CN102211664A

CN102211664A - Cross titling coaxial aircraft

Info

Publication number: CN102211664A
Application number: CN201110120501XA
Authority: CN
Inventors: 王略
Original assignee: 王略
Current assignee: Jiangsu Qitian Baird Aviation Technology Co. Ltd.
Priority date: 2011-05-11
Filing date: 2011-05-11
Publication date: 2011-10-12
Anticipated expiration: 2031-05-11
Also published as: CN102211664B

Abstract

The invention provides a cross titling coaxial aircraft. The cross titling coaxial aircraft consists of an umbrella-supporting type machine body, a power transmission mechanism, a cross ring titling mechanism, a double-handle control rod mechanism, a rotor wing reversing counter gear box, upper and lower rotor wings, a propeller hub and paddle clamp mechanism, a pitch control mechanism and a V-shaped empennage; the empennage is connected with a lower rotor wing gear shaft bearing pedestal cover plate through an empennage support pipe; the tail part of the V-shaped empennage support pipe is provided with a V-shaped empennage shaft; a V-shaped empennage steering gear which is provided with two stay wire poles and of which the bevel gear surface faces upward is arranged above the V-shaped empennage shaft, and an empennage is linked with the double-handle control mechanism; a double-handle control rod of the double-handle control mechanism is provided with a steering stay wire seat; and the double-handle control rod is connected with the steering stay wire seat and a stay wire between two stay wire poles which are arranged on the V-shaped empennage steering gear. The coaxial aircraft has the advantages of more simplified structure and low cost, is easy to maintain and operate and the driving mode is greatly simplified.

Description

The coaxial aircraft of cross tilting type

Technical field

The present invention relates to a kind of aviation aircraft, particularly relate to a kind of coaxial aircraft of cross tilting type of vertical takeoff and landing (VTOL).

Background technology

Along with China low latitude is open, various aircraft will enter the every aspect of people's life more and more, satisfy the needs of society to traffic, monitoring and sports and amusement, as the helicopter of vertical takeoff and landing (VTOL) market will be arranged greatly.Helicopter is mainly by pure helicopter and coaxial machine two big classes.Pure helicopter is compared with coaxial twin-rotor helicopter, for the reactive torque that overcomes rotor has had more the tail-rotor control mechanism, causes redundant power consumption, also is not so good as coaxial machine two width of cloth rotors counter-rotating work limitation rate height on hoverning stability; Simultaneously, therefore pure helicopter is compared coaxial machine two width of cloth rotors and will be reached the diameter that same lift need be bigger owing to have only a secondary rotor; And for avoiding the collision of tail-rotor and main rotor, tail-rotor need be extended back usually allowed main rotor wave scope, can cause fuselage long like this, took bigger pad.

Conventional coaxial machine is owing to needs control two width of cloth rotors, so fuselage is higher.Simultaneously owing to need subsidiary two cover tilt table devices to control the displacement and the cycle rotation of upper and lower rotor respectively, the dozens of point of connection needs precision-fit to reverse synchronously to each other, so its control structure is complicated more a lot of than pure helicopter, making and maintenance difficulties are much larger than pure helicopter.At present controlling of these two kinds of types all needs trick to cooperate in addition, and inconvenient operation requires all higherly to driving quality, and the cost of the two and maintenance cost are high, promote being subjected to great limitation as general purpose vehicle.

Summary of the invention

The present invention is directed to the prior art deficiency, when keeping traditional coaxial machine advantage, propose the coaxial aircraft that a kind of structure is simplified more, cheap, safeguard that simply drive manner is simplified greatly, easily operation.

The technical solution adopted in the present invention: the coaxial aircraft of a kind of cross tilting type, it is by umbrella support formula fuselage, Power train, partition ring inclining rotary mechanism, double handle control stalk mechanism, rotor commutation counter gear case, rotor, propeller hub and blade clamp mechanism, pitch-changing mechanism, v type tail are formed up and down.

Described umbrella supports formula fuselage support mechanism by the fuselage column, fuselage column hinged seat, the slide hinged seat of fuselage column, support tube, scaffold pole, the scaffold pole seat, the support tube connector, tray deck, foot-driven lever, the support damping spring, column damping limit base, drive seat board, the column sleeve pipe, the speed reduction gearing clamping plate, the column rubber pad, driving engine yielding rubber cover, the engine bed plate, the partition ring front frame, the partition ring after poppet, the cross ring flexible joint internal axle sleeve, preceding cross ring flexible joint connecting panel, the supporting plate of speed reduction gearing clamping plate and fuel tank are formed.

The fuselage column from top to down, pass the driving seat board, fuselage column hinged seat, the slide hinged seat of fuselage column, utilize the scaffold pole seat on the support tube, scaffold pole, the support connector is the support and connection of umbrella umbrella frame shape with 3 support tubes, driving seat board is fixed by bolts on the fuselage column hinged seat, the foot-driven lever that two ends have steamboat is installed in the front support pipe lower end, next two support tube lower ends are equipped with a tray deck respectively, be equipped with one between the slide hinged seat of fuselage column hinged seat and fuselage column and be enclosed within the outer support damping spring of column, fuselage column bottom is equipped with a column damping limit base, and fuselage column rear portion and top are used for being connected and fixed power part.When fuselage is subjected to from the downward pressure of carrying, three support tubes can outwards strut separately, the pulling scaffold pole, the slide hinged seat of scaffold pole pulling fuselage column can upwards slide, support damping spring between the slide hinged seat of extruding fuselage column hinged seat and fuselage column, the effect of realization elastic buffer damping.

Fuselage column top is equipped with the column sleeve pipe and connects the speed reduction gearing clamping plate respectively, the engine bed plate, be lined with the column rubber pad between the joint face, between the bonded assembly speed reduction gearing clamping plate of fuselage column top, be equipped with three of conversion one-level double reduction have the belt pulley bearing to button-type Pulley shaft bearing, the front end middle-end and the rear end of speed reduction gearing clamping plate are connected with the partition ring front frame respectively, the supporting plate of partition ring after poppet and speed reduction gearing clamping plate, column sleeve pipe lower engine supporting plate is used for fixing driving engine, driving engine damping gum cover is installed between the engine bed plate, vibrations when being used for cushioning engine operation, preceding cross ring flexible joint connecting panel are played the partition ring front frame and are strengthened being connected with fuselage and column sleeve pipe.

Partition ring front frame and partition ring after poppet all are equipped with the cross ring flexible joint internal axle sleeve, partition ring front frame and partition ring after poppet all are processed with top v type limited step up towards the partition ring direction, are used for limiting the amplitude of verting about the partition ring lower plane.

Described dynamic retarding transmission device is by the driving engine that has centrifugal block for clutch use, the centrifugal clutch combined cover, one-level deceleration driving wheel, one-level deceleration flower wheel, the double reduction driving wheel, the double reduction flower wheel, the ball cage verts, the bulb bellows verts, unilateral bearing in the double reduction flower wheel, the unilateral bearing spline, the bracket bearing of unilateral bearing, the double reduction follower shaft, double reduction follower shaft spline, the spacing pin of the bulb that verts, the Pulley shaft bearing, tooth form synchronous belt, the belt pulley bearing, the belt pulley jam nut is formed.

When having the engine operation of centrifugal block for clutch use, reach necessarily in conjunction with rotating speed, centrifugal block for clutch use combines with the centrifugal clutch combined cover, with transmission of power to the one-level driving wheel that slows down, one-level deceleration driving wheel is delivered to one-level deceleration flower wheel with power via tooth form synchronous belt, and be passed to coaxial double reduction driving wheel by one-level deceleration flower wheel, the double reduction driving wheel is delivered to power on the ball cage that verts on the double reduction flower wheel via tooth form synchronous belt, the bracket bearing of a unilateral bearing and unilateral bearing is installed in the double reduction flower wheel, between cover and the double reduction follower shaft double reduction follower shaft spline being installed in the unilateral bearing is connected, between unilateral bearing overcoat and double reduction flower wheel 28 inwalls unilateral bearing spline being housed is connected, the ball cage that verts inserts from double reduction follower shaft upper end, the utilization ball cage lower end castellated shaft that verts combines with double reduction follower shaft inwall spline, the spacing pin of the bulb that verts passes the double reduction follower shaft and the ball cage axle that verts, the outside, two ends is enclosed within the bracket bearing of unidirectional bearing in the double reduction follower shaft, after being delivered to unilateral bearing via double reduction, the engine power that has a centrifugal block for clutch use is delivered to again on the ball cage that verts, being enclosed within the bulb bellows that verts on the ball cage that verts makes the vert spline axle head of the last rotor angular wheel shaft in ball cage and the rotor commutation counter gear case be connected the maintenance sealing state, unilateral bearing ensures that the driving engine moment when power failure have centrifugal block for clutch use ensures rotor rotating freely under force of inertia with power cut.

Described partition ring inclining rotary mechanism by partition ring, partition ring front frame, partition ring after poppet, the arm that verts, the arm gum cover that verts, the suspension rod that verts, the suspension rod nut that verts, the suspension rod spring cotter that verts, front and back vert transverse axis bolt, front and back vert transverse axis bolt spring card, the ball cage that verts, go up rotor angular wheel shaft, rotor commutation counter gear case and both hands control stalk formed.

Partition ring is along axis of pitch a, two spindle noses of a` direction respectively with its below partition ring front frame, the partition ring after poppet connects, partition ring is axis b longitudinally, two spindle noses of b` direction are along the axis direction transverse axis bolt mounting holes that verts before and after having, longitudinal axis b, have two trough type holes that the suspension rod that verts can upwards be installed on two spindle noses of b` direction in addition, long slot bore is passed in two suspension rod lower ends of verting, transverse axis bolt difference axis b longitudinally verts in two front and back, penetrate the suspension rod bottom axis hole that verts in axle center hole and the hole in two spindle noses of b` direction, after partition ring is connected, fasten spacing by the front and back transverse axis bolt spring that verts, two suspension rods that vert are upward through the arm gum cover and by the suspension rod nut locking of verting of verting in the arm that verts respectively, the arm gum cover that verts is used for cushioning the suspension rod that verts and lifts the vibrations that process and rotor commutation counter gear case transmits, vert suspension rod with vert behind the suspension rod nut locking, passing the suspension rod top of verting with the suspension rod spring cotter that verts comes spacing, the arm that will vert fuses with the suspension rod that verts, vert arm upper end is connected formation cross inclining rotary mechanism with rotor commutation counter gear case.The axial line of four spindle noses of the partition ring under the coupled condition is consistent with the ball journal heart of the ball cage that verts, the arm lower end of verting all is processed with plane contact on v type limited step and the partition ring towards the partition ring direction, restriction partition ring anteversion and retroversion gyration, each 7 degree about the v type limited step of partition ring front frame, partition ring after poppet is limited in, be used for controlling axis of pitch a, a` left and right sides to tilt angle, each 10 degree about the v type limited step on two arms that vert of rotor commutation counter gear case both sides are used for controlling longitudinal axis b, b` fore-and-aft direction tilt angle.After the spline axle head of last rotor angular wheel shaft lower end stretches out from rotor commutation counter gear case, insertion is verted behind the spline in the ball cage, the ball journal heart with the ball cage that verts is the center, moving both hands all around makes control stalk partition ring both can vert along about axis of pitch a, a` direction, partition ring also longitudinally verts before and after axis b, the b` direction direction, ensures the output of power under the various states that vert.

Described rotor commutation reversing device by rotor commutation counter gear case, go up the rotor angular wheel shaft, go up rotor angular wheel shaft bearing, commutation counter-rotating bevel gear, commutation counter-rotating bevel gear bearing, commutation counter-rotating bevel gear setscrew nut, backspin parafoil gear wheel shaft, backspin parafoil gear wheel shaft bearing, backspin parafoil gear wheel shaft bearing seat, down rotor gear wheel shaft bearing seat cover plate, go up the rotor shaft backup bearing, go up the rotor shaft supporting bearing base and form.

Last rotor angular wheel shaft lower end be equipped with two go up rotor angular wheel shaft bearing pass downwards be installed at the bottom of the rotor commutation counter gear case on, the terminal spline axle head of last rotor angular wheel shaft stretches out the commutation umbrella gear box that reverses, ball cage inner spline housing is connected with verting.After last rotor angular wheel shaft is upward through down the rotor gear wheel shaft, link together by last rotor shaft backup bearing, last rotor shaft supporting bearing base with backspin parafoil gear wheel shaft, last rotor supporting bearing base and following rotor gear wheel shaft are by being threaded, and adopting bolt locking spacing, last rotor shaft backup bearing and last rotor shaft supporting bearing base play the supporting role between rotor angular wheel shaft and the backspin parafoil gear wheel shaft.Opposed between the rotor angular wheel shaft face of gear up and down two commutation counter-rotating bevel gears are installed, described commutation counter-rotating bevel gear is meshed with the face of gear of rotor angular wheel shaft up and down, the gear wheel shaft of commutation counter-rotating bevel gear respectively penetrates two commutation counter-rotating bevel gear bearings, be installed on the rotor commutation counter gear case, the gear wheel shaft end of commutation counter-rotating bevel gear is fixed by commutation counter-rotating bevel gear setscrew nut, power comes up and the engagement of opposed two commutation counter-rotating bevel gears via the bottom spline transmission of last rotor angular wheel shaft, and promotes the contrarotation of backspin parafoil gear wheel shaft via opposed two commutation bevel gears.

Because rotary wing changing is very little apart from required separation distance, utilize in the rotor commutation counter gear case two commutation counter-rotating bevel gears and up and down in the finite space between the rotor angular wheel shaft face of gear, installed by last rotary wing changing apart from the dish outer shroud, last rotary wing changing is apart from the dish bearing, last rotary wing changing encircles in dish, last rotary wing changing is apart from dish inner ring card, last rotary wing changing encircles the molecular rotary wing changing of going up of push rod pin apart from disc mechanism in dish, install one in the last rotor angular wheel shaft and gone up the rotor Adjustable length rod, last rotary wing changing ring push rod pin in the dish pass rotary wing changing encircle in the dish with last rotor angular wheel shaft on trough type displacement hole be connected with last rotor Adjustable length rod lower end, last rotary wing changing apart from the dish bearing inner sleeve with last rotary wing changing apart from the dish in loops fashionable, it is spacing apart from the interior ring of dish push rod pin two ends to go up rotary wing changing, last rotary wing changing combines apart from the dish bearing with last rotary wing changing with the make-up form apart from dish is inside and outside, and use respectively rotary wing changing apart from dish inner and outer ring Spring Card will go up rotary wing changing apart from the dish bearing fixing at last rotary wing changing apart from coiling in the middle of the inner and outer ring, last rotary wing changing utilizes two chutes in the rotor commutation counter gear case apart from two pipe links of dish on the outer shroud, is upward through backspin parafoil gear wheel shaft bearing seat, following rotor gear wheel shaft bearing seat cover plate is connected with pitch-changing mechanism.

Described double handle control stalk mechanism by both hands control stalk, starting switch, displacement pawl axle, fan-shaped displacement shift fork, displacement pawl shaft alignment bolt, displacement pawl, displacement wisp, throttle shifting fork bar, control stalk pedestal, control stalk axle, control stalk spindle nut, turn to the backguy seat, turn to backguy seat Spring Card and up and down rotary wing changing form apart from disc mechanism.

The control stalk axle passes control stalk pedestal the first half, backspin parafoil gear wheel shaft bearing cover, after control stalk pedestal the latter half, utilize the locking of control stalk spindle nut to constitute the control stalk pedestal, the first half of control stalk pedestal is installed displacement pawl axle, fan-shaped displacement shift fork is installed in the middle of the displacement pawl axle, both sides are equipped with two and turn to the backguy seat, two displacement pawls are equipped with at two ends, and utilize backguy connecting strap on the control stalk to be connected respectively with both hands, fan-shaped displacement shift fork and displacement pawl are bolted on the displacement pawl axle by displacement pawl shaft alignment, two turn to the backguy seat keep and displacement pawl axle between be rotatably connected in, the slip about backguy seat Spring Card restriction of turning to by both sides, the latter half of control stalk pedestal is equipped with both hands control stalk, double handle control stalk left and right handles all is equipped with the displacement wisp, wherein the left hand handgrip is equipped with engine start switch, be used for start the engine, right hand handgrip is equipped with the throttle shifting fork bar, is used for the control of throttle and rotating speed.

Both hands can be control stalk to reverse about the center with the control stalk axle, utilization turns to the backguy seat to affect to connect the backguy between the stay rod on the v type tail steering gear, drive the deflection of v type tail, under the purling that rotor produces impacts, produce traverse resistance promotion fuselage and realize turning to flight, also can move both hands all around control stalk, make whole rotor shaft mechanism vert all around, flight left and right sides cross side flies before and after realizing.

The left and right sides displacement wisp of double handle control stalk mechanism can be separately or is controlled the rotor pitch angle of attack jointly, displacement wisp by the tension right-hand man, the rotation of displacement pawl axle is moved in backguy between pulling displacement wisp and the displacement pawl, and drive fan-shaped displacement shift fork on the displacement pawl axle simultaneously, press down the arcs of recesses alveolar surface on the following rotor displacement dish outer shroud that is meshed with fan-shaped displacement shift fork, driving up and down, rotary wing changing mechanism realizes rotor angle of attack displacement, with the control stalk axle is that central sector displacement shift fork is in Turning radius, all the time with following rotor displacement outer shroud exterior front be the center with the control stalk axle equally, and the arcs of recesses alveolar surface of the following rotor displacement outer shroud exterior front that also equates of radius is meshed.Even reverse both hands in the control stalk steering procedure, be that the fan-shaped displacement shift fork at center is meshed with arcs of recesses alveolar surface on the following rotor displacement dish outer shroud all the time with the control stalk axle, ensure that the displacement action is finished in the handling maneuver scope.

Described rotary wing changing spacing mechanism up and down is by encircling in the rotor displacement dish down, following rotor displacement dish inner ring card, following rotor displacement dish outer shroud, following rotor displacement dish outer ring spring card, following rotor displacement dish bearing, following rotor displacement bulb push rod, last rotary wing changing encircles in dish, last rotary wing changing is apart from dish inner ring card, last rotary wing changing is apart from lever pin, last rotary wing changing is apart from the dish outer shroud, last rotary wing changing is apart from dish outer ring spring card, last rotary wing changing is apart from the dish bearing, last rotor Adjustable length rod, last rotary wing changing is apart from the stem nut cover, last rotor Adjustable length rod cross bar, last rotary wing changing is apart from ball-head tension rod, last rotary wing changing is apart from pull back spring, the displacement wisp, fan-shaped displacement shift fork, the blade Adjustable length rod, propeller hub, the blade folder, rotor is formed.

Because rotary wing changing is very little apart from required separation distance, utilize two commutation counter-rotating bevel gears and the gap between the rotor angular wheel shaft face of gear up and down, last rotary wing changing has been installed apart from the dish outer shroud, last rotary wing changing is apart from the dish bearing, last rotary wing changing encircles in dish, last rotary wing changing is apart from dish inner ring card, last rotary wing changing apart from the molecular rotary wing changing of going up of lever pin apart from disc mechanism, install one in the last rotor angular wheel shaft and gone up the rotor Adjustable length rod, the upper shaft head thread of last rotor Adjustable length rod stretches out the rotor angular wheel shaft, pass rotary wing changing behind pull back spring, by last rotary wing changing apart from the stem nut cover locking, to go up rotary wing changing and be pressed on rotor angular wheel shaft top apart from pull back spring, last rotor Adjustable length rod cross bar passes rotary wing changing behind the stem nut cover, two ends are connected apart from the ball-head tension rod upper end with two last rotary wing changings respectively, last rotary wing changing is connected on the blade Adjustable length rod of upper strata rotor hub apart from the ball-head tension rod lower end, last rotary wing changing apart from lever pin pass rotary wing changing apart from the dish in the ring with last rotor angular wheel shaft on trough type displacement hole be connected with last rotor Adjustable length rod lower end, last rotary wing changing apart from the dish bearing inner sleeve with last rotary wing changing apart from the dish in loops fashionable, it is spacing apart from the sub-two ends of lever pin to go up rotary wing changing, last rotary wing changing combines apart from the dish bearing with last rotary wing changing apart from dish inner and outer ring make-up form, and above respectively rotary wing changing apart from dish inner and outer ring Spring Card will go up rotary wing changing apart from the dish bearing fixing at last rotary wing changing apart from coiling in the middle of the inner and outer ring, last rotary wing changing utilizes two chutes in the rotor commutation counter gear case apart from two pipe links of dish on the outer shroud, being upward through backspin parafoil gear wheel shaft bearing seat is connected with the arcs of recesses alveolar surface of following rotor displacement outer shroud exterior front and the pawl that is connected at rear portion with following rotor gear wheel shaft bearing seat cover plate, on the outside of ring two screw seats are up arranged in the following rotor displacement, be used for installing down rotor displacement bulb push rod, following rotor displacement bulb push rod connects two blade Adjustable length rod A of lower floor's rotor respectively, between ring and the following rotor displacement dish outer shroud rotor displacement dish bearing is housed down in the following rotor displacement dish, and respectively by rotor displacement dish inner ring card and following rotor displacement dish outer ring spring fasten spacing down.

When tension displacement wisp drives fan-shaped displacement shift fork, press down down the arcs of recesses alveolar surface on the rotor displacement dish outer shroud, the change mechanism that drives whole rotor moves down, realize the angle of attack displacement of rotor, under this state, last rotary wing changing is apart from ball-head tension rod and the following rotor displacement bulb push rod blade Adjustable length rod A of push-and-pull levels propeller hub on blade presss from both sides separately respectively, make that the rotor at levels propeller hub A two ends is that the center is reversed with blade folder axle, the change of the generation angle of attack, last rotary wing changing is compressed in the process that moves down apart from pull back spring, when unclamping the displacement wisp, the compressed rotary wing changing of going up can push back the home position with the change mechanism of rotor apart from the tension force that the pull back spring utilization discharges, and makes the angle of attack of rotor restore.

Described v type tail mechanism is made up of v type tail support tube, v type tail support tube damping blob of viscose, v type tail, v type tail steering gear, v type tail steering gear axle, v type tail axle, v type tail support, storage battery, v type tail axle lock nut.V type tail support tube is connected down on the rotor gear wheel shaft bearing seat cover plate, can vert together along with rotor shaft angular wheel shaft up and down, be lined with v type tail support tube damping blob of viscose between the two, sagging 10 degree of v type tail support tube afterbody are installed, avoid colliding with the top rotor, v type tail support tube afterbody is equipped with v type tail axle, v type tail axle top is installed and is had two stay rods, and the prone v type tail of bevel gear steering gear, and, the two is fixed together by v type tail steering gear axle insertion v type tail steering gear and v type tail axle.Have turn to bevel gear and v type tail pipe spreader v type tail carrying sleeve on v type tail axle, v type tail axle lock nut is fixed together v type tail axle and v type tail support, storage battery as both hands the operation of control stalk with turn to the counterweight of return, be contained in the v type tail support, the v type tail is installed on the v type tail support, when reversing both hands control stalk, affect both hands turning to the backguy seat on the control stalk, turn to the backguy seat drive to connect and v type tail steering gear on backguy between two stay rods, make v type tail steering gear when reversing, with be engaged with to have the v type tail support and the bonded assembly v type tail thereof that turn to bevel gear be that the center deflects with v type tail axle, the aerofoil on the go of the v type tail that upward deflects is subjected to the purling impact that rotor produces, produce the side horizontal thrust, promotion v type tail is walked crosswise mobile and is driven fuselage and finishes handling maneuver.

Described propeller hub A mechanism is made up of propeller hub A, propeller hub flange A, blade spindle damping gum cover A, a blade folder axle A, blade folder axle sleeve A, blade folder A, blade Adjustable length rod A, a blade folder axle caging bolt A, four rib propeller hub bolt of rear end plates.Propeller hub A up and down is towards rotor angular wheel shaft direction up and down, both sides, the left and right sides are processed with six square openings separately, utilize four square rib propeller hub bolt of rear end plates, after passing up and down propeller hub A six square openings blocking six square grooves leaving separately on the rotor angular wheel shaft up and down separately, fixed.It in the middle of two ends screwed spindle nose of difference and the polished rod spindle nose polished rod spindle nose one end that spherical blade presss from both sides axle A, penetrate and penetrate blade spindle damping gum cover A again behind the blade folder axle sleeve A and be installed in the propeller hub A, be fixed on the propeller hub A by the propeller hub flange A that has the spill sphero-cylindrical lens, after screwed spindle nose one end of blade folder axle A stretches out propeller hub A, after utilizing screw thread and blade folder to be connected and fixed, and it is spacing by blade folder axle caging bolt A locking, the centre of blade folder axle A be spherical with propeller hub flange A on ball head structure that can obtain to reverse up and down significantly of spill sphero-cylindrical lens formation, satisfy the needs of cross hinge function.Blade folder axle A inserts the part polished rod spindle nose in the propeller hub A, pushes blade spindle damping gum cover A up and down, and can be in blade presss from both sides axle sleeve A free torsion, make rotor lift down at blade Adjustable length rod A, reverse rotor folder axle and produce an angle of attack displacement.

Described another set of propeller hub B mechanism is made up of propeller hub B, concave ball shape bearing shell B, a blade folder axle damping gum cover B, a blade folder axle B, blade folder B, blade folder flange B, blade folder axle bearing B, blade Adjustable length rod B, a blade folder axle captive nut B, four rib propeller hub bolt of rear end plates.Propeller hub B is connected and fixed mode with rotor angular wheel shaft up and down and propeller hub A is consistent, adopt equally four rib propeller hub bolt of rear end plates with propeller hub B and up and down the rotor angular wheel shaft be fixed together.Blade folder axle B is that an end is the bulb type, the other end is screwed spindle nose, what concave ball shape bearing shell B was enclosed within blade folder axle B is bulb type one end spindle nose, and utilize being threaded togather in concave ball shape bearing shell B self and the propeller hub B, the bulb type one end spindle nose that is of blade folder axle B is locked in the propeller hub B, blade folder axle damping gum cover B is enclosed within on the blade folder axle B, and be installed in the propeller hub B, spindle nose that is the bulb type and the concave ball shape bearing shell B of blade folder axle B are nested together, form a ball head structure that can reverse up and down significantly, satisfy the needs of cross hinge function, and blade folder axle damping gum cover B is as the spacing and buffering of blade folder axle B activity up and down in propeller hub, the blade folder axle B other end is screwed head, after passing blade folder flange B and two blades folder axle bearing B, a B is fixed in the blade folder B, during push-and-pull blade Adjustable length rod B by blade folder axle B captive nut, blade folder B can blade folder axle B be the center free torsion, drives the bonded assembly rotor and produces angle of attack displacement.

Useful good effect of the present invention:

1, the coaxial aircraft of cross tilting type of the present invention is simple in structure, adopts contrarotation bispin wing structure, the hovering efficiency height, and the landing floor area is little.Upper and lower rotor adopts inside and outside two pitch-changing mechanisms of axle, has substituted complicated tilt table device, has omitted the direction control of pure helicopter both feet.Traditional tail-rotor and complicated auto-bank unit mechanism have been omitted, propeller hub is connected with the bulb form with the blade folder, the hinge type structure that has replaced traditional cross hinge, keep flapping hinge and lead lag hinge simplified its structure greatly in the function, cost and maintenance cost are very cheap.

2, the coaxial aircraft of cross tilting type of the present invention, drive manner is simple, possesses all flight characteristicses of conventional helicopters, but compared with the brothers of conventional helicopters and with controlling, has liberated driver's both feet, only just can finish the control of all flights by both hands.Succinct practical built-in rotary wing changing spacing mechanism makes helicopter can tackle the different condition needs calmly.

3, the coaxial aircraft of cross tilting type of the present invention, possess in-flight engine breakdown and cause under the motorless state, changing pitch and rear-inclined oar axle makes rotor keep spinning glide landing function, require very low to pad, maneuverability, not only be suitable for low latitude monitoring, rescue, be more suitable in sports and amusement.Adopt umbrella support formula fuselage framework, very light in weight, succinct practical, and possess certain damping performance.

4, the coaxial aircraft of cross tilting type of the present invention possesses the hypsokinesis displacement spin landing function under the unpowered state.Adopt partition ring mechanism to change verting all around, and by elastic buffer rubber coating connection fuselage and rotor shaft part, possess the propeller hub of cross hinge function and blade folder kept flapping hinge and lead lag hinge function, be installed in that double handle control stalk on the rotor commutation counter gear case can be finished fore-and-aft direction flight, left and right sides flies sidelong and by about reverse control v type tail pivot stud and the aloft function that turns to.Change pitch by the cooperation of any one hand or both hands, can ensure under its different conditions demand the rotor angle of attack.Technology of the present invention can be used on the rotor class aircrafts such as helicopter, conventional cyclogyro, tilting type cyclogyro equally.

Description of drawings

Fig. 1: complete machine External view under the coaxial aircraft driving condition of invention cross tilting type;

Fig. 2: the coaxial aircraft power transmission of cross tilting type of the present invention scheme drawing;

Fig. 3: the coaxial aircraft wings axle of the present invention reverses, verts, pitch-changing mechanism and empennage part exploded drawings;

Fig. 4: umbrella support formula fuselage support part main composition;

Fig. 5: all exploded views of umbrella support formula fuselage;

Fig. 6: umbrella support formula fuselage assembling assumption diagram;

Fig. 7: the partition ring structure member exploded drawings that verts;

Fig. 8: rotor shaft and displacement controlling machine composition;

Fig. 9: control the signal of piecemeal activity direction scope;

Figure 10: both hands control stalk and rotary wing changing up and down apart from the dish constructional drawing;

Figure 11: propeller hub A part-structure scheme drawing one;

Figure 12: propeller hub A part-structure scheme drawing two;

Figure 13: propeller hub B part-structure scheme drawing one;

Figure 14: propeller hub B part-structure scheme drawing two.

Each parts label in the accompanying drawing:

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71A 72A 73A 74 A 75 A 76A 77 A 78 A 79 80B 81 B 82 B 83B 84B 85 B 86B 87B 88B 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 v 112 v 113 v 114 v 115 v 116 v 117 v 118 119 v。

The specific embodiment

Embodiment one: referring to Fig. 1, Fig. 2, the coaxial aircraft of cross tilting type of the present invention, comprise rotor 89, empennage 113, the described rotor of going up, following rotor is arranged on fuselage column 1 top, fuselage column bottom is provided with drives seat board 12, stationary engine 23 on described fuselage column 1 and driving seat board 12, fuel tank and speed reduction gearing, engine output power passes through speed reduction gearing, the ball cage 29 that verts is connected rotor and following rotor with rotor commutation counter gear case 90, the output flower wheel center of described speed reduction gearing is provided with a unilateral bearing, in the described unilateral bearing 30 cover with export follower shaft 33 and be connected by spline, unilateral bearing 30 overcoats are connected by spline 31 with the inwall of output flower wheel 28, the described ball cage 29 that verts inserts and combines with its castellated shaft inwall from output follower shaft 33 upper ends of speed reduction gearing, the rotor that is in transmission connection commutation counter gear case 90.Foregoing description is referring to Fig. 7.The effect of unilateral bearing 30 is to ensure that driving engine 23 moment when power failure have centrifugal block for clutch use ensures rotor 89 rotating freely under force of inertia with power cut.

Among Fig. 3, be provided with the rotor angular wheel shaft in the described rotor commutation counter gear case, commutation counter-rotating bevel gear, backspin parafoil gear wheel shaft, the lower end of last rotor angular wheel shaft 91 is stretched out from described rotor commutation counter gear case 90 bottoms and is connected with the ball cage that verts, last rotor angular wheel shaft is upward through down the rotor gear wheel shaft, with opposed two the commutation counter-rotating bevel gears that are equipped with that are meshed with two face of gears between the rotor bevel gear up and down, two commutation counter-rotating bevel gears are installed on the rotor commutation counter gear case, and power comes up and the engagement of opposed two commutation counter-rotating bevel gears via the bottom spline transmission of last rotor angular wheel shaft; Commutation counter-rotating bevel gear 93 will be from the transmission of power of last rotor angular wheel shaft 91 to the face of gear of backspin parafoil gear wheel shaft 96, make backspin parafoil gear wheel shaft 96 produce the opposite spin with last rotor angular wheel shaft 91, contrarotation is simultaneously separately in power driven for last rotor angular wheel shaft 91 and backspin parafoil gear wheel shaft 96, drive propeller hub A71 separately, and be connected rotor 89 rotary works on the blade folder A76 separately; The ball cage 29 that verts is connected via the arm 103 that verts power with the last rotor angular wheel shaft 91 lower end spline axle heads that stretch out partition ring 102 bonded assembly rotors commutation counter gear case 90 bottoms, last rotor angular wheel shaft 91 spline axle head that utilizes and ball cage 29 inner spline grooves that vert are interlocked, the outside of the two binding site is covered by the bulb bellows 110 that verts, prevent that dust from entering 29 li in the ball cage of verting, last rotor angular wheel shaft 91 upper ends are passed backspin parafoil gear wheel shaft 96 and are protruded upward, between last rotor angular wheel shaft 91 and rotor angular wheel shaft 96 tops rotor shaft supporting bearing base 101 is installed, last rotor shaft backup bearing 100 in the utilization in the rotor shaft supporting bearing base 101 is separated upward rotor angular wheel shaft 91 and rotor angular wheel shaft 96, interference-free when supporting the two and the two is rotated freely separately, face about the axle mounted on surface propeller hub A71 position separately of last rotor angular wheel shaft 91 and backspin parafoil gear wheel shaft 96, all be processed with the square groove that fixing propeller hub A71 uses, can cooperate four rib propeller hub bolt of rear end plates 79 that propeller hub A71 is fixed on rotor angular wheel shaft 91 and the backspin parafoil gear wheel shaft 96, two opposed commutation counter-rotating bevel gears 93 are installed between the face of gear of last rotor angular wheel shaft 91 and backspin parafoil gear wheel shaft 96, commutation counter-rotating bevel gear bearing 94 is housed on the axle of commutation counter-rotating bevel gear 93, and is fixed on commutate 90 li in counter gear case of rotor by the commutation counter-rotating bevel gear setscrew nut 95 counter-rotating bevel gear 93 that will commutate.

Empennage of the present invention and steering structure such as Fig. 3, shown in Figure 9: v type tail support tube 111 is connected down on the rotor gear wheel shaft bearing seat cover plate 99, can be along with rotor shaft angular wheel shaft 91 up and down, 96 vert together, be lined with v type tail support tube damping blob of viscose 112 between the two, sagging 12 degree of v type tail support tube 111 afterbodys are installed, avoid and 89 collisions of top rotor, v type tail support tube 111 afterbodys are equipped with v type tail axle 116, v type tail axle 116 tops are installed one and are had two stay rods, and the prone v type tail of bevel gear steering gear 114, and, the two is fixed together by v type tail steering gear axle 115 insertion v type tail steering gear 114 and v type tail axles 116.Having the v type tail support 117 that turns to bevel gear and v type tail pipe spreader is enclosed within on the v type tail axle 116, v type tail axle lock nut 119 is fixed together v type tail axle 116 and v type tail support 117, storage battery 118 as both hands the operation of control stalk 63 with turn to the counterweight of return, be contained in the v type tail support, the v type tail is installed on the v type tail support, when reversing both hands control stalk, affect both hands turning to backguy seat 69 on the control stalk 63, the backguy that turns to backguy seat 69 to drive between connection and the v type tail steering gear 114, make v type tail steering gear 114 when reversing, with be engaged with to have the v type tail support 117 and the bonded assembly v type tail 113 thereof that turn to bevel gear be that the center deflects with v type tail axle 116, the aerofoil on the go of the v type tail 113 that upward deflects is subjected to the purling impact that rotor 89 produces, produce the side horizontal thrust, promotion v type tail 113 is walked crosswise mobile, and the drive fuselage is finished handling maneuver.

Poewr transmission mechanism of the present invention such as Fig. 2, it is shown in Figure 3: after the driving engine 23 that has centrifugal block for clutch use starts, after reaching certain rotating speed, combine with centrifugal clutch combined cover 24, transmission of power is arrived one-level deceleration driving wheel 25, be delivered to one-level deceleration flower wheel 26 via tooth form synchronous belt 37, one-level deceleration flower wheel 26 arrives double reduction driving wheel 27 with transmission of power, double reduction driving wheel 27 is delivered on the ball cage 29 that verts of double reduction flower wheel 28 via tooth form synchronous belt 37, the bracket bearing 32 of a unilateral bearing 30 and unilateral bearing 30 is installed in the double reduction flower wheel 28, between cover and the double reduction follower shaft 33 double reduction follower shaft spline 34 being installed in the unilateral bearing 30 is connected, between unilateral bearing 30 overcoats and double reduction flower wheel 28 inwalls unilateral bearing spline 31 being housed is connected, the ball cage 29 that verts inserts from double reduction follower shaft 33 upper ends, the utilization ball cage 29 lower end castellated shafts that vert combine with the castellated shaft inwall of double reduction follower shaft 33, the spacing pin 35 of the bulb that verts passes double

reduction follower shaft

33 and 29 in the ball cage of verting, the outside, two ends is enclosed within the double reduction follower shaft 33 in the bracket bearing 32 of unidirectional bearing, after being delivered to unilateral bearing 30 via double reduction, driving engine 23 power that have a centrifugal block for clutch use are delivered to again on the ball cage 29 that verts, being enclosed within the bulb bellows 110 of verting on the ball cage 29 that verts makes the vert spline axle head of the last rotor angular wheel shaft 91 in ball cage 29 and the rotor commutation counter gear case 90 be connected the maintenance sealing state, unilateral bearing 30 ensures that driving engine 23 moment when power failure that has centrifugal block for clutch use ensures rotor 89 rotating freely under force of inertia with power cut.

Embodiment two: the coaxial aircraft of cross tilting type of present embodiment, cooperate with described rotor commutation counter gear case and to be provided with the displacement control mechanism, described displacement control mechanism comprises that rotary wing changing is apart from dish structure and following rotor displacement dish structure, referring to Fig. 3, Fig. 8, Fig. 9, Figure 10.

As Fig. 3, it is shown in Figure 8: because the displacement required separation distance of rotor 89 is very little, utilize two commutation counter-rotating bevel gears 93 and rotor angular wheel shaft 91 up and down in the rotor commutation counter gear case 90, in the finite space between 96 face of gears, installed by last rotary wing changing apart from dish outer shroud 50, last rotary wing changing is apart from dish bearing 52, last rotary wing changing encircles 47 in dish, last rotary wing changing is apart from dish inner ring card 48, the last rotary wing changing that last rotary wing changing is formed apart from lever pin 49 is apart from coiling structure, install one in the last rotor angular wheel shaft 91 and gone up rotor Adjustable length rod 53, the upper shaft head thread of last rotor Adjustable length rod 53 stretches out rotor angular wheel shaft 91, pass rotary wing changing behind pull back spring 57, lock apart from stem nut cover 54 by last rotary wing changing, to go up rotary wing changing and be pressed on rotor angular wheel shaft 91 tops apart from pull back spring 57, last rotor Adjustable length rod cross bar 55 passes rotary wing changing behind stem nut cover 54, two ends are connected apart from ball-head tension rod 56 upper ends with two last rotary wing changings respectively, last rotary wing changing is connected on the blade Adjustable length rod A77 of upper strata rotor hub A71 apart from ball-head tension rod 56 lower ends, last rotary wing changing apart from lever pin 49 pass rotary wing changing apart from the dish in the ring 47 with last rotor angular wheel shaft 91 on trough type displacement hole be connected with last rotor Adjustable length rod 53 lower ends, when last rotary wing changing is enclosed within last rotary wing changing apart from dish that ring 47 combines in dish in the bearing 52, it is spacing apart from lever pin 49 two ends to go up rotary wing changing, last rotary wing changing is apart from dish inner and

outer ring

47,50 combine apart from dish bearing 52 with make-up form and last rotary wing changing, and above rotary wing changing is apart from dish inner and outer ring Spring Card 48 respectively, 51 will go up rotary wing changing is fixed on rotary wing changing apart from dish inner and outer ring 47 apart from dish bearing 52, in the middle of 50, last rotary wing changing utilizes two chutes in the rotor commutation counter gear case 90 apart from two pipe links of dish on the outer shroud 50, being upward through backspin parafoil gear wheel shaft bearing seat 98 is connected with the arcs of recesses alveolar surface of following rotor displacement outer shroud 43 exterior front and the pawl that is connected at rear portion with following rotor gear wheel shaft bearing seat cover plate 99, on the outside of ring 41 two screw seats are up arranged in the following rotor displacement, be used for installing down rotor displacement bulb push rod 46, following rotor displacement bulb push rod 46 connects two blade Adjustable length rod A77 of lower floor's rotor respectively, between ring 41 and the following rotor displacement dish outer shroud 43 rotor displacement dish bearing 45 is housed down in the following rotor displacement dish, and respectively by following rotor displacement dish inner ring card 42 and following rotor displacement dish outer ring spring card 44 fixed limits.

As shown in figure 10: control stalk axle 67 passes control stalk pedestal 66 the first half, backspin parafoil gear wheel shaft bearing cover 99, after the latter half of control stalk pedestal 66, utilize 68 lockings of control stalk spindle nut to constitute control stalk pedestal 66, the first half of control stalk pedestal 66 is installed displacement pawl axle 59, fan-shaped displacement shift fork 60 is installed in the middle of the displacement pawl axle 59, be equipped with two in the middle of the both sides and turn to backguy seat 69, two displacement pawls 62 are equipped with at two ends, and utilize backguy connecting strap on the control stalk 63 to be connected respectively with both hands, fan-shaped displacement shift fork 60 and displacement pawl 62 are fixed on the displacement pawl axle 59 by displacement pawl shaft alignment bolt 61, two turn to backguy seat 69 keep and displacement pawl axle 59 between be rotatably connected in, the slip about backguy seat Spring Card 70 restriction of turning to by both sides, the latter half of control stalk pedestal 66 is equipped with both hands control stalk 63, double handle control stalk 63 left and right handles all are equipped with displacement wisp 64, wherein the left hand handgrip is equipped with engine start switch 58, be used for start the engine, right hand handgrip is equipped with throttle shifting fork bar 65, be used for the control of throttle and rotating speed, both hands can be control stalk 63 to reverse about the axle center with control stalk pedestal 66, utilization turns to backguy seat 69 to affect to connect the backguy between the shifting fork bar on the v type tail steering gear 114, drive 113 deflections of v type tail, produce traverse resistance promotion fuselage and realize turning to flight, also can move both hands all around control stalk 63, make whole rotor shaft mechanism vert all around, flight and left and right sides cross side fly before and after realizing.

As Fig. 3, Fig. 8, Fig. 9, shown in Figure 10: by tension right-hand man's

displacement wisp

64,59 rotations of displacement pawl axle are moved in backguy between pulling displacement wisp 64 and the displacement pawl 62, and drive fan-shaped displacement shift fork 60 on the displacement pawl axle 59 simultaneously, press down down the arcs of recesses alveolar surface on the rotor displacement dish outer shroud 43, drive the pitch-changing mechanism realization rotor angle of attack displacement of rotor 89 up and down, right-hand man's displacement wisp 64 can be separately or is controlled the pitch angle of attack of rotor 89 jointly, with control stalk axle 67 is that central sector displacement shift fork 60 is in Turning radius, all the time with following rotor displacement outer shroud 43 exterior front be the center with control stalk axle 67 equally, and the arcs of recesses alveolar surface of following rotor displacement outer shroud 43 exterior front that radius also equates is meshed, even reverse both hands in control stalk 63 steering procedures, with control stalk axle 67 is that the fan-shaped displacement shift fork 60 at center is meshed with arcs of recesses alveolar surface on the following rotor displacement dish outer shroud 43 all the time, ensures that the displacement action is finished in the handling maneuver scope.

When tension displacement wisp 64 drives fan-shaped displacement shift fork 60, press down down the arcs of recesses alveolar surface on the rotor displacement dish outer shroud 43, the pitch-changing mechanism that drives whole rotor 89 moves down, realize the angle of attack displacement of rotor 89, under this state, the blade that last rotary wing changing is distinguished push-and-pull levels propeller hubs 71 apart from ball-head tension rod 56 and following rotor displacement bulb push rod 46 presss from both sides the blade Adjustable length rod A77 on 76, make that the rotor 89 at levels propeller hub A71 two ends is that the center is reversed with separately blade folder axle 74, the change of the generation angle of attack, the normality angle of attack of rotor 89 is set at 10 degree up and down, when tension displacement wisp 64, last rotary wing changing is compressed in the process that moves down apart from pull back spring 57, along with pitch-changing mechanism moves down, the angle of attack of rotor 89 may be compressed to minimum angle of attack 2 degree up and down, be convenient to rotate and during in unpowered forced landing, when whole rotor mechanism hypsokinesis 10 was spent, rotor 89 can enter spin states safety and force-land in the starting state low resistance.When unclamping displacement wisp 64, the compressed rotary wing changing of going up utilizes the tension force that discharges the change mechanism of rotor 89 can be pushed back the home position apart from pull back spring 57, makes that the angle of attack of rotor 89 restores up and down.

Embodiment three: the coaxial aircraft of cross tilting type of present embodiment, both hands control mechanism by both hands control stalk, starting switch, displacement pawl axle, fan-shaped displacement shift fork, displacement pawl shaft alignment bolt, displacement pawl, displacement wisp, throttle shifting fork bar, control stalk pedestal, control stalk axle, control stalk spindle nut, turn to the backguy seat, turn to backguy seat Spring Card and upper and lower rotary wing changing to form apart from disc mechanism; The control stalk axle passes control stalk pedestal the first half, backspin parafoil gear wheel shaft bearing cover, after control stalk pedestal the latter half, utilize the locking of control stalk spindle nut to constitute the control stalk pedestal, the first half of control stalk pedestal is installed displacement pawl axle, fan-shaped displacement shift fork is installed in the middle of the displacement pawl axle, both sides are equipped with two and turn to the backguy seat, two displacement pawls are equipped with at two ends, and utilize backguy connecting strap on the control stalk to be connected respectively with both hands, fan-shaped displacement shift fork and displacement pawl are bolted on the displacement pawl axle by displacement pawl shaft alignment, two turn to the backguy seat to be rotatably connected, and be provided with in both sides that restriction horizontally slips turn to backguy seat Spring Card, the latter half of control stalk pedestal is equipped with both hands control stalk, double handle control stalk left and right handles all is equipped with the displacement wisp, wherein the left hand handgrip is equipped with engine start switch, and right hand handgrip is equipped with the throttle shifting fork bar.

Both hands of the present invention are the major control structure action radius of control stalk as shown in Figure 9: a, a` and b, two central axis of b ` are represented about four spindle noses of center cross respectively and the action radius of verting of front and back, and this scope ensures that coaxial machine realizes that left and right sides crabbing realizes fore-and-aft direction flight.C, the c` central axis represents that with control stalk pedestal 66 be the center, action radius when both hands drive the implementation handling maneuver of displacement pawl axles 62 to control stalk 63, in this steering range, displacement pawl axle 62 drives on the displacement pawl axles 62 two and turns to backguy seat 69 to affect v type tail steering gear 114 on the 116 v type tail axles with the d of v type tail steering gear axle 115, the d` central axis is the center, be meshed with the bevel gear face on the v type tail support 117 that has bevel gear, drive v type tail support 117 central axis g with 116 v type tail axles, g` is the center, when utilizing v type tail 113 left and right sides deflections on the v type tail support 117, the resistance that the left and right sides aerofoil of v type tail 113 is subjected under rotor 89 purlings changes, and promotes fuselage and realizes dogled.

The e` central axis is represented is to be the center with displacement pawl axle 62, tension displacement wisp 64 and be attached thereto the displacement pawl 61 that connects by backguy, driving displacement pawl axle 62 rotates, rotation along with displacement pawl axle 62, drive fan-shaped displacement shift fork 60 on 62 on the displacement pawl axle and press down down arcs of recesses tooth on the rotor displacement dish outer shroud 43, thereby when driving whole pitch-changing mechanism and move down, ring 41 spurs backspin wing displacement bulb push rod 46 downwards in the following rotor displacement dish, following rotor displacement bulb push rod 46, stir the blade Adjustable length rod A77 that is attached thereto, driving blade folder A74 moves down, central axis f with propeller hub A71, f` is the center, reaches the effect that changes rotor 89 pitches.

Embodiment four: the coaxial aircraft of cross tilting type of present embodiment, by partition ring 102, partition ring front frame 18, partition ring after poppet 19, arm 103 verts, suspension rod 105 verts, ball cage 29 verts, last rotor angular wheel shaft 91, rotor commutation counter gear case 90 and handgrip control mechanism are formed the partition ring control mechanism that verts, described partition ring 102 along two spindle noses of axis of pitch direction respectively with the partition ring front frame 18 of its below, partition ring after poppet 19 connects, partition ring 102 two spindle noses along the longitudinal axis are along axis direction transverse axis bolt 108 mounting holes that vert before and after having, have two trough type holes that the suspension rod 105 that verts upwards is installed on two spindle noses of longitudinal axis direction in addition, long slot bore is passed in two suspension rod 105 lower ends of verting, two front and back bottom axis hole that transverse axis bolt 108 penetrates the suspension rod 105 that verts in axle center hole and the hole respectively in along the longitudinal axis two spindle noses that verts is connected with partition ring 102, and by front and back transverse axis bolt spring card 109 fixed limits that vert, two suspension rods 105 that vert are upward through the arm gum cover 104 and by suspension rod nut 106 lockings of verting of verting in the arm 103 that verts respectively, after the suspension rod 105 that verts is locked with the suspension rod nut 106 that verts, passing the suspension rod top of verting with the suspension rod spring cotter 107 that verts comes spacing, the arm 103 that will vert fuses with the suspension rod 105 that verts, arm upper end and the rotor of the rotor commutation reversing device counter gear case 90 that commutates that verts is connected, and the axial line of four spindle noses of the partition ring 102 under the coupled condition is consistent with the ball journal heart of the ball cage 29 that verts.

As shown in Figure 7: partition ring front frame 18, partition ring after poppet 19 all are equipped with cross ring flexible joint internal axle sleeve 20, partition ring front frame 18 and partition ring after poppet 19 all are processed with top v type limited step up towards partition ring 102 directions, are used for limiting the amplitude of verting about partition ring 102 lower planes.Partition ring 102 is along a, two spindle noses of a` central transverse axis direction respectively with partition ring front frame 18, partition ring after poppet 19 connects, partition ring 102 is along b, two spindle noses of b` longitudinal center axis direction are along central axial direction transverse axis bolt 108 mounting holes that vert before and after having, b, have the vert trough type hole of suspension rod 105 of two installations on two spindle noses of b` longitudinal center axis direction in addition, long slot bore is passed in two suspension rod 105 lower ends of verting, transverse axis bolt 108 is verted respectively along b in two front and back, penetrate the suspension rod 105 bottom axis holes that vert in axle center hole and the hole in two spindle noses of b` longitudinal center axis direction, after partition ring 102 is connected, by front and back transverse axis bolt spring card 109 fixed limits that vert, two suspension rods 105 that vert are upward through the arm gum cover 104 and by suspension rod nut 106 lockings of verting of verting in the arm 103 that verts respectively, the arm gum cover 104 that verts is used for cushioning the suspension rod 105 that verts and lifts vibrations in the process up and down, after the suspension rod 105 that verts is locked with the suspension rod nut 106 that verts, passing suspension rod 105 tops of verting with the suspension rod spring cotter 107 that verts comes spacing, the arm 103 that will vert fuses with the suspension rod 105 that verts, arm 103 upper ends and the rotor commutation counter gear case 90 that verts is connected formation cross inclining rotary mechanism.The axial line of four spindle noses of the partition ring 102 under the coupled condition is consistent with the ball journal heart of the ball cage 29 that verts, vert arm 103 lower ends towards the partition ring direction all be processed with top down v type limited step and partition ring 2 on plane contact, can limit partition ring 102 anteversion and retroversion gyrations.As shown in Figure 9: the ball journal heart with the ball cage 29 that verts is the center, move both hands all around and make control stalk 63 partition ring 102 both can vert along about a, a` central transverse axis direction, partition ring 102 also can vert before and after b, b` longitudinal center axis direction direction.

Embodiment five: referring to Fig. 4～Figure 10, the coaxial aircraft of cross tilting type of present embodiment adopts umbrella support formula fuselage support shock-damping structure.As shown in Figure 4: fuselage column 1 from top to down, pass and drive seat board 12, fuselage column hinged seat 2, the slide hinged seat 3 of fuselage column, utilize the scaffold pole seat 6 on the support tube, scaffold pole 5, support connector 7 is the support and connection of umbrella umbrella frame shape with 3 support tubes 4, driving seat board 12 is fixed by bolts on the fuselage column hinged seat 2, the foot-driven lever 9 that two ends have steamboat is installed in front support pipe 4 lower ends, next two support tube 4 lower ends are equipped with a tray deck 8 respectively, be equipped with one between the slide hinged seat 3 of fuselage column hinged seat 2 and fuselage column and be enclosed within the outer support damping spring 10 of column, fuselage column 1 bottom is equipped with a column damping limit base 11, when fuselage be subjected to from the carrying countryside pressure the time, three support tubes 4 can outwards strut separately, pulling scaffold pole 5, the slide hinged seat 2 of scaffold pole 5 pulling fuselage columns can upwards slide, support damping spring 10 between the slide hinged seat 3 of extruding fuselage column hinged seat 2 and fuselage column, the effect of realization elastic buffer damping.

As Fig. 5, shown in Figure 6: fuselage column 1 top is equipped with column sleeve pipe 13 and connects speed reduction gearing clamping plate 14, engine bed plate 17 respectively, be lined with column rubber pad 15 between the joint face, between the fuselage column 1 top bonded assembly speed reduction gearing clamping plate 14, what be equipped with that three of conversion one-level double reduction have a belt pulley bearing 38 locks the castellated shaft of double reduction driving wheel 27, double reduction follower shaft 33, centrifugal clutch combined cover 24 respectively to 36, three belt pulley jam nuts 39 of button-type Pulley shaft bearing.The front end middle-end and the rear end of speed reduction gearing clamping plate 14 are connected with partition ring front frame 18 respectively, the supporting plate 22 of partition ring after poppet 19 and speed reduction gearing clamping plate, column sleeve pipe lower engine supporting plate 17 is used for fixing the driving engine 23 that has centrifugal block for clutch use, driving engine damping gum cover 16 and column rubber pad 15 are installed between the engine bed plate 17, vibrations when being used for cushioning driving engine 23 work that have centrifugal block for clutch use, preceding cross ring flexible joint connecting panel 21 plays partition ring front frame 18 and strengthens being connected with the column sleeve pipe 13 on the fuselage column 1, driving seat board 12 is fixed on the fuselage column hinged seat 2, for adjusting center of gravity, fuel tank 40 is installed in speed reduction gearing clamping plate supporting plate 22 and operator's saddle 12 back.

Propeller hub structure of the present invention provides two sets of plan, and as Figure 11, shown in Figure 12: a cover propeller hub mechanism is made up of propeller hub A 71, propeller hub flange A 72, blade spindle damping gum cover A 73, a blade folder axle A 74, blade folder axle sleeve A 75, blade folder A 76, blade Adjustable length rod A 77, a blade folder axle caging bolt A 78, four rib propeller hub bolt of rear end plates 79.Propeller hub A71 up and down is towards the both sides of rotor angular wheel shaft 91,96 directions up and down, be processed with six square openings separately, utilize four square rib propeller hub bolt of rear end plates 79, after passing up and down propeller hub A71 six square openings blocking six square grooves leaving separately on the rotor angular wheel shaft 91,96 up and down separately, fixed.Two ends are polished rod spindle nose one end that spherical blade presss from both sides axle A74 in the middle of being threaded spindle nose and polished rod spindle nose respectively, penetrate and penetrate blade spindle damping gum cover A73 again behind the blade folder axle sleeve A75 and be installed in the propeller hub A71, be fixed on the propeller hub A71 by the propeller hub flange A72 that has the spill sphero-cylindrical lens, after the screwed end of blade folder axle A74 stretches out propeller hub A71, after utilizing screw thread and blade folder 75 to be connected and fixed, and it is spacing by blade folder axle caging bolt A78 locking, the centre of blade folder axle A74 be spherical with propeller hub flange A75 on ball head structure that can obtain to reverse up and down significantly of spill sphero-cylindrical lens formation, satisfy the needs of cross hinge function.Blade folder axle A74 inserts the part polished rod spindle nose in the propeller hub A71, push blade spindle damping gum cover A73 up and down, and can be in blade presss from both sides axle sleeve A75 free torsion, make rotor lift down at blade Adjustable length rod A77, reverse rotor folder axle A74 and produce an angle of attack displacement.

As Figure 13, shown in Figure 14: another set of propeller hub mechanism is made up of propeller hub B 80, concave ball shape bearing shell B 81, a blade folder axle damping gum cover B 82, a blade folder axle B 83, blade folder B 84, blade folder flange B 85, blade folder axle bearing B 86, blade Adjustable length rod B 87, a blade folder axle captive nut B 87, four rib propeller hub bolt of rear end plates 79.Propeller hub B 80 is connected and fixed mode with rotor angular wheel shaft 91,96 up and down and propeller hub A71 is consistent, adopts four rib propeller hub bolt of rear end plates 79 that propeller hub B80 is fixed together with rotor angular wheel shaft 91,96 up and down equally.A blade folder axle B 83 is that to be bulb type one end be screwed spindle nose to an end, concave ball shape bearing shell B 81 is enclosed within the spindle nose that is the bulb type one end of blade folder axle B 83, and utilize being threaded togather in concave ball shape bearing shell B 81 self and the propeller hub B 80, the bulb type one end spindle nose of blade folder axle B 83 is locked in the propeller hub B 80, blade folder axle damping gum cover B 82 is enclosed within on the blade folder axle B 83, and be installed in the propeller hub B 80, the spindle nose that is the bulb type one end and the concave ball shape bearing shell B 81 of blade folder axle B 83 are nested together, form a ball head structure that can reverse up and down significantly, satisfy the needs of cross hinge function, blade folder axle damping gum cover B 82 is as the spacing and buffering of blade folder axle B 83 activity up and down in propeller hub B 80, blade folder axle B 83 other ends are screwed spindle nose, after passing blade folder flange B 85 and two blades folder axle bearing B 86, be fixed in the blade folder B 84 by blade folder axle captive nut B 88, during push-and-pull blade Adjustable length rod B 87, blade folder B 84 can blade folder axle B 83 be the center free torsion, drives bonded assembly rotor 89 and produces angle of attack displacement.

Claims

1. coaxial aircraft of cross tilting type, contain rotor, following rotor, empennage, the described rotor of going up, following rotor is arranged on fuselage column top, fuselage column bottom is provided with the driving seat board, stationary engine on described fuselage column and driving seat board, fuel tank and speed reduction gearing, engine output power passes through speed reduction gearing, the ball cage that verts is connected rotor and following rotor with rotor commutation counter gear case, it is characterized in that: the output flower wheel center of described speed reduction gearing is provided with a unilateral bearing, cover is connected by spline with the output follower shaft in the described unilateral bearing, the unilateral bearing overcoat is connected by spline with the inwall of output flower wheel, the described ball cage that verts inserts and combines with its castellated shaft inwall from the output follower shaft upper end of speed reduction gearing, the rotor that is in transmission connection commutation counter gear case; Be provided with the rotor angular wheel shaft in the described rotor commutation counter gear case, commutation counter-rotating bevel gear, backspin parafoil gear wheel shaft, the lower end spline axle head of last rotor angular wheel shaft stretches out from described rotor commutation counter gear case bottom and is connected with the ball cage inner spline housing that verts, last rotor angular wheel shaft is upward through down the rotor gear wheel shaft, two commutation counter-rotatings of opposed installation bevel gear is meshed with two face of gears of rotor angular wheel shaft up and down, two commutation counter-rotating bevel gears are installed on the rotor commutation counter gear case by its bearing seat, and power comes up and the engagement of opposed two commutation counter-rotating bevel gears via the bottom spline transmission of last rotor angular wheel shaft; Described empennage is connected down on the rotor gear wheel shaft bearing seat cover plate by the empennage support tube, along with rotor shaft angular wheel shaft up and down verts together, v type tail support tube afterbody is equipped with v type tail axle, v type tail axle top is installed and is had two stay rods and the prone v type tail of bevel gear steering gear, be provided with both hands control mechanism with described empennage interlock, both hands are provided with the both hands of control mechanism to control stalk and turn to the backguy seat, and both hands connect control stalk the backguy turn on backguy seat and the v type tail steering gear between two stay rods.

2. the coaxial aircraft of cross tilting type according to claim 1, it is characterized in that: cooperate with described rotor commutation counter gear case to be provided with the displacement control mechanism, described displacement control mechanism comprises that rotary wing changing is apart from dish structure and following rotor displacement dish structure, two commutation counter-rotating bevel gears in rotor commutation counter gear case with on, install rotary wing changing between the backspin parafoil gear wheel shaft face of gear successively apart from the dish outer shroud, last rotary wing changing is apart from the dish bearing, last rotary wing changing encircles in dish, last rotary wing changing is apart from dish inner ring card, last rotary wing changing is apart from lever pin, rotary wing changing is apart from disc mechanism on the composition, install the rotor Adjustable length rod in the last rotor angular wheel shaft, the last end grain of last rotor Adjustable length rod stretches out the rotor angular wheel shaft, pass rotary wing changing behind pull back spring, by last rotary wing changing apart from the stem nut cover locking, last rotor Adjustable length rod cross bar passes rotary wing changing behind the stem nut cover, two ends are connected apart from the ball-head tension rod upper end with two last rotary wing changings respectively, last rotary wing changing is connected on the blade Adjustable length rod of upper strata rotor hub apart from the ball-head tension rod lower end, last rotary wing changing apart from lever pin pass rotary wing changing apart from the dish in the ring with last rotor angular wheel shaft on trough type displacement hole be connected with last rotor Adjustable length rod lower end, last rotary wing changing combines apart from the dish bearing with last rotary wing changing with the make-up form apart from the dish inner and outer ring, and above respectively rotary wing changing apart from dish inner and outer ring Spring Card will go up rotary wing changing apart from the dish bearing fixing at last rotary wing changing apart from coiling in the middle of the inner and outer ring, last rotary wing changing utilizes two chutes in the rotor commutation counter gear case apart from two pipe links of dish on the outer shroud, being upward through backspin parafoil gear wheel shaft bearing seat is connected with the arcs of recesses alveolar surface of following rotor displacement outer shroud exterior front and the pawl that is connected at rear portion with following rotor gear wheel shaft bearing seat cover plate, on the outside of ring two screw seats are up arranged in the following rotor displacement, be used for installing down rotor displacement bulb push rod, following rotor displacement bulb push rod connects two blade Adjustable length rods of lower floor's rotor respectively, between ring and the following rotor displacement dish outer shroud rotor displacement dish bearing is housed down in the following rotor displacement dish, and respectively by rotor displacement dish inner ring card and following rotor displacement dish outer ring spring fasten spacing down.

3. the coaxial aircraft of cross tilting type according to claim 1 and 2 is characterized in that: both hands control mechanism by both hands control stalk, starting switch, displacement pawl axle, fan-shaped displacement shift fork, displacement pawl shaft alignment bolt, displacement pawl, displacement wisp, throttle shifting fork bar, control stalk pedestal, control stalk axle, control stalk spindle nut, turn to the backguy seat, turn to backguy seat Spring Card and upper and lower rotary wing changing to form apart from disc mechanism; The control stalk axle passes control stalk pedestal the first half, backspin parafoil gear wheel shaft bearing cover, after control stalk pedestal the latter half, utilize the locking of control stalk spindle nut to constitute the control stalk pedestal, the first half of control stalk pedestal is installed displacement pawl axle, fan-shaped displacement shift fork is installed in the middle of the displacement pawl axle, both sides are equipped with two and turn to the backguy seat, two displacement pawls are equipped with at two ends, and utilize backguy connecting strap on the control stalk to be connected respectively with both hands, fan-shaped displacement shift fork and displacement pawl are bolted on the displacement pawl axle by displacement pawl shaft alignment, two turn to the backguy seat to be rotatably connected, and be provided with in both sides that restriction horizontally slips turn to backguy seat Spring Card, the latter half of control stalk pedestal is equipped with both hands control stalk, double handle control stalk left and right handles all is equipped with the displacement wisp, wherein the left hand handgrip is equipped with engine start switch, and right hand handgrip is equipped with the throttle shifting fork bar.

4. the coaxial aircraft of cross tilting type according to claim 3, it is characterized in that: by partition ring, the partition ring front frame, the partition ring after poppet, arm verts, suspension rod verts, the ball cage verts, last rotor angular wheel shaft, rotor commutation counter gear case and handgrip control mechanism are formed the partition ring control mechanism that verts, described partition ring along two spindle noses of axis of pitch direction respectively with the partition ring front frame of its below, the partition ring after poppet connects, partition ring two spindle noses along the longitudinal axis are along the axis direction transverse axis bolt mounting holes that verts before and after having, have two trough type holes that the suspension rod that verts upwards is installed on two spindle noses of longitudinal axis direction in addition, long slot bore is passed in two suspension rod lower ends of verting, two front and back bottom axis hole that the transverse axis bolt penetrates the suspension rod that verts in axle center hole and the hole respectively in along the longitudinal axis two spindle noses that verts is connected with partition ring, and fasten spacing by the front and back transverse axis bolt spring that verts, two suspension rods that vert are upward through the arm gum cover and by the suspension rod nut locking of verting of verting in the arm that verts respectively, vert suspension rod with vert behind the suspension rod nut locking, passing the suspension rod top of verting with the suspension rod spring cotter that verts comes spacing, the arm that will vert fuses with the suspension rod that verts, arm upper end and the rotor of the rotor commutation reversing device counter gear case that commutates that verts is connected, and the axial line of four spindle noses of the partition ring under the coupled condition is consistent with the ball journal heart of the ball cage that verts.

5. according to claim 1, the coaxial aircraft of 2 or 4 described cross tilting types, it is characterized in that: fuselage support adopts umbrella support formula damping machine mechanism, by the fuselage column, fuselage column hinged seat, the slide hinged seat of fuselage column, support tube, scaffold pole, the scaffold pole seat, the support tube connector, tray deck, foot-driven lever, the support damping spring, column damping limit base, the driving seat board is formed, the fuselage column passes the driving seat board from top to bottom, fuselage column hinged seat, the slide hinged seat of fuselage column, the scaffold pole seat, scaffold pole, the support connector is the support and connection of umbrella umbrella frame shape with 3 support tubes, driving seat board is fixed by bolts on the fuselage column hinged seat, the foot-driven lever that two ends have steamboat is installed in the front support pipe lower end, next two support tube lower ends are equipped with a tray deck respectively, be equipped with one between the slide hinged seat of fuselage column hinged seat and fuselage column and be enclosed within the outer support damping spring of column, fuselage column bottom is equipped with a column damping limit base.

6. the coaxial aircraft of cross tilting type according to claim 5, it is characterized in that: propeller hub mechanism comprises propeller hub A, propeller hub flange A, blade spindle damping gum cover A, blade folder axle A, blade folder axle sleeve A, blade folder A, blade Adjustable length rod A, blade folder axle caging bolt A, four rib propeller hub bolt of rear end plates, propeller hub A up and down is towards rotor angular wheel shaft direction up and down, both sides, the left and right sides are processed with six square openings separately, utilize four square rib propeller hub bolt of rear end plates pass up and down propeller hub A separately six square openings block six square grooves leaving separately on the rotor angular wheel shaft up and down and fixed; It in the middle of two ends screwed spindle nose of difference and the polished rod spindle nose polished rod spindle nose one end that spherical blade presss from both sides axle A, penetrate and penetrate blade spindle damping gum cover A again behind the blade folder axle sleeve A and be installed in the propeller hub A, be fixed on the propeller hub A by the propeller hub flange A that has the spill sphero-cylindrical lens, after screwed spindle nose one end of blade folder axle A stretches out propeller hub A, after utilizing screw thread and blade folder to be connected and fixed, and spacing by blade folder axle caging bolt A locking, the ball head structure that can reverse up and down of spill sphero-cylindrical lens formation on spherical of the centre of blade folder axle A and the propeller hub flange A; Blade folder axle A inserts the part polished rod spindle nose in the propeller hub A.

7. the coaxial aircraft of cross tilting type according to claim 5, it is characterized in that: propeller hub mechanism comprises propeller hub B, concave ball shape bearing shell B, blade folder axle damping gum cover B, blade folder axle B, blade folder B, blade folder flange B, blade folder axle bearing B, blade Adjustable length rod B, blade folder axle captive nut B, four rib propeller hub bolt of rear end plates, propeller hub B is connected and fixed mode with rotor angular wheel shaft up and down and propeller hub A is consistent, adopt equally four rib propeller hub bolt of rear end plates with propeller hub B and up and down the rotor angular wheel shaft be fixed together; Blade folder axle B is that an end is the bulb type, the other end is screwed spindle nose, what concave ball shape bearing shell B was enclosed within blade folder axle B is bulb type one end spindle nose, and utilize being threaded togather in concave ball shape bearing shell B self and the propeller hub B, the bulb type one end spindle nose that is of blade folder axle B is locked in the propeller hub B, blade folder axle damping gum cover B is enclosed within on the blade folder axle B, and be installed in the propeller hub B, the blade folder axle B other end is screwed head, after passing blade folder flange B and two blades folder axle bearing B, a B is fixed in the blade folder B by blade folder axle B captive nut.