Variable-sweepback aircraft variant structure with inner and outer telescopic wings

Abstract

The invention discloses a variable sweepback aircraft variant structure with inner and outer telescopic wings. The variable sweepback aircraft variant structure comprises outer wings, a fuselage, a lead screw system, push rods, inner wings, push rod connecting pieces, graphite copper sleeves and upper and lower guide rails, wing accommodating grooves are formed in the two sides of the fuselage respectively and used for accommodating the outer wings and the inner wings; the inner wing is located in the outer wing and connected with the outer wing through a rotating pair, and rotating motion can be achieved. The inner and outer wings are provided with chutes with special tracks, one end of a push rod is connected with the chutes, the other end of the push rod is fixed with a sliding table of a ball screw through a connecting piece, and a motor drives the screw to rotate to realize symmetrical movement of the push rod, control of actions of the inner and outer wings and wing deformation. Through the design of the sliding grooves of the inner and outer wings, the push rods are connected with the inner and outer wings through the sliding grooves, a certain supporting effect is achieved, the length of the sliding grooves is increased, the change range of the sweepback angle can be increased, the constant-speed movement of the lead screws realizes constant-speed extension of the outer wings and constant-speed rotation of the inner wings through movement of the push rods along the sliding grooves, and the overall structural design is simple and ingenious and flexible and convenient to use.

Description

Technical Field

[0001] The invention belongs to the field of aerospace technology, and in particular relates to a variable-sweep inner and outer telescopic wing aircraft variant structure. Background Art

[0002] For hypersonic aircraft, the flight speed varies over a wide range, going through subsonic, transonic, supersonic and hypersonic stages. The optimal wing sweep angle is different in each stage. Current wing designs extend outward from the fuselage at a fixed angle, and are unable to improve the wing sweep angle as the flight environment changes. Since the wing needs to extend outward at a uniform speed, the design structure is complex and requires the coordination of multiple structures.

[0003] In order to overcome the shortcomings of the above-mentioned prior art, the purpose of the present invention is to provide a new type of variable-sweep telescopic wing aircraft variant solution, which completes the deployment and retraction of the outer wing and the inner wing through a screw system combined with a push rod slider mechanism; the slide is driven to move by the screw system to achieve a change in the sweep angle within a certain range. When the wing is fully unfolded, the outer wing has a certain connecting and supporting effect on the inner wing, thereby reducing the bending deformation amplitude of the inner wing.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is:

[0005] A variable-sweep inner and outer telescopic wing aircraft variant structure comprises an outer wing 1, a fuselage 2, a screw system 3, a push rod 4, an inner wing 5, a push rod connector 6, a graphite copper sleeve 7 and an upper and lower guide rail 8; wing storage grooves are respectively processed on both sides of the fuselage 2 to accommodate the outer wing 1 and the inner wing 5, the upper and lower guide rails 8 are installed on the upper and lower sides of the fuselage 2, the push rod 4 is connected to the push rod connector 6 by bolts, and the push rod connector 6 is connected to the slide on the screw system 3 to form a push rod slider structure, which is driven by the electric power of the screw system 3. The machine converts the rotational driving force into the translational motion of the push connector 6, and then through the push rod 4, along the special slide groove of the outer wing, the vertical translational motion of the slide of the screw system 3 is converted into the lateral motion of the outer wing 1 along the upper and lower guide rails 8, so as to realize the deployment and retraction of the outer wing 1; the inner wing 5 is located inside the outer wing 1, and is connected to the outer wing 1 through a revolute pair, so that the inner wing 5 can rotate relative to the outer wing 1. The graphite copper sleeve 7 is located at the connection between the push rod 4 and the slide grooves of the outer wing 1 and the inner wing 5, and rolls when the push rod 4 moves. The screw system 3 is a double-helix screw system.

[0006] The variable-sweep telescopic wing aircraft has two working postures: wing deployment posture and wing retraction posture. When the wing is deployed, the double-threaded screw system 3 drives the double-sided slides to gradually push toward the middle. Under the action of the push rod slider structure, the push rod 4 moves toward the middle along the outer wing 1 and inner wing 5 slide grooves. When it moves to the inflection point of the slide groove, the outer wing 1 reaches the maximum extension. It continues to move to the end point of the slide groove, and the inner wing 5 reaches the maximum opening angle. When the wing is retracted, the double-threaded screw system 3 drives the double-sided slides to gradually pull toward both sides, and the push rod 4 retracts the outer wing 1 and the inner wing 5 along the slide groove until they are completely retracted into the fuselage 2.

[0007] The graphite copper sleeve 7 is located at the connection between the push rod and the inner and outer wing slideways. Due to its high temperature resistance and self-lubrication characteristics, it reduces friction through rolling contact.

[0008] Compared with the prior art, the present invention uses the design of the slide grooves of the inner and outer wings, and the push rod is connected to the inner and outer wings through the slide grooves, which plays a certain supporting role. The length of the slide groove is increased, which can increase the range of the sweep angle. The uniform motion of the lead screw realizes the uniform extension of the outer wing and the uniform rotation of the inner wing through the push rod along the slide groove. The structural design is simple and ingenious, and it is flexible and convenient to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 This is a schematic diagram of the wing deployment posture of a variable-sweep retractable wing aircraft.

[0010] Figure 2 This is a schematic diagram of the wing retraction posture of a variable-sweep retractable wing aircraft.

[0011] Figure 3 It is a structural schematic diagram of the outer wing being extended to the maximum and the push rod being at the turning point of the slide slot.

[0012] Figure 4 It is a structural schematic diagram of the connection between the graphite copper sleeve, the push rod and the slide groove.

[0013] In the figure: 1. Outer wing; 2. Half of the fuselage; 3. Double helical screw system; 4. Push rod; 5. Inner wing; 6. Push rod connector; 7. Graphite copper sleeve; 8. Upper and lower guide rails. DETAILED DESCRIPTION

[0014] The specific implementation of the present invention is described in detail below with reference to the accompanying drawings and examples.

[0015] A variable-sweep inner and outer telescopic wing aircraft variant structure, comprising an outer wing 1, a fuselage 2, a screw system 3, a push rod 4, an inner wing 5, a push rod connector 6, a graphite copper sleeve 7 and upper and lower guide rails 8; both sides of the fuselage 2 are respectively processed with wing storage grooves for accommodating the outer wing 1 and the inner wing 5;

[0016] The upper and lower guide rails 8 are installed on the upper and lower sides of the fuselage 2; the push rod 4 is connected to the push rod connector 6 by bolts, and the push rod connector 6 is connected to the slide on the screw system 3 to form a push rod slider structure, and the motor of the screw system 3 converts the rotational driving force into the translational movement of the push connector 6, and then the push rod 4 moves along the special slide groove of the outer wing to convert the vertical translational movement of the slide of the screw system 3 into the lateral movement of the outer wing 1 along the upper and lower guide rails 8, so as to realize the opening and retraction of the outer wing 1; the inner wing 5 is located inside the outer wing 1, and is connected to the outer wing 1 through a revolute pair to realize the rotation of the inner wing 5 relative to the outer wing 1, and the graphite copper sleeve 7 is located at the connection between the push rod 4 and the slide grooves of the outer wing 1 and the inner wing 5, and performs rolling motion when the push rod 4 moves;

[0017] The special slide groove refers to the inner wing 5 and the outer wing 1 making a translational movement outward along the upper and lower guide rails 8, while the push rod 4 makes a linear movement downward; since the two tracks of the guide rail 8 and the push rod 4 are in a vertical state, in order to reduce wear, the special slide groove track begins to tilt at a certain angle, and when the outer wing 1 translates to the maximum position, the graphite copper sleeve 7 on the push rod 4 moves to the inflection point of the special slide groove of the outer wing 1, and the special slide grooves on the inner wing 5 and the outer wing 1 coincide with each other at this time; after reaching the inflection point, the outer wing 1 does not move, and the special slide groove of the outer wing 1 after the inflection point is consistent with the movement direction of the push rod 4. Since the special slide groove of the inner wing 5 is inclined, under the action of the push rod 4, it rotates around the rotation point on the outer wing 1 as the axis, thereby realizing the unfolding of the inner wing 5; the special slide grooves on the outer wing 1 are symmetrically arranged to increase the structural rigidity.

[0018] The variable sweep wing has two working postures: a wing-extended posture and a wing-retracted posture.

[0019] The outer wing 1 is provided with a special slide groove. When the push rod 4 is driven by the screw system to reciprocate vertically at a uniform speed, the outer wing 1 can move horizontally along the upper and lower guide rails at a uniform speed. The starting point and turning point of the special slide groove correspond to the fully retracted state and the fully extended state of the outer wing 1.

[0020] The inner wing 5 is provided with a special slide groove. When the push rod 4 reciprocates in a straight line, the inner wing 5 first performs translational motion with the outer wing 1, and then realizes uniform rotational motion. The starting point and the end point of the special slide groove correspond to the fully retracted state and the fully extended state of the inner wing 5; the slide groove trajectories on the inner wing 5 and the outer wing 1 are determined by their motion forms.

[0021] The outer wing 1 and the inner wing 5 cooperate with each other through a revolving pair and a slide groove, and the push rod 4 is driven by the double-helical screw system 3 to push the outer wing 1 and the inner wing 5 to move in translation and rotation along the slide groove, thereby realizing the unfolding and retracting action of the entire wing.

[0022] like Figure 1As shown, the wings are fully deployed. At this time, the push rod 4 is at the end of the slide grooves on the outer wing 1 and the inner wing 5. Under the action of the push rod slider structure, the outer wing 1 reaches the maximum translation, the inner wing 5 reaches the maximum deployment angle, and the double-threaded screw system 3 reaches the maximum travel point.

[0023] like Figure 2 The figure shows the wing fully retracted posture, at this time, the inner wing 5 is completely retracted into the outer wing 1 through the rotating pair, the outer wing 1 is completely retracted into the outer shell of the fuselage 2, the push rod 4 reaches the starting point of the inner wing 5 and the outer wing 1 slide groove, and the double-thread screw system 3 is at the starting end.

[0024] like Figure 3 The figure shows the process of the wing extending outward. At this time, the push rod 4 is located at the inflection point of the slide grooves on the outer wing 1 and the inner wing 5. The outer wing 1 reaches the maximum translation along the upper and lower guide rails 8, and the inner wing 5 begins to rotate outward at a uniform speed step by step through the revolute pair.

[0025] like Figure 4 As shown, the graphite copper sleeve 7 is sleeved on the long round nut between the upper and lower push rods 4. When the push rods 4 push the outer wing 1 and the inner wing 5 to move, they perform rolling motion to reduce friction.

[0026] The variable-sweep inner and outer telescopic wing aircraft of the present invention has two working postures: posture one, the motor rotates forward and the push rod pushes symmetrically toward the middle along the inner and outer wing slide grooves, so that the outer wing is translated outward along the guide rail, and when the translation reaches the maximum position, the inner wing starts to rotate, and the sweep angle reaches the maximum, realizing the maximum deformation posture, and the wing is fully unfolded; posture two, the motor reverses and the push rod moves oppositely along the slide groove, so that the inner wing first rotates to the state where the sweep angle reaches the minimum, and then the outer wing is translated inward along the guide rail, and the wing is completely retracted into the fuselage, completing the wing retraction.

Claims

1. A variable-sweep inner and outer retractable wing aircraft variant structure, characterized in that: It comprises an outer wing (1), a fuselage (2), a screw system (3), a push rod (4), an inner wing (5), a push rod connecting piece (6), a graphite copper sleeve (7) and upper and lower guide rails (8); both sides of the fuselage (2) are respectively processed with wing storage grooves for accommodating the outer wing (1) and the inner wing (5); The upper and lower guide rails (8) are installed on the upper and lower sides of the fuselage (2); the push rod (4) is connected to the push rod connecting member (6) by bolts, and the push rod connecting member (6) is connected to the slide on the screw system (3) to form a push rod slider structure, and the motor of the screw system (3) converts the rotational driving force into a translational motion of the push rod connecting member (6), and then the push rod (4) moves along the special slide groove of the outer wing, so as to convert the vertical translational motion of the slide of the screw system (3) into a lateral motion of the outer wing (1) along the upper and lower guide rails (8), thereby realizing the opening and retraction of the outer wing (1); the inner wing (5) is located inside the outer wing (1), and is connected to the outer wing (1) by a revolving pair, so that the inner wing (5) can rotate relative to the outer wing (1); the graphite copper sleeve (7) is located at the connection between the push rod (4) and the slide grooves of the outer wing (1) and the inner wing (5), and performs rolling motion when the push rod (4) moves; The special slide groove refers to the inner wing (5) and the outer wing (1) moving outward along the upper and lower guide rails (8) together, while the push rod (4) moves linearly downward; since the upper and lower guide rails (8) and the push rod (4) are in a vertical state, in order to reduce wear, the special slide groove track begins to tilt at a certain angle. When the outer wing (1) moves to the maximum position, the graphite copper sleeve (7) on the push rod (4) moves to the turning point of the special slide groove of the outer wing (1), and the special slide grooves on the inner wing (5) and the outer wing (1) overlap at this time; after reaching the turning point, the outer wing (1) does not move, and the special slide groove of the outer wing (1) after the turning point is consistent with the movement direction of the push rod (4). Since the special slide groove of the inner wing (5) is tilted, under the action of the push rod (4), it rotates around the rotation point on the outer wing (1) as the axis, so that the inner wing (5) is unfolded; the special slide grooves on the outer wing (1) are symmetrically arranged to increase the structural rigidity.

2. The variable-sweep retractable-wing aircraft variant structure according to claim 1, characterized in that: The variable sweep wing has two working postures: a wing-extended posture and a wing-retracted posture.

3. The variable-sweep retractable-wing aircraft variant structure according to claim 1 or 2, characterized in that: The outer wing (1) is provided with a special slide groove. When the push rod (4) is driven by the screw system to reciprocate vertically at a uniform speed, the outer wing (1) can move horizontally along the upper and lower guide rails at a uniform speed. The starting point and turning point of the special slide groove correspond to the fully retracted state and the fully extended state of the outer wing (1).

4. The variable-sweep retractable-wing aircraft variant structure according to claim 1 or 2, characterized in that: The inner wing (5) is provided with a special slide groove. When the push rod (4) moves back and forth in a straight line, the inner wing (5) first moves in translation with the outer wing (1), and then realizes uniform rotation. The starting point and the end point of the special slide groove correspond to the fully retracted state and the fully extended state of the inner wing (5). The slide groove tracks on the inner wing (5) and the outer wing (1) are determined by their movement forms.

5. The variable-sweep retractable-wing aircraft variant structure according to claim 1 or 2, characterized in that: The outer wing (1) and the inner wing (5) cooperate with each other through a rotating pair and a slide groove, and the push rod (4) is driven by the screw system (3) to push the outer wing (1) and the inner wing (5) along the slide groove to perform translational and rotational movements, thereby realizing the unfolding and retracting movements of the entire wing.

6. The variable-sweep retractable-wing aircraft variant structure according to claim 1 or 2, characterized in that: The lead screw system (3) is a double-helix lead screw system; the variable-sweep telescopic wing aircraft has two working postures: a wing deployment posture and a wing retracting posture; when the wing is in the wing deployment posture, the lead screw system (3) drives the double-sided slides to gradually push toward the middle, and under the action of the push rod slider structure, the push rod (4) moves toward the middle along the outer wing (1) and the inner wing (5) slide grooves, and when it moves to the inflection point of the slide groove, the outer wing (1) reaches the maximum extension amount, and continues to move to the end point of the slide groove, and the inner wing (5) reaches the maximum opening angle; when the wing is in the wing retracting posture, the lead screw system (3) drives the double-sided slides to gradually pull toward both sides, and the push rod (4) retracts the outer wing (1) and the inner wing (5) along the slide groove until they are completely retracted into the fuselage (2).

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