CN104773291A - Disc-shaped rotor wing unmanned helicopter - Google Patents
Disc-shaped rotor wing unmanned helicopter Download PDFInfo
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- CN104773291A CN104773291A CN201510162324.XA CN201510162324A CN104773291A CN 104773291 A CN104773291 A CN 104773291A CN 201510162324 A CN201510162324 A CN 201510162324A CN 104773291 A CN104773291 A CN 104773291A
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Abstract
The invention discloses a disc-shaped rotor wing unmanned helicopter which is structurally characterized in that a disc which is taken as a rotor disc is arranged on the top of a fuselage; four paddles which are arranged at intervals extend outside from the rotor disc; a bypass engine provided with a vector nozzle is arranged at the tail of the fuselage; the paddles are telescopic, and each paddle is divided into three sections which are respectively a paddle root connected with the rotor disc, an intermediate section and a paddle tip; the lengths of the chord lines of cross sections are reduced from the paddle roots to the paddle tips; the three sections of each paddle are connected with one another by springs with high elastic coefficients; each paddle tip is provided with a small wing, and the paddles can stretch along with the change of centrifugal force. The disc-shaped rotor wing unmanned helicopter has the advantage that the unmanned helicopter can be freely switched between a helicopter flight mode and a fixed wing flight mode, and has vertical take-off and landing capacity, hovering capacity, high endurance property and stealth capability; after different task devices are loaded on the disc-shaped rotor wing unmanned helicopter, the disc-shaped rotor wing unmanned helicopter has a breakthrough in the aspects of high altitude reconnaissance, armed attack for ground targets, anti-radar detection, air transportation, satellite guidance and the like in the military field.
Description
Technical field
The present invention relates to a kind of novel composite helicopter, be 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 object of the present invention 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 present invention 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, covers whole fuselage, and size is specified by lift size.
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.
Advantage of the present invention is: (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 invention.
Fig. 2 is oar dish structure birds-eye view of the present invention.
Fig. 3 is oar dish structural front view of the present invention.
Fig. 4 is paddle blade structure schematic diagram of the present invention.
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 present invention 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 invention 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 present invention 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 present invention 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 invention 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 (5)
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, is respectively the blade root, interlude and the blade tip that are connected with oar dish.
4. from blade root to blade tip, section chord line length reduces, and three sections of blade are connected by spring, and blade tip is with winglet.
5. 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 |
|---|---|---|---|
| CN201510162324.XA CN104773291A (en) | 2015-04-08 | 2015-04-08 | Disc-shaped rotor wing unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510162324.XA CN104773291A (en) | 2015-04-08 | 2015-04-08 | Disc-shaped rotor wing unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
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| CN104773291A true CN104773291A (en) | 2015-07-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510162324.XA Pending CN104773291A (en) | 2015-04-08 | 2015-04-08 | Disc-shaped rotor wing unmanned helicopter |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741888A (en) * | 2017-02-15 | 2017-05-31 | 南京航空航天大学 | A kind of bionical unmanned reconnaissance helicopter |
| CN106741857A (en) * | 2017-03-02 | 2017-05-31 | 南京那尔朴电子有限公司 | A kind of propeller that can be adjusted with thrust |
| CN107340782A (en) * | 2017-07-03 | 2017-11-10 | 深圳市中微信息技术有限公司 | A kind of intelligence follows unmanned vehicle and its control method |
| CN108045601A (en) * | 2017-12-22 | 2018-05-18 | 南京航空航天大学 | A kind of spacecraft return capsule using extension type jet autorotating rotor system |
| CN108657427A (en) * | 2017-03-28 | 2018-10-16 | 天津京东智联科技发展有限公司 | A kind of blade |
| GB2567299A (en) * | 2017-08-21 | 2019-04-10 | Patrick Ettridge Snr John | Rotary wing flying machine |
| CN113232853A (en) * | 2021-04-02 | 2021-08-10 | 陈�峰 | Short-distance take-off and landing aircraft |
| CN113232888A (en) * | 2021-06-08 | 2021-08-10 | 南京航空航天大学 | Variant rotor drone |
| CN113353253A (en) * | 2021-07-13 | 2021-09-07 | 南京航空航天大学 | Rotor-fixed wing combined target drone |
| CN113353287A (en) * | 2021-07-13 | 2021-09-07 | 南京航空航天大学 | Darkroom test device and paddle |
| CN114426098A (en) * | 2022-02-28 | 2022-05-03 | 上海埃依斯航天科技有限公司 | Novel dish wing |
Citations (5)
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| US2684212A (en) * | 1951-10-31 | 1954-07-20 | Piasecki Helicopter Corp | Disk rotor with retracting blades for convertible aircraft |
| US3273655A (en) * | 1966-09-20 | Center body fivotally retractable rotor | ||
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN102649476A (en) * | 2011-02-28 | 2012-08-29 | 波音公司 | Disc rotor retraction system |
| CN204660024U (en) * | 2015-04-08 | 2015-09-23 | 南昌航空大学 | A kind of dish-type rotor unmanned helicopter |
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2015
- 2015-04-08 CN CN201510162324.XA patent/CN104773291A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3273655A (en) * | 1966-09-20 | Center body fivotally retractable rotor | ||
| US2684212A (en) * | 1951-10-31 | 1954-07-20 | Piasecki Helicopter Corp | Disk rotor with retracting blades for convertible aircraft |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN102649476A (en) * | 2011-02-28 | 2012-08-29 | 波音公司 | Disc rotor retraction system |
| CN204660024U (en) * | 2015-04-08 | 2015-09-23 | 南昌航空大学 | A kind of dish-type rotor unmanned helicopter |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741888A (en) * | 2017-02-15 | 2017-05-31 | 南京航空航天大学 | A kind of bionical unmanned reconnaissance helicopter |
| CN106741888B (en) * | 2017-02-15 | 2023-09-26 | 南京航空航天大学 | Bionic unmanned reconnaissance helicopter |
| CN106741857A (en) * | 2017-03-02 | 2017-05-31 | 南京那尔朴电子有限公司 | A kind of propeller that can be adjusted with thrust |
| CN108657427A (en) * | 2017-03-28 | 2018-10-16 | 天津京东智联科技发展有限公司 | A kind of blade |
| CN107340782A (en) * | 2017-07-03 | 2017-11-10 | 深圳市中微信息技术有限公司 | A kind of intelligence follows unmanned vehicle and its control method |
| GB2567299B (en) * | 2017-08-21 | 2022-06-29 | Patrick Ettridge Snr John | Rotary wing flying machine |
| GB2567299A (en) * | 2017-08-21 | 2019-04-10 | Patrick Ettridge Snr John | Rotary wing flying machine |
| CN108045601A (en) * | 2017-12-22 | 2018-05-18 | 南京航空航天大学 | A kind of spacecraft return capsule using extension type jet autorotating rotor system |
| CN108045601B (en) * | 2017-12-22 | 2023-07-25 | 南京航空航天大学 | Spacecraft return cabin adopting retractable jet autorotation rotor system |
| CN113232853A (en) * | 2021-04-02 | 2021-08-10 | 陈�峰 | Short-distance take-off and landing aircraft |
| CN113232888A (en) * | 2021-06-08 | 2021-08-10 | 南京航空航天大学 | Variant rotor drone |
| CN113353287A (en) * | 2021-07-13 | 2021-09-07 | 南京航空航天大学 | Darkroom test device and paddle |
| CN113353253A (en) * | 2021-07-13 | 2021-09-07 | 南京航空航天大学 | Rotor-fixed wing combined target drone |
| CN114426098A (en) * | 2022-02-28 | 2022-05-03 | 上海埃依斯航天科技有限公司 | Novel dish wing |
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Application publication date: 20150715 |