CN105329437A

CN105329437A - Vertical/horizontal flight fixed-nozzle fixed wing aircraft

Info

Publication number: CN105329437A
Application number: CN201510483109.XA
Authority: CN
Inventors: 任军
Original assignee: Individual
Current assignee: Individual
Priority date: 2014-08-04
Filing date: 2015-07-21
Publication date: 2016-02-17

Abstract

A vertical/horizontal flight fixed-nozzle fixed wing aircraft is characterized in that a nozzle backward blows gas from the leading edge of the upper aerofoil of a pinion to realize pinion lift augmentation, and the ejector action increasing gas flow downwash of gas flow is deflected through the lower aerofoil of a proximal limb and then flows toward the ground to make the proximal limb lift augmentation of the pneumatic layout, so the fluid supercharging ratio is small, the flow is large, and fuel oil is saved.

Description

The motionless Fixed Wing AirVehicle of spout of vertical/horizontal flight

The present invention relates to a kind of endoatmospheric flight instruments, especially can the motionless Fixed Wing AirVehicle of spout of vertical takeoff and landing horizontal flight.

At present, the aircraft of known vertical takeoff and landing horizontal flight, such as: autogyro, tilt rotor aircraft, F-35 etc., due to aerodynamic arrangement and the structure of its flight, cause flight instruments weight large, fuel oil consumption is large, and helicopter horizontal flight fuel oil consumption is large, and cost is expensive.

High for overcoming existing vertical/horizontal aircraft cost, fuel oil consumes large deficiency, the invention provides the motionless Fixed Wing AirVehicle of spout of a kind of vertical/horizontal flight, and not only fuel oil consumption is low for this aircraft, and cost is low.

The scheme of technical solution problem of the present invention is: equal with wing length in length, be arranged in finedraw Fig. 5 of front wing top airfoil leading edge, in 1, spout 13 is backward in air blowing Fig. 1 shown in 18, because Coanda effect air-flow can flow along wing top airfoil, in Fig. 1 18, shown in 19, thus provide the lift that front wing takes off vertically.Through front wing downwash flow backward due to finedraw blowout jet flow ejector action, its flow increases about 10 times, gas flow rate reduce.This increased flow capacity, the downwash flow that flow velocity reduces flows to equal with front wing length parallel with front wing, and setting height(from bottom) is a little less than the full dynamic formula of front wing (both series type wing) and the wing lower aerofoil of the rear wing of the rear wing flap of band.During vertical takeoff and landing, after full dynamic formula, trailing edge adjusts downwards, and in Fig. 1 shown in 2, the rear wing flap aileron of rear wing deflects down about 90 °, in Fig. 1 shown in 23, makes it flow through in the air flow direction surface map 1 of lower aerofoil shown in 20.Air-flow produces horizontal component of force backward in the flowing of rear wing and to blow with front wing finedraw and that compressor inlet produces is equal to front wing horizontal component of force forward, makes its aircraft not have parallel motion when vertical takeoff and landing.The component vertically upward that air-flow produces in rear wing flowing, the component vertically upward produced with front wing jet flow, then for aircraft vertical landing provides lift.The wing flap aileron on full dynamic formula rear wing and rear wing must be adjusted when aircraft has the angle of attack/horizontal flight, the air-blowing quantity of front wing finedraw must be adjusted, during aircraft vertical landing, horizontal flight speed is zero, the mass ratio of induced-to-inducing air of blowout air-flow is maximum, increase injection rate along with horizontal flight speed reduce gradually correspondingly duct when quality to add the momentum increase brought less, so the interaction force (Effective specific impulse) of air-flow and wing flies at vertical takeoff and landing, the angle of attack, level flight condition changes not quite.

In above-mentioned vertical takeoff and landing illustrates, the particularly increase of rear wing charge air and the increase equivalence of aircraft engine duct ratio before flowing through, speed and the quality of aircraft vertical lifting are little by the velocity contrast of the air-flow that addition of, the air-flow large area wing phase reactive fluid rate of supercharging intrinsic with fixed-wing is little, horizontal gas flow and wing particularly front wing aerodynamic lift are large, these can make the output work of driving engine effectively be utilized, reach the object of vertical lift process flight fuel saving, profitable fruit of the present invention is, aircraft vertical/horizontal flight fuel oil consumption is little, structure is simple, cost is low.

Below in conjunction with drawings and Examples, the present invention is further described:

Fig. 1 is vertical lift pneumatic diagram of the present invention.

Fig. 2 is the A-A view of Fig. 3

Fig. 3 is the E direction view of Fig. 2

Fig. 4 is the D direction view of Fig. 1

Fig. 5 is the B-B cutaway view of Fig. 3, F-F cutaway view

In figure 1, air blowing finedraw, 2, wing after full dynamic formula, 3, rear wing flaps, 4, cabin dividing plate, 5, seat Cang Gai, 6, front wing, 7, inlet channel, 8, fuel tank, 9, wing turning cylinder after full dynamic formula, 10, seat, 11, driving engine, 12, gas compressor, 13, air blowing finedraw air nozzle, 14, pressure gas stream in wing, 15, the direction wing, 16, gas channel before air blowing finedraw, 17, enter the air of air compressor, 18, the air-flow of air blowing finedraw ejection, 19, by the air-flow of injection, 20, the air-flow flowed downward, 21, front and back wing tie-beam, 22, rear wing winglet, 23, aileron.

Charge flow (17) in FIG, by inlet channel (7), compressed by air compressor (12), by the gas flow pipeline (14) in wing compressed, (16), (1) air blowing finedraw (1), finally sprayed by spout (13), along front wing top airfoil flowing below jet flow, after flowing out, below injection, gas forms air-flow (19), ejection gas forms air-flow (19) above, form downwards flow backward increase the downwash flow of flow velocity reduction and flow to rear wing (2), (3), (23), ground is flowed to along lower aerofoil deflect airflow (20).

Claims

1. the motionless Fixed Wing AirVehicle of spout of vertical/horizontal flight, in front wing, front flap, rear wing flap and front wing are dynamically connected, and it is characterized in that: the leading edge of front wing top airfoil is provided with the finedraw gas channel of blowing backward.

2. the motionless Fixed Wing AirVehicle of spout of vertical/horizontal flight according to claim 1, it is characterized in that: finedraw length is equal with wing length, air blowing finedraw air-blowing quantity is adjustable.Rear wing is full dynamic formula, and rear wing flap is multiple stage.