CN102756806A

CN102756806A - Upright-standing vertical take-off and landing airplane

Info

Publication number: CN102756806A
Application number: CN2012102619356A
Authority: CN
Inventors: 郗杰
Original assignee: SHENYANG SHENLAN AVIATION TECHNOLOGY Co Ltd
Current assignee: SHENYANG SHENLAN AVIATION TECHNOLOGY Co Ltd
Priority date: 2012-07-26
Filing date: 2012-07-26
Publication date: 2012-10-31

Abstract

An upright-standing vertical take-off and landing airplane is designed to solve the technical problems that much difficulty exists in controlling the vertical take-off and landing, hovering and the like of a conventional horizontal vertical take-off and landing airplane, the required cost is relatively higher and the controlling force is insufficient when the airplane uses a pneumatic control plane in the low-speed and idle states in the air. An upright-standing main body is adopted, a jet vane is taken as an airplane control plane, and an engine jet orifice corresponds to the center of the jet vane behind an X-type tail wing in position. The invention has the benefits that the upright-standing vertical take-off and landing airplane is a high-speed aircraft adopting an upright-standing machine body and having the design characteristic that the machine body is fused with a guided missile; owing to the upright take-off, the efficiency of an engine per se can be given into full play and the steering and balancing designs are simplified; the maneuverability is more excellent than that of the conventional layout; the controllability is good and the maneuverability is outstanding; and the airplane on the ground for taking off occupies a small area so as to facilitate hiding.

Description

The VTOL aircraft of vertically standing

Technical field:

The present invention relates to a kind of VTOL aircraft, relate in particular to a kind of VTOL aircraft of vertically standing.Belong to field of aerospace technology.

Background technology:

The VTOL technology of aircraft is to adopt conventional horizontal VTOL at present; Engine thrust can not be directly as VTOL power; Technology is auxiliary and will adopt that spout turns to etc.; Therefore at present unmanned plane exists and realizes that VTOL is very big with relevant control problem difficulty such as hover, the also more high relatively technical matters of required cost.

Summary of the invention

The present invention is bigger with relevant control problem difficulty such as hover for the realization VTOL that solves present horizontal VTOL machine and exist; Required cost aircraft also higher relatively and that exist uses technical matterss such as its control effort deficiency of aerodynamic force rudder face under low speed and aerial quiescence; A kind of VTOL aircraft of vertically standing is provided; It uses gas rudder control aspect, has overcome aircraft in low speed and the not enough problem of aerial quiescence therapeutic method to keep the adverse qi flowing downward power rudder face control effort.Concrete solution is: the VTOL aircraft of vertically standing, and it comprises fuselage, wing, power supply, flight control system, avionics system, driving engine and gas rudder; Said fuselage is the vertical fuselage, with said gas rudder as the aircraft handling rudder face; The position of the flow jeting port of said driving engine is corresponding with the center of the gas rudder behind the aircraft tail; Said wing is a delta wing, adopts big sweepback angle to be arranged symmetrically in waist; Said empennage is a undercarriage.

Characteristics of the present invention and beneficial effect: this machine is a type high-speed aircraft of design feature to adopt the fuselage of vertically standing; Aircraft wing adopts single delta wing in the big sweepback angle; Airplane design becomes the vertical VTOL of body; Attitude when aircraft is taken off with aerial static and landing through gas rudder control promptly can not stand upside down through horizontal gas rudder and orientation gas rudder control aircraft, controls the aircraft lift-over through the differential level gas rudder.Vertical fuselage adopts the X type tail to support as fuselage, adopts to push away ratio engine greatly and aircraft is vertically stood take off and land; Vertical takeoff can be given full play to the usefulness of driving engine own, simplifies to turn to and balanced design; Gas rudder makes maneuvering performance not rely on air speed, and is outstanding than the pneumatic rudder of routine; Its road-holding property is good, and maneuvering performance is excellent.

Description of drawings:

Fig. 1 structural representation of the present invention

Fig. 2 is the construction profile scheme drawing of Fig. 1

Fig. 3 is a tail structure scheme drawing among Fig. 1

Fig. 4 is the inner structure distribution schematic diagram of Fig. 1

The specific embodiment:

Referring to Fig. 1-Fig. 3, the VTOL aircraft of vertically standing, it comprises fuselage 1, wing 2, power supply 3, flight control system 4, avionics system 5, driving engine 6 and gas rudder 7; Said fuselage 1 is the vertical fuselage, with said gas rudder 7 as the aircraft handling rudder face; The position of the flow jeting port 8 of said driving engine is corresponding with the center of the gas rudder 7 behind the X-shaped aircraft tail; Said wing 2 is a delta wing, adopts big sweepback angle to be arranged symmetrically in fuselage 1 middle part; Said empennage is a undercarriage.

Said empennage as undercarriage is " X ", "+", " Y " or " * " shape.

The diving rudder of aircraft and yaw rudder are installed in the aircraft tail trailing edge, and stretch entering jet cutting car flow district to heart, form gas rudder.

Principle of work: be application space inverted pendulum principle, because landing speed when hovering is little, the aerodynamic force contribution is less, can become rigid body to the aircraft modelling, makes rigid body keep standing upside down through the control of engine gas rudder, and then realizes that vertical fuselage hovers and controlled landing.

Embodiment

Referring to Fig. 4, the VTOL aircraft of vertically standing, it comprises fuselage 1, wing 2, power supply 3, flight control system 4, avionics system 5, driving engine 6 and gas rudder 7; Wherein: fuselage 1 is that upright standing places, the position of flow jeting port 8 just with the X type tail after gas rudder 7 centers corresponding; Wing 2 is the individual layer delta wing, adopts big sweepback angle to be arranged in fuselage 1 middle part.The electronic governor of said electronic governor 5 adopts brushless, and it regulates the rotating speed of electrical motor according to the control signal of flight control system 4.Fuselage 1 in-to-in structural arrangement is that the input line of electronic governor is connected with power supply 3, and the output line of electronic governor is connected with driving engine 6, and the signal wire (SW) of electronic governor is connected with the autopilot/remote control receiver of flight control system 4; In addition, electronic governor also has the power supply output function, promptly between the both positive and negative polarity of signal wire (SW), the voltage output about 5V is arranged, and is the remote control receiver power supply through signal wire (SW), and remote control receiver is other control convenience power supplies of autopilot and gas rudder again.Fully the thrust direction of utilization driving engine 6 realizes vertically standing the fuselage VTOL.Aircraft autopilot adopts MEMS gyro and integrated GPS of acceleration pick-up and bellows.

Said aircraft is taking off and landing and aerial static when being in low speed, through gas rudder 7 control aspect and balances, when high-speed flight through power-assisted steering and gas rudder 7 common control aspects.

Aircraft is a normal aerodynamic arrangement aircraft, uses gas rudder 7 control aspects, makes aircraft static vertically standing and not falling aloft.

The said empennage of aircraft also can be adopted as "+", " Y " or " * " T tail except that " X " shape, and as undercarriage, the assurance aircraft is stable stands.

This unmanned plane can become a type unmanned battle/reconnaisance flight vehicle, and land, sea and air all can be used.Also can make the high speed target drone.Can be designed to accomplish strike to ground or waterborne target from carrying warhead; Or carry reconnaissance equipment, realize that the region of war threatens scouting.Can realize autonomous navigation/GPS integrated navigation; Autonomous classification/lock onto target, directly bump is injured ground or waterborne target.Aircraft can realize that extension flies to throw in emission, take off vertically in ground and the vehicle-mounted isotype of taking off that moves, and can realize VTOL or parachuting; Aircraft has the pattern of hovering, and can realize revolving in the air and stop.

Claims

1. the VTOL aircraft of vertically standing, it comprises fuselage (1), wing (2), power supply (3), flight control system (4), avionics system (5), driving engine (6) and gas rudder (7); It is characterized in that: said fuselage (1) is the vertical fuselage, with said gas rudder (7) as the aircraft handling rudder face; The center of the position of the flow jeting port of said driving engine (8) and the gas rudder behind the aircraft tail (7) is corresponding; Said wing (2) is a delta wing, adopts big sweepback angle to be arranged symmetrically in fuselage (1) middle part; Said empennage is a undercarriage.

2. the VTOL aircraft of vertically standing according to claim 1 is characterized in that: the said empennage as undercarriage is " X ", "+", " Y " or " * " shape.

3. the VTOL aircraft of vertically standing according to claim 1 and 2, it is characterized in that: the diving rudder of aircraft and yaw rudder are installed in the aircraft tail trailing edge, and stretch entering jet cutting car flow district to heart, form gas rudder.