CN206634220U - A kind of drive mechanism for aircraft - Google Patents

Abstract

The utility model proposes a kind of drive mechanism for aircraft, including：The optical axis (11) being arranged in the horn (1) of aircraft；Axle sleeve (12), axle sleeve (12) are enclosed on optical axis (11) outside；Anti- red seat (13), anti-red seat (13) are arranged on axle sleeve (12) outside.The utility model substantially improves the axiality and frictional force of aircraft.

Description

A kind of drive mechanism for aircraft

Technical field

It the utility model is related to aircraft field.More particularly, to a kind of drive mechanism for aircraft.

Background technology

Current racing unmanned plane, machine (Racing drone) is also known as passed through, be a kind of consumption fraction of four-axle aircraft Branch, its game content be racing in racing track in the air, and in general this kind of aircraft has manoeuvrable in light weight and resistance to fallen Feature.The variable racing unmanned plane that verts (Tilt racing drone) is the enhanced edition for appealing aircraft, and the aircraft can be Do not change by rotating horn by propeller towards top rake in the case of aspect, so as to reach obtained in the short time it is larger The effect of forward acceleration.

DHL Parcelcopter 3.0 are DHL companies third generation transport unmanned planes, and the unmanned plane combines fixed-wing and flown Machine (Fixed wing) and three axle aircraft (Tri-copter), ducted fan is built in ventral and controlled for controlling flight The pitching (Pitch) of device is stable.

In current racing unmanned plane, the scheme of four axles is largely taken to rely on propeller differential steering, in high-speed flight When turn to it is not direct, electricity can largely be wasted in deceleration and bend on, and due to four-axle aircraft accelerate lean on lateral attitude, A part of visual dead angle can be caused make it that operator's experience is bad.The variable racing unmanned plane that verts (Tilt racing drone) Appearance improve the performance of acceleration to a certain extent, but due to changing the characteristic of driftage by differential, this unmanned plane for Bend commonly may pass through machine not as good as more light-duty, and light weight inertia is small, does not stop by operator's reaction speed really up to the mark Its posture is adjusted to control aircraft, to a certain extent for increase the threshold of introduction.

Utility model content

According to the problems of the prior art, the utility model proposes a kind of drive mechanism for aircraft, including：Set Optical axis in the horn of aircraft；Axle sleeve, axle sleeve are enclosed on outside optical axis；Anti- red seat, anti-red seat are arranged on outside axle sleeve.

Alternatively, described drive mechanism also includes：Thrust ball bearing, connection of the thrust ball bearing positioned at two horns Place.

Alternatively, described drive mechanism also includes：Cup type connector, it is inside that cup type connector is arranged on anti-red seat axle Side.

Alternatively, described drive mechanism also includes：U-shaped rocking arm, U-shaped rocking arm are enclosed on the smaller one end of cup type connector diameter On.

Alternatively, between axle sleeve and anti-red seat it is interference fit.

Alternatively, it is that gap coordinates between optical axis and axle sleeve.

Alternatively, cup type connector is coordinated with erosion control seat contact portion using thrust ball bearing mode.

Alternatively, connected between thrust ball bearing by thrust ball bearing connector, the inner side of thrust ball bearing connector End is provided with the counterbore for being used for placing flange bearing, thrust ball bearing and flange bearing by screw through connection.

Alternatively, thrust ball bearing connector is located at cup type connector radially inner side.

Alternatively, described drive mechanism also includes：Ducted fan, ducted fan are arranged on the belly of aircraft, It is oriented fuselage direction.

The beneficial effects of the utility model are：Aircraft of the present utility model can be during advancing at utmost speed, by getting rid of Tail and manual open out accomplished curved acceleration, energy is at utmost used to accelerate, also optimizes the visual angle experience of operator.

Brief description of the drawings

Fig. 1 is the stereogram of two horns of the drive mechanism of aircraft of the present utility model；

Fig. 2 is the sectional view of two horns of the drive mechanism of aircraft of the present utility model；

Fig. 3 is the left view of two horns shown in Fig. 2；

Fig. 4 is the stereogram of the drive mechanism of aircraft of the present utility model；

Fig. 5 is the side view of the drive mechanism of aircraft of the present utility model；

Fig. 6 is the front view of the empennage in Fig. 4；

Fig. 7 is the rearview of the empennage in Fig. 4；

Fig. 8 is the top view of the empennage in Fig. 4；

Fig. 9 is the stereogram of a part for the empennage in Fig. 4.

Reference

1- horns；11- optical axises；12- axle sleeves；The anti-red seats of 13-；14- thrust ball bearings；15- cup type connectors；

16-U type rocking arms；17- thrust ball bearing connectors；18- flange bearings；The tooth screws of 19- half；

2- empennages；21- vertical tails；22- tailplanes；23- rudder faces；24- steering wheels；25- long connecting rods；

26- tailplane connectors；27- semicircle rocking arms；28- baffle plates；29- tail pipes；

The connection ends of 261- first；262- second connection ends；The connection ends of 263- the 3rd；

3- ducted fans.

Embodiment

Embodiment of the present utility model, wherein identical part identical reference table are described with reference to the accompanying drawings Show.

Fig. 1 shows the stereogram of two horns of the drive mechanism of aircraft of the present utility model, wherein for ease of seeing Examine, do not show optical axis 11.Fig. 2 shows the sectional view of two horns of the drive mechanism of aircraft of the present utility model.

The drive mechanism of aircraft of the present utility model includes：Two horns 1, the centre of each horn 1 have one section it is hollow Optical axis 11, axle sleeve 12 is provided with outside optical axis 11, and optical axis 11 is that gap coordinates with axle sleeve 12.Erosion control seat is provided with outside axle sleeve 12 13, hole is provided with anti-red seat 13, is passed through for optical axis 11, but between axle sleeve 12 and anti-red seat 13 is interference fit.Anti- red seat Hole is provided with 13, axle sleeve 12 is interference fitted with it.Optical axis 11 passes through axle sleeve 12, and both gaps coordinate.

The anti-axially inner side of red seat 13 is provided with cup type connector 15 (being preferably manufactured from aluminum).The diameter of cup type connector 15 is smaller One end on be cased with U-shaped rocking arm 16.With screw and nut, clamp lock lives optical axis 11 and U-shaped rocking arm 16 to cup type connector 15 simultaneously, U-shaped to shake There is hole position to be used to fix metal ball-head on arm 16.U-shaped rocking arm 16 is connected and (is explained in detail below) with bulb and long connecting rod 25 with steering wheel 24.

The effect of anti-red seat 13 and cup type connector 15 is that limitation horn 1 has rotational freedom, can not axial direction and footpath To activity.The outer shape of anti-red seat 13 can change with the shape of the fuselage of aircraft from now on.

Advantageously, cup type connector 15 also uses thrust ball bearing with the anti-contact portion of red seat 13, radially movable to reduce Gap and pivoting friction, or, smooth axle sleeve with flange can also be used to substitute.

U-shaped rocking arm 16 is connected by model plane ball-head tension rod (not shown) with underface steering wheel (not shown), and steering wheel is by torque U-shaped rocking arm 16 is transferred to, and U-shaped rocking arm is mutually fixed with horn, is flown so as to which steering wheel can control whole horn 1 to reach control Row device driftage (YAW) and pitching (P).

Two horns 1 of aircraft are connected by bearing, it is preferred to use thrust ball bearing 14 connects.Thrust ball bearing makes Obtaining two horns 1 has very high axiality and low-down pivoting friction, is advantageous to servos control.

More specifically, connected between thrust ball bearing 14 by thrust ball bearing connector 17.Thrust ball bearing connector 17 medial extremity is provided with the counterbore for being used for placing flange bearing 18.Thrust ball bearing 14 is positioned over two thrust ball bearing connectors Among 17.Half tooth screw 19 sequentially passes through flange bearing 18- thrust ball bearing 14- flange bearings 18, with self-tightening nut by the whole series Rotation system connects.Thrust ball bearing connector 17 wraps flange bearing 18.The outside of thrust ball bearing connector 17 is Cup type connector 15.

Hollow optical axis 11 is fixed by screw and nut and cup type connector 15, cup type connector 15 also by screw and nut with The carbon fiber pipe of horn 1 is fixed, collectively regarded as a rigid body, and power is finally transmitted to anti-red seat 13.Extraneous axial impact then because Stop lock effect for cup type connector 15, power is again acted upon on anti-red seat 13, so as to protect thrust ball bearing 14 and optical axis 11.

In addition, hollow optical axis 11 ensure that axiality in axle sleeve 12, the radial load of two axle aircraft is reduced, and thrust Ball bearing and anti-red seat 13 reduce the axial force of two axle aircraft so that whole two axles aircraft has very high axiality and non- Often low pivoting friction.

As shown in figure 4, the drive mechanism of double-wing aerobat of the present utility model also includes：Ducted fan 3, ducted fan 3 The belly of aircraft is arranged on, is oriented fuselage direction.Ducted fan 3 by air-flow to fuselage after-blow, meanwhile, ducted fan 3 are converted to controllable variable to the air-flow of after-blow, compensate for unstability of the twin shaft aircraft on pitch axis.

As shown in figure 5, the utility model also proposes a kind of tail structure for aircraft, including：Empennage portion 2, tail Alar part 2 is arranged on the afterbody of double-wing aerobat, and empennage portion 2 includes vertical tail 21 and tailplane 22.

Tailplane 22 uses symmetrical airfoil, ensures air-flow not stall to a certain extent, and symmetrical airfoil is beneficial to rotating shaft Structure design.Tailplane 22 is located at the side rear of vertical tail 21, and such layout can protect in structure and pneumatic aspect Demonstrate,prove tailplane 22 and vertical tail 21 is non-interference, and vertical tail 21 can be by air-flow rectification in front so that be horizontal Empennage 22 preferably produces torque in aerodynamic center.

Advantageously, as shown in figure 8, the trailing edge of tailplane 22 vertically rises the baffle plate 28 of certain percentage chord length, it is therefore an objective to Under the conditions of wing area is confined, farthest ensure that fluid bubbles do not separate, and finally allow empennage 2 preferably to control Air-flow processed.

For double vertical tails 21 equally by winged control mixing control, double vertical tails 21 and the co- controlling aircraft of two-shipper arm 1 are inclined Navigate (YAW).When aircraft enters high-speed forward flight state (FFF), the driftage weight of two-shipper arm 1 diminishes, double vertical tails 21 driftage weights become big.Design above can allow aircraft to be realized similar in Thrash Rally during high-speed flight Whipping, the throttle of ducted fan 3 is completely manual, it can be understood as the throttle in racing car due to not controlled by winged control.

As illustrated in figures 4-5, vertical tail 21 is fixed on the tail pipe 29 of double-wing aerobat.The trailing edge of vertical tail 21 has One piece of rotatable rudder face 23, for changing airflow direction.The rudder face 23 is controlled by steering wheel 24, and steering wheel 24 is located at (see Fig. 5-6) The lower section of vertical tail 21.

As shown in figure 5, long connecting rod 25 extends below tail pipe 29 along the direction of tail pipe 29, tailplane 22 passes through horizontal tail Wing connector 26 links together with long connecting rod 25.

Tailplane connector 26 is described referring to Fig. 6-9.Tailplane connector 26 includes the first connection end 261st, the connection end 263 of second connection end 262 and the 3rd.Thrust ball bearing mode is taken to be connected to tail pipe 29 in the first connection end 261 Tail end, the first connection end 261 can rotate relative to tail pipe 29.Second connection end 262 takes thrust ball bearing mode to connect To long connecting rod 25.3rd connection end 263 is patched fixed to tailplane 22 by 4 bolts.When long connecting rod 25 moves forward and backward, Second connection end 262 can be pulled to move forward and backward, thus, the first connection end 261 rotates around tail pipe 29, and then the 3rd connection end 263 drive tailplane rotation (by taking Fig. 7 as an example, tailplane 22 can rotate in the plane perpendicular to paper), so as to change Become airflow direction.

Referring again to Fig. 5, the one end of long connecting rod 25 connection tailplane connector 26, other end connection semicircle rocking arm 27.Half Circle rocking arm 27 is located at the lower section of ducted fan 3, by the servos control of the lower section of ducted fan 3.The swing of semicircle rocking arm 27, pull length The swing of connecting rod 25, and because tailplane connector 26 is connected to tailplane 22, by the transmission of long connecting rod 25, realize By semicircle rocking arm 27 come controlled level empennage 22.

Torque is delivered to long connecting rod 25 since semicircle rocking arm 27, the limited location in transmission process, it is such it is spacing can be with Ensure the validity of the driving force of long connecting rod 25.Substantially, the parallelogram double-crank mechanism of a limited location, main rocker are formed It is tailplane connector 26 from rocking bar for semicircle rocking arm 27.

Tailplane 22 designs for swept-back wing and aerodynamic center is located at rotating shaft.Here rotating shaft refers to tailplane connector The axle center of thrust ball bearing in 26 (being described in detail below), fixing means be half tooth screw through flange bearing-thrust ball bearing- Flange bearing, then coordinate with self-tightening nut.Aerodynamic center is located at the mobility that this mode of rotating shaft enhances aircraft.

One steering wheel of implementation above controls the pitching of a horn with two push rods, is passed than gear drive and conveyer belt Dynamic, such link transmission mode diastema is smaller, beneficial to servos control.The rotational angle of steering wheel can be fine by the middle level carbon in frame It is spacing to tie up plate, so as not to rotate excessively.

Pitching (Pitch) of the utility model with empennage portion 2 by winged control mixing aircraft, and ducted fan 3 is direct Controlled by the one of passage of remote control (be the equal of an external force factor in flight stabilization system, such as wind), empennage portion 2 are divided to control Fluctuation of analytical signal generation torque according to winged to correct attitude of flight vehicle in real time.

Aircraft of the present utility model also includes flying control part.Fly control (FC) is using the KK2.1.5 to increase income, firmware OpenAeroVTOL V1.4 increase income firmware, and the firmware maximum feature is to possess 8 self-defined mixed empty passages, support two kinds of flights Pattern seamless switching (such as VTOL fixed wing aircraft V22 and now many fixed-wing VTOL schemes).

The winged control part includes：Double oars up and down, wherein upper oar pitch is small, lower oar pitch is big, realizes the difference of rotating speed. Flying control part includes four motors, and four motors account for four mixing passage control throttles (THR) and aileron (AIL).Fly control part Including two steering wheels, two horns 1 are controlled respectively, and two steering wheels account for two mixing passage control direction rudders (RUDD) and elevator (ELE).Flying control part 4 includes a tailplane steering wheel, accounts for a mixing passage control elevator (RUDD).Fly control part 4 Including two vertical tail steering wheels, two vertical tail steering wheels take a mixing passage control direction by a Y steering wheels line Rudder (RUDD).Alternatively, ducted fan can be purely manual not take a remote control passage (AUX) individually by flying control.

Aircraft of the present utility model is simulated by Solidworks flow simulation, and empennage torque reaches design It is required that the size of power can highly be adjusted according to baffle plate 28.

Embodiment described above, simply the utility model more preferably embodiment, those skilled in the art The usual variations and alternatives carried out in the range of technical solutions of the utility model should all be included in the scope of protection of the utility model It is interior.

Claims (10)

1. A kind of 1. drive mechanism for aircraft, it is characterised in that including：

   The optical axis (11) being arranged in the horn (1) of aircraft；

   Axle sleeve (12), axle sleeve (12) are enclosed on optical axis (11) outside；

   Anti- red seat (13), anti-red seat (13) are arranged on axle sleeve (12) outside.
2. 2. drive mechanism according to claim 1, it is characterised in that also include：

   Thrust ball bearing (14), thrust ball bearing (14) is positioned at the junction of two horns (1).
3. 3. drive mechanism according to claim 2, it is characterised in that also include：

   Cup type connector (15), cup type connector (15) are arranged on anti-red seat (13) axially inner side.
4. 4. drive mechanism according to claim 3, it is characterised in that also include：

   U-shaped rocking arm (16), U-shaped rocking arm (16) are enclosed on cup type connector (15) smaller one end of diameter.
5. 5. drive mechanism according to claim 1, it is characterised in that also include：

   It is interference fit between axle sleeve (12) and anti-red seat (13).
6. 6. drive mechanism according to claim 1, it is characterised in that

   It is that gap coordinates between optical axis (11) and axle sleeve (12).
7. 7. drive mechanism according to claim 3, it is characterised in that

   Cup type connector (15) is coordinated with anti-red seat (13) contact portion using thrust ball bearing mode.
8. 8. drive mechanism according to claim 3, it is characterised in that

   Connected between thrust ball bearing (14) by thrust ball bearing connector (17),

   The medial extremity of thrust ball bearing connector (17) is provided with the counterbore for being used for placing flange bearing (18), thrust ball bearing (14) With flange bearing (18) by screw through connection.
9. 9. drive mechanism according to claim 8, it is characterised in that

   Thrust ball bearing connector (17) is located at cup type connector (15) radially inner side.
10. 10. drive mechanism according to claim 1, it is characterised in that also include：

    Ducted fan (3), ducted fan (3) are arranged on the belly of aircraft, are oriented fuselage direction.