CN107839872B - Linear displacement override rod structure and method thereof - Google Patents
Linear displacement override rod structure and method thereof Download PDFInfo
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- CN107839872B CN107839872B CN201710966097.5A CN201710966097A CN107839872B CN 107839872 B CN107839872 B CN 107839872B CN 201710966097 A CN201710966097 A CN 201710966097A CN 107839872 B CN107839872 B CN 107839872B
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- outer cylinder
- inner cylinder
- cylinder
- linear displacement
- override
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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
-
- 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
- B64C13/12—Dual control apparatus
Abstract
The invention relates to a linear displacement override rod structure, which comprises an inner cylinder, an outer cylinder and a braking device, wherein the inner cylinder is fixedly connected with the outer cylinder; one end of the inner cylinder is an airplane control lever system connecting end, one end of the outer cylinder is an airplane control lever system connecting end, the other end of the inner cylinder and the other end of the outer cylinder are inserted together to form a sleeving structure, and the inner cylinder and the outer cylinder are in sliding fit; the braking device is fixed on the outer cylinder and exerts a limiting force between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder cannot slide mutually to form rigid connection. The mode that adopts torque limiter and rack and pinion to combine together has realized the linear displacement override, and axial length is short, and light in weight can be applicable to little space installation, and the disconnection is rapid during the override, and the residual stress is little after the disconnection, alleviates driver's manipulation burden greatly, but ground manual reset, and the maintainability is good, and the reliability is high, and is longe-lived, has improved the security and the manipulation quality that the aircraft was controlled.
Description
Technical Field
The invention belongs to the technical field of design of airplane control systems, and relates to a linear displacement override lever structure and a method thereof, in particular to a linear displacement override lever structure of a control lever system between a primary pilot and a secondary pilot of an airplane.
Background
In the airplane control system, the pilot operation and the copilot are mechanically interconnected through an override mechanism, synchronous motion between a pilot operation lever system and a copilot lever system is realized during normal operation, when the pilot operation (or the copilot) lever system has jamming faults, a pilot on the other side can disconnect the pilot lever system on the jamming side after overcoming certain threshold starting force to realize override, and then the pilot operation of the airplane can be still carried out on the non-jamming side, so that the safety of airplane operation is improved.
The existing wire displacement override mode is realized by a spring pull rod, and the main structure comprises a cylindrical compression spring, a cylindrical shell, a sleeve, a guide rod, a compression spring, earring joints at two ends, a lining and the like. The structure of the pilot is long, the installation length is limited by the volume of the cylindrical spiral spring, the spring pull rod override mechanism cannot be used in a small space, and additional operating force still exists after override, so that the operating burden of the pilot is increased.
Usually, the torque limiter is provided with a steel ball and a disc spring, and the steel ball is pressed into a groove by the disc spring through an action ring; when overload occurs, the steel ball is separated from the groove stop position, the disc spring is overturned through the action ring to release torque transmission, and the mutual acting force is released by the fixing part and the rotating part of the torque limiter.
Disclosure of Invention
The purpose of the invention is: the linear displacement override lever structure is provided to solve the defects of the existing spring pull rod type linear displacement override mechanism, is suitable for installation of the override mechanism in a small space, has no additional stress after override, does not increase the operation burden of a pilot, enables the pilot to have sufficient physical strength and energy to operate the airplane, and improves the operation quality of the airplane.
The technical scheme of the invention is as follows: a linear displacement override lever structure, comprising: comprises an inner cylinder, an outer cylinder and a braking device;
one end of the inner cylinder is an airplane control lever system connecting end, one end of the outer cylinder is an airplane control lever system connecting end, the other end of the inner cylinder and the other end of the outer cylinder are inserted together to form a sleeving structure, and the inner cylinder and the outer cylinder are in sliding fit;
the braking device is fixed on the outer cylinder, and exerts a limiting force between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder cannot slide mutually, rigid connection is formed, and a locking state is kept; when the pushing force or the pulling force applied between the inner cylinder and the outer cylinder is larger than the limiting force of the braking device, the inner cylinder and the outer cylinder slide mutually, and the locking state is released;
the connecting end of the inner barrel and the connecting end of the outer barrel are used as two connecting ends of the linear displacement override rod structure.
Further, the braking device comprises a torque limiter, a gear and a rack; the torque limiter is fixed on the outer barrel, the torque limiter outputs limiting force through a gear, the rack is fixed with the inner barrel, and the gear is meshed with the rack.
Further, the braking device comprises a torque limiter and a male-female matching structure; the torque limiter is fixed on the outer cylinder, the torque limiter exerts limiting force through one of the convex part and the concave part, the other of the convex part and the concave part is arranged on the inner cylinder, the inner cylinder and the outer cylinder cannot slide mutually through the convex-concave matching structure and the limiting force, and when pushing force or pulling force exerted between the inner cylinder and the outer cylinder is larger than the limiting force of the torque limiter, the convex-concave matching structure removes the restriction of the limiting force, so that the inner cylinder and the outer cylinder slide mutually, and the locking state is removed.
Furthermore, the braking device is a friction brake, the friction brake is fixed on the outer cylinder, a friction pair or friction pincers of the friction brake are in friction clasping with the inner cylinder, and when the pushing force or the pulling force applied between the inner cylinder and the outer cylinder is larger than the limiting force of the friction clasping, the inner cylinder and the outer cylinder slide mutually to release the friction clasping.
Furthermore, the connecting end of the inner cylinder and the outer cylinder is a ball joint or a lug.
Furthermore, a sliding bearing or a ball bearing assembly is arranged between the inner cylinder and the outer cylinder.
Furthermore, an anti-rotation mechanism is arranged between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder can be prevented from rotating relatively.
Further, the outer cylinder comprises a connecting section and a main body section, the connecting section is used for forming a connecting end, and the main body section is used for being in sliding fit with the inner cylinder.
Furthermore, the torque limiter is fixed on the outer cylinder shell, the torque output end of the torque limiter and the gear rotate integrally, the rack is fixed on the inner cylinder, the gear is meshed with the rack to realize torque transmission, and limiting force is applied to the inner cylinder.
The use method of the linear displacement override lever structure is characterized by comprising the following steps:
step one, two ends of a linear displacement override rod structure are respectively connected with the operating levers of a main driver and a copilot, and the limiting force of the linear displacement override rod structure forms rigid connection, so that the operating levers of the main driver and the copilot are synchronously linked;
step two, when one of the control levers of the main driver and the assistant driver is blocked or locked due to mechanical failure, one end connected with the linear displacement override lever structure is synchronously blocked or locked, the driver improves the operating force of the other control lever, and when the operating force exceeds the limiting force, the control lever is unlocked;
and step three, continuing to control the airplane to fly by means of the operating rod in the unlocked state.
The invention has the advantages that: the mode that adopts torque limiter and rack and pinion to combine together has realized the linear displacement override, and axial length is short, and light in weight can be applicable to little space installation, and the disconnection is rapid during the override, and the residual stress is little after the disconnection, alleviates driver's manipulation burden greatly, but ground manual reset, and the maintainability is good, and the reliability is high, and is longe-lived, has improved the security and the manipulation quality that the aircraft was controlled.
Drawings
FIG. 1 is a schematic cross-sectional view of an aircraft control wire displacement override lever configuration of the present invention;
FIGS. 2 and 3 are schematic diagrams of the torque limiter principle of the present invention;
FIG. 4 is an enlarged view of a portion of the torque limiter and gear rack;
wherein: 1-inner cylinder, 2-outer cylinder, 3-torque limiter, 4-gear, 5-rack, 6-connecting end, 7-sliding bearing, 8-connecting section, 9-main body section.
Detailed Description
Referring to fig. 1-4, a linear displacement override lever structure is provided, characterized in that: comprises an inner cylinder 1, an outer cylinder 2 and a braking device;
one end of the inner cylinder is an airplane control lever system connecting end, one end of the outer cylinder is an airplane control lever system connecting end, the other end of the inner cylinder and the other end of the outer cylinder are inserted together to form a sleeving structure, and the inner cylinder and the outer cylinder are in sliding fit;
the braking device is fixed on the outer cylinder, and exerts a limiting force between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder cannot slide mutually, rigid connection is formed, and a locking state is kept; when the pushing force or the pulling force applied between the inner cylinder and the outer cylinder is larger than the limiting force of the braking device, the inner cylinder and the outer cylinder slide mutually, and the locking state is released;
the connecting end of the inner barrel and the connecting end of the outer barrel are used as two connecting ends of the linear displacement override rod structure.
Further, the braking device comprises a torque limiter 3, a gear 4 and a rack 5; the torque limiter is fixed on the outer barrel, the torque limiter outputs limiting force through a gear, the rack is fixed with the inner barrel, and the gear is meshed with the rack.
Further, the braking device comprises a torque limiter and a male-female matching structure; the torque limiter is fixed on the outer cylinder, the torque limiter exerts limiting force through one of the convex part and the concave part, the other of the convex part and the concave part is arranged on the inner cylinder, the inner cylinder and the outer cylinder cannot slide mutually through the convex-concave matching structure and the limiting force, and when pushing force or pulling force exerted between the inner cylinder and the outer cylinder is larger than the limiting force of the torque limiter, the convex-concave matching structure removes the restriction of the limiting force, so that the inner cylinder and the outer cylinder slide mutually, and the locking state is removed.
Furthermore, the braking device is a friction brake, the friction brake is fixed on the outer cylinder, a friction pair or friction pincers of the friction brake are in friction clasping with the inner cylinder, and when the pushing force or the pulling force applied between the inner cylinder and the outer cylinder is larger than the limiting force of the friction clasping, the inner cylinder and the outer cylinder slide mutually to release the friction clasping.
Furthermore, the connecting end 6 of the inner cylinder and the outer cylinder is a ball joint or a lug.
Further, a sliding bearing 7 or a ball assembly is arranged between the inner cylinder and the outer cylinder.
Furthermore, an anti-rotation mechanism is arranged between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder can be prevented from rotating relatively.
Further, the outer cylinder comprises a connecting section 8 and a main body section 9, wherein the connecting section is used for forming a connecting end, and the main body section is used for being in sliding fit with the inner cylinder.
Furthermore, the torque limiter is fixed on the outer cylinder shell, the torque output end of the torque limiter and the gear rotate integrally, the rack is fixed on the inner cylinder, the gear is meshed with the rack to realize torque transmission, and limiting force is applied to the inner cylinder.
The use method of the linear displacement override lever structure is characterized by comprising the following steps:
step one, two ends of a linear displacement override rod structure are respectively connected with the operating levers of a main driver and a copilot, and the limiting force of the linear displacement override rod structure forms rigid connection, so that the operating levers of the main driver and the copilot are synchronously linked;
step two, when one of the control levers of the main driver and the assistant driver is blocked or locked due to mechanical failure, one end connected with the linear displacement override lever structure is synchronously blocked or locked, the driver improves the operating force of the other control lever, and when the operating force exceeds the limiting force, the control lever is unlocked;
and step three, continuing to control the airplane to fly by means of the operating rod in the unlocked state.
In a specific embodiment, the torque limiter is provided with a steel ball and a disc spring, and the steel ball is pressed into the groove by the disc spring through an action ring; when overload occurs, the steel ball is separated from the groove stop position, the disc spring is overturned through the action ring to release torque transmission, and the mutual acting force is released by the fixing part and the rotating part of the torque limiter.
The inner cylinder is provided with a section of opening with the length of 30mm, the bottom surface of the opening is provided with a rack with 2 teeth, the rack is positioned by two positioning pins and fixed by M3 countersunk head screws, the torque limiter part is a finished part with teeth on the circumference, the circumference of the torque limiter part 5 is provided with one tooth, the teeth on the circumference of the torque limiter part are meshed with the teeth on the rack, when the override torque is 500N, the radius of the gear is 25mm, and the disengagement torque of the torque limiter can be selected to be 500 Nx0.025-12.5 N.m;
a sliding bearing or a supporting ring component is arranged between the inner cylinder and the outer cylinder.
The supporting ring assembly comprises an inner ring, an O-shaped sealing ring and an outer ring, the inner ring is connected with the outer ring in a sleeved mode, the O-shaped sealing ring is located between the inner ring and the outer ring, the inner ring is in sliding fit with the outer wall surface of the inner cylinder, and the outer ring is fixed with the inner wall surface of the outer cylinder.
Claims (10)
1. A linear displacement override lever structure, comprising: comprises an inner cylinder, an outer cylinder and a braking device;
one end of the inner cylinder is an airplane control lever system connecting end, one end of the outer cylinder is an airplane control lever system connecting end, the other end of the inner cylinder and the other end of the outer cylinder are inserted together to form a sleeving structure, and the inner cylinder and the outer cylinder are in sliding fit;
the braking device is fixed on the outer cylinder, and exerts a limiting force between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder cannot slide mutually, rigid connection is formed, and a locking state is kept; when the pushing force or the pulling force applied between the inner cylinder and the outer cylinder is larger than the limiting force of the braking device, the inner cylinder and the outer cylinder slide mutually, and the locking state is released;
the connecting end of the inner barrel and the connecting end of the outer barrel are used as two connecting ends of the linear displacement override rod structure.
2. The linear displacement override lever structure of claim 1, wherein: the braking device comprises a torque limiter, a gear and a rack; the torque limiter is fixed on the outer barrel, the torque limiter outputs limiting force through a gear, the rack is fixed with the inner barrel, and the gear is meshed with the rack.
3. The linear displacement override lever structure of claim 1, wherein: the braking device comprises a torque limiter and a convex-concave matching structure; the torque limiter is fixed on the outer cylinder, the torque limiter exerts limiting force through one of the convex part and the concave part, the other of the convex part and the concave part is arranged on the inner cylinder, the inner cylinder and the outer cylinder cannot slide mutually through the convex-concave matching structure and the limiting force, and when pushing force or pulling force exerted between the inner cylinder and the outer cylinder is larger than the limiting force of the torque limiter, the convex-concave matching structure removes the restriction of the limiting force, so that the inner cylinder and the outer cylinder slide mutually, and the locking state is removed.
4. The linear displacement override lever structure of claim 1, wherein: the brake device is a friction brake which is fixed on the outer cylinder, a friction pair or friction pincers of the friction brake are in friction clasping with the inner cylinder, and when the pushing force or the pulling force applied between the inner cylinder and the outer cylinder is larger than the limiting force of the friction clasping, the inner cylinder and the outer cylinder slide mutually to release the friction clasping.
5. The linear displacement override lever structure of claim 1, wherein: the connecting end of the inner cylinder and the outer cylinder is a ball joint or a lug.
6. The linear displacement override lever structure of claim 1, wherein: a sliding bearing or a ball assembly is arranged between the inner cylinder and the outer cylinder.
7. The linear displacement override lever structure of claim 1, wherein: and an anti-rotation mechanism is arranged between the inner cylinder and the outer cylinder, so that the inner cylinder and the outer cylinder can be prevented from rotating relatively.
8. The linear displacement override lever structure of claim 1, wherein: the outer cylinder comprises a connecting section and a main body section, the connecting section is used for forming a connecting end, and the main body section is used for being in sliding fit with the inner cylinder.
9. The structure of claim 2, wherein: the torque limiter is fixed on the outer barrel shell, a torque output end of the torque limiter and the gear rotate integrally, the rack is fixed on the inner barrel, the gear is meshed with the rack to achieve torque transmission, and limiting force is applied to the inner barrel.
10. A method of using a linear displacement override lever structure according to any one of claims 1 to 8, comprising the steps of:
step one, two ends of a linear displacement override rod structure are respectively connected with the operating levers of a main driver and a copilot, and the limiting force of the linear displacement override rod structure forms rigid connection, so that the operating levers of the main driver and the copilot are synchronously linked;
step two, when one of the control levers of the main driver and the assistant driver is blocked or locked due to mechanical failure, one end connected with the linear displacement override lever structure is synchronously blocked or locked, the driver improves the operating force of the other control lever, and when the operating force exceeds the limiting force, the control lever is unlocked;
and step three, continuing to control the airplane to fly by means of the operating rod in the unlocked state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710966097.5A CN107839872B (en) | 2017-10-17 | 2017-10-17 | Linear displacement override rod structure and method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710966097.5A CN107839872B (en) | 2017-10-17 | 2017-10-17 | Linear displacement override rod structure and method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN107839872A CN107839872A (en) | 2018-03-27 |
| CN107839872B true CN107839872B (en) | 2020-11-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710966097.5A Active CN107839872B (en) | 2017-10-17 | 2017-10-17 | Linear displacement override rod structure and method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112373704A (en) * | 2020-11-17 | 2021-02-19 | 中国商用飞机有限责任公司 | System for realizing emergency control of airplane by controlling engine thrust and airplane |
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