CN218112973U - Locking adjusting device of helicopter control rod - Google Patents
Locking adjusting device of helicopter control rod Download PDFInfo
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- CN218112973U CN218112973U CN202222811696.9U CN202222811696U CN218112973U CN 218112973 U CN218112973 U CN 218112973U CN 202222811696 U CN202222811696 U CN 202222811696U CN 218112973 U CN218112973 U CN 218112973U
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- locking
- buckle sleeve
- locking buckle
- hemispheroid
- hemisphere
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Abstract
The utility model relates to an aviation field of making, and disclose a locking adjusting device of helicopter control rod, including setting up the hemispheroid on the passenger cabin floor, the hemispheroid is pegged graft and is had the action bars, the top of hemispheroid is provided with locking buckle sleeve, locking buckle sleeve is in the same place with action bars threaded connection, be provided with damping device and friction cap between hemispheroid and the locking buckle sleeve, rotatory locking buckle sleeve adjustment locking buckle sleeve and the action bars between twist the degree and adjust damping device, damping device gives friction cap holding down force and hemispheroid and laminates, this locking adjusting device of helicopter control rod, the structure of the invention is pleasing to the eye, combine together with the action bars, convenient operation, can screw up by one hand, and the practicality is strong, and play the damping effect.
Description
Technical Field
The utility model relates to an aviation field of making specifically is a locking adjusting device of helicopter control rod.
Background
The helicopter is an aircraft heavier than air, which takes an aircraft engine to drive a rotor wing to rotate as a source of lift force and propulsive force, can vertically rise and fall and hover in the atmosphere and can carry out controllable flight such as front flight, back flight, fixed-point rotation and the like,
the helicopter control lever is positioned in a helicopter cockpit and is divided into a total distance lever and a periodic distance lever, and when the periodic distance lever is operated along the transverse direction and the longitudinal direction, the automatic tilter can tilt in the corresponding direction, so that the pulling force direction of the rotor wing tilts towards the corresponding direction, the required propelling force, transverse direction and longitudinal direction operating force are obtained, and the motion state and flight attitude of the helicopter are changed.
For example, chinese patent CN206813299U relates to an operating lever position locking device for an airplane and an airplane, relates to the technical field of aviation, and solves the technical problem that the position of an airplane operating lever is unstable due to the lack of a locking mechanism in the existing airplane operating lever. The device comprises a fixed seat and a detachable locking mechanism, wherein the fixed seat is fixedly arranged in the airplane, the detachable locking mechanism is connected with the fixed seat, the detachable locking mechanism has a locking state and a free state, an operating rod of the airplane is connected with the fixed seat through the detachable locking mechanism in the locking state, the detachable locking mechanism in the locking state can lock the operating rod at a preset position, the detachable locking mechanism is separated from the operating rod when the detachable locking mechanism is in the free state, and the operating rod is in the free state. The utility model discloses make the control rod of aircraft can be in the state of locking, avoid the unstable condition to appear in the control rod, improved the security.
The control rod is fixed in the scheme in a mechanical structure limiting mode, operation is not easy, the structure is not attractive enough, and therefore the locking adjusting device of the helicopter control rod is provided.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
Not enough to prior art, the utility model provides a locking adjusting device of helicopter control rod has solved foretell problem.
(II) technical scheme
In order to achieve the above object, the utility model provides a following technical scheme: a locking adjusting device of a helicopter control lever comprises a hemisphere arranged on a cabin floor, wherein an operating rod is inserted into the hemisphere, a locking buckle sleeve is arranged at the top of the hemisphere, the locking buckle sleeve is in threaded connection with the operating rod, and a damping device and a friction cap are arranged between the hemisphere and the locking buckle sleeve;
and the locking buckle sleeve is rotated to adjust the screwing degree between the locking buckle sleeve and the operating rod to adjust the damping device, and the damping device gives downward pressure to the friction cap to keep fit with the hemispheroid.
Preferably, one side wall surface of the friction cap, which is jointed with the hemisphere, is an arc concave surface.
Preferably, the damping device comprises a belleville spring and a cover, the cross section of the cover is in a concave shape, and the belleville spring is arranged below the cover.
Preferably, the top of the friction cap and the outer side wall surface of the locking buckle sleeve form a first step surface, the bottom of the belleville spring is attached to the first step surface, an annular bulge is integrally formed on the side wall of the locking buckle sleeve relative to the top of the cover, and the top of the cover is attached to the bottom of the annular bulge.
(III) advantageous effects
Compared with the prior art, the utility model provides a locking adjusting device of helicopter control rod possesses following beneficial effect:
1. the locking adjusting device of the helicopter control rod is attractive in structure, is integrated with the control rod, is convenient to operate, can be screwed down by one hand, is high in practicability, and plays a damping effect.
2. The locking adjusting device of the helicopter control lever can reduce additional damping devices, reduce the dead weight of a helicopter and optimize the design in the actual use process.
3. According to the locking adjusting device of the helicopter control lever, the annular protrusion on the locking buckle sleeve can be adjusted to provide extrusion force for the cover to downwards provide for the butterfly spring through rotating the locking buckle sleeve, and the damping force is adjusted.
Drawings
FIG. 1 is a schematic view of the present invention;
fig. 2 is a schematic sectional view of the present invention.
In the figure: 1. an operating lever; 2. locking buckle sleeves; 3. a belleville spring; 4. a hemisphere; 5. a cover; 6. a friction cap; 7. floor of the cabin.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-2, a locking adjusting device of a helicopter control lever comprises a hemisphere 4 arranged on a cabin floor 7, an operating rod 1 is inserted into the hemisphere 4, a locking buckle sleeve 2 is arranged at the top of the hemisphere 4, the locking buckle sleeve 2 is connected with the operating rod 1 in a threaded manner, and a damping device and a friction cap 6 are arranged between the hemisphere 4 and the locking buckle sleeve 2;
the rotary locking buckle sleeve 2 is rotated to adjust a rotary screwing degree adjusting damping device between the locking buckle sleeve 2 and the operating rod 1, the damping device gives downward pressure to the friction cap 6 to keep fit with the hemispheroid 4, different pilots have different control force and flight habits, the control damping requirements on the operating rod are different, and through rotating the locking buckle sleeve 2, the annular protrusion on the locking buckle sleeve 2 can be adjusted to give downward extrusion force to the butterfly spring 4 to the cover 5, and the damping force is adjusted.
One side wall surface of the friction cap 6, which is attached to the hemisphere 4, is an arc concave surface.
The damping device comprises a belleville spring 3 and a cover 5, the cross section of the cover 5 is in a concave shape, and the belleville spring 3 is arranged below the cover 5.
The top of the friction cap 6 and the outer side wall surface of the locking buckle sleeve 2 form a first step surface, the bottom of the belleville spring 3 is attached to the first step surface, the side wall of the locking buckle sleeve 2 is integrally formed with an annular bulge on the top of the cover 5, and the top of the cover 5 is attached to the bottom of the annular bulge.
Helicopter control rod locking function:
when the helicopter is stored or driven on the ground, the control lever must be locked in order to prevent the control lever from being touched by mistake and causing the periodic pitch change of the blades of the helicopter to cause potential safety hazards. The present invention can achieve the above functions with simple friction. The whole system is arranged on the floor of the cabin as shown in figure 2, and the functional steps are as follows:
the first step is as follows: the locking buckle sleeve 2 is sleeved on the operating rod 1, and the locking buckle sleeve 2 is connected with the operating rod 1 through threads.
(2) The locking buckle sleeve 2 is screwed down, downward extrusion force is given to the cover 5, and the belleville spring 3 is compressed.
(3) The belleville spring 3 extrudes the friction cap 6 to apply downward pressure to the friction cap 6, so that the purpose of attaching the arc concave surface of the friction cap 6 to the hemispheroid 4 is achieved.
(4) The friction cap 6 presses the hemisphere 4 downward.
(5) The friction force generated between the friction cap 6 and the hemisphere 4 makes the fixation between them unable to generate displacement and lock the helicopter control stick.
Helicopter control rod damping function:
different pilots have different control dynamics and flight habits, and the control damping requirements on the control lever are different, and through the steps, the locking buckle sleeve 2 and the control lever 1 are adjusted to realize the damping adjustment through the self-threaded tightening degree.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. A locking adjusting device of a helicopter control lever is characterized by comprising a hemisphere (4) arranged on a cabin floor (7), wherein an operating rod (1) is inserted into the hemisphere (4), a locking buckle sleeve (2) is arranged at the top of the hemisphere (4), the locking buckle sleeve (2) is in threaded connection with the operating rod (1), and a damping device and a friction cap (6) are arranged between the hemisphere (4) and the locking buckle sleeve (2);
the locking buckle sleeve (2) is rotated to adjust the screwing degree between the locking buckle sleeve (2) and the operating rod (1) to adjust the damping device, and the damping device gives downward force to the friction cap (6) to keep fit with the hemispheroid (4).
2. A locking adjustment device for a helicopter control stick according to claim 1, characterized by: one side wall surface of the friction cap (6) attached to the hemisphere (4) is an arc concave surface.
3. A locking adjustment device for a helicopter control stick according to claim 1, characterized by: the damping device comprises a belleville spring (3) and a cover (5), the cross section of the cover (5) is in a concave shape, and the belleville spring (3) is arranged below the cover (5).
4. A locking adjustment device for a helicopter control stick according to claim 3, characterized by: the top of the friction cap (6) and the outer side wall surface of the locking buckle sleeve (2) form a first step surface, the bottom of the belleville spring (3) is attached to the first step surface, an annular bulge is formed on the side wall of the locking buckle sleeve (2) for the top of the cover (5) in an integrated mode, and the top of the cover (5) is attached to the bottom of the annular bulge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222811696.9U CN218112973U (en) | 2022-10-25 | 2022-10-25 | Locking adjusting device of helicopter control rod |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222811696.9U CN218112973U (en) | 2022-10-25 | 2022-10-25 | Locking adjusting device of helicopter control rod |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218112973U true CN218112973U (en) | 2022-12-23 |
Family
ID=84497066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222811696.9U Active CN218112973U (en) | 2022-10-25 | 2022-10-25 | Locking adjusting device of helicopter control rod |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218112973U (en) |
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2022
- 2022-10-25 CN CN202222811696.9U patent/CN218112973U/en active Active
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