CN206520752U

CN206520752U - Double mode rotary wing aircraft based on folding wing

Info

Publication number: CN206520752U
Application number: CN201621363991.0U
Authority: CN
Inventors: 及兰平; 王旭
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-12-01
Filing date: 2016-12-01
Publication date: 2017-09-26
Anticipated expiration: 2026-12-01

Abstract

Title of the present utility model is：" the double mode rotary wing aircraft based on folding wing ", it is that folding wing is applied to rotary wing aircraft, enable airborne vehicle according to different mission phases, implement rotary wing aircraft offline mode and Fixed-Wing offline mode, so that it is provided simultaneously with the advantage of two class airborne vehicles.

Description

Double mode rotary wing aircraft based on folding wing

Technical field：

Title of the present utility model is：" the double mode rotary wing aircraft based on folding wing " belongs to aviation field.

Background technology：

Rotary wing aircraft (including helicopter and rotor VTOL aircraft), and Fixed-Wing is two kinds of different types Airborne vehicle, so that helicopter and fixed wing aircraft compare as an example, helicopter is to produce downwash flow by main rotor rotation to go straight up to Machine provides prevailing lift, and fixed wing aircraft is for aircraft to provide prevailing lift by wing, and the advantage and fixed-wing of helicopter are flown The advantage of machine is combined, and is always the direction technically made great efforts, if but by lifting airscrew, and fixed wing aircraft wing simultaneously Applied to an airplane, effect is conflicting between them, and prior art is difficult to solve this problem, and folding wing Appearance there is provided solve problem method.

The content of the invention：

The purpose of this utility model is：By the folding wing (patent No.：201620324195；201610228024.1；Folding The optimization patent No. of stacked wing：201610830956.3) rotary wing aircraft is applied to, so that by rotary wind type airborne vehicle and fixation Wing airborne vehicle is combined, and constitutes double mode rotary wing aircraft, the advantage for making it be provided simultaneously with two kinds of airborne vehicles.

Feature of the present utility model is：By technical measures, folding wing is applied to rotary wing aircraft, bimodulus is constituted Formula rotary wing aircraft, i.e.,；Rotary wing aircraft is taken off, landing phases, and lift is provided by rotor wing rotation, and implementation is taken off vertically, landed Pattern, in the rotary wing aircraft flat winged stage, implements fixed wing aircraft offline mode.

Further：By taking helicopter as an example, folding wing is applied to helicopter, double mode helicopter is constituted, folded Formula wing is arranged on helicopter fuselage bottom, takes off, landing phases, and wing-folding is drawn in below fuselage, by engine driving Main rotor rotation provides lift, by the Mode normal landing of helicopter；

Further：Unfolded formula wing when double mode helicopter is flat winged in the air, formation can produce the fixation machine of lift The wing, thrust (pulling force) propeller provides flying power, prevailing lift is provided by wing, by the mode flight of fixed wing aircraft；

Further：When double mode helicopter puts down winged in the air, main rotor tail-off is to save the energy, and rotor is in Free rotation state, now rotor can ensure the stability of aircraft and part lift can be provided；

Further：Double mode helicopter is before landing, and gathering has folded wing below fuselage, starts main rotor and starts Machine makes rotor wing rotation, closes thrust (pulling force) propeller, now, and double mode helicopter reverts to main rotor rotation and provides lift Offline mode, vertical landing；

Occupied little space after there is folding due to folding wing, the fixation machine that area expands several times can be formed after expansion The performance of the wing, can provide main lift, being installed on helicopter to accomplish for aircraft：Helicopter takes off or landed When make wing-folding, draw in below fuselage, to lifting airscrew rotate produce downwash flow it is unobstructed or only smaller resistance Gear, the lift effect produced to rotor is small；

Further：When putting down winged after helicopter lift-off, folded wing deploys to form the fixation wing that area expands several times, is Aircraft flight provides main lift.

The utility model is applied to helicopter and rotor VTOL aircraft, unmanned can be gone straight up to using polytype Machine, small-sized manned versions of helicopter, and small-sized manned and unpiloted rotor VTOL aircraft.

Brief description of the drawings：

The utility model is discussed in detail below in conjunction with the accompanying drawings：

Fig. 1 --- double mode single-rotor helicopter top view under wing-folding state；

Fig. 2 --- double mode single-rotor helicopter top view during wing expansion；

Double mode single-rotor helicopter top view when Fig. 3 --- wing expansion, tail-rotor adjustment；

Double mode single-rotor helicopter top view after the completion of Fig. 4 --- wing expansion, tail-rotor adjustment；

Double mode single-rotor helicopter lateral plan after the completion of Fig. 5 --- wing expansion, tail-rotor adjustment；

Double mode single-rotor helicopter front view after the completion of Fig. 6 --- wing expansion, tail-rotor adjustment；

Fig. 7 --- double mode single-rotor helicopter upward view under wing-folding state；

Fig. 8 --- double mode single-rotor helicopter upward view during wing expansion；

Fig. 9 --- double mode coaxial double-rotor helicopter top view under wing-folding state；

Figure 10 --- double mode coaxial double-rotor helicopter top view during wing expansion；

Figure 11 --- double mode coaxial double-rotor helicopter top view after wing expansion；

Figure 12 --- double mode coaxial double-rotor helicopter front view after wing expansion；

Figure 13 --- double mode coaxial double-rotor helicopter lateral plan after wing expansion；

Figure 14 --- rotor VTOL aircraft front view under folded storage position；

Figure 15 --- rotor VTOL aircraft top view under folded storage position；

Figure 16 --- rotor VTOL aircraft side view under folded storage position；

Figure 17 --- deploy rotor VTOL aircraft front view under state to be flown；

Figure 18 --- deploy rotor VTOL aircraft top view under state to be flown；

Figure 19 --- deploy rotor VTOL aircraft side view under state to be flown；

Figure 20 --- rotor VTOL aircraft front view under airflight state；

Numbered in accompanying drawing：

1- fuselages；2- folding wings；3--- main rotors；4--- tail-rotors, propelling screws；5--- undercarriages；6--- is total to Axle DCB Specimen；7--- propellers；8--- folds undercarriage；9--- tailplanes；10--- vertical tails；11--- movable pulleys；

Embodiment：

Embodiment is discussed in detail in control accompanying drawing below：

1st, the double mode single-rotor helicopter based on folding wing：

Folding wing (2) is arranged on single-rotor helicopter fuselage (1) bottom, double mode single-rotor helicopter is constituted；

Fig. 1 is double mode single-rotor helicopter top view under wing-folding state；

Fig. 7 is double mode single-rotor helicopter upward view under wing-folding state；

Helicopter is folded and drawn in fuselage (1) below in takeoff phase, wing (2), and Helicopter Main rotor (3) rotation is provided Lift, tail rotor (4) rotation keeps fuselage balance, and helicopter vertically goes up to the air；

Main rotor (3), which tilts generation horizontal direction component, after helicopter lift-off makes helicopter advance, then, unfolded formula Wing (2), the fixation wing of lift can be produced by becoming, meanwhile, tail-rotor (4) starts to rotate adjustment to tail direction, and Fig. 2 is Double mode single-rotor helicopter top view during wing expansion；Fig. 8 is double mode single-rotor helicopter during wing expansion Upward view；Double mode single-rotor helicopter top view when Fig. 3 is wing expansion, tail-rotor adjustment；

Helicopter tail rotor (4) is rotated by 90 ° angle, becomes the thrust propeller of helicopter, and folding wing (2) is complete Full expansion, constitutes the fixation wing of helicopter, double mode single-rotor helicopter is bowed after the completion of Fig. 4 is wing expansion, tail-rotor is adjusted View；Fig. 5 is double mode single-rotor helicopter lateral plan after the completion of wing expansion, tail-rotor adjustment；Fig. 6 is wing expansion, tail Double mode single-rotor helicopter front view after the completion of oar adjustment；Main rotor engine is closed, the angle of main rotor (3) blade is adjusted Degree, makes main rotor (3) be in free rotation state, now, and helicopter provides prevailing lift and preceding precession by main rotor (3) rotation The offline mode of power, is changed into and provides onward impulse by thrust propeller (4), and prevailing lift is provided by the wing (2) deployed Fixed wing aircraft offline mode, aircraft enters the flat winged stage,

Folding wing (2) is drawn in and is folded to below fuselage before landing by helicopter, and starting main rotor engine makes master Rotor (3) rotates, and thrust propeller, which is rotated by 90 °, reverts to helicopter tail rotor (4), and now, helicopter reverts to main rotor (3) Lift is provided, tail-rotor (4) keeps the offline mode of fuselage balance, helicopter vertical landing；

2nd, the double mode coaxial double-rotor helicopter based on folding wing：

Folding wing (2) is arranged on coaxial double-rotor helicopter fuselage (1) bottom, double mode coaxial double-rotary wing is constituted Helicopter；

Power-actuated propeller (7) is installed in head or tail, power is provided when flying for aircraft is flat, Fig. 9 is wing folding Double mode coaxial double-rotor helicopter top view under overlapping state；

Helicopter is folded and drawn in fuselage (1) below in takeoff phase, folding wing (2), coaxial double-rotary wing (6) rotation Lift is provided, helicopter vertically goes up to the air；

After helicopter lift-off, coaxial double-rotary wing (6), which tilts generation horizontal direction component, makes helicopter advance, propelling screws (7) start, the flat power that flies is provided for helicopter, meanwhile, unfolded formula wing (2), the fixation of lift can be produced by becoming Wing, Figure 10 is double mode coaxial double-rotor helicopter top view during wing expansion；

Hereafter, coaxial double-rotary wing engine is closed, rotor blade angle is adjusted, coaxial double-rotary wing (6) is in and freely revolves Turn state；

Now, helicopter is rotated the offline mode for providing prevailing lift and onward impulse by coaxial double-rotary wing (6), is changed into Onward impulse is provided by power spin oar (7), the fixed wing aircraft offline mode of prevailing lift is provided by the wing (2) deployed, Aircraft enters the flat winged stage；

Figure 11 is double mode coaxial double-rotor helicopter top view after wing expansion；

Figure 12 is double mode coaxial double-rotor helicopter front view after wing expansion；

Figure 13 is double mode coaxial double-rotor helicopter lateral plan after wing expansion；

Helicopter is before landing, and folding wing (2), which is folded, to be drawn in fuselage (1) below, is started coaxial double-rotary wing and is started Machine rotates coaxial double-rotary wing (6), closes power spin oar (7), now, and helicopter reverts to coaxial double-rotary wing (6) and provides liter The offline mode of power, helicopter vertical landing.

3rd, the rotor VTOL aircraft based on folding wing；

Folding wing (2) and coaxial double-rotary wing VTOL aircraft are combined together, become wing it is foldable, The rotor VTOL aircraft of expansion；

Rotor VTOL aircraft is by including fuselage (1), folding wing (2), coaxial double-rotary wing (6), folding undercarriage (8), the part such as tailplane (9) vertical tail (10), movable pulley (11) is constituted,

Folding wing (2) is arranged on fuselage (1) both sides, blade, tailplane (9), the undercarriage of coaxial double-rotary wing (6) Etc. (11) it is also foldable design,

When aircraft is stored on ground, these parts are all folded to fuselage, to obtain smaller storage volume；

Figure 14 is rotor VTOL aircraft front view under folded storage position；

Figure 15 is rotor VTOL aircraft top view under folded storage position；

Figure 16 is rotor VTOL aircraft side view under folded storage position；

Movable pulley (11) is to be set for convenience of aircraft in ground moving, while also being risen with folding undercarriage (8) shared Fall the effect of frame；

Before taking off, folding wing (2) is launched into fixed wing, by the rotor (6) of folding, tailplane (9), Fold undercarriage (8) and be deployed into normal position, now, rotor VTOL aircraft tail-down head is sitting in undercarriage upward On, in state to be flown；

Figure 17 is to deploy rotor VTOL aircraft front view under state to be flown；

Figure 18 is to deploy rotor VTOL aircraft top view under state to be flown；

Figure 19 is to deploy rotor VTOL aircraft side view under state to be flown；

Starting engine makes coaxial double-rotary wing (6) rotation produce lift, aircraft vertical lift-off, coaxial double-rotary after aircraft lift-off The wing (6), which is tilted, produces horizontal direction component, and onward impulse is provided for aircraft, and the movable rudder face of adjustment tailplane (9) makes aircraft machine Body gradually switchs to horizontal direction, now, and coaxial double-rotary wing (6) turns into pulling force propeller and provides aircraft flight power, the machine of expansion The wing (2) produces lift, and aircraft is the flat winged pattern of fixed wing aircraft by the Mode change that takes off vertically；

Figure 20 is rotor VTOL aircraft front view under airflight state；

Head is adjusted to before aircraft landing upward, the state of tail-down, now, the wing (2) of expansion are in vertical configuration State does not provide lift, and coaxial double-rotary wing (6) provides the lift of aircraft, aircraft vertical landing.

The utility model has following main feature：

1st, the fixation that area expands several times is formed because folding wing (2), which has, folds small volume after gathering, after expansion The characteristic of wing, after helicopter, the ability for making helicopter possess double mode flight is provided with helicopter and vertically rises Drop, flexible performance, it may have fixed wing aircraft flight less energy consumption, the ability that speed is fast, voyage is remote, have accomplished two kinds The perfect adaptation of type.

2nd, folding wing (2) is applied to after DCB Specimen VTOL aircraft so that aircraft only takes up smaller in storage Space, position expansion will be folded, aircraft can normally take off, land, be readily transported and in the restricted clearance of naval vessels etc again Use.

3rd, it is with a wide range of applications in terms of the utility model is in terms of the logistics transportation, as Personal Transporter.

Claims

1. the double mode rotary wing aircraft based on folding wing, including helicopter and rotor VTOL aircraft, mainly by sending out Motivation, rotor, propeller, fuselage, folding wing, undercarriage are constituted, it is characterized in that：Folding wing (2) is applied to rotor Airborne vehicle, constitutes double mode rotary wing aircraft, and aircraft takeoff, landing phases provide lift by rotor wing rotation, implement vertical rise Winged, landing mode, in the airborne vehicle flat winged stage, provides prevailing lift by the wing deployed, implements fixed wing aircraft offline mode.

2. double mode rotary wing aircraft according to claim 1, it is characterized in that：Folding wing (2) is applied to single rotor Helicopter, constitutes double mode single-rotor helicopter, and folding wing (2) is arranged on fuselage (1) bottom, and helicopter takes off, landed In the stage, folding wing (2), which is folded, to be drawn in fuselage (1) below, and driven by engine main rotor (3) rotation produces lift, implements Take off vertically, landing mode, flat winged stage folding wing (2) expansion of helicopter forms the fixation wing of aircraft, by propulsion spiral shell Revolve oar (4) and flying power is provided, the wing of expansion provides prevailing lift, implements fixed wing aircraft offline mode.

3. double mode rotary wing aircraft according to claim 1, it is characterized in that：Helicopter can be closed in the flat winged stage Main rotor engine, makes main rotor (3) be in free rotation state.

4. double mode rotary wing aircraft according to claim 1, it is characterized in that：Helicopter tail rotor (4) can be rotated by 90 °, Propelling screws are converted to from tail-rotor, or tail-rotor is converted to from propelling screws.

5. double mode rotary wing aircraft according to claim 1, it is characterized in that：Folding wing (2) is applied to coaxial double Heligyro, constitutes double mode coaxial double-rotor helicopter, and folding wing (2) is arranged on fuselage (1) bottom, and helicopter rises Winged, landing phases, folding wing (2), which is folded, to be drawn in fuselage (1) below, driven by engine coaxial double-rotary wing (6) rotation production Raw lift, implementation is taken off vertically, landing mode, flat winged stage folding wing (2) expansion of helicopter, forms the fixation machine of aircraft The wing, flying power is provided by propeller (7), and the wing of expansion provides prevailing lift, implements fixed wing aircraft offline mode.

6. double mode rotary wing aircraft according to claim 1, it is characterized in that：Power is installed in head or tail position to drive Dynamic propeller (7), power is provided when flying for aircraft is flat.

7. double mode rotary wing aircraft according to claim 1, it is characterized in that：In the aircraft flat winged stage, it can close coaxial DCB Specimen engine, rotor is in free rotation state.

8. double mode rotary wing aircraft according to claim 1, it is characterized in that：Folding wing (2) is applied to coaxial double Rotor VTOL aircraft, constitutes double mode rotor VTOL aircraft, and folding wing (2) is arranged on fuselage (1) both sides, deposited Folding wing (2), which is drawn in, during storage is folded, and aircraft vertical is placed on into folding in ground to reduce space-consuming, before taking off and risen and fallen On frame (8), folding wing (2) is deployed, fixed wing is constituted, taken off, landing phases, aircraft vertical is in ground, by coaxial DCB Specimen (6) rotation produces lift, and implementation aircraft vertical takes off, landing mode.

9. double mode rotary wing aircraft according to claim 1, it is characterized in that：In the aircraft flat winged stage, fuselage is adjusted to water Square to coaxial double-rotary wing (6) is converted to pulling force propeller, and flying power is provided for aircraft, and the wing of expansion provides main rise Power, by fixed wing aircraft mode flight.

10. double mode rotary wing aircraft according to claim 1, it is characterized in that：The utility model is applied to unmanned type, And small-sized manned type.