CN114671006A - Aircraft rotor support arm folding mechanism and aircraft rotor support arm - Google Patents
Aircraft rotor support arm folding mechanism and aircraft rotor support arm Download PDFInfo
- Publication number
- CN114671006A CN114671006A CN202210395931.0A CN202210395931A CN114671006A CN 114671006 A CN114671006 A CN 114671006A CN 202210395931 A CN202210395931 A CN 202210395931A CN 114671006 A CN114671006 A CN 114671006A
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- Prior art keywords
- abutting surface
- lock pin
- support
- rotating shaft
- folding mechanism
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention relates to the field of aircrafts, in particular to an aircraft rotor wing support arm folding mechanism and an aircraft rotor wing support arm, wherein the folding mechanism comprises a first support seat and a second support seat, wherein the first support seat is provided with a first abutting surface; the second support is provided with a second abutting surface; the first support and the second support are hinged through a rotating shaft and locked through a lock pin to form a folded state and an unfolded state, and in the unfolded state, the first abutting surface abuts against the second abutting surface; two sides of the first abutting surface are provided with first connecting lugs, two sides of the second abutting surface are provided with second connecting lugs, and the first connecting lugs are used for abutting against the second connecting lugs and matching with the second connecting lugs to install the rotating shaft and the lock pin; the abutting surfaces of the first connecting lug and the second connecting lug are deviated from the center of the first abutting surface and are close to the bottom of the first abutting surface. The folding mechanism is ingenious in design, can improve the stress performance and the fatigue performance of the folding mechanism, and has remarkable popularization significance.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to an aircraft rotor wing support arm folding mechanism and an aircraft rotor wing support arm.
Background
The existing multi-axis rotor craft generally adopts a mode of folding a rotor support arm to reduce the storage volume, for small and medium-sized multi-axis rotor craft, the mode of folding the rotor support arm mostly adopts a mode of combining a rotating shaft and a threaded sleeve, and after the threaded sleeve is unscrewed, the rotor support arm can be folded around the rotating shaft; after the rotor wing support arm is unfolded, the threaded sleeve is screwed down to fix the rotor wing support arm, the folding mode is simple and easy to operate, but the bearing capacity is weak, the fatigue performance is low, and the novel rotary wing support arm is mainly used for small and medium sizes with small loads.
In order to improve the connection strength, part of the rotor wing support arm folding mechanism adopts a mode of adding a bolt through a rotating shaft, namely, the rotor wing support arm folding mechanism is connected with the rotor wing support arm through two sleeve joints, and the connecting surface between the two sleeve joints is fixedly connected through the rotating shaft and the bolt penetrating through the lug joints in a mode of arranging the lug joints on two sides. After the bolt joint is pulled out, the rotor wing support arm can be folded around the rotating shaft; after the rotor support arm is unfolded, the bolt is inserted into the hole on the lug joint to fix the rotor support arm. The stress performance and fatigue performance of the folding mechanism are closely related to the thickness distribution of the lug joints and the connection form of the rotating shaft and the bolt, and other detailed designs.
There is a need to solve the above technical problems.
Disclosure of Invention
In order to solve the technical problems, the invention provides an aircraft rotor wing support arm folding mechanism and an aircraft rotor wing support arm, which greatly improve the connection strength of the folding aircraft rotor wing support arm and reduce the overall weight by optimizing the structure, and adopts the following technical scheme:
an aircraft rotor boom folding mechanism comprising:
the first support is provided with a first abutting surface;
the second support is provided with a second abutting surface;
the first support and the second support are hinged through a rotating shaft and locked through a lock pin to form a folded state and an unfolded state, and in the unfolded state, the first abutting surface abuts against the second abutting surface;
two sides of the first abutting surface are provided with first connecting lugs, two sides of the second abutting surface are provided with second connecting lugs, and the first connecting lugs are used for abutting against the second connecting lugs and matching with the second connecting lugs to install the rotating shaft and the lock pin;
the abutting surfaces of the first connecting lug and the second connecting lug deviate from the center of the first abutting surface and are close to the bottom of the first abutting surface.
In some embodiments, the two sides of the second abutting surface are also provided with third connecting lugs;
the second connecting lug is close to the top of the second abutting surface, the third connecting lug is close to the bottom of the second abutting surface, and an accommodating space of the first connecting lug is formed between the third connecting lug and the second connecting lug;
in the unfolded state, the first connecting lug abuts against the second connecting lug and the third connecting lug respectively, and abutting surfaces of the first connecting lug and the third connecting lug deviate from the center of the first abutting surface and are close to the bottom of the first abutting surface.
In some embodiments, the thickness of the first engaging lug is the same as the thickness of the second engaging lug and both are greater than the thickness of the third engaging lug.
In some embodiments, a first connection hole is disposed on the first connection lug;
the second connecting lug is provided with a second connecting hole;
a third connecting hole is formed in the third connecting lug;
the inner wall of the second connecting hole is provided with threads;
the screw thread is provided to a part of or the entire inner wall of the second connection hole, and the rotation shaft and the locking pin have screw threads adapted to the second connection hole, respectively.
In some embodiments, a bushing is also included;
the bushing is of a hollow pipe structure with a smooth inner wall surface and is arranged in the first connecting hole, the third connecting hole and the second connecting hole in an interference fit mode, and the portion, which is not provided with threads, of the second connecting hole is arranged in the first connecting hole, the third connecting hole and the second connecting hole.
In some embodiments, the rotating shaft comprises a shaft cap, a shaft polish rod portion, and a shaft threaded portion;
the rotating shaft thread portion is provided with threads used for being matched with the second connecting hole, and the rotating shaft cap is used as a limiting structure of the rotating shaft.
In some embodiments, the latch includes a latch cap, a latch polished rod portion, a latch threaded portion, and a latch arm;
the lock pin thread part is provided with threads matched with the second connecting hole, the lock pin cap is used as a limit structure of the lock pin, and the lock pin arm is installed on the lock pin cap or is integrally formed with the lock pin cap.
In some embodiments, the first seat;
and/or
And the second support is provided with a hollow sleeve and is used for being connected with an aircraft rotor support arm.
In some embodiments of the present invention, the,
and a protective gasket is arranged on the outer side surface of the hollow sleeve.
In another aspect, the present invention provides an aircraft rotor arm comprising:
a first support arm;
a second support arm;
the aircraft rotor wing support arm folding mechanism is provided;
the first support arm is connected to the first support, and the second support arm is connected to the second support.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention provides an aircraft rotor wing support arm folding mechanism which comprises a first support and a second support, wherein the first support and the second support are respectively provided with a butting surface and a connecting lug, and the butting surfaces of the first connecting lug and the second connecting lug are arranged at positions deviating from the center of the first butting surface and close to the bottom, so that the force arm of the first support and the second support when bearing bending load is lengthened, and the integral connection strength of a rotor wing support arm folding piece is improved.
2. According to the aircraft rotor wing support arm folding mechanism provided by the invention, the third connecting lugs are further arranged on the two sides of the second abutting surface and are close to the bottom of the second abutting surface, a single-lug and double-lug matching structure is formed between the first support and the second support, and the third connecting lugs are arranged to enable the shear surface of the folding mechanism, which mainly bears the tensile force, to be transferred to the space between the first connecting lug and the third connecting lug from the original space between the first connecting lug and the second connecting lug, so that the moment arm of the folding mechanism when bearing the bending load is further increased.
3. According to the aircraft rotor wing support arm folding mechanism provided by the invention, the inner wall of the second connecting hole is provided with the threads, and the threads can be arranged on part or all of the inner wall.
In conclusion, the folding mechanism is ingenious in design, stress performance and fatigue performance of the folding mechanism can be improved, the structural design is reasonable and compact, the overall weight is small, and the folding mechanism has remarkable popularization significance.
Drawings
The invention is described in further detail below with reference to the following figures and detailed description:
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is an exploded view of the overall structure of the present invention;
FIG. 3 is a schematic view of a second support of the present invention;
FIG. 4 is a schematic view of a first support structure of the present invention;
FIG. 5 is a schematic view of the load analysis of the present invention;
FIG. 6 is a schematic view of the overall structure of another embodiment of the present invention;
FIG. 7 is an exploded schematic view of the structure of FIG. 6;
the reference numbers illustrate:
100 is a first support; 101 is a first connecting lug, 111 is a first connecting hole, and 102 is a first abutting surface;
200 is a second support, 201 is a second lug, 202 is a third lug, 203 is a second contact surface, 211 is a second connecting hole, 221 is a third connecting hole;
300 is a rotation axis; 301 is a spindle cap, 302 is a spindle threaded portion, 303 is a spindle polished rod portion, and 304 is a nut;
400 is a lock pin, 401 is a lock pin cap, 402 is a lock pin screw portion, 403 is a lock pin lever portion, 404 is a lock pin arm;
500 is a bushing;
600 is a hollow sleeve;
700 is a protective gasket;
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
For the sake of simplicity, only the parts relevant to the invention are schematically shown in the drawings, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".
It should be further understood that the term "and/or" as used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.
In this context, it is to be understood that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, in the description of the present application, the terms "first," "second," and the like are used only for distinguishing the description, and are not intended to indicate or imply relative importance.
Referring to fig. 1-7, an embodiment of an aircraft rotor arm folding mechanism of the present invention is specifically illustrated and includes a first support 100 and a second support 200. Wherein the first support 100 has a first abutment surface 102 and the second support 200 has a second abutment surface 203; first support 100 and second support 200 are used for respectively being connected some aircraft rotor support arms, and it is articulated and lock through lockpin 400 through rotation axis 300 between first support 100 and the second support 200 to form fold condition and expansion state, first butt face 102 and second butt face 203 butt, two rotor support arm cooperations form a holistic rotor support arm fold condition, partial rotor support arm overlaps each other so that better accomodating.
The cross-sectional shapes of the first abutting surface 102 and the second abutting surface 203 are generally set, and may adopt a common shape such as a circle, a square, or a circular ring, in the unfolded state, the first abutting surface 102 and the second abutting surface 203 abut against each other and have a top and a bottom corresponding to each other, the first abutting surface 102 is provided with first connecting lugs 101 at both sides, the second abutting surface 203 is provided with second connecting lugs 201 at both sides, the first connecting lug 101 and the second connecting lug 201 on the same side correspond to each other to mount the rotating shaft 300 and the lock pin 400, the lock pin 400 may be pulled away from the first connecting lug 101 and the second connecting lug 201 to form a folded state, the first connecting lug 101 and the second connecting lug 201 for mounting the rotating shaft 300 are always abutted when in the folded state and the unfolded state, the first connecting lug 101 and the second connecting lug 201 for mounting the lock pin 400 are abutted when in the unfolded state, the abutting surfaces of the first engaging lug 101 and the second engaging lug 201 are disposed to be deviated from the center of the first abutting surface 102 and close to the bottom of the first abutting surface 102.
As shown in fig. 5, in the flying state, the folding mechanism is subjected to an upward bending load, a tensile load is generated at the lower portion of each of the first contact surface 102 and the second contact surface 203, and a compressive load is generated at the upper portion of the contact surface, the magnitude of the load depends on the position of the contact surface between the first engaging lug 101 and the second engaging lug 201, and during the flying state, the contact surface between the first engaging lug 101 and the second engaging lug 201 is a shear-receiving surface, and the longer the distance between the shear-receiving surface and the top portion of the first contact surface 102, the longer the arm of the shear force, and the smaller the tensile load and the compressive load. Therefore, the abutting surfaces of the first engaging lug 101 and the second engaging lug 201 are moved downward as much as possible to increase the distance between the abutting surfaces and the top of the first abutting surface 102, thereby reducing the magnitude of the compressive load and improving the overall connection strength of the rotor arm folding piece.
In some embodiments, third engaging lugs 202 are further disposed on two sides of the second abutting surface 203, the second engaging lug 201 is close to the top of the second abutting surface 203, the third engaging lug 202 is close to the bottom of the second abutting surface 203, an accommodating space of the first engaging lug 101 is formed between the third engaging lug 202 and the second engaging lug 201, after the first engaging lug 101 is disposed in the accommodating space, the rotating shaft 300 is disposed to pass through the second engaging lug 201, the first engaging lug 101 and the third engaging lug 202 on the same side, and the locking pin 400 is detachably disposed through the second engaging lug 201, the first engaging lug 101 and the third engaging lug 202.
In the deployed state, the first engaging lug 101 abuts against the second engaging lug 201 and the third engaging lug 202, and the abutting surfaces of the first engaging lug 101 and the third engaging lug 202 are disposed to be offset from the center of the first abutting surface 202 and close to the bottom of the first abutting surface 202, in this embodiment, although there are two shearing surfaces, the shearing surface between the first engaging lug 101 and the third engaging lug 202 bears a main shearing load, and a technical effect of reducing a compression load between the first abutting surface 202 and the second abutting surface 203 can also be achieved, and the provision of the single-double-lug matching structure is significant in reducing the magnitude of the shearing force applied to the rotating shaft 300 and the lock pin 400, and improving the service life thereof.
Further, on the basis of the foregoing embodiment, the thickness of the first engaging lug 101 and the thickness of the second engaging lug 201 are preferably set to be the same, and the thickness of both of them is greater than the thickness of the third engaging lug 202, which not only can further increase the distance between the first engaging lug 101 and the top of the first abutting surface 102, so as to lengthen the moment arm when bearing bending load, improve the overall connection strength of the rotor arm folding member, but also can save material.
In some embodiments, the first engaging lug 101 is provided with a first engaging hole 111, the second engaging lug 201 is provided with a second engaging hole 211, the third engaging lug 202 is provided with a third engaging hole 221, the inner wall of the second engaging hole 211 is provided with a screw thread, the screw thread is provided on a part of or the entire inner wall of the second engaging hole 211, the rotating shaft 300 and the locking pin 400 respectively have a screw thread adapted to the second engaging hole 211 and are engaged with the second engaging hole 211 through a screw thread structure, in an embodiment where the screw thread is provided on a part of the inner wall of the second engaging hole 211, a part of the screw thread is also preferably provided near the top of the second abutting surface 203, the screw thread is disposed on the second engaging hole 211 in a manner that the second engaging lug 201 is near the top of the second abutting surface 203 in an aircraft flight state, the position has small tensile load, the shearing force transmitted to the rotating shaft 300 and the lock pin 400 is small, the stress of a threaded connection part can be effectively reduced, the connection fatigue performance of the rotor wing support arm folding mechanism is improved, and the damage of a threaded structure is avoided.
On the basis of the foregoing embodiment, the present invention is preferably further provided with a bushing 500, wherein the bushing 500 is a hollow tube structure with a smooth inner wall surface, and is disposed in the first connecting hole 111, the third connecting hole 221 and the second connecting hole 211 through interference fit, where no thread is disposed, for matching the rotating shaft with the lock pin 400, the rotating shaft and the lock pin 400 are only provided with threads at a position matched with the second connecting hole 211, and the rest of the rotating shaft and the lock pin 400 are provided with a smooth rod side wall, and are matched with the bushing 500 so as to be rotatably connected with the first connecting lug 101 and the second connecting lug 201.
In some embodiments, the rotating shaft 300 is preferably configured to include a rotating shaft cap 301, a rotating shaft polished rod portion 303, and a rotating shaft threaded portion 302; the rotating shaft thread portion 302 is provided with a thread adapted to the second connecting hole 211, the rotating shaft cap 301 serves as a limit structure of the rotating shaft 300, the rotating shaft thread portion 302 is provided to be in fit connection with the thread in the second connecting hole 211, the rotating shaft polished rod portion 303 is provided to be in fit connection with the inner wall of the second connecting hole 211, which is not provided with a thread, and rotatably connected with the first connecting hole 111 and the third connecting hole 221, the position of the second connecting hole 211, which is not provided with a thread, and the inner wall of the first connecting hole 111, and the inner wall of the third connecting hole 221 can be provided with smooth wall surfaces, so as to be better connected with the rotating shaft polished rod portion 303, it is noted that, in the embodiment provided with the bushing 500, the rotating shaft polished rod portion 303 is provided to be in fit connection with the bushing 500 rotatably.
The rotating shaft thread portion 302 of the rotating shaft 300 can be arranged close to one side of the rotating shaft cap 301, the rotating shaft light rod portion 303 is far away from one side of the rotating shaft cap 301, the diameter of the rotating shaft thread portion 302 is larger than that of the rotating shaft light rod portion 303, the length of the rotating shaft light rod portion 303 is larger than that of the bolt thread rod, the rotating shaft 300 is inserted into the second connecting hole 211 and the first connecting hole 111 from top to bottom and is screwed, and in an embodiment provided with the third connecting hole 221, the third connecting hole 221 needs to be inserted after the first connecting hole 111 is inserted.
Or, the rotating shaft polished rod portion 303 of the rotating shaft 300 is close to the side including the rotating shaft cap 301, the rotating shaft threaded portion 302 is far from the side including the rotating shaft cap 301, the diameter of the rotating shaft threaded portion 302 is smaller than the diameter of the rotating shaft polished rod portion 303, and the length of the rotating shaft polished rod portion 303 is greater than the length of the rotating shaft threaded portion 302, the rotating shaft 300 is inserted into the first connecting hole 111 and the second connecting hole 211 from bottom to top and is screwed, in an embodiment provided with the third connecting hole 221, the third connecting hole 221 needs to be inserted before being inserted into the first connecting hole 111, in other embodiments, the rotating shaft 300 is provided with a nut 304 in a matching manner, and a portion of the rotating shaft 300 extending out of the second connecting hole 211 is provided with a thread, so that the nut 304 can be connected in a matching manner.
In some embodiments, the lock pin 400 is specifically configured to include a lock pin cap 401, a lock pin light bar portion 403, a lock pin thread portion 402, and a lock pin arm 404, wherein the lock pin thread portion 402 is provided with a thread for fitting with the second connection hole 211, the lock pin cap 401 serves as a limiting structure of the lock pin 400, and the lock pin arm 404 is mounted to the lock pin cap 401 or is integrally formed with the lock pin cap 401.
The locking pin thread part 402 may be disposed at a side close to the locking pin cap 401, the locking pin light bar part 403 is disposed at a side far from the locking pin cap 401, the diameter of the locking pin thread part 402 is greater than the diameter of the locking pin light bar part 403, the length of the locking pin light bar part 403 is greater than the length of the locking pin thread part 402, the locking pin 400 is inserted into the second connection hole 211 and the first connection hole 111 from top to bottom and is screwed, and in an embodiment where the third connection hole 221 is disposed, the third connection hole 221 is inserted into the first connection hole 111 and then is inserted into the third connection hole 221.
Or, the locking pin light rod part 403 of the locking pin 400 is close to the side including the locking pin cap 401, the locking pin thread part 402 is far from the side including the locking pin cap 401, the diameter of the locking pin thread part 402 is smaller than that of the locking pin light rod part 403, the length of the locking pin 400 light rod is longer than that of the locking pin thread part 402, the locking pin 400 is inserted into the first connecting hole 111 and the second connecting hole 211 from bottom to top and is screwed, in an embodiment provided with the third connecting hole 221, the locking pin arm 404 is inserted into the third connecting hole 221 before being inserted into the first connecting hole 111, and the locking pin arm 404 is provided in a sense that an operator takes out the locking pin 400, which is installed on the locking pin cap 401, or is an integral molding piece with the locking pin cap 401.
In some embodiments, the aircraft rotor arm folding mechanism provided by the present invention is connected to an aircraft rotor arm through a structural form of a hollow sleeve 600, a cross-sectional shape of the hollow sleeve 600 may be circular or square, and is sleeved with the aircraft rotor arm and fixedly connected by a fastener, and the sleeved manner is an external sleeved manner or an internal sleeved manner, in other embodiments, a protective gasket 700 is provided on an outer side surface of the hollow sleeve 600, and the protective gasket 700 has an inner surface that is attached to an outer surface of the aircraft rotor arm and is disposed on a side of a bolt head where the hollow sleeve 600 is connected to the aircraft rotor arm fastener, so as to protect the outer surface of the aircraft rotor arm from being crushed by the bolt head.
The invention also provides an aircraft rotor wing support arm, which comprises a first support arm, a second support arm and the aircraft rotor wing support arm folding mechanism, wherein the first support arm is connected to the first support 100, and the second support arm is connected to the second support 200, so that the stress performance and the fatigue performance of the folding mechanism can be improved, the structural design is reasonable and compact, the overall weight of the aircraft is effectively reduced, and the aircraft rotor wing support arm folding mechanism has good stability.
It should be noted that the above embodiments can be freely combined as necessary. The above is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and embellishments can be made without departing from the principle of the present invention, and these modifications and embellishments should also be regarded as the protection scope of the present invention.
Claims (10)
1. An aircraft rotor boom folding mechanism, comprising:
the first support is provided with a first abutting surface;
the second support is provided with a second abutting surface;
the first support and the second support are hinged through a rotating shaft and locked through a lock pin to form a folded state and an unfolded state, and in the unfolded state, the first abutting surface abuts against the second abutting surface;
two sides of the first abutting surface are provided with first connecting lugs, two sides of the second abutting surface are provided with second connecting lugs, and the first connecting lugs are used for abutting against the second connecting lugs and matching with the second connecting lugs to install the rotating shaft and the lock pin;
the abutting surfaces of the first connecting lug and the second connecting lug deviate from the center of the first abutting surface and are close to the bottom of the first abutting surface.
2. An aircraft rotor arm folding mechanism according to claim 1,
third connecting lugs are further arranged on two sides of the second abutting-joint surface;
the second connecting lug is close to the top of the second abutting surface, the third connecting lug is close to the bottom of the second abutting surface, and an accommodating space of the first connecting lug is formed between the third connecting lug and the second connecting lug;
in the unfolded state, the first connecting lug abuts against the second connecting lug and the third connecting lug respectively, and abutting surfaces of the first connecting lug and the third connecting lug deviate from the center of the first abutting surface and are close to the bottom of the first abutting surface.
3. An aircraft rotor arm folding mechanism according to claim 2,
the thickness of the first connecting lug is the same as that of the second connecting lug, and the thickness of the first connecting lug and that of the second connecting lug are both larger than that of the third connecting lug.
4. An aircraft rotor arm folding mechanism according to claim 2,
the first connecting lug is provided with a first connecting hole;
the second connecting lug is provided with a second connecting hole;
a third connecting hole is formed in the third connecting lug;
the inner wall of the second connecting hole is provided with threads;
the screw thread is provided to a part of or the entire inner wall of the second connection hole, and the rotation shaft and the locking pin have screw threads adapted to the second connection hole, respectively.
5. An aircraft rotor arm folding mechanism according to claim 4,
the device also comprises a lining;
the bushing is of a hollow pipe structure with a smooth inner wall surface and is arranged in the first connecting hole, the third connecting hole and the second connecting hole in an interference fit mode, and the portion, which is not provided with threads, of the second connecting hole is arranged in the first connecting hole, the third connecting hole and the second connecting hole.
6. An aircraft rotor arm folding mechanism according to any one of claims 1 to 5,
the rotating shaft comprises a rotating shaft cap, a rotating shaft polished rod part and a rotating shaft threaded part;
the rotating shaft thread portion is provided with threads used for being matched with the second connecting hole, and the rotating shaft cap is used as a limiting structure of the rotating shaft.
7. An aircraft rotor arm folding mechanism according to any one of claims 1 to 5,
the lock pin comprises a lock pin cap, a lock pin polished rod part, a lock pin thread part and a lock pin arm;
the lock pin thread part is provided with threads matched with the second connecting hole, the lock pin cap is used as a limit structure of the lock pin, and the lock pin arm is installed on the lock pin cap or is integrally formed with the lock pin cap.
8. An aircraft rotor arm folding mechanism according to any one of claims 1 to 5,
the first support;
and/or
And the second support is provided with a hollow sleeve and is used for being connected with an aircraft rotor support arm.
9. An aircraft rotor arm folding mechanism according to claim 8,
and a protective gasket is arranged on the outer side surface of the hollow sleeve.
10. An aircraft rotor boom, comprising:
a first support arm;
a second support arm;
an aircraft rotor arm folding mechanism according to any one of claims 1 to 7;
the first support arm is connected to the first support, and the second support arm is connected to the second support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210395931.0A CN114671006A (en) | 2022-04-15 | 2022-04-15 | Aircraft rotor support arm folding mechanism and aircraft rotor support arm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210395931.0A CN114671006A (en) | 2022-04-15 | 2022-04-15 | Aircraft rotor support arm folding mechanism and aircraft rotor support arm |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114671006A true CN114671006A (en) | 2022-06-28 |
Family
ID=82077858
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210395931.0A Pending CN114671006A (en) | 2022-04-15 | 2022-04-15 | Aircraft rotor support arm folding mechanism and aircraft rotor support arm |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114671006A (en) |
-
2022
- 2022-04-15 CN CN202210395931.0A patent/CN114671006A/en active Pending
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