CN103057702B - Jet-propelled type helicopter with rotating wings - Google Patents
Jet-propelled type helicopter with rotating wings Download PDFInfo
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- CN103057702B CN103057702B CN201210575392.5A CN201210575392A CN103057702B CN 103057702 B CN103057702 B CN 103057702B CN 201210575392 A CN201210575392 A CN 201210575392A CN 103057702 B CN103057702 B CN 103057702B
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Abstract
The present invention relates to a kind of jet-propelled type helicopter with rotating wings, comprise rotor, fuselage, undercarriage and roller, described fuselage lower end is provided with undercarriage, and undercarriage lower end is provided with multiple rollers that slide for rising and falling; Fuselage upper end is hinged with a horizontally disposed rotor by a rotor shaft, this rotor is made up of the rotor fin of branched radial equipartition, jet wing tip is all installed/be shaped with to described rotor fin, its concrete structure is, in a most advanced and sophisticated side of rotor fin, one shower nozzle is all installed, the plurality of shower nozzle all by pipeline connect one be arranged on engine in fuselage and, described afterbody is provided with a vertical propelling screws, and this propelling screws is by independent motor driven. The present invention is simple in structure, stable, failure rate is low, control are effective, can realize without sliding race tilting to take off and accurate vertical landing, and can greatly improve the useful load of helicopter, volume urine is in settling and vibrating littlely, and it all can increase significantly in load, voyage, performance.<!--1-->
Description
Technical field
The invention belongs to unmanned plane technical field, relate to rotor craft, especially a kind of jet-propelled revolvingWing helicopter.
Background technology
At present, it is to provide power by built-in motor that unmanned plane helicopter produces power, conventional startingMachine type has fuel engines, cylinder piston type engine or turbo type engine, engineRotary power is offered to a vertical parallel shaft, company of output of this vertical parallel shaftConnect the screw of six monomers, the propeller blade of these six monomers is horizontally rotated, like this, propeller blade cuts its upper stationary air, and the still air after being cut has just produced oneThe air stream flowing downward, air stream produces lift upwards to screw simultaneously, suchUnder the effect of active force and reaction force, helicopter is gone up in the air.
Gyroplane just refers to that its lift is all or part of and has the large of vertical axis by one (or multiple)Diameter spiral oar provides, and this screw is called " rotor " or " rotor blade ", before itPrecession power is to be provided by engine-driven advancing blade, and gyroplane needs certain in the time taking offSliding race of distance accelerate. Specifically, gyroplane is actually a kind of between helicopter and fixingAircraft between wing aircraft, removes outside rotor, also with a secondary vertical propelling spiral of placingOar is so that the power advancing to be provided, and generally less wing is also housed provides part lift awing. The maximum difference of gyroplane and pure helicopter is, the rotor of gyroplane not with engine transmissionSystem is connected, and engine is not to drive rotor to provide lift for aircraft, but before gyroplaneEnter in process, blow rotor wing rotation produce lift by air-flow, rotor system is only in the time of starting conventionallyDriven by self power, be referred to as to prewhirl, after taking off, drive by air effect power; And go straight up toThe rotor of machine is connected with engine driving system, can produce lift, and the moving of flight can be provided againPower. Because rotor is rotation type, be delivered to moment of torsion on fuselage very little, therefore gyroplane withoutThe tail-rotor that single-rotor helicopter is such, but empennage is generally housed, to control flight.
Current depopulated helicopter power drive system more complicated, is driven by gearbox by engineMain rotor, also will drive rear to stick up the empennage fortune on tail by the transmission mechanism of very long complexityMoving, complicated dynamic structure extremely makes people's headache like this. In addition, in the dynamical system of helicopterRotor also easily accidents caused, in the process that tail-rotor turns in low latitude be very easy to and treetop,The objects such as high-voltage line bump against, and tail-rotor is once fracture will cause comparatively serious the flying of helicopter grade out of controlOccur therefore act.
Find following Patents document through retrieval.
A kind of wind wheel single rotor helicopter (CN101284569B), by fuselage, engine, masterThe wind wheel single rotor of rotor, wind wheel, Hydraulic Power Transmission System, fuel tank and undercarriage composition is gone straight up toAircraft. Be characterized in driving again wind wheel contrary main by engine band hydraulic motor or buncherThe rotation that rotor direction rotation produces horizontal moment of torsion and removes balance fuselage, therefore without conventional helicoptersLong-tail beam and tail-rotor. And in the time of engine failure, except adopting traditional main rotor spin landing, be also furnished with the safety devices such as parachute, life saving air bag and lifesaving ring air cushion outward, these measures altogetherSame-action just can reduce to minimum to the injury of human body and helicopter by accident. The present invention carries for peopleSupplied a kind of compact conformation, flight freely, ride comfort, easy driving easy to learn, good looking appearanceRelatively safer helicopter. Can make large, medium and small type helicopter, when making minicomputerWhile sitting 4～5 people, as a kind of walking-replacing tool, its function can be positioned " aerial car ".
A kind of mechanical manoeuvring system (CN10186976 that is suitable for wireless remotecontrol single-rotor wing model helicopter9B), comprise a pair of mixing rocking arm, be located at respectively described rotor folder both sides, and by its middle partAxis hole and the mixing rocking arm of rotor folder both sides be rotatably connected; Wherein each mixing rocking arm two endsHave a control point, first pair of control point that wherein in a pair of mixing rocking arm, diagonal angle is relative is subject to from watchingThe machine that takes combines the cyclic torque control of transmitting to pitch, and second pair of relative control of diagonal angleSystem point is subject to the balance sysmte control of helicopter, and by the second pair of control point of balance sysmte control withFirst pair of control point support motion each other being controlled by pitch combination. In addition, the machine of helicopterTool longitudinal axis is within the scope of 70 °～20 ° of the contrary rotor wing rotation direction of the longitudinal axis of model copter; And the mechanical transversal line of helicopter is in 70 of the contrary rotor wing rotation direction of the transverse axis of model copter°～20 ° within the scope of. Possesses the single-rotor wing model helicopter of this control system, relativelyStable being easy to handled.
A kind of aircraft blade bush structure (CN202358298U) for helicopter assembling. ThisBrightly formed described turret head and lay respectively at the position up and down of body by two turret heads and bodyForm an entirety with body. The present invention adopts two turret heads to prevent that body from rotating and sliding,Be skillfully constructed, simple in structure, can make blade lining there is better reliability.
A kind of method of controlling and regulating thering is the rotor craft of high and stable gait of march(CN102267561A), this rotor craft comprises at least one main lifting rotor, at leastVariablepiston propelling screws and at least one is for driving main rotor and at least one spiral shellRevolve the power set of oar, described method comprises: use the first loop, so that pitching or attitude are enteredRow regulate, and with second servo loop to adjust by propelling screws is averaged to pitch controlJoint speed, wherein the method also comprises by carry out level of control tail plane with tertiary circuitDeflection angle, thus for given gait of march and attitude, make by main rotor and advance spiral shellRevolve the total output minimum that oar consumes, and tertiary circuit for to tailplane plane described partiallyCorner is controlled and is regulated.
By analysis, there is relatively big difference in the disclosed technology contents of above patent and present patent application.
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, fortune is providedLine stabilization, failure rate is low, the effective jet-propelled type helicopter with rotating wings of control.
The present invention solves its technical problem and takes following technical scheme to realize:
A kind of jet-propelled type helicopter with rotating wings, comprises rotor, fuselage, undercarriage and roller, described machineBody lower end is provided with undercarriage, and undercarriage lower end is provided with multiple rollers that slide for rising and falling;Fuselage upper end is hinged with a horizontally disposed rotor by a rotor shaft, and this rotor is by radially branchedUniform rotor fin composition, is characterized in that: the jet wing is all installed/be shaped with to described rotor finPoint, its concrete structure is, in a most advanced and sophisticated side of rotor fin, one shower nozzle is all installed, the plurality ofShower nozzle all connects an engine being arranged in fuselage by pipeline.
And described afterbody is provided with a vertical propelling screws, this propelling screws is by listOnly motor driven.
And the shoe upper rear that described fuselage tail is fixedly mounted with is provided with an adjustable small propeller。
And described jet wing tip comprises rotor fin and microjet, rotor finOne side is all provided with a microjet.
And described microjet adopts employing pulse-jet motor or punching simple in structurePress jet engine.
And described rotor is made up 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 rotor wing tip, and driving rotor wing rotation sprays paintThereby cause anti-twisted power, the engine compressed air in fuselage sprays backward from wing tip, just canPromotion blade rotates, and because oar axle is not driving shaft, rotor rotates does not have anti-twisted power, so notNeed tail-rotor, simplified overall structure, that has avoided that empennage easily ruptures and to cause in-flight is multipleProblem.
2, this heligyro is realized VTOL with jet wing tip, and bows apart from control with the cycle of rotorFace upward and roll, fly the stage flat, the control of pneumatic rudder face assisting in flying, wing produced in the flat stage that fliesLift raw over half, the pitch of rotor reduces to minimum, by air force spin, reduces resistancePower.
3, taking off and accurate vertical landing without sliding race inclination of this heligyro, has not only greatly reducedTo the requirement of airfield runway and headroom, also because the space of rising and falling is not overlapping, in fact increase sameDeng the capacity of the sortie that rises and falls in space, airport.
4, this heligyro adopts reaction power plant, useful year of can greatly improve helicopterLotus, volume urine is in settling and vibrating littlely, and it all can have aobvious in load, voyage, performanceThe raising of work.
5, simple in structure, stable, the failure rate is low of the present invention, control are effective, can realize nothingSliding race tilts to take off and accurate vertical landing, and can greatly improve the useful load of helicopter,Volume urine is in settling and vibrating littlely, and it all can have significantly in load, voyage, performanceImprove.
Brief description of the drawings
Fig. 1 is structural front view of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing and by specific embodiment, the invention will be further described, following examplesBeing descriptive, is 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, undercarriage 9 and roller 8, instituteState fuselage lower end undercarriage is installed, undercarriage lower end is provided with multiple rolling of sliding for rising and fallingWheel; Fuselage upper end is hinged with a horizontally disposed rotor by a rotor shaft 3, and this rotor is by branchedThe rotor fin composition of radial equipartition, is generally three to eight rotor fin compositions, the present embodimentAccompanying drawing is depicted as four rotor fins.
Innovative point of the present invention is:
The tip of described rotor fin is jet wing tip, and its concrete structure is: described jet wing tip comprisesRotor fin and shower nozzle 2, a most advanced and sophisticated side of rotor fin is all provided with a shower nozzle, the plurality of sprayHead all connects one by pipeline and is arranged on starting in fuselageMachine (not shown), fuel can easily be carried to wing tip under the effect of centrifugal force.
For power is provided better, described afterbody is provided with a vertical propelling screws 5, shouldPropelling screws is by independent motor driven.
For controlling party better to, shoe 7 upper rear that are also fixedly mounted with at fuselage tail are provided with adjustableFormula 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, the tip one of rotor finSide is all provided with a microjet, and this microjet requires must be gently little, thisIn embodiment, adopt employing pulse-jet motor or ramjet simple in structure. ByBe not driving shaft in rotor shaft, rotor rotates does not have anti-twisted power, so do not need tail-rotor, simplifiesOverall structure.
This heligyro possesses the advantage of helicopter, fixed wing aircraft and gyroplane simultaneously, canHovering, can realize vertical/STOL, and have good control, can meet manyPlanting short distance navigation needs.
Although disclose for the purpose of illustration embodiments of the invention and accompanying drawing, the technology people of this areaMember is understood that not departing from the spirit and scope of the present invention and claims, variousIt is all possible replacing, changing and revise, and therefore, scope of the present invention is not limited to embodimentWith the disclosed content of accompanying drawing.
Claims (1)
1. a jet-propelled type helicopter with rotating wings, comprises rotor, fuselage, undercarriage and roller, and described fuselage lower end has been provided withThe frame that falls, undercarriage lower end is provided with multiple rollers that slide for rising and falling; Fuselage upper end is hinged with a level by a rotor shaft and establishesThe rotor of putting, this rotor is made up of the rotor fin of branched radial equipartition, it is characterized in that: described rotor fin is all installed/is shaped withJet wing tip, its concrete structure is, in a most advanced and sophisticated side of rotor fin, one shower nozzle is all installed, the plurality of shower nozzle all passes through pipelineConnect an engine being arranged in fuselage;
Described afterbody is provided with a vertical propelling screws, and this propelling screws is by independent motor driven; Described machineThe shoe upper rear that body tail is fixedly mounted with is provided with an adjustable small propeller; Described jet wing tip comprises the tip of rotor finAnd microjet, a side of rotor fin is all provided with a microjet, and described microjet is adoptedWith pulse-jet motor simple in structure or ramjet;
Described rotor is made up 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 CN103057702A (en) | 2013-04-24 |
| CN103057702B true 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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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318405B (en) * | 2013-07-17 | 2015-11-18 | 国家电网公司 | A kind of unmanned plane |
| DE102014006112A1 (en) * | 2014-04-29 | 2015-10-29 | Autogyro Ag | aircraft |
| 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 |
| DE202017106992U1 (en) * | 2017-11-17 | 2017-11-30 | SCHOPPE DEVELOPMENT UG (haftungsbeschränkt) | gyrocopter |
| KR20200136470A (en) * | 2018-03-28 | 2020-12-07 | 데왈치 디버시파이드 엘피 | Aircraft propulsion and torque mitigation technology |
| CN110228585B (en) * | 2019-06-14 | 2022-11-22 | 安徽工业大学 | Combined wing aircraft |
| 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 |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1437669A (en) * | 1965-03-26 | 1966-05-06 | Marchetti Soc Charles | Vertical or short take-off 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 |
| HU227465B1 (en) * | 2009-08-04 | 2011-06-28 | Ferenc Apolczer | Method for constructing rotor blade with upraised boundary layer and rotor blade |
| US8931731B2 (en) * | 2010-11-02 | 2015-01-13 | Groen Brothers Aviation, Inc. | Tail jet apparatus and method for low speed yaw control of a rotorcraft |
| FR2969577B1 (en) * | 2010-12-22 | 2012-12-21 | Eurocopter France | AIRCRAFT HAVING BACK-UP 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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