CN201923320U

CN201923320U - Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle

Info

Publication number: CN201923320U
Application number: CN2011200097278U
Authority: CN
Inventors: 杨苡
Original assignee: 杨苡
Current assignee: Hangzhou Xiang Rong Intelligent Technology Co., Ltd.
Priority date: 2011-01-13
Filing date: 2011-01-13
Publication date: 2011-08-10
Anticipated expiration: 2021-01-13

Abstract

The utility model relates to a twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle, which is characterized in that: the whole body adopts a canard pneumatic configuration, and canard winglets are positioned at the front side of a main fuselage; main wings are positioned at the back side of the fuselage, and two engines with propellers are arranged at the tips of the main wings; backward swept H-shaped vertical tails are simultaneously arranged on nacelles of the engines at the wing tips, and take-off and landing pillars are arranged at the tops of the H-shaped vertical tails; and movable rudder surfaces are arranged on the back edges of the H-shaped vertical tails, and elevons are arranged at the outer sides of the back edges of the main wings. The unmanned aerial vehicle can vertically take off and land in a very small space like a helicopter, also can hover over the air to complete special observation and reconnaissance missions, and also can fly as fast as a fixed-wing aircraft. The unmanned aerial vehicle does not need an airport runway normally used by the fixed-wing aircraft, without catapults and parachutes, so the use is convenient, and the cost is lower; and the whole structure is simple and the manufacturing cost is low, and so the unmanned aerial vehicle has obvious cost price advantages compared with the helicopter, a tiltrotor and the like.

Description

Twin-engined vertical takeoff and landing fixed-wing unmanned planes

Technical field

The utility model relate to a kind of can be as the such vertical and landing takeoff of helicopter and hovering flight and can be as the unmanned aerial vehicle of fixed wing aircraft high-performance cruise flight.

Background technology

Its most special-purpose ejector catapult-assisted take-off that needs of taking off of fixed-wing unmanned plane in the past, or need one than long straight takeoff runway rolling start, need special-purpose parachute to cooperate buffer air bag to carry out parachuting in the time of landing mostly, perhaps adopting special-purpose arresting net to reclaim, is exactly to land with sliding race of special-purpose takeoff runway in addition.All these has caused conventional fixed-wing unmanned plane to take off and land need possess more limiting condition, causes it to use alerting ability to reduce, and use cost is higher.Though and vertical takeoff and landing (VTOL) easily of common depopulated helicopter and hovering flight are still because its complex structure, but the main rotor of its feathering and require the tail rotor assembly of displacement to need the movable a lot of manufacture difficulty of precision parts big equally, maintaining technical requirements height, face the cost problem of higher equally, and helicopter is because its principle and structural intrinsic factor cause its flying speed relatively low.

The utility model content

The purpose of this utility model be to provide a kind of can be as the such vertical and landing takeoff of helicopter and hovering flight and can be as the unmanned aerial vehicle of fixed wing aircraft high-performance cruise flight.

To achieve these goals, the technical solution adopted in the utility model is: twin-engined vertical takeoff and landing fixed-wing unmanned planes, it is characterized in that: complete machine adopts canard aerodynamic arrangement, the canard winglet is positioned at the fuselage front side, host wing is positioned at the fuselage rear side, the wing of host wing is installed two driving engines that screw propeller is housed slightly, the H shape vertical tail of sweepback is installed on the wing engine nacelle slightly simultaneously, top at this H shape vertical tail is equipped with the pillar that rises and falls, trailing edge is equipped with movable direction rudder face, and the host wing trailing edge outside is equipped with elevon.This host wing is trapezoidal or rectangle.This screw propeller is a tractor airscrew.

The beneficial effects of the utility model: the beneficial effects of the utility model are that it can be as helicopter at very narrow and small place vertical and landing takeoff, can also hover and finish special observation and reconnaissance mission in the air, can also quick flight as fixed wing aircraft, it does not need fixed wing aircraft airfield runway commonly used, need not ejector and parachute, practical and convenient cost is lower, its complete machine structure is simple, and low cost of manufacture is compared helicopter and tiltrotor etc. and had tangible cost of price advantage.

Description of drawings

Fig. 1 is to Figure 4 shows that the utility model adopts the integral structure scheme drawing of the twin-engined vertical takeoff and landing fixed-wing unmanned planes of canard aerodynamic arrangement.

The scheme drawing of the structure of each operation of components process when Fig. 5 is the up process of aircraft.

The scheme drawing of the structure of each operation of components process when Fig. 6 is the descending process of aircraft.

Fig. 7 is the scheme drawing of the structure of each operation of components process in the aircraft lift-over process to the right.

Fig. 8 is the scheme drawing of the structure of each operation of components process in the aircraft lift-over process to the left.

Fig. 9 is the aircraft scheme drawing of the structure of each operation of components process in the tilting procedure to the right.

Figure 10 is the aircraft scheme drawing of the structure of each operation of components process in the tilting procedure to the left.

The specific embodiment

The utility model proposes a kind of can be as the such vertical and landing takeoff of helicopter and hovering flight and can be as the unmanned aerial vehicle of fixed wing aircraft high-performance cruise flight.Its structure sees also Fig. 1 to shown in Figure 4, and its complete machine adopts canard aerodynamic arrangement, and canard winglet 3 is positioned at fuselage 1 front side, and watch-dog cabin 2 is positioned at the below of two canard winglets, 3 next door fuselage 1, and host wing 4 trapezoidal or rectangle is positioned at the fuselage rear side.The wing of host wing 4 is installed two driving engines that tractor airscrew 5 is housed slightly, the H shape vertical tail 7 of sweepback is installed on the wing engine nacelle 6 slightly simultaneously, top at this H shape vertical tail 7 is equipped with the pillar 10 that rises and falls, and trailing edge is equipped with movable direction rudder face 9.The host wing 4 trailing edges outsides is equipped with elevon 8, and is shared by the mixing mode, plays the effect of lifting rudder face when movable rudder face 9 deflections up or down simultaneously of host wing 4 both sides, for complete machine provides pitch control subsystem moment.As shown in Figure 5 and Figure 6, when the rudder face of both sides upward deflects simultaneously, make whole aircraft obtain nose-up pitching moment under the combined action of this rudder face gas washing stream under the wind stream in when flight and screw propeller, this moment, aircraft can come back upwards, as shown in Figure 5.When the rudder face of both sides deflects down simultaneously, make whole aircraft obtain nose-down pitching moment under the effect of this rudder face gas washing stream under the wind stream in when flight and screw propeller, this moment, aircraft can be bowed downwards.And upwards play aileron during the downward differential deflection of another side on one side when the movable rudder face of host wing both sides, for complete machine provides the lift-over control torque.As shown in Figure 7 and Figure 8.When if left side rudder face downward bias when visual tail direction then right side rudder face upward deflect, the left side rudder face can produce the upper lifting force square under the following gas washing stream combined action of the wind stream in when flight and screw propeller, and the right side rudder face can produce under the following gas washing stream combined action of the wind stream in when flight and screw propeller and press down moment, in the combined action of the moment of this left and right sides different directions lift-over to the right of getting off the plane, as shown in Figure 7.If the left side rudder face upward deflects and right side rudder face when deflecting down when visual tail direction, can produce under the combined action of left side rudder face gas washing stream under the wind stream in when flight and screw propeller and press down moment, and can produce the upper lifting force square under the combined action of right side rudder face gas washing stream under the wind stream in when flight and screw propeller, in the combined action of the moment of this left and right sides different directions lift-over to the left of getting off the plane.As shown in Figure 8.

This H shape vertical tail 7 plays the direction stabilator, the effect of yaw rudder and alighting gear simultaneously.This direction rudder face 9 can only be simultaneously synchronous to same direction deflection, when the four direction rudder 9 of seeing the left and right sides from the aircraft back simultaneously to the right during deflection, complete machine can produce yawing moment to the right under the combined action of the wind stream under screw propeller when gas washing stream and flight, this moment, plane nose can tilt to the right, as shown in Figure 9.When the four direction rudder 9 of seeing the left and right sides from the aircraft back simultaneously to the left during deflection, complete machine can produce yawing moment to the left under the combined action of the wind stream under screw propeller when gas washing stream and flight, and this moment, plane nose can tilt to the left.As shown in figure 10.Aircraft when vertical takeoff and landing since low its control of flying speed main rely under the screw propeller gas washing stream to act on respectively to control produce control torque on the rudder face and finish.When aircraft was in that level is flat at a high speed to fly, because flying speed is fast, the control torque that the combined action of gas washing stream produces on each control rudder face under wind stream the when control of this moment mainly relies on flight and the screw propeller was finished.

The twin-engined vertical takeoff and landing fixed-wing of the utility model unmanned plane four pillars 10 that rise and fall by H T tail 7 tops when taking off support vertical being parked on the ground of whole fuselage.Driving two tractor airscrews, the 5 generations power that draws high vertically upward behind the engine starting takes off vertically whole aircraft, aircraft also can keep perpendicular attitude to hover in the air, this moment, two screw propellers provided lift to complete machine, as long as the lift that two screw propellers produce equals or the own wt that is slightly larger than aircraft just can guarantee that hang is aerial.And thereby the attitude of aircraft control relies on screw propeller to rotate gas washing stream under the brute force that produces to act on and make complete machine produce around fuselage X on the yaw rudder rudder face of the elevon in the host wing trailing edge outside and H shape vertical tail trailing edge; Y; the rotation control torque that Z is three, thus the deflection angles by these control rudder faces of instant and trickle adjustment make complete machine vertical hover or the process of vertical drift motion at a slow speed in keep dynamical equilibrium.

Need do the fast flat engine speed that only need strengthen when flying when the twin-engined vertical takeoff and landing fixed-wing of the utility model unmanned plane makes the vertical acceleration of aircraft control elevating rudder then to adjust attitude by aircraft and become level flight condition, the aircraft of this moment just becomes the fixed wing aircraft of the canard aerodynamic arrangement of a routine fully, aircraft relies on host wing and preposition fixed type canard that lifting flight is provided, and the screw propeller of both sides only provides the power that draws in for aircraft.The yaw rudder of elevon on the aircraft and vertical tail trailing edge provides around fuselage X for complete machine, Y, the rotation control torque that Z is three.

Send out only need put down when vertical takeoff and landing fixed-wing unmanned planes need land and fly to overhead back, the zone of waiting to land and increase engine speed and make complete machine quicken to control then elevating rudder aircraft is come back up to the attitude of climbing vertically upward when the utility model is two, can progressively reduce engine speed this moment and reduce the lift of screw propeller and control each rudder face and decelerating to stable hovering until aircraft, then further slightly inching reduce engine speed and make lift be slightly less than vertical reductions height that aircraft deadweight aircraft just can be at a slow speed until the ground of landing.

Claims

1. twin-engined vertical takeoff and landing fixed-wing unmanned planes, it is characterized in that: complete machine adopts canard aerodynamic arrangement, the canard winglet is positioned at the fuselage front side, host wing is positioned at the fuselage rear side, the wing of host wing is installed two driving engines that screw propeller is housed slightly, and the H shape vertical tail of sweepback is installed on the wing engine nacelle slightly simultaneously, at the top of this H shape vertical tail the pillar that rises and falls is installed, trailing edge is equipped with movable direction rudder face, and the host wing trailing edge outside is equipped with elevon.

2. twin-engined vertical takeoff and landing fixed-wing unmanned plane as claimed in claim 1, it is characterized in that: this host wing is trapezoidal or rectangle.

3. twin-engined vertical takeoff and landing fixed-wing unmanned plane as claimed in claim 1, it is characterized in that: this screw propeller is a tractor airscrew.