阅读说明：本技术 翼面联动装置和飞行器 (Airfoil surface linkage device and aircraft ) 是由 王占军 孙勇 陈丰华 郜奥林 孙雪军 赵超越 陈光伟 董文辉 李少辉 高星亮 杨 于 2019-04-12 设计创作，主要内容包括：本发明实施例提供一种翼面联动装置和飞行器,该翼面联动装置包括：舵机组件、扭力管组件、第一翼面组件及第二翼面组件；扭力管组件包括主动扭力管、第一从动扭力管、第二从动扭力管、第一联轴器、第二联轴器；其中,舵机组件和主动扭力管连接并用于驱动主动扭力管绕自身轴线转动,并通过第一联轴器和第二联轴器分别作用于第一从动扭力管和第二从动扭力管,从而通过第一翼面组件和第二翼面组件分别带动飞行器的相对设置的两个翼面偏转；使得飞行器可以通过一套舵机组件、扭力管组件、第一翼面组件及第二翼面组件带动飞行器的两个翼面偏转,实现了两侧翼面实时作动,从而提高了飞行器的安全性。(The embodiment of the invention provides an airfoil linkage device and an aircraft, wherein the airfoil linkage device comprises: the device comprises a steering engine component, a torsion tube component, a first wing surface component and a second wing surface component; the torsion tube assembly comprises a driving torsion tube, a first driven torsion tube, a second driven torsion tube, a first coupler and a second coupler; the steering engine assembly is connected with the driving torque tube and used for driving the driving torque tube to rotate around the axis of the steering engine assembly, and the steering engine assembly and the driving torque tube act on the first driven torque tube and the second driven torque tube through the first coupler and the second coupler respectively, so that the first wing surface assembly and the second wing surface assembly drive two oppositely arranged wing surfaces of the aircraft to deflect respectively; the aircraft can drive two airfoil deflections of the aircraft through one set of steering engine component, the torsion tube component, the first airfoil component and the second airfoil component, the two airfoils on two sides can actuate in real time, and therefore safety of the aircraft is improved.)

1. An airfoil linkage disposed on an aircraft, comprising: the device comprises a steering engine component, a torsion tube component, a first wing surface component and a second wing surface component; the torque tube assembly comprises a driving torque tube, a first driven torque tube, a second driven torque tube, a first coupler and a second coupler;

the steering engine assembly is connected with the driving torsion tube and used for driving the driving torsion tube to rotate around the axis of the driving torsion tube, the first end of the driving torsion tube is connected with one end of the first driven torsion tube through the first coupler, and the second end of the driving torsion tube is connected with one end of the second driven torsion tube through the second coupler; one end of the first driven torque tube departing from the driving torque tube is connected with the first airfoil assembly device, the other end of the second driven torque tube departing from the driving torque tube is connected with the second airfoil assembly device, and the first airfoil assembly and the second airfoil assembly are respectively used for driving two oppositely arranged airfoils of the aircraft to deflect.

2. The apparatus of claim 1,

the first coupler and the second coupler are universal joint couplers.

3. The apparatus of claim 1,

and two ends of the active torsion tube are respectively positioned on two sides of the central axis of the aircraft.

4. The apparatus of claim 3,

the axis of the active torsion tube is perpendicular to the central axis of the aircraft.

5. The apparatus of claim 1,

the steering engine component is connected to the middle of the driving torsion tube along the length direction.

6. The apparatus of claim 1,

the torque tube assembly further comprises a plurality of bases, at least one of the bases is correspondingly arranged on each of the driving torque tube, the first driven torque tube and the second driven torque tube, and the driving torque tube, the first driven torque tube and the second driven torque tube are rotatably connected with the corresponding bases.

7. The device of claim 1, wherein the steering engine assembly comprises a steering engine and a rocker arm;

the steering engine with the organism of aircraft is relatively fixed, the first end of rocking arm with the action end of steering engine is articulated, the second end of rocking arm with initiative torque tube fixed connection, the steering engine is used for the drive the first end of rocking arm for the second end swing of rocking arm is held, in order to drive the rotation of initiative torque tube.

8. The apparatus of claim 7,

the steering engine is a linear steering engine or a rotary steering engine.

9. The apparatus of any of claims 1-8, wherein the first airfoil assembly comprises a first airfoil panel, a first pushrod, a first link, and a first rocker arm; the second wing surface assembly comprises a second wing surface plate, a second push rod, a second connecting rod and a second rocker arm;

the first end of the first rocker arm is connected with the tail end of the first driven torsion tube, the second end of the first rocker arm is hinged with one end of the first connecting rod, the other end of the first connecting rod is connected with the first push rod, and the first airfoil plate is fixed on the first push rod;

and/or the presence of a gas in the gas,

the first end of the second rocker arm is connected with the tail end of the second driven torsion tube, the second end of the second rocker arm is hinged with one end of the second connecting rod, the other end of the second connecting rod is connected with the second push rod, and the second wing panel is fixed on the second push rod.

10. An aircraft, further characterized by comprising a body, a pair of wings disposed on opposite sides of the body, and the airfoil linkage of any of claims 1-9; the airfoil linkage is coupled to an airfoil on the wing and is configured to drive the airfoil to deflect.

Technical Field

The invention relates to the technical field of aircrafts, in particular to an airfoil linkage device and an aircraft.

Background

At present, in flap transmission devices of aircraft, two sets of bilateral flap transmission devices are generally adopted to respectively control the motion of flaps on two sides of the aircraft. Wherein, each set of transmission all includes steering wheel, actuator and actuating mechanism etc..

In the process of controlling the flap drive through the drive device, the steering engine is used as an enabling end of an aircraft flap drive system and is arranged between an aircraft controller and an actuating mechanism, a flap control instruction sent by the aircraft controller is converted into corresponding action, and a certain torque or rotating speed is output to an actuator; the actuator is used as a bridge between the steering engine and the executing mechanism, and the torque or the rotating speed output by the steering engine is converted so as to be matched with the mechanism driving flap surfaces with different transmission parameters and transmit more accurate control action to the executing mechanism; the actuator has certain transmission ratio and structural parameters, and the control action transmitted from the actuator is converted into the flap at the corresponding end through a corresponding transmission path in a mode so as to control the flap to finish certain opening or folding operation, thereby improving the maximum lift coefficient of the aircraft and reducing the takeoff or landing distance of the aircraft.

However, the existing linkage device is adopted, and the steering engines and the actuators on the two sides and the parameters of the transmission mechanism have inevitable errors in the manufacturing and processing processes, so that the flaps on the two sides cannot be actuated in real time, and when the aircraft takes off or lands, the risk of crash of the aircraft exists, and the safety of the aircraft is not high.

Disclosure of Invention

The invention provides a wing surface linkage device and an aircraft, which are used for realizing real-time actuation of wing surfaces on two sides of the aircraft, so that the safety of the aircraft is improved.

In a first aspect, an embodiment of the present invention provides an airfoil linkage device disposed on an aircraft, where the airfoil linkage device may include: the device comprises a steering engine component, a torsion tube component, a first wing surface component and a second wing surface component; the torque tube assembly comprises a driving torque tube, a first driven torque tube, a second driven torque tube, a first coupler and a second coupler;

the steering engine assembly is connected with the driving torsion tube and used for driving the driving torsion tube to rotate around the axis of the driving torsion tube, the first end of the driving torsion tube is connected with one end of the first driven torsion tube through the first coupler, and the second end of the driving torsion tube is connected with one end of the second driven torsion tube through the second coupler; one end of the first driven torque tube departing from the driving torque tube is connected with the first airfoil assembly device, the other end of the second driven torque tube departing from the driving torque tube is connected with the second airfoil assembly device, and the first airfoil assembly and the second airfoil assembly are respectively used for driving two oppositely arranged airfoils of the aircraft to deflect.

In one possible implementation, the first coupling and the second coupling are both universal joint couplings.

In one possible implementation, the two ends of the active torsion tube are located on two sides of the central axis of the aircraft.

In one possible implementation, the axis of the active torsion tube is perpendicular to the central axis of the aircraft.

In a possible implementation manner, the steering engine component is connected to the middle position of the active torsion tube along the length direction.

In one possible implementation, the torque tube assembly further includes a plurality of bases, at least one of the bases is disposed on each of the driving torque tube, the first driven torque tube and the second driven torque tube, and the driving torque tube, the first driven torque tube and the second driven torque tube are rotatably connected to the respective bases.

In one possible implementation manner, the steering engine component comprises a steering engine and a rocker arm;

the steering engine with the organism of aircraft is relatively fixed, the first end of rocking arm with the action end of steering engine is articulated, the second end of rocking arm with initiative torque tube fixed connection, the steering engine is used for the drive the first end of rocking arm for the second end swing of rocking arm is held, in order to drive the rotation of initiative torque tube.

In one possible implementation, the steering engine is a linear steering engine or a rotary steering engine.

In one possible implementation, the first airfoil assembly includes a first airfoil panel, a first pushrod, a first link, and a first rocker arm; the second wing surface assembly comprises a second wing surface plate, a second push rod, a second connecting rod and a second rocker arm;

the first end of the first rocker arm is connected with the tail end of the first driven torsion tube, the second end of the first rocker arm is hinged with one end of the first connecting rod, the other end of the first connecting rod is connected with the first push rod, and the first airfoil plate is fixed on the first push rod;

and/or the presence of a gas in the gas,

the first end of the second rocker arm is connected with the tail end of the second driven torsion tube, the second end of the second rocker arm is hinged with one end of the second connecting rod, the other end of the second connecting rod is connected with the second push rod, and the second wing panel is fixed on the second push rod.

In a second aspect, an embodiment of the present invention further provides an aircraft, where the aircraft may include a body, a pair of wings disposed on opposite sides of the body, and the airfoil linkage device in any one of the possible implementations of the first aspect; the airfoil linkage is coupled to an airfoil on the wing and is configured to drive the airfoil to deflect.

The embodiment of the invention provides an airfoil linkage device and an aircraft, wherein the airfoil linkage device comprises: the device comprises a steering engine component, a torsion tube component, a first wing surface component and a second wing surface component; the torsion tube assembly comprises a driving torsion tube, a first driven torsion tube, a second driven torsion tube, a first coupler and a second coupler; the steering engine assembly is connected with the driving torsion tube and used for driving the driving torsion tube to rotate around the axis of the steering engine assembly, the first end of the driving torsion tube is connected with one end of the first driven torsion tube through the first coupler, and the second end of the driving torsion tube is connected with one end of the first driven torsion tube through the second coupler; one end of the first driven torque tube, which is far away from the driving torque tube, is connected with first airfoil assembly equipment, the other end of the second driven torque tube, which is far away from the driving torque tube, is connected with second airfoil assembly equipment, and the first airfoil assembly and the second airfoil assembly are respectively used for driving two oppositely arranged airfoils of the aircraft to deflect; the first driven torque tube and the second driven torque tube are respectively provided with an included angle with the axis of the driving torque tube, so that the aircraft can drive two oppositely-arranged airfoil surfaces of the aircraft to deflect through one set of steering engine assembly, the torque tube assembly, the first airfoil surface assembly and the second airfoil surface assembly, the airfoil surfaces on two sides can be actuated in real time, and the safety of the aircraft is improved.

Drawings

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

FIG. 1 is a schematic illustration of an airfoil linkage arrangement according to an embodiment of the present invention;

FIG. 2 is a schematic illustration of a drive mechanism for an airfoil linkage according to an embodiment of the present invention;

FIG. 3 is a schematic illustration of an airfoil deployment position of an airfoil linkage according to an embodiment of the present invention.

Description of reference numerals:

10-airfoil linkage;

101-a steering engine assembly;

1011-steering engine;

1012-rocker arm;

1013-a steering engine base;

102-a torsion tube assembly;

1021-active torsion tube;

1022-a first driven torque tube;

1023-a second driven torsion tube;

1024 — a first coupling;

1025-a second coupling;

103-a first airfoil assembly;

1031-a first flap panel;

1032-a first putter;

1033-a first link;

1034-a first rocker arm;

104-a second airfoil assembly;

1041-a second wing panel;

1042 — a second push rod;

1043-a second link;

1044-second rocker arm.

With the foregoing drawings in mind, certain embodiments of the disclosure have been shown and described in more detail below. These drawings and written description are not intended to limit the scope of the disclosed concepts in any way, but rather to illustrate the concepts of the disclosure to those skilled in the art by reference to specific embodiments.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.