阅读说明：本技术 一种飞机驾驶操纵结构及方法、飞机 (Aircraft driving control structure and method and aircraft ) 是由 徐颖 张景 于 2019-10-24 设计创作，主要内容包括：本发明一种飞机驾驶操纵结构及方法、飞机,包括在飞机驾驶舱内设置的多个作动器；多个作动器与飞机驾驶舱内的操控机构传动连接；多个作动器用于控制操控机构的运行；本发明提供的方案,使得现有飞机可以实现无人驾驶,同时可以适用于传统有人驾驶飞机升级成无人驾驶飞机,摆脱传统飞机对飞行员的依赖,降低飞行成本,提高现有飞机无人驾驶的安全性和稳定性；本发明提供的方案,可应用于大部分中小型通用航空飞行器以及实验教学场景,市场前景较为广阔。(The invention relates to an airplane piloting control structure, an airplane piloting control method and an airplane, wherein the airplane comprises a plurality of actuators arranged in a piloting cabin of the airplane; the actuators are in transmission connection with a control mechanism in the aircraft cockpit; the plurality of actuators are used for controlling the operation of the control mechanism; the scheme provided by the invention enables the existing airplane to realize unmanned piloting, is simultaneously suitable for upgrading the traditional piloted airplane into the unmanned pilotless airplane, gets rid of the dependence of the traditional airplane on pilots, reduces the flight cost and improves the safety and stability of the unmanned piloting of the existing airplane; the scheme provided by the invention can be applied to most of small and medium-sized general aviation aircrafts and experimental teaching scenes, and has a wide market prospect.)

1. An aircraft piloting structure, characterized in that it comprises a plurality of actuators arranged in an aircraft cockpit (1); the actuators are in transmission connection with a control mechanism in the aircraft cockpit (1); the plurality of actuators are used for controlling the operation of the control mechanism.

2. An aircraft piloting structure as in claim 1, further comprising an actuator frame (4), said actuator frame (4) being fixedly arranged inside the aircraft cockpit (1) for fixedly connecting said plurality of actuators.

3. An aircraft piloting structure as in claim 2, wherein said actuators comprise a first actuator (6) and a second actuator (7);

the control mechanism comprises a pitch push rod (8) and an accelerator push rod (9);

the first actuator (6) is fixedly arranged at the top of the actuator frame (4), and the transmission end of the first actuator (6) is connected with the propeller pitch push rod (8) through a connecting rod mechanism;

the second actuator (7) is fixedly arranged at the top of the actuator frame (4), and the transmission end of the second actuator (7) is connected with the accelerator push rod (9) through a connecting rod mechanism.

4. The aircraft driving control structure according to claim 3, characterized in that the second actuator (7) is a throttle push rod electric linear actuator, the throttle push rod electric linear actuator is arranged in the aircraft cockpit (1) along the longitudinal direction of the aircraft body and is in transmission connection with the throttle push rod (9), and the throttle push rod electric linear actuator is used for controlling the throttle size of the aircraft;

first actuator (6) are the electronic linear actuator of pitch push rod, the electronic linear actuator of pitch push rod along aircraft fuselage vertically set up in aircraft cockpit (1), and with pitch push rod (8) transmission is connected, the electronic linear actuator of pitch push rod is used for controlling the pitch size of aircraft.

5. An aircraft piloting steering arrangement as in claim 3, wherein said actuators further comprise a third actuator (17) and a fourth actuator (18);

the control mechanism also comprises an airplane steering rod (5) and a pedaling rotating shaft (13);

the aircraft cockpit (1) comprises a central console (2), and the central console (2) is arranged on the front side of the aircraft cockpit (1);

the airplane control lever (5) is arranged on the side edge of the central control console (2) along the vertical direction, and the pedaling rotating shaft (13) is arranged on a base of the airplane cockpit (1) and is positioned at the bottom of the central control console (2);

the third actuator (17) is fixedly arranged on the actuator frame (4), and the transmission end of the third actuator (17) is connected with the airplane steering column (5); the fourth actuator (18) is fixedly arranged on the actuator frame (4), and the transmission end of the fourth actuator (18) is connected with the pedaling rotating shaft (13).

6. Aircraft piloting structure as in claim 5, characterized in that said third actuator (17) is an electric linear actuator of pitch, arranged in the aircraft cockpit (1) in the longitudinal direction of the aircraft fuselage, for controlling the forward and backward pulling actions of the aircraft steering column (5);

the fourth actuator (18) is a yaw electric linear actuator which is arranged in the aircraft cockpit (1) along the longitudinal direction of the aircraft body and used for adjusting the rotation angle of the rudder.

7. The aircraft piloting structure of claim 6, characterized in that the transmission end of said pitch electric linear actuator is in transmission connection with said aircraft pilot lever (5) through a linkage mechanism; link mechanism includes actuator mount pad (19) and connecting rod, actuator mount pad (19) fixed set up in on aircraft pilot rod (5), connecting rod one end with aircraft pilot rod (5) are connected, the other end of connecting rod with the transmission end transmission of the electronic linear actuator of every single move is connected.

8. The aircraft steering arrangement according to claim 6, wherein the drive end of the yaw electric linear actuator is in drive connection with the pedal spindle (13) via a changeover mechanism; the switching mechanism comprises a connecting rod and a rudder rotating disc (16), and the rudder rotating disc (16) is arranged on the pedaling rotating shaft (13) and can drive the pedaling rotating shaft (13) to rotate; one end of the connecting rod is rotatably connected with the rudder rotary table (16), and the other end of the connecting rod is in transmission connection with the transmission end of the yaw electric linear actuator.

9. An aircraft piloting steering structure as in claim 7, wherein said actuators further comprise a fifth actuator (20), said fifth actuator (20) being fixedly arranged on said aircraft pilot column (5); one end of the fifth actuator (20) is fixed on the actuator mounting seat (19), and the other end of the fifth actuator (20) is fixed on the airplane steering column (5) for connection.

10. The structure according to claim 9, characterized in that the fifth actuator (20) is a rolling electric linear actuator, and the top of the flight bar (5) is provided with a rotating shaft (12); the rolling electric linear actuator is arranged on the airplane steering column (5) along the axial direction of the airplane steering column (5); the transmission end of the rolling electric linear actuator is in transmission connection with the rotating shaft (12) on the airplane steering column (5) through a clamping disc (15), so that the rolling action of the airplane is controlled.

11. An aircraft piloting structure as in claim 2, further comprising automatic flight control means (3); a first seat (10) and a second seat (11) are arranged in the aircraft cockpit (1), and the actuator frame (4) is fixedly arranged on the first seat (10); the automatic flight control device (3) is arranged on the second seat (11); an automatic flight control system is arranged in the automatic flight control device (3), and is respectively in communication connection with the plurality of actuators; the automatic flight control system is used for controlling the execution actions of the plurality of actuators so as to control the operation of the airplane.

12. An aircraft piloting operation method, applied to an aircraft piloting operation structure as defined in any one of claims 1 to 11, comprising the operations of:

when the aircraft runs on the ground, a small accelerator and a small propeller pitch are needed, the automatic flight control system controls the accelerator push rod electric linear actuator to contract and controls the propeller pitch push rod electric linear actuator to extend;

when the airplane turns left on the ground, the automatic flight control system controls the yaw electric linear actuator to extend;

when the airplane turns right on the ground, the automatic flight control system controls the yaw electric linear actuator to shorten;

when the aircraft runs in an accelerating way, a large accelerator and a large propeller pitch are needed, the automatic flight control system controls the accelerator push rod electric linear actuator to extend, and controls the propeller pitch push rod electric linear actuator to shorten;

when the airplane is pulled up, the elevator is required to be lifted up, the automatic flight control system controls the pitching electric linear actuator to contract, and the airplane steering column deflects towards the negative direction of the longitudinal axis of the airplane body;

when the airplane flies horizontally, each control surface is kept still, and each actuator is also kept still; when the airplane rolls to the right side, the automatic flight control system controls the yaw electric linear actuator to extend;

when the airplane descends, an accelerator and a small pitch need to be reduced, the automatic flight control system controls the accelerator push rod electric linear actuator to shorten, and controls the pitch push rod electric linear actuator to extend; or the like, or, alternatively,

when the airplane is ready to land, the airplane head is slightly tilted upwards while a small accelerator and a small pitch are kept, the automatic flight control system controls and keeps the positions of the accelerator push rod electric linear actuator and the pitch push rod electric linear actuator, and the pitch electric linear actuator is controlled to contract; after the aircraft body naturally decelerates after landing, a minimum accelerator and a minimum pitch are needed, and other control surfaces are kept at initial positions; the automatic flight control system controls and keeps the throttle push rod electric linear actuator to retract to the minimum stroke, controls the pitch push rod electric linear actuator to extend to the maximum stroke, and keeps other actuators at the zero position.

13. An aircraft comprising an aircraft piloting manoeuvring structure, wherein the aircraft piloting manoeuvring structure is an aircraft piloting manoeuvring structure as claimed in any one of claims 1 to 11.

Technical Field

The invention relates to the technical field of unmanned aircraft piloting, in particular to an aircraft piloting control structure and method and an aircraft.

Background

The existing aircraft mostly realizes the flight by the pilot, and along with the rapid development of the unmanned technology, the existing aircraft can realize safer and more reliable flight by the unmanned technology; the existing flight driving control technical field has the scheme that an unmanned aerial vehicle is changed by a man and is still in a starting stage, a specific scheme is not disclosed, and related practical schemes are all in a propaganda stage and are not really applied to the existing airplane.

Disclosure of Invention

The invention aims to solve and realize the problem of the existing airplane piloting control.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

the invention provides an aircraft piloting control structure, which comprises a plurality of actuators arranged in an aircraft cockpit; the actuators are in transmission connection with a control mechanism in the aircraft cockpit; the plurality of actuators are used for controlling the operation of the control mechanism; by adopting the scheme, the control over the airplane control mechanism can be realized, the unmanned piloting of the airplane is realized, the airplane control structure can be directly applied to the existing manned airplane improved structure, and the applicability is strong.

Further, the aircraft piloting control structure further comprises an actuator frame, wherein the actuator frame is fixedly arranged in the aircraft cockpit and is used for fixedly connecting the plurality of actuators.

Further, the actuators include a first actuator and a second actuator; the control mechanism comprises a propeller pitch push rod and an accelerator push rod; the first actuator is fixedly arranged at the top of the actuator frame, and the transmission end of the first actuator is connected with the propeller pitch push rod through a connecting rod mechanism; the second actuator is fixedly arranged at the top of the actuator frame, and the transmission end of the second actuator is connected with the accelerator push rod through a connecting rod mechanism.

Furthermore, the second actuator is an accelerator push rod electric linear actuator which is arranged in the aircraft cockpit along the longitudinal direction of the aircraft body and is in transmission connection with an accelerator push rod, and the accelerator push rod electric linear actuator is used for controlling the size of an accelerator of the aircraft; the first actuator is a propeller pitch push rod electric linear actuator which is arranged in the aircraft cockpit along the longitudinal direction of the aircraft body and is in transmission connection with the propeller pitch push rod, and the propeller pitch push rod electric linear actuator is used for controlling the size of the propeller pitch of the aircraft.

Further, the actuators also comprise a third actuator and a fourth actuator; the control mechanism also comprises an airplane steering column and a pedaling rotating shaft; the aircraft cockpit comprises a central control console, and the central control console is arranged on the front side of the aircraft cockpit; (ii) a The airplane control lever is arranged on the side edge of the central control console along the vertical direction, and the pedaling rotating shaft is arranged on a base of the airplane cockpit and is positioned at the bottom of the central control console; the third actuator is fixedly arranged on the actuator frame, and the transmission end of the third actuator is connected with the airplane steering column; the fourth actuator is fixedly arranged on the actuator frame, and the transmission end of the fourth actuator is connected with the pedaling rotating shaft.

Furthermore, the third actuator is a pitching electric linear actuator which is arranged in the aircraft cockpit along the longitudinal direction of the aircraft body and used for controlling the forward pushing and backward pulling actions of the aircraft steering column; the fourth actuator is a yaw electric linear actuator which is arranged in the aircraft cockpit along the longitudinal direction of the aircraft body and used for adjusting the rotation angle of the rudder.

Furthermore, the transmission end of the pitching electric linear actuator is in transmission connection with the airplane steering column through a link mechanism; the connecting rod mechanism comprises an actuator mounting seat and a connecting rod, the actuator mounting seat is fixedly arranged on the aircraft pilot rod, one end of the connecting rod is connected with the aircraft pilot rod, and the other end of the connecting rod is in transmission connection with the transmission end of the pitching electric linear actuator.

Furthermore, the transmission end of the yaw electric linear actuator is in transmission connection with the pedaling rotating shaft through a switching mechanism; the switching mechanism comprises a connecting rod and a rudder rotating disc, and the rudder rotating disc is arranged on the pedaling rotating shaft and can drive the pedaling rotating shaft to rotate; one end of the connecting rod is rotatably connected with the rudder turntable, and the other end of the connecting rod is in transmission connection with the transmission end of the electric yaw linear actuator.

Furthermore, the actuator still includes the fifth actuator, and the fifth actuator is fixed to be set up on the aircraft pilot rod, and on the one end of fifth actuator was fixed in the actuator mount pad, the other end of fifth actuator was fixed in the aircraft pilot rod and is connected.

Furthermore, the fifth actuator is a rolling electric linear actuator, and the top of the airplane steering column is provided with a rotating shaft; the rolling electric linear actuator is arranged on the airplane steering column along the axial direction of the airplane steering column; the transmission end of the rolling electric linear actuator is in transmission connection with a rotating shaft on the airplane steering column through a tightening disc, so that the rolling action of the airplane is controlled.

Further, the airplane piloting control structure also comprises an automatic flight control device; a first seat and a second seat are arranged in the aircraft cockpit, and the actuator frame is fixedly arranged on the first seat; the automatic flight control device is arranged on the second seat; an automatic flight control system is arranged in the automatic flight control device and is respectively in communication connection with the plurality of actuators; the automatic flight control system is used for controlling the execution actions of the plurality of actuators so as to control the operation of the airplane.

Accordingly, another object of the present invention is to provide an airplane piloting operation method, applied to the airplane piloting operation structure for controlling an airplane, comprising the following operations:

when the aircraft runs on the ground, a small accelerator and a small propeller pitch are needed, the automatic flight control system controls the accelerator push rod electric linear actuator to contract and controls the propeller pitch push rod electric linear actuator to extend;

when the airplane turns left on the ground, the automatic flight control system controls the yaw electric linear actuator to extend;

when the airplane turns right on the ground, the automatic flight control system controls the yaw electric linear actuator to shorten;

when the aircraft runs in an accelerating way, a large accelerator and a large propeller pitch are needed, the automatic flight control system controls the accelerator push rod electric linear actuator to extend, and controls the propeller pitch push rod electric linear actuator to shorten;

when the airplane is pulled up, the elevator is required to be lifted up, the automatic flight control system controls the pitching electric linear actuator to contract, and the airplane steering column deflects towards the negative direction of the longitudinal axis of the airplane body;

when the airplane flies horizontally, each control surface is kept still, and each actuator is also kept still; when the airplane rolls to the right side, the automatic flight control system controls the yaw electric linear actuator to extend;

when the airplane descends, an accelerator and a small pitch need to be reduced, the automatic flight control system controls the accelerator push rod electric linear actuator to shorten, and controls the pitch push rod electric linear actuator to extend;

when the airplane is ready to land, the airplane head is slightly tilted upwards while a small accelerator and a small pitch are kept, the automatic flight control system controls and keeps the positions of the accelerator push rod electric linear actuator and the pitch push rod electric linear actuator, and the pitch electric linear actuator is controlled to contract; after the aircraft body naturally decelerates after landing, a minimum accelerator and a minimum pitch are needed, and other control surfaces are kept at initial positions; the automatic flight control system controls and keeps the throttle push rod electric linear actuator to retract to the minimum stroke, controls the pitch push rod electric linear actuator to extend to the maximum stroke, and keeps other actuators at the zero position.

Accordingly, it is another object of the present invention to provide an aircraft including an airplane piloting steering structure, the airplane piloting steering structure being the airplane piloting steering structure described above.

The scheme provided by the invention enables the existing airplane to realize unmanned piloting, is simultaneously suitable for upgrading the traditional piloted airplane into the unmanned pilotless airplane, gets rid of the dependence of the traditional airplane on pilots, reduces the flight cost and improves the safety and stability of the unmanned piloting of the existing airplane; the scheme provided by the invention can be applied to most of small and medium-sized general aviation aircrafts and experimental teaching scenes, and has a wide market prospect.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced 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 based on the drawings without creative efforts.

Fig. 1 is a first overall schematic view of an airplane piloting control structure provided in embodiment 1 of the present invention;

fig. 2 is a second overall schematic view of an aircraft piloting control structure provided in embodiment 1 of the present invention;

fig. 3 is a schematic structural view of an aircraft cockpit according to embodiment 1 of the present invention;

fig. 4 is a partial schematic view of an airplane piloting control structure provided in embodiment 1 of the present invention.

In the figure: 1. an aircraft cockpit; 2. a center console; 3. an automatic flight control device; 4. an actuator frame; 5. an aircraft steering column; 6. a first actuator; 7. a second actuator; 8. a propeller pitch push rod; 9. an accelerator push rod; 10. a first seat; 11. a second seat; 12. a rotating shaft; 13. pedaling the rotating shaft; 14. fixing the rod; 15. tightening the disc; 16. a rudder rotary table; 17. a third actuator; 18. a fourth actuator; 19. an actuator mount; 20. and a fifth actuator.

Detailed Description

The technical solutions in the embodiments of the present invention are 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 only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or quantity or location.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.