CN104880277A - Main blade connecting arm for test table - Google Patents
Main blade connecting arm for test table Download PDFInfo
- Publication number
- CN104880277A CN104880277A CN201510249260.7A CN201510249260A CN104880277A CN 104880277 A CN104880277 A CN 104880277A CN 201510249260 A CN201510249260 A CN 201510249260A CN 104880277 A CN104880277 A CN 104880277A
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- linking arm
- hole
- blade
- mounting hole
- axle
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- Turbine Rotor Nozzle Sealing (AREA)
- Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
Abstract
The invention discloses a main blade connecting arm for a test table. The main blade connecting arm is divided into two parts including a connection arm (1) and a blade mounting pin. The connecting arm (1) is provided with a propeller hub mounting hole, a blade mounting hole and a yaw damper mounting hole. The blade mounting pin includes a shaft (2), a brake pin (201), a brake block (202), a spring (203), a slide block (204), a pin (205). According to the invention, a new blade can be mounted on a prior propeller hub in a transitional manner and no re-design of the propeller hub is needed. Therefore, time for refitting a rotor wing system of a blade dynamic balance test table can be saved by half.
Description
Technical field
The invention belongs to Helicopter Main blade inspection field, be specifically related to the main blade linking arm of a kind of testing table.
Background technology
Main blade dynamic balance test stand is proving installation Helicopter Main blade being carried out to transient equilibrium inspection, and the parts that itself and main blade carry out being connected are propeller hub, and the form of propeller hub joint determines the kind of Helicopter Main blade.For main blade dynamic balancing measurement, adopt three blades to load, three blades are respectively standard blade, chaperonage blade and blade to be detected simultaneously.Only the main blade of a slice is detected, by contrasting the measurement data of main blade to be measured and standard blade at every turn.And the helicopter in modern times is all the main blade of employing more than 4 usually.So when building main blade dynamic balance test stand, the rotor system to testing table is installed is needed to reequip or redesign, to adapt to the type of this model Helicopter Main blade.If directly adopt the rotor system of helicopter rotor system as testing table of other models three blades, the joint form of the rotor hub of this model helicopter rotor system is different from the joint form of main propeller shank to be measured, directly cannot install and use, also need to design propeller hub.
Rotor system propeller hub one end is arranged in rotor shaft, rotates with rotor shaft, and one end is used for installing main blade, drives main blade to rotate.In rotor wing rotation process, main blade produces huge centrifugal force, propeller hub is subject to the centrifugal action of blade, very strict requirement is had to the stiffness and strength of propeller hub joint, redesign joint form to need to carry out strength/rigidity test, whether detection tabs form can bear the huge centrifugal force that main blade produces, and cost consuming time is higher.
Summary of the invention
The helicopter rotor system choosing a three rotors is optimal design proposal as main blade dynamic balance test stand rotor system, but the propeller hub connecting rotor but needs to change, to be applicable to the joint form of up-to-date main blade, also need to calculate the rigidity of propeller hub simultaneously, produce huge vibration etc. in order to avoid install in new blade rotary course.Propeller hub change needs to redesign joint form, and also need to settle accounts the material of propeller hub and the stiffness and strength of joint form, workload is larger simultaneously.
In order to avoid the change of propeller hub, the intensity of former propeller hub meet new blade require time, increase the connection that a linking arm realizes new blade and propeller hub.
Therefore, the invention provides a kind of blade linking arm, for the connection of transition lifting airscrew head and new blade, and be furnished with two blade mount pins.
Consider the problems referred to above of prior art, according to an aspect disclosed by the invention, the present invention by the following technical solutions:
The main blade linking arm of testing table of the present invention, is mainly used to the connection of transition three propeller hub helicopter rotor system and new blade, is divided into two parts: linking arm (1) and blade mount pin.
Linking arm (1) is formed by one piece of intermetallic composite coating, and one end of linking arm (1) is arranged on propeller hub, according to the propeller hub mounting hole of blade mounting hole processing same size on linking arm (1) of propeller hub; According to the size of blade mounting hole to be measured, the blade mounting hole that processing two is through on the middle part of linking arm 1; According to the mounting hole size of shimmy-damper, process a through shimmy-damper mounting hole at the other end of linking arm (1).
Blade mount pin is made up of 6 parts: axle (2), banking pin (201), brake block (202), spring (203), slide block (204), safety pin (205), wherein banking pin (201), brake block (202), spring (203), slide block (204), safety pin (205) is all arranged on axle (2).
The main blade linking arm of testing table of the present invention, by installing blade linking arm, can make new blade transition be installed to original propeller hub, need not redesign propeller hub, saves the blade dynamic balance test stand rotor system repacking time over half.
Accompanying drawing explanation
Fig. 1 blade linking arm schematic diagram
Fig. 2 linking arm front schematic view
Fig. 3 linking arm A-A cut-open view
Fig. 4 lining 102 schematic diagram
Fig. 5 blade mount pin schematic diagram
Fig. 6 axle schematic diagram
Fig. 7 axle A-A cut-open view
Fig. 8 banking pin schematic diagram
Fig. 9 brake block schematic diagram
Figure 10 spring schematic diagram
Figure 11 slide block schematic diagram
Figure 12 slide block B is to attempting
Figure 13 slide block A-A cut-open view
Wherein, the name corresponding to the Reference numeral in accompanying drawing is called:
1-linking arm; 2-axle; The little lining of 101-; 102-Large lining; 201-banking pin; 202-brake block; 203-spring; 204-slide block; 205-safety pin.
Embodiment
Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited thereto.
As Fig. 1-13 of the present invention, the main blade linking arm of testing table of the present invention, is mainly used to the connection of transition three propeller hub helicopter rotor system and new blade, is divided into two parts: linking arm (1) and blade mount pin:
Linking arm (1) is formed by one piece of intermetallic composite coating, one end of linking arm (1) is arranged on propeller hub, according to the propeller hub mounting hole of blade mounting hole processing same size on linking arm (1) of propeller hub, install to adapt to propeller hub, the upper and lower two surperficial corners of linking arm (1) propeller hub mounting hole need to have a certain degree with linking arm (1) surface; According to the size of blade mounting hole to be measured, the blade mounting hole that processing two is through on the middle part of linking arm 1, the size of blade mounting hole is with blade mounting hole size to be measured; According to the mounting hole size of shimmy-damper, a through shimmy-damper mounting hole is processed at the other end of linking arm (1), install to adapt to shimmy-damper, the upper and lower two surperficial corners of linking arm (1) shimmy-damper mounting hole need to have a certain degree with linking arm (1) surface; In order to ensure that linking arm (1) does not collide with propeller hub with the position of propeller hub installation place, simultaneously also in order to the installation of propeller shank and shimmy-damper, six planes are processed in the surrounding of linking arm (1) shimmy-damper mounting hole, make blade install the corresponding plane in side;
According to the size of the upper propeller hub mounting hole of linking arm (1), abrasive rubber materials processing two little linings (101) are used to be arranged on the both sides of linking arm (1) propeller hub mounting hole, wearing and tearing to bearing pin when protection propeller hub and linking arm (1) relatively rotate, use fluid sealant in both cooperation places simultaneously;
According to the size of the upper shimmy-damper mounting hole of linking arm (1), process two metal Large linings (102), the interior shaft size of Large lining (102) is with shimmy-damper mounting hole size, and Large lining (102) is installed inside linking arm;
Blade mount pin is made up of 6 parts: axle (2), banking pin (201), brake block (202), spring (203), slide block (204), safety pin (205), wherein banking pin (201), brake block (202), spring (203), slide block (204), safety pin (205) is all arranged on axle (2);
Axle (2) entirety is right cylinder, come off from the bottom of mounting hole to prevent blade mount pin, the diameter at the top of axle (2) is than body diameter bigger formation bayonet socket, cut away the part at top along the edge of cylinder simultaneously, form a boss, blade mount pin for convenience detach; Diametrically process a groove at the top of axle (2), be convenient to blade is installed; The main body that axle (2) is blade mount pin; Spring (203) and slide block (204) are all along the exhibition of axle (2) to motion, a deep hole is processed in the inside of axle (2), and sentence at deep hole 1/2nd diameter being greater than deep hole and process outward, form the deep hole of a stairstepping, ladder place for stopping spring (203), the resilient support slided up and down by spring (203) of slide block (204); Banking pin (201) and brake block (202) all play barrier effect; A cross through hole is processed and with convex rank, the size of the same banking pin of diameter (201) and brake block (202) in the bottom of axle (2); Safety pin (205) be string in the through hole of axle (2) and slide block (204), a fixation;
Spring (203) is arranged on the inside of axle (2), for slide block (204) provides elastic force, so that slide block (204) has enough elastic force to slide up and down, there is certain gap in the hole of the size of spring (203) and the inside of axle (2), facilitates the motion of slide block (204);
Slide block (204) is arranged on the inside of axle (2), the internal diameter size of its diameter co-axial (2), slide block (204) with end face mid point for the center of circle processes vertical through hole, slide up and down for the ease of slide block (204), a slotted hole is had in its side, this slotted hole is inserted in one end of banking pin (201), coming off of anti-limited slip block (204), simultaneously in order to keep the overhang of slide block (204) minimum, process the slotted hole of the quadrant of one 90 ° along axis in slotted hole one end, rotary slider, banking pin (201) is just stuck in this slotted hole place, the continuation campaign of anti-limited slip block (204), in order to the installation of safety pin (205), in close bottom, process a cross through hole by vertical through hole,
Brake block (202) entirety is right cylinder, size two is dimensioned to according to axle (2) through hole semi-circular at right cylinder two ends, brake block (202) is arranged in cross through hole, outwardly, brake block (202) ladder place blocks mutually with convex rank in roundlet one end;
Banking pin (201) adopts intermetallic composite coating to form, overall one-tenth one stepped right cylinder, banking pin (201) left end is a rounded nose, right-hand member is a column part, the diameter of column part is 2 times of rounded nose diameter, length accounts for banking pin (201) 1/2nd, rounded nose diameter dimension is identical with the slotted hole diameter dimension of slide block (204), column part external diameter diameter dimension is identical with the clear size of opening of axle (2), banking pin (201) is arranged on the other end of through hole, and rounded nose inserts in the slotted hole of slide block (204).
Blade linking arm is mainly used in connecting main blade and propeller hub, when linking arm is connected with propeller hub, after installing shimmy-damper, is installed on the connecting arm by main blade simultaneously, now by among the mounting hole of blade mount pin insertion blade, is fixed on the connecting arm by blade.
The main blade linking arm of testing table of the present invention has been successfully applied on straight nine family machine testing tables.
Claims (2)
1. the main blade linking arm of testing table, is characterized in that, comprise two parts: linking arm (1) and blade mount pin;
Linking arm (1) is formed by one piece of intermetallic composite coating, one end of linking arm (1) is arranged on propeller hub, according to the propeller hub mounting hole of blade mounting hole processing same size on linking arm (1) of propeller hub, install to adapt to propeller hub, the upper and lower two surperficial corners of linking arm (1) propeller hub mounting hole need to have a certain degree with linking arm (1) surface; According to the size of blade mounting hole to be measured, the blade mounting hole that processing two is through on the middle part of linking arm 1, the size of blade mounting hole is with blade mounting hole size to be measured; According to the mounting hole size of shimmy-damper, a through shimmy-damper mounting hole is processed at the other end of linking arm (1), install to adapt to shimmy-damper, the upper and lower two surperficial corners of linking arm (1) shimmy-damper mounting hole need to have a certain degree with linking arm (1) surface; In order to ensure that linking arm (1) does not collide with propeller hub with the position of propeller hub installation place, simultaneously also in order to the installation of propeller shank and shimmy-damper, six planes are processed in the surrounding of linking arm (1) shimmy-damper mounting hole, make blade install the corresponding plane in side;
Blade mount pin is made up of 6 parts: axle (2), banking pin (201), brake block (202), spring (203), slide block (204) and safety pin (205), wherein banking pin (201), brake block (202), spring (203), slide block (204), safety pin (205) is all arranged on axle (2);
Axle (2) entirety is right cylinder, come off from the bottom of mounting hole to prevent blade mount pin, the diameter at the top of axle (2) is than body diameter bigger formation bayonet socket, cut away the part at top along the edge of cylinder simultaneously, form a boss, blade mount pin for convenience detach; Diametrically process a groove at the top of axle (2), be convenient to blade is installed; The main body that axle (2) is blade mount pin; Spring (203) and slide block (204) are all along the exhibition of axle (2) to motion, a deep hole is processed in the inside of axle (2), and sentence at deep hole 1/2nd diameter being greater than deep hole and process outward, form the deep hole of a stairstepping, ladder place for stopping spring (203), the resilient support slided up and down by spring (203) of slide block (204); Banking pin (201) and brake block (202) all play barrier effect; A cross through hole is processed and with convex rank, the size of the same banking pin of diameter (201) and brake block (202) in the bottom of axle (2); Safety pin (205) be string in the through hole of axle (2) and slide block (204), a fixation;
Spring (203) is arranged on the inside of axle (2), for slide block (204) provides elastic force, so that slide block (204) has enough elastic force to slide up and down, there is certain gap in the hole of the size of spring (203) and the inside of axle (2), facilitates the motion of slide block (204);
Slide block (204) is arranged on the inside of axle (2), the internal diameter size of its diameter co-axial (2), slide block (204) with end face mid point for the center of circle processes vertical through hole, slide up and down for the ease of slide block (204), a slotted hole is had in its side, this slotted hole is inserted in one end of banking pin (201), coming off of anti-limited slip block (204), simultaneously in order to keep the overhang of slide block (204) minimum, process the slotted hole of the quadrant of one 90 ° along axis in slotted hole one end, rotary slider, banking pin (201) is just stuck in this slotted hole place, the continuation campaign of anti-limited slip block (204), in order to the installation of safety pin (205), in close bottom, process a cross through hole by vertical through hole,
Brake block (202) entirety is right cylinder, size two is dimensioned to according to axle (2) through hole semi-circular at right cylinder two ends, brake block (202) is arranged in cross through hole, outwardly, brake block (202) ladder place blocks mutually with convex rank in roundlet one end;
Banking pin (201) adopts intermetallic composite coating to form, overall one-tenth one stepped right cylinder, banking pin (201) left end is a rounded nose, right-hand member is a column part, the diameter of column part is 2 times of rounded nose diameter, length accounts for banking pin (201) 1/2nd, rounded nose diameter dimension is identical with the slotted hole diameter dimension of slide block (204), column part external diameter diameter dimension is identical with the clear size of opening of axle (2), banking pin (201) is arranged on the other end of through hole, and rounded nose inserts in the slotted hole of slide block (204).
2. the main blade linking arm of testing table as claimed in claim 1, it is characterized in that, according to the size of the upper propeller hub mounting hole of linking arm (1), abrasive rubber materials processing two little linings (101) are used to be arranged on the both sides of linking arm (1) propeller hub mounting hole, wearing and tearing to bearing pin when protection propeller hub and linking arm (1) relatively rotate, use fluid sealant in both cooperation places simultaneously;
According to the size of the upper shimmy-damper mounting hole of linking arm (1), process two metal Large linings (102), the interior shaft size of Large lining (102) is with shimmy-damper mounting hole size, and Large lining (102) is installed inside linking arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510249260.7A CN104880277B (en) | 2015-05-15 | 2015-05-15 | A kind of main blade linking arm of testing stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510249260.7A CN104880277B (en) | 2015-05-15 | 2015-05-15 | A kind of main blade linking arm of testing stand |
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| Publication Number | Publication Date |
|---|---|
| CN104880277A true CN104880277A (en) | 2015-09-02 |
| CN104880277B CN104880277B (en) | 2017-11-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510249260.7A Active CN104880277B (en) | 2015-05-15 | 2015-05-15 | A kind of main blade linking arm of testing stand |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416580A (en) * | 2015-11-30 | 2016-03-23 | 哈尔滨飞机工业集团有限责任公司 | Method for avoiding shifting of frequency adapter side plates through bushes |
| CN109533390A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of bracket for propeller hub support arm installation angular measurement |
| CN113654725A (en) * | 2021-08-20 | 2021-11-16 | 江西昌河航空工业有限公司 | Helicopter blade dynamic balance test bed adapter assembly and use method thereof |
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| US20020179167A1 (en) * | 2001-04-30 | 2002-12-05 | Reflange, Inc. | Remotely operable closure device |
| CN201099871Y (en) * | 2007-09-18 | 2008-08-13 | 李凯 | Arch bridge crawler type drossing machine |
| GB2447732A (en) * | 2008-02-25 | 2008-09-24 | Buzzgames Ltd | Training apparatus with ball attached via hub to a swinging arm |
| CN101706349A (en) * | 2009-11-10 | 2010-05-12 | 武汉船用机械有限责任公司 | Static balancing method of whole propeller combination of adjustable pitch propellers |
| CN104344931A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Rotor head pulling and twisting strip type propeller hub for helicopter blade dynamic balance test table |
-
2015
- 2015-05-15 CN CN201510249260.7A patent/CN104880277B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020179167A1 (en) * | 2001-04-30 | 2002-12-05 | Reflange, Inc. | Remotely operable closure device |
| CN201099871Y (en) * | 2007-09-18 | 2008-08-13 | 李凯 | Arch bridge crawler type drossing machine |
| GB2447732A (en) * | 2008-02-25 | 2008-09-24 | Buzzgames Ltd | Training apparatus with ball attached via hub to a swinging arm |
| CN101706349A (en) * | 2009-11-10 | 2010-05-12 | 武汉船用机械有限责任公司 | Static balancing method of whole propeller combination of adjustable pitch propellers |
| CN104344931A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Rotor head pulling and twisting strip type propeller hub for helicopter blade dynamic balance test table |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416580A (en) * | 2015-11-30 | 2016-03-23 | 哈尔滨飞机工业集团有限责任公司 | Method for avoiding shifting of frequency adapter side plates through bushes |
| CN109533390A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of bracket for propeller hub support arm installation angular measurement |
| CN109533390B (en) * | 2018-11-15 | 2020-11-03 | 中国直升机设计研究所 | Support for measuring mounting angle of propeller hub support arm |
| CN113654725A (en) * | 2021-08-20 | 2021-11-16 | 江西昌河航空工业有限公司 | Helicopter blade dynamic balance test bed adapter assembly and use method thereof |
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| Publication number | Publication date |
|---|---|
| CN104880277B (en) | 2017-11-28 |
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