CN103057702A - Jet-propelled rotor helicopter - Google Patents
Jet-propelled rotor helicopter Download PDFInfo
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- CN103057702A CN103057702A CN2012105753925A CN201210575392A CN103057702A CN 103057702 A CN103057702 A CN 103057702A CN 2012105753925 A CN2012105753925 A CN 2012105753925A CN 201210575392 A CN201210575392 A CN 201210575392A CN 103057702 A CN103057702 A CN 103057702A
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Abstract
The invention relates to a jet-propelled rotor helicopter which comprises a rotor, a fuselage, an undercarriage and rollers. The lower end of the fuselage is provided with the undercarriage. The lower end of the undercarriage is provided with a plurality of rollers used for takeoff and landing running. The upper end of the fuselage is hinged with a horizontally arranged rotor through a rotor shaft, and the rotor is composed of a plurality of rotor wing panels uniformly distributed along a radial direction. Each rotor wing panel is equipped/fabricated with a jet wing tip; specifically speaking, each rotor wing panel is provided with a nozzle at the side of the tip of the rotor wing panel, and a plurality of the nozzles are connected with an engine mounted in the fuselage through pipelines. The tail of the fuselage is provided with a vertical propulsive propeller which is driven by an individual engine. The jet-propelled rotor helicopter provided by the invention has the advantages of a simple structure, stable operation, a low failure rate, a good control effect, capacity of realizing running-free inclined takeoff and quasi-vertical landing and substantially increasing useful load of the helicopter, a small volume, convenience in placing, small vibration and substantially improved load, air-range and performance.
Description
Technical field
The invention belongs to the unmanned plane technical field, relate to rotor craft, especially a kind of jet-propelled type helicopter with rotating wings.
Background technology
At present, it is to provide power by built-in motor that the unmanned plane helicopter produces power, engine type commonly used has fuel engines, cylinder piston type driving engine or turbo type engine, driving engine is individual to offer a vertical parallel shaft with rotary power, screw propeller that connects six monomers of the mouth of this vertical parallel shaft, the propeller blade of these six monomers is horizontally rotated, like this, propeller blade cuts its upper stationary air, still air after being cut has just produced an air stream that flows downward, air stream produces lift upwards to screw propeller simultaneously, and under the effect of such application force and antagonistic force, helicopter is gone up in the air.
Cyclogyro just refers to that its lift is all or part of and is had by one (or a plurality of) that the major diameter screw propeller of vertical axis provides, this screw propeller is called " rotor " or " rotor blade ", its onward impulse then is to be provided by engine-driven advancing blade, and cyclogyro needs sliding race of certain distance to accelerate when taking off.Specifically, cyclogyro is actually a kind of aircraft between helicopter and fixed wing aircraft, remove outside the rotor, also with a secondary vertical propelling screws of placing so that the power that advances to be provided, generally less wing also is housed provides part lift awing.The maximum difference of cyclogyro and pure helicopter is, the rotor of cyclogyro does not link to each other with engine driving system, driving engine is not to drive rotor to provide lift for aircraft, but in cyclogyro advances process, blow rotor wing rotation by air-flow and produce lift, usually rotor system is only driven by self power when starting, is referred to as to prewhirl, and drives by air effect power after taking off; And the rotor of helicopter links to each other with engine driving system, can produce lift, and the power of flight can be provided again.Because rotor is rotation type, the moment of torsion that is delivered on the fuselage is very little, so cyclogyro need not the such tail-rotor of single-rotor helicopter, but empennage generally is housed, so that control flight.
Present depopulated helicopter power drive system more complicated drives main rotor by driving engine by change speed gear box, also will drive the empennage that sticks up on tail at the rear by the transmission device of very long complexity and move, and complicated dynamic structure extremely makes people's headache like this.In addition, the rotor on the power system of helicopter is also accidents caused easily, and tail-rotor is very easy in the process that the low latitude turns to and the objects such as treetop, high tension cord bump against, and tail-rotor will be once fracture will cause the comparatively serious aircraft accident of helicopter grade out of control to occur.
Find following Patents document through retrieval.
A kind of wind wheel single rotor helicopter (CN101284569B), the wind wheel single rotor helicopter that is formed by fuselage, driving engine, main rotor, wind wheel, power hydraulic system, fuel tank and alighting gear.Be characterized in that driving the contrary main rotor direction rotation of wind wheel by driving engine band HM Hydraulic Motor or buncher produces the rotation that horizontal moment of torsion removes the balance fuselage again, therefore without long-tail beam and the tail-rotor of conventional helicopters.And when engine breakdown, except adopting traditional main rotor spin landing, also be furnished with the safety facilities such as parachute, life saving air bag and lifesaving ring air cushion, these measure combineds action just can reduce to minimum to the injury of human body and helicopter with accident.The present invention for people provide a kind of compact conformation, flight freely, ride comfort, easy driving easy to learn, good looking appearance and relative safer autogyro.Can make large, medium and small type helicopter, when making minicomputer seat 4～5 people, as a kind of walking-replacing tool, its function can be positioned " aerial small passenger car ".
A kind of mechanical manoeuvring system (CN101869769B) that is suitable for the radio telecommand single-rotor wing model helicopter comprises a pair of mixing rocking arm, is located at respectively described rotor folder both sides, and is rotatably connected by the axis hole at its middle part and the mixing rocking arm of rotor folder both sides; Wherein each mixing rocking arm two ends has a controlling point, first pair of controlling point that wherein diagonal angle is relative in a pair of mixing rocking arm controlled by the cyclic torque that combination is transmitted from the servo to the tilting frame, and second pair of relative controlling point of diagonal angle controlled by the balanced system of helicopter, and by the second pair of controlling point of balanced system control with by first pair of controlling point of tilting frame combination control support motion each other.In addition, the mechanical longitudinal axis of helicopter is in 70 °～20 ° scopes of the contrary rotor wing rotation direction of the longitudinal axis of model copter; And the mechanical lateral axis of helicopter is in 70 °～20 ° scopes of the contrary rotor wing rotation direction of the transverse axis of model copter.The single-rotor wing model helicopter that possesses this maneuvering system, relatively stable being easy to handled.
A kind of aircraft blade bush structure (CN202358298U) for the autogyro assembling.The present invention is comprised of two six-sided heads and body, described six-sided head and lay respectively at the up and down position of body and body consists of an integral body.The present invention adopts two six-sided heads to prevent that body from rotating and slides, be skillfully constructed, simple in structure, can make the blade lining have better reliability.
A kind of method (CN 102267561A) that rotor craft with high and stable gait of march is controlled and regulated, this rotor craft comprises at least one main lifting rotor, at least one variablepiston propelling screws and at least one are used for driving the engine installation of main rotor and at least one screw propeller, described method comprises: use the first loop, so that pitching or attitude are regulated, with with second servo loop to come governing speed by propelling screws is averaged pitch control, wherein the method also comprises by control the angle of inclination on tailplane plane with tertiary circuit, thereby for given gait of march and attitude, make the total output that is consumed by main rotor and propelling screws minimum, and tertiary circuit is used for the described angle of inclination on tailplane plane are controlled and regulated.
By analysis, the disclosed technology contents of above patent and present patent application exist more different.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art part, a kind of simple in structure, stable, failure rate is low, the effective jet-propelled type helicopter with rotating wings of control are provided.
The present invention solves its technical matters and takes following technical scheme to realize:
A kind of jet-propelled type helicopter with rotating wings comprises rotor, fuselage, alighting gear and roller, and described fuselage lower end is equipped with alighting gear, and the alighting gear lower end is equipped with a plurality of rollers that slide be used to rising and falling; The fuselage upper end is hinged with a horizontally disposed rotor by a rotor shaft, this rotor is comprised of the rotor fin of branched radial equipartition, it is characterized in that: jet wing tip is all installed/be shaped with to described rotor fin, its concrete structure is that the side at the tip of rotor fin all is equipped with a shower nozzle, and these a plurality of shower nozzles all connect a driving engine that is installed in the fuselage by pipeline.
And described afterbody is equipped with a vertical propelling screws, and this propelling screws is by independent engine drive.
And the shoe upper rear that described fuselage tail is fixedly mounted with is equipped with an adjustable small propeller.
And described jet wing tip comprises rotor fin and microjet, and a side of rotor fin all is equipped with a microjet.
And described microjet adopts employing pulse-jet motor or athodyd simple in structure.
And described rotor is comprised of three to eight rotor fins of radial equipartition.
Advantage of the present invention and good effect are:
1, jet wing tip is installed/be shaped with to this heligyro at the rotor wing tip, thereby the driving rotor wing rotation that sprays paint causes anti-twisted power, engine compressed air in the fuselage sprays backward from wing tip, just can promote blade rotates, because the oar axle is not axle drive shaft, rotor rotates does not have anti-twisted power, so do not need tail-rotor, simplified integral structure, the various problems of having avoided empennage in-flight to rupture easily and to cause.
2, this heligyro is realized vertical takeoff and landing (VTOL) with jet wing tip, and with cycle of rotor apart from control pitching and roll, fly the stage putting down, pneumatic rudder face assisting in flying control, wing produces lift over half in the flat stage that flies, and the pitch of rotor reduces to minimum, by the aerodynamic force spin, reduce resistance.
3, taking off and accurate vertical landing without sliding race inclination of this heligyro not only greatly reduced the requirement to airfield runway and headroom, also because the space of rising and falling is not overlapping, in fact increased the capacity of the sortie that rises and falls in the space, equal airport.
4, this heligyro adopts reaction power plant, can greatly improve the useful load of helicopter, and volume is urinated in settling and vibrating littlely, and it all can increase significantly on load, voyage, performance.
5, simple in structure, stable, the failure rate is low of the present invention, control are effective, can realize tilting to take off and accurate vertical landing without sliding the race, and can greatly improve the useful load of helicopter, volume is urinated in settling and vibrating littlely, and it all can increase significantly on load, voyage, performance.
Description of drawings
Fig. 1 is structural front view of the present invention.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing and by specific embodiment, and following examples are descriptive, are not determinate, can not limit protection scope of the present invention with this.
A kind of jet-propelled type helicopter with rotating wings comprises rotor 1, fuselage 4, alighting gear 9 and roller 8, and described fuselage lower end is equipped with alighting gear, and the alighting gear lower end is equipped with a plurality of rollers that slide be used to rising and falling; The fuselage upper end is hinged with a horizontally disposed rotor by a rotor shaft 3, and this rotor is comprised of the rotor fin of branched radial equipartition, is generally three to eight rotor fins and forms, and the present embodiment accompanying drawing is depicted as four rotor fins.
Innovative point of the present invention is:
The tip of described rotor fin is jet wing tip, its concrete structure is: described jet wing tip comprises rotor fin and shower nozzle 2, one side at the tip of rotor fin all is equipped with a shower nozzle, these a plurality of shower nozzles all connect a driving engine (not shown) that is installed in the fuselage by pipeline, and fuel can easily be carried to wing tip under the effect of centnifugal force.
For power is provided better, described afterbody is equipped with a vertical propelling screws 5, and this propelling screws is by independent engine drive.
For controlling party better to, shoe 7 upper rear that also are fixedly mounted with at the fuselage tail are equipped with adjustable small propeller 6.
The jet wing tip structure of another embodiment of the present invention is as follows:
Described jet wing tip comprises rotor fin and microjet 2, tip one side of rotor fin all is equipped with a microjet, this microjet requires must be gently little, adopts employing pulse-jet motor or athodyd simple in structure in the present embodiment.Because rotor shaft is not axle drive shaft, rotor rotates does not have anti-twisted power, so do not need tail-rotor, has simplified integral structure.
This heligyro possesses the advantage of helicopter, fixed wing aircraft and cyclogyro simultaneously, can hover, and can realize vertical/short take-off and landing (STOL), and have preferably control effort, can satisfy multiple short distance navigation needs.
Although disclose for the purpose of illustration embodiments of the invention and accompanying drawing, but it will be appreciated by those skilled in the art that: in the spirit and scope that do not break away from the present invention and claims, various replacements, variation and modification all are possible, therefore, scope of the present invention is not limited to embodiment and the disclosed content of accompanying drawing.
Claims (6)
1. a jet-propelled type helicopter with rotating wings comprises rotor, fuselage, alighting gear and roller, and described fuselage lower end is equipped with alighting gear, and the alighting gear lower end is equipped with a plurality of rollers that slide be used to rising and falling; The fuselage upper end is hinged with a horizontally disposed rotor by a rotor shaft, this rotor is comprised of the rotor fin of branched radial equipartition, it is characterized in that: jet wing tip is all installed/be shaped with to described rotor fin, its concrete structure is that the side at the tip of rotor fin all is equipped with a shower nozzle, and these a plurality of shower nozzles all connect a driving engine that is installed in the fuselage by pipeline.
2. jet-propelled type helicopter with rotating wings according to claim 1, it is characterized in that: described afterbody is equipped with a vertical propelling screws, and this propelling screws is by independent engine drive.
3. jet-propelled type helicopter with rotating wings according to claim 1, it is characterized in that: the shoe upper rear that described fuselage tail is fixedly mounted with is equipped with an adjustable small propeller.
4. jet-propelled type helicopter with rotating wings according to claim 1, it is characterized in that: described jet wing tip comprises rotor fin and microjet, a side of rotor fin all is equipped with a microjet.
5. jet-propelled type helicopter with rotating wings according to claim 4 is characterized in that: described microjet employing employing pulse-jet motor or athodyd simple in structure.
6. jet-propelled type helicopter with rotating wings according to claim 1, it is characterized in that: described rotor is comprised of three to eight rotor fins of radial equipartition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210575392.5A CN103057702B (en) | 2012-12-25 | 2012-12-25 | Jet-propelled type helicopter with rotating wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210575392.5A CN103057702B (en) | 2012-12-25 | 2012-12-25 | Jet-propelled type helicopter with rotating wings |
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| Publication Number | Publication Date |
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| CN103057702A true CN103057702A (en) | 2013-04-24 |
| CN103057702B CN103057702B (en) | 2016-05-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210575392.5A Active CN103057702B (en) | 2012-12-25 | 2012-12-25 | Jet-propelled type helicopter with rotating wings |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318405A (en) * | 2013-07-17 | 2013-09-25 | 国家电网公司 | Unmanned plane |
| CN105473441A (en) * | 2014-04-29 | 2016-04-06 | 旋翼机股份公司 | Aircraft |
| CN106516102A (en) * | 2016-11-29 | 2017-03-22 | 中国直升机设计研究所 | Composite blade with wingtip jet function |
| CN110228585A (en) * | 2019-06-14 | 2019-09-13 | 安徽工业大学 | A kind of combination rotor aircraft |
| CN111356634A (en) * | 2017-11-17 | 2020-06-30 | 肖珀发展创业有限责任公司 | Rotorcraft |
| CN112173143A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Emergency substitution device for helicopter tail rotor in failure state and control method |
| CN112424065A (en) * | 2018-03-28 | 2021-02-26 | 德瓦尔奇多元化有限责任合伙公司 | Aircraft propulsion and torque mitigation techniques |
| CN113942636A (en) * | 2021-11-16 | 2022-01-18 | 深圳市龙云创新航空科技有限公司 | Composite rotor craft |
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| US3458160A (en) * | 1965-03-26 | 1969-07-29 | Marchetti Soc Charles | Rotating-wing aircraft |
| US4059247A (en) * | 1976-09-15 | 1977-11-22 | Prewitt Richard H | Convertiblade |
| CN101638147A (en) * | 2008-07-30 | 2010-02-03 | 余志刚 | Helicopter with separated tip jet device and main rotor wing |
| WO2011015891A1 (en) * | 2009-08-04 | 2011-02-10 | Ferenc Apolczer | Method for constructing rotor blade with upraised boundary layer and rotor blade |
| US20120104153A1 (en) * | 2010-11-02 | 2012-05-03 | Groen Brothers Aviation, Inc | Gyroplane prerotation by compressed air |
| CN102530249A (en) * | 2010-12-22 | 2012-07-04 | 尤洛考普特公司 | Aircraft provided with a tilting rear rotor and associated method |
| CN203020542U (en) * | 2012-12-25 | 2013-06-26 | 天津全华时代航天科技发展有限公司 | Jet-propelled rotor helicopter |
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2012
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US3458160A (en) * | 1965-03-26 | 1969-07-29 | Marchetti Soc Charles | Rotating-wing aircraft |
| US4059247A (en) * | 1976-09-15 | 1977-11-22 | Prewitt Richard H | Convertiblade |
| CN101638147A (en) * | 2008-07-30 | 2010-02-03 | 余志刚 | Helicopter with separated tip jet device and main rotor wing |
| WO2011015891A1 (en) * | 2009-08-04 | 2011-02-10 | Ferenc Apolczer | Method for constructing rotor blade with upraised boundary layer and rotor blade |
| US20120104153A1 (en) * | 2010-11-02 | 2012-05-03 | Groen Brothers Aviation, Inc | Gyroplane prerotation by compressed air |
| CN102530249A (en) * | 2010-12-22 | 2012-07-04 | 尤洛考普特公司 | Aircraft provided with a tilting rear rotor and associated method |
| CN203020542U (en) * | 2012-12-25 | 2013-06-26 | 天津全华时代航天科技发展有限公司 | Jet-propelled rotor helicopter |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318405A (en) * | 2013-07-17 | 2013-09-25 | 国家电网公司 | Unmanned plane |
| CN103318405B (en) * | 2013-07-17 | 2015-11-18 | 国家电网公司 | A kind of unmanned plane |
| CN105473441A (en) * | 2014-04-29 | 2016-04-06 | 旋翼机股份公司 | Aircraft |
| CN106516102A (en) * | 2016-11-29 | 2017-03-22 | 中国直升机设计研究所 | Composite blade with wingtip jet function |
| CN106516102B (en) * | 2016-11-29 | 2018-10-02 | 中国直升机设计研究所 | A kind of composite material blade with wing tip air injection function |
| CN111356634A (en) * | 2017-11-17 | 2020-06-30 | 肖珀发展创业有限责任公司 | Rotorcraft |
| CN112424065A (en) * | 2018-03-28 | 2021-02-26 | 德瓦尔奇多元化有限责任合伙公司 | Aircraft propulsion and torque mitigation techniques |
| CN110228585A (en) * | 2019-06-14 | 2019-09-13 | 安徽工业大学 | A kind of combination rotor aircraft |
| CN112173143A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Emergency substitution device for helicopter tail rotor in failure state and control method |
| CN112173143B (en) * | 2020-09-25 | 2022-09-13 | 中国直升机设计研究所 | Emergency substitution device for helicopter tail rotor in failure state and control method |
| CN113942636A (en) * | 2021-11-16 | 2022-01-18 | 深圳市龙云创新航空科技有限公司 | Composite rotor craft |
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| Publication number | Publication date |
|---|---|
| CN103057702B (en) | 2016-05-18 |
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