Tilt-rotor aircraft elastic bearing fixing taper sleeve mounting mechanism

Abstract

The utility model discloses a tilt-rotor aircraft elastic bearing fixing taper sleeve mounting mechanism in the technical field, which is characterized by comprising a jack mounted in a rack, the rack comprises a support column for connecting a pressing plate and a base, a centrifugal force elastic bearing positioning groove is formed in the bottom of the pressing plate, and a centrifugal force elastic bearing is arranged in the centrifugal force elastic bearing positioning groove. A taper sleeve guide groove is formed in the top of the pressing plate, and a through hole is formed between the elastic bearing positioning groove and the taper sleeve guide groove.

Description

Technical Field

[0001] The utility model relates to the technical field of assembly equipment, in particular to an assembly device for an elastic bearing cone sleeve of a tiltrotor aircraft. Background Art

[0002] In order to solve the problem of speed fluctuation of the metal universal hinge rotor of the early tilt-rotor aircraft, elastic bearings were introduced to solve the problem of speed fluctuation. In the outer variable pitch elastic bearing assembly of the rotor system, such as Figure 5-6 As shown, the outer variable pitch elastic bearing assembly 700 is composed of an outer variable pitch elastic bearing 701, an outer mounting seat bracket 702, a centrifugal force elastic bearing 703, a tapered sleeve 704 and an anti-loosening block 705.

[0003] When installing the tapered sleeve 704, a compression force of up to 100KN needs to be applied to the outer variable pitch elastic bearing 701 and the centrifugal force elastic bearing 703 at the same time. The installer needs to manually install the tapered sleeve 704 into the reserved cavity on the upper part of the outer variable pitch elastic bearing 701 and the centrifugal force elastic bearing 703 in this state. Due to the large compression force, small force application area and limited operating space, there are great safety hazards in the installation process. Utility Model Content

[0004] In view of the deficiencies in the prior art, the utility model provides a mounting mechanism for fixing a tapered sleeve of an elastic bearing of a tiltrotor aircraft, which solves the problem of difficulty in mounting the existing tapered sleeve.

[0005] The purpose of the utility model is achieved as follows: a tilt-rotor aircraft elastic bearing fixed cone sleeve installation mechanism, including a jack installed in a frame, the frame including a support connecting a pressure plate and a base, a centrifugal elastic bearing positioning groove is provided at the bottom of the pressure plate, a cone sleeve guide groove is provided at the top of the pressure plate, and a through hole is provided between the elastic bearing positioning groove and the cone sleeve guide groove.

[0006] Furthermore, a connecting piece for installing an outer variable-pitch elastic bearing assembly is provided on the top of the jack.

[0007] Furthermore, the connecting member includes a top plate installed on the top of the jack, and a pin is provided in the middle of the top plate.

[0008] Furthermore, a boss is provided on the top of the top plate.

[0009] Furthermore, a connecting hole is provided in the centrifugal elastic bearing positioning groove along its axial direction, and a bolt for fixing the centrifugal elastic bearing is provided in the connecting hole.

[0010] Compared with the existing technology, the beneficial effects of the present invention are: the present invention completes the automatic installation of the tapered sleeve through the tapered sleeve guide groove on the pressure plate, the tapered sleeve does not require manual operation during the installation process, and a jack is used for force application during the force application process, and the force application method is stable and reliable. Using this method to install the tapered sleeve of the elastic bearing of the tilt-rotor aircraft can effectively ensure the installation accuracy of the parts and protect the safety of the operator. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0012] Figure 1 This is a schematic diagram of the structure of the utility model.

[0013] Figure 2 This is a schematic diagram of the structure of the medium pressure plate of the utility model.

[0014] Figure 3 This is a cross-sectional view of the medium pressure plate of the present utility model.

[0015] Figure 4 This is a state diagram used in the present utility model.

[0016] Figure 5 Schematic diagram of the structure of the outer variable pitch elastic bearing assembly.

[0017] Figure 6 This is a cross-sectional view of the outer variable pitch elastic bearing assembly.

[0018] Among them, 100 pressure plate, 200 top plate, 201 tapered sleeve guide groove, 202 centrifugal elastic bearing positioning groove, 203 connecting hole, 300 pillar, 400 base, 500 pin shaft, 600 jack, 700 outer variable pitch elastic bearing assembly, 701 outer variable pitch elastic bearing, 702 outer mounting seat bracket, 703 centrifugal elastic bearing, 704 tapered sleeve, 705 anti-loosening block. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0020] like Figure 1-4The illustrated embodiment of a tiltrotor aircraft elastic bearing fixing cone sleeve installation mechanism comprises six parts, namely, a pressure plate 100 , a top plate 200 , a support column 300 , a base 400 , a pin 500 and a jack 600 .

[0021] There are four pressing plate 100 mounting holes at the four corners of the pressing plate 100 for connecting the pressing plate 100 and the pillar 300. There is a centrifugal elastic bearing positioning groove 202 on the lower middle side of the pressing plate 100 for positioning the centrifugal elastic bearing 703, and two connecting holes 203 are used to connect and fix the centrifugal elastic bearing 703; there is a tapered sleeve guide groove 201 on the upper middle side of the pressing plate 100, which is used for positioning and guiding the automatic installation of the tapered sleeve 704 when the tapered sleeve 704 is installed.

[0022] There is a boss structure on the upper part of the top plate 200 for positioning and fixing the top plate 200 and the outer variable pitch elastic bearing 701, preventing the outer variable pitch elastic bearing 701 and the top plate 200 from relative movement during the force application process; a positioning pin hole is provided in the middle of the top plate 200 for inserting the pin shaft 500 to position and fix the elastic bearing; the top plate 200 and the outer variable pitch elastic bearing 701 adopt a clearance fit in the thickness direction to ensure smooth docking of the two parts; a circular groove is provided at the bottom of the top plate 200 for fixing the top rod of the jack 600, preventing the jack 600 and the top rod from relative sliding during the force application process.

[0023] The four pillars 300 are of equal length, and threaded holes are provided at both ends of the pillars 300 for connecting the pillars 300 with the top plate 200 and the base 400, so as to provide sufficient tension to fix the pressure plate 100 during the force application process.

[0024] There are four bottom plate mounting holes at the four corners of the base 400 for connecting the bottom plate to the bottom surface, and four countersunk holes at the middle corresponding to the pressure plate 100 for connecting the bottom plate to the support 300.

[0025] The pin 500 is a cylindrical stepped pin, which is mainly used to assist in positioning and fixing the top plate 200 and the outer variable-pitch elastic bearing 701 to prevent the parts from bending under force during the force application process and causing relative movement.

[0026] The working principle of this embodiment is as follows:

[0027] During the installation process of the rotorcraft elastic bearing cone sleeve 704, the outer variable pitch elastic bearing 701 and the centrifugal elastic bearing 703 can be subjected to force to produce elastic deformation along the axial direction. When the deformation is large enough, the cone sleeve 704 can be installed into the cavity of the outer variable pitch elastic bearing 701 and the centrifugal elastic bearing 703 to fix the outer variable pitch elastic bearing 701 and the centrifugal elastic bearing 703.

[0028] This method uses an installation mechanism to fix the outer variable pitch elastic bearing assembly 700, and places the tapered sleeve 704 in the tapered sleeve guide groove 201 of the pressure plate 100, and uses a force-applying tool such as a jack 600 to apply pressure to the outer variable pitch elastic bearing 701 and the centrifugal force elastic bearing 703, so that they are elastically deformed under the force, and the metal rod part of the outer variable pitch elastic bearing 701 moves upward while the centrifugal force elastic bearing 703 remains stationary. The cavities of the outer variable pitch elastic bearing 701 and the centrifugal force elastic bearing 703 increase with the increase in deformation. When the cavity is large enough, the tapered sleeve 704 slides downward along the inclined surface of the tapered sleeve guide groove 201 on the pressure plate 100 under the influence of gravity to the cavities of the outer variable pitch elastic bearing 701 and the centrifugal force elastic bearing 703, and then the pressure is released to complete the installation of the tapered sleeve 704.

[0029] During this installation process, the operator does not need to perform any operation on the cone sleeve 704 during the entire boosting process. The entire boosting installation process is continuous and stable, which greatly improves the safety and installation quality of the tiltrotor aircraft elastic bearing cone sleeve 704 installation process.

[0030] The above embodiments are only intended to help understand the method and core concept of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from the principles of the present invention, and such improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A tiltrotor aircraft elastic bearing fixed cone sleeve installation mechanism, characterized in that: The invention comprises a jack (600) installed in a frame, wherein the frame comprises a support (300) connecting a pressing plate (100) and a base (400), a centrifugal elastic bearing positioning groove (202) is provided at the bottom of the pressing plate (100), a tapered sleeve guide groove (201) is provided at the top of the pressing plate (100), and a through hole is provided between the elastic bearing positioning groove and the tapered sleeve guide groove (201).

2. The tiltrotor aircraft elastic bearing fixing cone sleeve installation mechanism according to claim 1, characterized in that: A connecting piece for mounting an outer variable-pitch elastic bearing assembly (700) is provided on the top of the jack (600).

3. The tiltrotor aircraft elastic bearing fixing cone sleeve installation mechanism according to claim 2, characterized in that: The connecting member comprises a top plate (200) mounted on the top of the jack (600), and a pin shaft (500) is provided in the middle of the top plate (200).

4. The tiltrotor aircraft elastic bearing fixing cone sleeve installation mechanism according to claim 3, characterized in that: A boss is provided on the top of the top plate (200).

5. A tiltrotor aircraft elastic bearing fixing cone sleeve installation mechanism according to any one of claims 1 to 4, characterized in that: A connecting hole (203) is provided in the centrifugal elastic bearing positioning groove (202) along its axial direction, and a bolt for fixing the centrifugal elastic bearing (703) is provided in the connecting hole (203).

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