阅读说明：本技术 一种易收纳式航空叶片 (Easily accomodate formula aviation blade ) 是由 陈燕 于 2020-11-25 设计创作，主要内容包括：本发明涉及航空零部件技术领域,尤其是一种易收纳式航空叶片,包括锥形导流头和叶片本体。本发明的一种易收纳式航空叶片包括锥形导流头和叶片本体,通过锥形导流头外侧面上开设有用于活动装配叶片本体的侧向收纳槽,通过翻转叶片本体来对其结构进行调节,从而方便改变航空叶片的运行状态,大大降低其空闲收纳状态下的体积占用；叶片本体由中置装配转轴、活动套接在中置装配转轴外侧端的外部叶片和固定在中置装配转轴内侧端的内部限位头组成,通过拉伸外部叶片可以方便叶片本体展开和调节,使其调节和收纳操作简单方便。(The invention relates to the technical field of aviation parts, in particular to an easily-contained aviation blade. The easily-stored aviation blade comprises a conical flow guide head and a blade body, wherein a lateral storage groove for movably assembling the blade body is formed in the outer side surface of the conical flow guide head, and the structure of the aviation blade is adjusted by overturning the blade body, so that the operation state of the aviation blade is conveniently changed, and the volume occupation of the aviation blade in an idle storage state is greatly reduced; the blade body is by put in the assembly pivot, the activity cup joints the outside blade of putting in the assembly pivot outside end and fix and put the inside spacing head of assembly pivot medial extremity in and constitute, can make things convenient for the blade body to expand and adjust through tensile outside blade, makes its regulation and accomodates easy operation convenience.)

1. The utility model provides an easily accomodate formula aviation blade, includes toper dado (1) and blade body (2), characterized by: the outer side surface of the conical flow guide head (1) is provided with a lateral accommodating groove (3) for accommodating a blade body (2), the blade body (2) is movably assembled in the lateral accommodating groove (3) through a transverse rotating shaft, the inner part of the conical flow guide head (1) is fixedly connected with a rotating shaft assembling cylinder (5) of a built-in transmission bearing (4) through a lateral bracket of an integrated structure, the outer side surface of the rotating shaft assembling cylinder (5) is provided with an inner side limiting jack (6), the inner side surface of the lateral accommodating groove (3) is provided with an outer side limiting jack (7) matched with the inner side limiting jack (6), the blade body (2) comprises a middle assembly rotating shaft (8) movably assembled in the lateral accommodating groove (3) through the transverse rotating shaft, an outer blade (9) movably sleeved at the outer side end of the middle assembly rotating shaft (8) and an inner side limiting head (10) fixed at the inner side end of the middle assembly rotating shaft (8), the outer side surface of the conical flow guiding head (1) is located on two sides of the lateral containing groove (3) and is provided with lateral guide grooves (11), the lower end of the blade body (2) is provided with an internal thread assembling pipe (12) of an integral structure matched with the lateral guide grooves (11), the inner arc surface of the inner side of the conical flow guiding head (1) is provided with an inner locking hole communicated with the inner side of the lateral guide grooves (11), the inner locking hole is internally inserted with an inner fastening bolt (13) matched with the internal thread assembling pipe, and the outer side surface of the transmission bearing (4) is provided with a lateral limiting clamping groove matched with an inner limiting head (10).

2. An easily stowable aircraft blade according to claim 1 wherein: the outer blade (9) near the middle assembly rotating shaft (8) connecting end outer side surface is provided with an arc assembly surface matched with the conical diversion head (1), and the arc assembly groove of the outer blade (9) and the outer arc surface of the conical diversion head (1) are provided with conical surfaces which are meshed with each other.

3. An easily stowable aircraft blade according to claim 1 wherein: the lateral containing groove (3) is provided with a lateral telescopic groove internally provided with an elastic lateral extrusion block (14), and the lateral containing groove is far away from the inner side surface of the elastic lateral extrusion block (14) and is provided with a lateral containing groove.

4. An easily stowable aircraft blade according to claim 1 wherein: the movable assembling type blade assembly is characterized in that an internal assembling jack (15) used for movably assembling the middle assembling rotating shaft (8) is arranged inside the external blade (9), an annular limiting adjusting groove (16) is formed in the inner side face of the internal assembling jack (15), and an integrated structure external limiting head (17) is arranged at the top end of the outer side of the middle assembling rotating shaft (8) and is positioned inside the annular limiting adjusting groove (16).

5. An easily stowable aircraft blade according to claim 4 wherein: the middle assembling rotating shaft (8) is internally provided with an internal telescopic cavity (20) internally provided with a first external thread telescopic rod (18) and a second external thread telescopic rod (19), the internal limiting head (10) and the external limiting head (17) are internally provided with a lateral telescopic through hole communicated with the internal telescopic cavity (20), and the outer ends of the first external thread telescopic rod (18) and the second external thread telescopic rod (19) are provided with internal telescopic ejector rods (21) protruding towards the lateral telescopic through hole.

6. An easily stowable aircraft blade according to claim 5 wherein: the outer side of the middle assembly rotating shaft (8) is provided with an outer annular adjusting groove (23) internally provided with an external manual control adjusting ring (22), the inner side of the outer annular adjusting groove (23) is provided with an inner transmission cavity communicated with the inner telescopic cavity (20), and the inner transmission cavity is movably provided with a thread adjusting rod (24).

7. An easily stowable aircraft blade according to claim 7 wherein: the outer side surface of the external manual control adjusting ring (22) is provided with an external hexagonal control groove.

Technical Field

The invention relates to the technical field of aviation parts, in particular to an easily-contained aviation blade.

Background

Aviation, a complex and strategic human activity. The aircraft is flying (sailing) in the earth atmosphere (air space), and related fields such as scientific research and education, industrial manufacturing, public transportation, professional operation, aviation movement, national defense and military, government management and the like. By the use of air space and aircraft (aeronautical vehicles), aviation activities can be subdivided into a number of independent industries and fields, typically aeronautical manufacturing, civil aviation, and the like. People can often see that the word is used from each field, and the content is extremely rich and varied.

Aircraft, also known as aircraft, that engage in flight activities are classified into lighter-than-air aircraft and heavier-than-air aircraft. The former is lifted by air static buoyancy, such as balloons and airships, and the latter is lifted by aerodynamic force generated by relative motion with air, such as airplanes and helicopters. According to whether manned, can be divided into unmanned aerial vehicle and unmanned aerial vehicle.

Aviation blade on the aircraft is the important power equipment spare part of aircraft, and traditional aviation blade single structure is fixed, and is unable folding, and it is big to lead to structural space to occupy under the idle state, accomodates very inconveniently.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: in order to solve the problem that exists among the above-mentioned background art, provide an easy formula aviation blade of accomodating of modified, it is fixed to solve traditional aviation blade single structure, and is unable folding, leads to structural space under the idle state to occupy greatly, accomodates very inconvenient problem.

The technical scheme adopted by the invention for solving the technical problems is as follows: an easily-contained aviation blade comprises a conical flow guide head and a blade body, wherein a lateral containing groove for containing the blade body is formed in the outer side surface of the conical flow guide head, the blade body is movably assembled in the lateral containing groove through a transverse rotating shaft, a rotating shaft assembling cylinder with a built-in transmission bearing is fixedly connected in the conical flow guide head through a lateral support in an integrated structure, an inner limiting jack is formed in the outer side surface of the rotating shaft assembling cylinder, an outer limiting jack matched with the inner limiting jack is formed in the inner side surface of the lateral containing groove, the blade body comprises a middle assembling rotating shaft movably assembled in the lateral containing groove through the transverse rotating shaft, an outer blade movably sleeved at the outer side end of the middle assembling rotating shaft and an inner limiting head fixed at the inner side end of the middle assembling rotating shaft, the outer side surface of the conical flow guide head is positioned at two sides of the lateral containing groove and provided with lateral guide grooves, the lower end of the blade body is provided with an integral structure internal thread assembly pipe matched with the side guide groove, the inner side arc-shaped surface of the conical flow guide head is provided with an inner locking hole communicated with the inside of the side guide groove, the inner locking hole is internally inserted with an inner side fastening bolt matched with the internal thread assembly pipe, and the outer side surface of the transmission bearing is provided with a lateral limiting clamping groove matched with the inner limiting head.

The outer blade near-middle assembly rotating shaft connecting end outer side face is provided with an arc assembly face matched with the conical flow guide head, and the arc assembly groove of the outer blade and the outer arc face of the conical flow guide head are provided with mutually meshed conical faces.

The lateral containing groove is provided with a lateral telescopic groove internally provided with an elastic lateral extrusion block, and the lateral containing groove is far away from the inner side surface of the elastic lateral extrusion block and is provided with a lateral containing groove.

The outer blade is internally provided with an internal assembly jack for movably assembling a middle assembly rotating shaft, the inner side surface of the internal assembly jack is provided with an annular limiting adjusting groove, and the top end of the outer side of the middle assembly rotating shaft is positioned in the annular limiting adjusting groove and is provided with an integrated structure outer limiting head.

The middle assembly rotating shaft is internally provided with an internal telescopic cavity internally provided with a first external thread telescopic rod and a second external thread telescopic rod, the internal limiting head and the external limiting head are internally provided with a lateral telescopic through hole communicated with the internal telescopic cavity, and the outer side ends of the first external thread telescopic rod and the second external thread telescopic rod are provided with internal telescopic ejector rods protruding towards the lateral telescopic through hole.

The outer side surface of the middle assembly rotating shaft is provided with an outer annular adjusting groove internally provided with an external manual control adjusting ring, the inner side surface of the outer annular adjusting groove is provided with an internal transmission cavity communicated with the internal telescopic cavity, and the internal transmission cavity is movably provided with a thread adjusting rod.

The outer side surface of the external manual control adjusting ring is provided with an outer hexagonal control groove.

The invention has the beneficial effects that:

(1) the easily-stored aviation blade comprises a conical flow guide head and a blade body, wherein a lateral storage groove for movably assembling the blade body is formed in the outer side surface of the conical flow guide head, and the structure of the aviation blade is adjusted by overturning the blade body, so that the operation state of the aviation blade is conveniently changed, and the volume occupation of the aviation blade in an idle storage state is greatly reduced;

(2) the blade body consists of a middle assembly rotating shaft, an external blade movably sleeved at the outer side end of the middle assembly rotating shaft and an internal limiting head fixed at the inner side end of the middle assembly rotating shaft, and the blade body can be conveniently unfolded and adjusted by stretching the external blade, so that the adjustment and the storage operation are simple and convenient;

(3) install outside manual adjustable ring on the outside annular adjustment groove in the middle assembly pivot outside, utilize outside manual adjustable ring control external screw thread telescopic link and inside flexible ejector pin to put the inside flexible of assembly pivot in, cooperation blade body lower extreme has with inboard fastening bolt matched with body structure internal thread assembly pipe to promote the storage and assembly stability and the firmness of blade body, the operation is very simple and convenient.

Drawings

The invention is further illustrated with reference to the following figures and examples.

Fig. 1 is a schematic structural view of the present invention.

Fig. 2 is a cross-sectional view of the interior of the conical flow directing head of the present invention.

Fig. 3 is a structural sectional view of a blade body in the present invention.

Detailed Description

The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic views illustrating only the basic structure of the present invention in a schematic manner, and thus show only the constitution related to the present invention.

An aviation blade easy to be accommodated as shown in fig. 1, fig. 2 and fig. 3 comprises a conical flow guiding head 1 and a blade body 2, wherein a lateral accommodating groove 3 for accommodating the blade body 2 is formed on the outer side surface of the conical flow guiding head 1, the blade body 2 is movably assembled in the lateral accommodating groove 3 through a transverse rotating shaft, a rotating shaft assembling cylinder 5 with a built-in transmission bearing 4 is fixedly connected in the conical flow guiding head 1 through a lateral bracket of an integrated structure, an inner limiting jack 6 is formed on the outer side surface of the rotating shaft assembling cylinder 5, an outer limiting jack 7 matched with the inner limiting jack 6 is formed on the inner side surface of the lateral accommodating groove 3, the blade body 2 comprises a middle assembling rotating shaft 8 movably assembled in the lateral accommodating groove 3 through the transverse rotating shaft, an outer blade 9 movably sleeved at the outer side end of the middle assembling rotating shaft 8 and an inner limiting head 10 fixed at the inner side end of the middle assembling rotating shaft 8, the lateral surface of the conical flow guide head 1 is located on the two sides of the lateral containing groove 3 and is provided with a lateral guide groove 11, the lower end of the blade body 2 is provided with an internal thread assembling pipe 12 of an integral structure matched with the lateral guide groove 11, an internal locking hole communicated with the inside of the lateral guide groove 11 is formed in the inner arc-shaped surface of the conical flow guide head 1, an internal fastening bolt 13 matched with the internal thread assembling pipe 12 is inserted into the internal locking hole, and a lateral limiting clamping groove matched with the internal limiting head 10 is formed in the lateral surface of the transmission bearing 4.

Example (b): the outer blade 9 is pulled out, the outer blade 9 is turned over, the female screw fitting pipe 12 is inserted along the side guide groove 11 to above the inner locking hole, and the outer blade 9 is fixed to the outside of the tapered flow guiding head 1 by screwing the female screw fitting pipe 12 with the inner fastening bolt 13. The flow direction of the outer blade 9 when rotating can be changed by only changing the adjustment angle of the outer blade 9.

Further, in order to promote the structural stability under assembly and the expansion state, set up on the nearly well-placed assembly pivot 8 link lateral surface of outside blade 2 and lead the first 1 matched with arc assembly surface of toper, intermeshing's conical surface is seted up to the arc assembly groove of outside blade 2 and the first 1 outside arc surface of toper conductance, furthermore, in order to reduce the windage, promote and accomodate stability, set up the flexible groove of side direction of built-in elasticity side direction extrusion piece 14 on the 3 medial surfaces of side direction accomodate groove, the side direction is accomodate groove 3 and is kept away from and has been seted up the side direction and accomodate the groove on the elasticity side direction extrusion piece 14 medial surface.

Furthermore, in order to match with telescopic adjustment and limiting, an inner assembly jack 15 for movably assembling the middle assembly rotating shaft 8 is arranged inside the outer blade 9, an annular limiting adjusting groove 16 is arranged on the inner side surface of the inner assembly jack 15, the top end of the outer side of the middle assembly rotating shaft 8, which is positioned inside the annular limiting adjusting groove 16, is provided with an integral structure outer limiting head 17, and further, in order to facilitate thread adjustment, be used for promoting assembly firmness and stability, in put 8 inside flexible cavities 20 of seting up built-in first external screw thread telescopic link 18 and the second external screw thread telescopic link of assembly pivot, inside limit head 10 and the inside side direction flexible through-hole that is linked together with inside flexible cavity 20 of seting up of outside limit head 17, first external screw thread telescopic link 18 and the 19 outside ends of second external screw thread telescopic link have to the inside bellied inside flexible ejector pin 21 of the flexible through-hole of side direction.

Further, for external transmission control, an outer annular adjusting groove 23 with a built-in external manual control adjusting ring 22 is formed in the outer side surface of the middle assembling rotating shaft 8, an inner transmission cavity communicated with the inner telescopic cavity 20 is formed in the inner side surface of the outer annular adjusting groove 23, a threaded adjusting rod 24 is movably assembled in the inner transmission cavity, and further, an outer hexagonal control groove is formed in the outer side surface of the external manual control adjusting ring 22 for external control.

The middle section of the thread adjusting rod 24 shown in fig. 3 is a transverse adjusting tooth surface, two ends of the thread adjusting rod are thread adjusting tooth surfaces respectively meshed with the first external thread telescopic rod 18 and the second external thread telescopic rod 19, a transverse meshed tooth surface meshed with the transverse adjusting tooth surface is arranged on the inner side surface of the external manual control adjusting ring 22, the external manual control adjusting ring 22 is meshed with the transverse adjusting tooth surface on the thread adjusting rod 24 through the transverse meshed tooth surface, and the first external thread telescopic rod 18 and the second external thread telescopic rod 19 are controlled to reversely stretch out and draw back in the middle assembling rotating shaft 8 by rotating the external manual control adjusting ring 22.

The easily-contained aviation blade comprises a conical flow guiding head 1 and a blade body 2, wherein a lateral containing groove 3 for movably assembling the blade body 2 is formed in the outer side surface of the conical flow guiding head 1, and the structure of the aviation blade is adjusted by turning over the blade body 2, so that the operation state of the aviation blade is conveniently changed, and the volume occupation of the aviation blade in an idle containing state is greatly reduced; the blade body 2 consists of a middle assembly rotating shaft 8, an external blade 9 movably sleeved at the outer side end of the middle assembly rotating shaft 8 and an internal limiting head 10 fixed at the inner side end of the middle assembly rotating shaft 8, and the blade body 2 can be conveniently unfolded and adjusted by stretching the external blade 9, so that the adjustment and the storage operation are simple and convenient; install outside manual adjustable ring 22 on the outside annular adjustment groove 23 of putting in the assembly pivot 8 outside, utilize outside manual adjustable ring 22 control external screw thread telescopic link and inside flexible ejector pin 21 to put in the assembly pivot 8 inside flexible, cooperate 2 lower extremes of blade body have with inboard fastening bolt 13 matched with body structure internal thread assembly pipe 12 to promote accomodating and assembly stability and the firmness of blade body 2, the operation is very simple and convenient.

In light of the foregoing description of the preferred embodiment of the present invention, many modifications and variations will be apparent to those skilled in the art without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.