CN203542450U - Clamping and locating device for dismounting and mounting aircraft pneumatic starter rotor - Google Patents
Clamping and locating device for dismounting and mounting aircraft pneumatic starter rotor Download PDFInfo
- Publication number
- CN203542450U CN203542450U CN201320733137.9U CN201320733137U CN203542450U CN 203542450 U CN203542450 U CN 203542450U CN 201320733137 U CN201320733137 U CN 201320733137U CN 203542450 U CN203542450 U CN 203542450U
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- rotor
- ratchet
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- studdle
- hole
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Abstract
The utility model discloses a clamping and locating device for dismounting and mounting an aircraft pneumatic starter rotor. The clamping and locating device comprises a fixed supporting ring and at least two pawl mounting and fixing assembly, and each pawl mounting and fixing assembly is composed of a pawl mounting and supporting screw rod, a gear fixing pawl and a rotary mounting handle. The pawl mounting and supporting screw rods penetrate through the fixed supporting ring and are spirally connected with the fixed supporting ring in a threaded mode, the gear fixing pawls are arranged at the inner rod ends, arranged in the fixed supporting ring, of the pawl mounting and supporting screw rods, a clearance is reserved between the gear fixing pawls and the inner rod ends of the pawl mounting and supporting screw rods after the gear fixing pawls are arranged, gear grooves matched with a gear of the rotor are formed in the inner end faces of the gear fixing pawls, the gear grooves of the gear fixing pawls are used for being meshed with the gear of the rotor when the rotor is mounted or dismounted, and the circumferential rotation of the gear of the rotor and the circumferential rotation of the rotor are limited. The clamping and locating device can dismount and mount aircraft pneumatic starter rotors of various part numbers conveniently.
Description
Technical field
The utility model relates to a kind of orientation tool of aircraft component, specifically refers to aircraft pneumatic primer rotor dismounting clamping and positioning device.
Background technology
Aircraft pneumatic primer is the core component of aircraft engine starting drive, and pneumatic primer adopts the speed governing of pneumatic leaf grating rotor banding moving gear group mostly, transmits the mode of output shaft moment, realizes its start-up function.
The rotor assembly of pneumatic primer, it is the core component of starter, the installation quality of rotor assembly has directly determined the quality of starter, the fit structure of rotor assembly is often comparatively complicated, assembly precision requires high, assembly space is comparatively narrow, general tool is difficult for realizing fixing, support and the disassemble and assemble work of rotor assembly, and assembly precision grade is difficult to reach standard-required, the installation of rotor assembly be affect starter installment work efficiency to pass factor, therefore, the location of rotor assembly, installation process are all extremely important.
The structure chart of the rotor assembly of pneumatic primer as shown in Figure 1 to Figure 3, comprise rotor 100, rotor is installed nut 5, gear 6 and safety plug 8, rotor 100 has armature spindle 7 and flywheel, during use, rotor 100 need to be arranged on stator 200, concrete mounting structure is: rotor 100 is inserted in stator 200 away from the armature spindle 7 of flywheel, the external part that armature spindle 7 exposes from stator 200 be provided with for the suitable four prismatic erection columns of gear 6, gear 6 is sleeved on armature spindle 7, and keep interlock with armature spindle 7, be that rotary rotor 100 or gear 6 can drive another parts synchronously to rotate, the termination of the external part that armature spindle 7 exposes from stator has with rotor installs the suitable installation screw thread of nut 5, rotor in aircraft pneumatic primer rotor assembly is installed to the termination of the armature spindle 7 of nut 5 precession rotors, rotor is installed after nut 5 is installed and is guaranteed that the center line of through hole and the central axis of armature spindle 7 of rotor installation nut 5 coincide.Therefore, at rotor 100, be installed in the whole installation process on stator 200, only need to guarantee that gear 6 does not rotate, guarantee that rotor 100 does not rotate, and completes the installation process of rotor.Rotor 100 is arranged on mechanism map after stator 200 as shown in Figure 2.But the accurate clamping and positioning that how to realize gear rotor is a great problem facing in current rotor disassembly process.
Utility model content
The purpose of this utility model is to provide a kind of aircraft pneumatic primer rotor dismounting clamping and positioning device, the aircraft pneumatic primer rotor that this clamping and positioning device can the multiple piece number of easy disassembly, and the repacking of can freely upgrading, dismounting is safeguarded simple and convenient.
This purpose of the present utility model realizes by following technical solution: a kind of aircraft pneumatic primer rotor dismounting clamping and positioning device, it is characterized in that: this clamping and positioning device comprises fixed support ring and at least two group ratchets installation fixation kit, many group ratchets installation fixation kits are evenly inserted on fixed support ring along the circumferencial direction of fixed support ring, and each group ratchet is installed fixation kit, by a ratchet, studdle, a gear fixed pawl and a rotation mounting handle composition is installed, described ratchet is installed studdle and is interted on fixed support ring, and with fixed support ring threadably spiral be connected, described gear fixed pawl is sector structure, gear fixed pawl is arranged on ratchet the rod end that studdle is positioned at fixed support ring is installed, after gear fixed pawl is installed and between the interior rod end of ratchet installation studdle, leave gap, this gap guarantees that ratchet installation studdle gear fixed pawl when circumferentially rotating keeps motionless, described ratchet is installed studdle can advance gear fixed pawl rectilinear motion when precession, the inner face of described gear fixed pawl has the teeth groove suitable with the gear of rotor, when rotor is installed or split, the teeth groove of gear fixed pawl is for being meshed with the gear of rotor, gear with clamping and positioning rotor, thereby the circumferential rotation of the gear of restrict rotor and rotor, described rotation mounting handle is inserted into ratchet installation studdle and is positioned at the outer rod end outside fixed support ring.
In the utility model, the center of described gear fixed pawl offers installing hole, the interior rod end that ratchet is installed studdle is inserted in this installing hole, and the interior rod end of ratchet installation studdle and the gap between the inwall of installing hole are within the scope of 0.0100～0.0375 millimeter.
In the utility model, described gear fixed pawl offers pin-and-hole in the direction perpendicular to end face, pin-and-hole be opened in installing hole a side and with the installing hole perforation that intersects; Described ratchet is installed the interior rod end of studdle along circumferentially offering a ring annular groove, the slotting position of this cannelure and the position of opening of pin-and-hole are suitable, the interior rod end that ratchet is installed studdle inserts after installing hole, cannelure is relative with pin-and-hole, in described pin-and-hole, be fitted with pin, this pin can prevent that interior rod end from deviating from installing hole, can guarantee again that interior rod end can freely rotate and not driven gear fixed pawl rotate.
In the utility model, described fixed support ring radially evenly offers with ratchet the internal thread through hole that studdle quantity is identical is installed, and it is suitable that internal thread through hole and described ratchet are installed studdle, for described ratchet installation studdle is installed.
In the utility model, it is three groups or four groups or five groups or six groups that described ratchet is installed fixation kit.
In the utility model, described outer rod end has handle hole, and described rotation mounting handle is inserted in this handle hole.
Described fixed support ring, can be improved to the fixed support ring of the pneumatic primer of different piece number types, realizes the installation function of all kinds of pneumatic primer rotor assembly.
Described ratchet is installed studdle, can be modified into the screw rod adapting according to the fixed support ring size processing adapting, to realize good screw thread and dimensional fits.
Described gear fixed pawl, can be modified into the ratchet adapting according to the parameter processing of different pneumatic primer rotor assembly gears, to realize good engagement.
Described clamping and positioning device, device materials can be the rapidoprint adapting according to the requirement improvement of the starter armature assembly dismounting moment of different model, and device itself is simple in structure, easy to operate, function-stable, easily realization, operating accuracy is high and processing and fabricating convenient.
Compared with prior art, clamping and positioning device of the present utility model can the multiple piece number of easy disassembly aircraft pneumatic primer rotor, particularly can realize the fixed support of pin dismounting, rotor is installed the load opposing of nut dismounting moment, the moment that will overcome during to dismounting has good supporting role, black box assembly precision is high, can effectively check the installation quality of rotor assembly simultaneously, simple to operate, convenient, reliably, assembly precision meets the requirements, and device is easy to, and dismounting is safeguarded and repacking upgrading, and the quality of device own is solid, durable, safe ready.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.
Fig. 1 is the structural representation of the rotor assembly of pneumatic primer in prior art;
Fig. 2 is that in prior art, the rotor assembly of pneumatic primer is installed to the overall package figure after stator;
Fig. 3 is the part-structure schematic diagram after the assembling of the rotor assembly of pneumatic primer in prior art;
Fig. 4 is the use state reference map of clamping and positioning device for the dismounting of the utility model aircraft pneumatic primer rotor;
Fig. 5 is the overall structure schematic diagram of clamping and positioning device for the dismounting of the utility model aircraft pneumatic primer rotor;
Fig. 6 is the structure chart of fixed support ring in clamping and positioning device for the dismounting of the utility model aircraft pneumatic primer rotor;
Fig. 7 is that the structure chart of studdle is installed in the dismounting of the utility model aircraft pneumatic primer rotor with ratchet in clamping and positioning device;
Fig. 8 is the structure chart of clamping and positioning device middle gear fixed pawl for the dismounting of the utility model aircraft pneumatic primer rotor.
Description of reference numerals
1, fixed support ring; 11, internal thread through hole; 2, ratchet is installed studdle; 21, interior rod end;
211, cannelure; 22, outer rod end; 221, handle hole; 3, gear fixed pawl;
31, installing hole; 32, pin-and-hole; 4, rotation mounting handle; 5, rotor is installed nut;
6, gear; 7, armature spindle; 8, safety plug; 100, rotor; 200, stator
The specific embodiment
A kind of aircraft pneumatic primer rotor dismounting clamping and positioning device as shown in Fig. 4 to Fig. 8, comprise fixed support ring 1 and three groups of ratchets installation fixation kits, three groups of ratchets are installed fixation kit and are evenly inserted on fixed support ring 1 along the circumferencial direction of fixed support ring 1, and each group ratchet is installed fixation kit and by a ratchet, studdle 2, a gear fixed pawl 3 and a rotation mounting handle 4 is installed and formed, ratchet is installed studdle 2 and is interted on fixed support ring 1, and with fixed support ring 1 threadably spiral be connected, the angle that adjacent ratchet is installed between studdle 2 is 120 °, gear fixed pawl 3 is sector structure, gear fixed pawl 3 is arranged on ratchet the rod end 21 that studdle 2 is positioned at fixed support ring 1 is installed, after gear fixed pawl 3 is installed and between the interior rod end 21 of ratchet installation studdle 2, leave gap, this gap guarantees that ratchet installation studdle 2 gear fixed pawl 3 when circumferentially rotating keeps motionless, ratchet is installed studdle 2 can advance gear fixed pawl 3 rectilinear motions when precession, the inner face of gear fixed pawl 3 has the teeth groove suitable with the gear of rotor, when rotor is installed or split, the teeth groove of gear fixed pawl 3 is for being meshed with the gear of rotor, gear with clamping and positioning rotor, thereby the circumferential rotation of the gear of restrict rotor and rotor, rotation mounting handle 4 is inserted into ratchet installation studdle 2 and is positioned at the outer rod end 22 outside fixed support ring 1, and concrete structure is: outer rod end 22 has handle hole 221, and rotation mounting handle 4 is inserted in this handle hole 221.
The center of described gear fixed pawl 3 offers installing hole 31, the interior rod end 21 that ratchet is installed studdle 2 is inserted in this installing hole 31, the gap that ratchet is installed between the interior rod end 21 of studdle 2 and the inwall of installing hole 31 is 0.0200 millimeter, and this gap is one-sided gap.
For further strengthening the stability that ratchet is installed studdle 2, gear fixed pawl 3 offers pin-and-hole 32 in the direction perpendicular to end face, pin-and-hole 32 be opened in installing hole 31 a side and with installing hole 31 perforation that intersects; Ratchet is installed the interior rod end 21 of studdle 2 along circumferentially offering a ring annular groove 211, the position of opening of the slotting position of this cannelure 211 and pin-and-hole 32 is suitable, the interior rod end 21 that ratchet is installed studdle 2 inserts after installing hole 31, cannelure 211 is relative with pin-and-hole 32, in pin-and-hole 32, be fitted with pin (not shown), this pin can prevent that interior rod end 21 from deviating from installing hole 31, can guarantee again that interior rod end 21 can freely rotate and not driven gear fixed pawl 3 rotate.
In the present embodiment, ratchet is installed the concrete structure that studdle 2 is arranged on fixed support ring 1 and is: fixed support ring 1 radially evenly offers with ratchet the internal thread through hole 11 that studdle 2 quantity are identical is installed, internal thread through hole 11 is suitable with ratchet installation studdle 2, for ratchet is installed, studdle 2 is installed.
Conversion as the present embodiment, it is at least two groups that described ratchet is installed fixation kit, such as four groups or five groups or six groups, many group ratchets are installed fixation kits and are evenly inserted on fixed support ring 1 along the circumferencial direction of fixed support ring 1, and each group ratchet is installed fixation kit and by a ratchet, studdle 2, a gear fixed pawl 3 and a rotation mounting handle 4 is installed and formed.
Conversion as the present embodiment, ratchet install one-sided gap between the interior rod end 21 of studdle 2 and the inwall of installing hole 31 also can be within the scope of 0.0100～0.0375 millimeter value, this gap guarantees that ratchet installation studdle gear fixed pawl when circumferentially rotating keeps motionless, simultaneously again can not be excessive, do not have transmission effect.
The rotor assembly and disassembly methods that adopts the above-mentioned clamping and positioning device of the utility model, comprises the steps:
(1) ratchet is installed to studdle 2 and screwed in fixed support ring 1 from internal thread through hole 11 outsides of fixed support ring 1;
(2) gear fixed pawl 3 is installed to the interior rod end 21 that ratchet is installed studdle 2, after gear fixed pawl 3 is installed and between the interior rod end 21 of ratchet installation studdle 2, leave the gap of 0.0200 millimeter, this gap guarantees that ratchet installation studdle 2 gear fixed pawl 3 when circumferentially rotating keeps motionless, ratchet is installed studdle 2 can advance gear fixed pawl 3 rectilinear motions when precession
(3) rotation mounting handle 4 is installed to the outer rod end 22 that ratchet is installed studdle 2, guaranteeing to rotate mounting handle 4 can drive ratchet that studdle 2 rotations are installed, complete the assembling of clamping and positioning device, after clamping and positioning device assembling, by fixed support ring 1, be sleeved on stator, the inner surface of fixed support ring 1 contacts with the outer face of stator, and fixed support ring 1 plays positioning supports effect;
(4) the complete clamping and positioning device of assembling is navigated on corresponding aircraft pneumatic primer rotor, each parts in aircraft pneumatic primer rotor assembly have been located complete on the stator of aircraft pneumatic primer before this, the armature spindle 7 that specifically comprises rotor is inserted in stator, the external part that armature spindle 7 exposes from stator is provided with for four suitable prismatic erection columns of the gear 6 with rotor, gear 6 is sleeved on armature spindle 7, and keeps interlock with armature spindle 7;
(5) rotation rotation mounting handle 4, advances gear fixed pawl 3 straight lines to travel forward, and gear fixed pawl 3 is meshed with the gear 6 of rotor, guarantees the tight engagement of between cog;
(6) rotor in aircraft pneumatic primer rotor assembly is installed to the termination of the armature spindle 7 of nut 5 precession rotors, the termination of armature spindle 7 has with rotor installs the suitable installation screw thread of nut 5, and the center line of through hole and the central axis of armature spindle 7 that rotor is installed the rear rotor installation of nut 5 installation nut 5 coincide; In this process, because gear fixed pawl 3 is meshed with gear 6, clamping and positioning gear 6, limiting gear 6 and with the circumferential rotation of the rotor of gear 6 interlock, when therefore rotor being installed to nut 5 and being installed to rotor, rotor keeps motionless;
(7) rotor is installed nut 5 and is radially provided with through hole, in through hole, insert safety plug 8, safety plug 8 is further installed rotor nut 5 after installing and is fixed on armature spindle 7, strengthens rotor the firm connection between nut 5 and armature spindle 7 is installed, and check the rotor assembly after installing;
(8) reverse rotation rotation mounting handle 4, moves gear fixed pawl 3 straight lines backward, and the gear 6 of gear fixed pawl 3 and rotor is thrown off, take off clamping and positioning device, complete the installation of starter armature assembly, the fractionation principle of starter armature assembly is identical with installation principle, and operation is contrary.
Above-described embodiment of the present utility model is not the restriction to the utility model protection domain; embodiment of the present utility model is not limited to this; all this kind is according to foregoing of the present utility model; according to ordinary skill knowledge and the customary means of this area; do not departing under the above-mentioned basic fundamental thought of the utility model prerequisite; the modification of other various ways that the utility model said structure is made, replacement or change, within all should dropping on protection domain of the present utility model.
Claims (6)
1. an aircraft pneumatic primer rotor dismounting clamping and positioning device, it is characterized in that: this clamping and positioning device comprises fixed support ring (1) and at least two group ratchets installation fixation kit, many group ratchets are installed fixation kits, and along the circumferencial direction of fixed support ring (1), to be evenly inserted into fixed support ring (1) upper, and each group ratchet is installed fixation kit, by a ratchet, studdle (2), a gear fixed pawl (3) and a rotation mounting handle (4) composition is installed, described ratchet is installed studdle (2) and is interted on fixed support ring (1), and with fixed support ring (1) threadably spiral be connected, described gear fixed pawl (3) is sector structure, gear fixed pawl (3) is arranged on ratchet the rod end (21) that studdle (2) is positioned at fixed support ring (1) is installed, after gear fixed pawl (3) is installed and between the interior rod end (21) of ratchet installation studdle (2), leave gap, this gap guarantees that ratchet installation studdle (2) gear fixed pawl (3) when circumferentially rotating keeps motionless, described ratchet is installed studdle (2) can advance gear fixed pawl (3) rectilinear motion when precession, the inner face of described gear fixed pawl (3) has the teeth groove suitable with the gear of rotor, when rotor is installed or split, the teeth groove of gear fixed pawl (3) is for being meshed with the gear of rotor, gear with clamping and positioning rotor, thereby the circumferential rotation of the gear of restrict rotor and rotor, described rotation mounting handle (4) is inserted into ratchet installation studdle (2) and is positioned at the outer outer rod end (22) of fixed support ring (1).
2. the aircraft pneumatic primer rotor dismounting clamping and positioning device described in 1 as requested, it is characterized in that: the center of described gear fixed pawl (3) offers installing hole (31), the interior rod end (21) that ratchet is installed studdle (2) is inserted in this installing hole (31), and the interior rod end (21) of ratchet installation studdle (2) and the gap between the inwall of installing hole (31) are within the scope of 0.0100～0.0375 millimeter.
3. the aircraft pneumatic primer rotor dismounting clamping and positioning device described in 2 as requested, it is characterized in that: described gear fixed pawl (3) offers pin-and-hole (32) in the direction perpendicular to end face, pin-and-hole (32) be opened in installing hole (31) a side and with installing hole (31) perforation that intersects, described ratchet is installed the interior rod end (21) of studdle (2) along circumferentially offering a ring annular groove (211), the position of opening of the slotting position of this cannelure (211) and pin-and-hole (32) is suitable, the interior rod end (21) that ratchet is installed studdle (2) inserts after installing hole (31), cannelure (211) is relative with pin-and-hole (32), described pin-and-hole is fitted with pin in (32), this pin can prevent that interior rod end (21) from deviating from installing hole (31), can guarantee again interior rod end (21) freely to rotate and not driven gear fixed pawl (3) rotation.
4. the aircraft pneumatic primer rotor dismounting clamping and positioning device described in 1 to 3 any one as requested, it is characterized in that: described fixed support ring (1) radially evenly offers with ratchet the internal thread through hole (11) that studdle (2) quantity is identical is installed, internal thread through hole (11) is suitable with described ratchet installation studdle (2), for described ratchet is installed, studdle (2) is installed.
5. the aircraft pneumatic primer rotor dismounting clamping and positioning device described in 1 to 3 any one as requested, is characterized in that: it is three groups or four groups or five groups or six groups that described ratchet is installed fixation kit.
6. the aircraft pneumatic primer rotor dismounting clamping and positioning device described in 1 to 3 any one as requested, is characterized in that: described outer rod end (22) has handle hole (221), and described rotation mounting handle (4) is inserted in this handle hole (221).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320733137.9U CN203542450U (en) | 2013-11-18 | 2013-11-18 | Clamping and locating device for dismounting and mounting aircraft pneumatic starter rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320733137.9U CN203542450U (en) | 2013-11-18 | 2013-11-18 | Clamping and locating device for dismounting and mounting aircraft pneumatic starter rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203542450U true CN203542450U (en) | 2014-04-16 |
Family
ID=50460617
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320733137.9U Withdrawn - After Issue CN203542450U (en) | 2013-11-18 | 2013-11-18 | Clamping and locating device for dismounting and mounting aircraft pneumatic starter rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203542450U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105033635A (en) * | 2015-07-29 | 2015-11-11 | 广州飞机维修工程有限公司 | Assembly tool for aircraft pressure-relief valve |
| CN104400690B (en) * | 2014-11-14 | 2016-03-16 | 安徽爱乐门窗***工程有限公司 | A kind of Sphere orientation device |
| CN110039472A (en) * | 2019-05-29 | 2019-07-23 | 北京深蓝航天科技有限公司 | Turn stator positioning device and its localization method |
| CN110614609A (en) * | 2019-10-09 | 2019-12-27 | 国网河北省电力有限公司邱县供电分公司 | Bolt fastener |
| CN114918877A (en) * | 2022-05-23 | 2022-08-19 | 国网河北省电力有限公司雄安新区供电公司 | Multifunctional bolt fastening and dismounting device |
-
2013
- 2013-11-18 CN CN201320733137.9U patent/CN203542450U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104400690B (en) * | 2014-11-14 | 2016-03-16 | 安徽爱乐门窗***工程有限公司 | A kind of Sphere orientation device |
| CN105033635A (en) * | 2015-07-29 | 2015-11-11 | 广州飞机维修工程有限公司 | Assembly tool for aircraft pressure-relief valve |
| CN110039472A (en) * | 2019-05-29 | 2019-07-23 | 北京深蓝航天科技有限公司 | Turn stator positioning device and its localization method |
| CN110614609A (en) * | 2019-10-09 | 2019-12-27 | 国网河北省电力有限公司邱县供电分公司 | Bolt fastener |
| CN114918877A (en) * | 2022-05-23 | 2022-08-19 | 国网河北省电力有限公司雄安新区供电公司 | Multifunctional bolt fastening and dismounting device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140416 Effective date of abandoning: 20150617 |
|
| RGAV | Abandon patent right to avoid regrant |