阅读说明：本技术 运五改无人机系统的发动机操纵系统 (Engine control system of five-in-one unmanned aerial vehicle system ) 是由 雷黎明 郭宏选 董文斌 沈洋 于 2020-10-27 设计创作，主要内容包括：本发明公开的运五改无人机系统的发动机操纵系统,包括中央操纵台,中央操纵台上表面固接操纵台面板,操纵台面板安装汽化器舵机系统、桨距舵机系统、油门舵机系统,中央操纵台一侧面安装停车舵机系统,中央操纵台另一侧面安装高空舵机系统、防尘舵机系统,汽化器舵机系统、桨距舵机系统、油门舵机系统、停车舵机系统、高空舵机系统、防尘舵机系统均连接发动机。本发明的运五改无人机系统的发动机操纵系统,具有结构简单、可靠性高的特点,解决了现有运五飞行员紧缺,运五飞机空置增加,资源浪费的问题。(The invention discloses an engine control system of a five-in-one unmanned aerial vehicle system, which comprises a central control console, wherein the upper surface of the central control console is fixedly connected with a control console panel, the control console panel is provided with a carburetor steering engine system, a propeller pitch steering engine system and an accelerator steering engine system, one side surface of the central control console is provided with a parking steering engine system, the other side surface of the central control console is provided with a high-altitude steering engine system and a dustproof steering engine system, and the carburetor steering engine system, the propeller pitch steering engine system, the accelerator steering engine system, the parking steering engine system, the high-altitude steering engine system and the. The engine control system of the five-in-five unmanned aerial vehicle system has the characteristics of simple structure and high reliability, and solves the problems of shortage of five-in-five pilots, increase of vacant space of five-in-five aircrafts and resource waste in the prior art.)

1. An engine control system of an unmanned aerial vehicle system is changed from five to five, and is characterized by comprising a central control console (1), wherein the upper surface of the central control console (1) is fixedly connected with a control console panel (2), a carburetor steering engine system, a propeller pitch steering engine system and an accelerator steering engine system are installed on the control console panel (2), a parking steering engine system is installed on one side surface of the central control console (1), a high-altitude steering engine system and a dustproof steering engine system are installed on the other side surface of the central control console (1), and the carburetor steering engine system, the propeller pitch steering engine system, the accelerator steering engine system, the parking steering engine system, the high-altitude steering engine system and the dustproof steering engine system are all connected with.

2. The engine control system of the unmanned aerial vehicle system is changed into five fortune according to claim 1, characterized in that, the carburetor steering engine system includes a steering engine a (3) fixed on a console panel (2), a rotating shaft key of the steering engine a (3) is connected with a rocker arm a (4), the rocker arm a (4) is hinged with a connecting rod a (5), the connecting rod a (5) is hinged with a carburetor heating rod (6), the console panel (2) is provided with a chute a (7), and the chute a (7) is connected with the bottom of the carburetor heating rod (6) in a sliding manner; the carburetor warming rod (6) is connected with a carburetor warming control device of the engine through an engine control pull rod.

3. The engine control system of the unmanned aerial vehicle system is changed to fortune five as claimed in claim 2, characterized in that, pitch steering wheel system includes steering wheel b (8) that is fixed in operation panel (2), key connection rocking arm b (9) in the pivot of steering wheel b (8), articulated connecting rod b (10) on rocking arm b (9), connecting rod b (10) articulated pitch pole (11), operation panel (2) are seted up spout b (12), spout b (12) inside sliding connection pitch pole (11) bottom, pitch pole (11) pass through the pitch controlling means of cable wire connection engine.

4. The engine control system of the unmanned aerial vehicle system is changed to fortune five of claim 3, characterized in that, throttle steering wheel system includes steering wheel c (13) that is fixed in operation panel (2), the pivot key-type connection rocking arm c (14) of steering wheel c (13), rocking arm c (14) hinge connecting rod c (15), connecting rod c (15) hinge throttle lever (16), operation panel (2) are seted up spout c (17), sliding connection throttle lever (16) bottom in spout c (17), throttle lever (16) are through the throttle control mechanism of engine control pull rod connection engine.

5. The engine control system of the unmanned aerial vehicle system with the five motors as claimed in claim 4, wherein the steering engine b (8) and the steering engine c (13) are arranged in parallel on the upper side of the console panel (2), and the rocker arm b (9) and the rocker arm c (14) are arranged oppositely between the steering engine b (8) and the steering engine c (13); steering wheel a (3), steering wheel b (8), steering wheel c (13) are the dual redundancy steering wheel.

6. The engine control system of the unmanned aerial vehicle system is changed to fortune five according to claim 1 or 5, characterized in that, the steering wheel system that parks includes steering wheel d (18) of being fixed in a side of central console (1), the pivot key-type connection rocking arm d (19) of steering wheel d (18), rocking arm d (19) articulated torsion bar a (20), torsion bar a (20) articulated parking rod (21), rocking arm d (19) and parking rod (21) equal arm length, with the pivot, spout d (22) that console panel (2) was seted up, spout d (22) inside sliding connection parking rod (21) bottom, parking rod (21) pass through the parking control device of cable junction engine.

7. The engine control system of the unmanned aerial vehicle system as claimed in claim 6, wherein the high altitude steering engine system comprises a steering engine e (23) fixed on the side surface of the central console (1), a rotating shaft key of the steering engine e (23) is connected with a rocker arm e (24), the rocker arm e (24) is hinged with a torsion bar b (25), and the torsion bar b (25) is hinged with a high altitude bar (26); a chute e (27) is formed in the console panel (2), the chute e (27) is internally connected with the bottom of the high-altitude rod (26) in a sliding manner, and the rocker arm e (24) and the high-altitude rod (26) have equal arm length and rotate together with the shaft; the high altitude rod (26) is connected with an air inlet control device of the engine through an original engine control pull rod of the airplane.

8. The engine control system of the unmanned aerial vehicle system as defined in claim 7, wherein the dustproof steering engine system comprises a steering engine f (28) fixed on the side of the central console (1), a rotating shaft of the steering engine f (28) is connected with a rocker arm f (29) in a key manner, the rocker arm f (29) is hinged with a torsion bar c (30), the torsion bar c (30) is hinged with a dustproof bar (31), a sliding groove f (32) is formed in the console panel (2), and the inside of the sliding groove f (32) is connected with the bottom of the dustproof bar (31) in a sliding manner; the rocker arm f (29) and the dust-proof rod (31) have the same arm length and rotate together; the dust-proof rod (31) is connected with an air inlet filter screen control device of the engine through a steel cable.

9. The engine control system of the five-in-one unmanned aerial vehicle system according to claim 8, wherein the steering engine d (18) is located on one side surface of the central console (1), the steering engine e (23) and the steering engine f (28) are oppositely arranged on the other side surface of the central console (1), and the steering engine d (18), the steering engine e (23) and the steering engine f (28) are single-redundancy steering engines.

Technical Field

The invention belongs to the technical field of large unmanned aerial vehicle power control systems, and particularly relates to an engine control system of an unmanned aerial vehicle system.

Background

The five-airplane transportation aircraft is a single-engine double-wing and semi-metal navigation aircraft, has good low-altitude and ultra-low-altitude flight performance, can take off and land on a short simple runway, is mature and reliable in performance, simple to maintain, widely applied to short-distance transportation and agricultural planting operation, and has huge reserves in China and all over the world.

However, the five-airplane fortune pilot has an early design, a small cockpit and no air conditioning system, and facilities in the cockpit are simple and crude, so that the comfort of the pilot and passengers is not fully considered, and the pilot of the five-airplane fortune pilot has a poor driving environment and poor experience. At present, the number of pilots willing to drive the five-plane carrier to perform tasks is less and less, and the five-plane carrier has more and more empty phenomena.

With the development of large unmanned aerial vehicle technology, the relevant control theory and technology become more mature, the five-plane transport is changed into the unmanned aerial vehicle to become a feasible model selection, and the dilemma of five-pilot transport in short supply can be effectively solved. In the process of changing five-plane into an unmanned aerial vehicle system, how to carry out unmanned control on an engine is made a key problem.

Disclosure of Invention

The invention aims to provide an engine control system of an unmanned aerial vehicle system modified from a carrier flight control system, which solves the problems that the existing carrier flight control system for carrier flight control is in short supply and the number of vacant carriers for carrier flight control is increased.

The engine control system of the five-in-one unmanned aerial vehicle system comprises a central control console, wherein a control console panel is fixedly connected to the upper surface of the central control console, a carburetor steering engine system, a propeller pitch steering engine system and an accelerator steering engine system are mounted on the control console panel, a parking steering engine system is mounted on one side surface of the central control console, a high-altitude steering engine system and a dustproof steering engine system are mounted on the other side surface of the central control console, and the carburetor steering engine system, the propeller pitch steering engine system, the accelerator steering engine system, the parking steering engine system, the high-altitude steering engine system and the dustproof steering engine system are all connected with an engine.

The present invention is also characterized in that,

the carburetor steering engine system comprises a steering engine a fixed on a console panel, a rotating shaft key of the steering engine a is connected with a rocker arm a, the rocker arm a is hinged with a connecting rod a, the connecting rod a is hinged with a carburetor heating rod, the console panel is provided with a chute a, and the bottom of the carburetor heating rod is in sliding connection in the chute a; the carburetor warming rod is connected with a carburetor warming control device of the engine through an engine control pull rod.

The pitch steering engine system comprises a steering engine b fixed on a control console panel, a rotating shaft of the steering engine b is connected with a rocker arm b through a key, the rocker arm b is hinged with a connecting rod b, the connecting rod b is hinged with a pitch rod, a chute b is formed in the control console panel, the inside of the chute b is connected with the bottom of the pitch rod in a sliding mode, and the pitch rod is connected with a pitch control device of the engine through a steel cable.

The accelerator steering engine system comprises a steering engine c fixed on an operating panel, a rotating shaft key of the steering engine c is connected with a rocker arm c, the rocker arm c is hinged with a connecting rod c, the connecting rod c is hinged with an accelerator lever, a chute c is formed in the operating panel, the bottom of the accelerator lever is connected in the chute c in a sliding mode, and the accelerator lever is connected with an accelerator control mechanism of an engine through an engine operating pull rod.

The steering engine b and the steering engine c are arranged on the upper side of the console panel in parallel, and the rocker arm b and the rocker arm c are arranged between the steering engine b and the steering engine c in an opposite mode; steering wheel a, steering wheel b, steering wheel c are the dual redundancy steering wheel.

The parking steering engine system comprises a steering engine d fixed on one side face of a central control console, a rotating shaft key of the steering engine d is connected with a rocker arm d, the rocker arm d is hinged with a torsion bar a, the torsion bar a is hinged with a parking rod, the rocker arm d and the parking rod have equal arm length and rotate together with the rotating shaft, a sliding groove d is formed in a panel of the control console, the inside of the sliding groove d is connected with the bottom of the parking rod in a sliding manner, and the parking rod is connected with a parking control;

the high-altitude steering engine system comprises a steering engine e fixed on the side surface of the central control console, a rotating shaft key of the steering engine e is connected with a rocker arm e, the rocker arm e is hinged with a torsion bar b, and the torsion bar b is hinged with a high-altitude rod; a chute e is formed in the control console panel, the inside of the chute e is connected with the bottom of the high-altitude rod in a sliding mode, and the rocker arm e and the high-altitude rod have equal arm length and are coaxial; the high-altitude rod is connected with an air inlet control device of the engine through an original engine control pull rod of the airplane.

The dustproof steering engine system comprises a steering engine f fixed on the side surface of the central control console, a rotating shaft key of the steering engine f is connected with a rocker arm f, the rocker arm f is hinged with a torsion bar c, the torsion bar c is hinged with a dustproof rod, a sliding groove f is formed in a panel of the control console, and the inside of the sliding groove f is connected with the bottom of the dustproof rod in a sliding manner; the rocker arm f and the dust-proof rod have the same arm length and rotate together with the shaft; the dust-proof rod is connected with an air inlet filter screen control device of the engine through a steel cable.

Steering wheel d is located one side on the central control board, steering wheel e and steering wheel f set up in central control board another side relatively, and steering wheel d, steering wheel e, steering wheel f are the single redundancy steering wheel.

The invention has the beneficial effects that:

(1) the invention provides an engine control system of a five-in-one unmanned aerial vehicle system, which is additionally provided with the device on the basis of the existing five-in-one airplane, the five-in-one airplane is changed into the unmanned aerial vehicle system, all functions of engine control of the original five-in-one airplane can be realized, and the consistency of the performance of the five-in-one unmanned aerial vehicle and the original five-in-one airplane power system is ensured;

(2) the invention is based on the original aircraft engine control system, keeps the original aircraft engine control logic, has simple operation and has the characteristic of high reliability;

(3) the invention has fewer structural components and simple transmission relation, and simultaneously, the key equipment adopts redundancy design and has higher safety.

Drawings

FIG. 1 is a schematic structural diagram of an engine control system of the UAV system of the present invention;

fig. 2 is a top view of the engine control system of the modified drone system of the present invention.

In the figure, 1, a central console, 2, a console panel, 3, steering gears a, 4, rocker arms a, 5, connecting rods a, 6, a carburetor heating rod, 7, a sliding groove a, 8, a steering gear b, 9, a rocker arm b, 10, a connecting rod b, 11, a propeller pitch rod, 12, a sliding groove b, 13, a steering gear c, 14, a rocker arm c, 15, a connecting rod c, 16, an accelerator rod, 17, a sliding groove c, 18, a steering gear d, 19, a rocker arm d, 20, a torque rod a, 21, a parking rod, 22, a sliding groove d, 23, a steering gear e, 24, a rocker arm e, 25, a torque rod b, 26, a high altitude rod, 27, a sliding groove e, 28, a steering gear f, 29, a rocker arm f, 30, a torque rod c, 31, a dust-proof rod and 32, a sliding groove f.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

The invention discloses an engine control system of a five-in-one unmanned aerial vehicle system, which comprises a central control console 1, wherein a control console panel 2 is fixedly connected to the upper surface of the central control console 1, a carburetor steering engine system, a pitch steering engine system and an accelerator steering engine system are mounted on the control console panel 2, a parking steering engine system is mounted on one side surface of the central control console 1, a high-altitude steering engine system and a dustproof steering engine system are mounted on the other side surface of the central control console 1, and the carburetor steering engine system, the pitch steering engine system, the accelerator steering engine system, the parking steering engine system, the high-altitude steering engine system and the dustproof steering engine system are all connected with.

The carburetor steering engine system comprises a steering engine a3 fixed on the control console panel 2, a rotating shaft key of the steering engine a3 is connected with a rocker arm a4, the rocker arm a4 is hinged with a connecting rod a5, the connecting rod a5 is hinged with the carburetor heating rod 6, the control console panel 2 is provided with a chute a7, and the chute a7 is in sliding connection with the bottom of the carburetor heating rod 6; the steering engine a3 drives the vaporizer warming rod 6 to rotate around the shaft; the carburetor warming rod 6 is connected with a carburetor warming control device of the engine through an original engine control pull rod.

One end of a rocker arm a4 is connected with a steering engine a3 through a rotating shaft, the other end of the rocker arm a4 is hinged with a connecting rod a5, and the connecting rod a5 is hinged with a vaporizer heating rod 6; a double rocker arm mechanism is formed among the rocker arm a4, the connecting rod a5 and the carburetor heating rod 6, the steering engine a3 drives the rocker arm a4 to act, and the carburetor heating rod 6 can be controlled to slide in the sliding groove a7 through transmission of the double rocker arm mechanism.

The pitch steering engine system comprises a steering engine b8 fixed on the control console panel 2, a rocker arm b9 is connected to a rotating shaft of the steering engine b8 through a key, a connecting rod b10 is hinged to the rocker arm b9, and a connecting rod b10 is hinged to the pitch rod 11 to form a double-rocker arm mechanism; the operating table panel 2 is provided with a sliding groove b12, the inside of the sliding groove b12 is connected with the bottom of the pitch rod 11 in a sliding manner, and the steering engine b8 drives the pitch rod 11 to rotate around a shaft; the pitch rod 11 is connected with a pitch control device of the engine through an original steel cable of the airplane.

The accelerator steering engine system comprises a steering engine c13 fixed on the console panel 2, a rotating shaft key of a steering engine c13 is connected with a rocker arm c14, the rocker arm c14 is hinged with a connecting rod c15, and a connecting rod c15 is hinged with an accelerator lever 16 to form a double-rocker arm mechanism; the operating board panel 2 is provided with a chute c17, and the chute c17 is connected with the bottom of the throttle lever 16 in a sliding way; the steering engine c13 drives the throttle lever 16 to rotate around the shaft; the throttle lever 16 is connected with a throttle control mechanism of the engine through an original aircraft engine control pull rod.

The steering engine b8 and the steering engine c13 are arranged on the upper side of the console panel 2 in parallel, and the rocker arm b9 and the rocker arm c14 are oppositely arranged between the steering engine b8 and the steering engine c 13; steering engine a3, steering engine b8 and steering engine c13 are dual-redundancy steering engines.

The parking steering engine system comprises a steering engine d18 fixed on one side surface of the central console 1, a rotating shaft key of a steering engine d18 is connected with a rocker arm d19, the rocker arm d19 is hinged with a torsion bar a20, the torsion bar a20 is hinged with the parking rod 21, the rocker arm d19 and the parking rod 21 have the same arm length and rotate with the same shaft, and the steering engine d18 drives the parking rod 21 to realize synchronous motion; the sliding chute d22 is arranged on the control console panel 2, the inside of the sliding chute d22 is connected with the bottom of the parking rod 21 in a sliding way, and the parking rod 21 is connected with a parking control device of an engine through an original steel cable of the airplane;

the high-altitude steering engine system comprises a steering engine e23 fixed on the side surface of the central console 1, a rotating shaft key of a steering engine e23 is connected with a rocker arm e24, the rocker arm e24 is hinged with a torsion bar b25, and the torsion bar b25 is hinged with a high-altitude bar 26; a sliding groove e27 is formed in the control console panel 2, the inside of the sliding groove e27 is connected with the bottom of the high altitude rod 26 in a sliding manner, and the rocker arm e24 and the high altitude rod 26 have the same arm length and rotate together; the steering engine e23 drives the high-altitude rod 26 to realize synchronous motion, and the high-altitude rod 26 is connected with an air inlet control device of an engine through an original engine control pull rod of the airplane.

The dustproof steering engine system comprises a steering engine f28 fixed on the side surface of the central control console 1, a rotating shaft key of a steering engine f28 is connected with a rocker arm f29, the rocker arm f29 is hinged with a torsion bar c30, the torsion bar c30 is hinged with a dustproof bar 31, a sliding groove f32 formed in the control console panel 2, and the inside of the sliding groove f32 is connected with the bottom of the dustproof bar 31 in a sliding manner; the rocker arm f29 and the dust-proof rod 31 have the same arm length and rotate together; the steering engine f28 drives the dust-proof rod 31 to realize synchronous motion; the dust-proof rod 31 is connected with an air inlet filter screen control device of the engine through an original steel cable of the airplane.

Steering engine d18 is located and is close to steering engine a3 one side on central console 1, and steering engine e23 and steering engine f28 are relative to be set up in central console 1 another side, and steering engine d18, steering engine e23, steering engine f28 are the single redundancy steering engine.

The working process and the principle of the engine control system of the five-in-one unmanned aerial vehicle system are as follows:

a steering engine d18 of the parking steering engine system drives a rocker arm d19 to rotate, a rocker arm d19 drives a parking rod 21 to synchronously rotate in a chute d22 through a torsion bar a20, and the parking rod 21 is connected with an engine parking control device through an original transmission steel cable; when the stop rod 21 is positioned at the rear limit position in the sliding groove d22, the carburetor steering engine system stops supplying oil, and the engine stops; when the stop lever 21 is located at the front limit position in the sliding groove d22, the carburetor steering engine system supplies oil, and the engine works normally.

A steering engine a3 of the carburetor steering engine system drives a rocker arm a4 to rotate, the rocker arm a4 pushes a carburetor heating rod 6 to rotate through a connecting rod a5, and the carburetor heating rod 6 is connected with a carburetor heating control device of an engine through an original engine control pull rod of the airplane; the vaporizer heating rod 6 is pushed to the front limit position in the chute a7, the vaporizer heating control device is in the maximum heating state, and the temperature of the vaporizer is highest; the carburetor warming lever 6 moves to the rear limit position in the chute a7, and the carburetor throttle is closed, at which time the carburetor is not warmed.

A pitch steering engine system steering engine b8 drives a rocker arm b9 to rotate, a rocker arm b9 pushes a pitch rod 11 to rotate through a connecting rod b10, and the pitch rod 11 is connected with an engine pitch control device through an original steel cable of the airplane to adjust the pitch of the propeller; the pitch of the pitch rod 11 is minimum when the pitch rod 11 is at the front limit position in the sliding chute b12, and the pitch of the pitch rod 11 is maximum when the pitch rod 11 is at the rear limit position in the sliding chute b 12; the full stroke of the pitch rod 11 can ensure that the engine keeps constant speed within the range of 2200 to 1500 rpm.

The accelerator steering engine system steering engine c13 drives the rocker arm c14 to rotate, the rocker arm c14 pushes the accelerator lever 16 to rotate through a connecting rod, and the accelerator lever 16 is connected with an engine accelerator control device through an original engine control pull rod of the airplane to adjust the power of the engine; when the throttle lever 16 moves to the rear limit position in the chute c17, the state is the engine slow running state; when the engine is pushed to the front limit position in the chute c17, the engine is in a take-off power state.

The high-altitude steering engine system steering engine e23 drives the rocker arm e24 to rotate, the rocker arm e24 drives the high-altitude rod to synchronously rotate in the chute e27 through the torsion bar b25, and the high-altitude rod 26 is connected with an engine air inlet control device through an original engine control pull rod of the airplane and used for adjusting the air inlet amount of an air inlet channel so as to change the oil-gas mixing ratio; when the high altitude rod 26 is located at the rear limit position in the sliding groove e27, the air inflow is minimum, and the engine is in an oil-rich state; when the high-altitude rod 26 is located at the front limit position in the slide groove e27, the air inflow is the largest, and the engine is in a lean state.

A dustproof steering engine system steering engine f28 drives a rocker arm f29 to rotate, the rocker arm f29 drives a dustproof rod 31 to synchronously rotate in a chute f32 through a torsion bar c30, and the dustproof rod 31 is connected with an engine air inlet filter screen control device through an original steel cable of an airplane; the dust-proof rod 31 is positioned at the rear limit position in the sliding groove f32, and air enters the engine through the filter screen; the dust-proof rod 31 rotates to the front limit position in the sliding groove f32, the air filter screen is laid down, and the air entering the engine is not filtered.

The engine control system of the invention has simple structure, clear transmission relation and accurate operation input; each operating lever reserves the adjustment allowance, and can completely realize all functions of the engine and exert all performances; the redundancy design is adopted, so that the reliability and the safety are high; the system components are reasonably arranged, the structure is compact, and the system components have good inspection and maintenance access.