Variable sweep inboard and outboard telescoping wing aircraft variable configuration

Abstract

The application discloses a variable sweep in-out telescopic wing aircraft variable structure, which comprises an outer wing, a fuselage, a screw system, a push rod, an inner wing, a push rod connecting piece, a graphite copper sleeve and upper and lower guide rails; wing storage grooves are formed on the two sides of the fuselage respectively and used for accommodating the outer wing and the inner wing; the inner wing is located inside the outer wing and connected with the outer wing through a rotating pair to realize rotating movement; the inner and outer wings are designed with special trajectory sliding grooves, one end of the push rod is connected with the sliding grooves, the other end is fixed with a sliding table of a ball screw through a connecting piece, a motor drives the screw to rotate, realizes the symmetrical movement of the push rod, controls the movement of the inner and outer wings and realizes the deformation of the wings. Through the design of the sliding grooves of the inner and outer wings, the push rod is connected with the inner and outer wings through the sliding grooves and plays a certain supporting role; the length of the sliding grooves is increased, the change range of the sweep angle is increased, the uniform movement of the screw is realized through the movement of the push rod along the sliding grooves, the outer wing is uniformly extended and the inner wing is uniformly rotated, the overall structure is simple and ingenious and is flexible and convenient to use.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace, and particularly relates to a variable rear-swept inner and outer retractable wing aircraft variable structure. BACKGROUND

[0002] For a hypersonic aircraft, the flight speed changes in a large range, and experiences subsonic speed, transonic speed, supersonic speed and hypersonic speed, and the optimal rear-swept angle of the wing in each stage is different. The current wing design is to extend outward from the fuselage at a fixed angle, and cannot improve the rear-swept angle of the wing along with the change of the flight environment. Since the speed of the wing extending outward is uniform, the design structure is complex, and multiple structures need to be matched.

[0003] In order to overcome the defects of the prior art, the purpose of the application is to provide a new variable rear-swept retractable wing aircraft variable structure. The outer wing and the inner wing are unfolded and retracted through a screw system combined with a push rod and a sliding block mechanism. The rear-swept angle is changed within a certain range through the movement of a sliding table driven by the screw system. When the wing is completely unfolded, the outer wing has a certain connecting support effect on the inner wing, and the bending deformation amplitude of the inner wing is reduced.

[0004] In order to achieve the above purpose, the technical scheme adopted by the application is:

[0005] A variable rear-swept inner and outer retractable wing aircraft variable structure, comprising 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. The fuselage 2 is provided with wing storage grooves on both sides 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 with the push rod connecting piece 6 through bolts. The push rod connecting piece 6 is connected with a sliding table on the screw system 3 to form a push rod and sliding block structure. The rotating driving force of the motor of the screw system 3 is converted into the translational motion of the connecting piece 6, and then the push rod 4 moves along the special sliding groove of the outer wing, so that the vertical translational motion of the sliding table of the screw system 3 is converted into the transverse motion of the outer wing 1 along the upper and lower guide rails 8, thereby realizing the unfolding and retraction of the outer wing 1. The inner wing 5 is located inside the outer wing 1 and is connected with the outer wing 1 through a rotating pair, so that the inner wing 5 can rotate relative to the outer wing 1. The graphite copper sleeve 7 is located at the sliding groove connection between the push rod 4 and the outer wing 1 and the inner wing 5, and rolls when the push rod 4 moves. The screw system 3 is a double-screw screw system.

[0006] The variable sweep stretch wing aircraft has two working postures: wing expansion posture and wing retraction posture. In the wing expansion posture, the double-threaded screw system 3 drives the double-sided sliding table to gradually push to the middle, under the action of the push rod sliding block structure, the push rod 4 moves to the middle along the sliding groove of the outer wing 1 and the inner wing 5, when moving to the inflection point of the sliding groove, the outer wing 1 reaches the maximum extension, and when moving to the end point of the sliding groove, the inner wing 5 reaches the maximum opening angle; in the wing retraction posture, the double-threaded screw system 3 drives the double-sided sliding table to gradually pull to the two sides, the push rod 4 retracts the outer wing 1 and the inner wing 5 along the sliding groove, and the wings are completely retracted into the fuselage 2.

[0007] The graphite copper sleeve 7 is located at the connection between the push rod and the sliding groove of the inner and outer wings, and due to the characteristics of high temperature resistance and self-lubrication, the friction is reduced through rolling contact.

[0008] Compared with the prior art, through the design of the sliding groove of the inner and outer wings, the push rod is connected with the inner and outer wings through the sliding groove, plays a certain supporting role, the length of the sliding groove is increased, the change range of the sweep angle is increased, the uniform motion of the screw rod is realized through the motion of the push rod along the sliding groove, and the outer wing is uniformly stretched out and the inner wing is uniformly rotated. The structure design is simple and ingenious, and the use is flexible and convenient. BRIEF DESCRIPTION OF DRAWINGS

[0009] Figure 1 It is a wing expansion posture schematic view of a variable sweep stretch wing aircraft.

[0010] Figure 2 It is a wing retraction posture schematic view of a variable sweep stretch wing aircraft.

[0011] Figure 3 It is a structure schematic view of the maximum extension of the outer wing and the inflection point of the push rod in the sliding groove.

[0012] Figure 4 It is a structure schematic view of the graphite copper sleeve connected with the push rod and the sliding groove.

[0013] In the figure: 1, outer wing; 2, half of the fuselage; 3, double-threaded screw system; 4, push rod; 5, inner wing; 6, push rod connecting piece; 7, graphite copper sleeve; 8, upper and lower guide rails. DETAILED DESCRIPTION

[0014] The specific embodiment of the present application will be described in detail below in combination with the drawings and examples.

[0015] A variable sweep inner and outer stretch wing aircraft variable structure, comprising 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; the fuselage 2 is respectively machined with wing storage grooves on both sides, 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 with the push rod connecting piece 6 through bolts, the push rod connecting piece 6 is connected with the sliding table on the screw system 3, and the push rod sliding block structure is formed, the rotating driving force of the motor of the screw system 3 is converted into the translational motion of the push rod connecting piece 6, then the push rod 4 moves along the special sliding groove of the outer wing, the vertical translational motion of the sliding table of the screw system 3 is converted into the transverse motion of the outer wing 1 along the upper and lower guide rails 8, so that the opening and retraction of the outer wing 1 are realized; the inner wing 5 is located in the inner wing 1, is connected with the outer wing 1 through a rotating pair, and realizes the rotation of the inner wing 5 relative to the outer wing 1; the graphite copper sleeve 7 is located at the sliding groove connection position of the push rod 4, the outer wing 1 and the inner wing 5, and rolls when the push rod 4 moves;

[0017] The special sliding groove refers to that the inner wing 5 and the outer wing 1 move together along the upper and lower guide rails 8 to move outward, and the push rod 4 moves downward in a straight line; 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 sliding groove track starts to be inclined at a certain angle, when the outer wing 1 is translated to the maximum position, the graphite copper sleeve 7 on the push rod 4 moves to the inflection point of the special sliding groove of the outer wing 1, and the special sliding grooves on the inner wing 5 and the outer wing 1 coincide at this time; after reaching the inflection point, the outer wing 1 does not move, the special sliding groove of the outer wing 1 after the inflection point is consistent with the movement direction of the push rod 4, and since the special sliding groove of the inner wing 5 is inclined, under the action of the push rod 4, the outer wing 1 rotates around the rotating point on the outer wing 1, and the inner wing 5 is unfolded; the special sliding 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 unfolding posture and a wing retraction posture.

[0019] The outer wing 1 is provided with a special sliding groove, when the push rod 4 is driven by the screw system to move vertically and reciprocally at a constant speed, the outer wing 1 moves transversely along the upper and lower guide rails at a constant speed, and the starting point and the inflection point of the special sliding groove correspond to the completely retracted state and the completely unfolded state of the outer wing 1.

[0020] The inner wing 5 is provided with a special sliding groove, when the push rod 4 moves linearly and reciprocally, the inner wing 5 first moves translationally with the outer wing 1, and then rotates at a constant speed, and the starting point and the end point of the special sliding groove correspond to the completely retracted state and the completely unfolded state of the inner wing 5; the sliding groove tracks on the inner wing 5 and the outer wing 1 are determined by the motion forms.

[0021] The outer wing 1 and the inner wing 5 are connected through a rotating pair and a sliding groove, the push rod 4 is driven by the double screw screw system 3, and moves the outer wing 1 and the inner wing 5 to move translationally and rotationally along the sliding groove, so that the unfolding and retraction of the whole wing are realized.

[0022] As Figure 1As shown, the fully wing fully deployed attitude, when the push rod 4 in the outer wing 1 and the inner wing 5 on the end of the sliding groove, under the action of push rod slider structure, the outer wing 1 reaches the maximum translation, the inner wing 5 reaches the maximum angle of expansion, double threaded screw system 3 reaches the maximum stroke point.

[0023] As shown in the figure, Figure 2 As shown, the wing fully retracted attitude, at this time, the inner wing 5 is completely retracted into the outer wing 1 through the rotating vice, the outer wing 1 is completely retracted into the fuselage 2 shell, the push rod 4 reaches the starting point of the inner wing 5 and the outer wing 1 sliding groove, and the double threaded screw system 3 is at the starting end.

[0024] As shown in the figure, Figure 3 As shown, the wing extends outward, at this time, the push rod 4 is located at the inflection point of the sliding groove of the outer wing 1 and the inner wing 5, the outer wing 1 reaches the maximum translation along the up and down guide rail 8, and the inner wing 5 starts to rotate outward at a uniform speed through the rotating vice.

[0025] As shown in the figure, Figure 4 As shown in the figure, the graphite copper sleeve 7 is sleeved on the circular long nut between the two push rods 4, when the push rod 4 pushes the outer wing 1 and the inner wing 5 to move, it makes rolling motion to reduce friction.

[0026] The variable sweep in-out telescopic wing aircraft has two working attitudes: attitude one, the motor pushes the push rod symmetrically to the middle along the inner and outer wing sliding groove, realizes the translation of the outer wing along the guide rail outward, and the inner wing starts to rotate, the sweep angle reaches the maximum, realizes the maximum attitude of deformation, and the wing is fully deployed; attitude two, the motor reverses the push rod to move in the opposite direction, realizes that the inner wing rotates to the minimum state first, and then the outer wing translates inward along the guide rail, the wing is completely retracted into the fuselage, and the wing retraction is completed.

Claims

1. A variable-sweep inward / outward telescopic wing aircraft variant structure, characterized in that, It includes an outer wing (1), a fuselage (2), a lead 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); the fuselage (2) has wing storage slots on both sides 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 table on the screw system (3) to form a push rod slider structure. The motor of the screw system (3) converts the rotational driving force into the translational motion of the connector (6), and then the push rod (4) moves along the special slide groove of the outer wing, converting the vertical translational motion of the slide table of the screw system (3) into the 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) through a rotary joint, 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 groove of the outer wing (1) and the inner wing (5), and rolls when the push rod (4) moves; The special groove refers to the movement of the inner wing (5) and outer wing (1) together along the upper and lower guide rails (8) to translate outwards, while the push rod (4) moves downwards in a straight line. Since the upper and lower guide rails (8) and the push rod (4) are perpendicular, the special groove trajectory starts to tilt at a certain angle to reduce wear. When the outer wing (1) is translated to the maximum position, the graphite copper sleeve (7) on the push rod (4) moves to the inflection point of the special groove on the outer wing (1), and the special grooves on the inner wing (5) and the outer wing (1) coincide at this time. After reaching the inflection point, the outer wing (1) does not move, and the special groove of the outer wing (1) after the inflection point moves in the same direction as the push rod (4). Since the special groove of the inner wing (5) is tilted, it rotates on the rotation point on the outer wing (1) as an axis under the action of the push rod (4), so that the inner wing (5) unfolds. The special grooves on the outer wing (1) are symmetrically arranged to increase the structural rigidity.

2. The variable-sweep telescopic wing aircraft variant structure according to claim 1, characterized in that, The variable-sweep wing has two operating attitudes: wing deployed and wing retracted.

3. The variable-sweep telescopic wing aircraft variant structure according to claim 1 or 2, characterized in that, The outer wing (1) has a special groove. When the push rod (4) is driven by the screw system to move vertically and uniformly back and forth, the outer wing (1) moves horizontally along the upper and lower guide rails at a uniform speed. The starting point and the inflection point of the special groove correspond to the fully retracted state and the fully deployed state of the outer wing (1).

4. The variable-sweep telescopic wing aircraft variant structure according to claim 1 or 2, characterized in that, The inner wing (5) has a special groove. When the push rod (4) moves in a straight line, the inner wing (5) first moves in translation with the outer wing (1) and then rotates at a constant speed. The starting point and the ending point of the special groove correspond to the fully retracted state and the fully extended state of the inner wing (5). The groove trajectories on the inner wing (5) and the outer wing (1) are determined by their motion patterns.

5. The variable-sweep telescopic wing aircraft variant structure according to claim 1 or 2, characterized in that, The outer wing (1) and inner wing (5) are connected by a rotary joint and a slide rail. The push rod (4) is driven by the lead screw system (3) to push the outer wing (1) and inner wing (5) to translate and rotate along the slide rail, thereby realizing the deployment and retraction of the entire wing.

6. The variable-sweep telescopic wing aircraft variant structure according to claim 1 or 2, characterized in that, The screw system (3) is a double-helix screw system; the variable sweep telescopic wing aircraft has two working attitudes: wing deployment attitude and wing retraction attitude; when the wing is deployed, the screw system (3) drives the two side slides to gradually push towards the middle. Under the action of the push rod and slider structure, the push rod (4) moves towards the middle along the slide grooves of the outer wing (1) and the inner wing (5). When it moves to the inflection point of the slide groove, the outer wing (1) reaches the maximum extension. When it continues to move to the end point of the slide groove, the inner wing (5) reaches the maximum opening angle; when the wing is retracted, the screw system (3) drives the two side slides to gradually pull towards both sides. 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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