the rectification cover plate.
2. glider target as claimed in claim 1 is characterized in that, main chute and extractor parachute are installed in the described deck store, and the main chute rope of described main chute flies to control the cabin and links to each other with described, and the extractor parachute rope of described extractor parachute links to each other with described deck store.
3. glider target as claimed in claim 1 is characterized in that, described fly to control be provided with in the cabin for control state of flight flight control system.
4. glider target as claimed in claim 1 is characterized in that, described deck store links to each other with described tail fairing by three cable wires.
5. glider target as claimed in claim 1 is characterized in that, described nose shell adopts the glass fibre reinforced plastic structure of female mould forming, and the anterior thickness of described nose shell is 0.6mm, and rear portion thickness is 3mm, and described nose shell connects with bolt and described middle fuselage.
6. glider target as claimed in claim 1 is characterized in that, described middle fuselage is to be processed by steel pipe, the external diameter 219mm of described middle fuselage.
7. glider target as claimed in claim 1 is characterized in that, described wing is to adopt steel skeleton also to be connected with the polyurethane foam filler with the fiberglass covering to make.
8. glider target as claimed in claim 1 is characterized in that, described to fly to control the cabin be the cylinder that forms with the thick steel plate rolling of 2mm, and the described external diameter that flies to control the cabin is 219mm.
9. glider target as claimed in claim 1 is characterized in that, described empennage is to adopt steel skeleton also to be connected with the polyurethane foam filler with the fiberglass covering to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320142125 CN203231699U (en) | 2013-03-26 | 2013-03-26 | Gliding drone aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320142125 CN203231699U (en) | 2013-03-26 | 2013-03-26 | Gliding drone aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203231699U true CN203231699U (en) | 2013-10-09 |
Family
ID=49287821
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320142125 Expired - Fee Related CN203231699U (en) | 2013-03-26 | 2013-03-26 | Gliding drone aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203231699U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110779397A (en) * | 2019-11-19 | 2020-02-11 | 中国人民解放军陆军工程大学 | A large-caliber supersonic target for experimental or training purposes |
-
2013
- 2013-03-26 CN CN 201320142125 patent/CN203231699U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110779397A (en) * | 2019-11-19 | 2020-02-11 | 中国人民解放军陆军工程大学 | A large-caliber supersonic target for experimental or training purposes |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131009 Termination date: 20140326 |