CN101117156A - Jetocopter - Google Patents
Jetocopter Download PDFInfo
- Publication number
- CN101117156A CN101117156A CNA2007101539758A CN200710153975A CN101117156A CN 101117156 A CN101117156 A CN 101117156A CN A2007101539758 A CNA2007101539758 A CN A2007101539758A CN 200710153975 A CN200710153975 A CN 200710153975A CN 101117156 A CN101117156 A CN 101117156A
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- CN
- China
- Prior art keywords
- jetocopter
- air blast
- rotor
- screw propeller
- airframe
- Prior art date
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Abstract
The invention discloses a jetocopter, which comprises an airframe 1, a rotor 8 and a tail rotor 4, and is characterized in that: both the left and the right sides of the airframe 1 are provided with gas ejectors 2; each gas ejector consists of a cylindrical outer frame 5 and an airscrew 6 arranged inside the cylindrical outer frame; the cylindrical outer frame 5 is connected with the turbo-engines 7 arranged at both sides of the airframe through a rotating mechanism; the airscrew 6 is connected with an accelerator 3 through a drive mechanism; in addition, the accelerator is connected with an additionally-arranged assistant main engine through a shaft coupling. Because the jetocopter is additionally provided with the gas ejectors capable of rotating 360 DEG C to increase the lift force of the jetocopter during taking off and landing, both cruising flight speed and flight safety factor are increased.
Description
Technical field
The present invention relates to a kind of spacecraft, be specifically related to a kind of screw propeller is combined with air blast and produce the jetocopter of lift and thrust.
Background technology
Present aircraft mainly is divided into fixed wing aircraft and utilizes screw propeller to produce the helicopter of lift.Fixed wing aircraft is to utilize powered generation air-flow to act on to produce lift on the fixed wing, and speed is fast, and steadily, but landing needs special place; Helicopter is because there are many other aircraft to be difficult to accomplish the advantage that maybe can not accomplish, be subjected to widespread use, helicopter is because the landing of can taking off vertically, without the large tracts of land airport, be mainly used in industries such as sightseeing tour, fire rescue, first aid at sea, anti-smuggling drug law enforcement, fire-fighting, commercial transport, medical rescue, communication and detection resource, it is that screw propeller provides lift that helicopter utilizes the engine drive rotor, helicopter is lifted holder aloft, propeller speed influences the lift of helicopter, and therefore helicopter has been realized taking off vertically and landing.But the speed of helicopter is slow, and breaks down at screw propeller or driving engine, and helicopter loses propulsive effort, air crash easily, and safety factor is lower.
Summary of the invention
The objective of the invention is provides a kind of being combined with air blast by screw propeller to produce the jetocopter of lift and thrust at the deficiencies in the prior art.
In order to achieve the above object, the present invention adopts following technical scheme: described jetocopter comprises fuselage, is positioned at the rotor by main force's driving engine drive of body upper, the tail-rotor of afterbody, it is characterized in that: the left and right sides at fuselage is provided with air blast, air blast is made up of cylindric housing and the screw propeller that is arranged in the cylindric housing, cylindric housing is connected with the turbo-dynamo that is arranged on the fuselage both sides by rotating mechanism, drive cylindric housing by turbo-dynamo and carry out 360 degree rotations, that is the drive air blast carries out 360 degree rotations; Screw propeller is connected with speed increaser by transmission device, speed increaser is connected with the secondary main force driving engine that other establishes by coupler, provide power to rotate generation thrust by secondary main force driving engine by the screw propeller that speed increaser drives air blast, when the different rotating speed of speed increaser output drives screw propeller, can obtain different thrust.When takeoff and landing, the rotor rotation that is driven by main force's driving engine produces lift, and adjust air blast downward jet generation thrust by turbo-dynamo this moment, makes fuselage obtain bigger lift; When aircraft flight, the direction of adjustment air blast forward or backward, can adjust the flying speed of aircraft, or the like, can adjust the landing or the state of flight of aircraft as required by the direction of adjusting air blast, and when main force's driving engine or rotor break down, utilize air blast can produce certain lift, aircraft can slowly be descended, avoid air crash, increase safety factor.
Jetocopter provided by the present invention is compared with traditional helicopter and since install additional can 360 the air blast of degree rotation, the lift when promoting takeoff and landing has been accelerated cruising flight speed, has improved the flight safety coefficient.
Description of drawings
Fig. 1 is the cross-section structure diagrammatic top view of jetocopter of the present invention.
Fig. 2 is the cutaway view of Fig. 1 along the A-A line.
The specific embodiment
In the structure shown in the figure, described jetocopter comprises fuselage 1, be positioned at the rotor 8 that is driven by main force's driving engine of body upper, the tail-rotor 4 that is positioned at afterbody, its feature is being to be provided with air blast 2 in the left and right sides of fuselage 1, air blast is made up of cylindric housing 5 and the screw propeller 6 that is arranged in the cylindric housing, cylindric housing 7 is connected with the turbo-dynamo 7 that is arranged on the fuselage both sides by rotating mechanism, carry out 360 degree by the cylindric housing 5 of turbo-dynamo 7 drives and rotate, that is drive air blast 2 carries out 360 degree rotations; Screw propeller 6 is connected with speed increaser 3 by transmission device, speed increaser is connected with the secondary main force driving engine that other establishes by coupler, provide power to pass through the screw propeller rotation generation thrust that speed increaser 3 drives air blast by secondary main force driving engine, when the different rotating speed of speed increaser 3 outputs drives screw propeller 6 rotations, can produce different thrust.When takeoff and landing, rotor 8 rotations that driven by main force's driving engine produce lift, and adjust air blast 2 downward jet generation thrusts by turbo-dynamo 7 this moment, makes fuselage obtain bigger lift, to adjust the speed of takeoff and landing; When aircraft flight, the direction of adjustment air blast 2 forward or backward, can adjust the flying speed of aircraft, or the like, adjust the landing or the state of flight of aircraft as required by the jet direction of adjusting air blast 2, and when main force's driving engine or rotor break down, utilize air blast 2 can produce certain lift, aircraft can slowly be descended, avoid air crash, increase safety factor.
Claims (1)
1. jetocopter, comprise fuselage [1], be positioned at the rotor [8] that drives by main force driving engine of body upper, the tail-rotor [4] that is positioned at afterbody, it is characterized in that: be provided with air blast [2] in the left and right sides of fuselage [1], air blast is made up of cylindric housing 5 and the screw propeller [6] that is arranged in the cylindric housing, cylindric housing [7] is connected with the turbo-dynamo that is arranged on the fuselage both sides [7] by rotating mechanism, screw propeller [6] is connected with speed increaser [3] by transmission device, and speed increaser is connected with the secondary main force driving engine that other establishes by coupler.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101539758A CN101117156A (en) | 2007-09-14 | 2007-09-14 | Jetocopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101539758A CN101117156A (en) | 2007-09-14 | 2007-09-14 | Jetocopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101117156A true CN101117156A (en) | 2008-02-06 |
Family
ID=39053459
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007101539758A Pending CN101117156A (en) | 2007-09-14 | 2007-09-14 | Jetocopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101117156A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101804863A (en) * | 2010-05-04 | 2010-08-18 | 刘辉 | Rotor wing helicopter |
| CN108082452A (en) * | 2017-12-04 | 2018-05-29 | 安徽工程大学 | A kind of jet reversing arrangement of aircraft |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN113815856A (en) * | 2021-10-22 | 2021-12-21 | 扬州工业职业技术学院 | VTOL gliding unmanned aerial vehicle |
-
2007
- 2007-09-14 CN CNA2007101539758A patent/CN101117156A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101804863A (en) * | 2010-05-04 | 2010-08-18 | 刘辉 | Rotor wing helicopter |
| CN108082452A (en) * | 2017-12-04 | 2018-05-29 | 安徽工程大学 | A kind of jet reversing arrangement of aircraft |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN113815856A (en) * | 2021-10-22 | 2021-12-21 | 扬州工业职业技术学院 | VTOL gliding unmanned aerial vehicle |
| CN113815856B (en) * | 2021-10-22 | 2023-08-25 | 扬州工业职业技术学院 | Vertical take-off and landing gliding unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Open date: 20080206 |