CN110422327A - A kind of tilting rotor wing unmanned aerial vehicle triangle power configuration method and structure - Google Patents

Abstract

A kind of tilting rotor wing unmanned aerial vehicle triangle power configuration method and structure, it is characterized in that the method is respectively to install the blade that can vert in the wing of fuselage two sides and the tail portion of fuselage, three blades that can vert can make 90 degree of rotations, when takeoff condition, three blades that can vert are in a horizontal state, lift needed for vertical lift is provided simultaneously, after taking off, first change the direction of the blade that verts on tail, preceding to fly to provide power, complete the smooth conversion of the direction of motion, then left by rotation, starboard wing changes left, the direction of the blade that verts on starboard wing, preceding to fly to provide power, three can vert and blade while fly to provide power before being.Power configuration of the present invention is reasonable, powerful, and conversion is steady, and safety is greatly improved.

Description

A kind of triangular power configuration method and structure of a tilt-rotor unmanned aerial vehicle

technical field

The invention relates to an unmanned aerial vehicle, in particular to an unmanned aerial vehicle power configuration technology, in particular to a power configuration method and structure of a triangular tilt-rotor unmanned aerial vehicle.

Background technique

As we all know, the landing power of UAVs has always been the focus of people's research, and different power configurations will produce different technical effects. But as far as the applicant knows, people's current research focus is still on how to improve the forward power of take-off power by increasing the power of the oil-driven engine, and by configuring tiltable blades for the UAV, by changing the arrangement of the blades and There have been no relevant reports on how to improve the take-off and forward performance of UAVs, especially how to improve the stability of the transition between take-off and landing and level flight has been difficult to solve.

Contents of the invention

The purpose of the present invention is to solve the problem that the power configuration mode of the existing unmanned aerial vehicle is single, invent a kind of triangular tilt rotor unmanned aerial vehicle power configuration method and structure that can obviously improve the lift and speed, and at the same time, provide the corresponding unmanned aerial vehicle structure.

One of technical solutions of the present invention is:

A triangular power configuration method and structure of a tilting-rotor unmanned aerial vehicle, which is characterized in that a tiltable blade is installed on the wings on both sides of the fuselage and the tail of the fuselage, and the three tiltable blades can all be used as Rotate at 90 degrees. In the take-off state, the three tiltable blades are all in a horizontal state, and at the same time provide the lift required for vertical lift. After take-off, first change the direction of the tiltable blades on the tail to the vertical direction to achieve Flying forward at a small speed provides lift to complete the smooth transition of the direction of motion, and then changes the direction of the tiltable blades on the left and right wings by rotating the left and right wings to provide the main force for forward flight, and finally the three tiltable blades The blades also provide forward flight power. The two tiltable blades installed on the left and right wings use an oil-driven engine as a power source, and the tiltable blades on the tail adopt electric power as a power source, and the electric power comes from a battery or an oil-driven engine to generate electricity. produce.

The three tiltable blades all use oil-powered generators or electric power as power sources, and the electric power still comes from generators driven by oil-powered engines.

The second technical scheme of the present invention is:

A kind of tilting-rotor unmanned aerial vehicle, it comprises fuselage 1 and tail plane tail 6, and the two sides of fuselage are respectively connected with the left wing 2 that can rotate 90 degrees and the right wing 5 that can rotate 90 degrees, it is characterized in that Tail tail 6 is equipped with tail tiltable blade 7, left side tiltable blade 3 is installed on left wing 2, right side tiltable blade 4 is installed on right wing 5, tail The tiltable paddle 7 , the left side tiltable paddle 3 and the right side tiltable paddle 4 are driven by respective power sources or by the same power source.

The power source of the left tiltable blade 3 and the right tiltable blade 4 is an oil-powered engine, and the power source of the tail tiltable blade 7 comes from electric power, and the electric power comes from a battery or an oil-powered engine Generate electricity.

The tail tiltable blade 7, the left side tiltable blade 3 and the right side tiltable blade 4 are all powered by an oil-powered engine or are powered by an electric power source, and the electric power source is still powered by an oil-powered engine. generating electricity from the engine.

Beneficial effects of the present invention:

The power configuration of the invention is reasonable, the power is strong, the conversion is stable, and the safety is greatly improved.

Description of drawings

Fig. 1 is a schematic diagram of the power configuration structure of the unmanned aerial vehicle of the present invention.

Fig. 2 is a structural schematic diagram of the conversion stage of the UAV of the present invention.

Fig. 3 is a schematic diagram of the high-speed forward flight state of the drone of the present invention.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

Embodiment one.

As shown in Figure 1.

A triangular power configuration method and structure of a tilting-rotor unmanned aerial vehicle, the key of which is to install a tiltable blade on the wings on both sides of the fuselage and the tail of the fuselage, and the three tiltable blades can all be used as Rotate at 90 degrees. In the take-off state, the three tiltable blades are all in a horizontal state, and at the same time provide the lift required for vertical lift. After take-off, first change the direction of the tiltable blades on the tail to the vertical direction to achieve Flying forward at a small speed provides lift to complete the smooth transition of the direction of motion, and then changes the direction of the tiltable blades on the left and right wings by rotating the left and right wings to provide the main force for forward flight, and finally the three tiltable blades The blades also provide forward flight power. As shown in Figure 1, the power configuration during specific implementation can be implemented in the following ways, and the specific structure can be realized by referring to the relevant patents previously applied by the applicant. 1. The two tiltable blades installed on the left and right wings use the oil-driven engine as the power source, and the tiltable blades on the tail use electric power as the power source, and the electric power comes from batteries or generated by the oil-driven engine. . 2. The three tiltable blades all use oil-powered generators or electric power as power sources, and the electric power still comes from generators driven by oil-powered engines.

Embodiment two.

A kind of tilting-rotor unmanned aerial vehicle, it comprises fuselage 1 and flat-tail tail 6, the left wing 2 that can rotate 90 degrees and the right wing 5 that can rotate 90 degrees are respectively connected on the both sides of fuselage, in flat-tail The tail 6 is equipped with a tail tiltable blade 7, a left side tiltable blade 3 is installed on the left wing 2, a right side tiltable blade 4 is installed on the right wing 5, and the tail is tiltable The paddle 7, the left side tiltable paddle 3 and the right side tiltable paddle 4 are driven by respective power sources or by the same power source. As shown in Figure 1, the power configuration of each tiltable blade can refer to the following methods: 1. The power source of the left side tiltable blade 3 and the right side tiltable blade 4 is an oil-powered engine, and the tail can be tilted. The power source of turning paddle 7 comes from electric power, and electric power comes from accumulator or oil-driven engine and generates electricity; Power is provided by an oil-powered engine or both are powered by an electric power source, and the electric power source is still generated by the oil-powered engine. The specific power transmission structure can refer to the relevant patents previously applied by the applicant or design and manufacture by itself.

Working process of the present invention is:

1. Take-off stage: As shown in Figure 1, the left tiltable power source and blade 3, the right tiltable power source and blade 4, and the tail tiltable power source and blade 7 jointly provide the UAV Takeoff lift of , with the tail blades under the fuselage.

2. The conversion stage of vertical flight to level flight: as shown in Figure 2, at the initial stage of conversion, the tail rotor 7 first turns 90 degrees to provide part of the power for forward flight. After the UAV generates a relatively good wing lift, it slowly tilts Turn the wings and blades on the left and right sides to provide greater forward flight power. Due to the forward flight lift provided by the tail rotor 7 in advance, the conversion process becomes relatively smooth and the drop height is greatly reduced. There are two power schemes in this embodiment,

3. Level flight stage: the propellers on the left and right sides and the tail propellers provide power for forward flight, and the forward flight speed of the aircraft is greatly improved, as shown in Figure 3.

There are two commonly used schemes for the power configuration of this embodiment:

Option 1: The power propellers on the left and right sides are driven by oil-powered engines, and the power of the tail propellers is driven by electric motors.

Option 2: Oil-electric hybrid, the three sets of propellers are all driven by motors, and a high-power engine is installed in the fuselage to drive the generator to generate electricity for the three power motors. This solution can effectively reduce the transmission mechanism, greatly reduce the overall weight of the UAV, and at the same time reduce the failure rate, making maintenance relatively simple.

The parts not involved in the present invention are the same as the prior art or can be realized by adopting the prior art.

Claims (6)

1. A kind of triangular power configuration method and structure of a tilting rotor unmanned aerial vehicle, it is characterized in that a tiltable blade is respectively installed at the tail of the wing on both sides of the fuselage and the fuselage, and the three tiltable blades are all It can rotate 90 degrees. In the take-off state, the three tiltable blades are all in a horizontal state, and at the same time provide the lift required for vertical lift. After take-off, first change the direction of the tiltable blades on the tail to the vertical direction. , to achieve low-speed forward flight to provide lift, complete the smooth conversion of the direction of motion, and then change the direction of the tiltable blades on the left and right wings by rotating the left and right wings to provide the main force for forward flight. Finally, the three can Tilting the blades also provides forward flight power. 2. The method according to claim 1, wherein the two tiltable blades installed on the left and right wings adopt an oil-driven engine as a power source, and the tiltable blades on the tail adopt electric power. As a power source, electric power comes from a battery or an oil-powered engine to generate electricity. 3. The method according to claim 1, characterized in that the three tiltable blades all use oil-powered generators or electric power as power sources, and the electric power still comes from generators driven by oil-powered engines . 4. A tilt-rotor UAV, which includes a fuselage (1) and a flat tail (6). The two sides of the fuselage are respectively connected with a left wing (2) that can rotate 90 degrees and a rotatable 90 degrees. The right wing (5) is characterized in that the tail tiltable blade (7) is installed on the flat tail (6), and the left side tiltable blade (3) is installed on the left wing (2). On the right wing (5), the right side tiltable blade (4) is installed, the tail portion tiltable blade (7), the left side tiltable blade (3) and the right side tiltable blade ( 4) Driven by their own power sources or by the same power source. 5. The UAV according to claim 4, characterized in that the power source of the left tiltable blade (3) and the right tiltable blade (4) is an oil-powered engine, and the tail can be The power source of the tilting blade (7) comes from electric power, and the electric power comes from a storage battery or an oil-powered engine to generate electricity. 6. The UAV according to claim 4, characterized in that the tail tiltable blade (7), the left side tiltable blade (3) and the right side tiltable blade (4) All are powered by the oil-powered engine or all are powered by the electric power source, and the electric power source is still generated by the oil-powered engine.