CN204660024U - A kind of dish-type rotor unmanned helicopter - Google Patents
A kind of dish-type rotor unmanned helicopter Download PDFInfo
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- CN204660024U CN204660024U CN201520206146.1U CN201520206146U CN204660024U CN 204660024 U CN204660024 U CN 204660024U CN 201520206146 U CN201520206146 U CN 201520206146U CN 204660024 U CN204660024 U CN 204660024U
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- rotor unmanned
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Abstract
The utility model discloses a kind of dish-type rotor unmanned helicopter, its constructional feature is: fuselage roof installs a disk as oar dish, and from protruding four blades arranged at equal intervals of oar dish, afterbody installs the duct driving engine with vector spout additional.Described blade is scalable, and each blade is divided into three sections, is respectively the blade root, interlude and the blade tip that are connected with oar dish.From blade root to blade tip, section chord line length reduces, and three sections of blades are connected by the spring of large elasticity modulus, and blade tip is with winglet, and the change with centnifugal force realizes blade and stretches.The utility model has the advantages that: this is gone straight up to function and flies between two kinds of patterns at helicopter flight and fixed-wing and freely switch, possess vertical takeoff and landing, hovering, high cruise-ability and stealth capabilities, after loading different task devices, in military domain, will investigate in high-altitude, equip with arms and hit making a breakthrough property achievement in terrain object, counter radar detection, air transportation, satellite guidance etc.
Description
Technical field
The utility model relates to a kind of novel composite helicopter, is specifically related to a kind of dish-type rotor unmanned helicopter.
Background technology
In today of military technology fast development, due to the performances such as the speed of pure helicopter, flying height and flying power with lag far behind fixed wing aircraft, people expect helicopter vertical takeoff and landing and hovering ability to be combined with conventional fixed-wing aircraft high-speed flight ability, and this mentality of designing has become modern and the new direction of future aircraft development.This novel disc type rotor unmanned helicopter, with its creationary structure design and engine installation, makes it take into account the advantage of two kinds of aircraft, more can adapt to the requirement of future battlefield arms strike, counter radar detection and investigation etc.
Summary of the invention
The purpose of this utility model is to provide a kind of dish-type rotor unmanned helicopter, this helicopter has good airworthiness, the rotor of helicopter and the wing of fixed wing aircraft are merged mutually, and two groups of flying power systems are set, pass through flight control system, realize freely switching of helicopter and fixed wing aircraft two kinds of patterns, make its field of application more extensive.
The utility model is achieved like this, a kind of dish-type rotor unmanned helicopter, form primarily of fuselage, oar dish, blade and the duct driving engine with vector spout, it is characterized in that: fuselage roof installs a disk as oar dish, from protruding four blades arranged at equal intervals of oar dish, afterbody installs the duct driving engine with vector spout additional.
Further, described whole body adopts absorbing material and coating manufacture, carries out Aerodynamic optimization design.
Further, described oar dish is a large diameter disk, the flat lift provided when flying needed for flight.
Further, described blade is scalable, and each blade is divided into three sections, be respectively the blade root be connected with oar dish, interlude and blade tip, from blade root to blade tip, section chord line length reduces, three sections of springs by large elasticity modulus of blade are connected, and blade tip is with winglet, and the change with centnifugal force realizes blade and stretches.
Further, described depopulated helicopter can load distinct device.
The utility model has the advantages that: (1) this helicopter has good airworthiness, the rotor of helicopter and the wing of fixed wing aircraft are merged mutually, and two groups of flying power systems are set, pass through flight control system, realize freely switching of helicopter and fixed wing aircraft two kinds of patterns, make its field of application more extensive.(2) this is gone straight up to function and flies between two kinds of patterns at helicopter flight and fixed-wing and freely switch, possess vertical takeoff and landing, hovering, high cruise-ability, after loading different task devices, in military domain, will investigate in high-altitude, equip with arms and hit making a breakthrough property achievement in terrain object, counter radar detection, air transportation, satellite guidance etc.(3) this helicopter removes tail-rotor on the basis of pure helicopter, and rotor blade and driving device are all wrapped within oar dish, greatly reduce radar area, makes this aircraft have higher Stealth Fighter.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is oar dish structure birds-eye view of the present utility model.
Fig. 3 is oar dish structural front view of the present utility model.
Fig. 4 is paddle blade structure schematic diagram of the present utility model.
In the drawings, 1 is fuselage, and 2 is oar dish, 3, blade, and 4 is the duct driving engine with vector spout, and 5 is blade root, 6, interlude, 7, blade tip, 8, spring, 9, winglet.
Detailed description of the invention
As shown in Figure 1, Figure 2, Figure 3 shows, the utility model is achieved like this, a kind of dish-type rotor unmanned helicopter, form primarily of fuselage 1, oar dish, blade 3 and the duct driving engine 4 with vector spout, it is characterized in that: a disk is installed as oar dish 2 in fuselage 1 top, from protruding four blades arranged at equal intervals 3 of oar dish 2, fuselage 1 afterbody installs the duct driving engine 4 with vector spout additional.
As shown in Figure 4, described blade 3 is scalable, and each blade 3 is divided into three sections, the blade root 5 be connected with oar dish 2, interlude 6 and blade tip 7, reduce from blade root 5 to blade tip 7 section chord line length, and three sections of blades 3 are connected by the spring 8 of large elasticity modulus, blade tip 7 is with winglet 9, and the change with centnifugal force realizes blade and stretches.
Design concept of the present utility model is: the design of lifting airscrew with fixed wing aircraft wing is merged by this type aircraft mutually, big diameter disc parcel rotor is installed additional at pure helicopter top, as oar disc system, the driving engine driving rotor wing rotation is had in fuselage, at the duct driving engine of afterbody carrier tape vector spout, two groups of flying power systems are by flight control system coordinated, control rotor to stretch and thrust size, this aircraft can be flown between two kinds of patterns at helicopter flight and fixed-wing and freely switch.
The scheme that the utility model solves maneuvering flight is: employ the mode that fixed-wing is combined with rotor, a large diameter disk has been installed as oar dish 2 at fuselage 1 top, from the protruding four telescopic blades 3 arranged at equal intervals of oar dish 2, and install the duct driving engine 4 with vector spout additional at fuselage 1 afterbody.Under vertical takeoff and landing, spot hover or low-speed condition, under the influence of centrifugal force, blade 3 full extension, becomes a disc rotary with the large propeller hub of central authorities, provides the lift needed for flight; At a high speed flat fly state under, oar dish 2 stall, blade 3 takes in oar dish 2, and lift is by the oar dish 2(disk wing) provide, rely on afterbody to produce forward thrust with the driving engine 4 of vector spout, overcome anti-twisted power simultaneously, control flight attitude together with oar dish 2.
The scheme that the utility model solves offline mode switching is: each blade of rotor is divided into three sections, reduce from blade root 5 to blade tip 7 section chord line length, three sections of blades 3 are connected by the spring 8 of large elasticity modulus, blade tip 7 is with winglet 9, change with centnifugal force realizes blade and stretches, thus completes the switching of offline mode.
The scheme that the utility model solves Stealth Fighter is: whole body adopts absorbing material and coating manufacture, and carry out Aerodynamic optimization design, on the basis of pure helicopter, remove tail-rotor simultaneously, rotor blade and driving device are all wrapped within oar dish, greatly reduce radar area, make this aircraft have higher Stealth Fighter.
Claims (4)
1. a dish-type rotor unmanned helicopter, form primarily of fuselage, oar dish, blade and the duct driving engine with vector spout, it is characterized in that: fuselage roof installs a disk as oar dish, from protruding four blades arranged at equal intervals of oar dish, afterbody installs the duct driving engine with vector spout additional.
2. a kind of dish-type rotor unmanned helicopter according to claim 1, is characterized in that: described whole body adopts absorbing material and coating manufacture, carries out Aerodynamic optimization design.
3. a kind of dish-type rotor unmanned helicopter according to claim 1, it is characterized in that: described blade is scalable, and each blade is divided into three sections, be respectively the blade root be connected with oar dish, interlude and blade tip, from blade root to blade tip, section chord line length reduces, three sections of blade are connected by spring, and blade tip is with winglet.
4. a kind of dish-type rotor unmanned helicopter according to claim 1, is characterized in that: described depopulated helicopter can load distinct device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520206146.1U CN204660024U (en) | 2015-04-08 | 2015-04-08 | A kind of dish-type rotor unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520206146.1U CN204660024U (en) | 2015-04-08 | 2015-04-08 | A kind of dish-type rotor unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204660024U true CN204660024U (en) | 2015-09-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520206146.1U Expired - Fee Related CN204660024U (en) | 2015-04-08 | 2015-04-08 | A kind of dish-type rotor unmanned helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN204660024U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104773291A (en) * | 2015-04-08 | 2015-07-15 | 南昌航空大学 | Disc-shaped rotor wing unmanned helicopter |
| CN106043696A (en) * | 2016-06-30 | 2016-10-26 | 天津曙光天成科技有限公司 | Flying system for unmanned aerial vehicle |
| CN110203395A (en) * | 2019-05-21 | 2019-09-06 | 华南理工大学 | A kind of sub- equipment methods of investigation of unmanned plane machine tool delivery intelligence and system |
| CN113086160A (en) * | 2021-04-30 | 2021-07-09 | 中国人民解放军陆军装甲兵学院 | Deformable unmanned aerial vehicle of wing |
-
2015
- 2015-04-08 CN CN201520206146.1U patent/CN204660024U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104773291A (en) * | 2015-04-08 | 2015-07-15 | 南昌航空大学 | Disc-shaped rotor wing unmanned helicopter |
| CN106043696A (en) * | 2016-06-30 | 2016-10-26 | 天津曙光天成科技有限公司 | Flying system for unmanned aerial vehicle |
| CN110203395A (en) * | 2019-05-21 | 2019-09-06 | 华南理工大学 | A kind of sub- equipment methods of investigation of unmanned plane machine tool delivery intelligence and system |
| CN113086160A (en) * | 2021-04-30 | 2021-07-09 | 中国人民解放军陆军装甲兵学院 | Deformable unmanned aerial vehicle of wing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150923 Termination date: 20160408 |