CN110001927B - Rudder sheet adjusting device, steering engine and aircraft thereof - Google Patents
Rudder sheet adjusting device, steering engine and aircraft thereof Download PDFInfo
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- CN110001927B CN110001927B CN201910253215.7A CN201910253215A CN110001927B CN 110001927 B CN110001927 B CN 110001927B CN 201910253215 A CN201910253215 A CN 201910253215A CN 110001927 B CN110001927 B CN 110001927B
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- 238000009434 installation Methods 0.000 claims 2
- 230000005540 biological transmission Effects 0.000 description 11
- 230000000712 assembly Effects 0.000 description 5
- 238000000429 assembly Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000005484 gravity Effects 0.000 description 3
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- 230000002441 reversible effect Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/40—Transmitting means with power amplification using fluid pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Automation & Control Theory (AREA)
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Abstract
The invention discloses a rudder piece adjusting device, a steering engine and an aircraft thereof, which comprise a linear driving mechanism, a sliding block, a rudder piece rocker arm, a fixed plate, an adjusting arm and a rudder shaft, wherein the rudder shaft is rotationally connected with the fixed plate, one end of the rudder piece rocker arm is connected with the rudder shaft, the other end of the rudder piece rocker arm is hinged with the sliding block, the driving mechanism drives the sliding block to reciprocate, one end of the adjusting arm is hinged with one side of the fixed plate, and the other end of the adjusting arm is connected with a shell of the driving device. The invention not only cancels one connecting rod in the existing connecting rod type adjusting component, simplifies the structure of the adjusting component, reduces the weight of the adjusting component, breaks through the traditional inertia thinking of fixing the linear driving mechanism on a part, creatively fixes the driving mechanism on the fixed plate in a hinged manner, and matches the required position of the sliding block in the rotating position of each rudder piece rocker arm by enabling the driving mechanism to rotate around the hinging axis between the driving mechanism and the fixed plate.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a rudder piece adjusting device, a steering engine and an aircraft thereof.
Background
An aircraft is an instrumental flyer manufactured by a human being, capable of flying off the ground, flying in space, and flying in space inside or outside the atmosphere under control of the human being. Steering engines are one of the most important components on an aircraft. In the aspect of aerospace, the steering engine is widely applied, and the pitching, yawing and rolling movements of the attitude transformation of the aircraft are completed by the mutual matching of the steering engines.
In the steering engine, each rudder piece is controlled by an adjusting component. The adjusting component controls the rotating angle of the rudder piece, thereby realizing the adjustment of the flight direction of the aircraft. When the adjusting component directly adopts the motor and the gear to rotate the rudder shaft of the rudder blade, noise is generated due to gear transmission, and the monitoring system is not beneficial to collecting the working condition sounds of the aircraft to analyze the state of the aircraft. On the premise of a certain manufacturing cost, gear noise is an unavoidable defect of the gear type rudder shaft driving device.
The prior art CN108286918A discloses a multi-axis driven annular rudder control device. Although the prior art cancels gear transmission, adopts an adjusting component composed of a motor, a screw rod, a shifting fork and a nut, the motor drives the screw rod to rotate, the screw rod drives the screw rod to axially move, 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, as the notch is open, the nut can only drive the shifting fork to one side far away from the motor, but the shifting fork cannot be pulled back, so that the rudder shaft can only rotate in one direction, cannot rotate reversely, and cannot meet the basic functional requirement of the forward and reverse rotating rudder shaft; meanwhile, the rotation of the rudder shaft in two directions can be realized through the shifting fork in time, but in the matching mode of the shifting fork and the nut, when the matching clearance is too small, the action lock can be generated, and the shifting fork can not be pushed smoothly; when the gap is too large, the shape and distance 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 accurately controlled.
Furthermore, prior art CN106976550a discloses an aircraft gas rudder and air rudder linkage. The prior art also cancels gear transmission, the adjusting component of the rudder piece comprises a screw nut, an action rod and a cam which are hinged in sequence, the screw nut is matched with the 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 component has extremely low transmission noise compared with gear drive and shifting fork drive, the stability of transmission can be ensured, and adverse factors such as forming errors and the like can not be generated. However, the transmission chain of the link mechanism type adjusting component is too long, so that the transmission error can be increased, the volume and the gravity of the rudder piece driving device can be increased, and the link mechanism type driving mechanism can not be smoothly developed on the fly.
Disclosure of Invention
The invention aims at: the rudder piece adjusting device, the steering engine and the aircraft thereof solve the problems that the transmission error is increased and the volume and the gravity of a driving mechanism are also increased due to overlong transmission chain of the traditional connecting rod mechanism type driving assembly for the rudder piece.
In the prior art, if an action rod connecting a screw nut and a cam is directly canceled, the screw nut is directly hinged with the cam, at the moment, the screw nut is fixed relative to the rotation center of the cam because of the fact that the driving motor is fixed relative to the rotation center of the cam, and at the moment, the screw nut has one position, so that the screw nut is positioned on the screw and is hinged with the cam; at this time, the screw nut cannot move, and the cam cannot rotate around its own rotation center. The screw nut and the steering shaft cannot be moved and rotated although the size and the weight of the screw can be reduced by removing one connecting rod, so that the position of the motor needs to be synchronously adjusted along with the movement of the screw nut, and the screw nut can be hinged with the cam and can also move along the screw as a driving piece. 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 whole structure of the linkage mechanism type driving mechanism, and is contrary to the technical problem to be solved at first.
The adjusting device for the rudder sheet of the aircraft, which is designed by the invention, breaks through the traditional inertia thought of fixing the linear driving mechanism on a part on the basis of canceling one connecting rod in the traditional connecting rod type adjusting assembly, creatively fixes the driving mechanism on the part supporting the rudder shaft, namely the fixing plate, and the fixing plate is fixed on the shell of the aircraft, and the driving mechanism can rotate around the hinge axis between the driving mechanism and the fixing plate. Specifically, when the screw rod drives the sliding block to move, as the rudder piece rocker arm can only rotate around the axis of the rudder shaft, and meanwhile the sliding block needs to move along the axial direction of the screw rod, the sliding block rotates around the rudder shaft together with the rocker arm under the drive of the screw rod, and simultaneously the sliding block rotates the linear driving mechanism around the axis of the hinge part between the driving mechanism and the fixed plate under the guide of the rudder piece rocker arm, so that the output end of the driving mechanism is continuously adjusted to be matched with the rotation of the sliding block, and the movement mode of the sliding block is planar movement: the slider moves linearly relative to the drive mechanism, and the slider rotates relative to the rudder piece rocker about the rotation axis of the rudder piece rocker, i.e., the axis of the rudder shaft.
The technical scheme adopted by the invention is as follows:
the utility model provides a rudder piece adjusting device, includes linear driving mechanism, slider, rudder piece rocking arm, fixed plate, regulating arm and rudder axle, the rudder axle rotates with the fixed plate and is connected, the one end and the rudder axle of rudder piece rocking arm are connected, and the other end and the slider of rudder piece rocking arm are articulated, driving mechanism drive slider reciprocates, one end and the one side of fixed plate of regulating arm are articulated, and the other end and the drive arrangement's of regulating arm shell are connected, just articulated axis is all parallel to the axis of rudder axle, and the slider removes in the plane of the axis of perpendicular to rudder axle.
The linear driving mechanism includes, but is not limited to, a linear motor, a combination of a servo motor and a screw rod, a pneumatic cylinder, a hydraulic cylinder, and the like. In the invention, the designed thrust and lift devices of the aircraft can adopt the existing aircraft power devices such as ducted fans, propeller devices or the combination of the ducted fans and the propeller devices.
When the rudder blade is used, the rudder blade is integrally positioned in the inner shell of the steering engine of the aircraft, the connecting block at the root of the rudder blade penetrates through the rudder shell and then is connected with the rudder shaft, and the fixing plate is fixed on the inner wall of the rudder shell. When the rudder blade is required to rotate in the forward direction, the driving mechanism is started to enable the sliding block to move in the forward direction relative to the driving direction of the driving mechanism, at the moment, the rudder blade rocker rotates around the rudder shaft under the pushing of the sliding block, and meanwhile, the driving mechanism rotates around the axis of the hinging part between the driving mechanism and the fixed plate so as to match the position adjustment required by the rotation of the sliding block around the rudder shaft; when the rudder blade is required to be reversely rotated, the driving mechanism is started to enable the sliding block to reversely linearly move along the driving direction of the driving mechanism, at the moment, the rudder blade rocker arm reversely rotates around the rudder shaft under the pushing of the sliding block, and meanwhile, the driving mechanism rotates around the axis of the hinge joint 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.
In summary, the rudder blade adjusting device designed by the invention not only cancels one connecting rod in the existing connecting rod type adjusting assembly, simplifies the structure of the adjusting assembly and reduces the weight of the adjusting assembly, but also breaks through the traditional inertia thinking of fixing the linear driving mechanism on a part, creatively fixes the driving mechanism on the fixed plate in a hinged manner, and matches the required position of the sliding block in the rotating position of each rudder blade rocker arm by enabling the driving mechanism to rotate around the hinging axis between the driving mechanism and the fixed plate without adding other driving devices to solve the matching adjustment of the position of the motor.
The utility model provides a steering engine, includes rudder cabin shell and a plurality of rudder piece subassembly, the rudder piece subassembly includes the rudder piece and fixes the rudder piece adjusting device in the inside of rudder cabin shell, the root of rudder piece passes behind the rudder cabin shell and is connected with rudder piece adjusting device, rudder piece adjusting device adopts foretell adjusting device, one side and the rudder cabin shell fixed connection of fixed plate, the epaxial one end of keeping away from rudder cabin shell axis of rudder is connected with the root of rudder piece, and the other end of rudder axle is connected with the one end of rudder piece rocking arm.
The steering engine designed by the invention not only cancels one connecting rod in the existing connecting rod type adjusting component, simplifies the structure of the adjusting component and reduces the weight of the adjusting component, but also breaks through the traditional inertia thinking of fixing the linear driving mechanism on a component, creatively fixes the driving mechanism on the fixed plate in a hinged manner, and matches the rotation position of each rudder piece rocker arm by enabling the driving mechanism to rotate around the hinge axis between the driving mechanism and the fixed plate, so that the position required by the sliding block is not required to be increased, the matching adjustment of the position of a motor is not required to be solved, the stability of the steering engine is improved, and the weight of the steering engine is reduced.
The utility model provides an aircraft, includes the aircraft body, the aircraft body is including hood, battery compartment, front wing cabin, control storehouse and the steering wheel that connects gradually, the steering wheel adopts foretell steering wheel, and rudder cabin shell in the steering wheel is connected with control storehouse.
The aircraft designed by the invention not only eliminates one connecting rod in the existing connecting rod type adjusting assembly, simplifies the structure of the adjusting assembly and reduces the weight of the adjusting assembly, but also breaks through the traditional inertia thinking of fixing the linear driving mechanism on a part, creatively fixes the driving mechanism on the fixed plate in a hinged manner, and matches the rotating position of each rudder piece rocker arm by enabling the driving mechanism to rotate around the hinging axis between the driving mechanism and the fixed plate, so that the position required by the sliding block is not required to be increased, the matching adjustment of the position of a motor is not required to be solved, the whole weight of the aircraft is reduced, and the whole performance of the aircraft is improved.
Due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the rudder sheet adjusting device not only cancels one connecting rod in the traditional connecting rod type adjusting assembly, simplifies the structure of the adjusting assembly and reduces the weight of the adjusting assembly, but also breaks through the traditional inertia thinking of fixing the linear driving mechanism on a part, creatively fixes the driving mechanism on the fixed plate in a hinged manner, and matches the required position of the sliding block in the rotating position of each rudder sheet rocker arm by enabling the driving mechanism to rotate around the hinging axis between the driving mechanism and the fixed plate without adding other driving devices to solve the matching adjustment of the position of the motor;
2. according to the steering engine, the stability of the steering engine is improved, and the weight of the steering engine is reduced;
3. the rudder piece adjusting device reduces the weight of the whole aircraft and improves the performance of the whole aircraft;
4. the invention is used for an adjusting device of an aircraft rudder piece, and the square groove is a through groove so as to reduce the processing cost; if the rudder piece rocker arm is directly processed into a square groove with the cross section shape consistent with the shape and the size of the cross section of the acquisition end, when the volume of the aircraft is smaller, the corresponding rudder piece rocker arm is smaller, and a smaller groove and inconvenience are caused on the rudder piece rocker arm, so that the processing cost is increased; the square groove is arranged into the through groove, so that the through groove can be machined only by multiple linear feed, the square groove structure can be machined conveniently, and the production cost is reduced.
Drawings
For a clearer description of the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and should not be considered as limiting the scope, for those skilled in the art, without performing creative efforts, other related drawings may be obtained according to the drawings, where the proportional relationships of the components in the drawings in the present specification do not represent the proportional relationships in actual material selection design, and are merely schematic diagrams of structures or positions, where:
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a top view of the present invention;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a schematic view of the invention in connection with rudder pieces;
FIG. 5 is an exploded view of the rudder-containing sheet of the present invention;
FIG. 6 is a schematic top view of the present invention in an initial state;
FIG. 7 is a schematic view of the rudder blade of FIG. 6 in a forward rotated position;
FIG. 8 is a schematic view of the rudder blade of FIG. 6 in a reverse rotated position;
FIG. 9 is a schematic structural view of a steering engine;
FIG. 10 is a schematic view of the rudder trunk housing of FIG. 9;
FIG. 11 is a schematic structural view of a retaining ring;
fig. 12 is a schematic structural view of an aircraft.
The reference numerals in the drawings indicate:
the steering engine comprises the following components of a 1-sliding block, a 2-rudder piece rocker arm, a 3-fixed plate, a 4-adjusting arm, a 5-rudder shaft, a 6-fixed block, a 7-through groove, an 8-threaded hole, a 9-screw A, a 10-servo motor, an 11-screw rod, a 12-anti-disengaging stop, a 13-screw B, a 14-motor seat, a 15-sleeve, a 16-pin, a 17-retainer ring, an 18-annular groove, a 19-potentiometer, a 20-potentiometer seat, a 21-screw C, a 22-screw D, a 23-square groove, a 24-collecting end, a 25-yielding hole, a 26-hinge shaft, a 27-bearing A, a 28-connecting block, a 29-screw E, a 30-rudder piece, a 31-limiting threaded section, a 32-smooth section, a 33-non-round hole, a 34-limiting nut, a 35-angular contact ball bearing, a 36-output shaft, a 37-shaft hole, a 38-bearing B, a 39-arm hinge hole, a 40-pin hole, a 41-mounting hole, a 42-rudder cabin shell, a 43-fixed ring, a 44-aircraft body, 45-46-battery cabin hood, a 47-front cabin hood, and a 48-front control cabin.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the particular embodiments described herein are illustrative only and are not intended to limit the invention, i.e., the embodiments described are merely some, but not all, of the embodiments of the invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. The terms of directions such as up, down, left, right, etc. used for describing the present invention are merely explained with respect to the illustrated structure, and are not necessarily limited in actual use.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by a person skilled in the art without making any inventive effort, are intended to be within the scope of the present invention.
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Example 1
A rudder blade adjusting device will be described in detail with reference to fig. 1 to 8.
As shown in fig. 1-8, the adjusting device for the rudder blade of the aircraft comprises a linear driving mechanism, a sliding block 1, a rudder blade rocker 2, a fixed plate 3, an adjusting arm 4 and a rudder shaft 5, wherein the rudder shaft 5 is rotationally connected with the fixed plate 3, one end of the rudder blade rocker 2 is connected with the rudder shaft 5, 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 a shell of the driving device, the hinged axes are parallel to the axis of the rudder shaft 5, and the sliding block 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, a pneumatic cylinder, a hydraulic cylinder, and the like.
When the rudder blade is used, the rudder blade is integrally positioned in the inner shell of the steering engine of the aircraft, the connecting block at the root of the rudder blade penetrates through the rudder shell and then is connected with the rudder shaft 5, and the fixing plate 3 is fixed on the inner wall of the rudder shell. When the rudder blade needs to be rotated in the forward direction, the driving mechanism is started to enable the sliding block 1 to move in the forward direction relative to the driving direction of the driving mechanism, at the moment, the sliding block moves to the side far away from the driving mechanism, the rudder blade rocker rotates around the rudder shaft 5 under the pushing of the sliding block 1, and meanwhile, the driving mechanism rotates around the axis of the hinge part between the driving mechanism and the fixed plate 3 under the pulling of the rudder blade rocker 2 so as to match the position adjustment required when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 7; when the rudder blade is required to be reversely rotated, the driving mechanism is started to enable the sliding block 1 to reversely linearly move along the driving direction of the driving mechanism, at the moment, the sliding block moves to the side close to the driving mechanism, the rudder blade rocker is reversely rotated around the rudder shaft 5 under the pushing of the sliding block 1, and meanwhile, the driving mechanism rotates around the axis of the hinge part between the driving mechanism and the fixed plate 3 under the pulling of the rudder blade rocker 2 so as to match the position adjustment required when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 8.
In summary, the invention not only eliminates one connecting rod in the existing connecting rod type adjusting assembly, simplifies the structure of the adjusting assembly, reduces the weight of the adjusting assembly, breaks through the traditional inertia thinking of fixing the linear driving mechanism on a part, creatively fixes the driving mechanism on the fixed plate in a hinged manner, and matches the required position of the sliding block in the rotating position of each rudder piece rocker arm by enabling the driving mechanism to rotate around the hinging axis between the driving mechanism and the fixed plate without adding other driving devices to solve the matching adjustment of the position of the motor.
The forward and reverse rotation angles of the rudder piece are alpha, and the value of alpha is 10-45 degrees, preferably 25 degrees.
Example 2
The embodiment is specifically described for the rotary connection of the rudder shaft 5 and the fixed plate 3.
As shown in fig. 3, in the present invention, the rudder shaft 5 is rotatably connected to the fixed plate 3 by the following scheme: the fixed plate 3 is provided with a rudder shaft hole 37, bearings B38 are arranged at the upper end and the lower end of the rudder shaft hole 37, the bearings B38 are preferably deep groove ball bearings, the inner diameter of the deep groove ball bearings is in interference fit with the rudder shaft 5, and the outer diameter of the deep groove ball bearings is in interference fit with the rudder shaft hole 37.
The rudder shaft hole 37 comprises a small-diameter hole and large-diameter holes at the upper end and the lower end of the small-diameter hole, and the bearing B38 is respectively clamped into one large-diameter hole and is in interference fit with the wall of the large-diameter hole.
The rotary connection of all parts in the invention mainly adopts a shaft hole matching mode, and bearings are correspondingly arranged in the shaft hole matching, so that the friction coefficient is reduced.
Example 3
In this embodiment, a structure in which a rudder blade is attached to a rudder shaft 5 is specifically described.
As shown in fig. 1 to 4, in the present invention, a fixed block 6 is disposed at the top of the rudder shaft 5, the bottom of the fixed block 6 is connected to the rudder shaft 5, the top of the fixed block is provided with a mounting through groove 7, and the bottom of the mounting through groove is provided with a plurality of threaded holes 8.
The connecting block 28 at the root of the rudder blade is inserted into the mounting through groove 7 and is fixed in the through groove 7 by a screw E29.
The rudder piece 30 is fixed through the mounting through 7, so that the connecting block 28 can be limited through the groove walls at two sides of the mounting through groove 7 when the screw E is used for fixing the connecting block 28, the shearing force born by the screw E is reduced when the rudder piece is stressed, and the service life of the adjusting device is prolonged.
Preferably, the connecting block 28 is a T-shaped block, the middle vertical part of the connecting block is connected with the root of the rudder piece 30, four screws E29 are symmetrically distributed on two sides of the connecting block 28 in a group, and the screws E29 penetrate through the horizontal section of the bottom of the T-shaped block and are in threaded connection with the threaded holes 8.
Preferably, the rudder piece rocker arm 2 is located at the bottom of the rudder shaft 5, the bottom end of the rudder shaft 5 penetrates through the fixing plate 3 and then is connected with the rudder piece rocker arm 2, and the rudder piece rocker arm 2 is connected with the bottom of the rudder shaft 5 through a screw A9.
Since the top of the rudder shaft 5 needs to be connected to the rudder piece, and in order to facilitate the disassembly and assembly of the present invention, it is preferable that the rudder piece rocker arm 2 is provided at the bottom of the rudder shaft 5 and connected to the rudder shaft 5 by a screw A9.
The rudder shaft 5 is formed integrally with the fixed block 6, so that the cross-sectional view of fig. 3 does not show the projection line of the contact surface between them.
Example 4
The present embodiment is to explain the present invention in terms of monitoring the rotation angle of the rudder shaft 5 in practical use.
In the present invention, as shown in fig. 5, an angle sensor assembly is disposed at the bottom of the rudder blade rocker 2, a square groove 23 is disposed at the bottom of the rudder blade rocker 2, the angle sensor assembly includes a potentiometer 19, a potentiometer seat 20, a screw C21 and a screw D22, the screw C21 fixes the potentiometer 19 on the potentiometer seat 20, the screw D22 fixes the potentiometer seat 20 on the fixed plate 3, the axis of the potentiometer 19 coincides with the axis of the rudder shaft 5, the collecting end 24 of the potentiometer 19 is a square shaft, and the collecting end is inserted into the square groove 23 after passing through a relief hole 25 on the potentiometer seat 20.
Preferably, the square groove 23 is a through groove, and the groove walls on two sides of the square groove are contacted with the collecting end 24.
The potentiometer is a typical contact absolute angle sensor, and is provided with a sliding contact on a resistor film, and the position of the contact is changed by external action so as to change the ratio of the upper resistance to the lower resistance of the resistor film, thereby realizing that the voltage of an output end changes along with the external position. The potentiometer is composed of an electronic element and a cursor, wherein the cursor can slide on the surface of the element and is in a linear sliding type or a rotary type. The former is used to detect linear displacement, and the latter is used to detect angle, tilt angle, etc. The output end of the potentiometer is connected with a controller of the aircraft. When the rudder blade is required to rotate, inputting a rotation angle instruction to the controller, and starting the driving mechanism by the controller according to the instruction so as to enable the driving mechanism to work and enable the rudder shaft to drive the rudder blade to rotate; the acquisition end 24 of the potentiometer rotates with the rotation of the rocker arm 2 and sends the acquired signal to the controller.
In the invention, the vernier of the potentiometer adopts a rotary vernier, namely the acquisition end 24, which is in a non-circular structure such as a square shaft, a flat shaft and the like. When the collection end is a square shaft, a pair of opposite side walls of the collection end are respectively contacted with two groove walls of the square groove 23.
The potentiometer 19 is preferably of the type 3590S-2-102L of BOURNS. The potentiometer 19 may be connected to the controller of the aircraft by wired connection, wireless connection, or the like.
The potentiometer 19 is provided to obtain the rotation angle of the rotation shaft 3 more accurately.
The square groove 23 is a through groove in order to reduce the processing cost. If it is directly machined into a square groove with a cross-sectional shape that is consistent with the cross-sectional shape of the collection end 24, when the aircraft is smaller, the corresponding rudder piece rocker arm is smaller, and a smaller groove and inconvenience are machined on the rudder piece rocker arm, which increases the machining cost; the square groove 23 is arranged as a through groove, and the through groove can be machined only by multiple linear feed, so that the square groove 23 is convenient to machine, and the production cost is reduced.
Example 5
This embodiment describes a first embodiment of the drive mechanism.
As shown in fig. 1 to 5, in the invention, 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.
When the sliding block is required to move towards one end far away from the servo motor 10, the servo motor 10 is started, and the 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 is required to move towards the servo motor 10, the servo motor 10 is started, and the output shaft of the servo motor drives the screw rod 11 to reversely rotate, 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 in real time to the control center of the aircraft. The output shaft of the servo motor 10 may be directly connected to the screw 11, or may be connected to the screw 11 through a coupling, a universal joint, or the like.
Further, an anti-drop stop 12 is provided at an end of the screw rod 11 remote from the servo motor 10.
The anti-drop block 12 prevents the slider 1 from coming off from the end of the screw 11 remote from the servomotor 10.
Example 6
In this embodiment, the connection between the screw 11 and the output shaft of the servo motor in embodiment 5 is specifically described.
As shown in fig. 5, in the present invention, a connection assembly is disposed between the servomotor 10 and the screw rod 11, the connection assembly includes a motor base 14, a sleeve 15, and a screw B13, one end of the screw rod 11 near the servomotor 10 is inserted into the sleeve 15 and is rotationally connected with the sleeve 15, the screw B13 sequentially passes through the outer edge of the sleeve 15 and the motor base 14 and then is in threaded connection with the housing of the servomotor 10, the output shaft of the servomotor 10 passes through the motor base 14 and then is inserted into and connected with the screw rod 11, and the adjusting arm 4 is connected with the motor base 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 is outwards protruded to form a fixing disc, and the fixing disc is inserted into the mounting groove; along the axis of lead screw 11, from being close to servo motor 10 to keeping away from the direction of motor 10, the outer wall of lead screw is limit screw thread section 31, smooth section 32 and with slider 1 complex drive screw thread section in proper order, its limit screw thread section 31 and smooth section 32 all are located sleeve 15, limit screw thread section 31 and limit nut 34 cooperation, the cover is equipped with two angular ball bearings 35 on smooth section 32, lead screw 11 passes through angular ball bearings 35 and sleeve 15 formation revolute pair, specifically, angular ball bearings 35's internal diameter and smooth section 32 interference fit, angular ball bearings 35's external diameter and sleeve 15's internal diameter interference fit.
A non-circular hole 33 matched with the output shaft of the servo motor is arranged at one end of the screw rod 11 close to the servo motor 10, 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 aperture 33 is a semi-circular aperture.
Preferably, the adjustment arm 4 is integrally formed with the motor mount 14.
Example 7
This embodiment describes a second embodiment of the drive mechanism.
In the invention, the driving mechanism is a pneumatic cylinder, the tail end of a piston rod of the pneumatic cylinder is connected with the sliding block 1, and the cylinder body of the pneumatic cylinder is connected with the adjusting arm.
Example 8
The embodiment is specifically described for the rotational connection between the slider 1 and the rudder blade rocker.
As shown in fig. 5, in the present invention, the slider is provided with the hinge shaft 26, the rudder piece rocker arm 2 is provided with the mounting hole 41 which is matched with the hinge shaft 26, the mounting hole is provided with the bearing a27, 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
This embodiment is specifically described for the articulation of the adjustment arm 4 with the pin 16.
In the invention, as shown in fig. 5, the adjusting arm 4 is hinged with the fixed plate 3 through a pin 16, the tail end of the rod part of the pin 16 sequentially passes through the fixed plate 3 and the adjusting arm 4, an annular groove 18 is arranged on one side, close to the tail end of the rod part, of the side wall of the pin 16, and a retainer ring 17 is clamped in the annular groove 18.
The fixing plate 3 is provided with an arm hinge hole 39, the adjusting arm 4 is provided with a pin hole 40, and the pin 37 is clamped with the retainer ring 17 after the arm hinge hole 39 and the pin hole 40 are sequentially arranged.
Example 10
On the basis of examples 1-6 and examples 8 and 9, the assembly method of the present invention is as follows:
s1 motor and screw assembly
S1.1, a sliding block 1 is arranged on a screw rod 11 and is in threaded connection with a driving thread section of the screw rod 11;
s1.2, inserting one end of the screw rod 11 provided with a limit thread section into the sleeve 15 from the bottom of the sleeve 15, mounting an angular contact bearing 35 on a smooth section 32 of the screw rod 11, mounting a limit nut on the screw rod limit thread section, enabling the axis of the screw rod 11 to coincide with the axis of the sleeve 15, and enabling the screw rod 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 seat 14 and a sleeve 15, inserting an output shaft of the servo motor 10 into the sleeve 15 after passing through the motor seat 10, and inserting the output shaft into a non-circular hole 33 on the end surface of a screw rod 11 to ensure torque transmission;
s1.4 is connected with the shell of the servo motor 10 by screw B13 after passing through the outer edge of the sleeve 15 and the motor base 14 in sequence,
s2 assembling rudder piece rocker arm 2 and fixing plate 3
S2.1, assembling a bearing B on the rudder shaft 5, and then assembling the outer wall of the bearing B into a rudder shaft hole 37 on the fixed plate 3;
s2.2, one end of the rudder piece rocker arm 2 is fixed to the lower end of the rudder shaft 5 through a screw A9;
s2.3, fixing the potentiometer base 20 on the fixed plate 3 through a screw C21, and fixing the potentiometer 19 on the potentiometer base 20 through a screw D22, so that a square shaft 24 of the potentiometer 19 is clamped into a square groove 23 of the rudder piece rocker 2, and the square shaft 24 is coaxial with the rudder shaft 5;
s3 assembling between the servo motor 10 and the fixed plate 3
S3.1, a pin 16 sequentially passes through an arm hinge hole on the fixed plate 3 and a small hole 40 on the adjusting arm 4 so as to enable the adjusting arm 4 to be hinged with the fixed plate 3;
s3.2, a deep groove ball bearing A27 is assembled on a hinge shaft 26 on the sliding block 1, and then the outer wall of the bearing A27 is installed on a mounting 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 are adjusted to each other during assembly of 3.1 and 3.2 until after the servo motor 10 has been fixed in the desired position, the retainer ring 17 is mounted in the annular groove 18 of the pin 16;
s4, inserting one end, far away from the rudder piece 30, of the connecting block 28 into the mounting through groove 7, and fixing the connecting block 28 in the mounting through groove through a screw E29;
and (3) assembling tools: a cross screwdriver, a clamp spring pliers, an adjustable spanner and the like.
A steering engine will be described in detail with reference to fig. 1 to 11.
Example 11
The embodiment is to make an implementation description for the steering engine.
As shown in fig. 1-11, the steering engine for the aircraft comprises a rudder cabin shell 42 and a plurality of rudder piece assemblies, wherein the rudder piece assemblies comprise rudder pieces 30 and rudder piece adjusting devices fixed inside the rudder cabin shell 42, the root parts of the rudder pieces 30 penetrate through the rudder cabin shell 42 and are connected with the rudder piece adjusting devices, the rudder piece adjusting devices comprise a linear driving mechanism, a sliding block 1, a rudder piece rocker arm 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 rotationally connected with the fixed plate 3, one end, far away from the axis of the rudder cabin shell 42, of the rudder shaft 5 is connected with the root parts of the rudder pieces 30, the other end of the rudder shaft 5 is connected with one end of the rudder piece rocker arm 2, the other end of the rudder piece rocker arm 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 axis is parallel to the axis of the sliding block 1, and the axis of the hinged axis is 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, a pneumatic cylinder, a hydraulic cylinder, and the like.
When the rudder blade needs to be rotated in the forward direction, the driving mechanism is started to enable the sliding block 1 to move in the forward direction relative to the driving direction of the driving mechanism, at the moment, the sliding block moves to the side far away from the driving mechanism, the rudder blade rocker rotates around the rudder shaft 5 under the pushing of the sliding block 1, and meanwhile, the driving mechanism rotates around the axis of the hinge part between the driving mechanism and the fixed plate 3 under the pulling of the rudder blade rocker 2 so as to match the position adjustment required when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 7; when the rudder blade is required to be reversely rotated, the driving mechanism is started to enable the sliding block 1 to reversely linearly move along the driving direction of the driving mechanism, at the moment, the sliding block moves to the side close to the driving mechanism, the rudder blade rocker is reversely rotated around the rudder shaft 5 under the pushing of the sliding block 1, and meanwhile, the driving mechanism rotates around the axis of the hinge part between the driving mechanism and the fixed plate 3 under the pulling of the rudder blade rocker 2 so as to match the position adjustment required when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 8.
In summary, in the steering engine designed by the invention, one connecting rod in the existing connecting rod type adjusting assembly is eliminated, the structure of the adjusting assembly is simplified, the weight of the adjusting assembly is reduced, the traditional inertia thinking of fixing the linear driving mechanism on a part is broken through, the driving mechanism is creatively fixed on the fixed plate, the driving mechanism can rotate around the hinge axis between the driving mechanism and the fixed plate to match the rotating position of each rudder piece rocker arm, the position required by the sliding block is not required to be increased, and the matching adjustment of the position of the motor is solved without adding other driving devices, so that the steering engine has more stable performance, more accurate angle adjustment and lower weight.
Example 12
The present embodiment further describes the fixing structure between the adjusting device and the rudder trunk shell 42.
As shown in the drawing, in the present invention, a fixing ring 43 is disposed in the inner cavity of the rudder cabin shell 42, the axis of the fixing ring 43 coincides 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 fastener, and the side of the fixing plate 3 away from the adjusting arm 4 is fixedly connected with the rudder cabin shell 42.
The fixing ring 43 is integrally formed with the fixing plate 3.
Example 13
The present embodiment is described in terms of the number of embodiments of rudder blade assemblies.
As shown in fig. 9-10, the rudder blade assemblies are three and are centrally symmetrical along the axis of the rudder trunk housing 42, i.e., the direction of flight of the aircraft.
Example 14
When the driving mechanism is a servo motor and a screw rod 11, the steering engine assembly method is as follows:
s1, assembling a motor and a screw rod:
s1.1, a sliding block 1 is arranged on a screw rod 11 and is in threaded connection with a driving thread section of the screw rod 11;
s1.2, inserting one end of the screw rod 11 provided with a limit thread section into the sleeve 15 from the bottom of the sleeve 15, mounting an angular contact bearing 35 and a smooth section 32 of the screw rod 11, mounting a limit nut on the screw rod limit thread section, enabling the axis of the screw rod 11 to coincide with the axis of the sleeve 15, and enabling the screw rod to be in rotary connection with the sleeve 15 through the angular contact bearing 35;
s1.3, sequentially contacting the servo motor 10, the motor base 14 and the sleeve 15, inserting an output shaft of the servo motor 10 into the sleeve 15 after passing through the motor base 10, and inserting the output shaft into a non-circular hole 33 on the end face of the screw rod 11 to ensure torque transmission;
s1.4, the screw B13 sequentially passes through the outer edge of the sleeve 15 and the motor base 14 and is in threaded connection with the shell of the servo motor 10,
s2, assembling the rudder piece rocker arm 2 and the fixing plate 3:
s2.1, assembling a bearing B on the rudder shaft 5, and then assembling the outer wall of the bearing B into a rudder shaft hole 37 on the fixed plate 3;
s2.2, fixing one end of the rudder piece rocker arm 2 to the lower end of the rudder shaft 5 through a screw A9;
s2.3, fixing the potentiometer base 20 to the fixed plate 3 through a screw C21, and fixing the potentiometer 19 to the potentiometer base 20 through a screw D22, so that a square shaft 24 of the potentiometer 19 is clamped into a square groove 23 of the rudder piece rocker 2, and the square shaft 24 is coaxial with the rudder shaft 5;
s3, assembling between the servo motor 10 and the fixed plate 3:
s3.1, a pin 16 sequentially passes through an arm hinge hole on the fixed plate 3 and a small hole 40 on the adjusting arm 4 so as to enable the adjusting arm 4 to be 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 mounting the outer wall of the bearing A27 on a mounting hole 41 on the steering engine rocker arm 2 so that one end of the rudder piece rocker arm 2 is rotationally connected with the hinge shaft 26 on the sliding block 1 through the bearing A27;
s3.3, mutually adjusting when assembling S3.1 and S3.2 until after fixing the servomotor 10 in the desired position, mounting the retainer ring 17 on the annular groove 18 of the pin 16;
s4, repeating the steps S1-S3, and assembling the other two rudder piece adjusting devices;
s5, placing the fixed ring 43 into the rudder cabin shell 42, fixedly connecting the fixed ring 43 with the rudder cabin shell 42 by using screws, and enabling each through groove 7 to be opposite to a rudder piece mounting through hole on one rudder cabin shell 42;
s6, inserting one end, far away from the rudder piece 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;
s7, repeating the step S6, and assembling the other two rudder pieces.
And (3) assembling tools: a cross screwdriver, a clamp spring pliers, an adjustable spanner and the like.
Example 15
The present embodiment is described with respect to an aircraft based on fig. 1-12.
As shown in fig. 1-12, the aviation aircraft comprises an aircraft body 44, wherein the aircraft body 44 comprises a hood 45, a battery compartment 46, a front wing compartment 47, a control compartment 48 and a steering engine which are sequentially connected, the steering engine comprises a rudder cabin shell 42 connected with the control compartment 48 and a plurality of rudder piece assemblies, each rudder piece assembly comprises a rudder piece 30 and a rudder piece adjusting device fixed in the rudder cabin shell 42, the root of each rudder piece 30 passes through the cabin shell 42 and then is connected with the rudder piece adjusting device, the rudder piece adjusting device comprises a linear driving mechanism, a sliding 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 each rudder piece 30, the other end of the rudder shaft 5 is connected with one end of the rudder piece rocker 2, the other end of the rudder piece 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 connected with one side of the fixed plate 3, and the other end of the adjusting arm is perpendicular to the axis of the rudder shaft 5, and the axis of the adjusting arm is perpendicular to the axis of the driving device.
The linear driving mechanism includes, but is not limited to, a linear motor, a combination of a servo motor and a screw rod, a pneumatic cylinder, a hydraulic cylinder, and the like.
When the rudder blade needs to be rotated in the forward direction, starting the driving mechanism to enable the sliding block 1 to move in the forward direction relative to the driving direction of the driving mechanism, enabling the sliding block to move towards the side far away from the driving mechanism, enabling the rudder blade rocker to rotate around the rudder shaft 5 under the pushing of the sliding block 1, and enabling the driving mechanism to rotate around the axis of the hinge part between the driving mechanism and the fixed plate 3 under the pulling of the rudder blade rocker 2 so as to match the position adjustment required when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 10; when the rudder blade is required to be reversely rotated, the driving mechanism is started to enable the sliding block 1 to reversely linearly move along the driving direction of the driving mechanism, at the moment, the sliding block moves to the side close to the driving mechanism, the rudder blade rocker is reversely rotated around the rudder shaft 5 under the pushing of the sliding block 1, and meanwhile, the driving mechanism rotates around the axis of the hinge part between the driving mechanism and the fixed plate 3 under the pulling of the rudder blade rocker 2 so as to match the position adjustment required when the sliding block 1 rotates around the rudder shaft 5, as shown in fig. 11.
In summary, in the steering engine designed by the invention, one connecting rod in the existing connecting rod type adjusting assembly is eliminated, the structure of the adjusting assembly is simplified, the weight of the adjusting assembly is reduced, the traditional inertia thinking of fixing the linear driving mechanism on a part is broken through, the driving mechanism is creatively fixed on the fixed plate, the driving mechanism can rotate around the hinge axis between the driving mechanism and the fixed plate to match the rotating position of each rudder piece rocker arm, the needed position of the sliding block is not needed to be added with other driving devices to solve the matching adjustment of the position of the motor, so that the performance of the steering engine is more stable, the angle adjustment is more accurate, the weight is reduced, the whole weight of the aircraft is reduced, and the whole performance of the aircraft is improved.
The above description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that are not creatively contemplated by those skilled in the art within the technical scope of the present invention should be included in the scope of 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. A rudder piece adjusting device which is characterized in that: including straight-line actuating mechanism, slider (1), rudder piece rocking arm (2), fixed plate (3), adjusting arm (4) and rudder axle (5), rudder axle (5) rotate with fixed plate (3) and are connected, the one end and the rudder axle (5) of rudder piece rocking arm (2) are connected, and the other end and the slider (1) of rudder piece rocking arm (2) are articulated, actuating mechanism drive slider (1) carries out reciprocating motion, one end and one side of fixed plate (3) of adjusting arm (4) are articulated, and the other end and the shell of drive arrangement of adjusting arm (4) are connected, just articulated axis is all parallel to the axis of rudder axle (5), and slider (1) are removed in the plane of the axis of perpendicular to rudder axle (5).
2. A rudder blade adjusting device according to claim 1, wherein: the top of rudder shaft (5) is provided with fixed block (6), the bottom of fixed block (6) is connected with rudder shaft (5), and its top is provided with installation through groove (7), is provided with a plurality of screw holes (8) at the tank bottom of installation through groove (7).
3. A rudder blade adjusting device according to claim 1, wherein: the rudder piece rocker arm (2) is positioned at the bottom of the rudder shaft (5), the bottom end of the rudder shaft (5) penetrates through the fixing plate (3) and then is connected with the rudder piece rocker arm (2), and the rudder piece rocker arm (2) is connected with the bottom of the rudder shaft (5) through the screw A (9).
4. A rudder blade adjusting device according to claim 3, wherein: the rudder piece rocker arm (2) is provided with an angle sensor component at the bottom, the rudder piece rocker arm (2) is provided with a square groove (23), the angle sensor component comprises a potentiometer (19), a potentiometer seat (20), a screw C (21) and a screw D (22), the screw C (21) is used for fixing the potentiometer (19) on the potentiometer seat (20), the screw D (22) is used for fixing the potentiometer seat (20) on the fixed plate (3), the axis of the potentiometer (19) coincides with the axis of the rudder shaft (5), the acquisition end (24) of the potentiometer (19) is a square shaft, and the square shaft penetrates through a yielding hole (25) on the potentiometer seat (20) and then is inserted into the square groove (23).
5. A rudder blade adjusting device according to 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. A rudder blade adjusting device according to 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), in the one end that is close to servo motor (10) on lead screw (11) inserts sleeve (15) to rotate with sleeve (15) and be connected, screw B (13) pass the outer fringe of sleeve (15) in proper order, behind motor cabinet (14) with the shell threaded connection of servo motor (10), insert behind motor cabinet (14) and be connected with lead screw (11) the output shaft of servo motor (10), adjusting arm (4) are connected with motor cabinet (14).
7. A rudder blade adjusting device according to any one of claims 1-6, wherein: the adjusting arm (4) is hinged with the fixed plate (3) through a pin (16), the tail end of the rod part of the pin (16) sequentially penetrates through the fixed plate (3) and the adjusting arm (4), an annular groove (18) is formed in one side, close to the tail end of the rod part, of the side wall of the pin (16), and a retainer ring (17) is clamped in the annular groove (18).
8. The utility model provides a steering engine, includes rudder cabin shell (42) and a plurality of rudder piece subassembly, rudder piece subassembly includes rudder piece (30) and fixes at the inside rudder piece adjusting device of rudder cabin shell (42), the root of rudder piece (30) passes behind rudder cabin shell (42) and is connected its characterized in that: the rudder piece adjusting device is an adjusting device according to any one of claims 1-7, one side of the fixing plate (3) is fixedly connected with the rudder cabin shell (42), one end, far away from the axis of the rudder cabin shell (42), of the rudder shaft (5) is connected with the root of the rudder piece (30), and the other end of the rudder shaft (5) is connected with one end of the rudder piece rocker arm (2).
9. The steering engine of claim 8, wherein: a fixing ring (43) is arranged in an inner cavity of the rudder cabin shell (42), the axis of the fixing ring (43) coincides 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 fastener, and one side, far away from the adjusting arm (4), of the fixing plate (3) is fixedly connected with the rudder cabin shell (42).
10. The utility model provides an aircraft, includes aircraft body (44), aircraft body (44) are including hood (45), battery compartment (46), front wing cabin (47), control storehouse (48) and steering wheel that connect gradually, its characterized in that: the steering engine is the steering engine as claimed in claim 8 or 9, and a steering engine cabin shell (42) in the steering engine is connected with a control cabin (48).
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| CN201910253215.7A CN110001927B (en) | 2019-03-29 | 2019-03-29 | Rudder sheet adjusting device, steering engine and aircraft thereof |
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| CN201910253215.7A CN110001927B (en) | 2019-03-29 | 2019-03-29 | Rudder sheet adjusting device, steering engine and aircraft thereof |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110455132A (en) * | 2019-08-30 | 2019-11-15 | 贵州航天控制技术有限公司 | A kind of small-sized integral type combination control mechanism |
| CN110702354A (en) * | 2019-11-23 | 2020-01-17 | 成都凯迪精工科技有限责任公司 | Blowing model rudder piece mounting structure |
| CN111717371A (en) * | 2020-05-29 | 2020-09-29 | 四川航天燎原科技有限公司 | High-load low-friction gap-eliminating type aircraft steering engine |
| CN112173072A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Control surface control mechanism of high-speed helicopter |
| CN113212736B (en) * | 2021-04-26 | 2024-02-09 | 北京航天控制仪器研究所 | Thin type large-reduction-ratio miniature electric steering engine system |
| CN113280689A (en) * | 2021-06-16 | 2021-08-20 | 重庆航天工业有限公司 | Rudder system |
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