CN102642612A

CN102642612A - Airplane full chord length aileron

Info

Publication number: CN102642612A
Application number: CN2012101462600A
Authority: CN
Inventors: 王银虎; 郭兆电; 李青; 陈涛; 余新春
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2012-05-11
Filing date: 2012-05-11
Publication date: 2012-08-22

Abstract

The invention belongs to the field of airplane design and relates to an airplane full chord length aileron used for airplane rolling control. Wingtips of a left wing and a right wing of an airplane are respectively disconnected in the position accounting for 10%-30% of the length of each wing inwards, and a left full chord length aileron and a right full chord length aileron are respectively formed on each wingtip part; a left inner wing and a right inner wing are respectively formed on the inner side parts of the left wing and the right wing; the inner ends of the left inner wing and the right inner wing are respectively connected with the fuselage; a driving motor is respectively fixedly arranged in the positions accounting for 30-60% of the local full chord length of the outer ends of the left inner wing and the right inner wing, shafts of the two driving motors respectively extend into the corresponding full chord length ailerons and are fixedly connected with the corresponding full chord length ailerons, and the two driving motors are both connected with the flight control system of the airplane. According to the full chord length aileron disclosed by the invention, the wing unfolding space occupied by the rolling control wing face is reduced, the flying resistance is reduced, and the control ability and the safety of the airplane are improved.

Description

The full chord length aileron of aircraft

Technical field

The invention belongs to the airplane design field, relate to a kind of full chord length aileron of aircraft that is used for the aircraft roll guidance.

Background technology

The aircraft roll guidance aerofoil of widespread usage is a part chord length aileron (see figure 1) at present both at home and abroad.The advantage of part chord length aileron is simple in structure, and its shortcoming is: the exhibition that accounts for wing is bigger to the space, has limited the operable wing exhibition of high lift device to the space, has limited the lift-rising ability of aircraft; In order to satisfy the stalling characteristics requirement of aircraft, the wing of mounting portion chord length aileron needs bigger wing twist angle, and this causes the induced drag of aircraft when cruising bigger, has reduced the 1ift-drag ratio of aircraft; The deflection of part chord length aileron is relatively low to the efficient of aircraft roll guidance, and particularly when part chord length aileron movement angle was big, its driving efficiency sharply descended; Part chord length aileron movement produces additional lift, and this part additional lift point of action is positioned at after the firm heart of local aerofoil profile; Cause aileron to lose efficacy even reversal easily; Aileron lost efficacy even the problem of reversal in order to overcome, and can strengthen the weight of wing structure, reduced the airworthiness of aircraft.

Summary of the invention

The objective of the invention is to propose the full chord length aileron of a kind of aircraft wing induced drag when cruising aircraft little, that aircraft roll guidance efficient is high.The technical solution of the present invention is summarized as a whole chord length of the aircraft aileron, characterized in that the left wing and right wing airplane wingtip inwardly respectively representing the length of each wing 10% to 30% Disconnect the location, on each side respectively formed part of the left wingtip full chord chord length full aileron and right aileron; inside of the left wing and right wing portion respectively formed inside the left and right inner wing inner wing; Within the left wing and right wing of the inner end inside the fuselage, respectively connected; left inner wing, the outer end of the right inner wing local chord length within 30% ~ 60%, respectively, fixedly mounted at a drive motor, two drive motor shaft extend respectively to the corresponding internal full chord ailerons and the entire chord length of the corresponding flap is fixedly connected with two drive motors are connected to the aircraft flight control system.

The shape of the full chord length aileron that described left and right sides wing forms is symmetrical or asymmetric.

Within the left wing and right wing inside the outer end of the inner front wing local chord length from the origin of 30% to 60%, respectively, at fixed mounting a drive motor.

The motor shaft that described and cooresponding full chord length aileron is captiveed joint is vertical with the fuselage plane of symmetry.

Advantage that the present invention has and beneficial effect the present invention proposes a kind of aircraft lift-over operation aerofoil---full chord length aileron that can overcome part chord length aileron drawback.The exhibition that full chord length aileron can dwindle the shared wing of 20%～40% roll guidance aerofoil is to the space; Make the operable wing exhibition of high lift device increase by 10%～20% to the space; Make aircraft when landing, increase by 3%～6% lift, be equivalent to the passenger or the goods of many transportations 3%～6%; Under the prerequisite that the stalling characteristics that satisfy same aircraft require, the wing twist angle that full chord length aileron is installed can reduce 1 °～3 °, makes the 1ift-drag ratio that cruises of aircraft improve 0.5%～2%, and fuel oil consumption reduces 0.5%～2%; When takeoff and landing, full chord length aileron can make aircraft aileron control efficient improve 25%～50%; In the tailspin process, full chord length aileron always can guarantee that aircraft has enough roll guidance efficient, improves the safety of aircraft in the whole stall of aircraft.

Description of drawings

Fig. 1 is the scheme drawing of existing part chord length aileron;

Fig. 2 is the cutaway view of the part chord length aileron of Fig. 1;

Fig. 3 full chord length aileron scheme drawing of the present invention;

Fig. 4 is the full chord length aileron of a Fig. 3 cutaway view;

Fig. 5 is a structural representation of the present invention.

The specific embodiment

Below in conjunction with accompanying drawing the present invention is elaborated.

As shown in the left wing and right wing airplane wingtip inwardly respectively representing the length of each wing 10% to 30% of the disconnected position, the portion on each side are formed left wingtip full chord chord length full aileron and right aileron 2; inside of the left wing and right wing portion respectively formed inside the inner left wing and right wing within 5; inside left wing and right wing within the inner end of five planes, respectively body contact; left inner wing, the outer end of the right inner surface 5 within 30% of the local chord length of ~ 60%, respectively, fixedly mounted at a drive motor 4, two drive motor shaft 3 extending respectively to the corresponding full chord aileron 2 inside, and the entire chord length of the corresponding flap 2 is fixedly connected with two drive motors 4 are both connected to the aircraft flight control system.

The present invention can divide for four steps realized:

(1), confirms full chord length aileron 2 needed areas according to the aircraft controllability requirement;

(2) from wing tip side direction in wing, the area of the needed full chord length aileron 2 of intercepting;

(3) confirm the position of drive motor 4 at 30%～60% place that aileron and main wing intersect the chord length of section, and drive motor 4 is fixedly connected on the inner wing 5;

(4) end away from drive motor 4 with drive motor axle 3 is fixedly connected on the full chord length aileron 2.

(5) send control signal to drive motor 4 from the aircraft flight controlling system, drive motor 4 drives full chord length aileron 2 through drive motor axle 3 and carries out yaw motion.

The present invention realizes the rolling movement of aircraft through following steps:

(1) with the full chord length aileron in right side (2) upward deflect, the full chord length aileron in left side deflects down, realize aircraft left side wing upwards, the downward rolling movement of right side wing;

(2) with the full chord length aileron in left side upward deflect, the full chord length aileron in right side (2) deflects down, realize aircraft right side wing upwards, the downward rolling movement of left side wing.

Claims

A method for aircraft ailerons whole chord length, characterized in that the left wing and right wing airplane wingtip inwardly respectively representing the length of each wing 10% to 30% of the disconnected position, wingtip portion on each side are formed left and right aileron full chord chord length full aileron (2); the inside of the left wing and right wing portion of the inner wing are formed inside left and right inner wing (5); Within the left wing and right inner wing (5) of the inner ends connected with the aircraft fuselage; left inner wing and right inner wing (5) within the outer end of the local chord length at 30% to 60%, respectively fixedly mounted a drive motor (4), two drive motor shaft (3) extend respectively to the corresponding chord length of the entire flap (2) the inside and the entire chord length of the corresponding flap (2) is fixedly connected, two drive motors (4) both the aircraft flight control system.
2. the full chord length aileron of a kind of aircraft according to claim 1 (2) is characterized in that, the shape of the full chord length aileron (2) that described left and right sides wing forms is symmetrical or asymmetric.
3 according to claim 1, wherein a full chord length aircraft aileron (2), characterized in that said inner wing of the left and right inner wing (5) within the outer end of the wing local chord length before the origin of the 30% to 60%, respectively, fixedly mounted at a drive motor (4).
4. the full chord length aileron of a kind of aircraft according to claim 1 (2) is characterized in that, the motor shaft (3) that described and cooresponding full chord length aileron (2) is captiveed joint is vertical with the fuselage plane of symmetry.