CN106938701A - It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula four - Google Patents

Abstract

The invention discloses a tail seat type four-rotor canard layout aircraft capable of vertical take-off and landing, which is composed of a fuselage, wings, canards, vertical tail and a power device. The two sides of the tail of the fuselage are wings, the top and bottom of the tail of the fuselage are respectively provided with vertical tails, and the wing tips and the vertical tail tips are respectively provided with power devices; the power devices are variable pitch propellers, and the rotating shaft of the power The axes of the fuselage are parallel. The wing tip of the four-rotor canard layout aircraft, the vertical tail wing tip and the rear end of the fuselage jointly form five support points; when in a stopped state, the five support points make the aircraft stop vertically upward on the ground. The vertical take-off and landing response speed of the aircraft is fast, and it has good maneuverability, stability and wind resistance performance during vertical take-off and landing. The aircraft adopts a canard layout, can fly at high speed and level with fixed wings, has a long flight time, and has good maneuverability and maneuverability.

Description

A tail seat type quadrotor canard layout aircraft capable of vertical take-off and landing

technical field

The invention relates to a vertical take-off and landing aircraft, in particular to a tail seat type four-rotor canard layout aircraft capable of vertical take-off and landing.

Background technique

Air vehicle design experts and researchers have been trying to design a vehicle that can take off and land short distances or vertically. To solve the problems that fixed-wing aircraft are limited by the take-off and landing site and the tilt-rotor aircraft has slow flight speed and short endurance time, as well as the problems of low control efficiency and poor wind resistance of the existing tailseat vertical take-off and landing fixed-wing unmanned aircraft .

At present, in practical applications, unmanned aerial vehicles are generally divided into two types: fixed-wing aircraft and rotary-wing aircraft. Although conventional fixed-wing unmanned aerial vehicles have the characteristics of fast speed, long range and long cruise time, they have long take-off and landing distances and require High-quality runways, take-off and landing are restricted by the geographical environment, and cannot hover in the air, so the application is limited; while the rotor UAV can take off and land vertically in a complex and narrow field without being restricted by the take-off and landing site, but the rotor efficiency Far inferior to the wings of fixed-wing aircraft, the power consumption is large and the flight resistance is large, thus affecting the flight speed and endurance time.

With the wide application of unmanned aerial vehicles, the requirements for the take-off and landing performance and endurance performance of unmanned aerial vehicles have been greatly improved. Since the fixed-wing aircraft that can take off and land vertically has the characteristics of fast speed, long range, and long cruise time of fixed-wing aircraft and Rotorcraft can perform all-terrain takeoff and landing capabilities in complex and narrow areas such as mountains, jungles, and ship decks. Therefore, fixed-wing unmanned aerial vehicles that can take off and land vertically have become a research hotspot.

The existing fixed-wing UAVs that can take off and land vertically include two types: tilting power type and tail seat type. Tilting power vertical take-off and landing fixed-wing unmanned aerial vehicle, through the tilting rotor or jet engine, the power can be converted from horizontal to vertical. When the power direction becomes vertical, it can take off and land vertically and hover by overcoming gravity, becoming Level forward flight by overcoming air resistance when level. The disadvantage of this vertical take-off and landing method is that the power tilting mechanism will increase the weight and complexity of the structure and reduce the reliability. For example, the V-22 "Osprey" tiltrotor aircraft in the United States is difficult to control, frequent flight accidents, complicated mechanism and heavy structural weight, which reduce its flight performance.

The power direction of the tail seat type vertical take-off and landing fixed-wing unmanned aerial vehicle is fixed, and no power tilting mechanism is needed, but there are obvious defects in the existing tail seat type vertical take-off and landing fixed-wing aircraft. Patent CN 204822068 U discloses "a kind of tail seat vertical take-off and landing aircraft". The technical solution adopted by the tail seat vertical take-off and landing aircraft is that the aircraft body includes main body wings, and Each socket has a fuselage wing plate assembly; the front of the main fuselage wing plate is provided with two motors, each motor is connected to a propeller through a drive shaft, and two sets of rudder surface components are connected to the tail of the main fuselage wing plate. Its disadvantages are that during the vertical take-off and landing and hovering stages, under the action of propeller slipstream, the steering torque is generated by the deflection of the aerodynamic rudder surface, the steering efficiency is low, and the wind resistance is poor.

Contents of the invention

In order to avoid the deficiencies in the prior art, the present invention proposes a tail seat-type four-rotor canard layout aircraft capable of vertical take-off and landing.

The technical scheme that the present invention adopts to solve its technical problem is: comprise fuselage, wing, canard, vertical empennage, power plant, the head of described fuselage is equipped with a pair of canard, and fuselage tail both sides are wing , the upper and lower parts of the tail of the fuselage are respectively provided with vertical empennages, and the centerlines of the upper vertical empennage and the lower vertical empennage are in the same vertical plane as the fuselage axis, and the wing tips and the vertical empennages are respectively provided with power devices , and the rotating shaft of the power unit is parallel to the axis of the fuselage; the rear edge of the wing is equipped with an elevon, the rear edge of the vertical tail is equipped with a rudder, and the rear edge of the canard is equipped with an elevator; the wing tip of the wing, the wing of the vertical tail The tip and the tail end of the fuselage jointly form five support points, and in the stop state, the five support points make the aircraft stop vertically upward on the ground;

There are four groups of power devices, wherein two groups of power devices are installed symmetrically on the wing tips of the wings on both sides, and the other two groups of power devices are respectively arranged on the wing tips of the vertical tail, and the rotating shafts of the power devices are respectively connected to the axis of the fuselage. Parallel; the power unit is a variable pitch propeller, the power unit on the wings on both sides of the tail of the fuselage rotates in the same direction, and the power unit on the vertical tail at the tail of the fuselage rotates in the same direction, and the power unit on the wing is in the same direction as the The powerplants on the vertical stabilizer rotate in opposite directions.

A battery or an internal combustion engine is installed in the fuselage, and the battery drives the motor to drive the power unit, or the internal combustion engine drives the power unit through mechanical transmission.

The vertical take-off and landing tail seat type four-rotor canard layout aircraft relies on the power unit to work together to balance the gravity of the aircraft during the vertical take-off and landing, hovering and low-speed flight stages, keeping the total pulling force constant, by increasing the propeller speed on the lower vertical tail /pitch while decreasing the propeller speed/pitch on the upper vertical tail to pitch the vehicle up and vice versa; keeping the total pull constant, increase the propeller speed/pitch on the left wing while decreasing the right Propeller RPM/pitch on the wings, roll the vehicle to the right and vice versa; keep the total pull constant, increase propeller RPM/pitch on the left and right wings while decreasing propeller RPM/pitch on the upper and lower vertical tails Pitch, if the rotation direction of the propellers on the left and right wings is counterclockwise, and the rotation direction of the propellers on the vertical tail is clockwise, the aircraft will yaw to the right; if the rotation direction of the propellers is opposite to this, the aircraft will yaw to the left, and vice versa Of course. In the horizontal flight stage, it mainly relies on the aerodynamic lift generated by the wings and canards to balance the gravity, and relies on the propulsion generated by the power unit to overcome air resistance and fly forward at high speed. The ailerons on the wings provide roll control and the rudder on the vertical tail provides yaw control.

Beneficial effect

The tail seat type four-rotor canard layout aircraft capable of vertical take-off and landing proposed by the present invention is equipped with a pair of canards on the head of the fuselage, the two sides of the tail of the fuselage are wings, and the top and bottom of the tail of the fuselage are respectively arranged Vertical empennage, and the centerline of the upper vertical empennage and the centerline of the lower vertical empennage are in the same vertical plane as the axis of the fuselage. It is arranged at the tip of the vertical tail, and the rotating shaft of the power unit is parallel to the axis of the fuselage; the wing tip of the wing, the wing tip of the vertical tail and the tail end of the fuselage together constitute five support points. Five support points make the aircraft stand vertically upward on the ground.

The vertical take-off and landing tail seat type four-rotor canard layout aircraft adopts the vertical take-off and landing method, which can greatly reduce the requirements for the take-off and landing site. The power unit adopts variable-pitch propeller, which has faster response speed and has good maneuverability and wind resistance.

The overall layout of the vertical take-off and landing four-rotor canard layout aircraft is a canard layout. It flies in a fixed-wing mode during horizontal flight. It has low energy consumption, fast flight speed, long battery life, and good stability. performance, maneuverability and mobility.

Description of drawings

A tail seat type quadrotor canard layout aircraft capable of vertical take-off and landing according to the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

Fig. 1 is a structural schematic diagram of a tail seat type quadrotor canard layout aircraft capable of vertical take-off and landing according to the present invention.

Fig. 2 is a schematic diagram of the vertical state of the tail seat type four-rotor canard layout aircraft capable of vertical take-off and landing according to the present invention.

In the picture:

1. Fuselage 2. Wing 3. Canard 4. Vertical tail 5. Power plant

detailed description

This embodiment is a tail seat type four-rotor canard layout aircraft capable of vertical take-off and landing.

Referring to Fig. 1 and Fig. 2, the tail seat type four-rotor canard layout aircraft capable of vertical take-off and landing in this embodiment includes a fuselage 1 in a horizontal position in the flight state, and the fuselage 1 is a streamlined structure, and the head of the fuselage 1 Canards 3 are installed symmetrically on both sides, and elevators are installed on the trailing edge of canards 3; A pair of vertical empennage 4 is provided with a rudder installed on the rear edge of the vertical empennage 4.

The wingtip of wing 2, the wingtip of vertical tail 4 constitute four supporting points together, or the wingtip of wing 2, the wingtip of vertical tail 4 and the tail end of fuselage 1 constitute five supporting points together; state, four support points or five support points make the aircraft stop vertically upward on the ground. In this embodiment, the wing tip of the wing 2, the wing tip of the vertical tail 4 and the tail end of the fuselage 1 jointly form five supporting points.

At wing 2 wingtips and vertical tail 4 wingtip positions, be respectively provided with power unit 5, can increase the quantity of power unit 5 according to the weight of aircraft, the rotating shaft of power unit 5 is parallel with the axis of fuselage 1; Power unit 5 is variable The pitch propeller is driven by the following two methods according to actual needs. The first driving method is that a battery is installed in the fuselage 1, and the battery drives the motor to drive the power unit 5; the second driving method is that an internal combustion engine is installed in the fuselage 1, and the internal combustion engine passes through The mechanical transmission drives the power unit 5 . The speed of the variable-pitch propeller is controlled by the ESC of the driving motor, or the throttle of the internal combustion engine, and the pitch of the variable-pitch propeller is controlled by the corresponding steering gear.

In this example, the control methods of each flight state of the tail seat type four-rotor canard layout aircraft that can take off and land vertically are as follows:

Ground stop stage: wing 2 wingtips, vertical tail 4 wingtips form four support points; or wing 2 wingtips, vertical tail 4 wingtips and fuselage 1 tail form five support points, so that the aircraft is vertically upward .

Vertical take-off and landing, hovering and low-speed flight stages: mainly rely on the power unit 5 to work together to balance the gravity of the aircraft, keep the total pulling force constant, and increase the speed/pitch of the propeller on the lower vertical tail 4 while reducing the upper vertical tail 4 Propeller RPM/pitch, pitch the vehicle up and vice versa; hold total pull constant, increase propeller RPM/pitch on left wing 2 while decreasing propeller RPM/pitch on right wing 2 , so that the aircraft rolls to the right, and vice versa, increase the propeller speed/pitch on the right wing 2, and decrease the propeller speed/pitch on the left wing 2, so that the aircraft rolls to the left; maintain the total tension No change, increase the propeller speed/pitch on the left and right wings 2, and decrease the propeller speed/pitch on the vertical tail 4 at the same time, if the rotation direction of the propellers on the left and right wings 2 is counterclockwise, and the propeller on the vertical tail 4 The direction of rotation is clockwise, which can make the aircraft yaw to the right. If the rotation direction of the propeller is opposite to this, the aircraft will yaw to the left, and vice versa.

Level flight stage: mainly rely on the aerodynamic lift produced by wing 2 and canard 3 to balance the gravity, rely on the propulsion produced by power unit 5 to overcome the air resistance and fly forward at high speed, and can carry out long-term and long-distance flight. Pitch control, ailerons on wing 2 for roll control and rudder on vertical tail 4 for yaw control.

Claims (2)

1. a tail seat type four-rotor canard layout aircraft that can take off and land vertically, is characterized in that: comprise fuselage, wing, canard, vertical empennage, power unit, the head of described fuselage is equipped with a pair of canards The two sides of the tail of the fuselage are wings, and vertical tails are arranged above and below the tail of the fuselage respectively, and the centerlines of the upper vertical tail and the lower vertical tail are in the same vertical plane as the fuselage axis, and the wing tips and The vertical tail wing tips are respectively equipped with power devices, and the rotating shaft of the power device is parallel to the axis of the fuselage; the rear edge of the wing is equipped with an elevon, the rear edge of the vertical tail is equipped with a rudder, and the rear edge of the canard is equipped with an elevator; The wingtips of the wings, the wingtips of the vertical tail and the tail end of the fuselage jointly form five support points. When in a stopped state, the five support points make the aircraft stop vertically upward on the ground; There are four groups of power devices, wherein two groups of power devices are installed symmetrically on the wing tips of the wings on both sides, and the other two groups of power devices are respectively arranged on the wing tips of the vertical tail, and the rotating shafts of the power devices are respectively connected to the axis of the fuselage. Parallel; the power unit is a variable pitch propeller, the power unit on the wings on both sides of the tail of the fuselage rotates in the same direction, and the power unit on the vertical tail at the tail of the fuselage rotates in the same direction, and the power unit on the wing is in the same direction as the The powerplants on the vertical stabilizer rotate in opposite directions. 2. the tail seat type four-rotor canard layout aircraft that can take off and land vertically according to claim 1, is characterized in that: a storage battery or an internal combustion engine is installed in the fuselage, and the storage battery drives a motor to drive the power unit, or the internal combustion engine passes through a mechanical The transmission drives the power unit.