CN204056301U - A kind of canard aerodynamic arrangement aircraft decoy of monocoque - Google Patents
A kind of canard aerodynamic arrangement aircraft decoy of monocoque Download PDFInfo
- Publication number
- CN204056301U CN204056301U CN201420497460.5U CN201420497460U CN204056301U CN 204056301 U CN204056301 U CN 204056301U CN 201420497460 U CN201420497460 U CN 201420497460U CN 204056301 U CN204056301 U CN 204056301U
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- support chassis
- fuselage
- mode
- canard
- monocoque
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- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
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Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model discloses a kind of canard aerodynamic arrangement aircraft decoy of monocoque, comprise support chassis, fuselage, canard, wing, vertical fin, secondary fin, alighting gear and nozzle; Wherein fuselage is connected with welding manner with support chassis; Canard is connected with fuselage with inserting mode; Wing is connected by wheeled slideway mode with support chassis; Vertical fin is connected with inserting mode with fuselage; Secondary fin is connected to support chassis afterbody in hook mode; Alighting gear is connected with axle connection mode with support chassis; Nozzle is connected with inserting mode with fuselage.The canard aerodynamic arrangement aircraft decoy of monocoque described in the utility model is reasonable in design, and raw MAT'L is cheap and easy to get, and processing technology is ripe, and skill and tactical ability is advanced in performance, is suitable for applying in the military.
Description
Technical field
The utility model relates to a kind of canard aerodynamic arrangement aircraft decoy of monocoque, be specially one and have monocoque, and profile is true to nature, the canard aerodynamic arrangement aircraft decoy of easy accessibility.
Background technology
The history that military decoy occurs can trace back to the Spring and Autumn and the Warring States Periods of ancient Chinese, owing to being in cold weapon era when fashion, no matter be that enemy's situation is scouted, grapple in logistics support or battlefield, all need to complete by manpower or animal power, so decoy at that time mainly utilizes favourable physical geography condition, adopt all kinds of naive models that all kinds of simple and easy material makes.
World War I period, along with aeronautical technology is in the application of military field, be scouting and the bombing of antagonism enemy aircraft, each belligerent state employs the decoy military target important to party B all in a large number and carries out pretend and protect, and has shown desirable effect.But decoy at that time remains with bamboo and wood, and waste metal etc. just become material, build according to the roughly profile of real goal.World War II period; along with appearance and the application of electromagnetic surveying technology; the maturation of military aviation technology and popularization; long-range detection and air attack become the significant threat of war both sides; for the military surveillance of confusing hostile; the safety of protection party B military target, each state manufactures all in a large number and employs camouflage decoy.
Since canard aerodynamic arrangement aircraft occurs, main based on fighter plane, with the dog fight ability of its excellence, develop the key member for attack and the weapons of system rapidly, progressively become one of trump card of military power and military power, also being enemy attack emphasis, is the military target needing key protection.Thus, the military creates the heavy demand to this machine decoy.
Aircraft decoy simply processes with wood or hard paper shell the earliest, and well reaching lures the enemy in opens fire, confuse the enemy, hide the object of oneself.Along with the development of science and technology, various types of aircraft decoy continues to bring out, and wherein inflatable aircraft decoy manufactures and designs with it and simple, is with low costly able to rapid popularization.The aircraft decoy in this period mainly designs, the similarity of the outward appearance that only pursues a goal optical signature for enemy's optical reconnaissance.
Since 20 century 70s, all kinds of detection reconnaissance means based on " sound, optical, electrical, magnetic " technology progressively move to maturity with perfect.Along with the comprehensive application of radar, satellite technology, microwave radar and infrared reconnaissance progressively become the main flow of modern military Detection Techniques.Traditional optical aircraft decoy is due to material, the difference of the aspects such as structure and true target, its Radar Cross Section and infrared emission feature all exist with true aircraft vehicle obviously to be distinguished, therefore, only pursue the similarity of appearance profile and visible light wave range, be more and more difficult to the demand adapting to modern war.
For resisting the radar of enemy and infrared reconnaissance, exploitation has appearance profile, visible ray, radar and infrared multiband multiple spectra concurrently and pretends aircraft decoy and progressively become common recognition in the industry and target.At present, international market of military product has occurred that some can at the radar of simulates real target, the build-up type aircraft decoy product of infrared signature in a certain degree scope.But these product structures are complicated, and a large amount of use high desnity metal material, cause unit manufacturing cost high, product is heavy, and dismounting difficulty is large, considerably increases military logistics task amount.
Utility model content
For active service canard aerodynamic arrangement aircraft decoy Problems existing, the purpose of this utility model is to provide that a kind of appearance profile is true to nature, and camouflage performance is excellent, the monocoque canard aerodynamic arrangement aircraft decoy of easy accessibility.
Particularly, the utility model adopts split type, modular design, comprises support chassis, fuselage, canard, wing, vertical fin, secondary fin, alighting gear and nozzle totally 8 parts.Wherein fuselage is connected with welding manner with support chassis; Canard is connected with fuselage with inserting mode; Wing is connected by wheeled slideway mode with support chassis; Vertical fin is connected with inserting mode with fuselage; Secondary fin is connected to support chassis afterbody in hook mode; Alighting gear is connected with axle connection mode with support chassis; Nozzle is connected with inserting mode with fuselage.
Described support chassis is divided into front support chassis and rear support chassis two parts, and these two parts connect in draw-in groove mode; Described top, front support chassis is provided with a hydraulic jacking device, and described rear support chassis middle front part is provided with the hydraulic jacking device of two same model; Three described hydraulic jacking devices are connected in latch mode with support chassis; Described hydraulic jacking device is connected with rotating shaft mode with alighting gear.
Described fuselage adopts cavity type structure design, and is divided into forebody and rear body; The thermosetting polyester resin that body shell strengthens with the metal gauze of small-bore and glass fabric by means of moulding technology manufacture; In moulding process, the framework of steel reinforcement that the inner pre-buried termination of body shell is exposed, by the embedded bar skeleton in fuselage expose termination and described support chassis realizes being interconnected with bond pattern, wherein forebody is connected with front support chassis, and rear body is connected with rear support chassis.
The nozzle of driving engine is the most significant infrared signal radiation area, the nozzle inside of the decoy involved by described the utility model can arrange heat power supply device, in order to the infrared signal of Reality simulation target, heat power supply device comprises heating resistor and high-power lead-acid battery group, and this device is fixed on inside nozzle with bolt.
Described wing adopts syllogic design, can carry out folding operation, connects, can directly fold between adjacent wing section with hinging manner; Described wing is being removed in receipts process, extract wing axis out certain space, each wing section folded successively subsequently, and fuselage both sides is fixed in suspension by wheel rail.
The utility model is low for Conventional pneumatic formula aircraft decoy fidelity, and the dismounting of novel fabricated aircraft decoy is loaded down with trivial details, the problems such as logistics task amount is large, the advantage both fully absorbing, and adopts brand-new design to develop.
Technical scheme involved by the utility model is simple, adopts glass fabric and small-bore metal gauze to strengthen thermosetting polyester resin composite material, and manufactures body shell with moulding technology; In moulding process, at the framework of steel reinforcement that the inner pre-buried termination of body shell is exposed, what utilize framework of steel reinforcement exposes termination, realizes being connected and fixed of fuselage and support chassis with support chassis with welding process; Thus, both improve the verisimilitude of aircraft decoy and true aircraft configuration profile, the conformability of radar return feature, and greatly reduced own wt.
The utility model adopts modular design, and support chassis is designed to be able to partition two joint, can conveniently load and unload.Wing is connected with skidding orbital fashion with support chassis, very easily can be pulled out by wing and fold, and so not only decreases to take up room but also time saving and energy saving; And canard, vertical fin, secondary fin, alighting gear and nozzle all can easily be dismantled, reach assembling simple, the object of convenient transportation.
The canard aerodynamic arrangement aircraft decoy of a kind of monocoque involved by the utility model is reasonable in design, and involved material is cheap and easy to get, good economy performance, and processing technology is ripe, and skill and tactical ability index is advanced, should in the field of businessly apply.
Accompanying drawing explanation
Fig. 1 is that monocoque destroys 10 aircraft decoy integral structure schematic diagrams.
Fig. 2 is the structural representation that monocoque destroys the support frame of 10 aircraft decoys.
Fig. 3 is that monocoque destroys the canard of 10 aircraft decoys and the connection structure schematic diagram of fuselage.
Fig. 4 is that monocoque destroys the wing of 10 aircraft decoys and the connection structure schematic diagram of support chassis.
Fig. 5 is wing and the support chassis communication port schematic diagram that monocoque destroys 10 aircraft decoys.
Fig. 6 is the wing birds-eye view that monocoque destroys 10 aircraft decoys.
Fig. 7 is vertical fin and body connection structure schematic diagram.
Fig. 8 is secondary fin and support chassis connection diagram.
Fig. 9 is nozzle structural representation.
Figure 10 is that monocoque destroys 20 aircraft decoys.
Figure 11 is monocoque phantom 4000 aircraft decoy.
Detailed description of the invention
Below in conjunction with specific embodiment, the utility model is described in detail.Following examples are just for further describing of the present utility model; can not be interpreted as the restriction to the utility model protection domain, technical personnel still belongs to protection content of the present utility model according to content of the present utility model to the unsubstantiality change that the utility model carries out.
Embodiment 1: monocoque destroys 10 aircraft decoys
As Fig. 1, for monocoque destroys 10 aircraft decoy overall structure schematic diagrams, comprising support chassis 1, fuselage 2, canard 3, wing 4, vertical fin 5, secondary fin 6, alighting gear 7 and nozzle 8.
As Fig. 2, for monocoque destroys the structural representation of support frame in 10 aircraft decoys.As can be seen from the figure, support chassis is divided into front support chassis 9 and rear support chassis 10 two parts, and these two parts connect with draw-in groove 11; Described top, front support chassis 9 is provided with a hydraulic jacking device 12, and described rear support chassis 10 middle front part is provided with the hydraulic jacking device 12 of two same model; Three described hydraulic jacking devices 12 are connected with latch 13 with support chassis; Described hydraulic jacking device is connected with rotating shaft mode 14 with alighting gear 7.Described alighting gear 7 is connected 15 modes with support chassis with axle and connects.
If Fig. 3 is the connection structure schematic diagram that monocoque destroys canard and fuselage in 10 aircraft decoys, canard is connected with fuselage with inserting mode.16 anchor shafts representing canard in figure, 17 is sky corresponding with canard axle on fuselage.When building canard, only need by canard insertion machine sky with it.
If Fig. 4 is the connection structure schematic diagram that monocoque destroys wing and support chassis in 10 aircraft decoys, Fig. 5 is wing and support chassis communication port schematic diagram, and Fig. 6 is wing birds-eye view; In conjunction with these three figure, wing mounting characteristic is stated.Wing 4 is connected in wheeled slideway 18 mode with support chassis 1, during unloading wing 4, extracts wing axis 19 out a segment distance by wheeled slideway 18.Wing 4 is divided into syllogic to design, and adjacent segment adopts hinging manner 20 to connect, and as shown in Figure 6, can carry out folding operation thus to wing, and the wing rolled well is turned to fuselage both sides by rotating shaft place 21 on wing axis 19.
If Fig. 7 is vertical fin and body connection structure schematic diagram, can find out in figure, vertical fin is connected with inserting mode with fuselage.Wherein 22 is vertical fin axle, and 23 is the junction of vertical fin axle and fuselage.
Fig. 8 is secondary fin and support chassis connection diagram, and secondary fin is connected with support chassis in hook mode, and wherein 24 is the hook position of secondary fin, and 25 is the hook place of secondary fin in support chassis.
Fig. 9 is nozzle structural representation, nozzle and fuselage connection mode are inserting mode, wherein 26 is the connection plug of nozzle, corresponding with this plug is afterbody three jacks (not shown in literary composition), nozzle three plugs is inserted corresponding jack place in fuselage and can realize connecting.In figure, 27 is heat power supply device, is fixed on nozzle internal layer with bolt.
In the present embodiment, it is motor-driven to appointed place monocoque can be destroyed 10 aircraft decoys, and arrange, this monocoque is destroyed 10 aircraft decoys and entered mode of operation then.
Embodiment 2: monocoque destroys 20 aircraft decoys
In the present embodiment, the design paper of destroying 10 aircraft decoys is changed into the design drawing of destroying 20 aircraft decoys, namely can be made into monocoque according to same material standard and manufacturing process and destroy 20 aircraft decoys, as shown in Figure 10.
Embodiment 3: monocoque phantom 4000 aircraft decoy
In the present embodiment, the design paper of destroying 10 aircraft decoys is changed into phantom 4000 aircraft decoy design drawing, namely can be made into monocoque phantom 4000 aircraft decoy, as Figure 11 according to same material standard and manufacturing process.
Claims (4)
1. a canard aerodynamic arrangement aircraft decoy for monocoque, comprises support chassis, fuselage, canard, wing, vertical fin, secondary fin, alighting gear and nozzle; It is characterized in that: wherein fuselage is connected with welding manner with support chassis; Canard is connected with fuselage with inserting mode; Wing is connected by wheeled slideway mode with support chassis; Vertical fin is connected with inserting mode with fuselage; Secondary fin is connected to support chassis afterbody in hook mode; Alighting gear is connected with axle connection mode with support chassis; Nozzle is connected with inserting mode with fuselage.
2. the canard aerodynamic arrangement aircraft decoy of a kind of monocoque according to claim 1, wherein said support chassis is divided into front support chassis and rear support chassis two parts, and these two parts connect in draw-in groove mode; Described top, front support chassis is provided with a hydraulic jacking device, and described rear support chassis middle front part is provided with the hydraulic jacking device of two same model; Three described hydraulic jacking devices are connected in latch mode with support chassis; Described hydraulic jacking device is connected with rotating shaft mode with alighting gear.
3. the canard aerodynamic arrangement aircraft decoy of a kind of monocoque according to claim 1, wherein said fuselage adopts cavity type structure, and is divided into forebody and rear body; Wherein said forebody is connected with front support chassis with welding manner, and described rear body is connected with rear support chassis with welding manner.
4. the canard aerodynamic arrangement aircraft decoy of a kind of monocoque according to claim 1, wherein said wing adopts syllogic design, can carry out collapsible operation, and connect with hinging manner between adjacent wing section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420497460.5U CN204056301U (en) | 2014-09-01 | 2014-09-01 | A kind of canard aerodynamic arrangement aircraft decoy of monocoque |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420497460.5U CN204056301U (en) | 2014-09-01 | 2014-09-01 | A kind of canard aerodynamic arrangement aircraft decoy of monocoque |
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| CN204056301U true CN204056301U (en) | 2014-12-31 |
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| CN201420497460.5U Active CN204056301U (en) | 2014-09-01 | 2014-09-01 | A kind of canard aerodynamic arrangement aircraft decoy of monocoque |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111177964A (en) * | 2019-12-25 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Balance adjusting method and equipment for jacking state of airplane |
-
2014
- 2014-09-01 CN CN201420497460.5U patent/CN204056301U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111177964A (en) * | 2019-12-25 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Balance adjusting method and equipment for jacking state of airplane |
| CN111177964B (en) * | 2019-12-25 | 2023-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Balance adjusting method and equipment for jacking state of airplane |
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| C14 | Grant of patent or utility model | ||
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| C56 | Change in the name or address of the patentee | ||
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Address after: 100043, room 901, room 9, 17 Garden South Road, Beijing, Shijingshan District Patentee after: UNIFORCE TECHNOLOGY Co.,Ltd. Address before: 100080, room 9, building 901, Building 29, Haidian District, Suzhou Street, Beijing Patentee before: UNIFORCE TECHNOLOGY Co.,Ltd. |
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Effective date of registration: 20190313 Granted publication date: 20141231 |
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Date of cancellation: 20211130 Granted publication date: 20141231 |
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Effective date of registration: 20211130 Granted publication date: 20141231 |
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Address after: 906-87, floor 9, building 17, yard 30, Shixing street, Shijingshan District, Beijing 100041 Patentee after: Beijing yunchuang Taihe Technology Co.,Ltd. Address before: 100043 room 901, 9 / F, No.17 Shidai Huayuan South Road, Shijingshan District, Beijing Patentee before: UNIFORCE TECHNOLOGY Co.,Ltd. |
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