CN86101536A - A kind of Foldable active type helicopter - Google Patents

Abstract

A kind of Foldable active type helicopter relates to the air material technology.

The present invention changes the mode of operation of general helicopter by the axle driving rotor of driving engine driven rotary, and engine installation directly is installed on rotor, produces the rotation of power direct drive rotor, and drives whole aircraft work.The major-minor rotor is detachable, coincide, but two rotor hoops are superimposed, and reduced volume is convenient to storage and is carried.This aircraft can be used for many-sides such as military affairs, civilian, physical culture.

Description

A kind of Foldable active type helicopter

A kind of collapsible active helicopter relates to the air material technology.

The autogyro that uses is therefore bulky, heavy because rotor is driven and rotor is not collapsible at present, has brought difficulty for use in particular cases.

The rotor that the present invention aims to provide a kind of light and flexible is that Zhu Dong Shi And is collapsible, for a helicopter to the four-player use.

The present invention is made up of rotor, fuselage support, actuating element, ground running part, stable part etc., change the shaft drying mode of operation of the rotor of general autogyro by the driving engine driven rotary, powerplant module directly is installed on rotor, drive whole aircraft work by its rotation ， And that produces the power driven rotor.Collapsible between main rotor and secondary rotor, launch folding at ordinary times before the flight, also can be initial point by the axle point between two rotors, hoop closes up for one and fuselage support fix, suit fuel tank in the main rotor, during flight, the centnifugal force that utilizes the rotor rotation to be produced, the oil plant in the fuel tank is directly automatically supplied with to driving engine, and the available manual mode of the startup of powerplant module obtains, aircraft advance, retreat and about turn and can control by effector, also available gravity center of human body's deflection is controlled.

Fig. 1,1～Fig. 1,3 what provide is the external form scheme drawing of single seat type machine of the present invention, Fig. 1 wherein, the 1st, single seat type pusher side view; Fig. 1, the 2nd, birds-eye view; Fig. 1, the 3rd, front elevation.

Fig. 2,1～Fig. 2,3 what provide is rotor structure scheme drawing of the present invention, wherein Fig. 2 is the birds-eye view of rotor; Fig. 2, the 2nd, the lateral plan of seeing along direction behind the rotor, Fig. 2, the 3rd, the lateral plan of seeing to the wing tip direction by wing root;

Fig. 3,1～Fig. 3,4 what provide is the collapsible scheme drawing of rotor of the present invention, Fig. 3 wherein, the 1st, the removable schematic top plan view of rotor wing tip free section; Fig. 3, the 2nd, Fig. 3,1 lateral plan; Fig. 3, the 3rd, Fig. 3,1 perspective view; Fig. 3, the 4th, rotor folding direction scheme drawing;

What Fig. 4 provided is the external form scheme drawing of tandem seat of the present invention and four-player seat type machine;

What Fig. 5 provided is simple type machine scheme drawing of the present invention.

Here provide embodiments of the invention, as shown in drawings.

The present invention is made up of five parts such as rotor (1) fuselage support (3) stable part (2) ground running part (5) actuating elements (4), and wherein: rotor (1) is common wing, by main rotor (1,1,1) and secondary rotor (1,1,2) form main rotor (1,1,1) is wing cavity, secondary rotor (1,1,2) also be wing cavity, main rotor (1,1, the near-end of far-end 1) and secondary rotor (1,1,2) is by box-shaped wing Beam (1,4,1) (1,4,2) patch connection, box-shaped wing Beam (1,4,1) there are two on the relevant position of (1,4,2) to perforation (7,1) (7,2) pin (7,7) passes perforation (7,1) (7,2), will lead, secondary rotor is fastening, forms the dihedral angle between the major-minor rotor.An engine installation of being made up of combustion engine (1,2), sieve rotating plasma (1,3), accel control parts such as (1,7) is fixed on main rotor (1,1,1) far-end forward position, by the work of engine installation, drives the rotor rotation.And provides active force for whole aircraft.Main rotor (1,1,1) in the wing cavity, puts a Fuel Tank (1,6) shown in figure one, when aircraft moved, the rotor rotation certainly will produce powerful centnifugal force, form the anti-pressure radially of fuel oil, fuel oil is under this pressure effect, and is the same with the oil pump operation naturally, fuel oil transferred to the engine installation that is positioned at the Fuel Tank outside.The rotor of aircraft is answered Cheng Dui And and is become point symmetry to occur, to guarantee the balance of aircraft.Pin (7,7) can be pulled out at ordinary times, secondary rotor (1,1,2) can be located to extract from the box-shaped wing Beam (1,4,1) of main rotor (1,1,1), folds on the main rotor (1,1,1).Form ability to dismantle, and two rotors can be amounted to, And and hold together the formation foldability in opposite directions in midpoint.The wing root coupling end of two rotors is connected by ball-bearing casing with rotor shaft, is fixed by locating dowel pin between each wing root, the point-symmetry property when guaranteeing rotor work, and the major-minor rotor can be made by glass-felt plastic, or makes with the frame skin structure.

The wing root end of rotor (1) and rotor shaft (4,1) upper extreme point connects, and rotor shaft (4,1) is a hollow bushing, tension rail adopts holds out in spite of difficulties rod type, one end and main rotor (1,1,1) outer end captive joint, the other end and rotor shaft (4,1) lower end connects, and the connection mode at two places is same as the connection mode of rotor (1) wing root coupling end and rotor shaft (4,1).The upper end of mandrel (4,8) is positioned in the rotor shaft (4,1), scalable connection, and the rear end of the lower end of mandrel (4,8) and coordinate formula connecting rod (4,3,8) (4,3,9) flexibly connects.Mandrel (4,8) the middle-end outside is with a direction support ring (4,2), and ring (4,2) connects with the triangle fuselage stature (3) that is made of device (3,1,1) (3,1,2) (3,1,3) and (3,2).Joystick (4,4) is contained in the preceding bottom of fuselage cradle by last underarm (4,4,6) (4,4,8) constitute, the front end of the underarm bottom of joystick (4,4) and coordinate formula control link (4,2) is connected, a road wheel (5,1) (5,2) (5 respectively is equipped with in the junction on triangle top, fuselage support bottom surface (11) (12) (13), 3) be convenient to move, (3,2) ， And are connected with empennage (2) to draw support at the connection row of fuselage support (3) (13), empennage (2) is by fixed fin (2,1), vertical manipulation face (2,1,1) horizontal stabilizer (2,2) horizontal controlsurface compositions such as (2,2,1).Controlsurface links to each other with step together with handling bracing cable (2,4,4), and turning to aux. controls of controlling aircraft moves forward and backward respectively.Grip, joystick top connects two bracing cables, respectively with two main rotors on throttle for IC engine (1,7) connect.Forebody fixed installation flight seat (3,4) pedal control device (4,2,1) (4,2,2) manual control device (4,4,1) (4,4,2) flight seat (3,4) branch has forms such as one-seater, double seat and many people seat; As a kind of variation, Figure 5 shows that the simple type individual lift device, no actuating element, the advance and retreat of aircraft are handled in the conversion that depends on aircraft operator's centre of body weight.

Charge of oil form in the Fuel Tank (1,6) is for poor

Charge of oil is to guarantee safe falling.

The present invention provides effective instrument for the aircraft of going straight up to that special occasions uses, and it is convenient to start, and flight is reliable, and is especially convenient when needs high maneuverability, individual soldier or group's action. Rotor is folding at ordinary times, is convenient to maintenance, stores, takes care of. Reformed audaciously the traditional structure of passive rotor, used initiatively rotor, will play good effect, this is gone straight up to aircraft and is applicable to the aspects such as military observation, forward position fast break, forest observation, rescue and relief work, sports.

Claims (3)

1, a kind of Foldable active type helicopter, relate to the air material technology, the present invention is by rotor, fuselage support, partly stable, actuating element, ground running partly waits component set-up, it is characterized in that: main rotor (1,1,1) be wing cavity, in one of its far-end forward position fixed installation for whole aircraft provide active force by combustion engine (1,2) sieve rotating plasma (1,3) (or jet engine and accel control) accel control (1,7) etc. the engine installation of component set-up is put the anti-radial pressure that is produced when Fuel Tank (1,6) utilizes rotor (1) rotation and is given the engine installation fueling in the cavity, main rotor (1,1,1) far-end and secondary rotor (1,1,2) near-end is by box-shaped wing Beam (1,4,1) (1,4,2) patch connection, pair pinned hole (7,1) (7,2) And pin (7 is arranged on the relevant position of box-shaped wing Beam, 7) be fastenedly connected, pull out pin, secondary rotor (1,1,2) can be from wing Beam (1,4,1) extract at the place of patching, and is folded into main rotor (1,1,1) on, (1) Cheng And becomes point symmetry to occur to rotor, and two rotors can be in rotor shaft (4,1) some place hoop is folding, forms one.

2, aircraft according to claim 1 is characterized in that: fuselage partly can be one-seater, double seat, also can be the four-player seat.

3, aircraft according to claim 1 is characterized in that, a kind of variation of fuselage, and simple and easy fuselage is an one-seater, the aircraft manipulation is to depend on the flight of advancing, retreat and turn left, turn right that aircraft is handled in the conversion of aircraft operator's centre of body weight.

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