CN202464125U

CN202464125U - Vertical take off and landing (VTOL) aerobat with twin-duct composite tail rudder

Info

Publication number: CN202464125U
Application number: CN2012200323339U
Authority: CN
Inventors: 刘长亮
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-02-02
Filing date: 2012-02-02
Publication date: 2012-10-03
Anticipated expiration: 2022-02-02

Abstract

The utility model discloses a vertical take off and landing (VTOL) aerobat with a twin-duct composite tail rudder, which comprises an airframe, load-bearing wings, two ducts, a composite tail rudder and alighting gears; the two ducts are connected with the airframe through the load-bearing wings, and are symmetrically arranged; the load-bearing wings are wing units of a convex-type thin-walled structure; one end of the composite tail rudder is connected with a lower part of the airframe, the other end of the composite tail rudder is of a plane fin-like structure, a shock absorption cushion is arranged in the middle part of the composite tail rudder, the plane fin-like structure of the composite tail rudder makes an appropriate angle with a transverse section of the airframe, and miniature ducts for configuring a propeller are arranged in the middle part of the composite tail rudder; and the alighting gears are symmetrically arranged on both sides of the airframe. By the adoption of the technical schemes, the aerobat can vertically take off and land without a limitation of a place, and can hover and circle with convenience in operation, the aerobat has the advantages of low speed in a low altitude and high speed in a high altitude, high flying efficiency, low noise during flying and good stealthiness, can be used for executing tasks of carry, scout, surveillance, attack and the like, and has high value of application.

Description

A kind of pair of compound tail vane vertically taking off and landing flyer of duct

Affiliated technical field

The utility model relates to a kind of pair of duct compound tail vane vertically taking off and landing flyer, especially unmanned vehicle, can realize VTOL, and takes into account high-speed flight and handle flexibly, belongs to the airflight technical field of transportation means.

Background technology

At present, the aircraft takeoff of the ordinary fixed wing all needs higher speed with landing just can make wing produce enough lift, therefore needs special-purpose taking-off and landing place, is unfavorable for very much using particularly military utilization.Take big place when in addition, parking on ground.And common rotor craft adopts rotor magnetic tape trailer oar or coaxial pair of paddle structure mostly, though the flexible shortcoming of flight also clearly, the blade of high speed revolution threatens personnel and equipment safety on the one hand, and flying speed is lower on the other hand, also is unfavorable for practical application.

The utility model content

In order to overcome present fixed-wing aircraft landing inconvenience and the dangerous low-tach shortcoming of rotary-wing aircraft, the utility model provides a kind of pair of compound tail vane vertically taking off and landing flyer of duct, and the two ducts of this aircraft utilization provide power; Realize the conversion of flight attitude in conjunction with compound tail vane; Reasonable in design, compact conformation not only can VTOL but also can handle flexibly and high-speed flight, can also static suspension; Has application promise in clinical practice, particularly at military aspect.

In order to achieve the above object, the technical scheme that the utility model adopted is:

A kind of pair of compound tail vane vertically taking off and landing flyer of duct comprises body, the load wing, duct, compound tail vane and alighting gear; Said duct is connected with body through the load wing, the left-right symmetric configuration; Said compound tail vane one end is connected with underpart, and the other end is the plane fin structure, and the middle part has the small-sized duct of configuration screw propeller; Said compound tail vane bottom is provided with cushion blocking; Said alighting gear has shock absorption device in the configuration of body bilateral symmetry on it.

Electrokinetic cell and flight-control computer are equipped with in the inside of said body.

Electrical motor is equipped with through connecting strap in the place, axis of said duct, and electrical motor is connected with screw propeller;

The said load wing is an epirelief formula thin-wall construction wing.

The plane fin structure of said compound tail vane is suitable angle with the cross-sectional plane of body.

The beneficial effect of the utility model is that design science, compact conformation can not receive place restriction VTOL; And can hover, spiral, manoeuvrable, but both low-altitude low-speed also but the high-altitude is at a high speed; Have higher flight efficiency, the flight noise is low, good concealment; Can carry out tasks such as delivery, scouting, supervision and attack, have very high using value.

Description of drawings

Below in conjunction with accompanying drawing and embodiment the utility model is further specified.

Fig. 1 is the utility model schematic perspective view;

Fig. 2 is the utility model front elevation;

Fig. 3 is the utility model right elevation;

Fig. 4 is the utility model birds-eye view.

1. ducts, 2. connecting straps, 3. screw propellers, 4. bodies, the 5. load wings, 6. electrical motors, 7. compound tail vane 8. plane fin structures 9. small-sized duct 10. alighting gears 11. cushion blockings 12. electrokinetic cells 13. flight-control computers 14. shock absorption devices among the figure

The specific embodiment

Below in conjunction with accompanying drawing the embodiment of this aircraft is described, but be not limited thereto.

Like Fig. 1-Fig. 4, a kind of pair of compound tail vane vertically taking off and landing flyer of duct comprises body 4, the load wing 5, duct 1, compound tail vane 7 and alighting gear 10; Said duct 1 is connected with body 4 through the load wing 5, the left-right symmetric configuration, and hand of rotation is opposite, and other all parameters are all identical, and left rotation and right rotation moment is cancelled out each other.

Said compound tail vane 7 can be " J " font; Also can be " I " font; One end is connected with underpart; The other end is a plane fin structure 8, and the middle part has the small-sized duct 9 of configuration screw propeller, produces torque-controllable to realize the state exchange and the control of aircraft acceleration, deceleration, vertical flight and horizontal flight; Compound tail vane 7 bottoms are provided with cushion blocking 11, can cooperate with alighting gear 10 to form 3 planes and be used for the landing of aircraft and park; Said alighting gear 10 has shock absorption device 14 in the configuration of body 4 bilateral symmetry on it, can support aircraft and make it to dock at vertical state, also can when aircraft lands, absorb impact simultaneously, protection machine inner component.

Electrokinetic cell 12 and flight-control computer 13 are equipped with in the inside of said body 4, and the former is used to provide the power source of aircraft, and the latter is the attitude of combined command controlling aircraft on the basis of fully gathering the aircraft state then.

Electrical motor 6 is equipped with through connecting strap 2 in the place, axis of said duct 1, and electrical motor 6 is connected with screw propeller 3, and electrical motor 6 drives screw propeller 4 rotations, produces negative pressure between blade tip and the duct 1, thereby produces lift upwards.

The said load wing 5 is an epirelief formula thin-wall construction wing, both can when VTOL, bear the power of vertical direction, also can when horizontal flight, bear the power of plane of structure direction; Simultaneously, the epirelief aerofoil profile can provide certain lift when the aircraft horizontal flight, improves flight efficiency.

The plane fin structure 8 of said compound tail vane 7 is suitable angle with body 4 cross-sectional planes, when the aircraft horizontal flight, forms the suitable angle of attack so that suitable longitudinal moment to be provided, thereby improves flight efficiency.

Claims

1. two compound tail vane vertically taking off and landing flyer of duct is characterized in that: comprise body, the load wing, duct, compound tail vane and alighting gear; Said duct is connected with body through the load wing, the left-right symmetric configuration; Said compound tail vane one end is connected with underpart, and the other end is the plane fin structure, and the middle part has the small-sized duct of configuration screw propeller; Said compound tail vane bottom is provided with cushion blocking; Said alighting gear has shock absorption device in the configuration of body bilateral symmetry on it.

2. the compound tail vane vertically taking off and landing flyer of pair duct according to claim 1, it is characterized in that: electrokinetic cell and flight-control computer are equipped with in the inside of said body.

3. the compound tail vane vertically taking off and landing flyer of pair duct according to claim 1 is characterized in that: electrical motor is equipped with through connecting strap in the place, axis of said duct, and electrical motor is connected with screw propeller;

4. the compound tail vane vertically taking off and landing flyer of pair duct according to claim 1 is characterized in that: the said load wing is an epirelief formula thin-wall construction wing.

5. the compound tail vane vertically taking off and landing flyer of pair duct according to claim 1 is characterized in that: the plane fin structure of said compound tail vane is suitable angle with the cross-sectional plane of body.