CN202464126U - Rotor wing blade tip jet one-man flight vehicle - Google Patents
Rotor wing blade tip jet one-man flight vehicle Download PDFInfo
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- CN202464126U CN202464126U CN2011205205601U CN201120520560U CN202464126U CN 202464126 U CN202464126 U CN 202464126U CN 2011205205601 U CN2011205205601 U CN 2011205205601U CN 201120520560 U CN201120520560 U CN 201120520560U CN 202464126 U CN202464126 U CN 202464126U
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Abstract
The utility model relates to the technical field of flight vehicles, in particular to a rotor wing blade tip jet one-man flight vehicle. The rotor wing blade tip jet one-man flight vehicle comprises a flight vehicle body, and a rotor wing system, a power system, a control system and an electric and flight control system which are arranged on the flight vehicle body, wherein the rotor wing system comprises a propeller boss and paddles; the power system comprises an engine which is connected with a gas transmission pipeline and is arranged above the propeller boss, and the gas transmission pipeline is communicated with the paddles; the control system comprises an automatic inclinator and a control rod; the electric and the flight control system comprises a battery, an engine controller and a flight parameter instrument; and an oil tank for providing a fuel for the engine is arranged on the flight vehicle body. The rotor wing blade tip jet one-man flight vehicle is portable in structure, is convenient to operate, effectively solves the problem of centrifugal force caused by mounting the engine on a wing tip, overcomes the defects of low speed and the like of a jet flight vehicle using a turbofan engine by using a rotor wing, and has the advantages of high speed, strong rotation controllability, high safety in operation and the like.
Description
Technical field
The utility model relates to the vehicle technology field, the jet-propelled individual lift device of particularly a kind of rotor blade tip.
Background technology
At present; Individual lift device is divided into two types of jet-propelled and propeller types substantially; Wherein, Jet-propelled individual lift device sucks anterior gas when placing the turbine engine high-speed operation of fuselage both sides and sprays through the rear portion, thus the thrust that flies before obtaining, and both sides wing difference of pressure up and down to be individual lift device climb has obtained lift.Because this aircraft does not have wing, whole flight course all produces lifting flight by the engine drives ducted fan, therefore, has defectives such as speed is slow, voyage is near, cruise duration is short.And the propeller type aircraft mainly relies on the screw propeller that places the fuselage top to obtain the power of climbing and descending; Such aircraft is to prevent that fuselage produces the change of team certainly fuselage prolongation formation is similar to the tail of dragonfly Yan and on tail, adorns screw propeller in addition in order to control, thereby also obtains the control on the direction.
Wherein, The helicopter type individual lift device is made up of legacy devices such as fanjet, retarder, starter-generator, rotor, tail-rotor, transmission device, fuselages usually; Because bulky, complex structure, processing be meticulous, cost an arm and a leg, especially big the and preponderance of maintenance difficulties has limited it in the more especially use of civil area of wide field.
In addition; Also have a kind of in the prior art with the aircraft of engine installation at wing tip; Through the jet promotion rotor of the afterbody of driving engine, produce the effect be similar to the helicopter type aircraft, the aircraft of this structure is inhomogeneous owing to internal oil passages and temperature field under centrifugal action; The damage of driving engine is very serious, makes feasibility and reliability have great risk.
The utility model content
The technical matters that (one) will solve
The technical matters that the utility model will solve provides the jet-propelled individual lift device of a kind of rotor blade tip, and the volume that exists in the existing aircraft is big to overcome, complex structure, and the production costliness is not suitable for civilian use, and defective such as feasibility and safety be relatively poor.
(2) technical scheme
In order to address the above problem, the utility model provides a kind of rotor blade tip jet-propelled individual lift device, and it comprises: the aircraft body be arranged on rotor system, power system, maneuvering system and the electric and flight control system on the aircraft body;
The system includes a rotor blade paddle and valleys;
The power system includes an engine, said engine connecting gas transmission pipelines, the engine is set in the valley above the paddle, paddle said gas transmission pipeline and connected;
Said maneuvering system comprises auto-bank unit and control lever, is used to handle the state of kinematic motion and the sense of motion of aircraft;
Said electric and flight control system comprises battery and engine controller, flight parameter instrument;
Said aircraft body is provided with the fuel tank that fuel is provided for driving engine.
Further, said driving engine is a turbojet, and its quantity is two.
Further, said gas transmission pipeline comprises: gas collection casket, combustion gas distribution plate and mozzle; The two ends of said combustion gas distribution plate are connected with mozzle with the gas collection casket respectively, and said mozzle communicates with paddle.
Further, said aircraft body comprises main body rack, assembles safety strap, articulated joint, stretcher and alighting gear on the said main body rack, has stretcher on the alighting gear.
Further, said main body rack middle part is provided with the control lever cover, and said control lever puts and connects two control lever, and the other end of said control lever connects eccentric wheel.
Further, said flight parameter instrument comprises oil measurer and gyroplane rotate speed table, and said one of them control lever is provided with throttle valve, oil measurer and gyroplane rotate speed table.
Further, the end of the blade near the paddle grains having an air inlet.
Further, said aircraft body rear side is provided with the steering wheel that is used to control heading.
Further, said blade hollow is provided with, and its cross-sectional plane is a stream line pattern.
Further, said electric and flight control system also comprises gyroscope, increases control and stability augmentation system.
(3) beneficial effect
The jet-propelled individual lift device of rotor blade tip that the utility model provides; Structure is light, easy to operate; Effectively eliminated the centnifugal force problem that engine installation is caused at wing tip; Utilize rotor to overcome and use the jet-propelled aircraft speed of fanjet to wait defective slowly, it is fast to have a moving velocity, and the strong and safety in operation of rotation controllability is than advantages such as height.
Description of drawings
Fig. 1 is the jet-propelled individual lift device structural representation of the utility model embodiment rotor blade tip;
Fig. 2 is the jet-propelled individual lift device medium power of a utility model embodiment rotor blade tip system architecture scheme drawing.
Among the figure: 1: driving engine; 2: blade; 3: propeller hub; 4: gauge panel; 5: joystick; 6: safety strap; 7: steering wheel; 8: fuel tank; 9: the combustion gas distribution plate; 10: the gas collection casket; 11: alighting gear.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment, the specific embodiment of the utility model is described in further detail.Following examples are used to explain the utility model, but are not the scopes that is used for limiting the utility model.
Shown in Fig. 1-2, it comprises the jet-propelled individual lift device of the utility model embodiment rotor blade tip: the aircraft body be arranged on rotor system, power system, maneuvering system and the electric and flight control system on the aircraft body.
The system includes a rotor blade paddle valleys and 2, a seesaw-type rotor, fixed pitch, variable pitch propeller grains without hinges, hinge shimmy, using high lift airfoil blades 2, no negative twist.The cross-sectional plane of this blade 2 is a stream line pattern, and its hollow is provided with, and its gas is sprayed by blade tip.
Power system includes an engine, the engine is a gas transmission pipeline connecting the engine 1 is set in the valley above the paddle, paddle two gas transmission pipeline and connected.Which, in this embodiment of the turbojet engine 1, the specific number and the momentum needed according to the actual type of engine is determined, in this embodiment in an amount of both the engine 1, the two vertically disposed side by side in the engine 1 paddle above the valley.The gas transmission pipeline comprises: gas collection casket 10, combustion gas distribution plate 9 and mozzle; The two ends of combustion gas distribution plate 9 are connected with mozzle with gas collection casket 10 respectively, and mozzle communicates with paddle 2.Driving engine 1 afterbody links to each other with gas collection casket 10, and the high-temperature fuel gas of ejection is collected in the gas collection casket 10, passes through finally to be sprayed by blade tip in the blade 1 of hollow to importing through combustion gas distribution plate 9 and mozzle, thereby promotes the rotor rotation.
Maneuvering system comprises auto-bank unit and control lever 5, is used to handle the state of kinematic motion and the sense of motion of aircraft; Operating system is through auto-bank unit, and whole tilting rotor axle realizes that the oar dish tilts.Electric and flight control system comprises battery and engine controller, flight parameter instrument, gyroscope, increases control, stability augmentation system.The aircraft body comprises main body rack, and assembling safety strap 6, articulated joint and alighting gear 11 has stretcher on this alighting gear 11 on the main body rack.In addition, this aircraft body is provided with the fuel tank 8 that fuel is provided for driving engine.This alighting gear 11 adopts three wheeled layouts, can realize ground roll-out, is convenient to transportation.Human body weight supports through pedal, and safety strap through shoulder belt, waistband, hip band position 6 is fixed in body with human body, makes that the driver safety coefficient is able to guarantee.
Wherein, the main body rack middle part is provided with the control lever cover, and control lever puts and connects two control lever 5, and the other end of control lever 5 connects eccentric wheel.The flight parameter instrument comprises oil measurer and gyroplane rotate speed table, and one of them control lever 5 is provided with throttle valve, oil measurer and gyroplane rotate speed table.One of them control lever tip placement has oil measurer and gyroplane rotate speed table; Thereby rotate this control lever and make two the differential realization of engine thrust directional controls; Lift the rotating speed of these control lever 5 may command turbojet engines 1; Thereby realize gyroplane rotate speed control or increase engine thrust synchronously, realize that helicopter vertically climbs or tiltedly climbs.Can realize that through handling 5 motions of another one control lever helicopter vertically reaches crabbing.When the operator pulled control lever up or down, the eccentric wheel that is fixed in the control lever both sides rotated thereupon, and drive paddle 2 through connecting rod and swing, thus the blowing direction of change rotor, with the heading of controlling aircraft.
Wherein the paddle blade 2 near one end of the corn air inlet, the outside air through the ejector way into the inner rotor, thereby increasing the air flow, a greater thrust.Aircraft body rear side is provided with steering wheel 7, and the stability of body is strengthened in the generation of the phenomenon of avoiding spinning.
The jet-propelled individual lift device of rotor blade tip that the utility model provides; Structure is light, easy to operate; Effectively eliminated the centnifugal force problem that engine installation is caused at wing tip; Utilize rotor to overcome and use the jet-propelled aircraft speed of fanjet to wait defective slowly, it is fast to have a moving velocity, and the strong and safety in operation of rotation controllability is than advantages such as height.
Above embodiment only is used to explain the utility model; And be not the restriction to the utility model; The those of ordinary skill in relevant technologies field under the situation of spirit that does not break away from the utility model and scope, can also be made various variations and modification; Therefore all technical schemes that are equal to also belong to the category of the utility model, and the scope of patent protection of the utility model should be defined by the claims.
Claims (10)
1. the jet-propelled individual lift device of rotor blade tip is characterized in that, comprising: the aircraft body be arranged on rotor system, power system, maneuvering system and the electric and flight control system on the aircraft body;
The system includes a rotor blade paddle and valleys;
The power system includes an engine, said engine connecting gas transmission pipelines, the engine is set in the valley above the paddle, paddle said gas transmission pipeline and connected;
Said maneuvering system comprises auto-bank unit and control lever, is used to handle the state of kinematic motion and the sense of motion of aircraft;
Said electric and flight control system comprises battery and engine controller, flight parameter instrument;
Said aircraft body is provided with the fuel tank that fuel is provided for driving engine.
2. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that said driving engine is a turbojet.
3. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that, said gas transmission pipeline comprises: gas collection casket, combustion gas distribution plate and mozzle; The two ends of said combustion gas distribution plate are connected with mozzle with the gas collection casket respectively, and said mozzle communicates with paddle.
4. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that said aircraft body comprises main body rack, assembles safety strap, articulated joint and alighting gear on the said main body rack, has stretcher on the alighting gear.
5. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that, said main body rack middle part is provided with the control lever cover, and said control lever puts and connects two control lever, and the other end of said control lever connects eccentric wheel.
6. the jet-propelled individual lift device of rotor blade tip as claimed in claim 5 is characterized in that said flight parameter instrument comprises oil measurer and gyroplane rotate speed table, and said one of them control lever is provided with throttle valve, oil measurer and gyroplane rotate speed table.
As claimed in claim 1, wherein the rotor blade tip single jet aircraft, wherein said propeller blade close to the end of the corn with an air intake port.
8. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that, said aircraft body rear side is provided with the steering wheel that is used to control heading.
9. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that, said blade hollow is provided with, and its cross-sectional plane is a stream line pattern.
10. the jet-propelled individual lift device of rotor blade tip as claimed in claim 1 is characterized in that, said electric and flight control system also comprises gyroscope, increases control and stability augmentation system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205205601U CN202464126U (en) | 2011-12-13 | 2011-12-13 | Rotor wing blade tip jet one-man flight vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205205601U CN202464126U (en) | 2011-12-13 | 2011-12-13 | Rotor wing blade tip jet one-man flight vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202464126U true CN202464126U (en) | 2012-10-03 |
Family
ID=46912309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205205601U Withdrawn - After Issue CN202464126U (en) | 2011-12-13 | 2011-12-13 | Rotor wing blade tip jet one-man flight vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202464126U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501969A (en) * | 2011-12-13 | 2012-06-20 | 北京君研院科技有限公司 | One-man flight vehicle capable of jetting at points of rotor blades |
| CN103057704A (en) * | 2013-01-07 | 2013-04-24 | 南京航空航天大学 | Rotor-type one-man aircraft |
| CN105235892A (en) * | 2015-10-21 | 2016-01-13 | 北京航空航天大学 | Multimodal flight conversion control method for hybrid layout rotary-wing unmanned aerial vehicle |
-
2011
- 2011-12-13 CN CN2011205205601U patent/CN202464126U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501969A (en) * | 2011-12-13 | 2012-06-20 | 北京君研院科技有限公司 | One-man flight vehicle capable of jetting at points of rotor blades |
| CN102501969B (en) * | 2011-12-13 | 2014-07-16 | 北京君研院科技有限公司 | One-man flight vehicle capable of jetting at points of rotor blades |
| CN103057704A (en) * | 2013-01-07 | 2013-04-24 | 南京航空航天大学 | Rotor-type one-man aircraft |
| CN103057704B (en) * | 2013-01-07 | 2015-07-29 | 南京航空航天大学 | Rotor-type one-man aircraft |
| CN105235892A (en) * | 2015-10-21 | 2016-01-13 | 北京航空航天大学 | Multimodal flight conversion control method for hybrid layout rotary-wing unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20121003 Effective date of abandoning: 20140716 |
|
| RGAV | Abandon patent right to avoid regrant |