CN100513214C - Rotor flight car - Google Patents
Rotor flight car Download PDFInfo
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- CN100513214C CN100513214C CNB031590209A CN03159020A CN100513214C CN 100513214 C CN100513214 C CN 100513214C CN B031590209 A CNB031590209 A CN B031590209A CN 03159020 A CN03159020 A CN 03159020A CN 100513214 C CN100513214 C CN 100513214C
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Abstract
The invention relates to a kind of self-rotation rotaplane , whose rotor wing pillar 14 , rotor wing and tailspin is easy for folding collection and take up small ground space , thus it is a kind of rotor wing flying cars which is easy for takoff or landing on the road and maneuvering traveling . The plane adopts technology as inclined-spinning storing rotor wing pillar 14 , folding rotor wing and tailspin , light prewhirl drive , land traveling system , etc , thus its flying and traveling mobility and its safety performance are great . On the base of assuring self lighting and safety , the invention can take off and land in short distance , fold or unfold the wings swiftly , and well imitate the bird's mobility in remotely flying and short walking . Generally , in the range of ten kilometers from the destination , it is easy to find the place as road that is suitable for takoff and landing of the plane . The invention can take off or land from the location , traveling to the destination and get into the family garage , finish the nonstop traffic mission from point to point , thus it is really a new kind of aircraft that can get into the family .
Description
Technical field
" rotor flight car " of the present invention relates to a kind of autorotating rotor aircraft, can be used for manned craft and model thereof, and it is the improvement invention to existing cyclogyro.
Background technology
A kind of cyclogyro of prior art, fuselage are big, the rotor pillar is fixed on body upper, and occupation space is big.It takes into account flight and ground maneuver, the power cost height of ground run with same driving engine.The aspects such as vibration damping of its high-power, light airframe structure and ground run are difficult to coupling, and its poor practicability is not carried out batch manufacturing.
The another kind of cyclogyro of prior art, its rotor pillar is fixedly mounted on body upper, and its long rotor and roomy empennage take very big space, can not park in common car garage, also do not possess the ability of highway powered travel.
The prior art helicopter has point-to-point through air communication ability, but its cost an arm and a leg, poor safety performance, limited its range of use.
The various rotor crafts of prior art, or put long rotor, roomy empennage because of height, or because of poor practicability, or because of sky high cost, or bad because of safety performance, make it or depend on special-purpose airport and come landing, or, influenced the process that aircraft enters family because of it costs an arm and a leg.People's dream hide in the hope of aerial, the dual-purpose flight car of highway, do not reach as yet practicability target, fail the numerous common people.
Observe the flight of the large birds, the landing that they can be intensive, action neatly, its important factor is: 1, their landings only need seldom be run, and have the short take-off and landing (STOL) ability.2, during the birds landing, its wing launches and regains easily and fast.3, load-carrying capacity is stronger.4, they have ground ambulatory capabilities flexibly, but with regard to its speed that moves and distance, it is auxilliary then walking about based on aerial high-speed and long distance flight, ground low speed and low coverage.5, possesses the excellent safety energy.
Summary of the invention
The present invention has reasonably solved the problems referred to above, on the basis of conventional cyclogyro, design a kind of: be suitable for flying, rotor and empennage is easy to fold, control comfort, with low cost, safe and reliable, load-carrying ability are strong, ground takes up room aircraft little, that be suitable for highway short take-off and landing (STOL) and powered travel.
This machine adopts technology such as the collected type rotor pillar 14 that verts, folding rotor and empennage, the light-duty driving of prewhirling, road running system, and its sky land manoevreability and safety and reliability are good.The lightweight highway of its equiping system drives small displacement engine, uses low speed driving, and vibration damping requires low, is fit to light-duty housing construction.In the city of traffic swelling resistance, generally less than 30 kilometers average passage rate, puffer can with its coupling, satisfied most destinations to suitable landing highway, be generally surplus in the of ten the requirement of travelling of the low coverage within the kilometer.The present invention is for aerial flight, and the relative load capacity of cyclogyro is strong, and the weightening finish that can bear its road running annex has good airflight ability; For the car of road running closely, the weight and volume that its flight part annex increases is less relatively, has more suitable road running ability.From ecological angle, this machine and flying bird are relatively, it is guaranteeing on its enough light basis, can launch quickly or folding " wing ", has good highway maneuvering performance, having simulated birds well and carried out point-to-point mobile sky, land manoevreability, is the personalized aircraft that the utmost point has development potentiality.
This machine, 1, adopt the collected type rotor pillar that verts; 2, use folding rotor and folding fin.Having reduced the land aerodynamic drag of back occupation space and road running of this machine significantly, improved its carrying capacity and lateral stability during powered travel on highway, made it easy to enter the small passenger car storehouse of family, is a kind of convenience, practical flight car.3, use the light-duty driving of prewhirling, alleviated system weight.4, the road running system that increases weight less has been installed, has possessed the ability of highway powered travel.5, blade tip is installed flash light, is used for warning of highway landing.
For achieving the above object, the present invention has adopted following technical scheme:
One of a kind of rotor flight car scheme comprises fuselage, power system, horizontal drive screw propeller, empennage, alighting gear, the parts such as collected type rotor pillar 14 and folding rotor of verting; Rotor pillar 14 upwards erect fixing after, the relative position between rotor pillar 14 and the aircraft center of gravity and the span at the oblique angle that retreats thereof are all identical with conventional cyclogyro;
The vert lower end of collected type rotor pillar 14 is rotationally connected by pillar rotating shaft 13 and fuselage, and rotor pillar 14 can vert and horizontally-arranged collection to the longitudinal axis of fuselage direction; When its rotor pillar 14 upwards erected, the pillar location lock 40 that is fixedly installed on the fuselage can lock together rotor pillar 14 and fuselage; Open pillar location lock 40 and rotor pillar 14 can be rotated and rely on fuselage, collection is to horizontally-arranged position; The collection mode of verting of rotor pillar 14 can be divided into: inhead type, collection mode such as underlying is exposed, underlying is built-in.
Above-mentioned rotor pillar 14 is an inhead type, and its pillar rotating shaft 13 is installed on the top of fuselage.
Above-mentioned rotor pillar 14 is exposed for underlying, and rotor pillar 14 is exposed to outside the fuselage, and its pillar rotating shaft 13 is installed on the underbelly outside.
Above-mentioned rotor pillar 14 is built-in for underlying, and its pillar rotating shaft 13 is installed within the fuselage;
The rotor pillar 14 that erects, its lower part is hidden within the fuselage; Its canopy 2 is laterally opened; Open canopy 2 and pillar location lock 40, upwards rotate rotor pillar 14, rotor pillar 14 is entered within the pillar hole 4 and erect, pillar location lock 40 can be fixed together rotor pillar 14 and fuselage top cover 41 together with fuselage; Open canopy 2, pillar location lock 40, rotor pillar 14 can vert and horizontally-arranged collection.
The above-mentioned collected type rotor pillar 14 that verts has oar dish pitching coordinated control;
Its oar dish pitching coordinated control comprises: the bearing of rotorshaft 10, pillar rotating shaft 13, rotor pillar 14, top interlock 63, bottom interlock 64, gangbar 65, top universal driving shaft 67 and inner interlock and pitch control bar;
Link and 63 captive joint in the bearing of its rotorshaft 10 and top; Being positioned at the top universal driving shaft 67 of top interlock 63 and the upper end of rotor pillar 14 is rotationally connected; Be positioned at the shaft hole of bottom interlock 64, be installed on the root of rotor pillar 14; Its underpart interlock 64 links to each other with the pitch control bar by inner interlock;
Above-mentioned folding rotor comprises parts such as spacing back flap hinge, blade 7; On the rotation hinge of its spacing back flap hinge, from the inside to the outside, be inserted in stop collar return spring 30 and slip stop collar 9 respectively; Its rotate hinge by flapping hinge 8 and lead lag hinge 6 both one of constitute;
Launch blade 7, the inner of slip stop collar 9 is subjected to the elastic force effect of stop collar return spring 30 and pushed outwardsly goes out, low-angle free flapping action when slip stop collar 9 does not influence blade 7 rotations is turned back but slip stop collar 9 can stop blade 7 to carry out wide-angle along the rotation hinge; Move inward slip stop collar 9, compression stop collar return spring 30, slip stop collar 9 no longer limits the turnover of blade 7, and its blade 7 can inwardly be turned back and be collected the direction of horizontally-arranged rotor pillar 14 extremely.
Two of a kind of rotor flight car scheme, it comprises fuselage, power system, horizontal drive screw propeller, empennage, alighting gear, autorotating rotor, the light-duty driving of prewhirling; Its light-duty prewhirling drives to the machine inhaul drives, and rotorshaft 10 links to each other with sheave 16 by the ratchet 27 of unidirectional rotation; Its sheave can be subjected to an end fixed thereon and with different directions twine thereon trailing cable 17 and the effect of the rope 38 that resets; The other end of pulling trailing cable 17 in machine drives the rotor rotation of prewhirling through pulley 20, sheave 16, check tooth 28, ratchet 27, rotorshaft 10; Spurring the rope 38 that resets makes trailing cable 17 recover original position.
Three of rotor flight car scheme, it comprises fuselage, power system, horizontal drive screw propeller, tail boom 74, vertical tail 5, alighting gear, the parts such as collected type rotor pillar 14 and folding rotor of verting; Its vertical tail 5 is a foldable structure; Vertical tail 5 is made up of the anterior rudder face 31 that is installed on tail boom 74 ends, rear portion rudder face 32, folding rudder face, rudder face location lock 35, back flap hinge etc.; Rear portion rudder face 32 includes folding rudder face; Folding rudder face can launch by back flap hinge, and folding rudder face can also fold by back flap hinge; Its rudder face location lock 35 is used for to folding the fixing of rudder face, to avoid the Free Slosh of folding rudder face.
Four of rotor flight car scheme comprises fuselage, power system, horizontal drive screw propeller, tail boom 74, vertical tail 5, alighting gear, the parts such as collected type rotor pillar 14 and folding rotor of verting; Its vertical tail 5 is a foldable structure; The vertical tail 5 of foldable structure is terminal hinged by vertical shaft back flap hinge 71, plane rotating hinge and tail boom 74; The plane rotating hinge is made of one of transverse axis back flap hinge 70a and longitudinal axis back flap hinge 70b; Vertical tail 5 can utilize vertical shaft back flap hinge 71, plane rotating hinge, with it or stand vertically normal use or the folding horizontally-arranged rear end that is concealed in tail boom 74, and by dowel bolt 72 and setscrew nut 73, is fixed in the rear end of tail boom 74.
Five of a kind of rotor flight car scheme comprises fuselage, power system, horizontal drive screw propeller, empennage, alighting gear, the collected type rotor pillar 14 that verts, folding rotor and road running system; Its road running system satisfies the needs of highway communication, and it comprises parts such as surface driving, vehicle acousto-optic, brake system; Its surface driving is used the special-purpose small displacement engine 15 of highway.
Six of a kind of rotor flight car scheme comprises fuselage, power system, horizontal drive screw propeller, empennage, alighting gear, the collected type rotor pillar 14 that verts, folding rotor and blade tip flash light; The blade tip flash light is by the transparent fairing 18 that is installed on blade tip, the aerial discharge flashtube 21 within the fairing 18, stroboscopic driving circuit, and devices such as the current colector 23 of rotorshaft 10 positions, brush 24, flash of light master cock are formed.
Advantage of the present invention is:
The present invention; Be suitable for flight, the short take-off and landing (STOL) performance is good, rotor, empennage are easy to fold, control comfort, that cost is low, safety performance is good, load-carrying ability is strong, ground takes up room is little, possess " the rotor flight car " of the motor-driven and landing ability of good highway.For most aerial mission,, generally can both find the highway and other place that are suitable for the cyclogyro short take-off and landing (STOL), and can drive thus to travel to the destination near within departure place and destination several kilometers.This machine can run out from family's hangar of user, comes the spacious highway of enough earning empty condition, and rise rotor pillar, expansion rotor can be spread its wings to fly as bird with empennage; Its flight is found after the landing of suitable highway near the destination, regains rotor pillar, rotor and vertical tail, just as the bird wing that closed; Drive driving engine again and sail the destination into, enter into Bird's Nest, become point-to-point through movement instrument as the bird walking from highway.This machine provides except that helicopter for people, can realize new a selection of point-to-point rapid transit.This machine is realized the dream of people to air communication easily with simple manipulation technology, very low transportation cost, higher safety factor, has broken away from it huge airport is relied on, and really can fly at any time as bird.
The present invention promptly has the advantage of conventional cyclogyro, also has the highway landing, freely characteristics of travelling, and it has adopted following technology:
1, the collected type rotor pillar 14 that verts.2, oar dish pitching coordinated control.3, folding rotor.4, the light-duty driving of prewhirling.5, folding fin.6, road running system.7, blade tip flash light.
Below in conjunction with drawings and Examples the present invention is described in detail:
Description of drawings
The component names of accompanying drawing and reference numeral:
Fig. 1 solid line part, the state of expression rotor pillar 14 collections; Its rotor pillar 14 has tilted forward, has been horizontally-arranged at machine top top, rotor with lead lag hinge 6 be that rotating shaft is folded back; The dotted line of Fig. 1 represents that rotor pillar 14 rise, rotor and empennage launch, and prepares flight;
Shown in Figure 2, collected type rotor pillar 14 lateral plans that vert before putting on being, rotor pillar 14 upwards rises, rotor launches;
Fig. 3 is the partial enlarged drawing of corresponding diagram 2, and pillar location lock 40 is with rotor pillar 14 fixing and lockings;
The rotor of Fig. 4 two blades goes to laterally, rotor pillar 14 tilts forward, the lateral plan that vertical tail is folding forward;
Fig. 5 is the partial enlarged drawing of corresponding diagram 4, and pillar location lock 40 is opened release with rotor pillar 14:
Fig. 6 is and the cooresponding front schematic view of Fig. 4;
Fig. 7, shown in Figure 8, rotor pillar 14 tilt forward to horizontally-arranged, and blade 7 is backfolding lateral plan of back flap hinge and front elevation with near the flapping hinge 8 the propeller hub 11.
Fig. 9 launches its rotor, and rotor pillar 14 upwards turnover rises, launches vertical tail 5, and rotor flight car is in the side schematic view of preparation state of flight;
Figure 10 is corresponding with Fig. 9, and rotor pillar 14 is by the partial enlarged drawing of pillar location lock 40 fixing and lockings;
Figure 11 rotor goes to laterally, the rotor pillar 14 horizontally-arranged side schematic view that verts backward;
Figure 12 is corresponding with Figure 11, pillar location lock 40 partial enlarged drawings of opening;
Figure 13 rotor pillar 14 verts backward, and blade 7 is the folding forward side schematic view of back flap hinge with flapping hinge 8.
Figure 14,15, the 16th, on put, after the collected type rotor pillar 14 that verts, when using high vertical tail 5, its upper end and horizontally-arranged backward rotor pillar 14 tops are laterally being left at interval;
Figure 14 launches rotor, and rotor pillar 14 upwards rises, and this machine is in the side schematic view of preparation state of flight;
Figure 15 rotor goes to laterally, the rotor pillar 14 horizontally-arranged side schematic view that verts backward; Because of the upper end of its vertical tail 5 and the staggered installation in top of horizontally-arranged rotor pillar 14 backward, both do not collide laterally leaving spacing:
Figure 16 blade 7 is a back flap hinge with flapping hinge 8, the side schematic view that blade 7 is folding forward.
Figure 17, Figure 18 put on being, the preceding collected type rotor pillar 14 that verts, its rotor with lead lag hinge 6 be that back flap hinge folds; The top interlock 63 of its oar dish pitching interlock and bottom interlock 64 are positioned at the back of the rotor pillar 14 of setting;
Figure 19, shown in Figure 20, put on it has used, after the collected type rotor pillar 14 that verts, its rotor with lead lag hinge 6 be that back flap hinge folds; The top interlock 63 of this oar dish pitching interlock and bottom interlock 64 are positioned at the front of the rotor pillar 14 of setting; The top of horizontally-arranged rotor pillar 14 and height are put vertical tail 5 upper ends and are staggered, and both do not collide laterally leaving spacing.
Figure 21 to Figure 27 is a kind of underlying, expose, the scheme drawing of the preceding collected type rotor pillar 14 that verts;
Shown in the lateral plan of Figure 21, launch its rotor, rotor pillar 14 upwards rises, and utilizes pillar location lock 40 with the rotor pillar 14 that erects and fuselage pin together;
Figure 22, Figure 23 rotor go to laterally, and pillar location lock 40 is with together side of rotor pillar 14 and fuselage pin, two views just;
Figure 24, Figure 25 open pillar location lock 40, and rotor pillar 14 tilts forward side to horizontally-arranged state, two views just;
Figure 26, Figure 27 blade 7 are the backfolding side of back flap hinge, two views just with flapping hinge 8.
Figure 28 to Figure 31 is a kind of underlying, expose, after the vert side schematic view of collected type rotor pillar 14;
Shown in Figure 28, launch rotor, rotor pillar 14 upwards rises, and pillar location lock 40 is with the rotor pillar 14 that erects and fuselage pin together;
Figure 29 rotor goes to laterally:
Figure 30 opens pillar location lock 40, and rotor pillar 14 retreats and goes to horizontally-arranged state;
Figure 31 blade 7 is that back flap hinge is folding forward with flapping hinge 8.
Figure 32 is to shown in Figure 42, it be the scheme drawing of a kind of underlying, built-in, the preceding collected type rotor pillar 14 that verts: Figure 34,36, etc. birds-eye view, rotor wherein is omitted and does not draw;
Shown in Figure 32,33,34, rotor pillar 14 upwards rises, rotor pillar 14 by pillar location lock 40 be fixed on side on the fuselage top cover 41, just, the three-view diagram of bowing;
Shown in Figure 35,36, rotor goes to laterally, opens side, two views of bowing of canopy 2 and pillar location lock 40;
Shown in Figure 37,38, rotor pillar 14, from about pass through between two passenger seat 3a, the 3b, tilt forward horizontally-arrangedly, rotor stretches out from head the place ahead, covers pillar port lid 4 ', closes side, two views of bowing of pillar location lock 40;
Shown in Figure 39,40, its rotor blade 7 is a back flap hinge with flapping hinge 8, the side of rotating to the fuselage rear, two views just:
Shown in Figure 41,42, cover the side of canopy 2, two views just;
Shown in Figure 43 to Figure 57, it is the scheme drawing of another kind of underlying, built-in, the preceding collected type rotor pillar 14 that verts; Figure 45, birds-eye vieies such as 49, rotor wherein is not omitted and draws;
Shown in Figure 43,44,45, rotor pillar 14 has erected, it by pillar location lock 40 be fixed on the side on fuselage top cover 41 tops, just, the three-view diagram of bowing;
Shown in Figure 46,47,48,49, its rotor goes to laterally, open the side of canopy 2, cover plate 1 and pillar location lock 40, just, birds-eye view;
Shown in Figure 50,51,52, its rotor pillar 14, from about pass through between two passenger seat 3a, the 3b, tilt forward horizontally-arrangedly, stretch out from head the place ahead, close the side of pillar location lock 40, just, the three-view diagram of bowing;
Shown in Figure 53, Figure 54, Figure 55, its rotor blade 7 is that back flap hinge changes to the fuselage rear with flapping hinge 8, closes side, the front elevation of cover plate 1;
Shown in Figure 56, Figure 57, cover the side of canopy 2, positive two views;
Figure 58 to Figure 63, be a kind of with lead lag hinge 6 scheme drawings (pillar among figure location lock 40 is not omitted and draws) for the underlying of its back flap hinge, built-in, the preceding collected type rotor pillar 14 that verts;
Figure 58 is the lateral plan that rotor pillar 14 has risen and has been fixed together by pillar location lock 40 and fuselage; The top interlock 63 of its oar dish pitching interlock and bottom interlock 64 are positioned at the back of the rotor pillar 14 of setting;
Shown in Figure 59, rotor goes to laterally, opens the lateral plan of canopy 2;
Shown in Figure 60, Figure 61, its rotor pillar 14 tilts forward horizontally-arranged side, two views just;
Shown in Figure 62, Figure 63, its rotor blade 7 with lead lag hinge 6 be back flap hinge, turn round to position near fuselage, close cover plate 1, pillar location lock 40, cover the side of canopy 2, two views just;
Figure 64 to Figure 71, it be another kind of with lead lag hinge 6 scheme drawings (the pillar location lock 40 among the figure is not omitted picture) for the underlying of its back flap hinge, built-in, the preceding collected type rotor pillar 14 that verts;
Shown in Figure 64, its vertical tail 5 is rotated via the direction of arrow shown in a and the b by the position of dotted line, and is folding towards the position of solid line; Its rotor pillar 14 and blade 7 via the direction of arrow shown in the c, tilt forward horizontally-arranged folding by the position of dotted line; The canopy 2 ' of lateral opening shown in the dotted line via the direction of arrow shown in the d, closes to the position of the canopy 2 shown in the solid line;
Shown in Figure 65,66, rotor goes to laterally, opens the side of the high laterally opened gate of canopy 2, pillar location lock 40 and half, two views just;
Shown in Figure 67, rotor pillar 14 tilts forward horizontally-arranged lateral plan;
Shown in Figure 68, control oar dish plane rotates; Vertical tail 5 serves as that axle rotates 90 degree with vertical shaft back flap hinge 71;
Shown in Figure 69, its rotor blade 7 with lead lag hinge 6 be back flap hinge, turn round to fuselage mutually by the lateral plan of position; Vertical tail 5 serves as that axially preceding rotation is horizontally-arranged with transverse axis back flap hinge 70a;
Shown in Figure 70, Figure 71, close cover plate 1, pillar location lock 40, cover the side of canopy 2, two views just;
Shown in Figure 72, rotor pillar 14 is put on being, the preceding collected type that verts; Its rotor pillar 14 tilt forward horizontally-arranged after, be that with Figure 68 identical point Figure 72 can control oar dish plane and rotate:
Figure 73, Figure 74 put on being, the preceding collected type rotor pillar 14 that verts, its folding rotor belong to lead lag hinge 6 be the mode that back flap hinge folds; The top interlock 63 of its oar dish pitching interlock and bottom interlock 64 are that its rigid gangbar 65 can be used soft drag-line instead here by Figure 17,18 and Figure 19,20 development that combines;
Shown in Figure 75 to Figure 80, it disposes mid-passenger seat 3c, and figure is the collection scheme drawing that verts of underlying, built-in, the preceding collected type rotor pillar 14 that verts; Rotor among the figure such as Figure 75, Figure 77 is not omitted and draws;
Figure 75 and Figure 76 have opened overlooking and front elevation of canopy 2;
Shown in Figure 77 and Figure 78, mid-passenger seat 3c is to folding the overlooking and front elevation of holding up of a side of fuselage;
Shown in Figure 79, rotor pillar 14 has tilted forward horizontally-arranged birds-eye view;
Shown in Figure 80, mid-passenger seat 3c is by the flat reduction of crouching, the birds-eye view that rotor pillar 14 passes below mid-passenger seat 3c;
Shown in Figure 81 to Figure 85, Figure 86 to Figure 90, Figure 91 to Figure 95, be respectively three kinds of aircraft that use drawing-in type driving engine screw propeller, the pillar location lock 40 among the figure is not omitted to be drawn;
Shown in Figure 81 to Figure 85, it be underlying, built-in, after the vert lateral plan of collected type rotor pillar 14;
Shown in Figure 81, its rotor pillar 14 is fixed on the fuselage top cover 41 by pillar location lock 40:
Figure 82, its rotor goes to laterally, opens canopy 2 and pillar location lock 40;
Shown in Figure 83, rotor pillar 14 verts horizontally-arranged backward:
Shown in Figure 84, rotor blade 7 is a back flap hinge with flapping hinge 8, goes to the position of leaning on mutually with fuselage forward;
Shown in Figure 85, close canopy 2.
Shown in Figure 86 to Figure 90, be underlying, built-in, preceding collected type rotor pillar 14 and the folding fin lateral plan of verting; Vertical tail 5 orders are the turning cylinder collection with longitudinal axis back flap hinge 70b and vertical shaft back flap hinge 71; The enlarged diagram of two turning cylinders is seen shown in Figure 124:
Shown in Figure 86, rotor pillar 14 is fixed on the fuselage top cover 41 by pillar location lock 40;
Figure 87, rotor blade 7 go to laterally, open canopy 2 and pillar location lock 40; Vertical tail 5 is a turning cylinder with longitudinal axis back flap hinge 70b, rotates 90 degree;
Shown in Figure 88, rotor pillar 14 tilts forward horizontally-arranged; Vertical tail 5 is a turning cylinder with vertical shaft back flap hinge 71, rotates 90 degree forward;
Shown in Figure 89, control oar dish plane rotates, and makes it parallel to the ground; Its rotor blade 7 with lead lag hinge 6 be back flap hinge, turn round to the position of leaning on mutually with fuselage;
Shown in Figure 90, be the scheme drawing of closing canopy 2;
Figure 91 to Figure 95 is the lateral plan of underlying, built-in, preceding vert collected type rotor pillar 14 and folding fin 5; Vertical tail 5 is a turning cylinder with vertical shaft back flap hinge 71 earlier, rotates 90 degree; Be turning cylinder with transverse axis back flap hinge 70a again, rotate horizontally-arranged forward; The enlarged diagram of two turning cylinders is seen shown in Figure 117 to 112;
Shown in Figure 91, rotor pillar 14 is fixed on the fuselage top cover 41 by pillar location lock 40;
Figure 92, rotor go to laterally, open canopy 2 and pillar location lock 40;
Shown in Figure 93, rotor pillar 14 tilts forward horizontally-arranged; Vertical tail is an axle with vertical shaft back flap hinge 71, rotates 90 degree;
Its rotor blade 7 of Figure 94 is a back flap hinge with flapping hinge 8, turns round to the position of leaning on mutually with fuselage; Vertical tail is an axle with transverse axis back flap hinge 70a, relies on tail boom 74 forward and horizontally-arranged;
Shown in Figure 95, close canopy 2.
Front elevation shown in Figure 96 to Figure 99, the folding of its laterally opened canopy 2 place the middle part deflection inboard (graphic left side) on machine top; This canopy 2 than the face area of scheme canopies 2 such as Figure 32 to Figure 95 little nearly half, belong to semi-open type canopy 2, so this canopy 2 comparatively light (the pillar location lock 40 among Figure 96 to Figure 104 is not omitted and draws);
Shown in Figure 96, its rotor goes to laterally;
Shown in Figure 97, canopy 2 serves as axially to go up upset to open to place the inboard folding of machine top deflection, opens cover plate 1 and pillar location lock 40 simultaneously;
Shown in Figure 98, rotor pillar 14 from about pass through between two passenger seat 3a, the 3b, tilt forward horizontally-arrangedly, stretch out from head the place ahead;
Shown in Figure 99, rotor blade 7 is that back flap hinge is folding to the fuselage rear with flapping hinge 8, closes cover plate 1 and canopy 2 again.
Shown in Figure 100 to Figure 104, the canopy 2 of this figure has lacked side panel (that is: the board-like canopy in no side) than Figure 96 to Figure 99 scheme, and the part of this side panel changes gate into, have the advantage of semi-open type canopy 2 and the board-like canopy 2 in no side concurrently, so this canopy 2 is more light;
Shown in Figure 100, Figure 101, the side of little canopy 2 schemes, two views just;
Shown in Figure 102, Figure 103, open the side of canopy 2, two views just to a side; By Figure 102 as seen, this programme has reduced side panel than the canopy 2 of schemes such as Figure 32 to Figure 42, and the part of this side panel changes gate into;
Shown in Figure 104, its rotor pillar 14 tilts forward horizontally-arranged, the lateral plan that stretches out from head the place ahead.
Shown in Figure 105,106,107, be a kind of folding rotor, it carries out folding storage and discharges the scheme drawing that launches to be back flap hinge near near the flapping hinge 8 the propeller hub 11;
Figure 105 is the scheme drawing (the stop collar return spring 30 among the figure does not omit and draws) that rotor launches;
Its folding rotor of Figure 106 is a back flap hinge with flapping hinge 8, inwardly promotes slip stop collar 9, the scheme drawing of compression stop collar return spring 30;
Figure 107 is the scheme drawing of folding rotor: inwardly promote slip stop collar 9, compression stop collar return spring 30, blade 7 get final product folding storage (the stop collar return spring 30 among the figure does not omit and draws).
Shown in Figure 108, be another kind of folding rotor, it with near near the oar firm 11 lead lag hinge 6 be the scheme drawing of back flap hinge;
Blade tip flash light shown in Figure 109 top and Figure 110 comprises parts such as transparent fairing 18, aerial discharge flashtube 21, current colector 23 and brush 24; Its optics corner reflector is installed in the blade tip place of rotor side by side;
Shown in the middle and lower part of Figure 109, the light-duty keystone configuration scheme drawing of prewhirling and driving that is to use drag-line to drive starts the rotation of rotor by the reciprocal pulling trailing cable 17 and the rope 38 that resets;
Figure 111 is to use the light-duty keystone configuration scheme drawing of prewhirling and driving of sheave retracing spring 19, and it back and forth spurs the rotation that trailing cable 17 starts rotor by control end, and the reset function of its sheave 16 is to be finished by sheave retracing spring 19.
Figure 112 to Figure 114 is the vertical tail scheme drawing of foldable structure, and Figure 112 is a lateral plan, and Figure 113,114 is a birds-eye view;
Shown in Figure 112, its rear portion rudder face 32 is divided into up and down two parts, and both link to each other by longitudinal axis back flap hinge 70b, utilizes rudder face location lock 35 that both are fixed in shown position;
Shown in Figure 113, the set pin of rudder face being located lock 35 upwards draws, and makes the top of rear portion rudder face 32 be in the state of unlocking;
What Figure 114 illustrated is the first half of rear portion rudder face 32, serves as axially folding down with longitudinal axis back flap hinge 70b, and vertical tail is in the position of folded state, and this moment, the influence of the side direction aerodynamic force that this machine is subjected on ground was less.
Figure 115 and 116 is full dynamic formula vertical tails 5, the vertical tail 5 of Figure 115 for launching; Figure 116 is folding vertical tail 5.
Figure 117 to 122 is a kind of horizontal folding vertical tail 5 lateral plans; The end of its tail boom is rotatedly connected with vertical tail 5 by transverse axis back flap hinge 70a, vertical shaft back flap hinge 71;
Figure 117 is the horizontal folding vertical tail 5 of deployed condition;
Figure 118 is the partial exploded view of back flap hinge, and what the arrow among the figure was represented is the graph of a relation that is mutually permanently connected; Shown in the figure, connection mode between its vertical tail 5 and two back flap hinges and the tail boom 74 is: the front of its vertical tail 5 (being described with shown position), the first half that cuts with scissors page or leaf with the front of vertical shaft back flap hinge 71 is fixedly linked, the left side hinge page or leaf of vertical shaft back flap hinge 71 links to each other with the hinge page fixing on transverse axis back flap hinge 70a right side, and the hinge page or leaf in transverse axis back flap hinge 70a left side and the upside of tail boom 74 ends are fixedly linked.
Figure 119 is that the dowel bolt 72 of folding vertical tail 5 is removed, and empennage 5 will serve as that axle rotates 90 degree with vertical shaft back flap hinge 71;
Figure 120, empennage 5 have served as the lateral plan that axle rotates 90 degree with vertical shaft back flap hinge 71, and empennage 5 will serve as axially preceding horizontally-arranged rotation with transverse axis back flap hinge 70a;
Its empennage 5 of Figure 121 has served as that axially preceding rotation is horizontally-arranged with transverse axis back flap hinge 70a, and dowel bolt 72 is upwards installed;
The dowel bolt 72 of its empennage 5 of Figure 122 has fixedly mounted, and vertical tail 5 is fixed in the end of tail boom 74.
Figure 123 is another kind of horizontal folding vertical tail 5, and arrow is represented the precedence diagram that is mutually permanently connected; The difference of this figure and Figure 117 to 122 is that the vertical tail 5 of this figure is a lateral rotation 90 degree with longitudinal axis back flap hinge 70b earlier, serves as that axle rotates 90 degree with the vertical shaft back flap hinge again.After vertical tail 5 folded, it was horizontally-arranged at the top of tail boom 74 forward.
Figure 124 is another kind of horizontal folding vertical tail 5, and arrow is represented the precedence diagram that it is mutually permanently connected; The vertical tail 5 of Figure 124 is a turning cylinder with longitudinal axis back flap hinge 70b earlier, rotates 90 degree; Be turning cylinder with vertical shaft back flap hinge 71 again, rotate 90 degree forward; After vertical tail 5 folds, be the below that is in tail boom 74.
Shown in Figure 124, its tail boom 74 with connection mode between two back flap hinges and the vertical tail 5 is: its tail boom 74 link to each other with the hinge page fixing in vertical shaft back flap hinge 71 left sides (seeing shown position), the hinge page or leaf on vertical shaft back flap hinge 71 right sides is fixedly linked with the front of crossing the bridging beam piece, the bottom surface of crossing the bridging beam piece links to each other with the below hinge page fixing of longitudinal axis back flap hinge 70b, and the first half hinge page or leaf that longitudinal axis back flap hinge 70b erects is fixedly linked with the back side of vertical tail 5.It is crossed the bridging beam piece and can also use one section angle bar to replace.
Shown in Figure 125, special-purpose small displacement engine 15 is installed on the bottom of forward engine room, wheel before driving by messenger chain, the direction control that preceding wheel is double when doing ground run;
Shown in Figure 126, before special-purpose small displacement engine 15 is installed on wheel near, wheel before the driving engine direct drive, the direction control that preceding wheel is double when doing ground run.
Embodiment
Embodiment one
Fig. 1 to Fig. 8, Figure 17,18 and Figure 72 to Figure 74 shown in, a kind of rotor flight car comprises that power system, the level of fuselage, cyclogyro advance and drives screw propeller, empennage, alighting gear, the parts such as collected type rotor pillar 14 and folding rotor of verting; Rotor pillar 14 upwards erect fixing after, the position of its installation, leaning angle backward are identical with conventional cyclogyro, the rotor of expansion is an autorotating rotor; The used rotor pillar 14 of present embodiment is put on being, the preceding collected type that verts.
The vert lower end of rotor pillar 14 of collected type is rotationally connected by pillar rotating shaft 13 and fuselage top, and it can rotate to the y direction of fuselage, turns forward then horizontally-arranged collection; When its rotor pillar 14 upwards erected, the pillar location lock 40 that is fixedly installed on the fuselage can be with rotor pillar 14 and fuselage pin together, opens pillar location lock 40 and rotor pillar 14 can be rotated and rely on fuselage, and collection is to horizontally-arranged position.
Shown in Figure 3, be pillar location lock 40 enlarged drawings with rotor pillar 14 fixing and lockings, it is corresponding with the state of the rotor pillar 14 of Fig. 2.Shown in Figure 5, be that pillar location lock 40 is opened the enlarged drawing of release with rotor pillar 14, it is corresponding with the state of the rotor pillar 14 of Fig. 4.
Embodiment two
Shown in Figure 125, present embodiment is that with the difference of " embodiment one " this routine canopy 2 can be to front opening, and the aviator can lean out body thus, the rotor that tilts forward horizontally-arranged rotor pillar 14 upper ends is folded back, and other parts are identical with " embodiment one ".
Embodiment three
Present embodiment is that with the difference of " embodiment two " this routine canopy 2 can be to side opening, and the aviator can lean out body thus, and the rotor that tilts forward horizontally-arranged rotor pillar 14 upper ends is folded back, and other parts are identical with " embodiment two ".
Embodiment four
Fig. 9 is to shown in Figure 13, and present embodiment is with the difference of " embodiment one ", the rotor pillar 14 of the present embodiment collected type that verts after being.For preventing that horizontally-arranged backward rotor pillar 14 and vertical fin top from colliding, this example has been used lower vertical tail, and other parts are identical with " embodiment one ".
Embodiment five
Shown in Figure 14 to Figure 16 and Figure 19,20, present embodiment is that with the difference of " embodiment four " " embodiment four " are low vertical fin, and this example has been used high vertical fin; In this example, collide for preventing horizontally-arranged rotor pillar 14 tops and high vertical fin top, both leave at interval at lateral alternate.Other parts are identical with " embodiment four ".
Embodiment six
Figure 21 is to shown in Figure 27, above-mentioned rotor pillar 14 for underlying, expose, the preceding collected type that verts, its rotor pillar 14 is exposed to outside the fuselage, its pillar rotating shaft 13 is installed on the bottom of fuselage, rotor pillar 14 collected type that verts before being, other parts are identical with " embodiment one ".
Embodiment seven
Figure 28 is to shown in Figure 31, and present embodiment is with the difference of " embodiment six ", this routine rotor pillar 14 collected type that verts after being, and other parts are identical with " embodiment six ".
Embodiment eight
Shown in each figure among Figure 32 to Figure 42, above-mentioned rotor pillar 14 is underlying, built-in, the preceding collected type that verts, and pillar rotating shaft 13 is installed on fuselage interior, and its canopy 2 is laterally opened.
The lower part of the rotor pillar 14 that erects is hidden within the fuselage; Rotor pillar 14 upwards rotates when erecting, its canopy 2 and pillar location lock 40 by opening, rotor pillar 14 is entered within the pillar hole 4 and erect, pillar location lock 40 is fixed together rotor pillar 14 and fuselage top cover 41 together with fuselage, cover canopy 2 again can fly; Rotor pillar 14 tilts forward horizontally-arranged and when collection, open canopy 2 and pillar location lock 40, rotor pillar 14 from about pass through between two passenger seat 3a, the 3b, tilt forward horizontally-arranged collection, rotor stretches out from head the place ahead, blade 7 is folding to the fuselage rear, covers canopy 2 again and can sail back hangar from highway.These routine other parts are identical with " embodiment one ".
Embodiment nine
Shown in each figure among Figure 64 to Figure 71, present embodiment and " embodiment eights' " difference is, present embodiment has been set up half high laterally opened gate, is convenient to occupant's discrepancy.Its part is identical with " embodiment eight ".
Embodiment ten
Shown in each figure among Figure 32 to Figure 42, present embodiment is that with the difference of " embodiment eight " present embodiment has been equipped with pillar port lid 4 ' in pillar hole 4 positions, and when rotor pillar 14 was in horizontally-arranged state, pillar port lid 4 ' covered pillar hole 4 completely.Its part is identical with " embodiment eight ".
Shown in each figure among Figure 43 to Figure 57, present embodiment is that with the difference of " embodiment eight " the preceding head of present embodiment is provided with cover plate 1, can reduce the area of canopy 2 front portions like this, and other parts are identical with " embodiment eight ".
Embodiment 12
Shown in each figure among Figure 64 to Figure 71, present embodiment is with the difference of " embodiment eight ", present embodiment, can carry out wide-angle control to the stagger angle of rotor oar dish, can between the position shown in the position shown in Figure 67 and Figure 68, carry out conversion, make that rotor can be shown in Figure 71, to the internal organs portion collection of fuselage.Other parts are identical with " embodiment eight ".
Shown in Figure 72, the difference of present embodiment and " embodiment 12 " is, present embodiment has been to use the collected type rotor pillar 14 that verts before putting, and present embodiment carries out wide-angle control in the counterclockwise direction to the stagger angle of rotor oar dish.
Shown in each figure among Figure 96 to Figure 99, it is with the difference of " embodiment eight ", present embodiment, the folding of its laterally opened canopy 2 places the middle part on machine top near graphic inboard, belong to semi-open type canopy 2, the face area and the weight of the canopy 2 that can reduce to open like this, other parts are identical with " embodiment eight ".
This embodiment and " embodiment eights' " difference is, the canopy 2 of present embodiment lacks than " embodiment nine " and to have used the part side panel, belongs to the board-like canopy 2 in no side, and this part side panel of minimizing is extended upward the gate that becomes overall height and replaces.So this canopy 2 is comparatively light; Other parts are identical with " embodiment eight ".
Shown in each figure among Figure 100 to Figure 104, present embodiment combines the advantage of " embodiment 14 and 15 ", has the advantage of semi-open type canopy 2 and the board-like canopy 2 in no side concurrently, so this canopy 2 is more light; Other parts are identical with " embodiment eight ".
Shown in each figure among Figure 75 to Figure 80, it is that with the difference of " embodiment eight " present embodiment has been installed mid-passenger seat 3c.This machine is when ground run, and it is horizontally-arranged to hinder rotor pillar 14 to vert downwards for fear of mid-passenger seat 3c, and this mid-passenger seat 3c adopts the way of side-foldable, and rotor pillar 14 is passed below mid-passenger seat 3c.The other parts of present embodiment are identical with " embodiment eight ".
Figure 17, shown in Figure 180, present embodiment have oar dish pitching coordinated control, and other parts are identical with " embodiment one ".
Its oar dish pitching coordinated control: comprise parts such as rotorshaft 10, pillar rotating shaft 13, rotor pillar 14, top interlock 63, bottom interlock 64, gangbar 65, top universal driving shaft 67, pitch control bar, inner interlock.
Link and 63 captive joint in the bearing of its rotorshaft 10 and top; Being positioned at the top universal driving shaft 67 of top interlock 63 and the upper end of rotor pillar 14 is rotationally connected; Be positioned at the shaft hole and pillar rotating shaft 13 concentric being rotatedly connected of bottom interlock 64; Top interlock 63 is rotatedly connected with bottom interlock 64 by gangbar 65, rotor pillar 14 respectively, and 4 interconnective four points constitute the parallelogram on the same plane; Its underpart interlock 64 links to each other with the pitch control bar by inner interlock; Its rotor pillar 14 is in the folding process of verting, and the pitch control bar keeps the control ability to oar dish stagger angle; Its top interlock 63 and bottom interlock 64 are positioned at the back of the rotor pillar 14 of setting.
Embodiment 19
Present embodiment also has oar dish pitching coordinated control, and present embodiment is with the difference of " embodiment 18 ", is positioned at the shaft hole of bottom interlock 64, is installed on the root of rotor pillar 14.These routine other parts are identical with " embodiment 18 ".
Embodiment 20
Figure 19 is to shown in Figure 20, the difference of " oar dish pitching coordinated control " in " the oar dish pitching coordinated control " of present embodiment and " embodiment 18 " is that top interlock 63 in its oar dish pitching coordinated control and bottom interlock 64 are positioned at the front of the rotor pillar 14 of setting.
The other parts of this embodiment are identical with " embodiment four ".
Shown in each figure among Figure 58 to Figure 63, above-mentioned rotor pillar 14 also has oar dish pitching coordinated control, and this example is that with the difference of " embodiment 18 " what present embodiment used is underlying, built-in, the preceding collected type that verts.Other is identical with " embodiment 18 ".
Embodiment 22
Shown in Figure 73,74, above-mentioned rotor pillar 14 also has oar dish pitching coordinated control, this example is with the difference of " embodiment 18,21 ", its top interlock 63 and bottom interlock 64 are combinations of relevant portion in " embodiment 18,21 " two examples, its rigid gangbar 65 can be used soft drag-line in this example.
Present embodiment can be used this oar dish pitching coordinated control in " embodiment 18,21 ", and forms a new embodiment.
Present embodiment is that with the difference of " embodiment one " screw propeller of " embodiment one " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment one ".
Present embodiment is that with the difference of " embodiment four " screw propeller of " embodiment four " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment four ".
Embodiment 25
Present embodiment is that with the difference of " embodiment six " screw propeller of " embodiment seven " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment six ".
Embodiment 26
Present embodiment is that with the difference of " embodiment eight " screw propeller of " embodiment seven " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment seven ".
Shown in Figure 91 to Figure 95, present embodiment is that with the difference of " embodiment eight " screw propeller of " embodiment eight " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment eight ".
Shown in Figure 81 to Figure 85, present embodiment is with the difference of " embodiment 27 ", the rotor pillar 14 of " embodiment 27 " is underlying, built-in, the preceding collected type that verts, and the rotor pillar 14 of the present embodiment collected type that verts after being, other parts are identical with " embodiment 27 ".
Shown in Figure 86 to Figure 90, present embodiment is that with the difference of " embodiment 12 " screw propeller of " embodiment 11 " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment 12 ".
Shown in Figure 91 to Figure 95, present embodiment is that with the difference of " embodiment 11 " screw propeller of " embodiment 11 " is a driving, and the screw propeller of present embodiment is a drawing-in type, and other parts are identical with " embodiment 11 ".
Shown in Fig. 2 to Figure 16, Figure 21 to Figure 57, Figure 75 to Figure 85, Figure 91 to Figure 95, Figure 105 to Figure 107, Figure 126, above-mentioned folding rotor, it comprises blade 7, rotorshaft 10, spacing back flap hinge; Its spacing back flap hinge constitutes by being enclosed within the slip stop collar 9, the stop collar return spring 30 that rotate on the hinge; It rotates hinge and is made of flapping hinge 8; Other parts are identical with " embodiment one ".
In flapping hinge 8 positions, from the inside to the outside, be inserted in stop collar return spring 30 and slip stop collar 9 respectively; Launch blade 7, the inner limited cover return spring 30 of slip stop collar 9 outwards ejects, and blade 7 can carry out low-angle free flapping action, turns back but slip stop collar 9 can stop blade 7 to carry out wide-angle along the rotation hinge; Move inward slip stop collar 9, compression stop collar return spring 30, slip stop collar 9 no longer limits the turnover of blade 7, and blade 7 can inwardly be turned back, and blade 7 is collected the direction of horizontally-arranged rotor pillar 14 extremely.
Figure 105 to Figure 107 be a kind of serve as the scheme drawing that rotates the folding rotor of hinge with flapping hinge 8, the stop collar return spring 30 among Figure 105, Figure 107 omits to be drawn; Slip stop collar 9 limited cover return springs 30 among Figure 105 eject, and blade 7 can not be sagging; Figure 106 inwardly promotes the stop collar 9 that slides, compression stop collar return spring 30, and Figure 107 blade 7 is unrestricted and can wide-angle turn back.
Shown in Fig. 1, Figure 17 to Figure 20, Figure 58 to Figure 72, Figure 86 to Figure 90, Figure 108, Figure 125, above-mentioned folding rotor is with the difference of " embodiment 31 ", its rotate hinge by lead lag hinge 6 constitute, this is folding, and to execute the other parts of the wing identical with " embodiment 31 ".Present embodiment used lead lag hinge 6 as the rotation hinge of folding rotor and constitute new embodiment.
Embodiment 33
Shown in Figure 109, a kind of rotor flight car, it has used the light-duty driving of prewhirling, and is that a kind of machine inhaul drives facility, and rotorshaft 10 links to each other with sheave 16 by the ratchet 27 of unidirectional rotation; Its sheave can be subjected to an end fixed thereon and with different directions twine thereon trailing cable 17 and the effect of the rope 38 that resets; The other end of pulling trailing cable 17 drives the rotor rotation of prewhirling through pulley 20, sheave 16, check tooth 28, ratchet 27, rotorshaft 10; Tooth retracing spring 29 is used to eject check tooth 28, to guarantee the unidirectional rotation of ratchet 27: spur the rope 38 that resets and can make trailing cable 17 recover original position.The light-duty driving of prewhirling of this embodiment has in light weight, advantage of simple structure.
Present embodiment also can be used this light-duty driving of prewhirling on above-mentioned " any one embodiment " basis, thereby forms a new embodiment.
Embodiment 34
Shown in Figure 111, a kind of light-duty driving of prewhirling of rotor flight car, it is with the difference of " embodiment 33 ", present embodiment has used sheave retracing spring 19, when loosening trailing cable 17, spur the rope 38 that resets by sheave retracing spring 19, make trailing cable 17 recover original position.Others are identical with " embodiment 33 ".
Shown in Figure 112 to 114, a kind of rotor flight car, its vertical tail is a foldable structure, it is made up of the anterior rudder face 31 that is installed on tail boom 74 ends, rear portion rudder face 32, rudder face location lock 35, back flap hinge, turning cylinder 37; That its back flap hinge uses is longitudinal axis back flap hinge 70b; Rear portion rudder face 32 is divided into two parts up and down, and its first half is folding rudder face, and both link to each other by longitudinal axis back flap hinge 70b.Shown in Figure 112, can utilize rudder face location lock 35 the fixing and lockings of two parts up and down here with rear portion rudder face 32; Also can shown in Figure 114, open rudder face location lock, both are unlocked, folding downwards.Rear portion rudder face 32 is an axle with turning cylinder 37, and left-right rotation can controlling aircraft turn to.
Present embodiment can be used this vertical tail 5 on the basis of above-mentioned " any one embodiment ", thereby forms a new embodiment.
Shown in Figure 115,116, present embodiment is folding complete moving vertical tail.Its rear portion rudder face 32 is double does folding rudder face, and turning cylinder 37 is as back flap hinge.When vertical tail launched, its anterior rudder face 31 and rear portion rudder face 32 were fixedly linked by rudder face location lock 35, and this front portion rudder face 31 replaces turning cylinder 37 with complete moving turning cylinder 37 ', the heading of control rotor flight car.
Shown in Figure 64 to Figure 71, Figure 91 to Figure 95, Figure 117 to 122, a kind of rotation " rotor flight car ", its vertical tail 5 is a foldable structure; The vertical tail 5 of foldable structure is terminal hinged by vertical shaft back flap hinge 71, plane rotating hinge and tail boom 74; This plane rotating hinge is made of transverse axis back flap hinge 70a; When folding vertical tail 5, utilize vertical shaft back flap hinge 71 earlier, vertical tail 5 is gone to laterally, utilize transverse axis back flap hinge 70a again, it is horizontally-arranged forward, at last by dowel bolt 72 and setscrew nut 73, be fixed in the end of tail boom 74; Operation when launching vertical tail 5 in contrast.This example can with " embodiment one to 34 " in any example combine and be new embodiment.
Shown in Figure 123, this embodiment is that with the difference of " embodiment 37 " the plane rotating hinge of its vertical tail 5 is made of longitudinal axis back flap hinge 70b; The vertical tail 5 of foldable structure is terminal hinged by vertical shaft back flap hinge 71, longitudinal axis back flap hinge 70b and tail boom 74.When folding vertical tail 5, utilize longitudinal axis back flap hinge 70b earlier, vertical tail 5 was laterally fallen, utilize vertical shaft back flap hinge 71 again, vertical tail 5 is rotated to heading; When launching vertical tail 5, operation in contrast.Other is identical with " embodiment 37 ".
Embodiment 39
Shown in Figure 86 to Figure 90, Figure 124, the difference of this embodiment and " embodiment 38 " is, the vertical tail 5 of " embodiment 38 " finish folding after, vertical tail 5 is concealed in the top of tail boom 74; The vertical tail 5 of present embodiment finish folding after, vertical tail 5 is concealed in the below of tail boom 74.Other is identical with " embodiment 38 ".
Shown in Figure 109 first half and Figure 110, a kind of rotor flight car, it comprises fuselage, power system, horizontal drive screw propeller, empennage, alighting gear, the collected type rotor pillar 14 that verts, folding rotor and blade tip flash light, this flash light can be by connecting the flash of light master cock, power supply passes through brush 24 and current colector 23 through lead, again via lead with power delivery to the blade tip place stroboscopic driving circuit in the transparent fairing 18, make aerial discharge flashtube 21 glittering again and again.This " embodiment " can also combine with above-mentioned any enforcement and be new embodiment.
A kind of rotor flight car, it is that with the difference of " embodiment 40 " present embodiment is equipped with the passive reflex reflector of blade tip, and optics corner reflector that it is passive and transparent fairing 18 are installed in the blade tip place of rotor side by side, and other is identical with " embodiment 40 ".
Embodiment 42
Shown in Figure 125, a kind of rotor flight car, it comprises fuselage, power system, horizontal drive screw propeller, empennage, alighting gear, the collected type rotor pillar 14 that verts, folding rotor and road running system; The road running system comprises parts such as surface driving, vehicle acousto-optic, brake system;
Surface driving is used the special-purpose small displacement engine 15 of forward type, is used for driving the preceding wheel of double as direction control, and small displacement engine 15 places in the cabin, and power passes wheel 69 forward by the messenger chain in the nose-gear 68.
This " embodiment " can also combine with above-mentioned any enforcement and be new embodiment.
Embodiment 43
Shown in Figure 126, a kind of rotor flight car, it is with the difference of " embodiment 42 ", the small displacement engine 15 of present embodiment be installed on preceding wheel 69 cabin outside near, the preceding wheel of direct drive, other is identical with " embodiment 42 ".
Embodiment 44
A kind of rotor flight car, it is that with the difference of " embodiment 42 " small displacement engine 15 of present embodiment drives the back wheel by messenger chain, other is identical with " embodiment 42 ".
Embodiment 45
A kind of rotor flight car, it is that with the difference of " embodiment 42 " small displacement engine 15 of present embodiment drives the back wheel by universal-joint, transmission shaft and diff, other is identical with " embodiment 42 ".
According to above each embodiment, the present invention both can fly as conventional cyclogyro, also can be as common small passenger car at road running, it is convenient to landing on highway, can in the small passenger car storehouse, park, have that cost is low, a control comfort, aerial and highway is dual-purpose, safety performance is good characteristics.Its rotor pillar 14, rotor folding, launch conveniently, only need just can finish in the very short time.
1, flight is prepared: it can utilize the ground drive system of this machine self, leave hangar, drive to suitable highway, upwards rise rotor pillar 14, launch rotor and empennage, after locating them, drive screw propeller, pulling trailing cable 17, its rotor of prewhirling, unclamp the wheel brake, get final product rolling start.This machine can fly as conventional cyclogyro, and it handles simple, convenient.
2, landing is regained: this machine flies to after the sky, destination, utilizes suitable highway landing nearby.Fell its tilting rotor pillar 14, folding rotor and empennage, ground drive system that can use itself utilizes highway to sail the destination into as car easily.It is when road running, if the ground Cross Wind Force is very little, its vertical tail 5 can fold, and it is a very convenient flight car.
If use certain part or a few part technology of the present invention, make it to become its reduced form, it still can possess its certain part or a few parts should have the simplification derivative aircraft of advantage.
This machine not only can manufacture practical manned craft, also can be made into the model aircraft, and this model is easy to carry because of it is easy to fold, and the cabin is bigger, and load performance is good, has excellent application value.
In sum, the present invention has adopted collection formula rotor pillar, folding rotor and empennage, the light-duty driving of prewhirling, has comprised blade tip flash lamp and highway The technology such as the empty land annex of the system of travelling. Its expansion rotor and empennage, rise rotor pillar aloft fly in the gyroplane mode; Folding on ground, Collect its rotor pillar, rotor and empennage, be convenient to ground maneuver and travel. This machine be easy to handle, be suitable for flight, security performance good, can rise by short distance Fall, that empty land conversion is quick, highway mobility is good, ground takes up room is little, simple in structure, with low cost, the load performance is good. It can be fine Finish door to the task of door through movement, be a kind of good flight car that carries out between points traffic.
Claims (9)
1, a kind of rotor flight car, this is a kind of improved rotor flight car that carries out on conventional cyclogyro basis, it comprises fuselage, power system, horizontal drive screw propeller, folding vertical tail, alighting gear, vert collected type rotor pillar 14 and folding rotor, light-duty prewhirling drive and the road running system, it is characterized in that:
The vert lower end of collected type rotor pillar 14 is rotationally connected by pillar rotating shaft 13 and fuselage, and the fly direction of car transverse axis of the pillar rotating shaft 13 that both link to each other and rotor is parallel; Rotor pillar 14 upwards rotates when erecting, and the pillar location lock 40 that is fixedly installed on the fuselage can be locked rotor pillar 14 and fuselage together; Open pillar location lock 40 and rotor pillar 14 can be rotated and rely on fuselage, collection is to horizontally-arranged position.
2, rotor flight car according to claim 1, it is characterized in that: rotor pillar 14 is inhead type, and its pillar rotating shaft 13 is installed on the top of fuselage.
3, rotor flight car according to claim 1, it is characterized in that: rotor pillar 14 is exposed for underlying, and its rotor pillar 14 is exposed to outside the fuselage, and its pillar rotating shaft 13 is installed on the outside of underbelly.
4, rotor flight car according to claim 1, it is characterized in that: rotor pillar 14 is built-in for underlying, and the bottom of the rotor pillar 14 that erects is hidden within the fuselage; Pillar rotating shaft 13 is installed within the fuselage; Its canopy 2 is laterally opened; Open canopy 2 and pillar location lock 40, upwards rotate rotor pillar 14, make it to enter within the pillar hole 4 and erect, pillar location lock 40 can be fixed on rotor pillar 14 on the fuselage; Open canopy 2 and pillar location lock 40, rotor pillar 14 can dip down then horizontally-arranged collection.
5, rotor flight car according to claim 1, feature is:
The collected type rotor pillar 14 that verts has oar dish pitching coordinated control; Its oar dish pitching coordinated control comprises: the bearing of rotorshaft 10, pillar rotating shaft 13, rotor pillar 14, top interlock 63, bottom interlock 64, gangbar 65, top universal driving shaft 67 and inner interlock and pitch control bar;
Link and 63 captive joint in the bearing of rotorshaft 10 and top; Being positioned at the top universal driving shaft 67 of top interlock 63 and the upper end of rotor pillar 14 is rotationally connected; Be positioned at the shaft hole of bottom interlock 64, be installed on the root of rotor pillar 14;
Top interlock 63 links to each other with bottom interlock 64 by gangbar 65, rotor pillar 14 respectively, and 4 interconnective four points are four summits that are rotatedly connected, the parallelogram on the same plane of formation;
Bottom interlock 64 links to each other with the pitch control bar by inner interlock.
6, rotor flight car according to claim 1, it is characterized in that: folding rotor comprises parts such as spacing back flap hinge, blade 7; This spacing back flap hinge rotates on the hinge at it, from the inside to the outside, is inserted in stop collar return spring 30 and slip stop collar 9 respectively; Its rotate hinge by flapping hinge 8 and lead lag hinge 6 both one of constitute;
Launch blade 7, slip stop collar 9 limited cover return springs 30 eject, and blade 7 can carry out low-angle free flapping action, turns back but can not carry out wide-angle; Move inward slip stop collar 9, compression stop collar return spring 30, slip stop collar 9 no longer limits the wide-angle of blade 7 and rotates.
7, rotor flight car according to claim 1, its light-duty driving feature of prewhirling is:
Its light-duty prewhirling drives to the machine inhaul drives, and rotorshaft 10 links to each other with sheave 16 by the ratchet 27 of unidirectional rotation; Sheave 16 be subjected to respectively an end fixed thereon, with different directions twine thereon trailing cable 17 and the effect of the rope 38 that resets; The other end of pulling trailing cable 17 in machine drives the rotor rotation of prewhirling through pulley 20, sheave 16, check tooth 28, ratchet 27, rotorshaft 10; Spurring the rope 38 that resets makes trailing cable 17 recover original position.
8, rotor flight car according to claim 1, its folding vertical tail feature is:
Folding vertical tail 5 is a foldable structure; Vertical tail 5 is made up of the anterior rudder face 31 that is installed on tail boom 74 ends, rear portion rudder face 32, folding rudder face, rudder face location lock 35, back flap hinge etc.; Rear portion rudder face 32 includes folding rudder face; Folding rudder face can launch by back flap hinge, and folding rudder face can also fold by back flap hinge; Its rudder face location lock 35 is used for to folding the fixing of rudder face, to avoid the Free Slosh of folding rudder face.
9, rotor flight car according to claim 1, its folding vertical tail feature is:
Folding vertical tail 5 is terminal hinged by vertical shaft back flap hinge 71, plane rotating hinge and tail boom 74; The plane rotating hinge is made of one of transverse axis back flap hinge 70a and longitudinal axis back flap hinge 70b; Vertical tail 5 can utilize vertical shaft back flap hinge 71, plane rotating hinge, and it is erected normal use; Vertical tail 5 also can utilize vertical shaft back flap hinge 71, plane rotating hinge, with its folding horizontally-arranged rear end that is concealed in tail boom 74.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031590209A CN100513214C (en) | 2003-09-11 | 2003-09-11 | Rotor flight car |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031590209A CN100513214C (en) | 2003-09-11 | 2003-09-11 | Rotor flight car |
Publications (2)
| Publication Number | Publication Date |
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| CN1593959A CN1593959A (en) | 2005-03-16 |
| CN100513214C true CN100513214C (en) | 2009-07-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB031590209A Expired - Fee Related CN100513214C (en) | 2003-09-11 | 2003-09-11 | Rotor flight car |
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| CN (1) | CN100513214C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102020202612A1 (en) | 2020-03-02 | 2021-09-02 | Volkswagen Aktiengesellschaft | Rotor arrangement for a vertically launchable aircraft, rotor blade, aircraft |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108437725B (en) * | 2018-03-12 | 2019-11-26 | 北京零创众成科技有限公司 | Rotary wind type hovercar |
| CN109130743B (en) * | 2018-07-03 | 2021-01-15 | 北京海空行科技有限公司 | Rotor wing tilting mechanism of coaxial type flying automobile |
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2003
- 2003-09-11 CN CNB031590209A patent/CN100513214C/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102020202612A1 (en) | 2020-03-02 | 2021-09-02 | Volkswagen Aktiengesellschaft | Rotor arrangement for a vertically launchable aircraft, rotor blade, aircraft |
| WO2021175470A1 (en) | 2020-03-02 | 2021-09-10 | Volkswagen Aktiengesellschaft | Rotor assembly for an aircraft capable of taking off vertically, rotor blade, aircraft |
Also Published As
| Publication number | Publication date |
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| CN1593959A (en) | 2005-03-16 |
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