A tilting and folding wing mechanism

Abstract

A tilting and folding wing mechanism is composed of a fuselage, a tilting mechanism, and a folding mechanism. The tilting mechanism is composed of a translation device, a limiting device, and a driving device. Through their combined movement, the wing beam can be translated relative to the fuselage while tilting. The folding mechanism is composed of an inner wing, a folding device, and an outer wing. Through their combined movement, the outer wing can be folded relative to the inner wing around an axis parallel to the wing chord. In conjunction with the movement of the tilting mechanism, the wing can be folded toward the rear side of the fuselage. The tilting and folding wing mechanism of the present invention can provide static stability to the tilt-wing UAV when flying in a fixed-wing state through reasonable coordination and connection, and reduce the space occupied by the tilt-wing UAV when parked on the ground.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft design, and in particular relates to a tilting and folding wing mechanism. Background Art

[0002] Tilt-wing drones (UAVs) tilt their wings to change the direction of their thrust vector, achieving the vertical takeoff and landing (VTOL) and fixed-point hovering capabilities of multi-rotor aircraft, combined with the high-speed, low-power cruising characteristics of fixed-wing aircraft. Compared to tilt-rotor and rotor / fixed-wing hybrid UAVs, tilt-wing UAVs offer superior hovering and cruising efficiency, making them valuable for engineering applications. To ensure stability in vertical takeoff, the center of gravity of tilt-wing UAVs is typically located behind the wings. However, when switching to fixed-wing flight, the wing's focal point is located forward of the center of gravity, resulting in poor flight stability. Furthermore, to ensure high speed and efficiency in level flight, tilt-wing UAVs typically employ a high aspect ratio configuration. Because their wings cannot fold, they occupy a large space when parked on the ground, severely limiting their application in both military and civilian applications, such as carrier-based aircraft and future urban transportation.

[0003] In order to overcome the above shortcomings, the present invention proposes a tilt-folding wing mechanism, which can make the wings move forward and backward relative to the fuselage while tilting, so that when the tilt-wing UAV switches to fixed-wing state for level flight, the center of gravity is located in front of the wing focus, so that the whole machine has good static stability. At the same time, the mechanism can realize folding of the wings, reducing the space occupied by the tilt-wing UAV when parked on the ground. Summary of the Invention

[0004] 1. Purpose: The purpose of the present invention is to provide a tilt-folding wing mechanism to enable a tilt-wing UAV to have static stability when flying in a fixed-wing state and to reduce the space occupied by the tilt-wing UAV when parked on the ground.

[0005] 2. Technical solution: A tilting and folding wing mechanism, characterized in that it consists of a fuselage, a tilting mechanism, and a folding mechanism.

[0006] The tilt mechanism comprises a fuselage, a translation mechanism, a limiter, and a drive mechanism. These mechanisms are connected as follows: the translation mechanism, limiter, and drive mechanism are all secured to the fuselage via bolts. The combined movement of the translation mechanism, limiter, and drive mechanism allows the spar 3 to simultaneously translate relative to the fuselage while tilting.

[0007] The translation device comprises a slide rail support 13, a slide rail 14, a spar support 4, and a spar 3. The connections between them are as follows: the slide rail 14 is bonded to the slide rail support 13; the slide rail support 13 and the slide rail 14 are connected via linear bearings, allowing the slide rail support 13 to translate forward and backward relative to the slide rail 14; and the spar 3 is connected to the slide rail support 13 via sliding bearings, allowing the spar 3 to rotate relative to the slide rail support 13.

[0008] The limiting device comprises a limiting shaft support 7, a limiting shaft 8, a limiting rocker arm 6, a spar rocker arm 5, and a spar 3. The connection between them is as follows: the limiting shaft 8 is connected to the limiting shaft support via a sliding bearing, allowing the limiting shaft 8 to rotate relative to the limiting shaft support 7; the limiting rocker arm 6 is bonded to the limiting shaft 8 and fixed; the limiting rocker arm 6 is hinged to the spar rocker arm 5 via bolts, allowing the spar rocker arm 5 to rotate relative to the limiting rocker arm 6; and the spar rocker arm 5 is bonded to the spar 3 and can drive the spar 3 to rotate.

[0009] The drive device comprises a front frame 10, a first servo 9, a first servo rocker arm 11, a spar tie rod 12, and a spar 3. The connections between these components are as follows: the first servo 9 is fixed to the front frame 10 via bolts; the first servo rocker arm 11 is fixed to the output shaft of the first servo 9 via bolts, allowing the first servo 9 to drive the first servo rocker arm 11 to rotate; the spar tie rod 12 is connected to the first servo rocker arm 11 via bolts, allowing the spar tie rod 12 to rotate relative to the first servo rocker arm 11; and the spar tie rod 12 is connected to the spar 3 via sliding bearings, allowing the spar 3 to rotate relative to the spar tie rod 12.

[0010] The fuselage is composed of a front frame 10, a rear frame 1, side panels 2, and a bottom panel 15. They are all connected and fixed in pairs by bolts.

[0011] The folding mechanism is characterized by comprising an inner wing section, a folding device, and an outer wing section. The folding device is driven to fold the outer wing section relative to the inner wing section about an axis parallel to the wing chord. In conjunction with the movement of the tilt mechanism, the wing section can be tilted toward the rear of the fuselage.

[0012] The folding device comprises a second servo 9, a second servo rocker arm 18, an inner reinforcement rib 19, a tie rod 20, and an outer reinforcement rib 21. The connections between them are as follows: the second servo 9 is fixed to the inner reinforcement rib 19 via bolts; the second servo rocker arm 18 is hingedly connected to the tie rod 20 via bolts, allowing the tie rod 20 to rotate relative to the second servo rocker arm 18; the tie rod 20 is hingedly connected to the outer reinforcement rib 21 via bolts, allowing the outer reinforcement rib 21 to rotate relative to the tie rod 20; and the outer reinforcement rib 21 is hingedly connected to the inner reinforcement rib 19 via bolts, allowing the outer reinforcement rib 21 to rotate relative to the inner reinforcement rib 19.

[0013] Described inner section wing is made up of wing spar 3, inner side reinforcing rib 19, inner section wing surface 16. They are all fixed to each other by bonding and cannot move relative to each other.

[0014] The outer wing section consists of an outer wing surface 22 and outer ribs 21. These are bonded together to prevent relative movement. Furthermore, a rod made of carbon fiber reinforced resin material connects the outer wing surface 22 to the outer ribs 21 to transfer the bending moment to the outer wing surface.

[0015] 3. Advantages and Efficacy: The tilt-wing device of the present invention enables the wings of a tilt-wing UAV to simultaneously tilt and translate forward and backward, providing the UAV with excellent static stability during fixed-wing flight. Furthermore, the wings, designed to fold toward the rear of the fuselage based on the kinematic characteristics of the tilt-wing, reduce the space occupied by the UAV when parked on the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention is further described below with reference to the accompanying drawings and examples:

[0017] Figure 1 This is a schematic diagram of the wing folding;

[0018] Figure 2 It is a schematic diagram of vertical take-off and landing state;

[0019] Figure 3 It is a schematic diagram of the fixed-wing state;

[0020] Figure 4 is a schematic diagram of the tilting mechanism;

[0021] Figure 4 Middle: Component 1 is the rear frame, component 2 is the side panel, component 3 is the spar, component 4 is the spar support, component 5 is the spar rocker, component 6 is the limit rocker, component 7 is the limit shaft support, component 8 is the limit shaft, component 9 is the first steering gear, component 10 is the front frame, component 11 is the first steering gear rocker, component 12 is the spar tie rod, component 13 is the slide rail support, component 14 is the slide rail, and component 15 is the bottom plate;

[0022] Figure 5 Schematic diagram of the tilt-folding wing mechanism;

[0023] Figure 5 Middle: Component 16 is the inner section of the airfoil, component 17 is the second servo, component 18 is the second servo rocker arm, component 19 is the pull rod, component 20 is the inner reinforcement rib, component 21 is the outer reinforcement rib, and component 22 is the outer section of the airfoil. DETAILED DESCRIPTION

[0024] Combine Figures 1 to 5 The specific embodiment of the present invention is described:

[0025] The present invention is a tilt-folding wing mechanism. When the tilt-wing UAV switches from a vertical take-off and landing state to a fixed-wing state, the first servo 9 is the prime mover, driving the first servo rocker arm 11 to rotate counterclockwise, pushing the wing spar 3 to translate backward along the slide rail 14 via the wing spar pull rod 12. At the same time, the limit rocker arm 6 pulls the wing spar rocker arm 5, causing the wing spar 3 to rotate clockwise, thereby realizing the coupling of wing tilt and translation motion.

[0026] When the wing is folding, the second servo 9 is the prime mover, driving the second servo rocker arm 18 to rotate counterclockwise, pushing the pull rod 20 to make the outer wing rotate counterclockwise around an axis parallel to the wing chord, thereby realizing the outer wing folding toward the rear side of the fuselage.

[0027] The following is further described in conjunction with an embodiment. Figures 1 to 3 For the tilt-folding wing mechanism installed: Figure 1 The figure shows a schematic diagram of the wing folding state. A tilt-rotor UAV using this mechanism can fold its wings when parked on the ground, reducing the width of the tilt-rotor UAV when parked on the ground. Figure 2 The figure shows a schematic diagram of vertical take-off and landing state; Figure 3 The figure shows a schematic diagram of the fixed-wing state. In this state, the focus of the wing of the tilt-rotor UAV is located behind the center of gravity of the tilt-rotor UAV. The tilt-rotor UAV has static stability when flying in the fixed-wing state.

Claims

1. A tilt-folding wing mechanism, characterized in that: It consists of a fuselage, a tilting mechanism, and a folding mechanism; The tilting mechanism is composed of a fuselage, a translation device, a limiting device, and a driving device. The translation device, the limiting device, and the driving device are all fixed to the fuselage by bolts. Through the combined movement of the translation device, the limiting device, and the driving device, the wing beam (3) can be translated relative to the fuselage while tilting. The translation device is composed of a slide rail support (13), a slide rail (14), a wing beam support (4), and a wing beam (3). The slide rail (14) is bonded and fixed to the slide rail support (13); the slide rail support (13) is connected to the slide rail (14) through a linear bearing, and the slide rail support (13) can translate back and forth relative to the slide rail (14); the wing beam (3) is connected to the slide rail support (13) through a sliding bearing, and the wing beam (3) can rotate relative to the slide rail support (13); The limiting device is composed of a limiting shaft support (7), a limiting shaft (8), a limiting rocker arm (6), a wing spar rocker arm (5), and a wing spar (3). The limiting shaft (8) is connected to the limiting shaft support through a sliding bearing, and the limiting shaft (8) can rotate relative to the limiting shaft support (7); the limiting rocker arm (6) and the limiting shaft (8) are bonded and fixed; the limiting rocker arm (6) and the wing spar rocker arm (5) are hinged through bolts, and the wing spar rocker arm (5) can rotate relative to the limiting rocker arm (6); the wing spar rocker arm (5) and the wing spar (3) are bonded and fixed, and the wing spar rocker arm (5) can drive the wing spar (3) to rotate; The driving device is composed of a front frame (10), a first steering gear (9), a first steering gear rocker arm (11), a wing spar pull rod (12), and a wing spar (3). The first steering gear (9) is fixed to the front frame (10) by bolt connection; the first steering gear rocker arm (11) is fixed to the output shaft of the first steering gear (9) by bolt connection, and the first steering gear (9) can drive the first steering gear rocker arm (11) to rotate; the wing spar pull rod (12) is connected to the first steering gear rocker arm (11) by bolt connection, and the wing spar pull rod (12) can rotate relative to the first steering gear rocker arm (11); the wing spar pull rod (12) is connected to the wing spar (3) by a sliding bearing, and the wing spar (3) can rotate relative to the wing spar pull rod (12); The fuselage is composed of a front frame (10), a rear frame (1), side panels (2), and a bottom panel (15), which are all connected and fixed in pairs by bolts; The folding mechanism consists of an inner wing, a folding device, and an outer wing. The folding device drives the outer wing to fold relative to the inner wing around an axis parallel to the wing chord. In conjunction with the movement of the tilting mechanism, the wing can be folded toward the rear of the fuselage. The folding device is composed of a second steering gear (17), a second steering gear rocker arm (18), an inner reinforcing rib (19), a pull rod (20), and an outer reinforcing rib (21). The second steering gear (17) is fixed to the inner reinforcing rib (19) by bolts; the second steering gear rocker arm (18) is hinged to the pull rod (20) by bolts, and the pull rod (20) can rotate relative to the second steering gear rocker arm (18); the pull rod (20) is hinged to the outer reinforcing rib (21) by bolts, and the outer reinforcing rib (21) can rotate relative to the pull rod (20); the outer reinforcing rib (21) is hinged to the inner reinforcing rib (19) by bolts, and the outer reinforcing rib (21) can rotate relative to the inner reinforcing rib (19). When the wing is in a non-folded state, the second steering gear rocker arm (18) and the pull rod (20) are collinear, and the folding mechanism is in a self-locking state, which can reduce the torque load of the second steering gear (17) when the folding device transmits the bending moment generated by the aerodynamic force of the wing; The inner section wing is composed of a wing spar (3), an inner side reinforcing rib (19), and an inner section wing surface (16), which are fixed to each other by bonding and cannot move relative to each other; The outer wing section is composed of an outer wing surface (22) and an outer reinforcement rib (21), which are fixed to each other by bonding and cannot move relative to each other. The outer wing surface (22) has a rod made of carbon fiber reinforced resin material connected to the outer reinforcement rib (21) to transmit the bending moment borne by the outer wing surface.

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