CN103224024B - Two main duct microlight-type vertical takeoff and landing individual lift device - Google Patents

Abstract

The present invention relates to the two main culvert one-seater aircraft of a kind of two main duct microlight-type vertical takeoff and landing, comprise cabin main body and the main duct being symmetricly set on top, the main body left and right sides, cabin, the bottom of cabin main body is provided with alighting gear; Wherein, be provided with screw propeller in described main duct, described driving engine drives it to rotate by centrifugal retarder transmission to screw propeller; Described driving engine is arranged on the bottom of main duct axis, and described main duct nozzle is also provided with deflecting plate.Two main duct aircraft net weight of the present invention is less than 116 kilograms, height and length are all less than 1.9 meters, and about its volume is equivalent to the half of general car, the site requirements like this for landing is very simple, be adapted at crowded city landing and flight, be convenient to control simultaneously.

Description

Two main duct microlight-type vertical takeoff and landing individual lift device

Technical field

The invention belongs to and relate to a kind of airflight vehicle, in particular, the present invention relates to a kind of two main duct microlight-type vertical takeoff and landing individual lift device.

Background technology

Main duct aircraft has the many merits that common fixed wing aircraft and helicopter do not possess, and plays an important role at dual-use aviation field.At present both at home and abroad, the Design and manufacture of main duct aircraft is comparatively more common in unmanned vehicle, and manned main duct vehicle technology report is less by contrast.More famous unmanned main duct aircraft has the GoldenEye of the U.S., Kestrel and iSTAR, and home products sees Harbin Shengshi Special Type Aerocraft Co., Ltd. and part scientific research institutions.As shown in Figure 1, be the constructional drawing of the micro-unmanned main culvert type aircraft of GTSpy.Main culvert type manned craft design plan is numerous and numerous design has feature separately, but element is substantially identical.Primarily of the blade that engine drives, control the main duct of flight attitude and air flow regulator and aircraft fuselage part composition.More typically be designed with the city aerospace company of the U.S. and the design of Trek space flight company.

The two main duct manned craft that Gary aerospace company (URBANAERONAUTICSLTD.) designs and develops 2008.Its fuselage comprises liftable main duct, advances main duct, fuselage, and composition such as part such as ten, take-off and landing device and driving engine etc., manned number can design as required.Main duct comprises, and an advance and a deflecting plate retreated, side deflecting plate regulates gas flow optimized center simultaneously.Its main duct structure, has multiple slot to arrange around main duct.Fuselage adopts Curve Design to reduce propelling resistance, and fuselage is arranged a pair propulsion blades on transverse axis, and personnel's passenger cabin lift force impeller midway location that distributes is parallel with fuselage datum.The main duct lift blade of the transverse axis arrangement that design adopts produces lift, at fuselage side, stabiliser is housed.The bare weight of aircraft reaches 700 kilograms, and maximum take-off weight can reach more than 1400 kilogram, adopts its horsepower output of turbine engine more than 900 horsepowers.But because this design uses at least two to four main duct structures, airframe structure is large, and required drive requires that typical engine is difficult to meet the demands.In load-carrying ability identical in addition and dimensional characteristic, the aircraft that this design is more conventional does not have advantage, and main culvert type aircraft important advantage is exactly advantages of compact and light structure.Obviously this design can not meet this requirement.The design plan comparatively similar to the present invention is that the single main duct that Trek Aerospace PLC, BAe of the U.S. designs can vertically taking off and landing flyer.Accompanying drawing 2 is the constructional drawing of the single main duct aircraft EFV-4A of Trek Aerospace PLC, BAe of U.S. exploitation.This main duct aircraft adopts 118 horsepowers of rotor list engines, and vertical takeoff and landing this design at present is still in test phase, and it has 7 main portion compositions.Be respectively and control deflecting plate, engine radiator, direction control handle, adjustable pedal, height regulating handle, escape clothes and main duct and blading.This main duct aircraft machine is high 2.5 meters, machine width 2.7 meters, net weight 167 kilograms, conventional load-carrying 274 kilograms, maximum take-off weight 320 kilograms, maximum load 102 kilograms, fuel bulk 40 liters; Maximum flying speed 97,000 ms/h, cruising speed 80,000 ms/h, level speed 27,000 ms/h, hover height 1097 meters, farthest flying distance 117 km, 1.5 hours hang times, climbing speed 555 ms/min.This Flight Vehicle Design is succinct, and structure is simply cheap for manufacturing cost.Owing to adopting CFD modeling, software optimization based on this makes winner's duct give play to best output efficiency.The control of this main duct aircraft adopts intelligentized design in addition, and main duct can change on three degree of freedom, and intelligentized control method makes aircraft remain flight optimization state.Embedded GPS navigation, prevents hitting position fixing system all as the feedback parameter of Based Intelligent Control.This design have employed simultaneously, and it is little that the drive technology based on new material makes Power output lose, and performance steadily.Add that the rotating combustion engine of 118 horsepowers makes this aircraft have excellent power system, for the excellent performance of aircraft provides guarantee simultaneously.It should be noted that, although this design is comparatively succinct light and handy, because this aircraft bare weight is 167 kilograms, and civil aviaton of China rules and regulations, ultra light aircraft material weight should lower than 116 kilograms.Thus this aircraft can not use as ultra light aircraft in China, and individual buys and drives the examination & verification and the approval that need associated mechanisms.Meanwhile, by the restriction of domestic engine technology level, the design of single main duct aircraft seems especially difficult in China.Adopt imported engine can increase the Design and manufacture difficulty of aircraft on the one hand, also greatly increase duration and the cost of whole development process in addition.Therefore, develop one and weigh less than 116 kilograms, be assembled with the main duct personal aircraft of microlight-type of domestic lightweight engine technology, be more suitable for the national conditions of China, be conducive to personal aircraft material in the universal of China and the development promoting China's light aircraft technology.

Summary of the invention

In order to solve the above-mentioned technical matters existed in prior art, the object of the present invention is to provide the two main culvert one-seater aircraft of a kind of two main duct microlight-type vertical takeoff and landing.First more traditional aircraft, light-duty main duct Flight Vehicle Structure of the present invention is more simple and compact, is adapted at crowded city landing and flight, is convenient to control simultaneously.

In order to solve the problems of the technologies described above and realize above-mentioned purpose, the invention provides following technical scheme:

The two main culvert one-seater aircraft of a kind of two main duct microlight-type vertical takeoff and landing, comprise cabin main body and the main duct being symmetricly set on top, the main body left and right sides, cabin, the bottom of cabin main body is provided with alighting gear; Wherein, be provided with screw propeller in main duct, driving engine drives it to rotate by centrifugal retarder transmission to screw propeller; Described driving engine is arranged on the bottom of main duct axis, and the nozzle of described culvert is also provided with deflecting plate.

Wherein, also have control stalk in the main body of described cabin, described control stalk controls the rotation of described deflecting plate by drive link.

Wherein, described cabin lower body part is monosymmetric is provided with stable duct, stablizes in duct and arranges the flexible cross wing.

Wherein, the top of described cabin main body is provided with parachute assembly.

Wherein, also have machinery space, the main body that described machinery space has container cavity and the hatchcover be arranged in main body, described driving engine is arranged in described container cavity, and described hatchcover is provided with matrix breather port, the rear portion of described machinery space container cavity is provided with blinds cabin.

Wherein, the structural materials of described individual lift device adopts carbon fiber or carbon fiber alclad alloy composite materials.

Wherein, described main duct entrance maximum gauge is no more than 750mm, and screw propeller is close to inwall internal diameter diameter place and is not less than 650mm; The main duct aspect ratio of described main duct is 1.5; Described main duct outlet diameter and main duct internal diameter are than being 1.15-1.2; Screw propeller is positioned at apart from main duct entrance about 1/3.

Wherein, described driving engine is turbo charged liquid-cooled engine, and engine water circulating system enters air port under main duct, reduces degradation of energy on the whole.

Compared with prior art, the present invention has following beneficial effect:

(1) two main duct aircraft net weight of the present invention is less than 116 kilograms, and height and length are all less than 1.9 meters, and about its volume is equivalent to the half of car, the site requirements like this for landing is very simple.

(2) compared with existing main culvert type aircraft, the main duct aircraft of design has less weight, is equipped with safety air bag and emergency parachute, thus the safety of more comprehensive multiple protective personnel.

(3) the present invention can go out a kind of nt wt net weight by domestic available engine technical merit and manufacture technics and is less than the single main duct aircraft that 116 kilograms have excellent aeroperformance, can in the area of urban population and building dense, landing and flight effectively.For Urban population trip provides a kind of selection of more simple and fast, also make urban air traffic more horn of plenty.

(4) the present invention adopts main duct power aerial vehicle, compared to traditional light helicopter, has more simple compact design and manufacturing cost, more simple to the requirement in landing place, parks just as motor bike simple and convenient.

(5) screw propeller is protected among main duct, and to surrounding, personnel do not have security threat.

(6) when aloft flying; run into fuel consumption totally with the emergency situation of flame-out in flight; the present invention has installed emergency parachute; can dish out in the above case; and in fuselage and main duct, safety air bag can be installed; omnibearing protection is done to body and operating personal, to the safety of body and operating personal when can not only ensure forced landing like this, also can ensure surrounding when landing and personal security simultaneously.

Accompanying drawing explanation

Fig. 1 is the constructional drawing of the micro-unmanned main culvert type aircraft of GTSpy in prior art.

Fig. 2 is the constructional drawing of the single main duct aircraft EFV-4A of Trek Aerospace PLC, BAe of U.S. exploitation.

Fig. 3 a is the front elevation of two single vertical translation aircraft of main duct microlight-type of the present invention.

Fig. 3 b is the lateral plan of two single vertical translation aircraft of main duct microlight-type of the present invention.

Fig. 3 c is the birds-eye view of two single vertical translation aircraft of main duct microlight-type of the present invention.

Fig. 3 d is the block diagram of two single vertical translation aircraft of main duct microlight-type of the present invention.

Fig. 4 is integral structure layout of the present invention schematic diagram.

Fig. 5 is overall drive mechanism schematic diagram of the present invention

Fig. 6 is the structural representation of main duct nozzle deflecting plate of the present invention.

Fig. 7 a is stable duct inner cross wing structure schematic diagram of the present invention.

Fig. 7 b is stable duct placement position schematic diagram of the present invention.

Fig. 7 c is stable duct whole structure schematic diagram of the present invention.

Fig. 8 is every size marking figure of main duct maximum cross section of the present invention.

Implication in figure represented by each Reference numeral is respectively: the main duct of 1-, 2-control stalk, 3-adjustable backrest, 4-stablize duct, 5-alighting gear, 6-driving engine, 7-mailbox, 8-cabin main body, 9-central overall, 10-turbocharger, 11-main shaft, 12-electrical generator and battery, the centrifugal retarder of 13-, 14-main duct strut member, 15-output shaft, 16-gear case, 17-flow backwards rod, 18-screw propeller, 19-prop shaft, 20-deflecting plate, the 21-axial wing, the free wing of 22-.

Detailed description of the invention

As shown in figures 3-5, the present embodiment relates to the two main culvert one-seater aircraft of a kind of two main duct microlight-type vertical takeoff and landing, it main duct 1 comprising cabin main body 8 and be symmetricly set on top, cabin main body 8 left and right sides, the bottom of cabin main body 8 is provided with alighting gear 5, wherein, screw propeller 18 is provided with in main duct 1, described driving engine 6 main output shaft changes axle hand of rotation by centrifugal retarder 13, thus offset main shaft torsion, fuselage is kept to stablize, being transferred to transmission direction that gear case 16 changes axle drives it to rotate to the last transmission of prop shaft 19 to screw propeller 18 power distribution, described driving engine is arranged on the bottom of cabin main body 8 axis, and described main duct 1 nozzle is also provided with deflecting plate 20.As long as the vector current that aircraft of the present invention changes main duct air-flow is to, flare maneuvers such as flying before aircraft just can be made to do, turn, fall back.In order to realize the control to air-flow, as shown in Figure 6, main duct air flow outlet can adopt the design of the deflecting plate 20 being similar to vehicle air conditioning outlet, so just can control the direction vector of high velocity air, and then realizes aircraft and do various action in the air.When deflecting plate 20 omnidirectional's rear steering, high velocity air sprays backward, promotes the action flown before aircraft does, realizes flight; When aircraft forward flight thinks aerial stopping-down, do hovering when stopping or move backward, deflecting plate rotates forward; When deflecting plate one in front and one in back, when the anglec of rotation is identical, instantaneous and inverse time pivot stud can be done aloft.Because aircraft volume is very little, radius of rotation is very little, and alerting ability will far above mosquito helicopter, and also simple a lot of in operation.In order to ensure reliability, will adopt control stalk to the control of deflecting plate, described control stalk is manually operated and is done the rotation controlling described deflecting plate by mechanical drive; As shown in Figure 7, in order to the stability that flies, turn, move backward before keeping further, described cabin lower body part is monosymmetric is provided with stable exhausting, the axial wing 21 and the free wing 22 is provided with in exhausting, when navigation channel, high velocity air flows through, the thrust that the axial wing 21 and the free wing 22 will produce to the left and right and backward, the power of left and right directions can keep body main frame left and right stress balance, power backward plays traction machine body center of gravity inclined downward thus make animal economy have a low-angle inclination to the back lower place backward, contributes to doing flight forward action.Stablize exhausting in body both sides, coaxial connection, keeping Coupled motion, greatly can increasing the stability of aircraft when doing airflight action, thus reach the object of flight flexibly.The top of described cabin main body is provided with parachute assembly, when because of driving engine flame-out in flight or fuel consumption, totally main duct does not reoffer the emergency situations such as power, operating personal only need release a parachute switch, and parachute will spray, and personnel and aircraft security are landed.Certainly inner at main duct and cabin body front part, rear portion, bottom can also arrange air bag, airbag aeration during landing, shield, also ensure that surrounding personal security simultaneously when landing to body and operating personal; Described driving engine is arranged in machinery space in the present invention, the main body that described machinery space has container cavity and the hatchcover be arranged in main body, described driving engine is arranged in described container cavity, and described hatchcover is provided with matrix breather port, the rear portion of described machinery space container cavity is provided with blinds cabin; Thus the heat produced during engine operation can be discharged.Design objective is reached in order to make aircraft weight, the structural materials of described individual lift device of the present invention adopts carbon fiber or carbon fiber alclad alloy composite materials, if adopt 69 pounds of driving engines that mosquito formula microlight-type helicopter is identical when not adding fuel, body can be controlled within double centner.Employing carbon fiber is that the benefit of material of main part is that structural strength is higher than traditional metal materials, and tensile strength is 7 to 9 times of steel, and weight is 1/4 of same volume steel.Two main duct is the lift unit of individual lift device in the present invention, is the critical component of individual lift device of the present invention.By to prior art years of researches, experiment and analog simulation, the present inventor designs the main duct aerodynamic configuration of this individual lift device applicable; Fig. 8 is every size marking figure of main duct maximum cross section of the present invention.Wherein, described main duct entrance maximum gauge is no more than 750mm, and screw propeller is close to inwall internal diameter diameter place and is not less than 650mm, the designing requirement of guarantee overall dimensions like this and lift.The main duct aspect ratio of described main duct is 1.5; Described main duct outlet diameter and main duct internal diameter are than being 1.15-1.2; Screw propeller is positioned at apart from main duct entrance about 1/3.Main duct aspect ratio for 1.5 time the main duct lift that self provides maximum; That strengthens that main duct lip radius can improve main duct entrance streams environment and static pressure distribution, thus improves main duct lift; What increase that main duct cone angle beta can improve main duct inside streams environment, increase main duct effective lift area, and then improve main duct lift, but to increase while β main duct self to the obstruction of oar dish wake flow also in increase, therefore need the optimum value of selected β in the design process; Increase main duct wall thickness and can improve main duct effective lift area, thus improve main duct lift, but also can increase the structural weight of main duct simultaneously, both relations should be weighed in the design; The comparison main duct lift of main duct outlet diameter D and main duct internal diameter d has obvious impact, but impact is nonlinear, and the optimal result of calculating is 1.15 ~ 1.2; Screw propeller be positioned at apart from main duct entrance about 1/3 place time, the lift that main duct produces is maximum; The gap increasing oar dish and main duct inwall can make main duct lift-rising effect reduce, and should reduce the gap between screw propeller and main duct in the design as much as possible.In order to reach the requirement of main duct thrust, and the effective power conduction of driving device, by the ripe driving engine selecting power/quality higher.The 64 horsepower CompactRadialEngine ' s-MZ202 driving engines identical with mosquito helicopter can be selected.In order to ensure power stage, increase torsion and the rotating speed of main shaft, driving engine will be done to necessary simple refit, the method that we adopt adopts existing technology, intake method by driving engine uses turbo charged method instead, under the condition that other structures are constant, increase the power stage of driving engine.Use axial flow turbine, increase the pressure in cylinder and level of oxygen.Adopt turbo charged benefit to be, not only can improve the power of driving engine, the fuelling rate of driving engine can also be improved, so just can play the object more fuel-efficient than mosquito driving engine.

In the present invention, described main duct geometric configuration adopts cylindrical-coordinate system (ξ, σ, γ) to carry out representation space, ξ, σ, γ are respectively axis, axial angle, radial coordinates, infinite distant place speed of incoming flow V α, along the positive dirction of ξ axle, V α is the function of γ; Wherein main duct length is a, and main duct characteristic radius (oar card place main duct inwall radius) is R _d, oar card is from main duct guide margin distance a _p, propeller radius is R _p.Put in the plane of main duct guide margin and ξ=0, ξ axle overlaps with oar shaft centre line, and main duct trailing edge is positioned at ξ=a; The inside and outside both side surface equation of described main duct is: r=R _in(ξ), r=R _ou(ξ), guide margin place has: R _in(0)=R _ou(0)=R _l; R _in(a)=R _ou(a)=R _t;

Then the angle of attack a of main duct section nose buttock line has:

$\mathrm{\α}=\mathrm{arctg}\left(\frac{R_l-R_t}{a}\right)---\left(1\right)$

The equation of the conical suface that nose buttock line is formed is:

γ＝R _t+(a-ξ)tgα(2)

Order

$C\left(\mathrm{\ξ}\right)=\frac{1}{a}\{\frac{R_{\mathrm{ou}}\left(\mathrm{\ξ}\right)+R_{\mathrm{in}}\left(\mathrm{\ξ}\right)}{2}-[R_t+(a-\mathrm{\ξ})\mathrm{tg\α}\left]\right\}---\left(3\right)$

$s\left(\mathrm{\ξ}\right)=\frac{1}{a}\left\{\frac{R_{\mathrm{ou}}\left(\mathrm{\ξ}\right)-R_{\mathrm{in}}\left(\mathrm{\ξ}\right)}{2}\right\}---\left(4\right)$

Wherein, C (ξ) is the radial distance between squelette and nose buttock line and the ratio of main duct length a, the ratio of the half thickness that s (ξ) is radial measurement and a; And z=ξ/a, x=r/R _p, x _d=R _d/ R _p

The axial slope in main duct surface can be write as:

$\frac{\mathrm{dr}}{\mathrm{d\ξ}}=R^{\′}\left(z\right)=-\mathrm{tg\α}+C^{\′}\left(z\right)\±s^{\′}\left(z\right)---\left(5\right)$

In formula ± number in+number to for outer surface ,-number correspond to inner surface; Make length-diameter ratio h _x=a/2R _p, regard oar as the infinite number of sheets, make v _sbe main shrouded propeller speed of incoming flow,

represent the radial induction velocity that main duct annulus snail system produces and v _sratio,

representing that main duct source is converged is the radial induction velocity and v that produce _sratio,

represent that the radial induction velocity of screw propeller generation is at aviation value circumferentially and v _sratio; The boundary condition on so main duct surface is:

${\left[\frac{w_r(z,x)}{v_s}\right]}_{\mathrm{\γ}}+{\left[\frac{w_r(z,x)}{v_s}\right]}_q+{\left[\frac{{\stackrel{\‾}{w}}_{r(z,x)}}{v_s}\right]}_p=R^{\′}\left(z\right)$

Comprehensive above-mentioned formula, can obtain following integral equation:

$\frac{1}{4\mathrm{\π}}{\∫}_0^l\frac{\mathrm{\γ}\left(z_0\right)}{z-z_0}{k}_1\{2E\left(k_1\right)-4{(z_0-z)}^2{h}^2[K\left(k_1\right)-E\left(k_1\right)\left]\right\}d{z}_0$

$+\frac{h}{2\mathrm{\π}}{\∫}_0^l{k}_{1}q\left(z_0\right)[K\left(k_1\right)-E\left(k_1\right)]d{z}_0\±\frac{1}{2}q\left(z\right)+{\left[\frac{{\stackrel{\‾}{w}}_r(z,x_d)}{v_s}\right]}_p=[C^{\′}\left(z\right)-\mathrm{tg\α}]\±s^{\′}\left(z\right)---\left(6\right)$

Wherein: r (z ₀) for being distributed in x=x _dthe face of cylinder on annulus snail system intensity distribution, use V _sj carries out nondimensionalization:

$h=\frac{a}{2R_d}=\frac{a}{2x_d{R}_p}$

$k_1^2=\frac{1}{{(z-z_0)}^2{h}^2+1}$

Function K, E are respectively first, second class complete elliptic integral;

From x=x _d-obe transitioned into x=d _d+o, in equation (6) except band ± number item except, all other are continuously excessively, can draw:

q(z)＝2s′(z)(7)

${\∫}_0^l\frac{\mathrm{\γ}\left(z_0\right)}{z-z_0}{k}_1\{2E\left(k_1\right)-4{(z_0-z)}^2{h}^2[K\left(k_1\right)-E\left(k_1\right)\left]\right\}{\mathrm{dz}}_0=$

$-4h{\∫}_0^l{k}_{1}q\left(z_0\right)[K\left(k_1\right)-E\left(k_1\right)]{\mathrm{dz}}_0-4\mathrm{\π}{\left[\frac{{\stackrel{\‾}{w}}_r(z,x_d)}{v_s}\right]}_p+4\mathrm{\π}[C^{\′}\left(z\right)-\mathrm{tg\α}]\±s^{\′}\left(z\right)---\left(8\right)$

Make g (z-z ₀)=-k ₁{ 2E (k ₁)-4 (z ₀-z) ²h ²[K (k ₁-E (k ₁))] (9)

$H\left(z\right)=4h{\∫}_0^l{k}_1{s}^{\′}\left(z\right)[K\left(k_1\right)-E\left(k_1\right){]\mathrm{dz}}_0-4\mathrm{\π}[C^{\′}\left(z\right)-\mathrm{tg\α}]+4\mathrm{\π}{\left[\frac{{\stackrel{\‾}{w}}_r(z,x_d)}{v_x}\right]}_p---\left(10\right)$

Function g (z-z ₀) only relevant with h; Function H (z) depends on the radial induction velocity of main duct shape and screw propeller; The impact of screw propeller only by $4\mathrm{\π}{\left[\frac{{\stackrel{\‾}{w}}_r(z,x_d)}{v_s}\right]}_p$ Item shows;

Displacement is introduced to formula (9) and (10):

$z=\frac{1}{2}(1-\cos \mathrm{\θ}),$ $z_0=\frac{1}{2}(1-\cos {\mathrm{\θ}}_0)$

Then the solution γ (z) of integral equation is

$\mathrm{\γ}\left(z\right)=\frac{1}{\sqrt{z}}{\mathrm{\γ}}^{*}\left(z\right)$

And ${\mathrm{\γ}}^{*}\left(\mathrm{\θ}\right)=f\left(\mathrm{\θ}\right)+\frac{\sin \frac{\mathrm{\θ}}{2}}{\mathrm{\π}}[-A_0\mathrm{ctg}\frac{\mathrm{\θ}}{2}+\underset{m=1}{\overset{N}{\mathrm{\Σ}}}{A}_m\sin \mathrm{m\θ}$

Wherein:

$f\left(\mathrm{\θ}\right)=\frac{1}{2{\mathrm{\π}}^2}\cos \frac{\mathrm{\θ}}{2}{\∫}_0^{\mathrm{\π}}\frac{1-\cos {\mathrm{\θ}}_0}{\cos {\mathrm{\θ}}_0-\cos \mathrm{\θ}}H\left({\mathrm{\θ}}_0\right)d{\mathrm{\θ}}_0$

And A ₀, A ₁... A _nsolution for linear algebraic equation systems below:

Wherein:

$C_{\mathrm{nm}}=\left\{\begin{array}{cc}-\frac{1}{2\mathrm{\π}}{\∫}_0^{\mathrm{\π}}(1+\cos {\mathrm{\θ}}_0)b_n\left({\mathrm{\θ}}_0\right)d{\mathrm{\θ}}_0& m=0\\ \frac{1}{2\mathrm{\π}}{\∫}_0^{\mathrm{\π}}\left(\sin {\mathrm{\θ}}_0\sin m{\mathrm{\θ}}_0\right)b_n\left({\mathrm{\θ}}_n\right)d{\mathrm{\θ}}_0& m=\mathrm{1,2,3}\·\·\·N\end{array}\right.---\left(14\right)$

$d_n={\∫}_0^{\mathrm{\π}}{b}_n\left({\mathrm{\θ}}_0\right)f\left({\mathrm{\θ}}_0\right)\cos \frac{{\mathrm{\θ}}_0}{2}d{\mathrm{\θ}}_0---\left(15\right)$

$\left.\begin{array}{c}{b}_0\left({\mathrm{\θ}}_0\right)=\frac{1}{\mathrm{\π}}{\∫}_0^{\mathrm{\π}}\frac{2+g(\cos {\mathrm{\θ}}_0-\cos {\mathrm{\θ}}^{\′})}{\cos {\mathrm{\θ}}^{\′}-\cos {\mathrm{\θ}}_0}d{\mathrm{\θ}}^{\′}\\ b_n\left({\mathrm{\θ}}_0\right)=\frac{2}{\mathrm{\π}}{\∫}_0^{\mathrm{\π}}\left[\frac{2+g(\cos {\mathrm{\θ}}_0-\cos {\mathrm{\θ}}^{\′})}{\cos {\mathrm{\θ}}^{\′}-\cos {\mathrm{\θ}}_0}\right]\cos n{\mathrm{\θ}}^{\′}d{\mathrm{\θ}}^{\′}\end{array}\right\}---\left(16\right)$

Consider the axial disturbance velocity of main duct to oar, it is the function of x; This speed and two parts are formed by stacking: a part is produce, with [w by main duct annulus snail _a(z _l, x)] _γrepresent, it is what produce that another part has main duct source to converge, with [w _a(z _l, x)] _qrepresent; Use v _scarry out nondimensionalization, and make

${\mathrm{\ψ}}_{\mathrm{\γ\α}}\left(x\right)=\frac{{\left[w_a(z_L,x)\right]}_{\mathrm{\γ}}}{v_s}={\left[\frac{w_a(z_L,x)}{v_s}\right]}_{\mathrm{\γ}}$

With

${\mathrm{\ψ}}_{\mathrm{q\α}}\left(x\right)=\frac{{\left[w_a(z_L,x)\right]}_q}{v_s}={\left[\frac{w_a(z_L,x)}{v_s}\right]}_q$

The circular rector that the upper annulus whirlpool of main duct each micro-section produces is the axial speed of incoming flow at this place is v _s, the diametral interference speed being subject to screw propeller is therefore the lift of this micro-section upper whirlpool generation at the component of axis is: ${\mathrm{dT}}_{\mathrm{di}}=-2\mathrm{\π\ρa}{R}_a{v}_s\mathrm{\γ}\left(z_0\right){\left[\frac{w_a(z_0,x_d)}{v_s}\right]}_p$

The thrust T of whole main duct _difor:

$T_{\mathrm{di}}=-2\mathrm{\π\ρa}{R}_a{v}_s{\∫}_0^1\mathrm{\γ}\left(z_0\right){\left[\frac{w_a(z_0,x_d)}{v_s}\right]}_p{\mathrm{dz}}_0.$

Above formula can provide the overall thrust of main duct in propeller speed one timing, backstepping designs the overall gear ratio of whole driving device, and then determine the parameter such as rotating speed, power, torsion of required driving engine, according to the rotation speed requirements that will reach, select driving engine.

Industrial applicability

At present, China is still in the stage of High-speed Urbanization, the density of urban population and building progressively raises, urban population gets more and more, and the recoverable amount of city automobile is more and more higher, but because the restriction of urban land, although broaden road, overpass increases, and subway starts to popularize, but the traffic pressure faced is increasing.Current city traffic also still belongs to the stage of plane traffic, although there is subway, can not reach the level of multilevel traffic.Congested traffic hinders urban development.The aerial degree of utilization of present city traffic is no better than zero, and expand the diversification of city traffic further, what actv. utilized air communication is fast the effective scheme addressed this problem.The light helicopter that the present invention adopts main duct power aerial vehicle more traditional, has more simple compact design and lower manufacturing cost, and more simple to the requirement in landing place, aircraft operation also becomes simple and reliable.For urban population City Regions provides the selection of a traffic, also enriched the diversification of air communication simultaneously.In addition, main duct aircraft also can play a significant role in other civil aviation fields, such as, city traffic commander, and quick responding, medical aid and special article fast transportation etc.Although the incipient stage is difficult to popularize, can preferentially in city responding, emergency medical rescue, fire fighting, the aspects, public sphere such as special article transport are promoted.In the area that personnel are more rare, can directly use as the vehicle.Etc. technology further maturation, when country improves field, low latitude laws and regulations, urban transportation tool use can be used as, will greatly alleviates the traffic pressure on ground.

Claims (7)

1. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing, comprise cabin main body and the main duct being symmetricly set on top, the main body left and right sides, cabin, the bottom of cabin main body is provided with alighting gear; It is characterized in that: be provided with screw propeller in described main duct, described driving engine drives it to rotate by centrifugal retarder transmission to screw propeller; Described driving engine is arranged on the bottom of main duct axis, and the nozzle of described main duct is also provided with deflecting plate; Cooling system is air-cooled and water-cooled, air-cooled have machinery space, the main body that described machinery space has container cavity and the hatchcover be arranged in main body, described driving engine is arranged in described container cavity, and described hatchcover is provided with matrix breather port, the rear portion of described machinery space container cavity is provided with blinds cabin; Under the hot water of circulation is entered main duct by pump by water-cooled, air port cools, and one provides additional energy for main duct, and two can reduce degradation of energy on the whole improves fuel efficiency; Described cabin lower body part is monosymmetric is provided with stable duct, stablizes in duct the cross wing being provided with freedom and flexibility.

2. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing according to claim 1, is characterized in that: also have control stalk in the main body of described cabin, described control stalk controls the rotation of described deflecting plate by drive link.

3. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing according to claim 1, is characterized in that: the top of described cabin main body is provided with parachute and lifesaving appliance.

4. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing according to claim 1, is characterized in that: described main duct entrance maximum gauge is no more than 750mm, and screw propeller is close to inwall internal diameter diameter place and is not less than 650mm; The main duct aspect ratio of described main duct is 1.5; Described main duct outlet diameter and main duct internal diameter are than being 1.15-1.2; Screw propeller is positioned at apart from main duct entrance about 1/3.

5. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing according to claim 1, it is characterized in that: described main duct geometric configuration adopts cylindrical-coordinate system (ξ, σ, γ) carry out representation space, ξ, σ, γ is respectively axis, axial angle, radial coordinates, infinite distant place speed of incoming flow V α, along the positive dirction of ξ axle, V α is the function of γ; Wherein main duct length is a, and main duct characteristic radius is R _d, oar card is a from main duct guide margin distance _p, propeller radius is R _p; In the plane of main duct guide margin and ξ=0, ξ axle overlaps with oar shaft centre line, and main duct trailing edge is positioned at ξ=a; The inside and outside both side surface equation of described main duct is: r=R _in(ξ), r=R _ou(ξ), guide margin place has: R _in(0)=R _ou(0)=R _l; R _in(a)=R _ou(a)=R _t;

Then the angle of attack a of main duct section nose buttock line has:

$\mathrm{\α}=\mathrm{arctg}\left(\frac{R_l-R_t}{a}\right)---\left(1\right)$

The equation of the conical suface that nose buttock line is formed is:

γ＝R _t+(a-ξ)tgα(2)

Order

$C\left(\mathrm{\ξ}\right)=\frac{1}{a}\{\frac{R_{\mathrm{ou}}\left(\mathrm{\ξ}\right)+R_{\mathrm{in}}\left(\mathrm{\ξ}\right)}{2}-[R_t+(a-\mathrm{\ξ})\mathrm{tg\α}\left]\right\}---\left(3\right)$

$s\left(\mathrm{\ξ}\right)=\frac{1}{a}\left\{\frac{R_{\mathrm{ou}}\left(\mathrm{\ξ}\right)-R_{\mathrm{in}}\left(\mathrm{\ξ}\right)}{2}\right\}---\left(4\right)$

Wherein, C (ξ) is the radial distance between squelette and nose buttock line and the ratio of main duct length a, the ratio of the half thickness that s (ξ) is radial measurement and a; And z=ξ/a, x=r/R _p, x _d=R _d/ R _p

The axial slope in main duct surface can be write as:

$\frac{\mathrm{dr}}{\mathrm{d\ξ}}=R^{\′}\left(z\right)=-\mathrm{tg\α}+C^{\′}\left(z\right)\±s^{\′}\left(z\right)---\left(5\right)$

In formula ± number in+number to for outer surface ,-number correspond to inner surface; Make length-diameter ratio h _x=a/2R _p, regard oar as the infinite number of sheets, make v _sbe main shrouded propeller speed of incoming flow,

represent the radial induction velocity that main duct annulus snail system produces and v _sratio,

representing that main duct source is converged is the radial induction velocity and v that produce _sratio,

represent that the radial induction velocity of screw propeller generation is at aviation value circumferentially and v _sratio; The boundary condition on so main duct surface is:

${\left[\frac{w_r(z,x)}{v_s}\right]}_{\mathrm{\γ}}+{\left[\frac{w_r(z,x)}{v_s}\right]}_q+{\left[\frac{{\stackrel{\‾}{w}}_r(z,x)}{v_s}\right]}_p=R^{\′}\left(z\right)$

Comprehensive above-mentioned formula, can obtain following integral equation:

$\begin{array}{c}\frac{1}{4\mathrm{\π}}{\∫}_0^l\frac{\mathrm{\γ}\left(z_0\right)}{z-z_0}{k}_1\{2E\left(k_1\right)-4{(z_0-z)}^2{h}^2[K]\left(k_1\right)-E\left(k_1\right)\}{\mathrm{dz}}_0\\ +\frac{h}{2\mathrm{\π}}{\∫}_0^l{k}_{1}q\left(z_0\right)[K\left(k_1\right)-E\left(k_1\right)]{\mathrm{dz}}_0\±\frac{1}{2}q\left(z\right)+{\left[\frac{{\stackrel{\‾}{w}}_r(z,x_d)}{v_s}\right]}_p=[C^{\′}\left(z\right)-\mathrm{tg\α}]\±s^{\′}\left(z\right)\end{array}$

$\left(6\right)$

Wherein: r ( _z0) for being distributed in x=x _dthe face of cylinder on annulus snail system intensity distribution, use V _sj carries out nondimensionalization:

$h=\frac{a}{{2R}_d}=\frac{a}{{2x}_d{R}_p}$

$k_1^2=\frac{1}{{(z-z_0)}^2{h}^2+1}$

Function K, E are respectively first, second class complete elliptic integral;

From x=x _d-obe transitioned into x=x _d+o, in equation (6) except band ± number item except, all other are continuously excessively, can draw:

q(z)＝2s′(z)(7)

$\begin{array}{c}{\∫}_0^l\frac{\mathrm{\γ}\left(z_0\right)}{z-z_0}{k}_1\{2E\left(k_1\right)-4{(z_0-z)}^2{h}^2[K\left(k_1\right)-E\left(k_1\right)\left]\right\}{\mathrm{dz}}_0=\\ -4h{\∫}_0^l{k}_{1}q\left(z_0\right)[K\left(k_1\right)-E\left(k_1\right)]{\mathrm{dz}}_0-4\mathrm{\π}{\left[\frac{{\stackrel{\‾}{w}}_r(z,z_d)}{v_s}\right]}_p+4\mathrm{\π}[C^{\′}\left(z\right)-\mathrm{tg\α}]\±s^{\′}\left(z\right)\end{array}---\left(8\right)$

Make g (z-z ₀)=-k ₁{ 2E (k ₁)-4 (z ₀-z) ²h ²[K (k ₁-E (k ₁))] (9)

$H\left(z\right)=4h{\∫}_0^l{k}_1{s}^{\′}\left(z\right)[K\left(k_1\right)-E\left(k_1\right)]{\mathrm{dz}}_0-4\mathrm{\π}[C^{\′}\left(z\right)-\mathrm{tg\α}]+4\mathrm{\π}{\left[\frac{{\stackrel{\‾}{w}}_r(z,x_d)}{v_s}\right]}_p---\left(10\right)$

Function g (z-z ₀) only relevant with h; Function H (z) depends on the radial induction velocity of main duct shape and screw propeller; The impact of screw propeller only by item shows;

Displacement is introduced to formula (9) and (10):

$z=\frac{1}{2}(1-\cos \mathrm{\θ}),$ $z_0=\frac{1}{2}(1-\cos {\mathrm{\θ}}_0)$

Then the solution γ (z) of integral equation is

$\mathrm{\γ}\left(z\right)=\frac{1}{\sqrt{z}}\mathrm{\γ}*\left(z\right)$

And $\mathrm{\γ}*\left(\mathrm{\θ}\right)=f\left(\mathrm{\θ}\right)+\frac{\sin \frac{\mathrm{\θ}}{2}}{\mathrm{\π}}[-A_0\mathrm{ctg}\frac{\mathrm{\θ}}{2}+\underset{m=1}{\overset{N}{\mathrm{\Σ}}}{A}_m\sin \mathrm{m\θ}]---\left(11\right)$

Wherein:

$f\left(\mathrm{\θ}\right)=\frac{1}{{2\mathrm{\π}}^2}\cos \frac{\mathrm{\θ}}{2}{\∫}_0^{\mathrm{\π}}\frac{1-\cos {\mathrm{\θ}}_0}{\cos {\mathrm{\θ}}_0-\cos \mathrm{\θ}}H\left({\mathrm{\θ}}_0\right){\mathrm{d\θ}}_0---\left(12\right)$

And A ₀, A ₁... A _nsolution for linear algebraic equation systems below:

Wherein:

$C_{\mathrm{nm}}=\left\{\begin{array}{cc}-\frac{1}{2\mathrm{\π}}{\∫}_0^{\mathrm{\π}}(1+\cos {\mathrm{\θ}}_0)b_n\left({\mathrm{\θ}}_0\right){\mathrm{d\θ}}_0& m=0\\ \frac{1}{2\mathrm{\π}}{\∫}_0^{\mathrm{\π}}\left(\sin {\mathrm{\θ}}_0\sin m{\mathrm{\θ}}_0\right)b_n\left({\mathrm{\θ}}_0\right){\mathrm{d\θ}}_0& m=\mathrm{1,2,3}...N\end{array}\right.---\left(14\right)$

$d_n={\∫}_0^{\mathrm{\π}}{b}_n\left({\mathrm{\θ}}_0\right)f\left({\mathrm{\θ}}_0\right)\cos \frac{{\mathrm{\θ}}_0}{2}{\mathrm{d\θ}}_0---\left(15\right)$

$\left.\begin{array}{c}{b}_0\left({\mathrm{\θ}}_0\right)=\frac{1}{\mathrm{\π}}{\∫}_0^{\mathrm{\π}}\frac{2+g(\cos {\mathrm{\θ}}_0-\cos {\mathrm{\θ}}^{\′})}{{\cos \mathrm{\θ}}^{\′}-{\cos \mathrm{\θ}}_0}{\mathrm{d\θ}}^{\′}\\ b_n\left({\mathrm{\θ}}_0\right)=\frac{2}{\mathrm{\π}}{\∫}_0^{\mathrm{\π}}\left[\frac{2+g({\cos \mathrm{\θ}}_0-{\cos \mathrm{\θ}}^{\′})}{{\cos \mathrm{\θ}}^{\′}-{\cos \mathrm{\θ}}_0}\right]\cos n{\mathrm{\θ}}^{\′}{\mathrm{d\θ}}^{\′}\end{array}\right\}---\left(16\right)$

Consider the axial disturbance velocity of main duct to oar, it is the function of x; This speed and two parts are formed by stacking :-part is produce, with [w by main duct annulus snail _a( _zL, x)] _γrepresent, it is what produce that another part has main duct source to converge, with [w _a(z _l, x)] _qrepresent; Use v _scarry out nondimensionalization, and make

${\mathrm{\ψ}}_{\mathrm{\γ\α}}\left(x\right)=\frac{{\left[w_a(z_L,x)\right]}_{\mathrm{\γ}}}{v_s}={\left[\frac{w_a(z_L,x)}{v_x}\right]}_{\mathrm{\γ}}$

With

${\mathrm{\ψ}}_{\mathrm{q\α}}\left(x\right)=\frac{{\left[w_a(z_L,x)\right]}_{\mathrm{q\γ}}}{v_s}={\left[\frac{w_a(z_L,x)}{v_x}\right]}_q$

The circular rector that the upper annulus whirlpool of main duct each micro-section produces is the axial speed of incoming flow at this place is v _s, the diametral interference speed being subject to screw propeller is therefore the lift of this micro-section upper whirlpool generation at the component of axis is;

${\mathrm{dT}}_{\mathrm{di}}=-2\mathrm{\π\ρa}{R}_a{v}_s\mathrm{\γ}\left(z_0\right){\left[\frac{w_a(z_0,x_d)}{v_s}\right]}_p$

The thrust T of whole main duct _difor:

$T_{\mathrm{di}}=-2\mathrm{\π\ρa}{R}_a{v}_s{\∫}_0^l\mathrm{\γ}\left(z_0\right){\left[\frac{w_a(z_0,x_d)}{v_s}\right]}_p{\mathrm{dz}}_0.$

6. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing according to claim 5, is characterized in that: described driving engine meets the thrust T of described whole main duct _direquirement, and determine rotating speed, power, the torsion parameter of required driving engine accordingly, according to the rotation speed requirements that will reach, select driving engine.

7. the two main culvert one-seater aircraft of two main duct microlight-type vertical takeoff and landing according to claim 1, is characterized in that: the structural materials of described individual lift device adopts carbon fiber or carbon fiber alclad alloy composite materials.