CN104129498B - A kind of rotor control mechanism for coaxal helicopter - Google Patents
A kind of rotor control mechanism for coaxal helicopter Download PDFInfo
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- CN104129498B CN104129498B CN201410353728.2A CN201410353728A CN104129498B CN 104129498 B CN104129498 B CN 104129498B CN 201410353728 A CN201410353728 A CN 201410353728A CN 104129498 B CN104129498 B CN 104129498B
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Abstract
The present invention discloses a kind of rotor control mechanism for coaxal helicopter, comprises outer axle, lower rotor distance-variable rocker arm that interior axle, inside and outside axle support seat, outer automatic inclinator, interior automatic inclinator, intermediate ring, the 3rd coupling device and some lower links, some first coupling devices, some sheer poles, some 2nd coupling devices, some lower rotor propeller hubs of being installed on outer axle propeller hub head, some upper rotor propeller hubs of being installed on interior axle propeller hub head, some and upper rotor propeller hub the inner are connected upper rotor distance-variable rocker arm, some and lower rotor propeller hub the inner are connected. Under the present invention, rotor control mechanism is distributed in fuselage nose cone and lower rotor nose cone, and upper rotor control mechanism is distributed in rotor shaft. By the manipulation that cooperatively interacts of lower link and long draw, and it is total apart from synchronous manipulation, always apart from differential manipulation and cycle displacement manipulation namely can to realize upper and lower rotor by each parts.
Description
Technical field
The present invention relates to technical field of aircraft design, particularly relate to the rotor control mechanism of coaxal helicopter.
Background technology
Operating mechanism is the important component part of vertiplane, and officer must control the flight of vertiplane by maneuvering system, keeps or change the equilibrium state of vertiplane. Coaxal helicopter a kind of has the rotor class aircraft of upper and lower two pairs around coaxial line reverse rotation rotor. Owing to coaxal helicopter has upper and lower two secondary rotors, its rotor maneuvering system is more more complicated than conventional vertiplane.
General single rotor helicopter hub resistance accounts for the 20%��30% of vertiplane always useless resistance, and coaxal helicopter has two propeller hubs, and propeller hub resistance accounts for more than the 50% of total useless resistance. Along with the raising of flight velocity, fuselage resistance can reduce further after drag reduction designs, and the proportion that propeller hub resistance accounts for total useless resistance can rise further, so it is very important to the total useless resistance reducing vertiplane to reduce propeller hub resistance. According to current technology, coaxal helicopter rotor control mechanism is outside rotor shaft, and area is big windward, and is difficult to propeller hub is taked Drag reduction devices, it is difficult to reduce rotor system resistance. Therefore, it is necessary to improve the operating mechanism of coaxal helicopter, to reduce rotor system resistance.
Summary of the invention
The technical problem that the present invention solves: overcome the deficiencies in the prior art, thering is provided a kind of rotor control mechanism for coaxal helicopter, operating mechanism is rationally distributed, compact, manoeuvrable, does not expose, can effectively reduce the useless resistance of coaxal helicopter, it is to increase vertiplane performance.
The technical scheme of the present invention is: a kind of rotor control mechanism for coaxal helicopter, it is characterised in that: comprise outer axle, lower rotor distance-variable rocker arm that interior axle, inside and outside axle support seat, outer automatic inclinator, interior automatic inclinator, intermediate ring, the 3rd coupling device and the identical lower link of quantity, the first coupling device, sheer pole, the 2nd coupling device, the lower rotor propeller hub being installed on outer axle propeller hub head, the upper rotor propeller hub that is installed on interior axle propeller hub head are connected upper rotor distance-variable rocker arm is connected with lower rotor propeller hub the inner with upper rotor propeller hub the inner; The inner hollow of inner shaft, outer shaft, interior axle is sleeved in outer axle by inside and outside axle supporting base, does not collide when inside and outside axle supporting base can ensure that interior axle and outer axle coaxially rotate backward; Outer inclinator automatically is positioned at the lower section of outer axle propeller hub head, and is sleeved on outer axle, and outer automatic inclinator can tilt to either direction and can slide up and down along outer axle; Lower link is connected on outer automatic inclinator so that when moving up and down lower link, and outer automatic inclinator can occur to tilt or slide up and down; It is inner that interior inclinator automatically is positioned at outer axle propeller hub head, and is sleeved on interior axle, and interior automatic inclinator can tilt to either direction and can slide up and down along interior axle; Outer inclinator automatically is connected by the first coupling device with interior automatic inclinator so that outer inclinator and interior automatic inclinator automatically synchronously can tilt in the same way or synchronously slide up and down; First coupling device is connected with lower rotor distance-variable rocker arm simultaneously so that when outer inclinator automatically occurs to tilt or slide up and down, lower rotor distance-variable rocker arm correspondingly shakes, and then changes lower rotor distance; Intermediate ring is positioned at the top of automatic inclinator, and is sleeved on interior axle; In the joint of interior axle and intermediate ring, interior axle being provided with the through hole identical with sheer pole quantity, through-hole aperture is greater than the bar footpath of sheer pole; It is inner that 2nd coupling device is positioned at axle; It is connected in the middle part of sheer pole on intermediate ring; The outer end of sheer pole is connected with interior automatic inclinator, the through hole that the inner of sheer pole is arranged on interior axle is connected with the lower end of the 2nd coupling device, the upper end of the 2nd coupling device is connected with upper rotor distance-variable rocker arm, by the cooperation of the first coupling device, sheer pole, intermediate ring, the 2nd coupling device, when outer automatic inclinator, interior automatic inclinator can be made synchronously to tilt or slide up and down, upper rotor distance-variable rocker arm and the shake of lower rotor distance-variable rocker arm synchronous backward, and then the upper and lower rotor distance of synchronous change; Upper rotor distance-variable rocker arm is connected with the 3rd coupling device simultaneously, by moving up and down the 3rd coupling device, it is possible to changes separately upper rotor distance and is not had an impact by lower rotor; Carry out upper and lower rotor total apart from when synchronously handling, move up and down all lower links simultaneously, outer automatic inclinator, interior automatic inclinator are synchronously slided up and down, first coupling device is the lower rotor distance-variable rocker arm of synchronously shake thereupon, thus change the lower total distance of rotor, 2nd coupling device is the upper rotor distance-variable rocker arm of synchronous backward shake thereupon, thus synchronously changes the upper total distance of rotor; When carrying out upper and lower rotor always apart from differential manipulation, move up and down all lower links simultaneously, then move up and down the 3rd upper rotor rocking arm of coupling device shake, thus rotor always distance and lower rotor distance in differential change; When the cycle of carrying out displacement is handled, by adjusting the relative position of each lower link, outer automatic inclinator, interior automatic inclinator are synchronously tilted in the same way, first coupling device is the lower rotor distance-variable rocker arm of synchronously shake thereupon, thus change displacement of lower rotor cycle, 2nd coupling device is the upper rotor distance-variable rocker arm of synchronous backward shake thereupon, thus synchronously changes upper rotor cycle displacement.
Preferably, outer automatic inclinator, interior automatic inclinator include ball hinge, inner ring, bearing, outer shroud; Inner ring sleeve is contained in ball hinge and above and can tilt to either direction around ball hinge, and inner ring, outer shroud are connected by bearing; The ball hinge of outer inclinator automatically is sleeved on outer axle and can slide up and down along outer axle, and the ball hinge of interior automatic inclinator is sleeved on interior axle and can slide up and down along interior axle; Between the outer shroud that first torsion arm is connected to outer automatic inclinator and fuselage, between the inner ring that the 2nd torsion arm is connected to outer automatic inclinator and outer axle; Between the outer shroud that 3rd torsion arm is connected to interior automatic inclinator and outer axle; First coupling device comprises middle pull bar, lower link bar; 2nd coupling device comprises pull bar, upper cross bar, long draw; 3rd coupling device is long draw, and long draw top is provided with the auricle identical with upper cross bar quantity; Lower rotor distance-variable rocker arm is provided with auricle and lower auricle, and upper rotor distance-variable rocker arm is provided with auricle; The outer shroud of outer inclinator automatically is connected with lower link; The bottom of outer axle propeller hub head is provided with the through hole identical with middle pull bar quantity, and middle pull bar is through through hole, and through-hole aperture is greater than middle pull bar bar footpath; The outer inner ring of inclinator automatically is connected with the lower end of middle pull bar, and middle pull bar upper end is connected with the lower auricle of lower rotor distance-variable rocker arm; The lower end of lower link bar is connected with the upper auricle of lower rotor distance-variable rocker arm, and the upper end of lower link bar is connected with the outer shroud of interior automatic inclinator; It is equipped with the auricle identical with sheer pole quantity in interior inclinator automatically, the outer end of sheer pole is connected with the auricle in interior automatic inclinator upper inner ring, the through hole that the inner of sheer pole is arranged on interior axle is connected with the lower end of upper pull bar, the upper end of upper pull bar is connected with in the middle part of upper cross bar, the inner of upper cross bar is connected with the auricle of long draw, and the outer end of upper cross bar is connected with the auricle of upper rotor distance-variable rocker arm; Being installed with position limit device and lower caging device on long draw, it is inner that position limit device, lower caging device are positioned at axle. This optimal technical scheme makes the mechanical layout of the present invention more rationally, more be convenient to handle, install, safeguard.
Preferably, being connected with, at the 2nd torsion arm, the annulus that can dismantle, annulus is anchored on outer axle. This optimal technical scheme can make the connection of the 2nd torsion arm and outer axle more firm, more even by power.
Preferably, upper rotor propeller hub, on the outside of rotor propeller hub head install rotor nose cone; Rotor nose cone under the outside installation of lower rotor propeller hub, lower rotor propeller hub head; Outer inclinator automatically is wrapped in fuselage nose cone. This optimal technical scheme is conducive to realizing vertiplane overall appearance airflow design, reduces the useless resistance of complete machine.
Preferably, intermediate ring can be dismantled, and intermediate ring is provided with the auricle identical with sheer pole quantity, is connected on the auricle of intermediate ring in the middle part of sheer pole. This optimal technical scheme is convenient to the installation and removal of intermediate ring, and sheer pole is moved around intermediate ring flexibly.
Preferably, inside and outside axle supports seat and comprises bearing support, bearing, and outer axle propeller hub head upper end forms a boss, inside and outside axle supports seat and is installed on the boss of outer axle propeller hub head upper end, the inside of bearing support is provided with bearing, and interior axle is through the inner ring of bearing, and the inner ring with bearing closely cooperates. When this optimal technical scheme can make inside and outside axle high speed rotating, stability is higher.
Preferably, upper rotor propeller hub, lower rotor propeller hub all comprise propeller hub centrepiece, bearing, propeller hub housing and securing gear, and bearing is installed on propeller hub enclosure interior; Propeller hub centrepiece outer end forms flange, is sticked in the bearing inner ring of outermost end bearing, for preventing propeller hub centrepiece slid inward; Propeller hub centrepiece is through bearing inner ring and closely cooperates with bearing inner ring, and securing gear is installed on the inner of propeller hub centrepiece, and bearing and securing gear prevent propeller hub centrepiece from outwards sliding jointly. This optimal technical scheme is conducive to realizing rotor distance-variable rocker arm to the convenient control of rotor.
Preferably, the outer end of upper rotor distance-variable rocker arm, lower rotor distance-variable rocker arm all forms a quadrangular projection, quadrangular projection embeds the inner of propeller hub centrepiece, quadrangular projection center is provided with cylindrical hole, and upper rotor distance-variable rocker arm is fastened on upper rotor propeller hub centrepiece, by lower rotor distance-variable rocker arm through cylindrical hole and is fastened on lower rotor propeller hub centrepiece by screw respectively.
The present invention compared with prior art useful effect be:
(1) in the present invention, rotor control mechanism is positioned at rotor axle completely, lower rotor control mechanism part is positioned at the outer axle of rotor, part is positioned at outside rotor shaft, fuselage nose cone, make rotor control mechanism without exposing, and by installing propeller hub nose cone, eliminate tradition pitch-change-link to the disturbance of air-flow, and area is less windward, effectively reduce the useless resistance of rotor system when flying, and make rotor, lower rotor and the variations in flow between rotor, fuselage more regular, it is to increase vertiplane performance.
(2) arrangement of mechanism of the present invention is reasonable, compact, manoeuvrable, effectively reduces the space shared by coaxal helicopter operating mechanism, is convenient to realize vertiplane overall appearance airflow design, reduces the useless resistance of complete machine.
(3) the present invention can realize being rigidly connected of upper and lower rotor and rotor shaft, and rotor is sensitiveer to manipulation reaction.
Accompanying drawing explanation
Fig. 1 a is three dimensional isometric view of the present invention;
Fig. 1 b is three-dimensional portion sectional view of the present invention;
Fig. 1 c is three dimensional sectional view of the present invention;
Fig. 1 d is the partial enlargement figure at A place in Fig. 1 c;
Fig. 1 e is the partial enlargement figure at B place in Fig. 1 c;
Fig. 2 a is outer automatic inclinator and coupled parts three-dimensional plot;
Fig. 2 b is outer automatic inclinator and coupled parts sectional view;
Fig. 3 a is lower rotor propeller hub and distance-variable rocker arm three-dimensional plot;
Fig. 3 b is lower rotor propeller hub and distance-variable rocker arm sectional view;
Fig. 4 is lower rotor distance-variable rocker arm and connects pull bar three-dimensional plot;
Fig. 5 a is interior automatic inclinator and coupled parts three-dimensional plot;
Fig. 5 b is interior automatic inclinator and coupled parts sectional view;
Fig. 6 is intermediate ring and sheer pole, upper pull bar three-dimensional plot;
Fig. 7 is upper rotor distance-variable rocker arm and long draw, cross bar, pull bar three-dimensional plot;
Fig. 8 is outer axle and interior axle three-dimensional plot;
Fig. 9 a is that inside and outside axle supports seat three-dimensional plot;
Fig. 9 b is that inside and outside axle supports seat sectional view.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
As shown in Fig. 1 a, Fig. 1 b, Fig. 1 c: the blade of rotor up and down of coaxal helicopter is four. corresponding operating mechanism comprises outer axle 10, interior axle 3, inside and outside axle supports seat 5, outer inclinator 12 automatically, interior inclinator 8 automatically, intermediate ring 7, and three lower links 23, four middle pull bars 21, four lower link bars 19, four sheer poles 39, four upper pull bars 17, four upper cross bars 15, one root length pull bar 24, position limit device 16, lower caging device, lower rotor propeller hub 6, upper rotor propeller hub 2, the upper rotary wing changing being connected with upper rotor propeller hub the inner is apart from Rocker arm 4, with the lower rotor distance-variable rocker arm 20 that lower rotor propeller hub the inner is connected, first torsion arm 22, 2nd torsion arm 11, 3rd torsion arm 9. wherein, lower link 23, middle pull bar 21, lower link bar 19, sheer pole 39, the two ends of upper pull bar 17 are rod end bearing, the outer end of upper cross bar 15, the first torsion arm 22, the 2nd torsion arm 11, the 3rd torsion arm 9 are rod end bearing with automatic inclinator coupling end, and each pull bar, torsion arm are connected with each other by rod end bearing, or it is connected with other parts so that each pull bar, torsion arm can rotate along rod end bearing to either direction. outer axle 10 and interior axle 3 are arranged on main speed reduction box, inside and outside axle supports seat 5 and is arranged on outer axle 10 top, outer inclinator 12 automatically is arranged on outer axle 10, interior inclinator 8 automatically is arranged on interior axle 3, it is positioned at outer axle 10 propeller hub head inner, intermediate ring 7 is arranged on interior axle 3, it is positioned at above automatic inclinator 8, upper rotor propeller hub 2 and lower rotor propeller hub 6 are arranged on the propeller hub head of axle 3 and outer axle 10 in rotor respectively, it is inner that upper rotor control member is arranged on interior axle, upper rotor propeller hub 2, upper rotor propeller hub head and lower rotor propeller hub 6, propeller hub nose cone 13 is all equipped with in the outside of lower rotor propeller hub head, 18, lower rotor propeller hub nose cone 18 do not affect its with outer axle 10 rotation situation under transition streamlined with fuselage nose cone, flight resistance can be effectively reduced.
As shown in Fig. 2 a, Fig. 2 b: outer inclinator 12 automatically is made up of ball hinge 29, the collar 30, inner ring 31, bearing 33, outer shroud 34 and bearing back-up ring 32,35. Ball hinge 29 is sleeved on outer axle 10, and can slide up and down along outer axle 10; Remaining part cuts with scissors with ball and 29 synchronously moves up and down, and 29 can be cut with scissors around ball, in addition axle axis be that symmetry axis tilts to either direction. Outer shroud 34 is connected with lower link 23, and the first torsion arm 22 is connected between outer shroud 34 and fuselage so that outer shroud 34 keeps not turning. 2nd torsion arm 11 one end is connected in inner ring 31, and the other end is connected with an annulus, and annulus is made up of dismountable two semicircular ring splicing, stitching portion is provided with auricle, with the use of bolted auricle, annulus is anchored on outer axle, so that inner ring 31 and outer axle 10 synchronous axial system.
As shown in Figure 3 a, 3 b: lower rotor propeller hub 6 and upper rotor propeller hub 2 quantity are four, and structure is identical, form by back-up ring, propeller hub housing 27 and securing gear 28 between propeller hub centrepiece 25, some bearings 26 and bearing. Propeller hub centrepiece 25 outer end is connected with rotor blade 1, and inner and lower rotor distance-variable rocker arm 20 is connected. Rotor propeller hub housing 27 is arranged on propeller hub head, and propeller hub centrepiece 25 is arranged in propeller hub housing 27. Between bearing back-up ring between some bearings 26 and keep off on the inner ring of bearing, to reduce the use quantity of bearing and can alter about preventing bearing. Bearing 26 in propeller hub housing 27 and between bearing back-up ring and securing gear 28 jointly prevent propeller hub centrepiece 25 outwards or slid inward, propeller hub centrepiece 25 freely can rotate around displacement axis. The inner protrusion of propeller hub housing forms disk shape propeller hub mounting face, propeller hub mounting face is along the circumferential direction provided with some threaded holes, for being connected with propeller hub head.
As shown in Fig. 1 b, Fig. 1 c, Fig. 4,5a, Fig. 5 b: interior automatic inclinator 8 is identical with outer automatic inclinator 12 structure, it is made up of ball hinge 40, the collar 45, inner ring 41, bearing 44, outer shroud 43 and bearing back-up ring 42,46. Ball hinge 40 is sleeved on interior axle 3 and can slide up and down along interior axle, remaining part cut with scissors 40 synchronous up and down motions with ball and 40 can be cut with scissors around ball, within axle axis be that symmetry axis tilts to either direction. Outer shroud 43 is connected with one end of torsion arm 9, and the other end of torsion arm 9 is connected with outer axle 10 by bolt, so that outer shroud 43 and outer axle 10 keep synchronous axial system. Inner ring 41 is connected with the outer end of sheer pole 39. The lower end of middle pull bar 21 is connected with the inner ring 31 of outer automatic inclinator 12, the through hole that the upper end of middle pull bar 21 is arranged through outer axle propeller hub head bottom is connected with the lower auricle arranged on lower rotor distance-variable rocker arm 20, the lower end of lower link bar 19 is connected with the upper auricle arranged on lower rotor distance-variable rocker arm 20, and the upper end of lower link bar 19 is connected with the outer shroud 43 of interior automatic inclinator 8. Lower rotor distance-variable rocker arm 20 is fixedly connected with propeller hub centrepiece 25. The outer end of lower rotor distance-variable rocker arm 20 all forms a quadrangular projection, quadrangular projection embeds the inner of propeller hub centrepiece, quadrangular projection center is provided with cylindrical hole, and lower rotor distance-variable rocker arm 20 is fastened on lower rotor propeller hub centrepiece by screw through cylindrical hole. Middle pull bar 21 moves up and down, it is possible to drive lower rotor distance-variable rocker arm 20 to rotate around displacement medullary ray, it is achieved the change of blade 1 oar distance. The motion of lower rotor distance-variable rocker arm 20 drives lower link bar 19 to move up and down, and the motion of lower link bar 19 drives again the motion of interior automatic inclinator outer shroud 43, and then drives the up and down motion synchronous with outer automatic inclinator 12 of whole interior automatic inclinator 8 or tilt.
As shown in Fig. 6, Fig. 8: intermediate ring 7 is sleeved on interior axle 3, interior axle 3 is provided with four square through holes at suit place. Intermediate ring is made up of dismountable two semicircular ring splicing, and stitching portion is provided with auricle, by using bolted auricle, intermediate ring 7 is anchored on interior axle 3. Being connected on the auricle of intermediate ring 7 in the middle part of sheer pole 39, the outer end of sheer pole 39 is connected with inner ring 41, and inner square through hole on interior axle 3 is connected with the lower end of upper pull bar 17. The motion of interior inclinator 8 inner ring 41 automatically drives sheer pole 39 to rotate around intermediate ring 7 ring wall, and then drives above pull bar 17 to move up and down.
As shown in Figure 7: the middle part of upper cross bar 15 is connected with the upper end of upper pull bar 17. The upper end of long draw arranges four pairs of auricles, and the auricle that the inner of upper cross bar 15 is arranged with the upper end of long draw 24 is connected. The outer end of upper cross bar 15 is connected apart from Rocker arm 4 with upper rotary wing changing. Upper rotary wing changing is fixedly connected with upper rotor propeller hub centrepiece apart from Rocker arm 4, and the outer end with upper cross bar 15 is connected. Upper rotary wing changing all forms a quadrangular projection apart from the outer end of Rocker arm 4, quadrangular projection embeds the inner of propeller hub centrepiece, quadrangular projection center is provided with cylindrical hole, and upper rotor distance-variable rocker arm is fastened on upper rotor propeller hub centrepiece through cylindrical hole by screw. The up and down motion of upper pull bar 17 drives upper rotary wing changing to rotate around displacement medullary ray apart from Rocker arm 4, it is achieved the change of blade oar distance. Long draw 24 moves up and down can change the total distance of upper rotor, and then changes the total apart from poor of upper and lower rotor, it is achieved the Heading control of vertiplane. In addition, as shown in Figure 1 b, long draw 24 being installed with the position limit device 16 and lower caging device that are cruciform, upper and lower stop means is positioned at axle 3, for increasing the rigidity of long draw 24, prevents long draw 24 from rocking. Wherein, position limit device 16 is positioned at rotary wing changing apart from below Rocker arm 4, above intermediate ring 7; Lower caging device is between interior automatic inclinator 8, outer automatic inclinator 12. Can also optionally increase some stop means.
As shown in Figure 8: the propeller hub head of outer axle 10 and interior axle 3 has four propeller hub mounting faces respectively, and it is provided with through hole in the middle of each propeller hub mounting face, it is evenly arranged some threaded holes around cylindrical hole periphery, threaded hole on propeller hub head mounting face mates mutually with the threaded hole on propeller hub mounting face, for the connection of outer axle propeller hub head and lower rotor propeller hub 6, and the connection of interior axle propeller hub head and upper rotor propeller hub 2. Outer axle 10 and interior axle 3 be reverse constant speed rotation around axle center.
As shown in Figure 9: inside and outside axle supports seat 5 and is made up of bearing support 36, bearing 37 and bearing back-up ring 38. Bearing support 36 is arranged on outer axle 10, and bearing 37 is arranged in bearing support 36 and fixes with bearing back-up ring 38, and bearing 37 coordinates with interior axle 3. Bearing support 36 rotates with outer axle 10. Inside and outside axle supports seat 5 and ensures that outer axle 10 and interior axle 3 do not collide when rotated.
Carrying out upper and lower rotor always apart from when synchronously handling, move up and down all lower links 23 simultaneously, outer automatic inclinator 12 is slided up and down, middle pull bar 21 is the lower rotor distance-variable rocker arm 20 of synchronous shake thereupon, thus the lower total distance of rotor of change; The shake of lower rotor distance-variable rocker arm 20 drives lower link bar 19 synchronously to move up and down, thus interior automatic inclinator 8 is synchronously slided up and down; Sliding up and down of interior inclinator 8 automatically, gives upper pull bar 17 by sheer pole 39 transmission, and upper cross bar 15 is given in upper pull bar transmission, and final above cross bar 15 transmission gives upper rotary wing changing apart from Rocker arm 4, thus synchronously changes the upper total distance of rotor.
When carrying out upper and lower rotor always apart from differential manipulation, move up and down all lower links 23 simultaneously, then move up and down long draw 24 and shake upper rotor rocking arm, thus rotor always distance and lower rotor distance in differential change.
When the cycle of carrying out displacement is handled, by the relative position that adjusts each lower link 23 (as a lower link moves downward, two other lower link upwards moves), outer automatic inclinator 12, interior automatic inclinator 8 are synchronously tilted in the same way, middle pull bar 21 is the lower rotor distance-variable rocker arm 20 of synchronous shake thereupon, thus change displacement of lower rotor cycle, lower rotor distance-variable rocker arm 20 is by the transmission successively of lower link bar 19, sheer pole 39, upper pull bar 17, upper cross bar 15, make rotary wing changing apart from the shake of Rocker arm 4 synchronous backward, thus synchronously change upper rotor cycle displacement.
Wherein, lower link 23 can be designed to more than three as required. For the manipulation of the coaxal helicopter of other quantity blades, correspondingly change the quantity of the upper rotary wing changing in the present embodiment apart from Rocker arm 4, lower rotor distance-variable rocker arm 20 and middle pull bar 21, lower link bar 19, sheer pole 39, upper pull bar 17, upper cross bar 15.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (8)
1. the rotor control mechanism for coaxal helicopter, it is characterized in that: comprise outer axle (10), interior axle (3), inside and outside axle supports seat (5), outer inclinator (12) automatically, interior inclinator (8) automatically, intermediate ring (7), 3rd coupling device, and some lower links (23), some first coupling devices, some sheer poles (39), some 2nd coupling devices, some lower rotor propeller hubs (6) being installed on outer axle propeller hub head, some upper rotor propeller hubs (2) being installed on interior axle propeller hub head, the upper rotor distance-variable rocker arm (4) that some and upper rotor propeller hub (2) the inner is connected, the lower rotor distance-variable rocker arm (20) that some and lower rotor propeller hub (6) the inner is connected,
The inner hollow of described interior axle (3), outer axle (10), interior axle (3) supports seat (5) by inside and outside axle and is sleeved in outer axle (10), and described inside and outside axle supports when seat (5) can ensure that described interior axle (3) and outer axle (10) coaxially rotate backward and do not collide;
Described outer automatic inclinator (12) is positioned at the lower section of described outer axle propeller hub head, and is sleeved on described outer axle (10), and described outer automatic inclinator (12) can tilt to either direction and can slide up and down along outer axle; Described lower link (23) is connected on described outer automatic inclinator (12) so that when moving up and down lower link (23), and described outer automatic inclinator (12) can occur to tilt or slide up and down;
It is inner that described interior automatic inclinator (8) is positioned at described outer axle propeller hub head, and is sleeved on described interior axle (3), and described interior automatic inclinator (8) can tilt to either direction and can slide up and down along interior axle (3); Described outer automatic inclinator (12) is connected by described first coupling device with interior automatic inclinator (8) so that outer inclinator (12) and interior automatic inclinator (8) automatically synchronously can tilt in the same way or synchronously slide up and down;
Described first coupling device is connected with described lower rotor distance-variable rocker arm (20) simultaneously, when making outer automatic inclinator (12) occur to tilt or slide up and down, described lower rotor distance-variable rocker arm (20) is correspondingly shaken, and then changes lower rotor distance;
Described intermediate ring (7) is positioned at the top of described automatic inclinator (8), and is sleeved on described interior axle (3), in the joint of interior axle (3) Yu intermediate ring (7), interior axle is provided with the through hole identical with described sheer pole (39) quantity on (3), and through-hole aperture is greater than the bar footpath of described sheer pole (39), it is inner that described 2nd coupling device is positioned at described axle (3), described sheer pole (39) middle part is connected on described intermediate ring (7), the outer end of described sheer pole (39) is connected with interior automatic inclinator (8), the inner of described sheer pole (39) is connected through the upper through hole arranged of described interior axle (3) with the lower end of described 2nd coupling device, the upper end of described 2nd coupling device is connected with described upper rotor distance-variable rocker arm (4), by described first coupling device, sheer pole (39), intermediate ring (7), the cooperation of the 2nd coupling device, outer automatic inclinator (12) can be made, when interior automatic inclinator (8) synchronously tilts or slides up and down, described upper rotor distance-variable rocker arm (4) and the shake of lower rotor distance-variable rocker arm (20) synchronous backward, and then in synchronous change, lower rotor distance, described upper rotor distance-variable rocker arm (4) is connected with described 3rd coupling device simultaneously, by moving up and down the 3rd coupling device, it is possible to changes separately upper rotor distance and is not had an impact by lower rotor,
Carry out upper and lower rotor total apart from when synchronously handling, move up and down all lower links simultaneously, outer automatic inclinator (12), interior automatic inclinator (8) are synchronously slided up and down, first coupling device is the lower rotor distance-variable rocker arm (20) of synchronously shake thereupon, thus change the lower total distance of rotor, 2nd coupling device is the upper rotor distance-variable rocker arm (4) of synchronous backward shake thereupon, thus synchronously changes the upper total distance of rotor; When carrying out upper and lower rotor always apart from differential manipulation, move up and down all lower links simultaneously, then move up and down the 3rd upper rotor rocking arm (4) of coupling device shake, thus rotor always distance and lower rotor distance in differential change; When the cycle of carrying out displacement is handled, by adjusting the relative position of each lower link, outer automatic inclinator (12), interior automatic inclinator (8) are synchronously tilted in the same way, first coupling device is the lower rotor distance-variable rocker arm (20) of synchronously shake thereupon, thus change displacement of lower rotor cycle, 2nd coupling device is the upper rotor distance-variable rocker arm (4) of synchronous backward shake thereupon, thus synchronously changes upper rotor cycle displacement.
2. the rotor control mechanism for coaxal helicopter according to claim 1, it is characterised in that:
Described outer automatic inclinator (12), interior automatic inclinator (8) include ball hinge, inner ring, bearing, outer shroud; Described inner ring sleeve is contained in ball hinge and above and can tilt to either direction around ball hinge, and inner ring, outer shroud are connected by bearing; Ball hinge (29) of described outer automatic inclinator is sleeved on described outer axle (10) and above and can slide up and down along described outer axle (10), and ball hinge (40) of described interior automatic inclinator (8) is sleeved on described interior axle (3) and above and can slide up and down along described interior axle (3); Between the outer shroud (34) that first torsion arm (22) is connected to described outer automatic inclinator (12) and fuselage, between the inner ring (31) that the 2nd torsion arm (11) is connected to described outer automatic inclinator (12) and outer axle (10); Between the outer shroud (43) that 3rd torsion arm (9) is connected to described interior automatic inclinator (8) and described outer axle (10);
Described first coupling device comprises middle pull bar (21), lower link bar (19); Described 2nd coupling device comprises pull bar (17), upper cross bar (15), long draw (24); Described 3rd coupling device is long draw (24), and described long draw (24) top is provided with the auricle identical with upper cross bar (15) quantity; Described lower rotor distance-variable rocker arm (20) is provided with auricle and lower auricle, and described upper rotor distance-variable rocker arm (4) is provided with auricle;
The outer shroud (34) of described outer automatic inclinator (12) is connected with described lower link (23), the bottom of described outer axle propeller hub head is provided with the through hole identical with described middle pull bar (21) quantity, and described middle pull bar (21) is through described through hole, and described through-hole aperture is greater than middle pull bar (21) bar footpath, the inner ring (31) of described outer automatic inclinator (12) is connected with the lower end of described middle pull bar (21), and described middle pull bar (21) upper end is connected with the lower auricle of described lower rotor distance-variable rocker arm (20), the lower end of described lower link bar (19) is connected with the upper auricle of described lower rotor distance-variable rocker arm (20), and the upper end of described lower link bar (19) is connected with the outer shroud (43) of described interior automatic inclinator (8), the inner ring (41) of described interior automatic inclinator (8) is provided with the auricle identical with described sheer pole (39) quantity, the outer end of described sheer pole (39) is connected with the auricle on described interior automatic inclinator (8) upper inner ring (41), the inner of described sheer pole (39) is connected through the upper through hole arranged of described interior axle (3) with the lower end of described upper pull bar (17), the upper end of described upper pull bar (17) is connected with described upper cross bar (15) middle part, the inner of described upper cross bar (15) is connected with the auricle of described long draw (24), the outer end of described upper cross bar (15) is connected with the auricle of described upper rotor distance-variable rocker arm (4),
Being installed with position limit device (16) and lower caging device on described long draw (24), it is inner that described position limit device, lower caging device are positioned at axle (3).
3. the rotor control mechanism for coaxal helicopter according to claim 2, it is characterised in that: described 2nd torsion arm (11) is connected with the annulus that can dismantle, and described annulus is anchored on outer axle (10).
4. the rotor control mechanism for coaxal helicopter according to claim 1, it is characterised in that: install rotor nose cone in the outside of upper rotor propeller hub (2), upper rotor propeller hub head; Rotor nose cone under outside installation outside lower rotor propeller hub (6), lower rotor propeller hub head; Described outer automatic inclinator (12) is wrapped in fuselage nose cone.
5. according to the arbitrary described rotor control mechanism for coaxal helicopter of Claims 1 to 4, it is characterized in that: described intermediate ring (7) can be dismantled, described intermediate ring (7) is provided with the auricle identical with described sheer pole (39) quantity, and described sheer pole (39) middle part is connected on the auricle of described intermediate ring (7).
6. according to the arbitrary described rotor control mechanism for coaxal helicopter of Claims 1 to 4, it is characterized in that: described inside and outside axle supports seat (5) and comprises bearing support (36), bearing (37), described outer axle propeller hub head upper end forms a boss, described inside and outside axle supports seat (5) and is installed on the boss of described outer axle propeller hub head upper end, the inside of described bearing support is provided with described bearing (37), described interior axle (3) is through the inner ring of described bearing (37), and the inner ring with bearing (37) closely cooperates.
7. according to the arbitrary described rotor control mechanism for coaxal helicopter of Claims 1 to 4, it is characterised in that: described upper rotor propeller hub (2), lower rotor propeller hub (6) all comprise propeller hub centrepiece (25), bearing (26), propeller hub housing (27) and securing gear (28); Described bearing is installed on described propeller hub enclosure interior; Described propeller hub centrepiece outer end forms flange, is sticked in the bearing inner ring of outermost end bearing, for preventing propeller hub centrepiece (25) slid inward; Described propeller hub centrepiece is through described bearing inner ring and closely cooperates with bearing inner ring, and described securing gear is installed on the inner of described propeller hub centrepiece, and described bearing and described securing gear prevent propeller hub centrepiece (25) from outwards sliding jointly.
8. the rotor control mechanism for coaxal helicopter according to claim 7, it is characterized in that: the outer end of described upper rotor distance-variable rocker arm (4), lower rotor distance-variable rocker arm (20) all forms a quadrangular projection, described quadrangular projection embeds the inner of described propeller hub centrepiece (25), described quadrangular projection center is provided with cylindrical hole, and upper rotor distance-variable rocker arm (4) is fastened on through cylindrical hole and is fastened on lower rotor propeller hub centrepiece on upper rotor propeller hub centrepiece, by lower rotor distance-variable rocker arm (20) by screw respectively.
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| CN201410353728.2A CN104129498B (en) | 2014-07-23 | 2014-07-23 | A kind of rotor control mechanism for coaxal helicopter |
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| CN111377050A (en) * | 2020-02-24 | 2020-07-07 | 深圳联合飞机科技有限公司 | Coaxial rotor wing control device |
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| CN113942640B (en) * | 2021-10-09 | 2023-04-28 | 中国直升机设计研究所 | Inner control rotor wing supporting piece structure |
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| RU2307766C1 (en) * | 2005-12-21 | 2007-10-10 | Открытое акционерное общество "Камов" | Coaxial lifting system |
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| CN111377050A (en) * | 2020-02-24 | 2020-07-07 | 深圳联合飞机科技有限公司 | Coaxial rotor wing control device |
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