CN112455656A - Bidirectional rigidity-adjustable dead zone implementation structure of aviation control lever - Google Patents
Bidirectional rigidity-adjustable dead zone implementation structure of aviation control lever Download PDFInfo
- Publication number
- CN112455656A CN112455656A CN202011549687.6A CN202011549687A CN112455656A CN 112455656 A CN112455656 A CN 112455656A CN 202011549687 A CN202011549687 A CN 202011549687A CN 112455656 A CN112455656 A CN 112455656A
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- Prior art keywords
- gear shaft
- dead zone
- fan
- shaped groove
- gear
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/34—Transmitting means without power amplification or where power amplification is irrelevant mechanical using toothed gearing
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention belongs to the field of airplane control systems, and discloses a bidirectional adjustable rigidity dead zone realization structure of an aviation control lever, which can realize that the control lever does not generate displacement along with the change of acting force within a certain load range when the control lever is positioned at a zero position, and the load range can be adjusted. The structure of the invention comprises a base, a gear shaft, a cylindrical spiral torsion spring, a limit screw, a gear shaft supporting seat, a dead zone adjusting plate and the like. In the installation process of the structure, the pre-tightening force is applied to the cylindrical spiral torsion spring through the fan-shaped groove, when a pilot applies load to the operating lever, the pre-tightening force of the cylindrical spiral torsion spring needs to be overcome, and then the effective displacement of the operating lever can be generated, so that the rigidity dead zone is realized. The adjustment of the rigidity dead zone range can be realized by changing the relative position of the fan-shaped grooves. The invention can provide more humanized operation experience for pilots, and can adjust the range of the rigidity dead zone according to the requirements of different pilots.
Description
Technical Field
The invention belongs to the field of airplane control mechanical systems, relates to an aviation control lever, and particularly relates to a bidirectional rigidity-adjustable dead zone implementation structure of the aviation control lever.
Background
The traditional airplane joystick realizes the centering function of the joystick through a spring structure. Because the rigidity of the spring is fixed in the elastic range, the spring can generate displacement when being subjected to small load, so that the operating experience of the operating lever near the zero position is poor, meanwhile, the operating lever can deflect near the zero position due to inertia and the like, error instructions are generated, and the control of the airplane is damaged.
In order to provide more humanized operation experience for a pilot and avoid the misoperation of the operating rod at a zero position due to reasons such as inertia, the design of a rigidity dead zone realization structure for the aircraft operating rod has important significance. Meanwhile, different pilots have different driving habits, and different requirements are imposed on the range of the stiffness dead zone. In addition, since the airplane joystick requires bidirectional movement, it is necessary to implement a bidirectional stiffness dead zone implementation function.
Disclosure of Invention
The purpose of the invention is as follows: the bidirectional adjustable rigidity dead zone realization structure of the aviation control lever is provided, and an adjustable rigidity dead zone is provided for the airplane control lever.
The technical scheme of the invention is as follows:
a bidirectional rigidity-adjustable dead zone realizing structure of an aviation control lever comprises a base, a gear shaft, a torsion spring, a limit screw and a gear shaft supporting seat; the base comprises a bottom plate and a side plate which is vertically arranged on the bottom plate, the gear shaft supporting seat is vertically arranged on the bottom plate in a manner of being parallel to the side plate, the same round holes are arranged at the same transverse position of the side plate and the gear shaft supporting seat, and two ends of the gear shaft are respectively arranged between the side plate and the gear shaft supporting seat through the round holes of the side plate and the gear shaft supporting seat; one end of the gear shaft, which is close to the side plate, is a cylindrical end, the end surface of the cylindrical end extends out of a step shaft and penetrates through a round hole of the side plate, a limit screw is arranged on the side surface of the cylindrical end, one end of the gear shaft, which is close to the gear shaft supporting seat, is a gear end, the end surface of the gear end extends out of a step shaft and penetrates through a round hole of the gear shaft supporting seat, another limit screw is arranged on the end surface of the gear end, and an included angle is formed; the torsion spring is sleeved on the gear shaft, and two ends of the torsion spring are limited by two limiting screws respectively.
Furthermore, an extended cylindrical pin is arranged beside the end surface step shaft of the cylindrical end of the gear shaft; a cylindrical pin extending out is also arranged beside the end face step shaft at the gear end of the gear shaft; a first fan-shaped groove is formed beside the round hole of the side plate, and a cylindrical pin at the cylindrical end of the gear shaft extends out of the first fan-shaped groove; and a second fan-shaped groove is formed beside the round hole of the gear shaft supporting seat, and a cylindrical pin at the gear end of the gear shaft extends out of the second fan-shaped groove.
Furthermore, an included angle is formed between the first fan-shaped groove and the second fan-shaped groove.
Further, the dead zone adjusting plate is provided with a round hole which is the same as the round hole of the gear shaft supporting seat, a third fan-shaped groove is further formed in the dead zone adjusting plate, the round hole of the dead zone adjusting plate is installed on the side face of the gear shaft supporting seat in a connected mode, the third fan-shaped groove of the dead zone adjusting plate is overlapped with the second fan-shaped groove, and the range of the second fan-shaped groove is larger than that of the third fan-shaped groove.
Furthermore, scales are arranged on the matching surface of the third fan-shaped groove and the second fan-shaped groove.
Further, the range of the second sector-shaped groove is larger than that of the first sector-shaped groove.
Further, the gear end and the cylindrical end of the gear shaft can rotate relatively.
Furthermore, the matching surface of the gear end and the cylindrical end of the gear shaft is provided with scales.
The invention has the advantages that:
based on the parallel action principle, the structural design of the bidirectional adjustable rigidity dead zone of the aviation control lever is realized through a simple mechanical structure, more humanized control experience is provided for pilots, meanwhile, the control lever is prevented from mistakenly moving at a zero position due to reasons such as inertia, meanwhile, the structure has the function of adjusting the dead zone range, the driving habits of different pilots can be met, and the bidirectional rigidity dead zone realizing function is realized.
Drawings
FIG. 1 is an assembly schematic diagram of a bidirectional adjustable rigidity dead zone implementation structure of an aviation control lever.
FIG. 2 is a schematic view of the structure of the base;
FIG. 3 is a schematic structural view of a gear shaft support seat;
FIG. 4 is a schematic structural view of a stiffness dead band adjusting plate;
FIG. 5 is an exploded view of the gear shaft;
FIG. 6 is a force-displacement curve for an aircraft control stick using the present configuration;
the gear assembly comprises a base 1, a gear shaft 2, a torsion spring 3, a limiting screw 4, a gear shaft supporting seat 5, a dead zone adjusting plate 6, a first fan-shaped groove 7, a second fan-shaped groove 8, a third fan-shaped groove 9, a first gear shaft assembly 10 and a second gear shaft assembly 11.
Detailed Description
This section is an example of the present invention for explaining and explaining the technical solution of the present invention
A bidirectional rigidity-adjustable dead zone implementation structure of an aviation control lever comprises a base 1, a gear shaft 2, a torsion spring 3, a limit screw 4 and a gear shaft supporting seat 5; the base 1 comprises a bottom plate and a side plate erected on the bottom plate, the gear shaft supporting seat 5 is erected on the bottom plate in a manner of being parallel to the side plate, the same round holes are formed in the same transverse position of the side plate and the gear shaft supporting seat 5, and two ends of the gear shaft 2 are arranged between the side plate and the gear shaft supporting seat 5 through the side plate and the round holes of the gear shaft supporting seat 5 respectively; one end of the gear shaft 2 close to the side plate is a cylindrical end, a step shaft extends out of the end surface of the cylindrical end and penetrates through a round hole of the side plate, a limit screw 4 is arranged on the side surface of the cylindrical end, one end of the gear shaft 2 close to the gear shaft supporting seat 5 is a gear end, a step shaft extends out of the end surface of the gear end and penetrates through a round hole of the gear shaft supporting seat 5, another limit screw 4 is arranged on the end surface of the gear end, and an included angle is formed between the two limit screws 4; the torsion spring 3 is sleeved on the gear shaft 2, and two ends of the torsion spring 3 are limited by two limit screws 4 respectively.
A cylindrical pin extending out is arranged beside the end face step shaft at the cylindrical end of the gear shaft 2; a cylindrical pin extending out is also arranged beside the end face step shaft at the gear end of the gear shaft 2; a first fan-shaped groove 7 is formed beside the round hole of the side plate, and a cylindrical pin at the cylindrical end of the gear shaft 2 extends out of the first fan-shaped groove 7; a second fan-shaped groove 8 is arranged beside the round hole of the gear shaft supporting seat 5, and a cylindrical pin at the gear end of the gear shaft 2 extends out of the second fan-shaped groove 8.
The first segment groove 7 and the second segment groove 8 have an included angle therebetween.
The dead zone adjusting plate is characterized by further comprising a dead zone adjusting plate 6, wherein the dead zone adjusting plate 6 is provided with a round hole identical to that of the gear shaft supporting seat 5, the dead zone adjusting plate 6 is further provided with a third fan-shaped groove 9, the round hole of the dead zone adjusting plate 6 is continuously arranged on the side face of the gear shaft supporting seat 5, the third fan-shaped groove 9 of the dead zone adjusting plate 6 is overlapped with the second fan-shaped groove 8, and the range of the second fan-shaped groove 8 is larger than that of the third fan.
Scales are arranged on the matching surfaces of the third fan-shaped groove 9 and the second fan-shaped groove 8.
The extent of the second sector grooves 8 is greater than that of the first sector grooves 7.
The gear end and the cylindrical end of the gear shaft 2 can rotate relatively.
The matching surface of the gear end and the cylindrical end of the gear shaft 2 is provided with scales.
For a better understanding of the present invention, reference is made to the following detailed description taken in conjunction with the accompanying drawings.
Referring to fig. 1-6, the structure for realizing the bidirectional adjustable stiffness dead zone of the aviation joystick of the present invention includes a base 1, a gear shaft 2, a cylindrical helical torsion spring 3, a limit screw 4, a gear shaft support base 5, a stiffness dead zone adjusting plate 6, and other main components, as well as auxiliary components such as bearings. This structure is in the installation, through the relative position of designing first sector groove 7 and third sector groove 9, realizes exerting the pretightning force to cylindrical helical torsion spring 3, and when the pilot exerted the load to the control rod, the load passed through gear system and transmitted to gear shaft 2, when the gear need rotate, must overcome cylindrical helical torsion spring 3's pretightning force earlier, just can produce effective displacement. By rotating the rigidity dead zone adjusting plate 6, the relative positions of the first fan-shaped groove 7 and the third fan-shaped groove 9 can be changed, so that the rigidity dead zone range can be adjusted.
As an embodiment, the rigidity dead zone adjusting plate 6 is provided with three installation fan-shaped grooves, the edge of the installation surface of the rigidity dead zone adjusting plate and the edge of the installation surface of the gear shaft supporting seat 5 are provided with scales, and the third fan-shaped groove 9 can rotate by matching with the installation fan-shaped grooves, so that the accurate adjustment of the rigidity dead zone range is completed.
As an embodiment, the gear shaft support base 5 is provided with a second sector groove 8 to ensure that the cylindrical helical torsion spring 3 can pass through the component, and the range of the second sector groove 8 must be larger than that of the sector groove 9.
As an example, 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 a cylindrical end of the gear shaft, and the second gear shaft assembly 11 includes a gear end of the gear shaft; two limit screws 4 are respectively arranged on the first gear shaft component 10 and the second gear shaft component 11 and respectively contacted with two ends of the cylindrical helical torsion spring 3, so that load transmission is realized. The adjustment of the stiffness dead band range of the operating rod is realized by the relative rotation of the first gear shaft assembly 10 and the second gear shaft assembly 11 in cooperation with the stiffness dead band adjusting plate 6. The matching surfaces of the first gear shaft assembly 10 and the second gear shaft assembly 11 are provided with scales, and accurate adjustment of the relative positions can be realized.
If the torsional rigidity of the selected cylindrical helical torsion spring 3 is k, and the included angle between the connecting line of the center of the cylindrical surface of the second sector-shaped groove 8 and the third sector-shaped groove 9, which are in contact with the helical torsion spring 3, and the center of the gear shaft 2 is theta, the dead zone range in the figure is limited by F0K θ. The included angle theta can be adjusted by adjusting the relative rotation angle of the gear shaft 2 assembly and the rotation angle of the rigidity dead zone adjusting plate 6, so that the rigidity dead zone range can be adjusted.
Claims (8)
1. A bidirectional rigidity-adjustable dead zone realizing structure of an aviation control lever is characterized by comprising a base (1), a gear shaft (2), a torsion spring (3), a limit screw (4) and a gear shaft supporting seat (5); the base (1) comprises a bottom plate and a side plate erected on the bottom plate, the gear shaft supporting seat (5) is erected on the bottom plate in a manner of being parallel to the side plate, identical round holes are formed in the same transverse position of the side plate and the gear shaft supporting seat (5), and two ends of the gear shaft (2) are arranged between the side plate and the gear shaft supporting seat (5) through the round holes of the side plate and the gear shaft supporting seat (5) respectively; one end of the gear shaft (2) close to the side plate is a cylindrical end, a step shaft extends out of the end surface of the cylindrical end and penetrates through a round hole of the side plate, a limit screw (4) is arranged on the side surface of the cylindrical end, one end of the gear shaft (2) close to the gear shaft supporting seat (5) is a gear end, a step shaft extends out of the end surface of the gear end and penetrates through a round hole of the gear shaft supporting seat (5), another limit screw (4) is arranged on the end surface of the gear end, and an included angle is formed between the two limit screws (4); the torsion spring (3) is sleeved on the gear shaft (2), and two ends of the torsion spring (3) are limited by two limiting screws (4) respectively.
2. The structure for realizing the bidirectional adjustable rigidity dead zone of the aviation control rod as claimed in claim 1, wherein a protruding cylindrical pin is further arranged beside the end surface step of the cylindrical end of the gear shaft (2); a cylindrical pin extending out is also arranged beside the end face step shaft at the gear end of the gear shaft (2); a first fan-shaped groove (7) is formed beside the round hole of the side plate, and a cylindrical pin at the cylindrical end of the gear shaft (2) extends out of the first fan-shaped groove (7); a second fan-shaped groove (8) is formed beside the round hole of the gear shaft supporting seat (5), and a cylindrical pin at the gear end of the gear shaft (2) extends out of the second fan-shaped groove (8).
3. The aviation joystick bidirectional adjustable rigidity dead zone implementation structure is characterized in that an included angle is formed between the first fan-shaped groove (7) and the second fan-shaped groove (8).
4. The aviation joystick bidirectional adjustable rigidity dead zone implementation structure is characterized by further comprising a dead zone adjusting plate (6), wherein the dead zone adjusting plate (6) is provided with a round hole identical to that of the gear shaft supporting seat (5), the dead zone adjusting plate (6) is further provided with a third fan-shaped groove (9), the round hole of the dead zone adjusting plate (6) is connected to the side face of the gear shaft supporting seat (5), the third fan-shaped groove (9) of the dead zone adjusting plate (6) is overlapped with the second fan-shaped groove (8), and the range of the second fan-shaped groove (8) is larger than that of the third fan-shaped groove (9).
5. The structure for realizing the bidirectional adjustable rigidity dead zone of the aviation control rod is characterized in that scales are arranged on the matching surfaces of the third fan-shaped groove (9) and the second fan-shaped groove (8).
6. The aviation joystick bidirectional adjustable stiffness dead zone implementation structure is characterized in that the range of the second fan-shaped groove (8) is larger than that of the first fan-shaped groove (7).
7. The aviation joystick bidirectional adjustable rigidity dead zone implementation structure is characterized in that the gear end and the cylindrical end of the gear shaft (2) can rotate relatively.
8. The structure for realizing the bidirectional adjustable rigidity dead zone of the aviation control rod as claimed in claim 7, wherein the matching surface of the gear end and the cylindrical end of the gear shaft (2) is provided with scales.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011549687.6A CN112455656A (en) | 2020-12-24 | 2020-12-24 | Bidirectional rigidity-adjustable dead zone implementation structure of aviation control lever |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011549687.6A CN112455656A (en) | 2020-12-24 | 2020-12-24 | Bidirectional rigidity-adjustable dead zone implementation structure of aviation control lever |
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| Publication Number | Publication Date |
|---|---|
| CN112455656A true CN112455656A (en) | 2021-03-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011549687.6A Pending CN112455656A (en) | 2020-12-24 | 2020-12-24 | Bidirectional rigidity-adjustable dead zone implementation structure of aviation control lever |
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| CN (1) | CN112455656A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911320A (en) * | 2021-10-09 | 2022-01-11 | 中国商用飞机有限责任公司 | Steering wheel mechanism |
-
2020
- 2020-12-24 CN CN202011549687.6A patent/CN112455656A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911320A (en) * | 2021-10-09 | 2022-01-11 | 中国商用飞机有限责任公司 | Steering wheel mechanism |
| CN113911320B (en) * | 2021-10-09 | 2024-05-14 | 中国商用飞机有限责任公司 | Steering wheel mechanism |
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Application publication date: 20210309 |
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| RJ01 | Rejection of invention patent application after publication |