A bidirectionally adjustable stiffness dead zone structure for aviation joystick

Abstract

This invention belongs to the field of aircraft control systems and discloses a bidirectional adjustable stiffness dead zone structure for an aircraft control stick. This structure enables the control stick to remain stationary within a certain load range even when at its zero position, without displacement due to changes in applied force, and the load range is adjustable. The structure includes a base, a gear shaft, a cylindrical helical torsion spring, a limiting screw, a gear shaft support, and a dead zone adjustment plate. During installation, a preload is applied to the cylindrical helical torsion spring via a sector groove. When the pilot applies a load to the control stick, this preload must be overcome before effective displacement of the control stick can occur, thus achieving the stiffness dead zone. By changing the relative position of the sector grooves, the stiffness dead zone range can be adjusted. This invention provides pilots with a more user-friendly control experience and allows for adjustment of the stiffness dead zone range according to the requirements of different pilots.

Description

Technical Field

[0001] This invention belongs to the field of aircraft control mechanical systems, and relates to an aircraft control stick, specifically to an aircraft control stick with bidirectional adjustable stiffness dead zone structure. Background Technology

[0002] Traditional aircraft control sticks use a spring structure to achieve the return-to-center function. Since the stiffness of the spring is constant within its elastic range, it will displace even under a small load. This results in a poor control experience near the zero position, and the control stick may also wobble near the zero position due to inertia, producing erroneous commands and endangering the control of the aircraft.

[0003] To provide pilots with a more user-friendly control experience and prevent accidental movement of the control stick from the zero position due to inertia, designing a mechanism to generate a starting force for the aircraft control stick is of great significance. Furthermore, different pilots have different flying habits, resulting in varying requirements for the range of starting force. In addition, since the aircraft control stick requires bidirectional movement, a bidirectional starting force function is necessary.

[0004] The proposed structure for realizing the bidirectional adjustable stiffness dead zone of an aircraft control stick (202011549687.6) is flawed due to errors in the described solution, thus failing to solve the proposed technical problem and produce the corresponding technical effect. Summary of the Invention

[0005] The purpose of this invention is to provide a structure for realizing the bidirectional adjustable stiffness dead zone of an aircraft control stick, giving the aircraft control stick an adjustable starting force.

[0006] The technical solution of this invention is:

[0007] A bidirectional adjustable stiffness dead zone realization structure for an aircraft control stick includes a base, a gear shaft, a cylindrical helical torsion spring, a limiting screw, and a gear shaft support. The base includes a base plate and a side plate erected on the base plate. The gear shaft support is erected on the base plate parallel to the side plate. The side plate and the gear shaft support have the same circular hole at the same position in the lateral direction. The two ends of the gear shaft are respectively located between the side plate and the gear shaft support through the circular holes of the side plate and the gear shaft support. The end of the gear shaft near the side plate is a cylindrical end, and a stepped shaft extends from the end face of the cylindrical end and passes through the circular hole of the side plate. A limiting screw is provided on the side of the cylindrical end. The end of the gear shaft near the gear shaft support is a gear end, which is a sector gear. A portion of the circumference angle includes the gear, and the remaining angles are cylindrical surfaces. The diameter of the cylinder is smaller than the inner diameter of the cylindrical helical torsion spring. A stepped shaft extends from the end face of the gear end and passes through the round hole of the gear shaft support. Another limiting screw is provided on the side of the cylindrical part of the gear end, and there is an included angle between the two limiting screws. A cylindrical helical torsion spring is sleeved on the gear shaft, and the two ends of the cylindrical helical torsion spring are respectively limited by two limiting screws.

[0008] Furthermore, the two mounting ends of the cylindrical helical torsion spring are a first cylinder and a second cylinder; a first sector-shaped groove is provided next to the circular hole of the side plate, and the first cylinder of the cylindrical helical torsion spring near the cylindrical end of the gear shaft extends out from the first sector-shaped groove. When the operating lever is in the zero position, the first cylinder at the cylindrical end of the gear shaft is close to the first lower semi-circular arc surface of the first sector-shaped groove and is tangentially constrained by it; a second sector-shaped groove is provided next to the circular hole of the gear shaft support, and the second cylinder of the cylindrical helical torsion spring near the gear end of the gear shaft extends out from the second sector-shaped groove.

[0009] Furthermore, the line connecting the center of the first lower semicircular arc surface in the first sector groove to the gear shaft axis and the line connecting the center of the first upper semicircular arc surface in the second sector groove to the gear shaft axis have an included angle when projected along the gear shaft axis direction.

[0010] Furthermore, it also includes a dead zone adjustment plate, which has a circular hole identical to the circular hole of the gear shaft support. The dead zone adjustment plate also has a third sector groove. The dead zone adjustment plate is installed on the side of the gear shaft support in connection with the circular hole. The third sector groove of the dead zone adjustment plate overlaps with the second sector groove, and the range of the second sector groove is larger than that of the third sector groove.

[0011] Furthermore, the second cylinder of the cylindrical helical torsion spring, which is close to the gear end of the gear shaft, extends from the third sector groove on the dead zone adjustment plate. When the control lever is in the zero position, the second cylinder at the gear end of the gear shaft is close to the second upper semi-circular surface in the third sector groove and is tangentially constrained by it.

[0012] Furthermore, the mating surfaces of the third and second sector grooves are provided with graduations.

[0013] Furthermore, the range of the second sector groove is larger than that of the first sector groove.

[0014] Furthermore, the gear end and the cylindrical end of the gear shaft can rotate relative to each other, thereby adjusting the included angle between the two limit screws on the gear shaft during assembly. The limit screws also enable relative locking between the gear end and the cylindrical end, ensuring that the gear end and the cylindrical end of the gear shaft remain relatively fixed during operation.

[0015] Furthermore, the mating surfaces of the gear end and the cylindrical end of the gear shaft are provided with graduations.

[0016] The advantages of this invention are:

[0017] Based on the principle of parallel action, a structural design for a bidirectional adjustable starting force of an aircraft control stick is realized through a simple mechanical structure, providing pilots with a more humanized operating experience, while avoiding accidental movement of the control stick at the zero position due to inertia and other reasons. At the same time, this structure has an adjustable dead zone range function, which can meet the flying habits of different pilots, and realizes the function of bidirectional starting force. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the assembly structure for realizing the bidirectional adjustable stiffness dead zone of an aircraft control stick according to the present invention.

[0020] Figure 2 This is a left view of the stiffness dead zone realization structure of the present invention;

[0021] Figure 3 This is a front view of the structure implementing the present invention;

[0022] Figure 4 This is a rear view of the structure implemented in this invention;

[0023] Figure 5 This is a structural diagram of the base;

[0024] Figure 6 This is a schematic diagram of the gear shaft support.

[0025] Figure 7 This is a schematic diagram of the dead zone adjustment plate;

[0026] Figure 8 This is a partial exploded view of the gear shaft and the limiting screw;

[0027] Figure 9 This is a schematic diagram of a cylindrical helical torsion spring structure;

[0028] Figure 10 This is a schematic diagram of the structure of the gear shaft, limit screw and cylindrical helical torsion spring assembly;

[0029] Figure 11 This is a schematic diagram of the structure of the gear shaft support and dead zone adjustment plate assembly;

[0030] Figure 12 This is the force-displacement curve of the aircraft control stick after adopting this structure;

[0031] Among them, 1-base, 2-gear shaft, 3-cylindrical helical torsion spring, 3.1-first cylinder, 3.2-second cylinder, 41-first limiting screw, 42-second limiting screw, 5-gear shaft support seat, 6-dead zone adjustment plate, 7-first sector groove, 7.1-first lower semicircular arc surface, 8-second sector groove, 8.1-first upper semicircular arc surface, 9-third sector groove, 9.1-second upper semicircular arc surface, 10-first gear shaft assembly, 11-second gear shaft assembly. Detailed Implementation

[0032] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0033] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are given in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0034] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0035] Example 1:

[0036] A bidirectional adjustable stiffness dead zone realization structure for an aircraft control stick includes a base 1, a gear shaft 2, a cylindrical helical torsion spring 3, a first limiting screw 41, a second limiting screw 42, a gear shaft support 5, and a dead zone adjustment plate 6. The base 1 includes a base plate and a side plate erected on the base plate. The gear shaft support 5 is erected on the base plate parallel to the side plate. The side plate and the gear shaft support 5 have the same circular hole at the same position in the lateral direction. The two ends of the gear shaft 2 are respectively located between the side plate and the gear shaft support 5 through the circular holes of the side plate and the gear shaft support 5. The end of the gear shaft 2 near the side plate is a cylindrical end. A stepped shaft extends from the end face of the cylindrical end and passes through the circular hole of the side plate. The side of the cylindrical end is provided with a first limiting screw 41. The end of the gear shaft 2 near the gear shaft support 5 is a gear end. The gear end of the gear shaft 2 is a sector gear. A portion of the circumference angle includes the gear, and the remaining angle is a cylindrical surface. Its cylindrical diameter is smaller than the inner diameter of the cylindrical helical torsion spring 3. A stepped shaft extends from the end face of the gear end and passes through the round hole of the gear shaft support seat 5. A second limiting screw 42 is provided on the side of the cylindrical part of the gear end. There is an included angle between the first limiting screw 41 and the second limiting screw 42. A cylindrical helical torsion spring 3 is sleeved on the gear shaft 2. The two ends of the cylindrical helical torsion spring 3 are respectively limited by two limiting screws.

[0037] The cylindrical helical torsion spring 3 has two mounting ends, namely a first cylinder 3.1 and a second cylinder 3.2; a first sector groove 7 is provided next to the circular hole of the side plate, and the first cylinder 3.1 of the cylindrical helical torsion spring 3 near the cylindrical end of the gear shaft 2 extends out from the first sector groove 7. When the operating lever is in the zero position, the first cylinder 3.1 of the cylindrical end of the gear shaft 2 is close to the first lower semi-circular arc surface 7.1 of the first sector groove 7 and is tangentially constrained by it; a second sector groove 8 is provided next to the circular hole of the gear shaft support 5, and the second cylinder 3.2 of the cylindrical helical torsion spring 3 near the gear end of the gear shaft 2 extends out from the second sector groove 8.

[0038] The line connecting the center of the first lower semicircular surface 7.1 in the first sector groove 7 to the axis of the gear shaft 2 and the line connecting the center of the first upper semicircular surface 8.1 in the second sector groove 8 to the axis of the gear shaft 2 have an angle when projected along the axis of the gear shaft 2.

[0039] It also includes a dead zone adjustment plate 6, which has a circular hole that is the same as the circular hole of the gear shaft support 5. The dead zone adjustment plate 6 also has a third sector groove 9. The dead zone adjustment plate 6 is installed on the side of the gear shaft support 5 in connection with the circular hole. The third sector groove 9 of the dead zone adjustment plate 6 overlaps with the second sector groove 8, and the range of the second sector groove 8 is larger than that of the third sector groove 9.

[0040] The second cylinder 3.2 of the cylindrical helical torsion spring 3, which is close to the gear end of the gear shaft 2, extends from the third sector groove 9 on the dead zone adjustment plate 6. When the control lever is in the zero position, the second cylinder 3.2 of the gear end of the gear shaft 2 is close to the second upper semi-circular surface 9.1 in the third sector groove 9 and is tangentially constrained by it.

[0041] The mating surfaces of the third sector groove 9 and the second sector groove 8 are marked with graduations.

[0042] The range of the second sector groove 8 is larger than that of the first sector groove 7.

[0043] The gear end and the cylindrical end of the gear shaft 2 can rotate relative to each other, so as to adjust the included angle between the two limit screws on the gear shaft 2 during the assembly process, and to lock the gear end and the cylindrical end relative to each other through the two limit screws, so as to keep the gear end and the cylindrical end of the gear shaft 2 relatively fixed during operation.

[0044] The gear end and the cylindrical end of the gear shaft 2 are provided with scales.

[0045] Example 2:

[0046] Please see Figure 1-12 This invention discloses a bidirectional adjustable stiffness dead zone structure for an aircraft control stick, comprising a base 1, a gear shaft 2, a cylindrical helical torsion spring 3, a first limiting screw 41, a second limiting screw 42, a gear shaft support 5, and a dead zone adjustment plate 6, as well as auxiliary components such as bearings. During installation, the relative positions of the first sector groove 7 and the third sector groove 9 are designed to apply a preload to the cylindrical helical torsion spring 3. When the pilot applies a load to the control stick, the load is transmitted to the gear shaft 2 through the gear system. When the gear needs to rotate, it must first overcome the preload of the cylindrical helical torsion spring 3 to generate effective displacement. By rotating the dead zone adjustment plate 6, the relative positions of the first sector groove 7 and the third sector groove 9 can be changed, thereby adjusting the range of starting force.

[0047] As one embodiment, the dead zone adjustment plate 6 is provided with three mounting sector slots, and the mounting surface edge of the gear shaft support 5 is provided with scale. By cooperating with the mounting sector slots, the rotation of the third sector slot 9 can be realized, thereby completing the precise adjustment of the starting force range.

[0048] As one embodiment, the gear shaft support 5 is provided with a second sector groove 8 to ensure that the cylindrical helical torsion spring 3 can pass through this component, and the range of the second sector groove 8 must be greater than that of the third sector groove 9.

[0049] In one embodiment, the gear shaft 2 is divided into two parts, including a first gear shaft assembly 10 and a second gear shaft assembly 11. The first gear shaft assembly 10 includes the cylindrical end of the gear shaft, and the second gear shaft assembly 11 includes the gear end of the gear shaft. Two limiting screws 4 are respectively installed on the first gear shaft assembly 10 and the second gear shaft assembly 11, and respectively contact the first cylinder 3.1 and the second cylinder 3.2 at both ends of the cylindrical helical torsion spring 3 to realize the transmission of load. During assembly, the relative rotation of the first gear shaft assembly 10 and the second gear shaft assembly 11, in conjunction with the dead zone adjustment plate 6, realizes the adjustment of the starting force range of the control lever. The mating surfaces of the first gear shaft assembly 10 and the second gear shaft assembly 11 are provided with scales, which can realize precise adjustment of the relative position.

[0050] As one embodiment, taking the direction from the gear shaft 2 axially along the gear end towards the cylindrical end as the frontal view, when the gear shaft 2 rotates instantaneously clockwise, the first limiting screw 41 at the cylindrical end of the gear shaft 2 rotates clockwise synchronously with the gear shaft 2, causing the first cylinder 3.1 of the cylindrical helical torsion spring 3 near the cylindrical end of the gear shaft 2 to rotate clockwise. The second limiting screw 42 at the gear end of the gear shaft 2 rotates clockwise synchronously with the gear shaft 2, having no effect on the second cylinder 3.2 of the cylindrical helical torsion spring 3 near the gear end of the gear shaft 2. The second cylinder 3.2 of the cylindrical helical torsion spring 3 near the gear end of the gear shaft 2 is affected by the third fan. The second upper semicircular surface 9.1 in the groove 9 is constrained; when the gear shaft 2 rotates counterclockwise, the second limiting screw 42 at the gear end of the gear shaft 2 rotates counterclockwise synchronously with the gear shaft 2, causing the second cylinder 3.2 of the cylindrical helical torsion spring 3 near the gear end of the gear shaft 2 to rotate counterclockwise. The first limiting screw 41 at the cylindrical end of the gear shaft 2 rotates counterclockwise synchronously with the gear shaft 2, and has no effect on the first cylinder 3.1 of the cylindrical helical torsion spring 3 near the cylindrical end of the gear shaft 2. The first cylinder 3.1 of the cylindrical helical torsion spring 3 near the cylindrical end of the gear shaft 2 is constrained by the first lower semicircular surface 7.1 in the first sector groove 7.

[0051] Let the torsional stiffness of the selected cylindrical helical torsion spring 3 be k.

[0052] The angle between the projection of the lines connecting the centers of the first upper semicircular surface 8.1 in the second sector groove 8 and the second upper semicircular surface 9.1 in the third sector groove 9 with the axis of gear shaft 2 along the axis of gear shaft 2 is θ. Therefore, the dead zone range limitation F0 = kθ is shown in the figure. By adjusting the relative rotation angle of the gear shaft 2 assembly and the rotation angle of the dead zone adjustment plate 6, the angle θ can be adjusted, thereby adjusting the starting force range.

[0053] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of this invention is defined by the appended claims and their equivalents.

Claims

1. A bidirectional adjustable stiffness dead zone structure for an aircraft control stick, characterized in that, The system includes a base (1), a gear shaft (2), a cylindrical helical torsion spring (3), a limiting screw (4), a gear shaft support seat (5), and a dead zone adjustment plate (6). The base (1) includes a base plate and a side plate standing on the base plate. The gear shaft support seat (5) is installed on the base plate parallel to the side plate. The side plate and the gear shaft support seat (5) have the same round hole at the same position in the lateral direction. The two ends of the gear shaft (2) are respectively located between the side plate and the gear shaft support seat (5) through the round holes of the side plate and the gear shaft support seat (5) and are connected by bearings. The end of the gear shaft (2) near the side plate is a cylindrical end. The side of the cylindrical end has a flat surface with a threaded hole. The first limiting screw (41) is threadedly connected to the threaded hole. The end of the gear shaft (2) near the gear shaft support seat (5) is a gear end. The gear end of the gear shaft (2) is a sector gear. The circumference range includes a portion of the gear, and the remaining angles are cylindrical surfaces. The diameter of the cylindrical surface is smaller than the inner diameter of the cylindrical helical torsion spring (3). The side of the cylindrical part of the gear end is also provided with a flat surface, and a threaded hole is also provided on the flat surface. The second limiting screw (42) is connected to the threaded hole by a thread. The first limiting screw (41) that cooperates with the side of the cylindrical end and the second limiting screw (42) that cooperates with the side of the gear end have a non-zero included angle. The cylindrical helical torsion spring (3) is sleeved on the gear shaft (2). The two ends of the cylindrical helical torsion spring (3) are respectively limited by the first limiting screw (41) and the second limiting screw (42). One end of the cylindrical helical torsion spring (3) extends out of the side plate, and the other end of the cylindrical helical torsion spring (3) extends out of the gear shaft support seat (5) and cooperates with the dead zone adjustment plate (6) installed on the outside of the gear shaft support seat (5). The two mounting ends of the cylindrical helical torsion spring (3) are a first cylinder (3.1) and a second cylinder (3.2); a first sector groove (7) is provided next to the round hole of the side plate, and the first cylinder (3.1) of the cylindrical helical torsion spring (3) near the cylindrical end of the gear shaft (2) extends out from the first sector groove (7). When the control lever is in the zero position, the first cylinder (3.1) of the cylindrical end of the gear shaft (2) is close to the first lower semi-circular arc surface (7.1) of the first sector groove (7) and is constrained by its tangential direction; a second sector groove (8) is provided next to the round hole of the gear shaft support (5), and the second cylinder (3.2) of the cylindrical helical torsion spring (3) near the gear end of the gear shaft (2) extends out from the second sector groove (8); The line connecting the center of the first lower semicircular arc surface (7.1) in the first sector groove (7) to the axis of the gear shaft (2) and the line connecting the center of the first upper semicircular arc surface (8.1) in the second sector groove (8) to the axis of the gear shaft (2) have an angle when projected along the axis of the gear shaft (2).

2. The bidirectional adjustable stiffness dead zone structure for an aircraft control stick according to claim 1, characterized in that, It also includes a dead zone adjustment plate (6), which has a round hole that is the same as the round hole of the gear shaft support (5). The dead zone adjustment plate (6) also has a third sector groove (9). The dead zone adjustment plate (6) is installed on the side of the gear shaft support (5) with the round hole connected to it. The third sector groove (9) of the dead zone adjustment plate (6) overlaps with the second sector groove (8), and the range of the second sector groove (8) is larger than that of the third sector groove (9).

3. The bidirectional adjustable stiffness dead zone structure for an aircraft control stick according to claim 2, characterized in that, The cylindrical helical torsion spring (3) extends from the third sector groove (9) on the dead zone adjustment plate (6) near the second cylinder (3.2) at the gear end of the gear shaft (2). When the control lever is at the zero position, the second cylinder (3.2) at the gear end of the gear shaft (2) is close to the second upper semicircular arc surface (9.1) in the third sector groove (9) and is tangentially constrained by it.

4. The bidirectional adjustable stiffness dead zone structure for an aircraft control stick according to claim 2, characterized in that, The mating surfaces of the third sector groove (9) and the second sector groove (8) are provided with scales.

5. The bidirectional adjustable stiffness dead zone structure for an aircraft control stick according to claim 2, characterized in that, The range of the second sector groove (8) is larger than that of the first sector groove (7).

6. The bidirectional adjustable stiffness dead zone structure for an aircraft control stick according to claim 4, characterized in that, The gear end and the cylindrical end of the gear shaft (2) can rotate relative to each other, thereby adjusting the included angle between the first limit screw (41) and the second limit screw on the gear shaft (2) during the assembly process. The gear end and the cylindrical end are locked relative to each other by the first limit screw (41) and the second limit screw, ensuring that the gear end and the cylindrical end of the gear shaft (2) remain relatively fixed during operation.

7. The bidirectional adjustable stiffness dead zone structure for an aircraft control stick according to claim 5, characterized in that, The gear end and the cylindrical end of the gear shaft (2) are provided with scales.

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