CN210235353U - Rotor shaft locking device for helicopter rotor shaft static test - Google Patents
Rotor shaft locking device for helicopter rotor shaft static test Download PDFInfo
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- CN210235353U CN210235353U CN201921242067.0U CN201921242067U CN210235353U CN 210235353 U CN210235353 U CN 210235353U CN 201921242067 U CN201921242067 U CN 201921242067U CN 210235353 U CN210235353 U CN 210235353U
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- rotor shaft
- fixing
- shaft fixing
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Abstract
A rotor shaft locking device for a helicopter rotor shaft static test comprises a main fixed support, a main speed reducer, a rotor shaft fixed disc, a rotor shaft sleeve and a rotor shaft, wherein the main fixed support is a helicopter frame; two fixing clamps are fixedly arranged at the bottom of the main fixing support; the fixing clamp can be fixedly arranged on the ground through a screw; the main speed reducer is fixedly arranged at the top of the main fixing support; a plurality of rotor shaft fixing rods are integrally formed on the periphery of the main speed reducer and the main fixing support; the rotor shaft sleeve is fixedly arranged on the rotor shaft fixing rod; the rotor shaft fixing disc is fixedly arranged on the main speed reducer through bolts; a rotor shaft fixing sleeve is fixedly arranged on the upper end surface of the wing shaft fixing disc; the rotor shaft fixing sleeve is uniformly provided with a plurality of mounting holes along the circumference; and the rotor shaft is provided with a plurality of through holes matched with the mounting holes. The utility model discloses can lock the rotor shaft, can not produce and rotate or slide.
Description
Technical Field
The utility model relates to a helicopter detects technical field, specifically is a quiet power test rotor shaft locking device of helicopter rotor shaft.
Background
The main rotor shaft is a key part in a helicopter transmission system, and the reliability of the main rotor shaft is directly related to the flight safety of the helicopter. In actual flight conditions, the main rotor shaft is subjected to various loads such as axial forces, bending moments, shearing forces, and torques from the rotor. Because the installation boundary conditions of actual parts are difficult to simulate, the influence of external factors such as materials, machining processes and the like on the strength of the parts cannot be considered, and the shaft strength is difficult to accurately obtain only by theoretical calculation and analysis, the theoretical calculation must be verified by adopting tests.
In order to verify the strength of the rotor shaft and the supporting structure of a helicopter of a certain model and whether the strength meets airworthiness provisions, an adopted calculation method and necessary test data are provided for strength calculation. The strength of helicopter rotor shafts and support structures of this type must be tested experimentally.
The rotor bears load, and the rotor shaft is in a locking state to bear various loads such as axial force, bending moment, shearing force, torque and the like. Otherwise the rotor shaft will rotate or slip, the load is unloaded and not loaded and the test will not be performed.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the not enough of existence among the prior art, providing a quiet power test rotor shaft locking device of helicopter rotor shaft, when the rotor shaft carries out quiet power test, can play fastening locking to the rotor shaft, prevent that the rotor shaft from producing to rotate or slide, cause the load to be difficult to the loaded problem.
In order to realize the purpose, the utility model discloses a technical scheme be:
a rotor shaft locking device for a helicopter rotor shaft static test comprises a main fixed support, a main speed reducer, a rotor shaft fixed disc, a rotor shaft sleeve and a rotor shaft, wherein the main fixed support is a helicopter frame; two fixing clamps are fixedly arranged at the bottom of the main fixing support; the fixing clamp can be fixedly arranged on the ground through a screw; the main speed reducer is fixedly arranged at the top of the main fixing support; a plurality of rotor shaft fixing rods are integrally formed on the periphery of the main speed reducer and the main fixing support; the end parts of the plurality of rotor shaft fixing rods and the plurality of rotor shaft fixing rods are integrally formed with a rotor shaft fixing ring; the rotor shaft fixing ring and the rotor shaft fixing ring are integrally formed into a plurality of rotor shaft fixing pieces along the circumferential direction of the rotor shaft fixing ring; a rotor shaft fixing platform is fixedly arranged in the rotor shaft fixing ring; the rotor shaft fixing table and the rotor shaft fixing sheet are fixed through bolts; one end of the rotor shaft sleeve is fixedly arranged in the rotor shaft fixing table, and the other end of the rotor shaft sleeve faces the rotor shaft fixing disc; the rotor shaft fixing disc is fixedly arranged on the main speed reducer through bolts; a rotor shaft fixing sleeve is fixedly arranged on the upper end surface of the wing shaft fixing disc; the rotor shaft fixing sleeve is uniformly provided with a plurality of mounting holes along the circumference; and the rotor shaft is provided with a plurality of through holes matched with the mounting holes.
Furthermore, the rotor shaft fixing sleeve is uniformly provided with 4 mounting holes along the circumferential direction; the mounting holes are all long round holes.
Further, the radius of the semicircle at the two ends of the mounting hole is equal to the radius of the through hole in the rotor shaft, and the radius of the through hole is 4 mm.
Furthermore, the center of a circle of the rotor shaft sleeve and the center of a circle of the rotor shaft fixing sleeve on the rotor shaft fixing disc are located on the same vertical line.
This helicopter rotor shaft static test rotor shaft locking device is when fixed to the rotor shaft, pass through bolt fixed mounting on the main reducer on main fixed bolster with the rotor shaft fixed disk earlier, the one end of seting up the through-hole with the rotor shaft again passes in the rotor shaft sleeve on the rotor shaft fixed station inserts the rotor shaft fixed disk on the rotor shaft fixed disk, the through-hole of seting up on the rotor shaft again is rotatory to the position of fixing epaxial mounting hole alignment with the rotor, beat a bolt that runs through mounting hole and through-hole in to mounting hole and through-hole, this bolt is worn out from another mounting hole on the rotor shaft fixed sleeve, wear out position screw in nut at the bolt again and tighten, thereby play the fixed action to the rotor shaft, conveniently exert load when testing the rotor shaft.
The utility model discloses simple structure, simple to operate, main fixed bolster are the helicopter frame, play the fixed action to the rotor shaft by main reducer and rotor shaft fixed disk that are fixed in the frame, are the current part on the helicopter mostly, low in manufacturing cost, and still can select the frame that corresponds with it as main fixed bolster according to the rotor shaft of different models, model phase-match between rotor shaft and the main fixed bolster for its test result is more accurate.
Drawings
FIG. 1 is a schematic structural diagram of the device of the present invention;
FIG. 2 is a schematic structural view of a rotor shaft;
figure 3 is a side view of the rotor shaft mounting plate;
figure 4 is a top view of the rotor shaft mounting plate;
FIG. 5 is a schematic view of a portion of a rotor shaft mounting platform;
in the figure: 1. main fixed bolster, 2, rotor axle dead lever, 3, main reducer, 4, rotor axle fixed disk, 5, rotor axle sleeve, 6, rotor axle, 7, mounting fixture, 8, the solid fixed ring of rotor axle, 9, rotor axle stationary blade, 10, rotor axle fixed station, 11, the fixed cover of rotor axle, 12, mounting hole, 13, through-hole.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The rotor shaft locking device for the helicopter rotor shaft static test comprises a main fixed bracket 1, a main speed reducer 3, a rotor shaft fixed disk 4, a rotor shaft sleeve 5 and a rotor shaft 6, wherein the main fixed bracket 1 is a helicopter frame; two fixing clamps 7 are fixedly arranged at the bottom of the main fixing support 1; the fixing clamp 7 can be fixedly arranged on the ground through a screw; the main speed reducer 3 is fixedly arranged at the top of the main fixing support 1; a plurality of rotor shaft fixing rods 2 are integrally formed on the periphery of the main speed reducer 3 and the main fixing support 1; the end parts of the plurality of rotor shaft fixing rods 2 and the plurality of rotor shaft fixing rods 2 are integrally formed with a rotor shaft fixing ring 8; the rotor shaft fixing ring 8 and the rotor shaft fixing ring 8 are integrally formed with a plurality of rotor shaft fixing pieces 9 along the circumferential direction of the rotor shaft fixing ring 8; a rotor shaft fixing table 10 is fixedly arranged in the rotor shaft fixing ring 8; the rotor shaft fixing table 10 and the rotor shaft fixing plate 9 are fixed through bolts; one end of the rotor shaft sleeve 5 is fixedly arranged in the rotor shaft fixing table 10, and the other end of the rotor shaft sleeve faces the rotor shaft fixing disc 4; the rotor shaft fixing disc 4 is fixedly arranged on the main speed reducer 3 through bolts; a rotor shaft fixing sleeve 11 is fixedly arranged on the upper end surface of the wing shaft fixing disc 4; the rotor shaft fixing sleeve 11 is uniformly provided with a plurality of mounting holes 12 along the circumference; the rotor shaft 6 is provided with a plurality of through holes 13 matched with the mounting holes 12. The rotor shaft fixing sleeve 11 is uniformly provided with 4 mounting holes 12 along the circumferential direction; the mounting holes 12 are all long round holes; the radius of the semi-circles at the two ends of the mounting hole 12 is equal to that of the through hole 13 on the rotor shaft 6, and the radius of the semi-circles is 4 mm; the centre of a circle of rotor shaft sleeve 5 with the centre of a circle of the rotor shaft fixed sleeve 11 on rotor shaft fixed disk 4 is located same vertical line.
This helicopter rotor shaft static test rotor shaft locking device is when fixed to rotor shaft 6, earlier with rotor shaft fixed disk 4 through bolt fixed mounting on main reducer 3 on main fixed bolster 1, the one end of seting up through-hole 13 with rotor shaft 6 again passes rotor shaft sleeve 5 on rotor shaft fixed station 10 and inserts in the fixed cover 11 of rotor shaft on rotor shaft fixed disk 4, the through-hole 13 of seting up on rotor shaft 6 is rotatory to the position of aliging with mounting hole 12 on the fixed cover 11 of rotor shaft, beat a bolt that runs through mounting hole 12 and through-hole 13 in mounting hole 12 and the through-hole 13 again, this bolt is worn out from another mounting hole 12 on the fixed cover 11 of rotor shaft, the position screw in nut that wears out at the bolt is screwed up again, thereby play the fixed action to rotor shaft 6, the convenience is at the load of exerting when testing rotor shaft 6.
The utility model discloses simple structure, simple to operate, main fixed bolster are the helicopter frame, play the fixed action to the rotor shaft by main reducer and rotor shaft fixed disk that are fixed in the frame, are the current part on the helicopter mostly, low in manufacturing cost, and still can select the frame that corresponds with it as main fixed bolster according to the rotor shaft of different models, model phase-match between rotor shaft and the main fixed bolster for its test result is more accurate.
The above-described embodiments are illustrative of the present invention and not restrictive, it being understood that various changes, modifications, substitutions and alterations may be made herein without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims (4)
1. A rotor shaft locking device for a helicopter rotor shaft static test is characterized by comprising a main fixed bracket (1), a main speed reducer (3), a rotor shaft fixed plate (4), a rotor shaft sleeve (5) and a rotor shaft (6), wherein the main fixed bracket (1) is a helicopter frame; two fixing clamps (7) are fixedly arranged at the bottom of the main fixing support (1); the fixing clamp (7) can be fixedly arranged on the ground through a screw; the main speed reducer (3) is fixedly arranged at the top of the main fixed bracket (1); a plurality of rotor shaft fixing rods (2) are integrally formed on the periphery of the main speed reducer (3) and the main fixing support (1); the end parts of the rotor shaft fixing rods (2) and the rotor shaft fixing rods (2) are integrally formed into a rotor shaft fixing ring (8); the rotor shaft fixing ring (8) and the rotor shaft fixing ring (8) are integrally formed into a plurality of rotor shaft fixing pieces (9) along the circumferential direction of the rotor shaft fixing ring; a rotor shaft fixing platform (10) is fixedly arranged in the rotor shaft fixing ring (8); the rotor shaft fixing platform (10) and the rotor shaft fixing plate (9) are fixed through bolts; one end of the rotor shaft sleeve (5) is fixedly arranged in the rotor shaft fixing table (10), and the other end of the rotor shaft sleeve faces the rotor shaft fixing disc (4); the rotor shaft fixing disc (4) is fixedly arranged on the main speed reducer (3) through bolts; a rotor shaft fixing sleeve (11) is fixedly arranged on the upper end surface of the wing shaft fixing disc (4); the rotor shaft fixing sleeve (11) is uniformly provided with a plurality of mounting holes (12) along the circumference; and a plurality of through holes (13) matched with the mounting holes (12) are formed in the rotor shaft (6).
2. The helicopter rotor shaft static test rotor shaft locking device according to claim 1, characterized in that the rotor shaft fixing sleeve (11) is evenly provided with 4 mounting holes (12) along its circumferential direction; the mounting holes (12) are all oblong holes.
3. A helicopter rotor shaft static test rotor shaft locking device according to claim 2 wherein the radius of the semi-circles at both ends of the mounting hole (12) is equal to the radius of the through hole (13) on the rotor shaft (6), and the radii are both 4 mm.
4. The helicopter rotor shaft static test rotor shaft locking device according to claim 1, characterized by that, the centre of circle of the rotor shaft sleeve (5) and the centre of circle of the rotor shaft fixing sleeve (11) on the rotor shaft fixing disk (4) are located on the same vertical line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921242067.0U CN210235353U (en) | 2019-08-02 | 2019-08-02 | Rotor shaft locking device for helicopter rotor shaft static test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921242067.0U CN210235353U (en) | 2019-08-02 | 2019-08-02 | Rotor shaft locking device for helicopter rotor shaft static test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210235353U true CN210235353U (en) | 2020-04-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921242067.0U Active CN210235353U (en) | 2019-08-02 | 2019-08-02 | Rotor shaft locking device for helicopter rotor shaft static test |
Country Status (1)
| Country | Link |
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| CN (1) | CN210235353U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111232244A (en) * | 2020-04-29 | 2020-06-05 | 北京清航紫荆装备科技有限公司 | Unmanned helicopter rotor system test bench |
| CN111498140A (en) * | 2020-04-24 | 2020-08-07 | 山东大学 | Be used for wing to prevent and remove icing material test box |
-
2019
- 2019-08-02 CN CN201921242067.0U patent/CN210235353U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498140A (en) * | 2020-04-24 | 2020-08-07 | 山东大学 | Be used for wing to prevent and remove icing material test box |
| CN111232244A (en) * | 2020-04-29 | 2020-06-05 | 北京清航紫荆装备科技有限公司 | Unmanned helicopter rotor system test bench |
| CN111232244B (en) * | 2020-04-29 | 2020-08-04 | 北京清航紫荆装备科技有限公司 | Unmanned helicopter rotor system test bench |
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| GR01 | Patent grant | ||
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| CP01 | Change in the name or title of a patent holder |
Address after: 333000 No. 01, Zhihang Road, High tech Zone, Jingdezhen, Jiangxi Patentee after: Jiangxi Helicopter Co.,Ltd. Address before: 333000 No. 01, Zhihang Road, High tech Zone, Jingdezhen, Jiangxi Patentee before: BGAC JIANGXI HELICOPTER CO.,LTD. |