CN-122009472-A - Wheel-rail type variant telescopic wing structural design and dynamic simulation method

CN122009472ACN 122009472 ACN122009472 ACN 122009472ACN-122009472-A

Abstract

The application provides a wheel-rail type variant telescopic wing structural design and a dynamic simulation method, wherein the structural design comprises a base, fixed wings symmetrically arranged on the base, movable wings provided with running wheel sets, driving and transmission mechanism assemblies used for driving the movable wings to stretch and retract relative to the fixed wings, and the driving and transmission mechanism assemblies are connected with the movable wings, wherein the lifting force area is changed through the stretching of the movable wings relative to the fixed wings, so that the limitation of the traditional fixed-configuration wings is overcome, the display ratio and the lifting force area of the wings are changed, and the multi-working-condition adaptation capability of an aircraft is greatly improved.

Inventors

WU XINGWEN
LIANG SHULIN
YANG YIBO
HUANG HU
CHEN XIAOFENG
PU KEQIANG
SONG XIANZHE
Yang Ningrui
PENG BO
CHI MAORU

Assignees

西南交通大学

Dates

Publication Date: 20260512
Application Date: 20260413

Claims (8)

1. A wheeltrack type variant telescopic wing structural design, comprising: A base; The fixed wings are symmetrically arranged on the base; the movable wing is provided with a running wheel set, and the movable wing is used for moving along the fixed wing through the running wheel set; The driving and transmission mechanism assembly is used for driving the movable wing to stretch and retract relative to the fixed wing, and is connected with the movable wing; the lifting force area is changed by the extension and retraction of the movable wing relative to the fixed wing, so that the multi-working-condition adaptation capacity of the aircraft is improved.
2. The wheel-rail type variant telescopic wing structural design according to claim 1, wherein the fixed wing comprises T-shaped guide rails which are vertically opposite and are arranged at intervals, rail surfaces of the opposite T-shaped guide rails are arranged opposite, the rail surfaces are surfaces adjacent to protruding parts of the T-shaped guide rails, the running wheel set comprises running wheels which are vertically opposite, and the spacing of the running wheels which are vertically arranged is matched with the spacing of the rail surfaces which are oppositely arranged.
3. The wheel-rail variant telescopic wing structural design of claim 2, further comprising a limit mechanism comprising: the end limiting wheel set is arranged at the end part of the fixed wing far away from the base, and can slide along the longitudinal beam of the movable wing, so that when the movable wing is vertically deformed, the movable wing is prevented from being blocked or worn during expansion and contraction; The lateral limiting wheel set is arranged on the movable wing and used for limiting the lateral displacement of the movable wing; the vertical limiting wheels are arranged on the running wheel sets and used for limiting the vertical offset of the movable wings.
4. The wheel-rail type variant telescopic wing structural design according to claim 1, wherein the movable wing comprises a longitudinal beam arranged along the longitudinal direction and a wheel set mounting plate arranged along the longitudinal direction, the wheel set mounting plate is arranged in parallel with the longitudinal beam, and a plurality of mounting holes are formed in the wheel set mounting plate.
5. The wheel-rail type variable telescopic wing structural design according to claim 3, wherein the surface of the movable wing allowing the end limiting wheel set to slide is a movable wing rail surface, and the net size between the movable wing rail surface and the end limiting wheel set is A, and A is more than or equal to 0 and less than or equal to 2mm.
6. A dynamic simulation method for the structural design of a wheel-rail type variant telescopic wing is characterized by comprising the following steps: S1, constructing a three-dimensional geometric model of a wheel-rail type variant telescopic wing structure, and dividing grids of the three-dimensional geometric model to form a finite element model; S2, constructing a rigid-flexible coupling dynamic model, setting a fixed wing and a movable wing of the wheel-rail type variant telescopic wing structure as flexible bodies, setting other parts of the wheel-rail type variant telescopic wing structure as rigid bodies, introducing structural elasticity of the movable wing and the fixed wing through a modal synthesis method, and adopting a polygonal contact model to simulate nonlinear dynamic contact behaviors of a running wheel set and a T-shaped guide rail; S3, establishing a random vibration environment model based on virtual excitation, and simulating random vibration of the movable wing and the fixed wing through a PID control strategy; And S4, constructing a proportion model machine, carrying out calibration test, free mode test, static loading test, dynamic telescopic test and random vibration test on a running wheel set of the proportion model machine to obtain actual measurement data, comparing the actual measurement data with simulation data obtained in the steps S1-S3 to correct parameters of the rigid-flexible coupling dynamic model, wherein the calibration test is configured to carry out strain gauge pasting on the running wheel set, load by adopting stepped force and collect data, so as to complete calibration on the strain-load mapping relation of the running wheel set, the free mode test is configured to realize free boundary constraint on the proportion model machine by adopting an elastic suspension mode, the vibration response of the wheel-rail type variant telescopic wing structure is collected through vibration of an exciter, the natural frequency, the vibration mode and the damping ratio of the proportion model machine are obtained, the static loading test is configured to apply graded load to the end part of the movable wing, the static load transfer characteristic of the structure is obtained, the dynamic telescopic test is configured to drive the movable wing set to reciprocate under a set load condition, the dynamic telescopic wing structure is configured to apply dynamic displacement and random vibration power and vibration power is configured to collect dynamic vibration power and vibration power.
7. The dynamic simulation method of wheel-rail type variant telescopic wing structure design according to claim 6, wherein the three-dimensional geometric model is divided into areas and grids, a T-shaped guide rail, an end transverse plate of the fixed wing, a middle transverse plate of the movable wing and a longitudinal beam of the movable wing are divided into hexahedral units by using Solid185 units, and the rest parts of the wheel-rail type variant telescopic wing structure are divided into quadrilateral units by using Shell181 plate-Shell units.
8. The dynamic simulation method of wheel-rail type variant telescopic wing structural design according to claim 6, wherein the free mode test comprises a free mode test of the movable wing and a free mode test of the fixed wing to obtain a first tenth-order natural frequency, a vibration mode and a damping ratio of the proportionality model machine.

Description

Wheel-rail type variant telescopic wing structural design and dynamic simulation method Technical Field The application relates to the technical field of aircrafts, in particular to a wheel-rail type variant telescopic wing structural design and a dynamic simulation method. Background The aerospace field has increasingly stringent requirements on flight adaptability, mission suitability and maneuvering performance of aircrafts, diversified flight missions and complex flight environments, so that the limitations of the traditional fixed-configuration wing are increasingly prominent. The traditional fixed-configuration wing has fixed aerodynamic parameters such as aspect ratio, lifting area and the like, cannot be dynamically adjusted according to the flight working conditions, and cannot meet the multi-working-condition service requirements of modern aircrafts. Disclosure of Invention In view of the above, the application provides a wheel-rail type variant telescopic wing structural design, which overcomes the limitation of the traditional fixed-configuration wing, realizes the change of the display ratio and the lifting force area of the wing, and greatly improves the multi-working-condition adaptation capability of an aircraft. In addition, the application also provides a dynamic simulation method suitable for the structural design of the wheel-rail type variant telescopic wing. In order to achieve the above purpose, the present application provides the following technical solutions: a wheeltrack type variant telescopic wing structural design comprising: A base; The fixed wings are symmetrically arranged on the base; the movable wing is provided with a running wheel set, and the movable wing is used for moving along the fixed wing through the running wheel set; The driving and transmission mechanism assembly is used for driving the movable wing to stretch and retract relative to the fixed wing, and is connected with the movable wing; the lifting force area is changed by the extension and retraction of the movable wing relative to the fixed wing, so that the multi-working-condition adaptation capacity of the aircraft is improved. Optionally, in the design of the wheel-rail type variant telescopic wing structure, the fixed wing comprises T-shaped guide rails which are vertically opposite and arranged at intervals, rail surfaces of the T-shaped guide rails which are oppositely arranged are arranged opposite to each other, the rail surfaces are surfaces adjacent to protruding parts of the T-shaped guide rails, the running wheel set comprises running wheels which are vertically opposite arranged, and the space between the running wheels which are vertically arranged is matched with the space between the rail surfaces which are oppositely arranged. Optionally, in the design of the wheel-rail type variant telescopic wing structure, the telescopic wing further comprises a limiting mechanism, wherein the limiting mechanism comprises: the end limiting wheel set is arranged at the end part of the fixed wing far away from the base, and can slide along the longitudinal beam of the movable wing, so that when the movable wing is vertically deformed, the movable wing is prevented from being blocked or worn during expansion and contraction; The lateral limiting wheel set is arranged on the movable wing and used for limiting the lateral displacement of the movable wing; the vertical limiting wheels are arranged on the running wheel sets and used for limiting the vertical offset of the movable wings. Optionally, in the design of the wheel rail type variant telescopic wing structure, the movable wing comprises a longitudinal beam arranged longitudinally and a wheel set mounting plate arranged longitudinally, wherein the wheel set mounting plate is arranged in parallel with the longitudinal beam, and a plurality of mounting holes are formed in the wheel set mounting plate. Optionally, in the design of the wheel rail type variant telescopic wing structure, a surface of the movable wing allowing the end limiting wheel set to slide is a movable wing rail surface, and a net size between the movable wing rail surface and the end limiting wheel set is A, wherein A is more than or equal to 0 and less than or equal to 2mm. A dynamic simulation method for the structural design of a wheel-rail type variant telescopic wing comprises the following steps: S1, constructing a three-dimensional geometric model of a wheel-rail type variant telescopic wing structure, and dividing grids of the three-dimensional geometric model to form a finite element model; S2, constructing a rigid-flexible coupling dynamic model, setting a fixed wing and a movable wing of the wheel-rail type variant telescopic wing structure as flexible bodies, setting other parts of the wheel-rail type variant telescopic wing structure as rigid bodies, introducing structural elasticity of the movable wing and the fixed wing through a modal synthesis method, and adopting a pol