CN201882248U - Novel high-speed helicopter - Google Patents
Novel high-speed helicopter Download PDFInfo
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- CN201882248U CN201882248U CN2010205699166U CN201020569916U CN201882248U CN 201882248 U CN201882248 U CN 201882248U CN 2010205699166 U CN2010205699166 U CN 2010205699166U CN 201020569916 U CN201020569916 U CN 201020569916U CN 201882248 U CN201882248 U CN 201882248U
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Abstract
The utility model relates to a novel high-speed helicopter, which is characterized in that the front part of a streamlined aircraft body is provided with two pairs of propellers with the same vertical axial line, referred to as common vertical-axis propellers, the propellers are driven by a controllable engine or compressed gases to rotate, and the rotation and the speed of the propellers can be controlled; the tail part of the aircraft body is provided with a retractable horizontal tail wing or two pairs of common vertical-axis propellers and a vertical tail wing, the propellers are driven by a controllable engine or compressed gases to rotate, the rotation and the speed of the propellers can be controlled, and the vertical tail wing is provided with a rudder or no rudder but is provided with a vertical left tail gas nozzle and a vertical right tail gas nozzle; the front part of the aircraft body is also provided with a front left gas nozzle and a front right gas nozzle; and a horizontal propulsion engine is arranged inside or outside the aircraft body, and the compressed gases are guided to all the gas nozzles through control valves from the horizontal propulsion engine. The novel high-speed helicopter has the advantages of higher speed, higher mobility, longer flying range, good energy-saving performance, high safety and low noise.
Description
Technical field
The utility model relates to a kind of aircraft, particularly a kind of novel high speed autogyro.
Background technology
The positive routine helicopter of Mechanical Driven can vertical takeoff and landing and is hovered, but so far, existing positive routine helicopter is because induced drag and useless resistance are big, and flying speed is no more than 370km/h, and flying speed is low; Existing fixed wing aircraft flying speed is the highest to have reached 3 Mach, and flying speed is very high, but landing all must be slided the distance of running than long, and can not hover.Have wing type helicopter, composite helicopter, tiltrotor aircraft all to combine the advantage of helicopter and fixed wing aircraft, but maximum speed is difficult to break through 550km/h, and energy consumption is very big, capacity weight is little.Existing fixed wing aircraft and autogyro turn radius are all bigger.The flying disc type aircraft is except arbitrarily hovering, maximum characteristics are can arbitrarily very fast change of flight direction, and almost can reach no turn radius turns to, thereby flying disc type aircraft manoevreability is very high, but the flying disc type aircraft causes flying speed low more than existing fixed wing aircraft and autogyro because the very big critical defect of form resistance is because form resistance is very big.
Summary of the invention
The utility model discloses a kind of novel high speed autogyro, is intended to the advantage that comprehensive existing machinery drives positive routine helicopter, fixed wing aircraft, flying saucer, and flying speed is higher, manoevreability is very high, voyage length, economy, safety.
The utility model is realized by following technical scheme.
At forebody altogether vertical axis screw propeller of two pairs (two blades on the same diameter are a pair) is set, is called for short vertical axis screw propeller altogether, but screw propeller turn by control engine or pressure gas, the commentaries on classics of screw propeller stops and controllable rotation speed; The tailplane or two pairs that can actuate in the afterbody setting are total to vertical axis screw propeller and vertical tails, but screw propeller is turned by control engine or pressure gas, the commentaries on classics of screw propeller stops and controllable rotation speed, vertical tail band yaw rudder or be not with yaw rudder but vertical fin left side air nozzle be set and the right air nozzle of vertical fin; Left air nozzle, preceding right air nozzle before forebody is provided with; Horizontal propelling motor is set in fuselage or outside the fuselage, from horizontal propelling motor impulse contract gas through by-pass valve control to described all air nozzles.
When described novel high speed autogyro takes off, to this aircraft of the tailplane that can actuate is set, earlier tailplane is recovered to and the parallel position of pasting mutually of vertical tail, start vertical axis screw propeller altogether then, the hand of rotation of two width of cloth screw propellers is opposite, air offsets the torque to fuselage that the antagonistic force of screw propeller of rotation causes, under aerodynamic effect, and the aircraft vertical uplift; Can hover to the height that needs, when flying before wanting, start horizontal propelling motor, when horizontal flight speed reaches one regularly, open tailplane, while is stall one secondary screw propeller gradually, the spout ejection pressure gas of vertical tail is held the torque that the screw propeller of rotation causes fuselage to offset another collateral, when a width of cloth diameter of propeller of stall gradually is vertical with the fuselage length direction, rotate screw propeller and be locked into " fixed-wing ", when the resultant lift of this " fixed-wing " and tailplane generation can hold up whole aircraft, make the screw propeller of another secondary rotation also become " fixed-wing " by aforesaid method again, after this, aircraft becomes two fixed wing aircrafts, it is more much smaller than the useless resistance of the flight resistance of positive routine helicopter, so flying speed may reach more than the 700km/h.
Described novel high speed autogyro also can quicken by along continuous straight runs when rising, and when rising to the height of desiring to reach and before flying to certain speed, imports gradually by preceding method and is completely fixed wing offline mode.
When described novel high speed autogyro lands, slow down earlier, discharge a pair " fixed-wing " (screw propeller) again and make its rotation, then regain tailplane, discharge another width of cloth " fixed-wing " (screw propeller) again and make its rotation, in this process, the airplane nose down landing, when horizontal velocity is kept to zero, but just vertical landing; Certainly, also can reduce horizontal velocity component gradually near zero the time, vertical landing again.In the landing process, can utilize the motor regenerative electric power of the described driving engine of up current driving propeller-driven, recuperated energy, this process screw propeller plays the effect of parachute.
Described novel high speed autogyro heading is controlled perhaps steering rudder control by controlling vertical fin air nozzle ejection pressure gas.If control vertical fin left and right sides air nozzle and front portion are provided with left air nozzle, right air nozzle, described novel high speed autogyro is moved to the left or to the right or rotate 360 ° and turn around.
The effect that the utility model is useful is:
1, the utility model drawn positive routine helicopter and, the advantage of fixed wing aircraft, flying saucer, overcome their shortcoming, can vertical takeoff and landing, flying speed is higher more stable, mobility strong takes advantage of the charge material amount big; Use this aircraft, the area on required public airport is very little.
2, coaxial twin screw of the present utility model, when aircraft lifting and landing as elevating screw, when aircraft flight as fixed-wing, promptly under lifting and two kinds of operating modes of flight, all play crucial lift function, the service efficiency height, work efficiency is than non co axial formula height, the negative effect that produces is very little, and make aircraft lack a bigger lift member, thereby alleviated the weight of aircraft, useless resistance resistance under lifting and two kinds of operating modes of flight is little and energy-conservation, and these are better than that wing type helicopter is arranged, composite helicopter, tiltrotor aircraft.
3, in the described novel high speed autogyro landing process, renewable generating, recuperated energy;
4, the utility model driving engine adopts the motor that is similar to magneto-electric machine or superconduction electric machine, have many good qualities: energy consumption is little, does not produce pernicious gas, vibration is little, noise is little, heating is less, loss is little, efficient is high, weight is little, maintenance maintenance is easy, the lifting flight control is good;
5, the utility model adopts coaxial twin screw, its blade is than the weak point of single screw, reduced the aircraft size, alleviated blade weight (increasing) because blade weight is cube with diameter dimension, vibration is little during rotation, noise is little, tip speed during rotation (tangential speed) is little, has improved the rotating speed of screw propeller, thereby improves lift; Coaxial in addition twin screw hovering efficiency is higher;
6, aircraft of the present utility model is if aloft stop, highly begin to descend, at this moment can discharge a width of cloth screw propeller immediately earlier and become free rotor, along with aircraft descends, up current washes away free rotor makes its rotation, aircraft is produced upper pulling force, discharge another width of cloth screw propeller then gradually and become free rotor, two secondary free rotors make the slow graceful landing of aircraft; In case of emergency, discharge screw propeller one by one and return to by controlled engine drive state, thus control aircraft stable landing; In addition, coaxial twin screw aircraft wind loading rating is strong, so aircraft safety of the present utility model is fine.
Description of drawings
Fig. 1 is the structural representation of the utility model embodiment one;
Fig. 2 is the birds-eye view of blade 3 under blade 2 or the rectangle on the screw propeller rectangle among Fig. 1;
The left view of Fig. 1 when Fig. 3 is provided with single horizontal engine for the utility model embodiment one;
Fig. 4 is the left view of Fig. 1 during two horizontal engine for the utility model embodiment one is provided with;
Fig. 5 is the structural representation of the utility model embodiment two;
Fig. 6 is the birds-eye view that screw propeller sabre shape is gone up blade 2 or following blade 3 among Fig. 1;
Fig. 7 is the birds-eye view that screw propeller bird's wing shape is gone up blade 2 or following blade 3 among Fig. 1.
The specific embodiment
The utility model is described in further detail below in conjunction with drawings and Examples.
Embodiment one: show as Fig. 1.Two width of cloth vertical axis screw propeller altogether is set in fuselage 1 front portion, is called for short vertical axis screw propeller altogether, blade is last paddle 2 and following paddle 3, and its typical shape is a rectangle, as shown in Figure 2; Last blade 2 connects with sleeve rotor (being equivalent to propeller hub) 5 forms a secondary screw propeller, and rotor 5 and stator 6 are formed the driving engine of these screw propellers; Following blade 3, rotating shaft 4 and rotor 7 connect forms another secondary screw propeller, and the mesopore of sleeve rotor 5 is passed in rotating shaft 4, and rotor 7 and stator 8 are formed the driving engine of these screw propellers; Screw propeller is turned by driving engine, and vertical axis screw propeller hand of rotation is opposite altogether for two pairs; At tailplane 9 and the vertical tail 10 that the afterbody setting of fuselage 1 can actuate, vertical tail 10 band yaw rudders or not with yaw rudder but vertical fin left side air nozzle 15 and the right air nozzle 16 of vertical fin (projection and the vertical fin right air nozzle 16 of vertical fin left side air nozzle 15 in vertical paper overlaps among Fig. 1) are set; Left air nozzle 17, preceding right air nozzle 18 (projection and the preceding right air nozzle 18 of left air nozzle 17 in vertical paper overlaps before among Fig. 1) before forebody is provided with; Horizontal propelling motor is set in fuselage or outside the fuselage, from horizontal propelling motor impulse contract gas through by-pass valve control to vertical fin left side air nozzle 15, the right air nozzle 16 of vertical fin, preceding left air nozzle 17, preceding right air nozzle 18; (or in fuselage) is provided with a horizontal propelling motor outside fuselage, left view 3 as Fig. 1 shows, this driving engine is made up of axle 14, turbine 11 and the housing 12 of controollable driving machine 13 and its driving, engine drive turbine 11 sucks air, and from the ejection of the nozzle of driving engine, counteraction is tried hard to recommend aircraft and is advanced.
Embodiment two: the fuselage 1 at embodiment one described novel high speed autogyro laterally is set up in parallel two or many horizontal propelling motors, shows that as the left view 4 of Fig. 1 each is all identical with embodiment one described horizontal propelling motor.
Embodiment three: the driving engine of screw propeller described in embodiment one and the example two is removed, and design has the blade of air flue and propeller hub, oar axle in addition, and air flue leads to the blade tip spout of blade; Contract gas through the spout of by-pass valve control to blade tip from horizontal propelling motor impulse, and pressure gas is from the ejection of blade tip spout, and antagonistic force turns screw propeller.
Embodiment four: show as Fig. 5.Along fuselage 19 two groups of altogether vertical axis screw propellers vertically are set, each group is identical with the structure of embodiment one to embodiment three; One or more horizontal propelling motor can be set in fuselage or outside the fuselage; Afterbody at fuselage 19 is provided with vertical tail, vertical tail band yaw rudder or not with yaw rudder but vertical fin left side air nozzle 20 and the right air nozzle 21 of vertical fin (projection and the vertical fin right air nozzle 21 of vertical fin left side air nozzle 20 in vertical paper overlaps among Fig. 5) are set; Left air nozzle 22, preceding right air nozzle 23 (projection and the preceding right air nozzle 23 of left air nozzle 22 in vertical paper overlaps before among Fig. 5) before forebody is provided with; Horizontal propelling motor is set in fuselage or outside the fuselage, from horizontal propelling motor impulse contract gas through by-pass valve control to vertical fin left side air nozzle 20, the right air nozzle 21 of vertical fin, preceding left air nozzle 22, preceding right air nozzle 23.
Embodiment five: to embodiment four described aircrafts, with the screw propeller of coaxial screw propellers below, two groups of front and back with the synchronizing shaft contact or altogether air flue be communicated with the doing too of top, and the screw propeller hand of rotation that makes the below and top is opposite.The two screw propellers rotation that can guarantee like this to be got in touch makes screw propeller steady to the fixed-wing transition with speed, keeps work when the driving engine that can guarantee to drive screw propeller again has an et out of order, guarantees flight safety.
Embodiment four and embodiment five described aircrafts have the total advantage of close coupled type screw propeller, also have following significant advantage:
1, embodiment four and the embodiment five described realizations of taking off, fly, landing are described with embodiment one to embodiment five arbitrary embodiment, after the screw propeller of different is fuselage afterbody is transformed into fixed-wing, its function is served as tailplane, therefore do not need to be provided with again tailplane, alleviated aircraft weight, cost-cutting; To embodiment seven described aircrafts, can make one group of equidirectional rotation of screw propeller of forebody, and one group of equidirectional rotation of screw propeller of fuselage afterbody but anti-with last group hand of rotation, the screw propeller of rotation is offset the torque that fuselage produces, in the fixed-wing transition, also needn't control vertical tail at screw propeller;
2, make heavy airplane usefulness, the ratio unit transport rate greatly in other words height of capacity weight and total weight;
3, the center of gravity variation range can be bigger, and it is more steady to fly.
Embodiment six: to embodiment one to five described novel high speed autogyro, shape of blade 2 or following blade 3 also can be made as shown in Figure 6 sabre shape or bird's wing shape as shown in Figure 7 or other shape on it, and the control rotating mechanism is set, make the leaf in blade 2 or the following blade 3 arbitrary pairs, in rotation and " fixed-wing " mutual transition process,, also can do like this rectangle blade along ° also locking of blade length direction axis Rotate 180; To as embodiment four and embodiment five described two groups of its shaft type screw propellers, can adopt with a kind of blade, or adopt blade not of the same race to make up it, the mode of combination has multiple, but the shape of the blade of each width of cloth screw propeller is identical, be with a kind of as two groups of close coupled type screw propellers near the blade of two width of cloth screw propellers of fuselage, and is all another kind away from other blade of two width of cloth screw propellers of fuselage.
Claims (5)
1. novel high speed autogyro is characterized in that: at forebody two secondary vertical axis screw propellers altogether are set, are called for short vertical axis screw propeller altogether, but screw propeller turn by control engine or pressure gas, the commentaries on classics of screw propeller stops and controllable rotation speed; The tailplane or two pairs that can actuate in the afterbody setting are total to vertical axis screw propeller and vertical tails, but screw propeller is turned by control engine or pressure gas, the commentaries on classics of screw propeller stops and controllable rotation speed, vertical tail band yaw rudder or be not with yaw rudder but vertical fin left side air nozzle be set and the right air nozzle of vertical fin; Left air nozzle, preceding right air nozzle before forebody is provided with; Horizontal propelling motor is set in fuselage or outside the fuselage, from horizontal propelling motor impulse contract gas through by-pass valve control to described all air nozzles.
2. according to the described novel high speed autogyro of claim 1, it is characterized in that: two width of cloth vertical axis screw propeller altogether is set in fuselage (1) front portion, is called for short vertical axis screw propeller altogether, blade is last paddle (2) and following paddle (3), and its typical shape is a rectangle; Last blade (2) connects with sleeve rotor (5) forms a secondary screw propeller, and rotor (5) and stator (6) are formed the driving engine of this screw propeller; Following blade (3), rotating shaft (4) and rotor (7) connect forms another secondary screw propeller, and the mesopore of sleeve rotor (5) is passed in rotating shaft (4), and rotor (7) and stator (8) are formed the driving engine of this screw propeller; Screw propeller is turned by driving engine, and vertical axis screw propeller hand of rotation is opposite altogether for two pairs; At tailplane (9) and the vertical tail (10) that the afterbody setting of fuselage (1) can actuate, vertical tail (10) band yaw rudder or be not with yaw rudder but vertical fin left side air nozzle (15) be set and vertical fin right side air nozzle (16); Left air nozzle (17), preceding right air nozzle (18) before forebody is provided with; Horizontal propelling motor is set in fuselage or outside the fuselage, from horizontal propelling motor impulse contract gas through by-pass valve control to vertical fin left side air nozzle (15), the right air nozzle (16) of vertical fin, preceding left air nozzle (17), preceding right air nozzle (18); A horizontal propelling motor is set outside fuselage or in the fuselage, and this driving engine is made up of axle (14), turbine (11) and the housing (12) of controollable driving machine (13) and its driving.
3. according to claim 1 or 2 described novel high speed autogyros, it is characterized in that: the fuselage (1) at described high speed helicopters laterally is set up in parallel two or many horizontal propelling motors.
4. according to claim 1 or 2 described novel high speed autogyros, it is characterized in that: the engine design of described screw propeller is become to have the blade of air flue and propeller hub, oar axle, and air flue leads to the blade tip spout of blade; Contract gas through the spout of by-pass valve control to blade tip from horizontal propelling motor impulse.
5. according to claim 1 or 2 described novel high speed autogyros, it is characterized in that: two groups of altogether vertical axis screw propellers vertically are set along fuselage (19); One or more horizontal propelling motor can be set in fuselage or outside the fuselage; Afterbody at fuselage (19) is provided with vertical tail, vertical tail band yaw rudder or be not with yaw rudder but vertical fin left side air nozzle (20) be set and vertical fin right side air nozzle (21); Left air nozzle (22), preceding right air nozzle (23) before forebody is provided with; Horizontal propelling motor is set in fuselage or outside the fuselage, from horizontal propelling motor impulse contract gas through by-pass valve control to vertical fin left side air nozzle (20), the right air nozzle (21) of vertical fin, preceding left air nozzle (22), preceding right air nozzle (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205699166U CN201882248U (en) | 2010-10-21 | 2010-10-21 | Novel high-speed helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205699166U CN201882248U (en) | 2010-10-21 | 2010-10-21 | Novel high-speed helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN201882248U true CN201882248U (en) | 2011-06-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010205699166U Expired - Fee Related CN201882248U (en) | 2010-10-21 | 2010-10-21 | Novel high-speed helicopter |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539832A (en) * | 2015-12-24 | 2016-05-04 | 上海埃威航空电子有限公司 | Variable-pitch power device for multi-rotor-wing unmanned aerial vehicle |
| CN106828885A (en) * | 2016-12-30 | 2017-06-13 | 上海牧羽航空科技有限公司 | A kind of use jet form control driftage and the tiltrotor of pitching |
| CN108945484A (en) * | 2018-07-02 | 2018-12-07 | 山东理工大学 | A kind of two-way air injection aerial vehicle |
-
2010
- 2010-10-21 CN CN2010205699166U patent/CN201882248U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539832A (en) * | 2015-12-24 | 2016-05-04 | 上海埃威航空电子有限公司 | Variable-pitch power device for multi-rotor-wing unmanned aerial vehicle |
| CN106828885A (en) * | 2016-12-30 | 2017-06-13 | 上海牧羽航空科技有限公司 | A kind of use jet form control driftage and the tiltrotor of pitching |
| CN108945484A (en) * | 2018-07-02 | 2018-12-07 | 山东理工大学 | A kind of two-way air injection aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110629 Termination date: 20111021 |