CN2741869Y

CN2741869Y - Improved plane turning and lifting device

Info

Publication number: CN2741869Y
Application number: CN 200420070427
Authority: CN
Inventors: 栾松瑞; 李春生; 张伟
Original assignee: 栾松瑞
Priority date: 2004-08-25
Filing date: 2004-08-25
Publication date: 2005-11-23
Anticipated expiration: 2014-08-25

Abstract

The utility model discloses an improved plane turning and lifting device, comprising a turning mechanism, a lifting mechanism, and a built-in control system. The improved plane turning and lifting device is characterized in that the turning mechanism and the lifting mechanism are arranged on an aeroplane head, wherein, the turning mechanism comprises a head part, a rotation body arranged on the head part, and the horizontal turning wings of variable angles arranged on the both sides of the components; the lifting wings of the lifting mechanism are arranged on a lifting turning movable wing shaft which is fixed on a built-in control lifting turning stand by fixing bolts and nuts; the hydraulic oil cylinder assembly of the built-in control system is connected with the built-in control lifting turning stand by a hydraulic control draw rod; the swiveling gear of a fore body is engaged with the semicircular ring gear of the fore body; a swiveling motor for controlling the fore body is installed on a post body. The turning lifting device has the advantages of small turning torque, small turning radius, fast lifting action, flexible maneuver, safety and reliability, etc.; the improved plane turning and lifting device is not easy to generate severe crash accidents.

Description

A kind of follow-on aircraft turns to and jacking system

Technical field

The utility model relates to a kind of technical field with lifting mechanism of turning to of aircraft, and specifically a kind of follow-on aircraft turns to and jacking system.

Background technology

Domestic and international various aircrafts turns to and jacking system at present, almost all be arranged on the afterbody top of aircraft, shape triangular in shape, its shortcoming is that steering torque is big, and Turning radius is big, and maneuvering performance is poor, especially be a fatal weakness for operational aircraft, and when the aircraft et out of order, major accidents such as air crash take place easily, very dangerous.

The utility model content

The technical problems to be solved in the utility model provides a kind of follow-on aircraft and turns to and jacking system, it has, and steering torque is little, Turning radius is little, lifting action is fast, operational performance is good, maneuverability, safe and reliable, when aircraft breaks down, be difficult for taking place major accidents such as air crash.

Follow-on aircraft described in the utility model turns to and jacking system, trail the bionics principle that head changes according to animal walking, the steering hardware and the lifting mechanism of this device are arranged on aeroplane nose, wherein the steering hardware of the aircraft variable angle level that includes head section, be installed in the rotation fuselage of head section and be contained in head section and rotate the fuselage both sides turns to wing, and above-mentioned parts constitute relative gyro-rotor with rear body; Lifting mechanism comprises the lifting wing, this lifting wing is installed in lifting and turns on the movable wing axle, lifting turns to the movable wing axle to be fixed on the machine inner control lifting turning rack with wing axle anchor bolt nut and forms the swing revolution, turns to about can the realization level and can realize climbing and down maneuver; Machine inner control system comprises the fluid control pull bar, the hydraulic ram assembly, travel(l)ing rest pull bar actuating spindle, the semicircle internally toothed annulus of forebody, control forebody swiveling gear, control forebody slewing motor, wherein the hydraulic ram assembly is connected with machine inner control lifting turning rack by the fluid control pull bar, this lifting turning rack is fixed on aircraft lifting and landing with wing axle anchor bolt nut and turns on the wing axis, this lifting turns to wing axis and revolution forebody to flexibly connect, the revolution forebody is connected with bearing with rear body, the semicircle internally toothed annulus engagement of control forebody swiveling gear and forebody, this semicircle internally toothed annulus is fixed on the revolution forebody, and control forebody slewing motor is installed on the rear body.

The utility model its advantage compared with the prior art is:

1. the Turning radius of its steering hardware is little, can make 180 degree fast rotation, flexible movements, and manoevreability is good;

2. safety is good, and the air crash accident be difficult for to take place, when aircraft in flight course during as the accidental mechanical fault, but aviator's operating aircraft do repeatedly to glide, gliding flight in landing locally, is avoided air crash, compares safety, reduces the loss;

3. because aeroplane nose is equipped with the variable angle level and turns to wing 3 and lifting wing 5, make to take off to come back soon, the distance of taking off is short, when it takes off during scooter 220km/, take-off angle is big,, can taken off on the capital ship deck or on temporary runway such as the express highway to 70 degree by 0 degree;

4. because lifting mechanism and steering hardware are arranged on aeroplane nose, remove tail vane, thereby make aircraft balanced good, its host wing can drag aircraft total weight 4/5, and the variable angle level turns to wing 3 can drag aircraft total weight 1/5, owing to remove tail vane, alleviate the aircraft own wt, increase load carrying ability, reduce manufacturing cost, increase economic efficiency;

5. owing to adopt the utility model, wing can adopt ultrathin structure design, alleviates the aircraft own wt greatly, cost-cutting.

Description of drawings

Fig. 1 turns to structural representation with jacking system for follow-on aircraft.

Fig. 2 is that the A of Fig. 1 is to view.

Fig. 3 is that the B of Fig. 1 is to view.

Fig. 4 is that the C of Fig. 1 is to view.

Fig. 5 is that the D of Fig. 1 is to view.

Fig. 6 is revolution forebody and rear body connection diagram.

The specific embodiment

The utility model structure such as Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5 and shown in Figure 6, it comprises steering hardware, lifting mechanism and machine inner control system, machine inner control system is used to control that aircraft lifting and landing mechanism steering hardware climbs, decline and level left and right sides handling maneuver; The rear body brace panel is housed on rear body, on machine inner control lifting turning rack, is provided with brace panel.

Below in conjunction with the description of drawings operating principle that turns to lifting mechanism of the present utility model.

Because the utility model adopts the variable angle level to turn to the wing 3 and host wing to form parastate, the variable angle level turns to the wing 3 to form lead angle when turning to, not parallel with the back wing, get off the plane in the air resistance effect and to produce left and right sides deflection, aircraft flight path is curved, the aircraft guiding changes because the rotation fuselage 2 of aircraft forward changes with the host wing degreeof turn, and aircraft can be done to turn to about level; Because fuselage head has the fuselage 2 of rotation and variable angle level to turn to wing 3, when elevating plane 5 and ground are not parallel and ground forms angle, under the air resistance effect, under the effect of aircraft potential energy, kinetic energy, makes aircraft realize climbing and down maneuver.

Label among the figure: 1 is head section, and 4 is wing axis, and 6 is bolt and nut, and 7 for turning to Frame, 8 are the hydraulic control pull bar, and 9 is the hydraulic jack assembly, and 10 is rear body, and 11 is forebody, 12 is Control Shaft, and 13 is the rear body stiffener, and 14 for rotating stiffener, and 15 is ring gear, and 16 are Swiveling gear, 17 is motor.

Claims

1. a follow-on aircraft turns to and jacking system, it comprises steering hardware, lifting mechanism and machine inner control system, it is characterized in that: the steering hardware and the lifting mechanism of this device are arranged on aeroplane nose, wherein the steering hardware of aircraft includes head section (1), the variable angle level that is installed in the rotation fuselage (2) of head section (1) and is contained in head section (1) and rotates fuselage (2) both sides turns to wing (3), and above-mentioned parts constitute relative gyro-rotor with rear body (10); Lifting mechanism comprises elevating plane (5), and this elevating plane (5) is installed in lifting and turns on the movable wing axle (4), and lifting turns to movable wing axle (4) to be fixed on the machine inner control lifting turning rack (7) with wing axle anchor bolt nut (6); Machine inner control system comprises fluid control pull bar (8), hydraulic ram assembly (9), travel(l)ing rest pull bar actuating spindle (12), the semicircle internally toothed annulus (15) of forebody, control forebody swiveling gear (16), control forebody slewing motor (17), wherein hydraulic ram assembly (9) is connected with machine inner control lifting turning rack (7) by fluid control pull bar (8), this lifting turning rack (7) is fixed on aircraft lifting and landing with wing axle anchor bolt nut (6) and turns on the wing axis (4), this lifting turns to wing axis (4) and revolution forebody (11) to flexibly connect, revolution forebody (11) is connected with bearing with rear body (10), control forebody swiveling gear (16) is meshed with the semicircle internally toothed annulus of forebody (15), this semicircle internally toothed annulus (15) is fixed on the revolution forebody (11), and control forebody slewing motor (17) is installed on the rear body (10).

2. turn to and jacking system according to the described follow-on aircraft of claim 1, it is characterized in that: rear body brace panel (13) is housed on the rear body (10), on machine inner control lifting turning rack (7), is provided with kinematic support and rotates brace panel (14).