CN205418105U - Formula flying device is lift vertically to dish - Google Patents

Abstract

The utility model belongs to the technical field of flight equipment, the utility model relates to a formula flying device is lift vertically to dish, the major structure includes the chassis, driving system, the dustcoat, the gas vent, the vent, hem and grafting claw, the circumferential edge on chassis is along the formation hem of bending downwards, set up 2 gas vents on the hem, the upper surface on chassis is provided with the dustcoat, the inside of dustcoat is provided with driving system, driving system is fixed to be set up in the upper surface center on chassis department, the bottom edge of dustcoat is provided with the grafting claw, dustcoat and chassis are through grafting claw plug -in type fixed connection, form space formula vent between the upper surface on grafting claw and chassis, the dish that each part cooperation constitutes is lift vertically the stabilized flight of formula aircraft and is lift vertically and hover in the air, be applied to unmanned formula aerial reconnaissance and agriculture occasion, its simple structure, principle scientific and reasonable, performance safe and reliable, preparation and cost of maintenance are low, and operations and maintenance is convenient, and flight environment is friendly.

Description

A kind of dish direct lifting type flight instruments

Technical field:

This utility model belongs to flight equipment technical field, relates to a kind of dish direct lifting type flight instruments, can stabilized flight and go straight up to and hover in the air, be applied to unmanned formula aerial reconnaissance and agricultural applications.

Background technology:

Aircraft refers to be manufactured by the mankind, can fly away from ground and at space flight, the apparatus flying object flown in endoatmosphere or space, exoatmosphere (space) of manual control, be applied to the fields such as Science Explorations, ocean and military affairs；Aircraft is generally divided into airborne vehicle, spacecraft, rocket, guided missile and the big class of guided weapon five: the aircraft in endoatmosphere flight is referred to as airborne vehicle, including balloon, aerodone, dirigible, aircraft and helicopter, by quiet buoyancy or the air force lift-off flight of air relative motion generation of air；The aircraft arbitrarily flown in space is referred to as spacecraft, and including artificial earth satellite, manned spaceship, space probe and space shuttle, the speed obtaining necessity under the promotion of carrier rocket enters space, then completes track motion under graviational interaction；Rocket is the aircraft with rocket engine as power, can be in endoatmosphere, also can be in extra-atmospheric flight；Guided missile is equipped with the controllable rocket of warhead, including main at the ballistic missile of extra-atmospheric flight, the surface-to-air ballistic missile flown in endoatmosphere equipped with aerofoil and cruise missile；Guided weapon is that can carry out according to certain rule, that fly in an atmosphere, high hit rate weapon, including Terminal munition and guided cartridge.At present, having had a lot of scientific research institutions and individual to have deeper research to aircraft, LMT of the U.S. releases the single aerodynamic vehicle that a applicable manned marked price is 100,000 dollars, but in China also in the exploratory stage.nullAlong with the step of era development has people courageously to propose multiple flight scenario，In June, 2008，By Harbin Shengshi Special Type Aerocraft Co., Ltd.、The single-blade circuit " flying saucer " that China Aerospace Ke Gong group the 4th academy and space flight institute of Harbin Institute of Technology research and develop jointly is succeeded in developing in Harbin，This aircraft diameter is about 1.2 meters，Use dish ring contour of flange design and special formula aerodynamic arrangement，Flying height is between 50 meters to 1000 meters，Flight speed is 0 to 80 kilometer of weight 10 kilograms per hour，Fill fuel once can aloft fly 40 minutes，Can apply and take pictures in aviation、Geological survey、Accident illuminates and builds the aspects such as temporary communications platform，There is low latitude、Low speed、VTOL and the feature of hovering，Have the function of helicopter and fixed wing airplane concurrently，Technical support can be provided for multiple fields，Flight is without geographical restrictions，Flight track can preset，Also can change at any time，Can be widely applied to aviation take pictures、Geological survey、Ultra-high-tension power transmission line is maked an inspection tour、Oil filed pipeline checks、Freeway management、Forest fire protection cruising、Poison is reconnoitred、Drug law enforcement、Accident illuminates、Build temporary communications、The aspects such as platform emergency management and rescue and rescue；But its structure is complicated, manufacturing process is loaded down with trivial details, with high costs.Therefore, research and develop a kind of simple in construction, dish-shaped direct lifting type flight instruments simple for production and with low cost, have good society and economic worth, have a extensive future.

Summary of the invention:

The purpose of this utility model is the shortcoming overcoming prior art to exist, a kind of simple in construction of design, the dish-shaped direct lifting type flight instruments that processing technology is easy and with low cost.

To achieve these goals, agent structure of the present utility model includes chassis, dynamical system, outer housing, air vent, vent, flanging and grafting pawl；The circumferential edges downward bending on the chassis of circular configuration forms the flanging of 0-10mm height, and flanging is symmetrically arranged with 2 air vents, and the air flow outlet duct type that 2 air vents produce with dynamical system respectively connects；The upper surface center on chassis is fixedly installed outer housing, the inside of the outer housing of hollow type structure is fixedly installed dynamical system, dynamical system is bolted the upper surface center being arranged on chassis, the bottom margin of outer housing has been equidistantly spaced grafting pawl, outer housing is connected by grafting pawl plug-in type is fixing with chassis, forms space formula vent between grafting pawl and the upper surface on chassis；The upper surface on chassis is arc formula structure, the thickness on chassis is uniformly progressively increased by cylindrical circumference center, the thickness of the center on chassis is not more than 2 times of thickness at outer circumferential edges, the radius on chassis is more than more than 6 times of outer housing radius, and the power size produced according to deadweight and the dynamical system on chassis determines through Theoretical Calculation or flight test；Dynamical system includes internal combustion engine, motor and powered by nuclear energy machine, and the center of dynamical system overlaps with the center of circle on chassis.

This utility model is compared with prior art, the fraction produced by dynamical system is persistently sprayed promotion dish direct lifting type flight instruments and moves ahead by air vent, and major part air-flow is flow through along chassis upper surface external spraying type by each vent, make the upper surface pressure lower surface pressure less than chassis on chassis, provide climbing power to make it upwards fly for dish direct lifting type flight instruments；Its simple in construction, scientific in principle is reasonable, and performance safety is reliable, makes and maintenance cost is low, and operation and maintenance is convenient, and flight environment of vehicle is friendly.

Accompanying drawing illustrates:

Fig. 1 is agent structure principle schematic of the present utility model.

Detailed description of the invention:

Below by embodiment and combine accompanying drawing this utility model is described further.

Embodiment:

The agent structure of the dish-shaped direct lifting type flight instruments that the present embodiment relates to includes chassis 1, dynamical system 2, outer housing 3, air vent 4, vent 5, flanging 6 and grafting pawl 7；The circumferential edges downward bending on the chassis 1 of circular configuration forms the flanging 6 of 0-10mm height, 2 air vents 4 it are symmetrically arranged with on flanging 6, the air flow outlet duct type that 2 air vents 4 produce with dynamical system 2 respectively connects, and the regulation and control of air-flow can be realized by dynamical system 2, make transform exhaust in 2 air vents 4, control advance and heading and reset；The upper surface center on chassis 1 is fixedly installed outer housing 3, the inside of the outer housing 3 of hollow type structure is fixedly installed dynamical system 2, dynamical system 2 is bolted the upper surface center being arranged on chassis 1, the bottom margin of outer housing 3 has been equidistantly spaced grafting pawl 7, outer housing 3 is connected by grafting pawl 7 plug-in type is fixing with chassis 1, space formula vent 5 is formed between the upper surface on grafting pawl 7 and chassis 1, the air-flow produced for dynamical system 2 and the heat distributed are discharged, and make the air velocity of the upper surface on chassis 1 be more than the air velocity on lower surface, form air-flow difference and produce the buoyancy risen；The upper surface on chassis 1 is arc formula structure, the thickness on chassis 1 is uniformly progressively increased by cylindrical circumference center, the thickness of the center on chassis 1 is not more than 2 times of thickness at outer circumferential edges, the radius on chassis 1, more than more than 6 times of outer housing 3 radius, determines through Theoretical Calculation or flight test according to the power size that deadweight and the dynamical system 2 on chassis 1 produce；Dynamical system 2 includes internal combustion engine, motor and powered by nuclear energy machine, and the center of dynamical system 2 overlaps with the center of circle on chassis 1；Each parts coordinate composition dish direct lifting type aircraft, it is achieved lift-off is flown, turned to function skyborne with steadily hovering.

When the dish-shaped direct lifting type flight instruments that the present embodiment relates to uses, the air flow power that dynamical system 2 provides makes chassis 1 rotation take off and be discharged by vent 5, air-flow and heat be uniform outflow the upper surface jet flow along chassis 1 from each vent 5, make the upper surface pressure lower surface pressure less than chassis 1 on chassis 1, climbing power is provided to make it upwards fly for dish direct lifting type flight instruments, dynamical system 2 can regulate generation air-flow and the size of heat, and by controlling air-flow and heat ejection air vent 4 and the speed of vent 5, position and size realize turning to, advance, retreat, rise and the skyborne function of steadily hovering.

Claims (1)

1. a dish-shaped direct lifting type flight instruments, it is characterised in that agent structure includes chassis, dynamical system, outer housing, air vent, vent, flanging and grafting pawl；The circumferential edges downward bending on the chassis of circular configuration forms the flanging of 0-10mm height, and flanging is symmetrically arranged with 2 air vents, and the air flow outlet duct type that 2 air vents produce with dynamical system respectively connects；The upper surface center on chassis is fixedly installed outer housing, the inside of the outer housing of hollow type structure is fixedly installed dynamical system, dynamical system is bolted the upper surface center being arranged on chassis, the bottom margin of outer housing has been equidistantly spaced grafting pawl, outer housing is connected by grafting pawl plug-in type is fixing with chassis, forms space formula vent between grafting pawl and the upper surface on chassis；The upper surface on chassis is arc formula structure, the thickness on chassis is uniformly progressively increased by cylindrical circumference center, the thickness of the center on chassis is not more than 2 times of thickness at outer circumferential edges, the radius on chassis is more than more than 6 times of outer housing radius, and the power size produced according to deadweight and the dynamical system on chassis determines through Theoretical Calculation or flight test；Dynamical system includes internal combustion engine, motor and powered by nuclear energy machine, and the center of dynamical system overlaps with the center of circle on chassis.