CN110979682A

CN110979682A - Variable-area duck-type forward-swept wing variant aircraft

Info

Publication number: CN110979682A
Application number: CN201911393296.7A
Authority: CN
Inventors: 刘双喜; 闫斌斌; 戴沛; 尹英明; 张鸿林; 曾诚之; 张添钧
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2019-12-30
Filing date: 2019-12-30
Publication date: 2020-04-10

Abstract

The invention discloses a variable-area duck-type forward swept wing variant aircraft, which adopts a duck-type layout, wherein the plane shape of a wing surface is quadrilateral, and when the wing is completely retracted, the wing and the duck wing are jointed into a triangular wing. The head of the machine body is provided with a duck wing; wings on two sides of the tail part of the fuselage can be synchronously folded and attached to the inner fuselage side forward or unfolded to the outer side backward around the wing body connecting rotating shaft; when the wings are folded forwards, the wings are gradually folded forwards to reduce the sweepforward angle, the wings are completely attached to the fuselage, and the whole aircraft is in a curved streamline aerodynamic shape. When the wings are completely unfolded into forward swept wings, the wingspan of the aircraft is greatly increased, so that the aircraft can ensure larger lift force. The double vertical tails are symmetrically arranged at the upper rear part of the fuselage, the lifting ailerons are arranged at the rear end of the fuselage and are positioned at the rear parts of the two vertical tails, and the air inlet channel is positioned below the fuselage. Through the reasonable matching of the variable-area duck-type forward swept wing variants, the aircraft has smaller flight resistance when the wings are in the unfolded and folded states; the flight flexibility of the aircraft is improved.

Description

Variable-area duck-type forward-swept wing variant aircraft

Technical Field

The invention relates to the technical field of airplane design, in particular to a variable-area canard forward-swept wing variant aircraft.

Background

The shape of the variant aircraft is changed in flight to adapt to different flight states, all performances are considered, the comprehensive flight performance of the existing aircraft can be effectively improved, and the variant aircraft has a great development prospect. The overall deformation of the aircraft is difficult to realize, but within a bearable range, the improvement of the performance of the aircraft by utilizing local deformation is completely feasible. Such as Mige-23 of the former Soviet Union, F-14 of the United states, and a variable sweepback airplane such as a fierce fighter developed together in British, Germany and Italy, can have both high and low speed performance. However, because the structural weight is larger than that of the same aircraft type at the same time, and the deformation mechanism is more complex, the subsequent research and development of the sweep-wing aircraft are basically abandoned in all the countries, and a large amount of manpower and material resources are invested to search for a new aircraft deformation mode. While the preliminary work was done, several variant techniques have been successfully applied to the validator. Such as the hummingbird micro ornithopter developed by the united states space environment corporation and the tilted rotor wing aircraft osprey helicopter designed and manufactured by the united states bell and boeing corporation.

In the literature, "simulation study of unsteady aerodynamic characteristics of variable airfoil profile of a morphing aircraft" ("computer simulation", 2015.10. wangxhi "), the unsteady aerodynamic characteristics of the variable airfoil profile are studied to provide a useful reference for aerodynamic layout design and dynamics analysis of the morphing aircraft, but the lack of strength verification results in poor practicability and poor innovation. And the traditional fixed-wing aircraft cannot meet the performance requirements in all aspects under different flight states.

The variable-area canard forward-swept wing variant aircraft is designed, and aims to solve the problem that the fixed-wing aircraft cannot meet performance requirements of various aspects in different flight states. The design of the variable-area canard forward-swept wing variant aircraft can ensure that the aircraft keeps good aerodynamic characteristics in a full-speed domain, gives consideration to low-speed cruising and high-speed penetration attack, and better adapts to the change of a future complex battlefield.

Disclosure of Invention

In order to avoid the defects in the prior art, the invention provides a variable-area duck-type forward-swept wing variant aircraft; the forward swept wing variant aircraft adopts a duck-type layout, and the wings are completely unfolded into forward swept wings at low speed, so that larger lift force is ensured; the variable-area duck-type forward-swept wing variant aircraft adopts a duck-type layout variable-forward-swept wing delta wing configuration design, so that the overall streamline aerodynamic shape of the aircraft can be ensured; and to ensure that the aircraft maintains good aerodynamic characteristics at full speed.

The invention solves the technical problem by adopting the technical scheme that the wing-shaped airplane wing assembly comprises a fuselage, a V-shaped vertical tail, wings, duck wings, a stud and a connecting rod, and is characterized in that a duck-type layout is adopted, the integral change range of a front edge sweepforward angle is 56.625-90 degrees, the plane shape of a wing surface is quadrilateral, and when the wings are retracted, the wings and the duck wings are combined to form a triangular wing; symmetrical canard wings are arranged at the head of the fuselage, wings on two sides of the tail of the fuselage can be synchronously folded and attached to the inner fuselage side forward or unfolded to the outer side backward around a wing body connecting rotating shaft, the V-shaped double vertical tails are symmetrically arranged on the upper rear part of the fuselage, the lifting ailerons are arranged at the rear end of the fuselage and positioned on the rear parts of the two vertical tails, and the air inlet channel is positioned below the fuselage;

when the wings are completely unfolded, the aircraft is in a forward-swept canard layout, the forward sweep angle is 26.625 degrees, the full span is 15.8m, and the aspect ratio is 8; the wings are folded forwards to reduce the sweepforward angle until the wings are completely folded, the aircraft is in a tailless delta wing layout, the wingspan is 9.2m, and the aspect ratio is reduced to 2.2; the design method comprises the following steps:

step 1, determining basic data of the shape of the morphing aircraft, establishing a coordinate system by using CATIA software, determining intersection points of each design plane and a straight line, and establishing a frame model of the aircraft according to design parameters through filling, bridging, stretching and symmetry; designing the body appearance of the aircraft, drawing the control surface layout of wings, canard wings and empennages, and drawing the position of an engine;

step 2, designing the integral curve of the machine head into a streamline form, gradually widening the machine body from front to back, and reserving a design gap between the middle and rear sections and the upper and lower machine bodies; ensuring that the upper and lower points of the wing profile trailing edge are superposed with the intersection point of the design plane and the straight line, and drawing and designing the wing profile torsion angle;

and 3, the deformation mechanism is connected with the connecting rod by adopting a stud, the stud drives the connecting rod to pull the wing to move, and the root of the wing is provided with a rotating shaft so that the wing can rotate around the rotating shaft, so that the variable-area sweepforward angle is realized.

Advantageous effects

The invention provides a variable-area duck-type forward swept wing variant aircraft which adopts a duck-type layout, wherein the plane shape of a wing surface is quadrilateral, and when the wing is completely retracted, the wing and the duck wing are connected to form a triangular wing. The head of fuselage is provided with a pair of duck wing, and fuselage afterbody both sides wing can be connected the pivot around the wing body and fold the laminating to interior fuselage side in the synchronous forward direction, or expand backward to the outside, and the two vertical tails of V type are located the fuselage upper rear portion symmetry and set up, and the lift aileron is installed and is located two vertical tail rear portions at the fuselage rear end, and the intake duct is located the fuselage below.

Wings on two sides of the variable-area duck-type forward-swept wing variant aircraft can be synchronously folded and attached to the inner fuselage side forwards or unfolded outwards and backwards; when the wings are folded forwards, the wings are gradually folded forwards to reduce the sweepforward angle, the wings are completely attached to the fuselage, and the whole aircraft is in a curved streamline aerodynamic shape. When the wing is completely unfolded into a forward swept wing, the wingspan of the aircraft is greatly increased, so that the aircraft has larger lift force.

Through the reasonable matching of the variable-area duck-type forward swept wing variant, the aircraft has high maneuverability and high cruising economic performance. By optimizing the wing body joint, the aircraft has smaller flight resistance in the unfolding state and the folding state of the wing. The flight flexibility of the aircraft is improved.

Drawings

The invention relates to a variable-area canard forward-swept wing variant aircraft, which is further described in detail with reference to the accompanying drawings and an embodiment.

FIG. 1 is a schematic view of a wing of the variable-area canard forward-swept wing morphing aircraft during unfolding.

FIG. 2 is a schematic view of a variable-area canard forward-swept wing morphing aircraft with the wings folded.

Fig. 3 is a schematic diagram of a deformation mechanism of the variable-area canard forward-swept wing variant aircraft.

In the drawings

V-shaped vertical fin 2, wing 3, duck wing

Detailed Description

The embodiment is a variable-area canard forward-swept wing variant aircraft.

Referring to fig. 1, 2 and 3, the variable-area canard forward swept wing variant aircraft of the present embodiment is composed of an airframe, a V-shaped vertical tail 1, wings 2, canard wings 3, a stud and a connecting rod; the wing adopts a duck-type layout, the integral change range of the forward sweep angle of the leading edge is 56.625-90 degrees, the plane shape of the wing surface is quadrilateral, and when the wing is completely retracted, the wing and the duck wing are jointed to form a delta wing. Wherein, the head of the fuselage is provided with a pair of duck wings 3, the wings at both sides of the tail of the fuselage can be synchronously folded and attached to the inner fuselage side forward or unfolded to the outside and back around the wing body connecting rotating shaft; the V-shaped double vertical tails are symmetrically arranged at the upper rear part of the fuselage, the lifting ailerons are arranged at the rear end of the fuselage and positioned at the rear parts of the two vertical tails, and the air inlet channel is positioned below the fuselage.

When the wings are completely unfolded, the wings of the aircraft are unfolded to be in a forward-swept canard layout, the forward sweep angle is 26.625 degrees, the full span is 15.8m, and the aspect ratio is 8; the wings are folded forwards to reduce the sweepforward angle until the wings are completely folded, the aircraft is in a tailless delta wing layout, the wingspan is 9.2m, and the aspect ratio is reduced to 2.2.

The design method of the embodiment comprises the following steps:

step 1, determining basic data of the shape of the morphing aircraft, establishing a coordinate system by using CATIA software, determining intersection points of each design plane and a straight line, and establishing a frame model of the aircraft according to design parameters through filling, bridging, stretching and symmetry; the body appearance of the airplane is designed, the control surface layout of wings, canard wings and empennages is drawn, and the position of an engine is planned. The wing unfolding and folding mechanism is realized by utilizing a rotating function.

The main design parameters are as follows:

step 2, designing the integral curve of the machine head into a streamline form, gradually widening the machine body from front to back, and leaving a design gap between the middle and rear sections and the upper and lower machine bodies to provide a space for the fusion of the wings and the machine body when the wings rotate and are completely retracted; ensuring that the upper and lower points of the wing profile trailing edge are superposed with the intersection point of the design plane and the straight line, and drawing and designing the wing profile torsion angle;

and 3, the deformation mechanism adopts the design of the connection of a stud and a connecting rod, a driving motor is arranged in the center of the fuselage to enable the central stud to rotate, a threaded shaft sleeve is arranged on the stud, the shaft sleeve is connected with the connecting rod through a gear rotating mechanism, the connecting rod is connected with the wing, the shaft sleeve can move back and forth along with the rotation of the stud so as to drive the connecting rod to pull the wing to move, and a rotating shaft is arranged at the root of the wing so that the wing can rotate around the rotating shaft to realize forward sweep angle variation.

In the embodiment, after the wings of the aircraft are unfolded, the resistance of the aircraft is increased by a small value, but the lift-drag ratio of the aircraft is greatly improved, the cruising economy of the aircraft is improved, and the aircraft is more suitable for actual task needs. The aircraft is completely attached to the fuselage before the wings are unfolded, so that the streamline aerodynamic shape of the whole aircraft is ensured; after the wings are unfolded, the fuselage and the split sections of the wings still ensure that the fuselage is a streamline lifting body, namely the resistance change of the two states of unfolding and folding of the wings is very small.

Claims

1. A variable-area duck-type forward-swept wing variant aircraft comprises an aircraft body, a V-shaped vertical tail, wings, duck wings, studs and connecting rods, and is characterized in that a duck-type layout is adopted, the forward-swept angle variation range of a front edge is 56.625-90 degrees, the plane shape of a wing surface is quadrilateral, and the wings and the duck wings are combined to form triangular wings when the wings are retracted; symmetrical canard wings are arranged at the head of the fuselage, wings on two sides of the tail of the fuselage can be synchronously folded and attached to the inner fuselage side forward or unfolded to the outer side backward around a wing body connecting rotating shaft, the V-shaped double vertical tails are symmetrically arranged on the upper rear part of the fuselage, the lifting ailerons are arranged at the rear end of the fuselage and positioned on the rear parts of the two vertical tails, and the air inlet channel is positioned below the fuselage; when the wings are completely unfolded, the aircraft is in a forward-swept canard layout, the forward sweep angle is 26.625 degrees, the full span is 15.8m, and the aspect ratio is 8; the wings are folded forwards to reduce the sweepforward angle until the wings are completely folded, the aircraft is in a tailless delta wing layout, the wingspan is 9.2m, and the aspect ratio is reduced to 2.2; the design method comprises the following steps: