Folding wing unfolding and locking device based on disc spring locking

Abstract

The invention discloses a folding wing unfolding and locking device based on disc spring locking. The folding wing unfolding and locking device comprises a steering engine, a wing box, a bearing end cover, a wing rocker arm, a locking device, a locking pin, a folding combined disc spring, a guide rail, a sliding block, a connecting rod, a steering engine push rod connector, a rotating shaft and a bearing. In an initial state, the folding combined disc spring is in a free state, and when a wing rocker arm touches the inclined surface of the locking pin in the rotating process of a wing, the locking pin moves downwards under the action of normal force to pre-tighten the folding combined disc spring; when a locking hole in a wing rocker arm coincides with a first mounting hole, by utilizing the characteristics of high rigidity, quick deformation response and small impact force of the folding combined disc springs, the multiple sets of folding combined disc springs quickly push the locking pin to bounce into the locking hole by releasing stored elastic potential energy, so that the aim of quickly locking a wing is fulfilled; the folding wing unfolding and locking device is compact in structure, simple, reliable, quick in response, high in universality and capable of being applied to quick locking of airfoils of various aircrafts.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft structures, and in particular to a folding wing unfolding locking device based on disc spring locking. Background Art

[0002] In response to the demand for miniaturization of aircraft launch devices and simple and convenient transportation and storage, foldable wings are widely used in the field of aircraft because of their advantages of being able to reduce the size of aircraft and launch devices and improve the flight capabilities of aircraft. The unfolding performance of folding wings is directly related to the aerodynamic shape of the aircraft and affects the flight accuracy of the aircraft. At present, the unfolding of traditional folding wings generally relies on the locking force of the servo itself to lock the wings. When subjected to high wing loads, the mechanism and drive device of this locking method are relatively bulky and require a larger drive system to provide sufficient power, resulting in an increase in the load on the wing itself, limiting the performance of the aircraft.

[0003] Therefore, it is necessary to develop a folding wing deployment locking device based on disc spring locking to solve the above problems. Summary of the invention

[0004] The purpose of the present invention is to design a folding wing unfolding locking device based on disc spring locking in order to solve the above-mentioned problem.

[0005] The present invention achieves the above-mentioned purpose through the following technical solutions: A folding wing deployment locking device based on disc spring locking, comprising: Steering gear; Rotating shaft; a wing box; a first end of the wing is disposed below the wing box; The connecting rod; the action end of the servo is rotatably connected to the first end of the wing rocker arm, and the servo is used to drive the wing rocker arm to rotate around the axis of the rotating shaft; the second end of the wing rocker arm is connected to the first end of the rotating shaft, and the second end of the rotating shaft passes downward through the wing box and is connected to the first end of the wing; Bearing; the bearing is mounted on the outside of the rotating shaft and installed in the wing box; The locking device comprises a locking pin and a matched combination disc spring, a retaining ring is mounted on the middle part of the locking pin, a first mounting hole and a second mounting hole are vertically opened on the top of the outer ring of the bearing, the second mounting hole is arranged below the first mounting hole, the matched combination disc spring is mounted on the locking pin and arranged below the retaining ring; the widths of the matched combination disc spring and the retaining ring are both smaller than the width of the first mounting hole, the width of the matched combination disc spring is larger than the width of the first mounting hole, and the width of the second mounting hole is smaller than the width of the locking pin; an inclined surface is arranged on the top of the locking pin, the inclined surface faces the tangent direction of the movement of the wing rocker arm when the wing is unfolded, a locking hole is vertically arranged on the wing rocker arm, the first mounting hole is on the movement trajectory of the locking hole, and the width of the locking pin is smaller than the width of the locking hole.

[0006] The beneficial effects of the present invention are: 1. Taking advantage of the characteristics of large stiffness, fast deformation response and small impact force of the combined disc spring, the rapidity and stability of wing deployment and locking can be achieved; 2. The accuracy of wing deployment locking can be achieved through the special-shaped design of the locking pin structure and the position design of the locking pin hole; 3. Compact mechanical design, compact structure, easy assembly, disassembly and maintenance; 4. It has a wide range of applications and can be used for the deployment and locking of various aircraft wing surfaces. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 It is a schematic diagram of the overall structure of the device designed by the present invention; Figure 2 is a partial cross-sectional view of the present invention at the locking device; Figure 3 It is a partial enlarged view of the locking device; Figure 4 It is a schematic diagram of the wing deployment process; Figure 5 This is a schematic diagram of the disc spring pressed down by the locking pin during the wing deployment process; Figure 6 This is a schematic diagram of the wings deployed and locked; Figure 7 It is a schematic diagram of the locking device structure when the wing is unfolded and locked.

[0008] In the figure, 1-servo; 2-wing box; 3-bearing end cover; 31-through hole; 4-wing rocker arm; 5-wing; 6-locking device; 61-locking pin; 611-inclined surface; 612-vertical surface; 62-matched combined disc spring; 63-retaining ring; 7-guide rail; 8-slider; 9-connecting rod; 10-servo push rod joint; 11-rotating shaft; 12-bearing; 121-first mounting hole; 122-second mounting hole; 13-locking hole. DETAILED DESCRIPTION

[0009] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0010] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0011] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0012] In the description of the present invention, it should be understood that the terms "upper", "lower", "inside", "outside", "left", "right", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, or are directions or positional relationships in which the product of the invention is usually placed when in use, or are directions or positional relationships commonly understood by those skilled in the art. These directions or positional relationships are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present invention.

[0013] Furthermore, the terms “first”, “second”, etc. are merely used for distinguishing descriptions and should not be understood as indicating or implying relative importance.

[0014] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms such as "setting" and "connection" should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0015] The specific implementation modes of the present invention are described in detail below in conjunction with the accompanying drawings.

[0016] like Figure 1-7 As shown, a folding wing deployment locking device based on disc spring locking comprises: Servo 1; Rotating shaft 11; The wing box 2; the first end of the wing 5 is placed below the wing box 2; The connecting rod 9; the servo 1 is used to drive the wing rocker arm 4 to rotate around the axis of the rotating shaft 11; the second end of the wing rocker arm 4 is connected to the first end of the rotating shaft 11 through a nut, and the second end of the rotating shaft 11 passes downward through the wing box 2 and is connected to the first end of the wing 5 through a screw; The bearing 12 is sleeved on the outside of the rotating shaft 11, and the bearing 12 is installed in the wing box 2; The locking device 6 comprises a locking pin 61 and a matching disc spring 62. A retaining ring 63 is sleeved on the middle of the locking pin 61. A first mounting hole 121 and a second mounting hole 122 are vertically opened on the top of the outer ring of the bearing 12. The second mounting hole 122 is arranged below the first mounting hole 121. The matching disc spring 62 is sleeved on the locking pin 61 and is arranged below the retaining ring 63. The widths of the matching disc spring 62 and the retaining ring 63 are both smaller than the width of the first mounting hole 121 (clearance fit). The matching disc spring 6 2 is greater than the width of the first mounting hole 121, and the width of the second mounting hole 122 is less than the width of the locking pin 61 (clearance fit); the top of the locking pin 61 is provided with an inclined surface 611, and the inclined surface 611 faces the movement tangent direction of the wing rocker arm 4 when the wing 5 is unfolded. The wing rocker arm 4 is vertically provided with a locking hole 13, and the first mounting hole 121 is on the movement track of the locking hole 13. The width of the locking pin 61 is less than the width of the locking hole 13, so as to ensure that the locking pin 61 can be smoothly ejected into the locking hole 13 of the rocker arm; Connecting rod 9, steering gear push rod joint 10; the working end of the steering gear 1 is connected to the steering gear push rod joint 10, the steering gear push rod joint 10 is rotatably connected to the first end of the connecting rod 9, and the second end of the connecting rod 9 is rotatably connected to the first end of the wing rocker arm 4.

[0017] Guide rail 7, slider 8; slider 8 is connected to the steering gear push rod joint 10, guide rail 7 is installed in wing box 2, the setting direction of guide rail 7 is consistent with the action direction of steering gear 1, and slider 8 is slidably installed in guide rail 7. The cooperation of guide rail 7 and slider 8 is used for power output guidance of steering gear.

[0018] In some embodiments, a bearing end cover 3 is disposed on the top of the outer ring of the bearing 12, and a through hole 31 is vertically disposed on the bearing end cover 3. The through hole 31 is placed above the first mounting hole 121, and the width of the through hole 31 is greater than the width of the locking pin 61 (clearance fit) and less than the width of the mating combined disc spring 62. The top of the retaining ring 63 is limited by the bearing end cover 3, thereby realizing the upward movement limit of the locking pin 61.

[0019] In some embodiments, a vertical surface 612 is disposed on the top of the locking pin 61 , and the vertical surface 612 is located on the opposite side of the inclined surface 611 .

[0020] To ensure that the locking pin 61 can be smoothly pressed into the locking hole 13, one side of the upper half of the locking pin 61 is a slope 611, facing the tangential direction of the movement of the connecting rod 9 when the wing 5 is unfolded, and the other side is designed to be a straight surface; the lower end of the locking pin 61 serves as a guide rod to pass through the inner hole of the matching combination disc spring 62, and the lower end passes through the second mounting hole 122, and the matching combination disc spring 62 is limited by the retaining ring 63, and the upper end of the locking pin 61 passes through the through hole 31 on the bearing end cover 3 and exceeds a certain distance, which is the stroke of the locking pin 61 to lock the wing 5; the matching combination disc spring 62 is in the form of multiple matching combinations, and the number of disc springs is determined by the stroke of the locking pin 61 to lock the wing 5.

[0021] In the present application, the combined disc spring 62 is in a free state in the initial state. Figure 1-3 The servo 1 drives the slider 8 and the connecting rod 9 to push the wing rocker arm 4 to rotate, thereby driving the wing 5 to unfold around the rotation axis 11. When the wing rocker arm 4 moves to contact the inclined surface 611 of the locking pin 61, the locking pin 61 moves downward under the action of the normal force, and the combined disc spring 62 is pre-tightened, as shown in FIG. Figure 4 and Figure 5 As shown; when the locking hole 13 on the rocker arm coincides with the first mounting hole 121, the multiple sets of the combined disc springs 62 release the stored elastic potential energy by utilizing the characteristics of large stiffness, fast deformation response and small impact force, and quickly push the locking pin 61 into the locking hole 13 of the wing rocker arm 4, thereby achieving the purpose of fast locking of the wing 5, as shown in FIG. Figure 6 and Figure 7 shown.

[0022] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A folding wing deployment locking device based on disc spring locking, characterized in that: include: Steering gear; Rotating shaft; wing box; A first end of the wing is placed below the wing box; link; The action end of the servo is rotatably connected to the first end of the wing rocker arm, and the servo is used to drive the wing rocker arm to rotate around the axis of the rotating shaft; the second end of the wing rocker arm is connected to the first end of the rotating shaft, and the second end of the rotating shaft passes downward through the wing box and is connected to the first end of the wing; Bearing; the bearing is mounted on the outside of the rotating shaft and installed in the wing box; The locking device comprises a locking pin and a matched combination disc spring, a retaining ring is mounted on the middle part of the locking pin, a first mounting hole and a second mounting hole are vertically opened on the top of the outer ring of the bearing, the second mounting hole is arranged below the first mounting hole, the matched combination disc spring is mounted on the locking pin and arranged below the retaining ring; the widths of the matched combination disc spring and the retaining ring are both smaller than the width of the first mounting hole, the width of the matched combination disc spring is larger than the width of the first mounting hole, and the width of the second mounting hole is smaller than the width of the locking pin; an inclined surface is arranged on the top of the locking pin, the inclined surface faces the tangent direction of the movement of the wing rocker arm when the wing is unfolded, a locking hole is vertically arranged on the wing rocker arm, the first mounting hole is on the movement trajectory of the locking hole, and the width of the locking pin is smaller than the width of the locking hole.

2. A folding wing deployment locking device based on disc spring locking according to claim 1, characterized in that: A bearing end cover is arranged at the top of the outer ring of the bearing, and a through hole is vertically arranged on the bearing end cover. The through hole is placed above the first mounting hole, and the width of the through hole is greater than the width of the locking pin and less than the width of the mating combined disc spring.

3. A folding wing deployment locking device based on disc spring locking according to claim 1, characterized in that: A vertical surface is arranged on the top of the locking pin, and the vertical surface is located on the opposite side of the inclined surface.

4. A folding wing deployment locking device based on disc spring locking according to claim 1, characterized in that: The folding wing unfolding locking device also includes a connecting rod and a steering gear push rod joint, the working end of the steering gear is connected to the steering gear push rod joint, the steering gear push rod joint is rotatably connected to the first end of the connecting rod, and the second end of the connecting rod is rotatably connected to the first end of the wing rocker arm.

5. A folding wing deployment locking device based on disc spring locking according to claim 4, characterized in that: The folding wing unfolding locking device also includes a guide rail and a slider. The slider is connected to the steering gear push rod joint. The guide rail is installed in the wing box. The setting direction of the guide rail is consistent with the action direction of the steering gear. The slider is slidably installed in the guide rail.

Images