A fixed-pitch variable-speed twin-rotor tandem unmanned helicopter

Abstract

The invention discloses a fixed-pitch variable-speed twin-rotor tandem unmanned helicopter, which is composed of a body assembly, a power assembly and an attitude adjustment assembly arranged on the body in front and behind, and the attitude adjustment assembly is arranged one by one with the power assembly. In the invention, the pitch of the propeller remains unchanged, the lift is changed by adjusting the motor speed, and the attitude is changed by the tilting swash plate angle, the structure is simplified, the weight is reduced, the waste resistance is reduced, the cost is reduced, the reliability is improved, and the maintenance is simplified.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a fixed-pitch variable-speed twin-rotor tandem type unmanned helicopter. Background Art

[0002] Multi-rotor drones have a simple structure and low cost, but their payload and flight time are generally small. They are mostly used in applications with low requirements and short range, such as agricultural and forestry plant protection, film and television shooting, etc. Fixed-wing drones have high aerodynamic efficiency, long flight time, and fast flight speed, but they cannot hover and require a runway. They are mostly used in long-range application scenarios, such as geographic surveying and mapping, power line inspection, forest fire inspection, etc. Unmanned helicopters (referring to single-rotor tail-rotor unmanned helicopters, also known as conventional unmanned helicopters) can take off and land vertically (without a runway) and hover freely. Their flight time and flight speed are relatively moderate. They can be used in medium-range application scenarios, such as island transportation, aerial geophysical exploration, rescue and disaster relief, etc. Conventional unmanned helicopters have certain shortcomings, such as being difficult to control and having high requirements for flight control and control personnel. In addition, in order to increase the take-off weight, the rotor diameter needs to be increased. However, when the rotor diameter is too large, it will cause an increase in weight, higher costs, larger storage and transportation space, and poorer space survivability. In addition, a tail rotor needs to be installed to balance the anti-torque moment derived from the main rotor. Because of the presence of the tail rotor, the mechanical efficiency is low (tail rotor loss is about 7% to 12%), it is easily affected by side winds, the fuselage is too narrow and long, the tail failure rate is high, and the balancing process is cumbersome, and external attachments are easily affected by the landing gear.

[0003] The main advantage of a twin-rotor tandem helicopter is that the two rotors offset each other's anti-torque, and there is no need for a tail rotor or a tail beam to support the tail rotor. The blade size is small for the same lift, so the structure is relatively compact and there is no fault caused by the tail rotor. Secondly, the two rotors are arranged front and back along the longitudinal axis of the fuselage. In this form, the fuselage volume is large and the center of gravity can be moved in a large range. Since no special balancing is required, the loading and transportation efficiency is very high. Thirdly, since there is no tail rotor, the power loss is reduced, the power is relatively abundant, the ability to resist crosswinds is strong, and the load capacity is relatively high. At present, twin-rotor tandem helicopters generally use fully articulated hubs and three-servo swash plates, which are complex in structure, heavy in weight, and difficult to maintain, and the advantages of this model are not fully utilized. Summary of the invention

[0004] The object of the present invention is to provide a fixed-pitch variable-speed twin-rotor tandem unmanned helicopter without a speed reduction mechanism and a pitch change mechanism, which can solve the deficiencies existing in the background technology.

[0005] In order to solve the above-mentioned technical problems, the technical solution adopted by the present invention is:

[0006] A fixed-pitch variable-speed twin-rotor tandem unmanned helicopter consists of an airframe assembly, a power assembly and an attitude adjustment assembly arranged on the airframe front and rear. The attitude adjustment assembly and the power assembly are arranged in a one-to-one correspondence. A fixed-pitch propeller is used instead of a variable-pitch rotor. The lift size is changed by adjusting the motor speed. Lifting and lowering can be achieved by increasing or decreasing the motor speed. A dual-servo swash plate is used to change the orientation of the entire power assembly, thereby achieving pitch, roll and yaw, rather than achieving them through cyclic pitch variation.

[0007] The fuselage assembly includes side panels, reinforcement members, an upper panel, a bottom panel, a seat panel and a landing gear.

[0008] The machine body component adopts a plate structure, and is composed of two side plates, an upper plate, a lower plate, five reinforcement members sandwiched between the two side plates, and two seat plates for placing posture adjustment components to form the main frame of the machine body.

[0009] The landing gear adopts a skid-type structure and is connected to the reinforcement pieces at both ends through semicircular pipe clamps.

[0010] The posture adjustment assembly comprises a column, a fisheye bearing, a swash plate, a bearing cover, a ball head connecting rod, a steering gear and a steering gear seat, one end of the column is connected to the seat plate, the other end is inserted into the inner ring of the fisheye bearing and is provided with a shaft retaining ring for limiting, the outer ring of the fisheye bearing is placed in the bearing seat of the swash plate and is limited by the bearing cover screwed on the swash plate, one end of the ball head connecting rod is hinged on the swash plate, and the other end is hinged on the steering gear rocker arm, and the steering gear is installed on the steering gear seat screwed on the bottom of the seat plate;

[0011] The swash plate is tilted in a small angle range by only two steering gears without rotation and sliding, and the center lines of the two holes of the articulated ball head connecting rod and the center of the fisheye bearing are on the same plane.

[0012] The steering gear is installed on a steering gear seat screwed to the bottom of the seat plate and is arranged symmetrically on both sides.

[0013] The power assembly includes a motor, an electric speed controller, a propeller, a paddle and a fairing. One end of the motor is fixed on the swash plate, and the other end is directly connected to the propeller without passing through any transmission mechanism. The paddle is pressed on the propeller and the propeller is connected to the motor by screws. The electric speed controller is installed at the bottom of the seat plate, and the fairing is installed on the upper part of the paddle.

[0014] The power assembly adopts a direct drive structure, that is, the motor is directly connected to the propeller without any transmission mechanism.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] 1) The structure is simple, without transmission mechanism and pitch-changing mechanism. It can be composed of at least 20 kinds and more than 40 parts, with low cost, light weight, high reliability and easy maintenance;

[0017] 2) Simple control: raising and lowering can be achieved by increasing or decreasing the motor speed, and pitching, rolling and yaw can be achieved by tilting the swash plate angle;

[0018] 3) Low drag, a significant reduction in the number of parts and the use of a vertical panel fuselage within the xoy plane are all conducive to reducing air resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0020] Figure 2 It is a schematic diagram of the component composition of the present invention.

[0021] Figure 3 It is a schematic diagram of the body assembly of the present invention.

[0022] Figure 4 It is a schematic diagram of the posture adjustment component and the power component of the present invention. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings. The embodiments described here are only used to explain the present invention, rather than to limit the implementation methods of the present invention.

[0024] like Figure 1 As shown, a fixed-pitch variable-speed twin-rotor tandem unmanned helicopter is composed of a body component 1, a power component 2 and a posture adjustment component 3, and the posture adjustment component 3 and the power component 2 are arranged in a one-to-one correspondence.

[0025] like Figure 2 As shown, the fuselage assembly 1 includes two side panels 11, five reinforcement members 12, an upper panel 13, a lower panel 14, two seat panels 15 and a pair of landing gears 16. The two side panels 11, an upper panel 13, a lower panel 14, five reinforcement members 12 sandwiched between the two side panels and two seat panels 15 for placing the posture adjustment components constitute the main frame of the fuselage, and the skid-type landing gear 16 is connected to the reinforcement members 12 at both ends through semicircular pipe clamps.

[0026] like Figure 3 As shown, the side plate 11 is the main load-bearing component, which is fixedly connected by five reinforcement members 12. The upper plate 13 is screwed to the two upper reinforcement members 12, and can be used to place the GPS. The lower plate 14 is screwed to the three lower reinforcement members 12, and can be used to place batteries, flight control, data transmission radio, etc. The seat plate 15 is placed at the front and rear ends of the side plate 11, and is used to place the posture adjustment component 3.

[0027] The landing gear 16 adopts a skid-type structure and is connected to the reinforcement members at both ends through semicircular pipe clamps.

[0028] like Figure 4 As shown, the posture adjustment assembly 3 includes a column 31, a fisheye bearing 32, a swash plate 33, a bearing cover 34, a ball head connecting rod 35, a steering gear 36 and a steering gear seat 37. One end of the column 31 is connected to the seat plate 15, and the other end is inserted into the inner ring of the fisheye bearing 32 and is provided with a shaft retaining ring for limiting. The outer ring of the fisheye bearing 32 is placed in the bearing seat of the swash plate 33 and is limited by the bearing cover 34 screwed on the swash plate 33. One end of the ball head connecting rod 35 is hinged on the swash plate 33, and the other end is hinged on the steering gear rocker arm. The steering gear 36 is installed on the steering gear seat 37 screwed on the bottom of the seat plate.

[0029] The swash plate 33 is tilted within a small angle range by only two steering gears 36 without rotation and sliding. The center lines of the two holes of the articulated ball head connecting rod 35 and the center of the fisheye bearing 33 are on the same plane.

[0030] The steering gear 36 is mounted on a steering gear seat 37 screwed to the bottom of the seat plate, and is symmetrically arranged.

[0031] like Figure 4 As shown, the power assembly 2 includes a motor 21 , an electric speed controller 22 , a propeller 23 , a paddle 24 and a fairing 25 .

[0032] One end of the motor 21 is fixed on the swash plate 32, and the other end is directly connected to the propeller 23 without passing through any transmission mechanism. The paddle plate 24 is pressed on the propeller and the propeller 23 is connected to the motor 21 by screws. The electric regulator 22 is installed at the bottom of the seat plate 15, and the fairing 25 is installed on the upper part of the paddle plate 24.

[0033] Flight principle:

[0034] Up and down movement: Increase the motor speed at the same time to achieve ascending, and reduce the motor speed at the same time to achieve descending.

[0035] Forward and backward movement: The two servos push the ball-joint rod upwards at the same time, causing the swash plate to tilt forward, and the propeller lift produces a forward component, thus achieving forward movement. Conversely, the two servos pull the ball-joint rod downwards at the same time, causing the swash plate to tilt backwards, and the propeller lift produces a backward component, thus achieving backward movement.

[0036] Left and right movement: Pull the left servo downward and push the right servo upward to tilt both the front and rear swash plates to the left. The propeller lift produces a left component, which can achieve left movement. Push the left servo upward and pull the right servo downward to tilt both the front and rear swash plates to the right, which can achieve right movement.

[0037] Yaw movement: pull the front left servo downward, push the right servo upward, tilt the swash plate to the left, push the rear left servo upward, pull the right servo downward, and tilt the swash plate to the right to achieve counterclockwise yaw; push the front left servo upward, pull the right servo downward, tilt the swash plate to the right, pull the rear left servo downward, push the right servo upward, and tilt the swash plate to the left to achieve clockwise yaw.

[0038] The above embodiments are merely examples for illustrating the present invention and are not intended to limit the implementation methods of the present invention. For those skilled in the art, other different forms of changes can be easily thought of, and it is not necessary and impossible to list all the implementation methods here. Any electric motor made on the basis of the present invention falls within the protection scope of the present invention.

Claims

1. A fixed-pitch variable-speed twin-rotor tandem unmanned helicopter, characterized in that: The invention is composed of a body component and a power component and an attitude adjustment component arranged on the body in front and behind. The attitude adjustment component is arranged in a one-to-one correspondence with the power component. The body component includes side panels, reinforcements, an upper panel, a lower panel, a seat panel and a landing gear. Two side panels, an upper panel, a lower panel, five reinforcements sandwiched between the two side panels and two seat panels for placing the attitude adjustment components constitute the main frame of the body. The landing gear is connected to the reinforcements at both ends through semicircular pipe clamps; the upper panel is screwed to the two upper reinforcements to place the GPS; the lower panel is screwed to the three lower reinforcements to place the battery, flight control and data transmission radio; the attitude adjustment component includes a column, a fisheye bearing, a swash plate, a bearing cover, a ball head connecting rod, a servo and a servo seat. One end of the column is connected to the seat panel and the other end is inserted into the fisheye bearing. The inner ring is provided with a shaft retaining ring for limiting, the outer ring of the fisheye bearing is placed in the bearing seat of the swash plate and is limited by the bearing cover screwed on the swash plate, one end of the ball head connecting rod is hinged on the swash plate, and the other end is hinged on the steering gear rocker arm, and the steering gear is installed on the steering gear seat screwed on the bottom of the seat plate; the power assembly includes a motor, an electric regulator, a propeller, a paddle plate and a fairing, one end of the motor is fixed on the swash plate, and the other end is directly connected to the propeller without passing through any transmission mechanism, the paddle plate is pressed on the propeller and the propeller is connected to the motor by screws, the electric regulator is installed at the bottom of the seat plate, and the fairing is installed on the upper part of the paddle plate; the swash plate is pushed and tilted within a small angle range by only two servos, without rotation and sliding, and the center line of the two holes of the articulated ball head connecting rod is on the same plane as the center of the fisheye bearing.

2. The fixed-pitch variable-speed twin-rotor tandem unmanned helicopter according to claim 1, characterized in that: A fixed-pitch propeller is used to change the lift by adjusting the motor speed. Increasing or decreasing the motor speed can achieve lifting and lowering.

3. The fixed-pitch variable-speed twin-rotor tandem unmanned helicopter according to claim 1, characterized in that: It adopts double servo type swash plate.

4. The fixed-pitch variable-speed twin-rotor tandem unmanned helicopter according to claim 1, characterized in that: The landing gear adopts a skid-type structure.

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