CN1699114A

CN1699114A - Unmanned aerobat with ring-like wing

Info

Publication number: CN1699114A
Application number: CN 200510009821
Authority: CN
Inventors: 王忠信; 青泉; 孙树生; 吴世海; 丛林枝
Original assignee: 王忠信
Priority date: 2005-03-15
Filing date: 2005-03-15
Publication date: 2005-11-23

Abstract

This invention relates to a ring-foil unattended airplane, wherein the divider divides the volume into two-piece volumes in an empty ducted, the upper volume has the airplane's fuel tank in it, and the down volume has the airplane's control embarkation storehouse in it, the center part of the ducted has the engine, and the down part of the engine is assembled with the fixed bar, which connects with the ducted inwall, the upper end of the engine has the locking, and the upper end of the duct's center part has the load storehouse, wherein the frame connects with the ducted outwall, the down part of the fixed bar has the blind, which connects with the ducted inwall, the bottom end of the blind has the vane, and the bottom end of the ducted has the airplane frame.

Description

Unmanned aerobat with ring-like wing

Technical field

The present invention relates to a kind of unmanned flight communications instrument, can vertical takeoff and landing (VTOL), and can realize the data in real time transmission, have the characteristics of all-weather flight.

Background technology

At present, known unmanned vehicle, because its applied range, cheap, characteristics such as usability is strong are by various circles of society's widespread use, but popularize the unmanned plane that uses at present, often big because of its volume, carry inconvenience, constraint with high content of technology, can not popularize use widely, and its emission all needs bigger place with reclaiming, especially relate to flight stability and easily control aspect all be the major issue that unmanned plane faced.This makes that the use for unmanned plane still is in space state in a lot of fields, what particularly require at aspects such as military surveillance, communications is more strict, limited to the development and the use of unmanned vehicle greatly, this just causes the use of having in some field to abandon to unmanned vehicle.Thereby the loss of aspects such as increase personnel and financial resources, material resources, for all direct or indirect generation of progress of development of productivity and science and technology obstruction.

Summary of the invention

The technical problem to be solved in the present invention is: overcome that weak point in the above-mentioned technology provides a kind of can realize stabilized flight under round-the-clock environment, easily controls, cheap, the unmanned data transmission aircraft that has wide range of applications.

For achieving the above object, the technical solution used in the present invention is:

The duct inner route clapboard of cavity is divided into two cavitys up and down with the duct cavity, the Fuel Tank of aircraft is installed in the upper cavity, the control instrument that aircraft is installed in the lower chamber carries the storehouse, the duct centre is equipped with driving engine, the driving engine lower end part is equipped with fixed link and is connected with the duct inwall, the driving engine upper end is equipped with screw propeller, upper end, duct centre is provided with the load storehouse, there is support to be connected on it with the duct outer wall, the fixed link bottom is equipped with flow deflector and is connected with the duct inwall, the flow deflector bottom is equipped with the wind direction sheet, and the duct bottom is equipped with aircraft landing gear.

The invention has the beneficial effects as follows:

1, anywhere vertical takeoff and landing, hover, noise is very low during orbit, and is disguised very good;

2, it have speed fast, control flexible and convenient, mobility strong, can do and realize the data acquisition real-time Transmission;

3, flight efficiency height, and fuel saving, so easy maintenance is economical and practical;

4, comformability is strong, can be in the city, and country, factory, seashore, naval vessels, the grassland, high mountain, round-the-clock vertical takeoff and landing flight is carried out in places such as express highway;

5, wide application: can take photo in the sky on civilian, advertising, communication repeating, oil pipeline supervision, resource exploration, sightseeing, the monitoring of fire flood situation pursue and capture an escaped prisoner guiding of traffic, sports and amusement etc.; The advantage that militarily has other communication delivery means to hardly match equally, special operations, air-borne early warning, information gathering, region of war observation, low-level penetration, air patrol, anti-terrorism rescue, etc.The utility model is a kind of rational in infrastructure, design ingenious, function admirable, convenient and practical individual lift device.

Description of drawings:

Fig. 1 is a structural representation of the present invention;

Fig. 2 is the section-drawing of A-A among Fig. 1;

Fig. 3 is the birds-eye view of Fig. 1;

Fig. 4 is the upward view of Fig. 1;

Fig. 5 is a schematic perspective view of the present invention.

The specific embodiment

Below in conjunction with accompanying drawing the present invention is described in further details.

By Fig. 1-Fig. 4 as can be known the present invention be: duct 1 inner route clapboard 10 of cavity is divided into up and down two cavitys 13 with the duct cavity, 14, the Fuel Tank 2 of aircraft is installed in the upper cavity 13, the control instrument that aircraft is installed in the lower chamber 14 carries storehouse 3, duct 1 centre is equipped with driving engine 4, driving engine 4 lower end parts are equipped with fixed link 11 and are connected with duct 1 inwall, driving engine 4 upper ends are equipped with screw propeller 5, upper end, duct 1 centre is provided with load storehouse 6, there is support 12 to be connected on it with duct 1 outer wall, fixed link 11 bottoms are equipped with flow deflector 7 and are connected with duct 1 inwall, flow deflector 7 bottoms are equipped with wind direction sheet 8, and duct 1 bottom is equipped with aircraft landing gear 9.

Be provided with two cavitys 13 up and down in the duct 1 of cavity of the present invention; 14; be provided with aircraft fuel case 2 in the upper cavity 13; lower chamber is provided with the aircraft control instrument and carries storehouse 3; Fuel Tank 2 carries the spatial volume that the position can be reduced aircraft to a great extent that is provided with in storehouse 3 with control instrument; made full use of the redundant space of aircraft duct; help the whole pneumatic exterior design collocation of aircraft; carry in the storehouse 6 flight control system and instrument and equipment are installed; driving engine 4 starts the back and drives screw propeller 5 cw high speed revolutions; for the flight of aircraft provides power; fixed link 11 is used for being connected between driving engine 4 and the duct 1; guarantee the stable of driving engine 4; the eddy airstream that screw propeller 5 rotations produce can make aircraft produce violent twisting; common aircraft adopts positive and negative pair of oar to come the balance torque usually; but the carrying and the loss propeller power that therefore can add aerodyne; and unstable eddy current vertical out-fall behind overcommutation that flow deflector 7 of the present invention can produce screw propeller 5 rotations; this just can guarantee the downward stable emissions of eddy current that screw propeller 5 produces by actv.; thereby play the effect of anti-torque; this has not only alleviated the deadweight of aircraft; also guaranteed simultaneously the Streamline Design of aircraft; the wind direction sheet 8 of flow deflector 7 bottom connections can be controlled by the control instruments that are installed in the control instrument lift-launch storehouse 3; thereby can carry out the angled swing in front and back; swing by wind direction sheet 8; can make by the directive discharging of slip-stream after flow deflector 7 integration; by changing the heading of slip-stream emission direction and then change of flight device; then flight forward of aircraft when wind direction sheet 8 is swung forward; the angle of wind direction sheet 8 swings is big more; aircraft and ground-surface angle are more little; aircraft flight speed is also just fast more; otherwise it is then slow more; if wind direction sheet 8 is not swung; and be in plumbness; then aircraft will be in the vertical uplift state; alighting gear 9 is positioned at duct 1 bottom; when aircraft lands, play the single-piece effect of supporting; its inside is equipped with pressure spring; suddenly born or play buffer protection function, the overall security of protection aircraft when landing by force at aircraft.

Claims

1, a kind of unmanned aerobat with ring-like wing, comprise duct (1), driving engine (4), flow deflector (7), it is characterized in that: the duct of cavity (1) inner route clapboard (10) is divided into two cavitys (13) up and down with the duct cavity, (14), the Fuel Tank (2) of aircraft is installed in the upper cavity (13), the control instrument that aircraft is installed in the lower chamber (14) carries storehouse (3), duct (1) centre is equipped with driving engine (4), driving engine (4) lower end part is equipped with fixed link (11) and is connected with duct (1) inwall, driving engine (4) upper end is equipped with screw propeller (5), upper end, duct (1) centre is provided with load storehouse (6), there is support (12) to be connected on it with duct (1) outer wall, fixed link 11 bottoms are equipped with flow deflector (7) and are connected with duct (1) inwall, flow deflector (7) bottom is equipped with wind direction sheet (8), and duct (1) bottom is equipped with aircraft landing gear (9).