CN112453963A

CN112453963A - Helicopter blade bore hole erection equipment

Info

Publication number: CN112453963A
Application number: CN202011393569.0A
Authority: CN
Inventors: 李懿; 叶凯; 孙涛; 杨威; 蒋振坤
Original assignee: Hefei Lianhe Airplane Technology Co ltd
Current assignee: Hefei Lianhe Airplane Technology Co ltd
Priority date: 2020-12-03
Filing date: 2020-12-03
Publication date: 2021-03-09

Abstract

The invention discloses a helicopter blade boring installation device which comprises a bottom frame, wherein a blade root base is installed at the left end of the bottom frame, a blade tip base is installed at the right end of the bottom frame, blades are detachably and fixedly installed between the blade root base and the blade tip base through a blade root clamp, and the blades are arranged along the length direction of the bottom frame. The invention has the beneficial effects that: the installation, processing, allotment of relevant subassembly are carried out on the chassis, and this frock can be installed, dismantled on the empty door milling machine, can improve equipment's rate of utilization, practices thrift the cost (traditional helicopter paddle is the paddle mostly needs a set of dedicated frock and equipment, and rate of equipment utilization is low). In addition, through the location of polylith anchor clamps, can fix the relative position of paddle to guarantee the angle of airfoil profile, this aerodynamic effect when directly influencing the paddle and rotating.

Description

Helicopter blade bore hole erection equipment

Technical Field

The invention relates to the technical field of helicopter blades, in particular to a boring installation device for a helicopter blade.

Background

The blade is an important component of a helicopter rotor system, ensures the manufacturing quality and the processing precision of the blade, and is an important guarantee for the flight performance and the safety of the helicopter. The boring of the blade root bushing after the blade is formed is a process which is crucial to the blade, and how to complete the high-standard process with low cost and high efficiency is always the direction of research in the industry.

The traditional helicopter blade boring tool is a fixed tool and a boring machine, one type of blade needs to be specially provided with one boring machine and one boring tool, and the equipment utilization rate is very low.

Disclosure of Invention

The invention aims to provide a helicopter blade boring installation device, wherein related components are installed, processed and allocated on a chassis, and the tool can be installed and disassembled on an empty door milling machine, so that the utilization rate of the device can be improved, and the cost is saved; through the location of polylith anchor clamps, can fix the relative position of paddle to guarantee the angle of airfoil profile, this aerodynamic effect when directly influencing the paddle and rotating.

The technical scheme of the invention is realized as follows:

the utility model provides a helicopter paddle bore hole erection equipment, includes the chassis, the root base is installed to the chassis left end, the oar point base is installed to the chassis right-hand member, the left end of fixed mounting paddle can be dismantled through the root anchor clamps to the root base surface, the right-hand member of paddle passes through the detachable fixed mounting of oar point base, the paddle is arranged along the length direction of chassis.

Further, the oar root anchor clamps include the reference surface of setting in oar root base upper end, the leading flank and the trailing flank of reference surface are installed first fine setting piece and second fine setting piece through the bolt correspondence, the paddle left end extends to in the reference surface and extends to between first, two fine setting pieces.

Further, the paddle root fixture further comprises a third fine adjustment block matched with the paddle, the third fine adjustment block is arranged on the left side face of the reference surface, and a paddle root pressing plate matched with the top face of the left end of the paddle is arranged on the surface of the reference surface.

Furthermore, a waist-shaped groove is formed in the surface of the paddle root pressing plate.

Further, an airfoil section base is further arranged on the bottom frame, the airfoil section base is close to the propeller root base, and an airfoil section clamp matched with the propeller blade is installed at the upper end of the airfoil section base.

Further, a blade tip clamp matched with the blade is arranged at the upper end of the blade tip base.

The invention has the beneficial effects that: the installation, processing, allotment of relevant subassembly are carried out on the chassis, and this frock can be installed, dismantled on the empty door milling machine, can improve equipment's rate of utilization, practices thrift the cost (traditional helicopter paddle is the paddle mostly needs a set of dedicated frock and equipment, and rate of equipment utilization is low). In addition, through the location of polylith anchor clamps, can fix the relative position of paddle to guarantee the angle of airfoil profile, this aerodynamic effect when directly influencing the paddle and rotating.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a front view of a helicopter blade bore hole mounting apparatus;

FIG. 2 is a schematic structural view of a helicopter blade bore hole mounting apparatus;

fig. 3 is an enlarged view of a portion a in fig. 2.

Fig. 4 is an enlarged view of fig. 2 with the root pressure plate removed at a.

In the figure:

1. a chassis; 2. a paddle root base; 3. an airfoil section base; 4. a tip base; 5. a paddle root clamp; 6. an airfoil section clamp; 7. a blade tip clamp; 8. a paddle; 51. a bolt; 52. a second trimming block; 53. a first trimming block; 54. a reference plane; 55. a paddle root pressing plate; 56. a third trimming block; 57. a waist-shaped groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

According to an embodiment of the present invention, a helicopter blade bore hole mounting apparatus is provided.

Referring to fig. 1-3, the helicopter blade boring installation equipment according to the embodiment of the invention comprises a chassis 1, wherein a blade root base 2 is installed at the left end of the chassis 1, a blade tip base 4 is installed at the right end of the chassis 1, one end of a blade 8 is detachably and fixedly installed on the surface of the blade root base 2 through a blade root clamp 5, the other end of the blade 8 is detachably and fixedly installed through the blade tip base 4, and the blade 8 is arranged along the length direction of the chassis 1.

Further, the blade root clamp 5 comprises a reference surface 54 arranged at the upper end of the blade root base 2, a first fine adjustment block 53 and a second fine adjustment block 52 are correspondingly arranged on the front side surface and the rear side surface of the reference surface 54 through bolts 51, and the left end of the blade 8 extends into the reference surface 54 and extends between the first fine adjustment block 53 and the second fine adjustment block 52.

Further, the root fixture 5 further comprises a third fine tuning block 55 matched with the blade 8, the third fine tuning block is arranged on the left side face of the reference plane 54, and a root pressing plate 55 matched with the top face of the left end of the blade 8 is arranged on the surface of the reference plane 54.

Further, a waist-shaped groove 57 is arranged on the surface of the paddle root pressure plate 55.

Further, an airfoil section base 3 is further arranged on the underframe 1, the airfoil section base 3 is close to the propeller root base 2, and an airfoil section clamp 6 matched with the propeller blade 8 is installed at the upper end of the airfoil section base 3.

Further, a blade tip clamp 7 matched with the blade 8 is arranged at the upper end of the blade tip base 4.

Specifically, the bottom feet of the underframe 1 are contacted with a tooling table of a gantry mill, 12 bottom foot planes are processed by the gantry mill once after welding in order to ensure good fitting property with the tooling table, the turnover bottom feet of the underframe are placed downwards after processing, and the gap between the bottom feet and the tooling table of the gantry mill is not more than 0.02 mm; a paddle root base: after the installation plane of the paddle root clamp, the base of the same-wing section, the base of the paddle tip and the chassis are welded, the assembly is finished by one-time processing by using a gantry mill; base of the wing section: after the installation plane, the same propeller root base, the propeller tip base and the underframe of the airfoil section clamp are welded, the installation plane, the same propeller root base, the propeller tip base and the underframe are machined at one time by using a gantry mill; a blade tip base: after the mounting plane of the blade tip clamp, the same blade root base, the wing section base and the chassis are welded, the blade tip clamp is machined by a gantry mill in one step; a paddle root clamp: the fixing clamp at the blade root position, X, Y, Z three coordinate directions can play a role in fixing the blade; wing section anchor clamps: the front edge of the blade is attached to a tool, and is fixed in the Z-axis direction; blade tip clamp: the mounting fixture of paddle point portion, the laminating of frock is laminated with to the paddle front edge, and the Z axle direction is fixed.

Firstly, the blade 8 is placed on the tool of the chassis 1, the wing section clamp 6 and the blade tip clamp 7 are used for fixing in the Z-axis direction, then a dial indicator on a machine tool spindle is used for dotting a reference surface from a bushing to a blade root sliding block, and a fine adjustment block is used for fine adjustment in the blade root X, Y axis direction, so that the root of the blade 8 is completely fixed through the blade root pressing plate 55 after the front edges of the blade 8 at the wing section clamp 6 and the blade tip clamp 7 are completely attached to the tool in the process. The clamping process is finished, and boring can be performed.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims

1. The helicopter blade boring installation equipment is characterized by comprising an underframe (1), wherein a blade root base (2) is installed at the left end of the underframe (1), a blade tip base (4) is installed at the right end of the underframe (1), the left end of a blade (8) which is fixedly installed on the surface of the blade root base (2) in a detachable mode through a blade root clamp (5) is arranged at the left end of the blade root base, the right end of the blade (8) is fixedly installed in a detachable mode through the blade tip base (4), and the blade (8) is arranged in the length direction of the underframe (1).

2. A helicopter blade bore hole mounting arrangement according to claim 1 wherein the root clamp (5) includes a datum surface (54) disposed at the upper end of the root base (2), the front and rear sides of the datum surface (54) having correspondingly mounted thereon a first vernier block (53) and a second vernier block (52) by means of bolts (51), the left end of the blade (8) extending into the datum surface (54) and between the first and second vernier blocks (53, 52).

3. A helicopter blade bore mounting apparatus according to claim 2, wherein said root fixture (5) further comprises a third vernier block (55) which mates with the blade (8), said third vernier block being disposed on the left side of the datum surface (54), the surface of said datum surface (54) being provided with a root pressure plate (55) which mates with the top surface of the left end of the blade (8).

4. A helicopter blade bore hole mounting apparatus according to claim 3, wherein the root pressure plate (55) is provided with a waist-shaped groove (57) on its surface.

5. A helicopter blade boring installation arrangement according to any one of claims 1 to 4 wherein an airfoil section mount (3) is further provided on the base frame (1), said airfoil section mount (3) being adjacent the root mount (2), the upper end of said airfoil section mount (3) being fitted with an airfoil section clamp (6) for engagement with a blade (8).

6. A helicopter blade bore hole mounting arrangement according to claim 1, wherein the tip mount (4) is provided at its upper end with a tip clamp (7) for engagement with a blade (8).