CN114812291A

CN114812291A - Completely-contractible flexible wing-changing mechanism

Info

Publication number: CN114812291A
Application number: CN202210332824.3A
Authority: CN
Inventors: 王旭刚
Original assignee: Nanjing University of Science and Technology
Current assignee: Nanjing University of Science and Technology
Priority date: 2022-03-31
Filing date: 2022-03-31
Publication date: 2022-07-29

Abstract

The invention discloses a flexible wing-changing mechanism capable of being completely contracted, which is used for realizing bird-like wing-changing flight of an aircraft in the flight process, and the aircraft can fly in an optimized pneumatic layout under the conditions of different flight speeds and heights by changing the shape of a flexible missile wing. The flexible wing-changing mechanism consists of an aircraft main body, a main driving rod with a turbine, a flexible skin, a framework, two motors, a worm rod coaxially connected with the motors, a torsion spring and an end cover. Two ends of the flexible skin are respectively fixed on the framework and the torsion spring, the flexible skin is unfolded and keeps certain rigidity by means of the tension of the framework and the torsion spring, and different missile wing flexible deformations are realized through different included angles between the framework and the missile body; when the flexible missile wing does not need to be unfolded, the flexible missile wing is wound on the torsion spring shaft completely by means of the directional tension of the torsion spring, and complete contraction is achieved. The wing changing mechanism has the characteristics of light weight and small occupied space of the structure, and can effectively improve the load of the flying body.

Description

Completely-contractible flexible wing-changing mechanism

Technical Field

The invention belongs to the technical field of variable-wing flight of aircrafts, and particularly relates to a fully-retractable flexible variable-wing mechanism suitable for a high-speed flight body.

Background

The bionic variant flight technology is the key development direction in the field of current aircraft design, and with the continuous progress of various disciplines such as aerodynamics, mechanics, materials science, control science and the like, the variant flight technology developed from the bionics gets more and more attention of researchers, and particularly with the demand for the development of intelligent aircraft, the variant flight shows huge application prospects in the field of aircraft research. The shape of the aircraft is changed in flight, bionic optimization flight is realized or control force for changing the flight attitude is provided, along with higher and higher requirements on the flight performance of the aircraft, a variety of variant aircrafts in different modes appear, wherein variable wing flight is an aircraft variant flight mode with wide application. The wing-variable aircraft can adapt to different flight states by changing the area of an airfoil or a certain critical dimension in the flight process, for example, in the process of long-distance gliding flight, the parameters of the airfoil are changed along with the change of the flight height and the speed, the optimal lift-drag ratio shapes in different states are realized, and the aircraft can fly in the optimal aerodynamic shape in the whole trajectory.

The wing changing mechanism of the bionic morphing aircraft can be divided into a rigid wing and a flexible wing, the rigid wing is relatively simple in structure, but occupies a larger structure and weight proportion of the flying body, the effective load of the aircraft is reduced, and the power mechanism required for driving the rigid wing is larger in power; the flexible wing has the characteristics of light weight, small space occupied by the projectile body after contraction, quick drive response, low power consumption of a drive system and the like. In addition, from the perspective of bionics, the flexible wing-changing technology better conforms to the characteristic of flexible change of wings of birds, insects and the like, and is more beneficial to improving the flying efficiency of the flying body. The flexible wing-changing technology is a more excellent wing-changing scheme, but the flexible wing-changing technology has higher requirements on materials, mechanisms, control and the like, so that greater design complexity is brought, and for different aircrafts, a suitable wing-changing mechanism needs to be designed by combining the structure and the flying characteristics of the aircrafts. As the morphing aircraft becomes the focus of research in the current field of aircraft design, research on flexible morphing mechanisms is urgently needed.

Disclosure of Invention

The invention aims to provide a design scheme of a flexible wing-changing mechanism capable of being completely contracted so as to realize bird-like wing-changing flight of an aircraft in the flight process, thereby improving the flight performance and efficiency.

The technical solution for realizing the purpose of the invention is as follows:

a flexible wing-changing mechanism capable of being completely contracted is assembled on an elastic body and comprises an aircraft main body, a main driving rod, a flexible skin, a driving part, a scroll rod connected with the driving part, a torsion spring and an end cover;

two ends of the flexible skin are respectively fixed on the main driving rod and the torsion spring, and the flexible skin is unfolded by means of the tension of the main driving rod and the torsion spring; the front side end of the main driving rod is provided with a turbine, and the turbine is supported in the aircraft main body through a rotating shaft; the turbine is matched with the worm rod to realize transmission; the driving part drives the scroll rod to rotate and is used for driving the main driving rod to expand and contract, so that the included angle between the main driving rod and the axis of the missile body is changed, and the shape change of the missile wing is realized;

the torsion spring is fixed on the end cover through a torsion spring shaft, and the end cover is fixed at the tail part of the aircraft main body; notches are formed in the two sides of the aircraft main body and used for accommodating the flexible skin and the main driving rod on the left side and the right side; when the flexible missile wing does not need to be unfolded, the flexible missile wing is wound on the torsion spring shaft by means of the tension of the torsion spring, and complete contraction is achieved.

Compared with the prior art, the invention has the following remarkable advantages:

(1) by adopting the flexible skin, the missile wing can be completely folded and unfolded, and the missile wing has the characteristics of light weight and small structure occupation space on the basis of meeting the requirement of large-scale wing change of an aircraft, and can effectively improve the load of a flight body.

(2) The flexible wing surface is light in weight, so that the flexible wing surface can be conveniently and rapidly contracted and expanded, and the power consumption of a driving system is reduced.

Drawings

Fig. 1 is a schematic structural diagram of a variable wing on a projectile body.

FIG. 2 is a schematic view of a variable wing attachment member.

Detailed Description

The invention is further described with reference to the following figures and embodiments.

With reference to fig. 1 and 2, the fully retractable variable missile wing mechanism of the invention is assembled on a missile body and arranged along the longitudinal axis of the missile body, and the main components comprise an aircraft body 1, a main driving rod 2 with a turbine, a flexible skin 3, a framework 4, two motors 5, a worm rod 6 coaxially connected with the motors, a torsion spring 7 and an end cover 8. Two ends of the flexible skin 3 are respectively fixed on the main driving rod 2 and the torsion spring 7, the flexible skin is unfolded and keeps certain rigidity by depending on the tension of the main driving rod 2 and the torsion spring 7, and different flexible deformation of the missile wing is realized by different included angles between the driving rod 2 and the missile body; a plurality of skeletons 4 are arranged in the middle of the flexible skin 3 at intervals to enhance the rigidity of the flexible skin 3. The end part of the main driving rod 2 is provided with a turbine which is matched with the worm 6 to realize transmission, and the turbine is supported in the aircraft main body 1 through a rotating shaft; the motor 5 is fixed at the front end in the aircraft body 1, and the rotating shaft of the motor 5 is connected with the scroll bar 6. The torsion spring 7 is fixed on the end cover 8 through a torsion spring shaft, and the end cover 8 is fixed at the tail part of the aircraft main body 1.

Aircraft main part 1 both sides are equipped with the notch, and motor antiport, main drive pole 2 rotate and accomodate in the notch to notch department, when need not expand, rely on the direction pulling force of torsional spring completely with flexible missile wing winding on the torsional spring axle, realize complete shrink. By the elastic rotation of the two torsion springs fixed to the end cover 8, the pair of the missile wings 3 can be completely wound around the torsion springs, so that the missile wings are completely retracted into the missile body.

In the aircraft flight process, receive and expand the missile wing instruction, then motor 5 begins the forward rotation, drives the vortex rod 6 motion rather than coaxial coupling, and vortex rod 6 further drives main drive pole 2 that has the turbine and rotates, and the 1 notch of main drive pole 2 aircraft main part expands, from the contained angle that changes main drive pole 2 and projectile axis, through the difference that changes the contained angle, realizes different missile wing shape changes. By changing the shape of the flexible missile wing, the aircraft can fly in an optimized aerodynamic layout under the conditions of different flying speeds and heights.

The mechanism can be used for bionic variable-wing flight of a variant aircraft, realizes the whole-course flight with the optimized appearance by changing the shape of the flexible missile wing in real time, has the characteristics of easy realization, light weight, small structural volume, small driving power and the like, can realize the complete contraction into the missile body, can also be completely unfolded, can be widely applied to various aircrafts needing the flexible variable wing, and is particularly suitable for the aircrafts with limited launching modes and missile body structures such as gun-launched guided projectiles, tube-launched guided rockets and the like. The bionic variable-wing mechanism is provided, so that the effective load and the flying efficiency of the variable aircraft can be greatly improved.

Claims

1. A flexible wing changing mechanism capable of being completely contracted is characterized by being assembled on an elastic body and comprising an aircraft main body, a main driving rod, a flexible skin, a driving part, a worm rod connected with the driving part, a torsion spring and an end cover;

the torsion spring is fixed on the end cover through a torsion spring shaft, and the end cover is fixed at the tail part of the aircraft main body; notches are formed in the two sides of the aircraft main body and used for accommodating the flexible skin and the main driving rod on the left side and the right side; when the flexible missile wing does not need to be unfolded, the flexible missile wing is wound on the torsion spring shaft by virtue of the tension of the torsion spring, so that complete contraction is realized.

2. The fully retractable flexible wing mechanism according to claim 1, wherein the flexible skin 3 is provided with a plurality of skeletons at intervals.

3. The fully retractable flexible wing-changing mechanism according to claim 1, wherein the driving part is two motors, and the main driving rods on the left and right sides are independently driven by one motor.

4. The fully retractable flexible wing varying mechanism according to claim 1, wherein the torsion spring shaft is coaxial with the opposing side scroll.