CN1086184A - The microlight-type autogyro - Google Patents
The microlight-type autogyro Download PDFInfo
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- CN1086184A CN1086184A CN93118478A CN93118478A CN1086184A CN 1086184 A CN1086184 A CN 1086184A CN 93118478 A CN93118478 A CN 93118478A CN 93118478 A CN93118478 A CN 93118478A CN 1086184 A CN1086184 A CN 1086184A
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- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 3
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- 238000007334 copolymerization reaction Methods 0.000 claims 1
- 230000010355 oscillation Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 2
- 239000002917 insecticide Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
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- 101150034459 Parpbp gene Proteins 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
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- YFONKFDEZLYQDH-BOURZNODSA-N indaziflam Chemical compound CC(F)C1=NC(N)=NC(N[C@H]2C3=CC(C)=CC=C3C[C@@H]2C)=N1 YFONKFDEZLYQDH-BOURZNODSA-N 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/08—Geodetic or other open-frame structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/52—Skis or runners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface specially adapted for helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
- Current-Collector Devices For Electrically Propelled Vehicles (AREA)
- Powder Metallurgy (AREA)
- Inorganic Compounds Of Heavy Metals (AREA)
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Abstract
A kind of ultra light aircraft, particularly a kind of autogyro, its basis weight range is from 210 kilograms to 230 kilograms, and maximum take-off weight is 450 kilograms.The length of this aircraft (L) scope is between 4950 and 5150 millimeters.The load supporting structure that constitutes the distinctive support frame of autogyro is to be made by the tubular member of several titanium alloys, they are converged to many nodes, be positioned at the center node (KC1 on the plane of symmetry of autogyro ... KC4), the horizontal node (KL1 that is symmetrically distributed with respect to the plane of symmetry ... KL7).The node locus of representing with three coordinate axlees is proportional with the length (M) of the load supporting structure that is elected to be basic specification.
Description
The present invention relates to a kind of aircraft of microlight-type, particularly a kind of autogyro makes it be easy to finish hover, move to all directions around self axle rotation with respect to self axis of symmetry, comprises flight backward.
The ultra light aircraft that exists can be divided into three types at present:
The aircraft of 1 medium-sized rigid wing;
The aircraft of 2 flexible wings (Luo Jialuo wing Rogallo wing);
The cyclogyro of 3 rotor blades.
The structure of above-mentioned three class aircrafts is fairly simple, and just because of this reason, their weight can be comprised at an easy rate by in the law regulations institute restricted portion.Yet the aircraft of all these types all needs an esplanade, though can be shorter on the length, so that land and take off.Because these aircrafts all do not have ability hover or around self axle rotation or vertical flight as autogyro, thereby the manoevreability of these aircrafts and autogyro is compared in fact very big difference.
Delta-winged aircraft, cyclogyro and little ultra light aircraft have been created by the amateurs that those have flight mechanics knowledge, although these aircraft have many advantages, yet, in the field of autogyro, in fact also do not realize, this is because relevant flight mechanics and manufacturing process also will be tried to achieve too complexity and too accurate, has exceeded non-professional designer's scope.
In other words, though in order to satisfy the requirement of microlight-type level, as long as the physical dimension of dwindling aircraft pari passu, just can accomplish this point, and be foolproof, even reduce maximum flying speed, provide ability for oneself, ceiling altitude and similar other characteristic, still, some problems in the aircraft (as autogyro) quite complicated on physical construction of solving must be difficulties more.
The objective of the invention is to make a kind of weight limit the autogyro that is the microlight-type level, that is to say, scope with basis weight is not having under the situation of floating drum between 210 to 230 kilograms, and maximum take-off weight is 450 kilograms, under the situation of amphibious type, maximum take-off weight is 500 kilograms, and such aircraft is with regard to airworthiness, for example manoevreability that people were concerned about, stability and safety, as common autogyro, and easy operating.
Further object of the present invention is, autogyro can be equipped needed accessory equipment and control setup, has more comfortable aircraft cockpit, and has the shirtsleeve operation control system, and this system utilizes prior art manufacturing.Autogyro also can be provided with some specialized apparatus (snowfield skid, floating drum that the landing ocean is used and miscellaneous equipment) according to the final use of aircraft.These equipment have exceeded the scope of the application's patent.
Except in order to move and to carry out various work and transport one to two personnel, it also is favourable in agriculture field that this class autogyro uses, and for example is used to spray insecticide.At present, various autogyros or aircraft are rented in carrying out this work, just not saying the operating charges of their costliness and need traffic pass, these aircraft also to mean to exist some with such as the relevant practical problems of product such as spraying insecticide.In order to transport personnel; particularly importantly can use the little lightweight aircraft of size; make and on mountain area, bank or boats and ships, to use very limited hardstand natural or building, so that in the area of road difficulty rescue noneffectives or monitor road traffic, forest and ocean.
At present, some above-mentioned work can't be implemented, can not be realized by common autogyro even, yet, by using a kind of problem that can reduce the driver training aspect, have the microlight-type autogyro that productive costs is low and be easy to drive again, overcome above-mentioned difficult aspect, obtained great success.
From above-described content, and notice this microlight-type autogyro than low production cost, the commercial promise of such autogyro is very good.
According to the present invention, as long as according to specific aerodynamic relational expression, and the relation between size, weight and the basic three-dimensional structure shape, and the configuration mode (these will be narrated below) of power part and main quality just can be reduced to desired degree with the size and the weight of autogyro.In addition, these relational expressions itself are not purposes, and they represent the feature of this class autogyro.
Owing to relate to quite complicated structure, so can only narrate some most important structure members.In order to realize predetermined purpose of the present invention, the leading dimensions of these parts, the configuration of quality, the particularly relation between these parameters all are proved to be very crucial and play a decisive role.
Obviously, the present invention is not limited to embodiment shown in the drawings, or rather; the protection domain of the structure of microlight-type double seat autogyro commonly used; the structure that also includes the single seated autogyro just slightly reduces a bit on width, still represents its characteristic by identical fundamental relation formula.
As shown in drawings:
Fig. 1 represents the schematic side view by whole the autogyro of one embodiment of the present of invention, and demonstrates the in-to-in parts with transparent way;
Figure 1B has represented the enlarged diagram of Fig. 1 upper end, demonstrates the main screw head especially;
Fig. 2 represents to include the full side view of landing gear in interior basic structure;
Fig. 3 represents along the front elevation of the semi-sictional view of Fig. 2 III-III line;
Fig. 4 represents along structure back view shown in Fig. 2 IV-IV direction, that have landing gear;
Fig. 5 represents the birds-eye view by structure shown in Figure 2;
Fig. 6 represents the signal front-side perspective view to structure shown in Figure 5 by Fig. 2;
Fig. 7 represents the lateral plan of the center-of-gravity position of main quality such as driving engine, fuel tank, reduction gear apparatus, chaufeur and passenger;
Fig. 8 represents the birds-eye view of the position configuration of the main quality similar to Fig. 7;
Fig. 9 represents the front elevation of the position configuration of basic load.
Fig. 1 is the schematic side view of microlight-type autogyro, and by numeral 1 its complete machine of expression, therein, A is expressed as forward region, and B is expressed as middle region, and C is expressed as rear area.
The A district is equipped with aircraft cockpit, and it has comprised crew's seat; Flight controller, as joystick 12, it allows propeller plane tilt with known method operation, makes aircraft advance, fall back or shifted laterally; Also have pedal 14, it works to tail undercarriage 26, be used for controlling party to; The kit instrument is on instrument carrier panel 16, and instrument carrier panel 16 is arranged on the opposite of driver's seat.Under the situation of double seat autogyro, controller is provided with two covers, so that allow two chaufeurs to drive an airplane.These control setups all are the equipment that everybody is familiar with already.
But aircraft cockpit adopts Fast Installation/or the mode of dismounting, and with composite material fairing 13 it is protected, and the positive front portion of aircraft cockpit is provided with big window 15, and this window obtains the fabulous visual field with assurance.Enter aircraft cockpit by two fan doors 17, this two fans door 17 also can be removed, and does not entail dangers to flight operation like this.
The load supporting structure of the autogyro that is configured to by the metal support of tubular member is indicated all sidedly in Fig. 1 to Fig. 6, represents with numeral 50.Support frame is the integral structure that is made of interconnective tubular member, in above-mentioned support frame, its high parts that rise are flagged as 50B, these parts are the middle region B that are in autogyro in fact, just Qian extended part is flagged as 50A, this member supporting the floor of seat and aircraft cockpit, and flight control unit and instrument carrier panel also are fixed on this parts place.The function of parts 50B is to guarantee to obtain necessary stability and rigidity with the little weight of most probable.The driving engine 44 that the band centrifugal clutch is arranged that is connected with above-mentioned parts, fuel tank, the main-gear box 40 that has flywheel gear and the storage battery of starting device.Above-mentioned support frame is also supporting the axle sleeve 45 of main screw axle.Engine controller and aircraft tension bar also pass above-mentioned support frame.
According to the present invention, rear area C has comprised the tail boom 20 that is made of self-supporting steel plate cylinder, and this cantilever directly is fixed on the parts 50B of load supporting structure 50, and it is being supported by two shaft-like members 22, and member 22 is fastened on the load supporting structure.Be fixed with in the end of above-mentioned tail boom 20 empennage 24 be suitable for guaranteeing desired longitudinally with horizontal stability, also be fixed with counter torque screw propeller assembly 26, it has 90 ° of mitre wheel 25.The turning cylinder 47 that passes tail boom 20 will be transmission of torque in screw propeller and its controller.
Power part includes: main screw 30, it is made up of the blade of two symmetries, adopts the method for the Hooke's coupling sleeve (being called the rocker-arm screw propeller) of two-dimensional freedom, and above-mentioned main screw and transmission shaft are joined, propeller blade can fold back, to reduce its total length; The flight controller that is used for main screw, it is made up of with horizontal alternator and total pitch changeable device axial, controls the geometrical pitch of main screw by the wobble-plate of screw propeller head 31.
Similar to main screw, counter torque screw propeller 26 also is made up of the blade of two symmetric profiles.
Control main screw by the main-gear box 40 that the belt pulley 42 from driving engine 44 moves, and control tail undercarriage 26 by horizontal shaft 47.Under the situation of engine shutdown, gear case can automatically cut off power transmission by flywheel assembly, thereby makes main screw and tail undercarriage freely rotate (spinning motion) under the internal resistance of minimum.
Below construction parameter of the present invention will be proposed.
Overall dimension:
With reference to figure 1, the overall dimension of autogyro is determined by following each relational expression again:
R
1=(screw propeller thickness of head (H))/(extreme length (L))
R
1The scope from 0.4 to 0.47 of value, preferably from 0.43 to 0.45;
R
2=(screw propeller thickness of head (H))/(maximum width (W))
R
2The scope from 1.4 to 1.5 of value, preferably from 1.42 to 1.46.
Size value L and W represented in the above-mentioned relation formula do not comprise blade.Exactly, length dimension L is the distance of measuring between the mitre wheel case 25 of the cross bar 55 of front support framework 50A and tail undercarriage; Its scope is from 4800 millimeters to 5300 millimeters, preferably from 4950 millimeters to 5150 millimeters; And maximum width W is referring to Fig. 4 corresponding to alighting run frame 56() between distance, from 1400 to 1600 millimeters of its scopes, preferably from 1450 to 1550 millimeters.
Height H be measure skid 56,56 ' bearing surface and the distance between the axle of universal coupling assembling 29.
R
3=(screw propeller disk diameter (E))/(tail undercarriage diameter (F))
R
3The scope from 5.5 to 6.5 of value, preferably from 5.9 to 6.2.
The relation of quality:
R
4=(weight of tubular support framework (50))/(basis weight (P of autogyro
V))
Its scope from 0.08 to 0.15, preferably from 0.09 to 0.12.
R
5=(weight of tail boom (20 and 24))/(basis weight (P of autogyro
V))
Its scope from 0.02 to 0.07, preferably from 0.038 to 0.045.
R
6=(weight of main screw blade)/(maximum functional weight (P
M))
Its scope from 0.05 to 0.08, preferably from 0.05 to 0.06.
At R
4To R
6Relational expression in, basis weight (P
V) be meant the weight of flight-ready autogyro under the situation of the ballace that does not have crew, fuel oil and may exist; And working weight (P
M) be meant and have all crews on the fuel tank that is full of fuel oil and the machine and the weight of flight-ready autogyro.
R
7=(main screw radius (E/2))/(width of relevant blade)
Its scope from 15 to 25, preferably from 16 to 18.
R
8=(tail undercarriage radius (F/2))/(width of relevant blade)
Its scope from 4 to 6, preferably from 4.2 to 4.4.
R
9The solidity of=main screw
Its scope from 0.033 to 0.056, preferably from 0.035 to 0.042.
R
10The solidity of=tail undercarriage
Its scope from 0.12 to 0.19, preferably from 0.13 to 0.15.The solidity value is determined by the ratio between the face area of blade and the relevant propeller circle dish cart area.
R
11=propeller load
From 8 to 16 kilograms/meter of base scopes
2, preferably from 11 to 14 kilograms/meter
2Propeller load is meant the working weight of autogyro and the main screw disc surfaces ratio between long-pending.
R
12=(distance h c)/(main screw radius (E/2))
Its scope from 0.01 to 0.02, preferably from 0.013 to 0.016.Distance between the axle that here (referring to Figure 1B), " hc " are meant universal connecting components 29 and the axis of symmetry of the leaf hub of the blade that supports main screw 30.
R
13=(the full swing angle of screw propeller)/(maximum axial displacement of center of gravity)
From 0.03 to 0.07 °/millimeter of its scope.
Power and weight relationships:
R
14=(basis weight (P
V))/(maximum functional weight (P
M))
Its scope from 0.40 to 0.60, preferably from 0.45 to 0.55.
R
15=(engine power)/(basis weight (P
V))
From 0.30 to 0.50 kilowatt/kilogram of its scope, preferably from 0.35 to 0.45 kilowatt/kilogram.
R
16=(engine power)/(maximum functional weight (P
M))
From 0.15 to 0.25 kilowatt/kilogram of its scope, preferably from 0.18 to 0.23 kilowatt/kilogram.
R
17=effectiveness factor
Its scope from 0.5 to 0.85 is preferably big as far as possible.Here, effectiveness factor be meant got rid of the ground influence, when the aerial hover of set point required minimum theoretical power and the ratio between the actual power that requires.
R
18=advance coefficient
Its scope from 0.15 to 0.35, preferably from 0.2 to 0.28.Advance coefficient is meant the ratio between the circumferential velocity of the translatory velocity of autogyro and main screw blade.
Fig. 2 to Fig. 6 expresses the three-dimensional load supporting structure according to autogyro of the present invention, represents total with numeral 50.Above-mentioned carry that to cut supporting structure be that metal support by tubular member is configured to, preferably make by titanium alloy.Owing to adopted this means, made under minimum weight, to obtain maximum drag.By present embodiment-double seat autogyro, describe above-mentioned support frame in detail.In order to determine to the space the specific member of above-mentioned load supporting structure, to represent with three cartesian corrdinate, here, Z axle or vertical axis be with the vertical symmetry plane that is arranged on support frame on the axis of turning cylinder of main screw 30 corresponding to, and constitute three, obtain along horizontal surface by X and the Y-axis shown among Fig. 5, this horizontal surface is the tubular member 52 by basic horizontal, 54 is formed, and with skid 56,56 ' plane parallel, as the ground-surface supporting base of aircraft cockpit (referring to Fig. 2).
The total length M of load supporting structure 50 is meant that in fact, it equals the 40%(of autogyro total length L referring to Fig. 1 by measured distance between the terminal vertical surface of the preceding bar 55 of just preceding extended part 50A and parts 50B).In the embodiment that is narrated, preferably from 2000 to 2060 millimeters of the scopes of M.By transparent view 6, and, can understand the very complicated spatial destribution state of the tubular member of load supporting structure 50 well in conjunction with Fig. 2,3,4,5.These accompanying drawings are that the actual size with the member of above-mentioned load supporting structure serves as that the basis is drawn in proportion and formed.
This load supporting structure is to be made of many tubular members (for for simplicity, being called pipe fitting), has many node K simultaneously.If what relate to is the center node, just be positioned at the node on the vertical symmetrical plane of autogyro, these nodes are marked as KC; If node is to be on the side, then be marked as KL, always be positioned at and above-mentioned vertical symmetrical plane symmetry between the position of putting.
The top node KC1 that is positioned on the Z axle is the vertex that is in support frame, it be with the sleeve 45 that is positioned at the main screw turning cylinder on, by three pipe fittings 60,60 ' and 62 intersection points that form coincide.The coordinate plane that it is set up from X and Y-axis is the place of the distance of Z, the scope of Z from 0.63 to 0.67M.
In one embodiment, the coordinate position of KC1 is X=0; Y=0; The Z=1330 millimeter.
From the pipe fitting 60,60 of symmetrical node KL1 ' and from the pipe fitting 64,64 of node KL2 ' be continuous, they coincide at above-mentioned node KL1 place, and are bent at this some place.
Seven pipe fittings are in node KL2 place simultaneously, pipe fitting 66 be from node KL2 downwards towards node KL3, and node KL3 is arranged on the X-Y coordinate plane, its coordinate Z=0.Pipe fitting 66 be with pipe fitting 64,60 and 60 ', 64 ' locate at grade, above-mentioned plane tilts to the afterbody of autogyro, becomes 8 ° to 12 ° leaning angle with corresponding vertical surface, preferably becomes 10 ° of leaning angles.
Another basic node is a complexity, the rear portion node KC2 through fully strengthening, and the X coordinate figure of this node approximates 800 millimeters, promptly arrives in the scope of 0.4M 0.37; The scope of its Z coordinate figure is from 950 to 965 millimeters, promptly arrives in the 0.46M scope 0.42.The coordinate of symmetry node KL4 is: X is about 800 millimeters, Y=± 300 millimeter, the Z=315 millimeter promptly is followed successively by: X is 0.38 in the 0.41M scope, Y is ± 0.14 in ± 0.15M scope, and Z 0.13 in the 0.16M scope.By a continuous pipe fitting is bent to inverted V-shaped form arm 68,68 ', node KL4 is connected with node KC2.Tension member 69(is referring to Fig. 5) be fastened to arm 68,68 ' on, as the unitor of tail boom 20.By horizontal cross bar 70,71 strengthen arm 68,68 ', above-mentioned arm 68,68 ' the lower end, just symmetrical node KL4 is coupled together them by horizontal cross bar 72.With unitor 73(referring to Fig. 2) and the horizontal tube 74 of rear support 75 be fastened on the horizontal cross bar 72, the lower end of rear support 75 is fastened with skid 56,56 ', and 56,56 ' corresponding end also is connected with similar bearing 76, it is the middle part that is fastened on extension 50A basically, and extension 50A begins to extend forward from node KL3, will narrate below about node KL3.
Coming down to be arranged on the Z coordinate figure by skid 56,56 ' formed supporting plane is 0.24 to 0.26M position.Must be noted that bending pipe fitting 68,68 among Fig. 2 ' and bearing 75 all be to be on the same terminal vertical plane surface of load supporting structure 50B.
Use pipe fitting 80,82; 80 ', 82 ', node KL4 and node KL2, KL3 are coupled together, in the both sides of symmetry, with pipe fitting 66,66 ' together, form a leg-of-mutton member.Usage level cross bar 84 and 86, paired node KL1 is balancedly coupled together, and horizontal brace rod 84 and 86 is to be connected node KC3 place, center, above-mentioned center node KC3 again successively with pipe fitting 88,88 ' be connected, pipe fitting 88,88 ' form a triangle with transverse horizontal pipe fitting 90, and pipe fitting 90 directly is connected with node KL2.
According to one embodiment of present invention, node KL1 has following coordinate figure:
From-85 to-95 millimeters of the scopes of X are promptly from-0.04 to-0.05M;
From ± 390 to ± 410 millimeters of the scopes of Y are promptly from ± 0.19 to ± 0.21M;
From 820 to 860 millimeters of the scopes of Z, promptly from 0.4 to 0.42M.
Node KL2 has following coordinate figure:
From-175 to-195 millimeters of the scopes of X are promptly from-0.085 to-0.10M;
From ± 460 to ± 490 millimeters of the scopes of Y are promptly from ± 0.22 to ± 0.24M;
From 275 to 295 millimeters of the scopes of Z, promptly from 0.13 to 0.16M.
Node KL3 has following coordinate figure:
From-225 to-245 millimeters of the scopes of X are promptly from-0.11 to-0.12M;
From ± 465 to ± 485 millimeters of the scopes of Y are promptly from ± 0.23 to ± 0.24M;
Z＝0。
Node KC3 has following coordinate figure:
From-90 to-100 millimeters of the scopes of X are promptly from-0.044 to-0.048M;
From 790 to 810 millimeters of the scopes of Z, promptly from 0.37 to 0.42M.
Parallelogram tubular member between paired node KL2 and KL3 also needs to give same rigidity.From the node KC4 at the middle part that is positioned at pipe fitting 90,, use pipe fitting 94 that node KL3 is laterally connected mutually by pipe fitting 92,92 ' node KC4 is connected with above-mentioned node KL3.In order further to improve the high bilge construction spare 50B of rising, by using pipe fitting 100,100 ', allow node KC2 be fastened on the paired node KL1, and pipe fitting 100,100 ' be to be on the also downward-sloping slightly forward plane, in fact, with respect to the horizontal plane (referring to Fig. 2), its inclination is 5 ° to 9 °, preferably tilts 7 °.In addition, by paired pipe fitting 102,102 ', allow node KC2 be fastened on the paired node KL2.
The X of node KC4 is identical with the Z coordinate figure with the X of node KL2 with the Z coordinate figure.
The forepiece 50A(of load supporting structure 50 is referring to power 6) be to be connected with KL3 with paired node KL2.Begin to extend forward from node KL3, have long whole boss N(for 0.5M referring to Fig. 1) above-mentioned forepiece 50A form an obtuse-angled triangle in side direction, the base of this obtuse-angled triangle is to be made of two continuous pipe fitting 52-54 and 52 '～54 ', each root is made by identical horizontal tube, all be terminated on the end node KL5, by cross bar 55, node KL5 machine is coupled together to ground.Re-use pipe fitting 58,58 '; 59,59 ', node KL5 will be connected with node KL2.The middle part of the boss N of part 50A forwardly, be provided with a vertical middle tension member, represent with alphabetical P, respectively by node KL6 and last node KL7 limit down, two following node KL6 are laterally connected it by pipe fitting 110, and in addition two go up node KL7 and it laterally connected by pipe fitting 112.Above-mentioned intermediate member P couples together with several reinforcement tubular members in its scope.The tubular member of these reinforcements can utilize known method, for example, can be used as the support of control operating rod.Following horizontal pipe fitting 110 is connected on the horizontal pipe fitting 94 of front rail 55 and link node KL3 by pipe fitting 120,120 ' end wise.Pipe fitting 120 and 120 ' the space apart from the scope of n be from 0.08M to 0.09M.By bar 124,124 ', the last pipe fitting 112 of tension member is connected on the horizontal pipe fitting 90 that joins with node KL2, bar 124 and 124 ' space distance be with above-mentioned pipe fitting 120 and 120 ' spacing distance basic identical.In addition, pipe fitting 126,126 ' node KL7 is connected with node KL3.
As mentioned defined like that, node KL5 and KL6 are on the X that is positioned at the X, the Y that use as the benchmark of load supporting structure 50, Z three axes, the Y plane, therefore, their coordinate figure Z=0, and node KL7 has the Z coordinate figure, its scope from 0.065 to 0.075M.
It is following numerical value that the X and Y coordinates value of node KL5 and KL6 is divided in addition:
The scope of KL5:X value is from-0.58 to-0.62M;
The scope of Y value is from ± 0.190 to ± 0.215M;
The scope of KL6:X value is from-0.34 to-0.36M;
The scope of Y value is from ± 0.23 to ± 0.24M
The X and Y coordinates value of node KL7 is identical with the X and Y coordinates value of KL6.
Distance between the node KL5 is corresponding to 0.42M in pairs.
Configuration state (referring to Fig. 7,8,9) about main quality, the distance that mass cg S1 that is made up of chaufeur and passenger (in aircraft cockpit each other laterally in abutting connection with) and S2 are arranged on from the X-Y reference plane is the place of Q, the scope of Q value from 0.23 to 0.27M, above-mentioned quality S1 and S2 are with respect to the plane of symmetry and separated, the coordinate figure of the distance Y of being separated is about ± and 280 millimeters, the scope that is Y is from ± 0.12 to ± 0.15M, and the scope of X coordinate figure is from-0.22 to-0.25M.
The center-of-gravity position of the driving engine of representing with digital S3 is: the Z coordinate figure is substantially equal to the Z coordinate figure of above-mentioned quality S1 and S2, and the scope of X coordinate figure is to 0.22M from 0.2.
The center of gravity of the speed reduction gearing of representing with digital S4 is that its Z coordinate figure is about 880 millimeters with the axis being aligned of the transmission shaft 47 of running tail undercarriage, promptly its scope from 0.42 to 0.44M.
Fuel tank S5 is actually vertical with speed reduction gearing and aligns, be positioned at speed reduction gearing below, the height Z coordinate figure of the center of gravity of this fuel tank is to approach the coordinate figure passenger and height of gravitational center Z driving engine.
About chaufeur and passenger's mass value, normally single consideration changes between 75 and 85 kilograms.The deviation on the total weight might occur, be alone on autogyro if chaufeur is only arranged, and may only be 1/2nd weight.Usually, all quality of having considered and other basis weight value of sign autogyro level P
VConnect, its scope is within following train value:
S1 and S2(be value individually) 0 to 0.38Pv;
S3 0.125 to 0.25Pv;
S4 and S5 0.10 to 0.27Pv
In all loads, the maximum along track bias of center of gravity estimates in ± 240 millimeters scopes, and maximum lateral deviation is defined in ± 150 millimeters scopes in.With the Z axle that coincides with the main screw axle is the center of gravity that benchmark comes quality measurement.
Though the present invention is had been described in detail and sets forth according to embodiment, those of skill in the art recognize that under the situation of the protection domain of claims of the present invention, can make many changes.
Claims (16)
1, a kind of ultra light aircraft, particularly a kind of autogyro is not having under the situation of floating drum maximum take-off weight P
MIt is 450 kilograms; Basis weight P
VFrom 210 to 230 kilograms of scopes, it comprises a support frame that load supporting structure (50) that tubular member makes is arranged as aircraft, tail boom (20) is fastened on this framework; In the known manner, the counter torque screw propeller (26) that is provided with empennage (24) in the rear end of tail boom, drives by mitre wheel case (25), and main screw (30), above-mentioned load supporting structure is to be made by many tubular members of using as press rods and tension bar basically, the integrated many center node (KC1 of meeting ... KC4), be arranged on vertical plane of symmetry of autogyro; Horizontal node (KL1 ... KL7), be arranged on two sides of the above-mentioned plane of symmetry symmetrically, above-mentioned node (the KC of load supporting structure (50) ...) and (KL ...) the locus, and other parts, for example main quality (S1 ... S5) locus all is indicated on X, Y, on the Z 3-D walls and floor, the geometrical axis of the vertical axis Z of this system of axes and main screw axle (30) coincides, and X-axis and horizontal Y-axis lay respectively on the formed horizontal surface of following pipe fitting by forepiece (50A) longitudinally, at the rear portion, parts (50B) in addition, it in height further raises, and forms a complete load supporting structure (50), it is characterized in that:
1) when removing main screw, the mensuration of the length of autogyro (L) is from the mitre wheel case (25) of the preceding cross bar (55) of the forepiece (50A) of load supporting structure (50) beginning up to counter torque tail undercarriage (26), from 4800 to 5300 millimeters of its length ranges, preferably from 4950 to 5150 millimeters;
2) mensuration of the length (M) of load supporting structure (50) is the terminal vertical plane surface from above-mentioned cross bar (55) to load supporting structure (50), as many as 0.4L, and promptly the scope of length M is from 1920 to 2120 millimeters, preferably from 2000 to 2060 millimeters;
3) scope of the maximum width (W) of transverse distance is from 0.70 to 0.80M between expression alighting run frame (56,56 '), preferably from 0.72 to 0.75M;
4) by the wobble-plate of the head (31) of main screw (30) and above-mentioned skid (56,56 ') areal of support between measured height (H) scope preferably from 0.43 to 0.45L, and when being benchmark with maximum width (W), highly the scope of (H) is from 1.4 to 1.5W, preferably from 1.42 to 1.46W;
5) when with X, Y, when the Z three axes is represented, be benchmark with the length (M) of load supporting structure (50), the center node (KC1 of the parts (50B) of structure (50) ... KC4) coordinate figure scope is between following numerical value:
(KC1) X=0 Z=0.63 is to 0.67M;
(KC2) X=0.37 to 0.40M Z=0.42 to 0.46M;
(KC3) X=-0.044 to-0.048M Z=0.37 to 0.42M;
(KC4) X=-0.08 to-0.10M Z=0.13 to 0.16M.
When 6) being benchmark with the length (M) of load supporting structure (50), the horizontal node (KL1 of the parts (50B) of structure (50) ... KL4) coordinate figure scope is between following numerical value:
(KL1) X=-0.04 arrives-0.05M;
Y=± 0.19 is to 0.21M;
Z=0.40 is to 0.42M;
(KL4) X=0.38 is to 0.41M;
Y=± 0.15 is arrived ± 0.15M;
Z=0.13 is to 0.16M;
(KL2) X=-0.085 arrives-0.10M;
Y=± 0.22 is to 0.24M;
Z=0.13 is to 0.16M;
(KL3) X=-0.11 arrives-0.12M;
Y=± 0.23 is to 0.24M;
Z=0。
When 7) being benchmark with the length (M) of load supporting structure (50), the horizontal node (KL5 of the forepiece (50A) of structure (50) ... KL7) coordinate figure scope is between following numerical value:
(KL5) X=-0.58 arrives-0.62M;
Y=± 0.190 is arrived ± 0.215M;
Z=0；
(KL6) X=-0.34 arrives-0.36M;
Y=± 0.23 is arrived ± 0.24M;
Z=0；
(KL7) X=-0.34 arrives-0.36M;
Y=± 0.23 is to 0.24M;
Z=0.065 is to 0.075M.
2, by the described ultra light aircraft of claim 1, particularly a kind of autogyro, it is characterized in that, node (KC1) be on the pilot sleeve (45) with the vertical rotation axle, by three pipe fittings (60,60 ' and 62) intersection point that forms coincides, this vertical rotation axle is that transmission of torque is arrived on the blade of main screw (30), the first two pipe fitting (60 of being mentioned, 60 ') the other end be secured on the symmetrical node (KL1), and the other end of another pipe fitting (62) is secured on the node (KC2).
3, by claim 1 and 2 described ultra light aircrafts, particularly a kind of autogyro, it is characterized in that, thereby node (KC2) is connected with node (KL4) by a continuous pipe fitting being curved inverted V-shaped, the arm (68 of above-mentioned bending pipe fitting, 68 ') strengthened by horizontal cross bar (70,70 '); The tension member of the tail boom that is used for connecting autogyro (69) is placed on the crooked summit by the formed V-arrangement pipe of above-mentioned pipe fitting.
4, by the described ultra light aircraft of claim 1 to 3, particularly a kind of autogyro, it is characterized in that, symmetry node (KL4) is connected with each other them by cross bar (72), and cross bar (72) is fastened on the horizontal tube (74) of bearing (75) with unitor (73), the lower end of bearing (75) is fixed on the rear portion of skid (56,56 '), above-mentioned node (KL4) and (KC2) be on the same vertical plane surface with above-mentioned bearing (75).
5, by the described ultra light aircraft of claim 1 to 4, particularly a kind of autogyro is characterized in that, node (KC1, KL1, KL2, KL3) on the rear portion plane inclined of load supporting structure (50), become 8 ° to 12 ° leaning angle with vertical direction, preferably become 10 ° leaning angle.
6, by the described ultra light aircraft of claim 1 to 5, particularly a kind of autogyro, it is characterized in that, by being in the pipe fitting (100 on the plane that turns forward, 100 '), node (KL1) is connected with node (KL2), and this clinoplane is from the horizontal by 5 ° to 9 °, preferably near 7 °.
7, by the described ultra light aircraft of claim 1 to 6, particularly a kind of autogyro, it is characterized in that, by pipe fitting (84,86), node (KL1) is connected with node (KC3), again by means of pipe fitting (88,88 ') node (KC3) is connected with node (KL2), thereby form a triangle with the transverse horizontal pipe fitting (90) of link node (KL2).
8, by the described ultra light aircraft of claim 1 to 7, particularly a kind of autogyro, it is characterized in that, node (KL4) and node (KL2) are joined by pipe fitting (80,80 '), again by means of pipe fitting (82,82 '), node (KL4) and node (KL3) are joined, thus with link node (KL2) and pipe fitting (KL3) (66,66 ') together, form a triangle member in the both sides of load supporting structure (50).
9, by the described ultra light aircraft of claim 1 to 8, particularly a kind of autogyro, it is characterized in that, by pipe fitting (100,100 '), node (KC2) is connected with node (KL1), thus with the pipe fitting (60 of copolymerization on the vertex (KC1) of load supporting structure (50), 60 ', 62) form a tetrahedral angle together.
10, by the described ultra light aircraft of claim 1 to 9, particularly a kind of autogyro, it is characterized in that, the forepiece (50A) that is placed on the load supporting structure (50) in the autogyro proparea (A) forms a boss, this boss be fastened to load supporting structure (50) back part (50B) node (KL2) and (KL3) on, the longitudinal length (N) of above-mentioned boss parts (50A) is the distance of measuring between cross bar (55) and the node (KL3), approximates 0.5M.
11, by the described ultra light aircraft of claim 1 to 10, particularly a kind of autogyro, it is characterized in that, in the forepiece (50A) of load supporting structure (50), the horizontal base of boss parts is by two continuous pipe fittings (52,54) and (52 ", 54 ') form, first section pipe fitting (52; 52 ') be parallel to each other; second section pipe fitting (54,54 ') assembled symmetrically forward, form node (KL5); node (KL5) is coupled together by means of cross bar (55); the length of cross bar (55) be between the described parallel pipe fitting (52,52 ') distance 90%, this distance is corresponding to 0.42M.
12, by the described ultra light aircraft of claim 1 to 11, particularly a kind of autogyro is characterized in that, by pipe fitting (58,59; 58 ', 59 '), node (KL5) and node (KL2) are joined, the boss of horizontal surface form and below pipe fitting (52,54,52 ', 54 ') setting of same structure, pipe fitting (52,54) point of inflection forms node (KL6), the point of inflection of pipe fitting (58,59) forms node (KL7), and they all have the node of symmetry, above-mentioned node is connected respectively with (112) by pipe fitting (110), form the vertical member (P) of a centre, above-mentioned vertical member (P) connects with many reinforcement pipe fittings with skew intersection vertically in self scope.
13, by the described ultra light aircraft of claim 1 to 12, particularly a kind of autogyro is characterized in that:
The diameter of main screw disk (E) is 5.9 to 6.2 times of diameter (F) of tail undercarriage (26) preferably;
The scope of the radius of main screw (E/2) is 15 to 25 times of width of corresponding blade (30), preferably 16 to 18 times;
The scope of the radius of tail undercarriage (F/2) is 4 to 6 times of width of corresponding blade (26), preferably 4.2 to 4.4 times;
Ratio between the area of main screw blade (30) and the area of main screw disk is in 0.033 to 0.056 scope, preferably in 0.035 to 0.042 scope, and the area of the blade of tail undercarriage (26) and the ratio between the tail undercarriage disc area are in 0.12 to 0.19 scope, preferably in 0.13 to 0.15 scope;
The weight range of load supporting structure (50) is microlight-type level aircraft regulation basis weight (P
V) 0.08 to 0.15P
V, preferably 0.09 arrive 0.12P
V;
And the weight range of empennage (24) tail boom (20) together is to 0.07P from 0.02
V, preferably 0.038 arrive 0.045P
V;
Ratio between the working weight of aircraft and the main screw disc area is at 8 to 16 kilograms/meter
2Scope in, preferably at 11 to 14 kilograms/meter
2In the scope;
The scope of the distance (hc) between the axle of Hooke's coupling and the axis of symmetry of leaf hub is 0.01 to 0.02(E/2), preferably 0.013 arrive 0.016(E/2), (E) be the diameter of main screw disk;
Ratio range between the maximum angle of oscillation of main screw and the maximum longitudinal travel of center of gravity is 0.03 °/millimeter to 0.07 °/millimeter;
Engine power and basis weight P
VRatio be in 0.30 to 0.50 kilowatt of/kilogram scope, preferably in 0.35 to 0.45 kilowatt of/kilogram scope, and engine power and maximum functional weight P
MRatio be in 0.15 to 0.25 kilowatt of/kilogram scope, preferably in 0.18 to 0.23 kilowatt of/kilogram scope;
Get rid of the ground influence, the ratio range when hover between the power of needed minimum theoretical power and actual needs is 0.5 to 0.85;
Ratio between the circumferential velocity of the moving velocity of microlight-type autogyro and main screw blade, promptly " advance coefficient " is in 0.15 to 0.35 scope, preferably in 0.2 to 0.28 scope.
14, by the described ultra light aircraft of claim 1 to 13, particularly a kind of autogyro, it is characterized in that, represent the coordinate figure scope of center of gravity of main quality of chaufeur and passenger (S1 and S2), driving engine (S3), drop-gear box (S4) and fuel tank (S5) as follows:
(S1 and S2) X=-0.22 arrives-0.25M;
Y=± 0.12 is to 0.15M;
Z=0.23 is to 0.27M;
(S3) X=0.20 is to 0.22M;
Y＝0;
Z=0.23 is to 0.27M;
（S4） X＝0;
Y＝0;
Z=0.42 is to 0.44M;
（S5） X＝0;
Y＝0;
Z=0.23 is to 0.27M;
15, by the described ultra light aircraft of claim 1 to 14, particularly a kind of autogyro is characterized in that, with the basis weight P of autogyro
VBe benchmark, the maxim of the chaufeur (S1) and the passenger's (S2) that may exist the quality 0.38P that respectively does for oneself
V; The mass range of driving engine (S3) is to 0.25P from 0.125
V, and the mass range of drop-gear box (S4) and fuel tank (S5) sum from 0.10 to 0.27P
V
16, by claim requirement 1 to 15 described ultra light aircraft, particularly a kind of autogyro, it is characterized in that, constitute the pipe fitting of load supporting structure (50), comprise the member (22) that supports tail boom (20), bearing (75,76) and alighting run frame (56,56 ') all are the tubular members of titanium alloy.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ITMI92A00243 | 1992-10-23 | ||
| ITMI922433A IT1255907B (en) | 1992-10-23 | 1992-10-23 | ULTRALIGHT AIR VEHICLE, IN PARTICULAR HELICOPTER. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1086184A true CN1086184A (en) | 1994-05-04 |
Family
ID=11364159
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN93118478A Pending CN1086184A (en) | 1992-10-23 | 1993-10-14 | The microlight-type autogyro |
Country Status (7)
| Country | Link |
|---|---|
| CN (1) | CN1086184A (en) |
| AR (1) | AR248246A1 (en) |
| AU (1) | AU5154993A (en) |
| BR (1) | BR9307278A (en) |
| IT (1) | IT1255907B (en) |
| WO (1) | WO1994010033A1 (en) |
| ZA (1) | ZA936671B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102774492A (en) * | 2012-06-08 | 2012-11-14 | 无锡汉和航空技术有限公司 | Small unmanned helicopter fuselage |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
| CN105235896A (en) * | 2015-10-20 | 2016-01-13 | 洲际联合超伦科技（北京）有限公司 | Multifunctional lightweight unmanned helicopter |
| CN105329435A (en) * | 2014-12-19 | 2016-02-17 | 四川精石航空科技开发有限公司 | Tubular ultra-light helicopter frame |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738504B (en) * | 2014-01-06 | 2017-04-19 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2818226A (en) * | 1951-11-20 | 1957-12-31 | Hiller Helicopters | Rotary wing aircraft frame construction |
| NL6500474A (en) * | 1964-09-26 | 1966-03-28 | ||
| US3520497A (en) * | 1968-06-05 | 1970-07-14 | Rotorway Inc | Framework for a helicopter |
-
1992
- 1992-10-23 IT ITMI922433A patent/IT1255907B/en active IP Right Grant
-
1993
- 1993-09-08 AU AU51549/93A patent/AU5154993A/en not_active Abandoned
- 1993-09-08 BR BR9307278A patent/BR9307278A/en not_active Application Discontinuation
- 1993-09-08 WO PCT/IT1993/000092 patent/WO1994010033A1/en active Application Filing
- 1993-09-09 ZA ZA936671A patent/ZA936671B/en unknown
- 1993-10-14 CN CN93118478A patent/CN1086184A/en active Pending
- 1993-10-20 AR AR93326329A patent/AR248246A1/en active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102774492A (en) * | 2012-06-08 | 2012-11-14 | 无锡汉和航空技术有限公司 | Small unmanned helicopter fuselage |
| CN102774492B (en) * | 2012-06-08 | 2016-03-30 | 无锡汉和航空技术有限公司 | A kind of small-sized depopulated helicopter fuselage |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
| CN105329435A (en) * | 2014-12-19 | 2016-02-17 | 四川精石航空科技开发有限公司 | Tubular ultra-light helicopter frame |
| CN105235896A (en) * | 2015-10-20 | 2016-01-13 | 洲际联合超伦科技（北京）有限公司 | Multifunctional lightweight unmanned helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| ZA936671B (en) | 1994-04-29 |
| IT1255907B (en) | 1995-11-17 |
| ITMI922433A1 (en) | 1994-04-23 |
| WO1994010033A1 (en) | 1994-05-11 |
| AU5154993A (en) | 1994-05-24 |
| AR248246A1 (en) | 1995-07-12 |
| BR9307278A (en) | 1999-06-01 |
| ITMI922433A0 (en) | 1992-10-23 |
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