CN1380222A

CN1380222A - Flying vehicle air-form regulation system

Info

Publication number: CN1380222A
Application number: CN 02114585
Authority: CN
Inventors: 孔小乐
Original assignee: Individual
Current assignee: Individual
Priority date: 2002-05-21
Filing date: 2002-05-21
Publication date: 2002-11-20

Abstract

The air attitude regulation system of flight vehicle adopts six electric engines, mounted on three freedomes of motion of aircraft body to regulate flight attitude of aircraft. Every group of electric engines (two electric engines on one freedom of motion are formed into a group of attitude regulation engine) can be simultaneously foreward rotated, simultaneously backward rotated or can make one of them be foreward rotated and another be backward rotated so as to produce same direction thrust, reverse-direction thrust and make one of them be foreward rotated and another be backward rotated, so that it can quickly and effectively regulate air attitude of the flight vehicle.

Description

Aircraft aerial statue Adjustment System

Affiliated technical field

This patent belongs to the aviation aircraft design field, especially aircraft aerial statue Adjustment System.

Background technology

At present, the main mode that adopts main screw not only to produce lift but also control attitude in the design of known autogyro, involve the anglec of rotation that complicated mechanical control pull rod structure changes screw propeller, the material of pull bar involves the many aspects of fatigue of material and mechanical control, and is very complicated.Be difficult to make, keep in repair, control.

The concrete difference of 44 heligyroes that this patent and prior art are particularly mentioned in the patent 00118238.2 is: four driving engines of this patent become rectangular arranged, counterturn respectively and are the direct driving force sources of aircraft.And the driving engine of this patent is not the direct driving force source of aircraft, only adjusts power as auxiliary aerial statue, and overlappingly is distributed in the fuselage both sides, and not specific employing counterturn.Different its engine installations that are with 00221091.6 are on the main screw blade.

Summary of the invention

The present invention solves the aircraft aerial statue and adjusts the technical scheme that problem adopted and be: do not adopt the mode of mechanical control screw propeller angle to regulate the aerial statue of aircraft, but be installed in the flight attitude of regulating aircraft on the three degree of freedom of airframe with six genemotors.Every group of genemotor wherein (two genemotors on the one degree of freedom are that one group of attitude is adjusted driving engine) can just be changeed simultaneously according to the control needs, anti-pass simultaneously, a positive opposite spin.Thereby produce equidirectional thrust, reversing sense thrust and positive and reverse return torque.

The beneficial effects of the utility model are to adjust the aircraft aerial statue apace, and Installation and Debugging are safeguarded simple.

Below in conjunction with drawings and Examples the utility model is further specified.

Per two driving engines are one group, be respectively applied for adjust fuselage x direction (from head to tail line direction) y direction (from wing two ends line direction) and and x, the aerial statue of the three degree of freedom of the aircraft that the z direction that y is vertical is formed.

Aircraft in the process of taking off 1. 2. 3. 4. driving engine can just change simultaneously, producing downward thrust assists main screw to make rapid rising of aircraft reach the designated flying zone, in aircraft decline process 1. 2. 3. 4. driving engine can reverse simultaneously, thereby produce downward thrust aircraft is descended rapidly.Attitude is adjusted driving engine and the aerial statue of aircraft is carried out control method is:

1. 2. driving engine is that the x direction level of aircraft is regulated, and 3. 4. driving engine is regulated the y direction level of aircraft.5. 6. the head direction is regulated.More than produce different control effects by the rotating speed of controlling six driving engines with turning in the process of various aerial adjustings.For example 1. 2. in the powerplant module 1. number driving engine just changeing 2. that number engine inversion then makes the axial moment of rotation of the horizontal x of aircraft generation, regulate because the attitude that wind direction and active force produce.Thereby same reason 3. 4. number driving engine also by a positive despining produce the axial cw of y or C.C.W. moment make the horizontal y of aircraft generation axially rotation reach the purpose that comes back and stick up tail.5. the thrust that 6. number driving engine is just changeing simultaneously or the aircraft horizontal direction is supplied with in counter-rotating simultaneously, aircraft produces the axial moment of rotation of z and changes the head direction and both turned in the air during a positive despining.

Claims

1, a kind of aerial statue of aircraft is adjusted structure, is made up of six driving engines.

2, adjustment structure according to claim 1 is characterized in that per two each groups of driving engine, make screw propeller produce different thrusts by the control rotating speed, be respectively applied for adjust fuselage x direction (from head to tail line direction) y direction (from wing two ends line direction) and and x, the three degree of freedom of the z direction that y is vertical is with respect to the attitude of ground frame of reference.

3, adjustment structure according to claim 1 is characterized in that one group of 2 driving engine adjusting aerial statue generation y axle moment of rotation are installed in head and tail part respectively, and their line is parallel with the x direction, and their dynamical axis is axially parallel with the z direction.

4, adjustment structure according to claim 1 is characterized in that one group of 2 driving engine adjusting aerial statue generation x axle moment of rotation are installed in the wing two end portions symmetrically, and their line is parallel with the y direction, and their dynamical axis is axially parallel with the z direction.

5, adjustment structure according to claim 1 is characterized in that one group of 2 driving engine adjusting aerial statue generation z axle moment of rotation are installed in the wing two end portions symmetrically, their line is parallel with the y direction and overlaps with adjusting the line that aerial statue produces one group of 2 driving engine of x axle moment of rotation, and their dynamical axis is axial parallel with the x direction.

6, adjustment structure according to claim 1 is characterized in that these 6 driving engines can Be Controlled produce the positive and reverse return biography.

7, adjustment structure according to claim 1 is characterized in that these 6 driving engines can Be Controlled produce the different biography speed of revolving.