CN218142095U - Steering control mechanism of double vertical tail unmanned aerial vehicle - Google Patents

Abstract

The utility model provides a two vertical fin unmanned aerial vehicle rudder operating mechanism. The rudder control mechanism of the double-vertical-tail unmanned aerial vehicle comprises a horizontal tail wing, a first vertical tail wing, a second vertical tail wing, a first rudder, a second rudder and a driving assembly; first perpendicular fin is connected horizontal fin one side, the perpendicular fin of second is connected the horizontal fin opposite side, first rudder rotates to be installed first perpendicular fin tip, the second rudder rotates to be installed the perpendicular fin tip of second, drive assembly installs on the horizontal fin, just drive assembly drives first rudder with the synchronous rotation of second rudder, the utility model discloses a two functions of two rudders of steering engine drive can be realized to two vertical fin unmanned aerial vehicle rudder steering mechanism, the utility model discloses reduce the weight of the control complete machine that the weight of one set of steering engine can be better, and also can reduce manufacturing and maintenance cost.

Description

Steering control mechanism of double vertical tail unmanned aerial vehicle

Technical Field

The utility model relates to a rudder operating mechanism's technical field, especially two vertical fin unmanned aerial vehicle rudder operating mechanisms.

Background

In the prior art, the control of the double vertical tail rudder surfaces is approximately realized by controlling left and right rudder surfaces by two sets of same control system mechanisms and controlling the rudder surfaces by connecting a steering engine, a swing arm, a pull rod and a rudder surface rudder angle.

The following defects and shortcomings mainly exist: 1. because the control surface load of the large and medium-sized unmanned aerial vehicle is large, the selected steering engine and the steering engine controller are undoubtedly increased in mass and volume, the vertical tail is generally long in the tail force arm of the rear section of the airplane, the influence on the gravity center of the airplane is large, and the counterweight needs to be correspondingly increased, so that the self weight is undoubtedly increased if two sets of control systems are used, and the performance of the airplane is influenced;

2. for large and medium-sized unmanned aerial vehicles, the price of a steering engine or a motor is high, so that the manufacturing cost and the subsequent use and maintenance cost are not controlled;

3. the two sets of control mechanisms have little challenge to the stability synchronism of the control surface, are independently connected with the flight control through respective controllers and depend on the synchronism of the steering engine, the controllers and the flight control;

4. for most of two sets of controllers of airplane types with thinner horizontal tails and vertical tails, the external hanging, the semi-external hanging and the outside of the airplane body are selected, and a larger fairing is required to be manufactured for covering, so that the pneumatic performance of the horizontal tail or the vertical tail of the airplane is influenced, and the resistance is increased.

Therefore, the redesign of a new steering control mechanism of the double vertical tail unmanned aerial vehicle is urgently needed to solve the problem.

SUMMERY OF THE UTILITY MODEL

The utility model provides a two vertical fin unmanned aerial vehicle rudder control mechanisms to solve the technical problem who proposes in the above-mentioned background art.

The utility model provides a rudder control mechanism of a double-vertical-tail unmanned aerial vehicle, which comprises a horizontal tail wing, a first vertical tail wing, a second vertical tail wing, a first rudder, a second rudder and a driving component; first vertical tail is connected horizontal tail one side, the vertical tail of second is connected the horizontal tail opposite side, the first rudder rotates to be installed first vertical tail tip, the second rudder rotates to be installed the vertical tail tip of second, drive assembly installs on the horizontal tail, just drive assembly drives the first rudder with the second rudder synchronous revolution.

Optionally, the driving assembly comprises a steering engine, a first swing arm, a first connecting rod, a second swing arm, a first transmission shaft, a second transmission shaft, a third swing arm, a second connecting rod, a fourth swing arm and a third connecting rod, the steering engine is installed on the horizontal tail wing, one end of the first swing arm is connected with the output end of the steering engine, the other end of the first swing arm is connected with one end of the first connecting rod, the other end of the first connecting rod is connected with the second swing arm, one end of the first transmission shaft is connected with one side of the second swing arm, the other end of the first transmission shaft is connected with the third swing arm, one end of the second connecting rod is connected with the third swing arm, the other end of the second connecting rod is connected with the first rudder, one end of the second transmission shaft is connected with the other side of the second swing arm, the other end of the second transmission shaft is connected with the fourth swing arm, one end of the third connecting rod is connected with the third swing arm, and the other end of the third connecting rod is connected with the second rudder.

Optionally, a first rudder angle used for improving the angle rotation precision of the first rudder is arranged between the first rudder and the second connecting rod, one end of the first rudder angle is rotatably connected with the first rudder, and the other end of the first rudder angle is rotatably connected with the second connecting rod.

Optionally, a first orthodontic rod end bearing used for improving the rotating fit of the second connecting rod with the first rudder angle is arranged at a joint of the second connecting rod and the first rudder angle, and a first anti-orthodontic rod end bearing used for improving the rotating fit of the second connecting rod and the third swing arm is arranged at a joint of the second connecting rod and the third swing arm.

Optionally, a second rudder angle used for improving the angle rotation precision of the second rudder is arranged between the second rudder and the third connecting rod, one end of the second rudder angle is rotatably connected with the second rudder, and the other end of the second rudder angle is rotatably connected with the third connecting rod.

Optionally, a second orthodontic rod end bearing used for improving the rotation matching performance of the third connecting rod and the second rudder angle is arranged at the joint of the third connecting rod and the second rudder angle, and a second anti-orthodontic rod end bearing used for improving the rotation matching performance of the third connecting rod and the fourth swing arm is arranged at the joint of the third connecting rod and the fourth swing arm.

Optionally, the second swing arm includes that the swing arm is connected on the left side and the swing arm is connected on the right side, the swing arm is connected on the left side with swing arm fixed connection is connected on the right side, just the swing arm is connected on the left side with the swing arm tip is connected on the right side all with head rod one end is connected, the swing arm is connected on the left side with first transmission shaft one end is connected, the swing arm is connected on the right side with second transmission shaft one end is connected.

Optionally, the swing arm is connected on the left side with be provided with between the first transmission shaft and be used for improving the swing arm is connected on the left side with the first ring flange of first transmission shaft stability, the swing arm is connected on the right side with be provided with between the second transmission shaft and be used for improving the swing arm is connected on the right side with the second ring flange of second transmission shaft stability.

Optionally, a transmission shaft supporting seat is arranged on the outer side of the first swing arm, the transmission shaft supporting seat is installed on the horizontal tail wing, and the second swing arm is rotatably connected with the transmission shaft supporting seat.

Optionally, the orientation of the third swing arm and the orientation of the fourth swing arm are opposite.

The utility model has the advantages as follows:

the rudder control mechanism of the double-vertical-tail unmanned aerial vehicle comprises a horizontal tail wing, a first vertical tail wing, a second vertical tail wing, a first rudder, a second rudder and a driving assembly; first perpendicular fin is connected horizontal fin one side, the perpendicular fin of second is connected the horizontal fin opposite side, first rudder rotates to be installed first perpendicular fin tip, the second rudder rotates to be installed the perpendicular fin tip of second, drive assembly installs on the horizontal fin, just drive assembly drives first rudder with the synchronous rotation of second rudder, wherein, the utility model discloses a two vertical fin unmanned aerial vehicle rudder operating mechanism can realize the function of two rudders of a steering wheel drive, and the weight of one set of steering wheel and driver is directly effectually subtracted to reliability and uniformity have been improved, can guarantee two rudder face synchronizations and then improve the steering control performance of aircraft through this mode, simultaneously, control the rudder through a plurality of connecting rods transmission torsional force, fine avoiding because the horizontal tail space situation leads to interfering improvement space utilization, furtherly, the utility model discloses reduce the weight of one set of control steering wheel that weight can be better, and also can reduce manufacturing and maintenance cost.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a first viewing angle of a rudder control mechanism of a double-vertical-tail unmanned aerial vehicle provided by the present invention;

fig. 2 is a schematic structural diagram of a second viewing angle of the rudder control mechanism of the double vertical fin unmanned aerial vehicle provided by the present invention;

FIG. 3 is an enlarged view of a portion of area A of FIG. 2;

FIG. 4 is a partial enlarged view of area B of FIG. 2;

fig. 5 is a partially enlarged view of the region C in fig. 2.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures associated with the present invention are shown in the drawings, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without making creative efforts belong to the protection scope of the present invention.

Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the invention. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein may be combined with other embodiments.

Referring to fig. 1 to 5, the rudder control mechanism of the dual vertical fin unmanned aerial vehicle of the present invention includes a horizontal rear wing 100, a first vertical rear wing 200, a second vertical rear wing 300, a first rudder 400, a second rudder 500, and a driving assembly 600;

the first vertical tail wing 200 is connected to one side of the horizontal tail wing 100, the second vertical tail wing 300 is connected to the other side of the horizontal tail wing 100, the first rudder 400 is rotatably installed at the end of the first vertical tail wing 200, the second rudder 500 is rotatably installed at the end of the second vertical tail wing 300, the driving assembly 600 is installed on the horizontal tail wing 100, and the driving assembly 600 drives the first rudder 400 and the second rudder 500 to rotate synchronously;

wherein, horizontal tail 100 is right the utility model discloses an each structure in the two vertical fin unmanned aerial vehicle rudder control mechanisms all plays the effect of fixed stay to, first vertical tail 200 plays the effect of fixed stay to first rudder 400, and second vertical tail 300 plays the effect of fixed stay to second rudder 500, and drive assembly 600 can realize the first rudder 400 of simultaneous control and the operation of second rudder 500, reaches the afterbody and subtracts heavy and realize the purpose of rudder face linear control.

In this embodiment, the driving assembly 600 includes a steering engine 610, a first swing arm 620, a first connecting rod 630, a second swing arm, a first transmission shaft 650, a second transmission shaft 651, a third swing arm 660, a second connecting rod 670, a fourth swing arm 680 and a third connecting rod 690, the steering engine 610 is installed on the horizontal rear wing 100, one end of the first swing arm 620 is connected to the output end of the steering engine 610, the other end of the first swing arm 620 is connected to one end of the first connecting rod 630, the other end of the first connecting rod 630 is connected to the second swing arm, one end of the first transmission shaft 650 is connected to one side of the second swing arm, the other end of the first transmission shaft 650 is connected to the third swing arm 660, one end of the second connecting rod 670 is connected to the third swing arm 660, the other end of the second connecting rod 670 is connected to the first rudder 400, one end of the second transmission shaft 651 is connected to the other side of the second swing arm, the other end of the second transmission shaft 651 is connected to the fourth swing arm 680, one end of the third connecting rod 690 is connected to the third swing arm 660, and the other end of the third connecting rod 690 is connected to the rudder 500.

The steering engine 610 is mainly used for generating a driving force for the first swing arm 620, that is, when the steering engine 610 works, the output end of the steering engine 610 drives the first swing arm 620 to rotate by a certain angle, so that the first swing arm 620 drives the first connecting rod 630 to move, the second connecting rod 670 drives the second swing arm to rotate, the second swing arm simultaneously drives the first transmission shaft 650 and the second transmission shaft 651 to rotate, the first transmission shaft 650 drives the third swing arm 660 to rotate by a certain angle, the third swing arm 660 drives the second connecting rod 670 to move, and the second connecting rod 670 further drives the first direction rudder 400 to rotate by a certain angle, so that the adjustment of the angle of the first direction rudder 400 is realized;

meanwhile, when the second swing arm rotates, the second transmission shaft 651 is driven to rotate, the second transmission shaft 651 drives the fourth swing arm 680 to rotate by a certain angle, the fourth swing arm 680 drives the third connecting rod 690 to move, and the third connecting rod 690 drives the second rudder 500 to rotate by a certain angle, so that the angle of the first rudder can be adjusted.

In this embodiment, a first rudder angle 700 for improving the angular rotation accuracy of the first rudder 400 is disposed between the first rudder 400 and the second connecting rod 670, one end of the first rudder angle 700 is rotatably connected to the first rudder 400, and the other end of the first rudder angle 700 is rotatably connected to the second connecting rod 670.

In this embodiment, a first orthodontic rod end bearing 710 for improving the rotation matching performance of the second connecting rod 670 and the first rudder angle 700 is disposed at a connection between the second connecting rod 670 and the first rudder angle 700, and a first anti-orthodontic rod end bearing 720 for improving the rotation matching performance of the second connecting rod 670 and the third swing arm 660 is disposed at a connection between the second connecting rod 670 and the third swing arm 660.

In this embodiment, a second rudder angle 800 for improving the angular rotation precision of the second rudder 500 is disposed between the second rudder 500 and the third connecting rod 690, one end of the second rudder angle 800 is rotatably connected to the second rudder 500, and the other end of the second rudder angle 800 is rotatably connected to the third connecting rod 690.

In this embodiment, a second orthodontic rod end bearing 810 for improving the rotation matching performance of the third connecting rod 690 and the second rudder angle 800 is disposed at a connection between the third connecting rod 690 and the second rudder angle 800, and a second anti-orthodontic rod end bearing 820 for improving the rotation matching performance of the third connecting rod 690 and the fourth swing arm 680 is disposed at a connection between the third connecting rod 690 and the fourth swing arm 680.

In this embodiment, the second swing arm includes a left connecting swing arm 641 and a right connecting swing arm 642, the left connecting swing arm 641 and the right connecting swing arm 642 are fixedly connected, the ends of the left connecting swing arm 641 and the right connecting swing arm 642 are connected to one end of the first connecting rod 630, the left connecting swing arm 641 is connected to one end of the first transmission shaft 650, and the right connecting swing arm 642 is connected to one end of the second transmission shaft 651.

In this embodiment, a first flange 643 is disposed between the left connecting swing arm 641 and the first transmission shaft 650 for improving stability of the left connecting swing arm 641 and the first transmission shaft 650, and a second flange 644 is disposed between the right connecting swing arm 642 and the second transmission shaft 651 for improving stability of the right connecting swing arm 642 and the second transmission shaft 651.

In this embodiment, a transmission shaft supporting seat 621 is disposed outside the first swing arm 620, the transmission shaft supporting seat 621 is installed on the horizontal rear wing 100, and the second swing arm is rotatably connected to the transmission shaft supporting seat 621.

Wherein, the transmission shaft supporting seat 621 can support the rotation of the second swing arm.

In this embodiment, the orientation of the third swing arm 660 is opposite to the orientation of the fourth swing arm 680.

The orientation of the third swing arm 660 is just opposite to that of the fourth swing arm 680, so that the direction in which the third swing arm 660 drives the second connecting rod 670 to move is just opposite to the direction in which the fourth swing arm 680 drives the third connecting rod 690 to move, and the angle adjustment of the first rudder 400 and the angle adjustment of the second rudder 500 are just opposite to each other, so that the consistency of the control surfaces is improved.

The rudder control mechanism of the double vertical fin unmanned aerial vehicle comprises a horizontal tail wing 100, a first vertical tail wing 200, a second vertical tail wing 300, a first rudder 400, a second rudder 500 and a driving assembly 600; first vertical tail 200 is connected horizontal tail 100 one side, second vertical tail 300 is connected horizontal tail 100 opposite side, first rudder 400 rotates to install first vertical tail 200 tip, second rudder 500 rotates to install second vertical tail 300 tip, drive assembly 600 is installed on horizontal tail 100, just drive assembly 600 drives first rudder 400 with second rudder 500 synchronous rotations, wherein, the utility model discloses a two vertical tail unmanned aerial vehicle rudder operating mechanism can realize the function of two rudders of a steering wheel 610 drive, and the direct effectual weight that subtracts one set of steering wheel 610 and driver to improved reliability and uniformity, can guarantee two rudder face synchronicity and then improve the direction control performance of aircraft through this mode, simultaneously, transmit the torsional force through a plurality of connecting rods and control the direction, fine avoiding because the horizontal tail space is urged to lead to interfering and improve space utilization, furtherly, the utility model discloses the weight that the weight of one set of steering wheel 610 can be better control the complete machine, and also can reduce the manufacturing and maintenance cost.

The above only is the embodiment of the present invention, not limiting the patent scope of the present invention, all the equivalent structures or equivalent processes that are used in the specification and the attached drawings or directly or indirectly applied to other related technical fields are included in the patent protection scope of the present invention.

Claims (10)

1. A steering mechanism of a double-vertical-tail unmanned aerial vehicle is characterized by comprising a horizontal tail wing, a first vertical tail wing, a second vertical tail wing, a first rudder, a second rudder and a driving assembly;

first vertical tail is connected horizontal tail one side, the vertical tail of second is connected the horizontal tail opposite side, the first rudder rotates to be installed first vertical tail tip, the second rudder rotates to be installed the vertical tail tip of second, drive assembly installs on the horizontal tail, just drive assembly drives the first rudder with the second rudder synchronous revolution.

2. The steering mechanism of claim 1, wherein the driving assembly comprises a steering engine, a first swing arm, a first connecting rod, a second swing arm, a first transmission shaft, a second transmission shaft, a third swing arm, a second connecting rod, a fourth swing arm and a third connecting rod, the steering engine is mounted on the horizontal tail wing, one end of the first swing arm is connected with an output end of the steering engine, the other end of the first swing arm is connected with one end of the first connecting rod, the other end of the first connecting rod is connected with the second swing arm, one end of the first transmission shaft is connected with one side of the second swing arm, the other end of the first transmission shaft is connected with the third swing arm, one end of the second connecting rod is connected with the third swing arm, the other end of the second connecting rod is connected with the first rudder, one end of the second transmission shaft is connected with the other side of the second swing arm, the other end of the second transmission shaft is connected with the fourth swing arm, one end of the third connecting rod is connected with the third swing arm, and the other end of the third connecting rod is connected with the second rudder.

3. The rudder control mechanism for a double-vertical-tail unmanned aerial vehicle according to claim 2, wherein a first rudder angle for improving the rotation precision of the first rudder angle is arranged between the first rudder and the second connecting rod, one end of the first rudder angle is rotatably connected with the first rudder, and the other end of the first rudder angle is rotatably connected with the second connecting rod.

4. The rudder control mechanism for a double-vertical-tail unmanned aerial vehicle according to claim 3, wherein a first orthodontic rod end bearing for improving the rotation matching performance of the second connecting rod with the first rudder angle is arranged at the joint of the second connecting rod and the first rudder angle, and a first anti-orthodontic rod end bearing for improving the rotation matching performance of the second connecting rod with the third swing arm is arranged at the joint of the second connecting rod and the third swing arm.

5. The rudder control mechanism for a double-vertical-tail unmanned aerial vehicle according to claim 2, wherein a second rudder angle for improving the rotation precision of the second rudder angle is arranged between the second rudder and the third connecting rod, one end of the second rudder angle is rotatably connected with the second rudder, and the other end of the second rudder angle is rotatably connected with the third connecting rod.

6. The steering mechanism for the double-vertical-tail unmanned aerial vehicle comprises a third connecting rod, a fourth swinging arm, a third connecting rod, a fourth vertical-tail unmanned aerial vehicle steering rudder and control mechanism according to claim 5, wherein a second orthodontic rod end bearing used for improving the rotating matching performance of the third connecting rod and the second rudder angle is arranged at the joint of the third connecting rod and the second rudder angle, and a second contra-orthodontic rod end bearing used for improving the rotating matching performance of the third connecting rod and the fourth swinging arm is arranged at the joint of the third connecting rod and the fourth swinging arm.

7. The rudder control mechanism according to claim 2, wherein the second swing arm includes a left connecting swing arm and a right connecting swing arm, the left connecting swing arm and the right connecting swing arm are fixedly connected, the ends of the left connecting swing arm and the right connecting swing arm are connected to one end of the first connecting rod, the left connecting swing arm is connected to one end of the first transmission shaft, and the right connecting swing arm is connected to one end of the second transmission shaft.

8. The rudder control mechanism according to claim 7, wherein a first flange plate for improving the stability of the left connecting swing arm and the first transmission shaft is disposed between the left connecting swing arm and the first transmission shaft, and a second flange plate for improving the stability of the right connecting swing arm and the second transmission shaft is disposed between the right connecting swing arm and the second transmission shaft.

9. The rudder control mechanism for a twin vertical fin unmanned aerial vehicle according to claim 2, wherein a transmission shaft support seat is provided outside the first swing arm, the transmission shaft support seat is mounted on the horizontal rear wing, and the second swing arm is rotatably connected to the transmission shaft support seat.

10. The twin vertical fin drone rudder steering mechanism of claim 2, wherein the orientation of the third swing arm and the orientation of the fourth swing arm are exactly opposite.

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