CN209795812U - aviation aircraft - Google Patents

Abstract

the utility model discloses an aviation aircraft, be provided with the aircraft body of steering wheel including the afterbody, the steering wheel includes rudder cabin shell and rudder piece subassembly, the rudder piece subassembly includes rudder piece and adjusting device, the root of rudder piece is connected with adjusting device after passing rudder cabin shell, adjusting device includes orthoscopic actuating mechanism, the slider, the rudder piece rocking arm, the fixed plate, adjustment arm and rudder axle, the fixed plate is connected with rudder cabin shell, the rudder axle rotates with the fixed plate to be connected, rudder axle one end is connected with the root of rudder piece, the rudder axle other end is connected with the rudder piece rocking arm, the rudder piece rocking arm is articulated with the slider, actuating mechanism drive slider carries out reciprocating motion, the one end of adjustment arm is articulated with the fixed plate, the other end and the drive arrangement's of adjustment arm shell are connected. The utility model discloses the holistic weight of aircraft has been reduced to the holistic performance of aircraft has been improved.

Description

Aviation aircraft

Technical Field

The utility model relates to an aircraft field, concretely relates to aviation aircraft.

Background

An aircraft is an instrumental flying object that is manufactured by humans, can fly off the ground, fly in space and be controlled by humans to fly in or out of the atmosphere. Steering engines are one of the most important components on aircraft. In the aspect of aerospace, the steering engine is widely applied, and pitching, yawing and rolling motions of attitude transformation of the aircraft are completed by mutual cooperation of the steering engine.

the steering engine of the aircraft is a device for controlling the flight direction of the aircraft. The adjustment of the aircraft in the pitching, left and right directions is adjusted by the steering engine. In the steering engine, each rudder sheet is controlled by an adjusting component. The adjusting component controls the rotation angle of the rudder sheet, so that the flight direction of the aircraft can be adjusted. When the adjusting component directly adopts motor and gear to carry out the rudder axle rotation of rudder piece, can be unfavorable for the state that each operating mode sound that monitored control system gathered the aircraft comes the analysis aircraft because gear drive produces the noise. On the premise of certain manufacturing cost, gear noise is a defect which cannot be avoided by a gear type rudder shaft driving device.

The prior art CN108286918A discloses a multi-axis driven annular steering control device. Although the prior art cancels gear transmission, an adjusting assembly consisting of a motor, a screw rod, a shifting fork and a nut is adopted, the motor drives the screw rod to rotate, the screw rod drives the screw rod to move along the axial direction, the shifting fork is clamped into a notch on one side of the nut far away from the motor, and the shifting fork is fixedly connected with a rudder shaft. In the driving mode, the gap is open, so that the nut can only drive the shifting fork to one side far away from the motor, and the shifting fork cannot be pulled back, so that the rudder shaft can only rotate towards one direction and cannot be reversed, and the basic function requirements of the forward and reverse rudder shaft cannot be met; meanwhile, the rotation of the rudder shaft in two directions can be realized in time through the shifting fork, but in the matching mode of the shifting fork and the nut, when the matching gap is too small, the action locking is generated, and the shifting fork cannot be smoothly pushed; when the clearance is too large, the shape error is extremely large, the rotating position of the rudder shaft cannot be adjusted in time, and the rotating angle of the rudder shaft cannot be controlled accurately.

furthermore, prior art CN106976550A discloses an aircraft rudder and air rudder linkage. The prior art also cancels gear transmission, the adjusting component of the rudder piece comprises a lead screw nut, an action rod and a cam which are sequentially hinged, the lead screw nut is matched with a lead screw, the rudder piece is in threaded connection with the cam, the cam is in threaded connection with a gas rudder support, and the gas rudder support is fixed on the outer cover. Although the connecting rod type adjusting assembly has extremely low transmission noise compared with gear driving and shifting fork driving, the transmission stability can be ensured, and adverse factors such as errors can not be generated. However, the transmission chain of the link mechanism type adjusting assembly is too long, which not only increases the transmission error, but also increases the volume and gravity of the rudder piece driving device, and thus the link mechanism type adjusting assembly cannot be developed on the fly smoothly.

Disclosure of Invention

The utility model aims to provide a: the utility model provides an aviation aircraft has solved the driving chain overlength of the steering wheel that current aircraft adopted, leads to the transmission error increase, the problem that its self gravity also increases.

in a link mechanism adopted by the existing steering engine, if an action rod for connecting a lead screw nut and a cam is directly cancelled, the lead screw nut is directly hinged with the cam, at the moment, the driving motor is fixed relative to the rotation center of the cam, and the lead screw nut has only one position, so that the lead screw nut is positioned on a lead screw and is hinged with the cam; at the moment, the feed screw nut cannot move, and meanwhile, the cam cannot rotate around the rotation center of the cam. The purpose of reducing the volume and the gravity can be achieved by removing one connecting rod, but the screw nut and the rudder shaft cannot be moved, so that the position of the motor needs to be synchronously adjusted along with the movement of the screw nut, and the screw nut serving as a driving piece can be hinged with the cam and can also move along the screw rod. In order to meet the above requirements, an additional motor is required to adjust the position of the driving motor, which in turn increases the complexity, volume and gravity of the overall structure of the link mechanism type driving mechanism, contrary to the technical problems to be solved at first.

And the utility model discloses an aviation aircraft has broken through traditional inertia thinking of fixing linear drive mechanism on the part on the basis of having cancelled a connecting rod among the current connecting rod formula adjusting part, fixes the part that supports the rudder axle with actuating mechanism articulated formula innovatively, on the fixed plate promptly, and the fixed plate is fixed on the shell of aircraft, and actuating mechanism can rotate around its and the articulated axis between the fixed plate. Specifically, when the screw rod drives the slider to move, because the rudder blade rocker can only rotate around the axis of the rudder shaft, and the slider needs to move axially along the screw rod, the slider rotates around the rudder shaft together with the rocker under the drive of the screw rod, and the slider enables the linear driving mechanism to rotate around the axis of the hinge part between the driving mechanism and the fixed plate under the guidance of the rudder blade rocker, so that the output end of the driving mechanism is continuously adjusted to match the rotation of the slider, and the movement mode of the slider is planar motion: the slide moves linearly relative to the drive mechanism and rotates about the axis of rotation of the rudder blade pivot, i.e. the axis of the rudder shaft, relative to the rudder blade pivot.

The utility model adopts the technical scheme as follows:

An aviation aircraft comprises an aircraft body, wherein the aircraft body comprises a hood, a battery cabin, a front wing cabin, a control cabin and a steering engine which are sequentially connected, the steering engine comprises a rudder cabin shell and a plurality of rudder blade assemblies, the rudder blade assemblies comprise rudder blades and rudder blade adjusting devices fixed inside the rudder cabin shell, the roots of the rudder blades penetrate through the rudder cabin shell and are connected with the rudder blade adjusting devices, the rudder blade adjusting devices comprise linear driving mechanisms, sliders, rudder blade rocker arms, fixed plates, adjusting arms and rudder shafts, one side of each fixed plate is fixedly connected with the rudder cabin shell, the rudder shafts are rotatably connected with the fixed plates, one ends, far away from the axis of the rudder cabin shell, of the rudder shafts are connected with the roots of the rudder blades, the other ends of the rudder shafts are connected with one ends of the rudder blade rocker arms, the other ends of the rudder blade rocker arms are hinged with the sliders, the driving mechanisms drive the sliders to move in a reciprocating mode, one end of the adjusting arm is hinged with one side of the fixing plate, the other end of the adjusting arm is connected with a shell of the driving device, the hinged axes are all parallel to the axis of the rudder shaft, and the sliding block moves in a plane perpendicular to the axis of the rudder shaft.

The linear driving mechanism includes, but is not limited to, a linear motor, a combination of a servo motor and a screw rod, and a working cylinder such as a pneumatic cylinder, a hydraulic cylinder, and the like. The utility model discloses in, the thrust of the aircraft of design, lift device can adopt current aircraft power device such as duct fan, screw device or the combination between them of the aforesaid, the utility model discloses directly with current aircraft power device take use can.

When the rudder sheet needs to be rotated forwards, the driving mechanism is started to enable the sliding block to perform forward linear movement relative to the driving direction of the driving mechanism, at the moment, the rocker arm of the rudder sheet rotates around the rudder shaft under the pushing of the sliding block, and meanwhile, the driving mechanism rotates around the axis of the hinged part between the driving mechanism and the fixed plate so as to match the position adjustment required when the sliding block rotates around the rudder shaft; when the rudder sheet needs to be rotated reversely, the driving mechanism is started to enable the sliding block to move linearly along the driving direction of the driving mechanism in a reverse direction, at the moment, the rocker arm of the rudder sheet rotates reversely around the rudder shaft under the pushing of the sliding block, and meanwhile, the driving mechanism rotates around the axis of the hinged part between the rocker arm and the fixed plate so as to match the position adjustment needed when the sliding block rotates around the rudder shaft.

To sum up, the utility model discloses not only cancel a connecting rod among the current connecting rod formula adjusting part, the structure of adjusting part has been simplified, adjusting part's weight has been reduced, and the inertia thinking of traditional fixing linear drive mechanism on the part has been broken through, innovatively fix actuating mechanism articulated formula on the fixed plate, rotate around its articulated axis between and the fixed plate and mate the rotational position of each rudder piece rocking arm through making actuating mechanism, the slider required position, need not to increase the matching nature adjustment of the position that other drive arrangement solved the motor, the holistic weight of aircraft has been reduced, and the holistic performance of aircraft has been improved.

Due to the adoption of the technical scheme, the beneficial effects of the utility model are that:

1. The utility model discloses aviation aircraft, a connecting rod in the current connecting rod formula adjusting part has not only been cancelled, adjusting part's structure has been simplified, adjusting part's weight has been reduced, and the inertia thinking of traditional fixing linear drive mechanism on the part has been broken through, innovatively fix actuating mechanism articulated formula on the fixed plate, rotate around the articulated axis between its and the fixed plate and match among the rotational position of each rudder piece rocking arm through making actuating mechanism, the slider required position, need not to increase the matching nature adjustment of the position that other drive arrangement solved the motor, the holistic weight of aircraft has been reduced, and the holistic performance of aircraft has been improved.

2. The square groove of the aviation aircraft is a through groove, so that the processing cost is reduced; if the rudder blade rocker arm is directly machined into a square groove with the cross section shape and the size consistent with the cross section shape and the size of the collecting end, when the aircraft is small in size, the corresponding rudder blade rocker arm is also small in size, and a smaller groove is machined on the rudder blade rocker arm, so that the machining cost is increased; and the through groove is formed, so that the through groove can be processed only by linear feed for many times, the processing of the structure of the square groove is facilitated, and the production cost is reduced.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments are briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, for those skilled in the art, other related drawings can be obtained according to the drawings without creative efforts, and the proportional relationship of each component in the drawings in the present specification does not represent the proportional relationship in the actual material selection design, and is only a schematic diagram of the structure or the position, in which:

Fig. 1 is a schematic structural diagram of the present invention;

FIG. 2 is a schematic structural diagram of a steering engine;

FIG. 3 is a schematic view of the structure with the rudder nacelle shell removed;

FIG. 4 is a schematic view of the retainer ring;

FIG. 5 is a schematic structural view of the adjustment assembly;

FIG. 6 is a top view of the adjustment assembly;

FIG. 7 is a cross-sectional view taken along A-A in FIG. 6;

FIG. 8 is a schematic structural view of a rudder blade assembly;

FIG. 9 is an exploded view of the rudder blade assembly;

FIG. 10 is a schematic view showing an initial state of the rudder sheet;

FIG. 11 is a schematic view of the position of the rudder blade of FIG. 10 in a forward direction;

fig. 12 is a schematic view of the position of the rudder piece in fig. 10 in reverse rotation.

Reference numerals in the drawings indicate:

1-slide block, 2-rudder blade rocker, 3-fixing plate, 4-adjusting arm, 5-rudder shaft, 6-fixing block, 7-through groove, 8-threaded hole, 9-screw A, 10-servo motor, 11-lead screw, 12-anti-drop block, 13-screw B, 14-motor base, 15-sleeve, 16-pin, 17-retainer ring, 18-annular groove, 19-potentiometer, 20-potentiometer base, 21-screw C, 22-screw D, 23-square groove, 24-collection end, 25-abdication hole, 26-articulated shaft, 27-bearing A, 28-connecting block, 29-screw E, 30-rudder blade, 31-limiting threaded section, 32-smooth section, 33-non-circular hole, 34-a limiting nut, 35-an angular contact ball bearing, 36-an output shaft, 37-a rudder shaft hole, 38-a bearing B, 39-an arm hinge hole, 40-a pin hole, 41-a mounting hole, 42-a rudder cabin shell, 43-a fixing ring, 44-an aircraft body, 45-a head cover, 46-a battery cabin, 47-a front wing cabin and 48-a control cabin.

Detailed Description

in order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention, i.e., the described embodiments are only some, but not all embodiments of the invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. The terms of orientation such as up, down, left, right, etc. used in the description of the present invention are only explained with respect to the illustrated structure, and are not necessarily limited to actual use.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiment of the present invention, all other embodiments obtained by the person skilled in the art without creative work belong to the protection scope of the present invention.

All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.

The present invention will be described in detail with reference to fig. 1 to 12.

Example 1

as shown in fig. 1-12, the utility model discloses an aviation aircraft, including aircraft body 44, aircraft body 44 includes hood 45, battery cabin 46, front wing cabin 47, control cabin 48 and the steering wheel that connects gradually, the steering wheel includes rudder cabin shell 42 and a plurality of rudder blade subassembly that are connected with control cabin 48, rudder blade subassembly includes rudder blade 30 and fixes the rudder blade adjusting device in rudder cabin shell 42 inside, the root of rudder blade 30 passes behind rudder cabin shell 42 and is connected with rudder blade adjusting device, rudder blade adjusting device includes linear drive mechanism, slider 1, rudder blade rocking arm 2, fixed plate 3, adjusting arm 4 and rudder axle 5, one side of fixed plate 3 and rudder cabin shell 42 fixed connection, rudder axle 5 is connected with fixed plate 3 is rotated, the one end of rudder axle 5 that keeps away from rudder cabin shell 42 axis is connected with the root of rudder blade 30, the other end of rudder axle 5 is connected with the one end of rudder blade rocking arm 2, the other end of the rudder piece rocker 2 is hinged with the slider 1, the driving mechanism drives the slider 1 to reciprocate, one end of the adjusting arm 4 is hinged with one side of the fixing plate 3, the other end of the adjusting arm 4 is connected with the shell of the driving device, the hinged axes are all parallel to the axis of the rudder shaft 5, and the slider 1 moves in a plane perpendicular to the axis of the rudder shaft 5.

the linear driving mechanism includes, but is not limited to, a linear motor, a combination of a servo motor and a screw rod, and a working cylinder such as a pneumatic cylinder, a hydraulic cylinder, and the like.

When the rudder sheet needs to be rotated forwards, the driving mechanism is started to enable the sliding block 1 to perform forward linear movement relative to the driving direction of the driving mechanism, at the moment, the sliding block moves to one side far away from the driving mechanism, the rudder sheet rocker arm rotates around the rudder shaft 5 under the pushing of the sliding block 1, and simultaneously, the driving mechanism rotates around the axis of the hinged part between the rudder sheet rocker arm 2 and the fixed plate 3 under the pulling of the rudder sheet rocker arm 2 so as to match the position adjustment needed when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 10; when the rudder sheet needs to be rotated reversely, the driving mechanism is started to enable the sliding block 1 to move linearly along the driving direction of the driving mechanism reversely, at the moment, the sliding block moves to one side close to the driving mechanism, the rudder sheet rocker arm rotates reversely around the rudder shaft 5 under the pushing of the sliding block 1, and simultaneously, the driving mechanism rotates around the axis of the hinged part between the rudder sheet rocker arm 2 and the fixed plate 3 under the pulling of the rudder sheet rocker arm 2 to match the position adjustment needed when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 11.

To sum up, the utility model discloses an among the steering wheel, not only cancelled a connecting rod among the current connecting rod formula adjusting part, adjusting part's structure has been simplified, adjusting part's weight has been reduced, and broken through traditional inertia thinking of fixing linear drive mechanism on the part, fix actuating mechanism articulated formula on the fixed plate innovatively, rotate around the articulated axis between it and the fixed plate and mate among the rotational position of each rudder piece rocking arm through making actuating mechanism, the slider required position, need not to increase the matching nature adjustment that other drive arrangement solved the position of motor, so that the performance of steering wheel is more stable, angle modulation is more accurate, weight descends, the holistic weight of aircraft has been reduced, and the holistic performance of aircraft has been improved.

The positive and negative angles of the rudder blade are alpha, and the value of alpha is 10-45 degrees, preferably 25 degrees.

Example 2

The present embodiment is specifically described for the rotation connection between the rudder shaft 5 and the fixed plate 3.

As shown in fig. 4, in the present invention, the rudder shaft 5 is rotatably connected to the fixing plate 3 by the following means: the fixed plate 3 is provided with a rudder shaft hole 37, the upper end and the lower end of the rudder shaft hole 37 are both provided with a bearing B38, the bearing B38 is preferably a deep groove ball bearing, the inner diameter of the bearing B38 is in interference fit with the rudder shaft 5, and the outer diameter of the bearing B38 is in interference fit with the rudder shaft hole 37.

The rudder shaft hole 37 includes a small-diameter hole and large-diameter holes located at the upper and lower ends of the small-diameter hole, and the bearings B38 are respectively inserted into one of the large-diameter holes and are in interference fit with the hole walls of the large-diameter holes.

The utility model discloses the rotation at well each position is connected, mainly adopts shaft hole complex mode, and in the shaft hole cooperation, the correspondence is provided with the bearing, reduces coefficient of friction.

Example 3

the present embodiment specifically describes a structure in which a rudder blade is attached to a rudder shaft 5.

As shown in fig. 5-8, in the utility model, the one end of keeping away from rudder cabin shell 42 axis on rudder shaft 5 is provided with fixed block 6, the bottom and the rudder shaft 5 of fixed block 6 are connected, and its top is provided with logical groove 7, is provided with a plurality of screw holes 8 at the tank bottom that leads to the groove, is provided with T-shaped block 28 at the root of rudder piece 30, the end and the rudder piece 30 of the vertical section in middle of T-shaped block 28 are connected, and the horizontal segment of T-shaped block 28 inserts in leading to the groove 7 to fix at rudder shaft 5 top through a plurality of screws E29, screw E29 pass behind the horizontal segment with respectively with a screw hole 8 threaded connection.

The rudder sheet 30 is fixed through the mounting through 7, so that when the fixing of the connecting block 28 is realized through the screw E, the connecting block 28 can be limited through the groove walls on two sides of the mounting through groove 7, so that the shearing force borne by the screw E is reduced when the rudder sheet is stressed, and the service life of the adjusting device is prolonged.

Preferably, four screws E29 are symmetrically arranged on both sides of the connecting block 28 in pairs, and the screws E29 are threaded into the threaded holes 8 after passing through the horizontal section of the bottom of the T-shaped block.

preferably, the rudder blade rocker 2 is connected to the bottom of the rudder shaft 5, i.e. the side close to the axis of the rudder trunk housing 42, by means of a screw a 9.

since the top of the rudder shaft 5 needs to be connected with the rudder blade, and in order to facilitate the assembly and disassembly of the present invention, the rudder blade rocker 2 is preferably arranged at the bottom of the rudder shaft 5 and connected with the rudder shaft 5 through a screw a 9.

The rudder shaft 5 is integrally formed with the fixed block 6, so that the projection line of the contact surface between them is not shown in the sectional view of fig. 3.

Example 4

The present embodiment is described with reference to monitoring the rotation angle of the rudder shaft 5 in practical use.

As shown in fig. 9, in the utility model, one side that rudder axle 5 was kept away from to rudder piece rocking arm 2 is provided with the angle sensor subassembly, is provided with square groove 23 on rudder piece rocking arm 2 on the side of keeping away from rudder axle 5, the angle sensor subassembly includes potentiometre 19, potentiometre seat 20 and screw C21 and screw D22, screw C21 fixes potentiometre 19 on potentiometre seat 20, screw D22 fixes potentiometre seat 20 on fixed plate 3, the axis of potentiometre 19 and the axis coincidence of rudder axle 5, the collection end 24 of potentiometre 19 is the square shaft, and it inserts in square groove 23 after passing the hole of stepping down 25 on potentiometre seat 20.

Preferably, the square groove 23 is a through groove, and both groove walls of the square groove are in contact with the collecting end 24.

The potentiometer is a typical contact absolute type angle sensor, and is provided with a sliding contact on a resistance film, and the position of the contact is changed by external action so as to change the ratio of upper resistance and lower resistance of the resistance film, and realize that the voltage of an output end is changed along with the external position. The potentiometer is composed of an electronic component and a cursor, wherein the cursor can slide on the surface of the component and is divided into a linear sliding type and a rotating type. The former is used to detect linear displacement, and the latter is used to detect angle, inclination angle, and the like. The output end of the potentiometer is connected with a controller of the aircraft. When the rudder sheet needs to be rotated, a rotation angle instruction is input to the controller, and the controller starts the driving mechanism according to the instruction so as to enable the driving mechanism to work and enable the rudder shaft to drive the rudder sheet to rotate; the acquisition end 24 of the potentiometer rotates along with the rotation of the rocker arm 2 and sends acquired signals to the controller.

The utility model discloses in, the vernier of potentiometre adopts rotary-type vernier, and the vernier is just to gather end 24, and it is non-circular structures such as square shaft, flat axle. When the collecting end is a square shaft, a pair of opposite side walls thereof are respectively in contact with two wall surfaces of the square groove 23.

The potentiometer 19 is preferably of the type 3590S-2-102L from BOURNS. The potentiometer 19 may be connected to the aircraft controller by a wired connection, a wireless connection, or the like.

The potentiometer 19 is provided to more accurately obtain the rotation angle of the rotary shaft 3.

The square groove 23 is a through groove to reduce the processing cost. If the rudder blade rocker arm is directly machined into a square groove with the cross section shape and the size consistent with the cross section shape and the size of the acquisition end 24, when the aircraft is small in size, the corresponding rudder blade rocker arm is also small in size, and a smaller groove is machined on the rudder blade rocker arm, so that the machining cost is increased; and the through groove is formed, so that only a plurality of linear feed operations are needed to process one through groove, the processing of the structure of the square groove 23 is facilitated, and the production cost is reduced.

Example 5

the present embodiment is a description of a first embodiment of the drive mechanism.

As shown in fig. 5-10, in the present invention, the driving mechanism includes a servo motor 10 and a lead screw 11, an output shaft of the servo motor 10 is connected to one end of the lead screw 11, the lead screw 11 is connected to the slider 1 by a thread, and the adjusting arm 4 is connected to a housing of the motor 10.

when the sliding block needs to move to one end far away from the servo motor 10, the servo motor 10 is started, and an output shaft of the servo motor drives the screw rod 11 to rotate, so that the sliding block 1 moves along the axial direction of the screw rod 11; when the sliding block 1 needs to move towards the servo motor 10, the servo motor 10 is started, and an output shaft of the servo motor drives the screw rod 11 to rotate reversely, so that the sliding block 1 moves along the axial direction of the screw rod 11.

The servo motor 10 feeds back the working signal to the control center of the aircraft in real time. The output shaft of the servo motor 10 may be directly connected to the lead screw 11, or may be connected to the lead screw 11 via a coupling, a universal joint, or the like.

Furthermore, an anti-falling stopper 12 is arranged at one end of the screw rod 11 far away from the servo motor 10.

The anti-dropping stopper 12 prevents the slider 1 from dropping off from the end of the screw rod 11 far away from the servo motor 10.

Example 6

this embodiment is a specific description of the connection between the screw 11 and the output shaft of the servo motor in embodiment 5.

As shown in fig. 9, in the utility model, be provided with coupling assembling between servo motor 10 and the lead screw 11, coupling assembling includes motor cabinet 14, sleeve 15 and screw B13, the one end that is close to servo motor 10 on the lead screw 11 inserts in the sleeve 15 to rotate with sleeve 15 and be connected, screw B13 pass outer fringe, motor cabinet 14 back and servo motor 10's shell threaded connection in proper order, insert behind the motor cabinet 14 and be connected with lead screw 11 servo motor 10's output shaft, adjusting arm 4 is connected with motor cabinet 14.

Specifically, a mounting groove is formed in one side, close to the sleeve 15, of the motor base 14, and the outer edge of one side, close to the motor base 14, of the sleeve 15 protrudes outwards to form a fixed disc which is inserted into the mounting groove; along the axis of the screw rod 11, from being close to servo motor 10 to keeping away from the direction of motor 10, the outer wall of screw rod is spacing screw thread section 31, smooth section 32 and the drive screw thread section of cooperating with slider 1 in proper order, its spacing screw thread section 31 and smooth section 32 all are located sleeve 15, spacing screw thread section 31 and spacing nut 34 cooperation, the cover is equipped with two angular contact ball bearing 35 on smooth section 32, the screw rod 11 passes through angular contact ball bearing 35 and forms the revolute pair with sleeve 15, specifically, angular contact ball bearing 35's internal diameter and smooth section 32 interference fit, angular contact ball bearing 35's external diameter and sleeve 15's internal diameter interference fit.

One end of the screw rod 11 close to the servo motor 10 is provided with a non-circular hole 33 matched with the output shaft of the servo motor, and the shape and the size of the cross section of the non-circular hole are consistent with those of the cross section of the output shaft 36 of the servo motor. Preferably the non-circular hole 33 is a semi-circular hole.

preferably, the adjustment arm 4 is integrally formed with the motor mount 14.

Example 7

The present embodiment is a description of a second embodiment of the drive mechanism.

The utility model discloses in, actuating mechanism is the pneumatic cylinder, and its piston rod is terminal to be connected with slider 1, and its cylinder body is connected with the adjustment arm.

Example 8

the embodiment is specifically described for the rotary connection between the slider 1 and the rudder blade rocker.

As shown in fig. 9, in the present invention, the hinge shaft 26 is provided on the slider, the mounting hole 41 matched with the hinge shaft 26 is provided on the rudder blade rocker 2, the bearing a27 is provided in the mounting hole, and the inner ring and the outer ring of the bearing a27 are respectively in interference fit with the hinge shaft 26 and the mounting hole.

bearing a27 is preferably a deep groove ball bearing.

Example 9

The present embodiment is specifically described for the hinge connection of the adjustment arm 4 to the pin 16.

As shown in fig. 9, in the present invention, the adjusting arm 4 is hinged to the fixing plate 3 through a pin 16, the rod end of the pin 16 sequentially passes through the fixing plate 3 and the adjusting arm 4, an annular groove 18 is provided on one side of the sidewall of the pin 16 close to the rod end, and a retaining ring 17 is clamped in the annular groove 18.

an arm hinge hole 39 is formed in the fixed plate 3, a pin hole 40 is formed in the adjusting arm 4, and the pin 37 is clamped with the retainer ring 17 after passing through the arm hinge hole 39 and the pin hole 40 in sequence.

Example 10

The present embodiment is further explained for the fixing structure between the adjusting device and the rudder nacelle housing 42.

As shown in the figure, in the utility model, be provided with solid fixed ring 43 in the inner chamber of rudder cabin shell 42, the axis of solid fixed ring 43 coincides with the axis of rudder cabin shell 42, and its outer wall passes through the fastener to be connected with rudder cabin shell 42, keep away from one side and rudder cabin shell 42 fixed connection of adjusting arm 4 on the fixed plate 3.

the fixing ring 43 is integrally formed with the fixing plate 3.

Example 11

The embodiment is to explain the number of the rudder blade assemblies.

As shown in fig. 2-3, the rudder blade assembly has three and is symmetrical about the axis of the rudder nacelle housing 42, i.e., the center of the aircraft's flight direction.

Example 12

When being servo motor and lead screw 11 to actuating mechanism, the utility model discloses an assembly method as follows:

s1, assembling a motor and a lead screw:

S1.1, installing a sliding block 1 on a lead screw 11 and connecting the sliding block with a driving thread section of the lead screw 11 in a threaded manner;

S1.2, inserting one end, provided with a limiting thread section, of the lead screw 11 into the sleeve 15 from the cylinder bottom of the sleeve 15, installing an angular contact bearing 35 and a smooth section 32 of the lead screw 11, installing a limiting nut in the limiting thread section of the lead screw, enabling the axis of the lead screw 11 to be overlapped with the axis of the sleeve 15, and enabling the lead screw to be in rotary connection with the sleeve 15 through the angular contact bearing 35;

s1.3, sequentially contacting a servo motor 10, a motor base 14 and a sleeve 15, inserting an output shaft of the servo motor 10 into the sleeve 15 after penetrating through the motor base 10, and inserting the output shaft into a non-circular hole 33 on the end face of a screw rod 11 to ensure torque transmission;

S1.4, a screw B13 sequentially penetrates through the outer edge of the sleeve 15 and the motor base 14 and then is in threaded connection with the shell of the servo motor 10,

s2, assembling the rudder blade rocker 2 and the fixed plate 3:

S2.1, assembling the bearing B on the rudder shaft 5, and then assembling the outer wall of the bearing B in a rudder shaft hole 37 on the fixed plate 3;

S2.2, fixing one end of the rudder blade rocker 2 to the lower end of the rudder shaft 5 through a screw A9;

S2.3, fixing the potentiometer seat 20 on the fixing plate 3 through a screw C21, fixing the potentiometer 19 on the potentiometer seat 20 through a screw D22, and ensuring that a square shaft 24 of the potentiometer 19 is clamped in a square groove 23 of the rudder piece rocker arm 2 and the square shaft 24 is coaxial with the rudder shaft 5;

S3, assembling the servo motor 10 and the fixing plate 3:

S3.1, a pin 16 sequentially penetrates through an arm hinge hole in the fixed plate 3 and a small hole 40 in the adjusting arm 4, so that the adjusting arm 4 is hinged with the fixed plate 3;

S3.2, assembling a deep groove ball bearing A27 on a hinge shaft 26 on the sliding block 1, and then installing the outer wall of a bearing A27 on an installation hole 41 on the steering engine rocker arm 2, so that one end of the rudder piece rocker arm 2 is rotatably connected with the hinge shaft 26 on the sliding block 1 through the bearing A27;

S3.3, mutually adjusting the assembly of S3.1 and S3.2 until the check ring 17 is installed on the annular groove 18 of the pin 16 after the servo motor 10 is fixed to an ideal position;

S4, repeating the steps S1-S3, and assembling the other two rudder piece adjusting devices;

s5, placing the fixing ring 43 into the rudder cabin shell 42, fixedly connecting the fixing ring 43 with the rudder cabin shell 42 by using screws, and enabling each through groove 7 to be opposite to a rudder sheet mounting through hole on one rudder cabin shell 42 respectively;

S6, inserting one end, far away from the rudder sheet 30, of the connecting block 28 into the mounting through groove 7 after penetrating through a through hole in the rudder cabin shell 42, and fixing the connecting block 28 in the mounting through groove through a screw E29;

And S7, repeating the step S6, and assembling the other two rudder pieces.

Assembling tools: a cross screwdriver, a clamp spring clamp, an adjustable spanner and the like.

the above description is only for the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can be covered within the protection scope of the present invention without the changes or substitutions conceived by the inventive work within the technical scope disclosed by the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope defined by the claims.

Claims (10)

1. Aviation aircraft, including aircraft body (44), aircraft body (44) are including hood (45), battery cabin (46), front wing cabin (47), control cabin (48) and the steering wheel that connects gradually, the steering wheel includes rudder cabin shell (42) and a plurality of rudder piece subassembly of being connected with control cabin (48), the rudder piece subassembly includes rudder piece (30) and fixes the inside rudder piece adjusting device in rudder cabin shell (42), the root of rudder piece (30) is passed and is connected its characterized in that with rudder piece adjusting device behind rudder cabin shell (42): the rudder piece adjusting device comprises a linear driving mechanism, a slide block (1), a rudder piece rocker (2), a fixed plate (3), an adjusting arm (4) and a rudder shaft (5), one side of the fixed plate (3) is fixedly connected with the rudder cabin shell (42), the rudder shaft (5) is rotatably connected with the fixed plate (3), one end of the rudder shaft (5) far away from the axis of the rudder cabin shell (42) is connected with the root of the rudder blade (30), the other end of the rudder shaft (5) is connected with one end of the rudder blade rocker (2), the other end of the rudder blade rocker (2) is hinged with the sliding block (1), the driving mechanism drives the sliding block (1) to reciprocate, one end of the adjusting arm (4) is hinged with one side of the fixed plate (3), the other end of the adjusting arm (4) is connected with the shell of the driving device, and the hinged axes are all parallel to the axis of the rudder shaft (5), and the sliding block (1) moves in a plane vertical to the axis of the rudder shaft (5).

2. The aerial vehicle of claim 1, wherein: one end of the rudder shaft (5) far away from the axis of the rudder cabin shell (42) is provided with a fixed block (6), the bottom of the fixed block (6) is connected with the rudder shaft (5), the top of the fixed block is provided with a through groove (7), the bottom of the through groove is provided with a plurality of threaded holes (8), a T-shaped block (28) is arranged at the root of the rudder sheet (30), the tail end of the middle vertical section of the T-shaped block (28) is connected with the rudder sheet (30), the horizontal section of the T-shaped block (28) is inserted into the through groove (7) and is fixed at the top of the rudder shaft (5) through a plurality of screws E (29), and the screws E (29) are respectively in threaded connection with one threaded hole (8) after passing through the horizontal section.

3. The aerial vehicle of claim 1, wherein: one side that rudder axle (5) were kept away from in rudder piece rocking arm (2) is provided with angle sensor assembly, is provided with square groove (23) on rudder piece rocking arm (2) on the side of keeping away from rudder axle (5), angle sensor assembly includes potentiometre (19), potentiometre seat (20) and screw C (21) and screw D (22), screw C (21) are fixed potentiometre (19) on potentiometre seat (20), screw D (22) are fixed potentiometre seat (20) on fixed plate (3), the axis of potentiometre (19) and the axis coincidence of rudder axle (5), and collection end (24) of potentiometre (19) are the square shaft, and it inserts in square groove (23) after passing abdication hole (25) on potentiometre seat (20).

4. The aerial vehicle of claim 3, wherein: the square groove (23) is a through groove, and the groove walls on the two sides of the square groove are in contact with the acquisition end (24).

5. The aerial vehicle of claim 1, wherein: the driving mechanism comprises a servo motor (10) and a screw rod (11), an output shaft of the servo motor (10) is connected with one end of the screw rod (11), the screw rod (11) is in threaded connection with the sliding block (1), and the adjusting arm (4) is connected with a shell of the motor (10).

6. The aerial vehicle of claim 5, wherein: and an anti-falling stop block (12) is arranged at one end of the screw rod (11) far away from the servo motor (10).

7. the aerial vehicle of claim 5, wherein: be provided with coupling assembling between servo motor (10) and lead screw (11), coupling assembling includes motor cabinet (14), sleeve (15) and screw B (13), the one end that is close to servo motor (10) on lead screw (11) inserts in sleeve (15) to rotate with sleeve (15) and be connected, screw B (13) pass outer fringe, motor cabinet (14) of sleeve (15) back in proper order and the shell threaded connection of servo motor (10), insert after passing motor cabinet (14) and be connected with lead screw (11) servo motor's (10) output shaft, adjusting arm (4) are connected with motor cabinet (14).

8. The aerial vehicle of any of claims 1-7, wherein: the rudder blade rocker arm (2) is provided with a mounting hole matched with the hinge shaft (26), a bearing A (27) is arranged in the mounting hole, and the inner ring and the outer ring of the bearing A (27) are in interference fit with the hinge shaft (26) and the mounting hole respectively.

9. the aerial vehicle of any of claims 1-7, wherein: adjusting arm (4) are articulated with fixed plate (3) through pin (16), the pole portion end of pin (16) passes fixed plate (3) and adjusting arm (4) in proper order, is provided with ring channel (18) near the terminal one side of pole portion on the lateral wall of pin (16), blocks in ring channel (18) and is equipped with retaining ring (17).

10. The aerial vehicle of any of claims 1-7, wherein: a fixing ring (43) is arranged in an inner cavity of the rudder cabin shell (42), the axis of the fixing ring (43) is overlapped with the axis of the rudder cabin shell (42), the outer wall of the fixing ring is connected with the rudder cabin shell (42) through a fastening piece, and one side, far away from the adjusting arm (4), of the fixing plate (3) is fixedly connected with the rudder cabin shell (42).