CN106828919A - It is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula - Google Patents

Abstract

The invention discloses it is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula, be made up of fuselage, wing, vertical tail and power set；The head of fuselage is provided with power set, and the rotating shaft of power set is located along the same line with the axis of fuselage；The both sides of fuselage are provided with wing, vertical tail is respectively arranged with above and below afterbody, and the center line of upper vertical empennage and downward vertical empennage is located in same perpendicular with fuselage axis, the trailing edge of wing is provided with elevon, and vertical tail trailing edge is provided with rudder.Power set are feathering contrarotation DCB Specimen, and coaxial front and rear two rotor wing rotations are in opposite direction.The tail end of the wing tip of wing, the wing tip of vertical tail and fuselage collectively forms five strong points, and in halted state, five strong points make aircraft vertically upright rest in ground；Aircraft vertical landing fast response time, and with good control stability and wind resistance.

Description

A Tailstock Coaxial Reversing Propeller Tailless Layout Aircraft Capable of Vertical Takeoff and Landing

technical field

The invention relates to a vertical take-off and landing aircraft, in particular to a vertical take-off and landing tail seat type coaxial reverse propeller tailless layout aircraft.

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 the defects of slow flight speed and short endurance time, as well as the problems of low control efficiency and poor wind resistance of the existing tail-sitting 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 vertical take-off and landing fixed-wing unmanned aerial vehicle is fixed, and no power tilting mechanism is needed, but the existing tail-seat vertical take-off and landing fixed-wing aircraft has obvious defects. Patent CN 204822068U discloses "a tail-sit vertical take-off and landing aircraft". The technical solution adopted by the tail-sit vertical take-off and landing aircraft is that the aircraft body includes main fuselage wings, and the opposite sides of the main fuselage wings each The fuselage wing plate assembly is socketed; the front part of the main body 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 body 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 vertically take-off and landing tailstock type coaxial reverse propeller tailless layout aircraft.

The technical scheme that the present invention adopts to solve its technical problem is: comprise fuselage, wing, vertical empennage, power unit, the head of described fuselage is equipped with power unit, and the both sides of fuselage are arranged as integral structure with fuselage The upper and lower sides of the tail of the fuselage are respectively provided with vertical tails, 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 rear edge of the wing is equipped with an elevon. The rear edge of the empennage is equipped with a rudder; the wingtips of the wings, the wingtips of the vertical empennage and the tail end of the fuselage together form five support points. When in a stopped state, the five support points make the aircraft stop vertically upward on the ground;

The power device is a period-variable-pitch coaxial reversing double-rotor, and the front and rear two rotors on the coaxial rotation direction are opposite; The throttle control of the formula engine, the distance between the coaxial reversing dual-rotors with period variable pitch is controlled by the swash plate driven by the steering gear; the rotating shaft of the power unit and the axis of the fuselage are on the same straight line.

A battery or a piston engine is installed in the fuselage, and the battery drives the motor to drive the power unit, or the piston engine drives the power unit.

The vertical take-off and landing tail seat type coaxial reverse propeller tailless layout aircraft mainly relies on the power plant to balance the gravity of the aircraft during the vertical take-off and landing, hovering and low-speed flight phases, by making the paddle discs of the coaxial reversing dual rotors or one of them The propeller disc of one rotor can be tilted forward, and the aircraft can be moved forward, and vice versa; the propeller disc of the coaxial contra-rotating rotor, or the disc of one of the rotors, can be tilted to the right, and the aircraft can be moved to the right, and vice versa However, keeping the total pulling force constant, by coordinatingly changing the collective pitch of the coaxial reversing dual-rotors, a rightward counter torque is produced, which can make the aircraft yaw to the right, and vice versa. The feature of the horizontal flight stage is to rely on the aerodynamic lift generated by the wings to balance the gravity, rely on the propulsion generated by the power plant to overcome the air resistance and fly forward at high speed, and can carry out long-term and long-distance flight, and the elevons on the wings perform pitch and roll Control, the rudder on the vertical tail for yaw control.

Beneficial effect

The vertical take-off and landing tailstock type coaxial anti-propeller tailless layout aircraft proposed by the present invention is composed of a fuselage, wings, vertical empennage and a power unit; the head of the fuselage is equipped with a power unit, and the rotating shaft of the power unit on the same line as the axis of the fuselage. The two sides of the fuselage are arranged as wings integrated with the fuselage, and 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 located on the same vertical plane as the axis of the fuselage Inside, the elevon is installed on the trailing edge of the wing, and the rudder is installed on the trailing edge of the vertical tail. The power device is a period-variable coaxial reversing dual-rotor, and the front and rear rotors rotate in opposite directions on the coaxial axis; the wing tip of the wing, the wing tip of the vertical tail and the tail end of the fuselage together form five support points. At the same time, the five support points make the aircraft stop vertically on the ground; the aircraft vertical take-off and landing response speed is fast, and it has good control stability and wind resistance performance.

The vertical take-off and landing tail seat type coaxial reverse propeller tailless layout aircraft adopts the period variable pitch coaxial reversing dual-rotor and adopts the vertical take-off and landing method, which can greatly reduce the requirements for the take-off and landing site. It can take off and land vertically in a narrow space, with faster response speed, and has good maneuverability, stability and wind resistance during vertical takeoff and landing.

The vertical take-off and landing tail seat type coaxial reverse propeller tailless layout aircraft adopts the tailless layout, can fly at high speed and level with fixed wings, has low energy consumption, fast flight speed, long battery life, good stability and manipulative.

Description of drawings

A vertical take-off and landing tailstock-type coaxial anti-propeller tailless layout aircraft of the present invention will be further described in detail in conjunction with the accompanying drawings and embodiments.

Fig. 1 is a schematic structural view of a tailstock type coaxial anti-propeller tailless layout aircraft capable of vertical take-off and landing according to the present invention.

Fig. 2 is a vertical state diagram of a tailstock type coaxial reverse propeller tailless layout aircraft capable of vertical take-off and landing according to the present invention.

In the picture:

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

detailed description

This embodiment is a tail seat type coaxial reverse propeller tailless layout aircraft that can take off and land vertically.

Referring to Fig. 1, Fig. 2, the tailstock type coaxial anti-propeller tailless layout aircraft that can take off and land vertically in this embodiment is made up of fuselage 1, wing 2, vertical empennage 3 and power plant 4; fuselage 1 is streamlined structure, the head of the fuselage 1 is equipped with a power unit 4, the two sides of the fuselage 1 are set as a wing 2 of an integral structure with the fuselage 1, and the trailing edge of the wing 2 is equipped with an elevon. Tail top and bottom are provided with vertical empennage 3, and the centerline of upper vertical empennage 3 and below vertical empennage 3 and fuselage 1 axis are in the same vertical plane, and vertical empennage 3 trailing edge is equipped with rudder.

The rear end of the wingtip of wing 2 or the tail brace installed on the wing 2, and the wingtip of the vertical tail 3 form four support points together; or the wingtip of wing 2 or the tail brace installed on the wing 2 The rear end of the rear end, the wingtip of the vertical tail 3 and the tail end of the fuselage 1 form five supporting points together, and before the aircraft takes off and after landing, four or five supporting points make the aircraft vertically upwards to stop on the ground. Four or five support points are used as the fulcrum for the aircraft to take off and land, without additional installation of landing gear.

The power unit 4 is a period-variable-pitch coaxial reversing double-rotor, and the front and rear two rotors on the coaxial rotation direction are opposite; The throttle of the engine is controlled, and the pitch of the cyclically variable-pitch coaxial reversing dual-rotor is controlled by the swash plate driven by the steering gear; the rotating shaft of the power unit and the axis of the fuselage are located on the same straight line.

The vertical take-off and landing tail seat type coaxial reverse propeller tailless layout aircraft can be driven by the following two methods according to actual needs. The first driving method is: a battery is installed in the fuselage 1, and the battery drives the motor to drive the power unit 4 or adopt the second kind of driving mode: a piston engine or a turboshaft engine are installed in the fuselage 1, and the engine drives the power unit 4.

The control mode of each flight state of the tailstock type coaxial anti-rotor tailless layout aircraft that can take off and land vertically is as follows:

Ground stop phase:

Wing 2 wingtips or wing 2 are equipped with strut bar, then strut bar rear end, vertical empennage 3 wingtips and fuselage 1 tail end constitute five support points, make aircraft vertically upwards.

VTOL, hover and low-speed flight phases:

The characteristics of these stages are to rely on the power unit 4 to balance the gravity of the aircraft, and the aircraft can be moved forward by making the paddle discs of the coaxial counter-rotating rotors or the paddle discs of one of the rotors tilt forward, and vice versa; Rotate the paddle discs of the dual-rotors or one of the rotors to the right to make the aircraft move to the right, or tilt the paddle discs of the coaxial reversing dual-rotors or one of the rotors to the left to make the aircraft Travel to the left; keep the total pulling force constant, and change the collective pitch of the coaxial counter-rotating rotors in a coordinated manner to generate a rightward counter torque, which can make the aircraft yaw to the right, and vice versa.

Level flight phase:

It relies on the aerodynamic lift generated by the wing 2 to balance the gravity, relies on the propulsion generated by the power unit 4 to overcome air resistance and fly forward at high speed, and can carry out long-distance and long-distance flight. , the rudder on the vertical stabilizer 3 performs yaw control.

Claims (2)

1. it is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula, it is characterised in that:Including fuselage, wing, Vertical tail, power set, the head of the fuselage are provided with power set, and the both sides of fuselage are set to and fuselage integrative-structure Wing, be respectively arranged with vertical tail above and below afterbody, and upper vertical empennage and downward vertical empennage Center line is located in same perpendicular with fuselage axis, and trailing edge is provided with elevon, and vertical tail trailing edge is provided with Rudder；The tail end of the wing tip of wing, the wing tip of vertical tail and fuselage collectively forms five strong points, in halted state, Five strong points make aircraft vertically upright rest in ground；

The power set be feathering contrarotation DCB Specimen, it is coaxial on front and rear two rotor wing rotation it is in opposite direction；Cycle The rotating speed of displacement contrarotation DCB Specimen by motor electricity regulation and control system, or the piston-mode motor by driving throttle control System, the spacing of feathering contrarotation DCB Specimen is controlled by servo driving pitch；The rotating shaft of the power set and fuselage Axis be located at same straight line.

2. it is according to claim 1 can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula, it is characterised in that: Battery or piston-mode motor are installed, battery motor drives power set, or piston engine in the fuselage Machine driving power device.