CN102285452A - Annular fixed wing aircraft - Google Patents

Abstract

The invention relates to a fixed wing aircraft, which consists of an annular fixed wing, a centrifugal wind power system, a universal induced air hood, a rudder, an aircraft body, a hanging gravity center adjusting system and some necessary auxiliary facilities, wherein the centrifugal wind power system comprises a man-powered drive system; and the rudder comprises a dual-wing and dual-impeller wind power system and a tail propeller rudder direction control method. The biggest characteristic of the annular fixed wing aircraft is high safety. The space occupied by the wing of the annular fixed wing aircraft is large, the space occupied by the entire aircraft is small, and the production of solar annular fixed wing aircrafts and man-powered aircrafts is facilitated very greatly.

Description

Coleopter (annular fixed-wing aircraft)

Technical field: a kind of fixed-wing aircraft.A kind of aerocraft of modern notion.Certainly, it is amphibious also can be designed to the sky land; Amphibious; The aerial platform of the scouting commander implementation and operation of the vehicle of dwelling in empty land and water three or public security, fire-fighting, rescue or the service platform or the weapons of special trade.The shared spatial dimension of coleopter wing is big, and the shared spatial dimension of complete machine is little, is very beneficial for being made into the solar power coleopter, the manually driven coleopter.

Technical background: modern aviation knowledge is told us: it is that wing is a fairing or an approximate fairing that aircraft can fly up groundwork, can produce lift under the condition that the angle of attack and high velocity air are arranged.The structure of aircraft have two kinds a kind of be fixed wing aircraft; A kind of is rotary wing aircraft, and rotary wing aircraft is divided into the helicopter of dynamic direct drive again and produces the cyclogyro of lift by the passive rotation of rough air.

The content of scheme: coleopter is a kind of of fixed wing aircraft, by ring-like fixed-wing; Centrifugal pneumatic power system (comprising manpower driving system, the solar-electricity power-driven system); Universal blower cover; Yaw rudder (comprises the pneumatic power of dicyclo wing bilobed wheel system; Monocycle wing bilobed wheel wind dynamical system; Spiral tail-rotor yaw rudder direction mode); Fuselage; Hang center of gravity Adjustment System and some indispensable auxiliary facilities formation.

1, annular fixed-wing; Desirable wing is an annular arrangement, make and also be relatively easy to, but because the necessary angle of attack is adjustable, so the overwhelming majority is made of polygon: the shape of the truncation surface of the wing of coleopter, structure are the same with fixed wing aircraft, rule are received 3 kinds of styles, stream line pattern, semi-streamlined form, owe semi-streamlined form.Be the major part that airplane ascensional force produces, its span is than about 10: 1.The annular fixed-wing different with the wing of fixed wing aircraft be, the wing of fixed wing aircraft is a yi word pattern, annular fixed-wing wing is ring-like; One end of fastening aircraft wing is fixed on the fuselage, the other end is unsettled, the annular fixed-wing is end to end, there is not free end, the sectional area of fixed wing aircraft wing is big near the size of fuselage, and is little near the sectional area of wing free end, and the size in the cross section of the wing of annular fixed wing aircraft is consistent, at least do not have too big gap, the material of annular fixed-wing wing can hang down than the rigidity requirement of yi word pattern fixed-wing material in view of structure.What the yi word pattern fixed wing aircraft leaned on the adjustment of the angle of attack is the flight attitude of aircraft, and the angle of attack of annular fixed wing aircraft must have a cover adjusting control system.Aviation knowledge is told us; The modern in-flight angle of attack of fixed wing aircraft changes, and the variation angle of attack of flight attitude just changes, and the angle of attack of annular fixed wing aircraft does not change with the attitude of aircraft, so rise or descend just to need the member of adjusting the angle of attack.The wing of annular wing aircraft is made of skeleton and covering in the scheme, and skeleton also is made of spar, stringer, Cong Qiang, common rib, reinforcement rib, bracing cable.Covering is that thin aluminium alloy plate constitutes.For the angle of attack adjustable the annular wing be equally divided into 8 sections or 12 sections or 24,36, etc.Each section independent adjustment angle of attack.The Adjustment System of the angle of attack can be used the worm and gear Adjustment System; Hydraulic control system; The pull bar hinge all can be adjusted the angle of attack, and angle-of-attack range is that negative 4 degree are to 14 degree.The annular wing is compared with the fixed wing yi word pattern wing in modern times, so there is not free end not have induced drag, the wing of annular wing aircraft is that multistage is evenly distributed, also be evenly distributed with the stressed of fixed frame of wing hinge, therefore lower to the material stiffness requirement of wing, thereby can lower the weight cost-cutting.Make bigger wing area easily.For the practicality pad of man-powered aircraft has been decided the basis.For the development and application pad of solar powered aircraft has been decided the basis.The annular wing is compared with the fixed wing in modern times, the problem that does not have big angle of attack stall, by contrast, the characteristics of coleopter maximum are safety, and the impeller of high speed revolution is that quilt cover gets up basically, at first around the coleopter the suitable big air cushioning quilt of air that outwards sprays is at a high speed arranged on the horizontal surface during with other object collision, be yaw rudder then, after be the some of wing, be only impeller at last, as long as impeller is normal, wing is not all to damage the people just can escape.Compare shortcoming with the fixed wing in modern times be that manoevreability is poor to the coleopter annular wing on the structure.

2, centrifugal pneumatic power system: principle be identical with centrifugal wind machine principle, pass to the impeller that is fixed on the axle by the power of the driving engine output axle by high speed revolution.The centnifugal force that impeller produced of high speed rotating drives ambient air and blows to wing, the pneumatic power that provides to coleopter.The pneumatic power that it provided is premium-quality stable; Continuous; Density also is uniform and stable; When the revolution of driving engine changes this variation of the variable density of bringing also be continuous.The conformability of density is very good, and the axial force of pneumatic power is a suction, establishes this axial suction of a dividing plate and can become lift between driving engine on the fuselage and impeller.The pneumatic power system of modern aircraft all is a screw propeller, and also nobody uses centrifugal pneumatic power system.The formed pneumatic power of screw propeller, with regard to its wind-force itself the wind-force of propeller center be weak, the screw propeller outer shroud has induced drag, wind-force also is weak gradually, the wind that it directly acts on the wing is uneven, in fact screw propeller has only provided a tractive force, and wing has just obtained a stable pneumatic power when aircraft travels forward at a high speed, has just produced lift.Problem is that the direction of the pneumatic power on tractive force and the wing sometimes is inconsistent, also is the problem that can occur big angle of attack stall for assorted petty fixed wing aircraft, also be that fixed wing aircraft is the very long runways of assorted petty needs, and the big more runway of aircraft is long more.Therefore centrifugal pneumatic power system is more much better than the pneumatic power of the fixed wing in the modern times of screw propeller.Have visual skylight on the dividing plate and stud with organism glass, so that the situation of driver's observation aircraft top, as being that system detail also is very complicated with regard to driving engine, want to make normal working of engine, one of system element can not lack, as storage battery, the sparking step-up transformer, light-up plug, airfilter, fuel carburator throttle, fuel tank freeing pipe silencer or the like here just not detail introduced.The power output shaft that the double-vane bilobed wheel of saying previously refers to driving engine drives two mutual opposite spins of impeller by driving device, pneumatic power is provided for respectively the wing of oneself.The single-blade bilobed wheel is that the power output shaft of driving engine drives two mutual opposite spins of impeller by driving device, pneumatic power is provided for a wing, and this divides two kinds of forms; A kind of coaxial two impellers up and down provide pneumatic power to wing; Another kind is that the shape of wing is the peripheral shape that an oblong has two semicircles to fence up in minor face one side, the power output shaft of driving engine drives two mutual opposite spins of impeller by driving device, is that axle provides pneumatic power to coleopter with the center of circle of two semicircles.Man-powered aircraft provides pneumatic power by the foot-operated power wheel impeller of people.The solar power coleopter provides driven by power motor drives impeller that pneumatic power is provided by solar panel.

3, the radially midway location of the impeller in the horizontal surface of annular fixed-wing and the centrifugal pneumatic power is on same truncation surface the time, and when the high-speed air flow that radially blows out, when flowing through the annular wing, annular fixed-wing just can produce lift.

4, universal blower cover: can improve the efficient on the pneumatic power system impeller; Can control heading.The structure of universal air inducing cap is: a slice is shaped as annular element, the member that ring and cylinder type tubular body are connected as a single entity and form with connector in it.Attaching parts is to connect with a kind of universal member attaching parts hinge.Universal member is by crossing the center of circle on the ring bodies two minor axises to be housed radially; Radially be that axle turn 90 degrees and is provided with two axis holes with the center of circle; Minor axis and axis hole are not in one plane.Universal member is installed in and forms the cylindrical tubular body in the middle of two sections cylindrical tube.Can be crooked by the cylinder on the universal air inducing cap of universal member bonded assembly to any direction swing.By control mechanism can control centrifugal pneumatic power system axial air intake towards.With hang the center of gravity Adjustment System; Engine revolution is the speed of advance of may command coleopter together; Working direction; With hang the center of gravity Adjustment System; The engine revolution angle of attack can be realized together; Rise down; Fall to revolve and stop waiting action.Universal air inducing cap is not essential the setting in coleopter, establishes on can be not under many situations, as man-powered aircraft; The aircraft that engine power is little; The aircraft that impeller rotation is slow.Universal air inducing cap is set can also protect impeller not to be subjected to external collision (this need establish a metal coating net at crown certainly).

5, yaw rudder can change fuselage towards, main is overcomes the hull rotation that centrifugal pneumatic power system antagonistic force produces and makes fuselage towards stable.Also can use single-blade bilobed wheel pneumatic power system or the pneumatic power of double-vane bilobed wheel system; Also can replace yaw rudder with screw propeller.Can produce a power opposite with engine rotation according to mechanics principle when the turn of engine, want to make fuselage to keep the static device that just needs to stablize fuselage, this device can also be controlled heading.This case is referred to as: yaw rudder.The formation of yaw rudder is: the strut bar (outrigger) that is connected in fuselage; The rudder body; Rotation controling mechanism (worm and wormwheel formation or hydraulic transmission control system or pole hinge); Principle is: when the high velocity air that flows through wing impacts the certain angle rudder face, can produce a power opposite with hand engine rotation and realize the relatively stable of aircraft.The angle that reduces or increase rudder can reduce or increase flat relatively Heng power and realize turning to.Yaw rudder (two one group) in groups is provided with, and can be provided with many groups as required.Want to make fuselage to keep the static device that just needs to stablize fuselage, also will control heading simultaneously.Also having several method in addition is one to utilize the empennage of modern helicopter similarly to install, and two also can replace yaw rudder with single-blade bilobed wheel pneumatic power system or the pneumatic power of double-vane bilobed wheel system (being that two impellers of single-blade or double-vane all are that hand of rotation is opposite).

6, the fuselage bag expands the frame and the driving compartment of coleopter, also is the platform of each part captive joint (connection) of coleopter.Fuselage comprises machine (structure) frame and the driving compartment that the various piece of coleopter can connect, frame comprises the pole (a slice wing must have one or two pole) of wing, strength beam below dividing plate and the dividing plate, the outrigger of yaw rudder is hung the flange of hanging of driving compartment.We have said that at impeller and driving engine one dividing plate is arranged the front, dividing plate is circular, with this dividing plate is departure point, be fixed with driving engine and fuel tank below the dividing plate, rectangular distribution is installed with the pole that connects wing around the dividing plate, and there is hinge the upper end of pole, and hinge is fixed in the middle of the wing main spar, if two poles, then be positioned on the place at two ends 1/4.The position that connects the support of dividing plate is that the middle part of pole is fixed; The lower end of pole connects the flange that hangs driving compartment, also is fixed on the flange.Mid-mounting driving compartment on the flange.Bracing frame (outrigger) at several groups of yaw rudders of flange peripheral radial rectangular distribution, bracing frame is an outrigger, bracing frame leaves flange a pole below the vertical line of wing girder, bracing frame (outrigger) is hung in wing top wing pole upper end constitutes gusseted, the vertical line below laterally also has pole that mutual the formation mutually of bracing frame (outrigger) supported simultaneously.

7, hang the center of gravity Adjustment System.Hanging the center of gravity Adjustment System is that the middle hanging scroll of flange has a Hanging bolt to connect with driving compartment, screw rod is fixed on the flange, also there is a flange plate to be connected with the driving compartment pine on the driving compartment with nut, screw rod has one to prolong pole, and it is that the center of gravity of hanging of chaufeur is adjusted stretcher that the other end of pole has a cross-arm.The seat of chaufeur is mounted on the driving compartment, just can adjust the center of gravity of hanging when chaufeur scrunches cross-arm, and flivver is no problem certainly, if big aircraft just needs the power-assisted setting.

8, be the equipment such as the elevator control lever of the control convenience auxiliary facilities of some aviation indispensabilities; The yaw rudder control stalk; Hang the center of gravity adjusting lever; Universal blower cover towards control stalk; The throttle of driving engine; Communication facilities; Lighting System; Position fixing system; Height indicator; Speed meter; Oil measurer; Volt meter; Or the like.The control system of the fuselage top wing angle of attack; The control system of universal air inducing cap; The control system of yaw rudder; Hanging the center of gravity Adjustment System can control with worm and gear, and the worm screw head is equipped with between miniature angle motor miniature angle motor and the worm screw one-level gear parameter, needing to realize the angle of control with the control motor angle.If man-powered aircraft can come the wing angle of attack by drag link mechanism; Yaw rudder; Hang the adjustment of center of gravity.Normally realize the control of the wing angle of attack with the hydraulic pressure Adjustment System; The control of universal air inducing cap; The control of yaw rudder; Hang the adjustment of center of gravity.Also has angle of attack adjusting lever; The yaw rudder control stalk; Hang the center of gravity Adjustment System; The blocking device at any time that throttle is adjusted.Also has alighting gear etc.

Accompanying drawing 1 is the scheme drawing of ring-like fixed-wing aircraft, among the figure; 1, be the wing of ring-like fixed-wing aircraft.2, be the impeller of centrifugal pneumatic power system.3, be the axle of impeller.4, be that the part studs with transparent machine glass on the dividing plate; The excircle of dividing plate fixes with a position of the support of wing 8 centres and connects; Fuel tank fixedly is equipped with in the dividing plate below; Driving engine fixedly is housed to be wrapped in by fairing 5.6, be yaw rudder, among the figure just picture one group, it can be two groups or three groups, what have adjusting mechanism has one group or two groups just passable.7, be the pole of yaw rudder.9, be driving compartment.

Accompanying drawing 2 is wing profile scheme drawings.

Accompanying drawing 3 is octagon part wing scheme drawings of embodiment.The 1st, wing; The 2nd, hinge; The 3rd, angle of attack control stalk bonded assembly position; The 4th, frame.

Accompanying drawing 4 is scheme drawings of angle of attack control system.The 1st, wing; The 2nd, frame; The 3rd, control stalk.

Accompanying drawing 5 is yaw rudder control system.The 1st, yaw rudder; The 2nd, frame; The 3rd, control stalk.

Accompanying drawing 6 is to hang center of gravity adjusting control system schematic.The 1st, frame; The 2nd, U type square tube; The 3rd, C type square tube; The 4th, foot control system pedal; Operating seat.

Accompanying drawing 7. is pneumatic power system schematic, and 1 is impeller among the figure; The 2nd, dividing plate 3 is that coupler 4 is that driving engine 5 is that frame 6 is positions of wing.

Accompanying drawing 8 is universal air inducing cap scheme drawings, and 1 is the axis hole of universal member among the figure; The 2nd, universal member; The 3rd, the cover edge; The 4th, the cover top; The 5th, to projecting inward minor axis.

Provide just the not scheme through testing here about embodiment, it at first is safe as a kind of aircraft, does not prove that through experiment safety is to ensure, therefore says that present embodiment can only be reference.

Embodiment: wing is combined into equilateral octagon by eight isosceles trapezoids connections, and trapezoidal upper base is 1250 millimeters; Go to the bottom is 1790 millimeters; Height is 540 millimeters.Truncation surface is a semi-streamlined form, and the wing chord ratio is 9: 1.Skeleton is made of two aileron spars of a main spar and seven vertical walls.Be to make with the Korean pine flitch.Thick 40 millimeters of main spar; Aileron spar is 25 millimeters thick; Main wing beam length 1533 millimeters long, two ends are 22.5 degree angles, on the minor face face at the two ends of beam hinge are arranged, and the bottom surface mid point is equipped with hinge behind the covering, can not slot on the girder.One of aileron spar is long 1655 millimeters; Long 1385 millimeters of another root.Vertical wall front end spacing is 200 millimeters, and tail end is 290 millimeters.Beam is made in 50 millimeters of the rearward end preferably impregnation and is handled.Beam has 2 millimeters chamfering; Joint (knot) can not be arranged, use along stubble, the annual ring line is consistent with the vertical direction of wing.Covering is 0.5 thick aluminum alloy plate materials, will stick with glue when covering system with skeleton to connect, and seam sews with pulling rivet.

Angle of attack control: have one to hang connecting element below every wing of two-chip computer wing front end seam, be fixed on the head both sides of control pull rod, the angle of attack of wing is to change in 25 degree scopes when downward pulling pull bar.8 control pull rod, 4 pull bars have been summarised in by pull bar and side steering, are controlled together by driving compartment angle of attack control handle.Pull bar is made with carbon fiber pipe, and side steering is made with three angle of spot hole iron.

Driving engine selects 40～50 horsepowers water cooled gasoline engine, and weight and power ratio are more than 1: 1.Long 1240 millimeters totally 4 of impeller vane; Long 400 millimeters of blade the preceding paragraph, wide 200 millimeters, 2 millimeters thick, leeward to (reverse rotational direction) bending.Long 950 millimeters of blade the preceding paragraph, wide 100 millimeters, what square aluminum pipe was straight is connected with axle.The deviated splitter vane overlap joint is riveted with pulling rivet for 150 millimeters.Engine revolution 300～2000 is changeed.Dividing plate on the fuselage is 2500 millimeters of diameters; Thick 1 millimeter round aluminium plywood has the aluminum alloy square tube rood beam under the plate, have 4 blocks of glass of 4 skylight edges on dividing plate.The output shaft that driving engine is fixed on driving engine merit on the rood beam is passed by the center of rood beam.Fixedly fixing of plate and beam with pulling rivet.Fuel tank also is to be fixed on the beam.4 terminations of rood beam also 4 square tubes link to each other and can gain in strength.

The rudder body of yaw rudder is that 300X300 millimeter truncation surface is a fairing, makes hollow by 0.5 millimeters thick aluminium sheet, in be full of polyamine fat vacuole foam.There is a thin axle to pass at vertical streamiline surface mid point.There are one 50 millimeters vertical 300X300 faces of pull bar to stretch out on the rudder and are connected to the direction control handle thus.Thin axle is fixed on the outrigger.(figure is arranged) yaw rudder one has 8 and controls with control pull rod, and 8 pull bars are summarised in together by pull bar and side steering, is controlled together by driving compartment yaw rudder control handle.Pull bar is made with carbon fiber pipe, and side steering is made with three angle of spot hole iron.If can not stablize the antagonistic force of centrifugal impeller when before reality is used, doing stable experiment, can install stable rudder additional at the vertical wall of the wing tail direction of wing, quantity is decided according to actual conditions.But certain symmetry installs additional.Angle can be fixed.

Fuselage (frame) is consistent with what say previously, and just the driving compartment of embodiment relatively subtracts list, is to hang loose the connection with bolt and nut with flange on the frame in the middle of a slice flange, all has through hole that the opening dowel fixes is arranged on screw rod and the nut.Be connected with a C font bend pipe on the nut, the bend pipe other end has above the both feet of a cross-arm chaufeur are placed on, and adjusts the center of gravity of suspension to stretch bent leg.Flange is welded with the U type square tube frame back seat that gets off by both sides, the center of circle and is welded in down 1/3 place.Angle of attack handle and yaw rudder handle provide the fulcrum of control operation by the cross-arm of C font bend pipe to chaufeur.Angle of attack handle and yaw rudder handle all have registration device at any time, the brake lever of pinching with hand, essential pinching brake lever can be controlled the angle of attack and yaw rudder when chaufeur is pulled handle, the position of handle locked at once (comprising that adjusting the center of gravity that hangs also is the same with throttle) when hand leaves handle.Its principle and stopping brake lock on the automobile be the same here not detail introduced.U-bottom portion front end is equipped with the castor rear end has cross-arm cross-arm two ends that castor and fwd castor formation alighting gear are installed.

The characteristics of coleopter maximum are safety, the impeller of high speed revolution roughly be that quilt cover gets up, at first around the coleopter the suitable big air cushioning quilt of air that outwards sprays is at a high speed arranged on the horizontal surface during with other object collision, be yaw rudder then, after be the some of wing, be only impeller at last, as long as impeller is normal, wing is not all to damage the people just can escape.When falling object is bigger can being blocked by metal gauze, and the linear velocity that little thing falls middle partly pars intermedia part leaf opinion that can only drop on impeller is that lower change of direction is then thrown outside the machine.At least fully the probability of Sun Huaiing is little.Coleopter is comparatively speaking safe on the structure.Coleopter should be safe in flight below 500 meters.We know according to the lift formula: wing area is directly proportional with lift, and the coleopter wing takes up space greatly, and complete machine takes up space little, is very beneficial for being made into the solar power coleopter.And man-powered aircraft.

Claims (10)

1. claim: a kind of fixed-wing aircraft is characterized by: ring-like fixed-wing; Centrifugal pneumatic power system; Universal blower cover; Yaw rudder (comprises the pneumatic power of bilobed wheel system; Spiral tail-rotor yaw rudder direction mode); Fuselage; Hang; Center of gravity Adjustment System and indispensable auxiliary facilities constitute.

2. content according to claim 1: fixed-wing is an annular arrangement, or polygonal, and wing has the skeleton covering to constitute, and angle of attack control system is arranged.

3. content according to claim 1: there is driving engine (comprising manpower driving system, the Driven by Solar Energy system) in centrifugal pneumatic power system; Outflow wheel; Dividing plate has visual window on the dividing plate.

4. content according to claim 1: universal blower cover; Ring and cylinder type tubular body connect as one the member of formation in the one sheet annular element, and attaching parts is to connect with a kind of universal member attaching parts hinge, and universal member is by crossing the center of circle on the ring bodies two minor axises to be housed radially; Radially be that axle turn 90 degrees and is provided with two axis holes with the center of circle; Minor axis and axis hole are not in one plane.Universal blower cover is can.

5. content according to claim 1: yaw rudder, heading control loop is arranged, another kind of method be utilize modern helicopter empennage device and utilize the pneumatic power of double-vane bilobed wheel system; System also is fine with the pneumatic power of single-blade bilobed wheel.

6. content according to claim 1: fuselage comprises machine (structure) frame and the driving compartment that the various piece of coleopter can connect.

7. content according to claim 1: hang; The center of gravity Adjustment System.

8. content according to claim 1: the control angle of attack and yaw rudder, adjust the center of gravity and the throttle that hang, there is the position of handle when hand leaves handle can locked at once device.

9. content according to claim 1: the castor alighting gear is arranged.

10. content according to claim 1: the radially midway location of the impeller in the horizontal surface of annular fixed-wing and the centrifugal pneumatic power is on same truncation surface.

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