CN203572672U - 300 kilogram helicopter comprehensive test platform - Google Patents
300 kilogram helicopter comprehensive test platform Download PDFInfo
- Publication number
- CN203572672U CN203572672U CN201320713310.9U CN201320713310U CN203572672U CN 203572672 U CN203572672 U CN 203572672U CN 201320713310 U CN201320713310 U CN 201320713310U CN 203572672 U CN203572672 U CN 203572672U
- Authority
- CN
- China
- Prior art keywords
- helicopter
- tilting
- housed
- platform
- pressure sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 20
- 238000005096 rolling process Methods 0.000 abstract description 2
- 230000005540 biological transmission Effects 0.000 abstract 2
- 238000007906 compression Methods 0.000 abstract 2
- 230000008878 coupling Effects 0.000 description 6
- 238000010168 coupling process Methods 0.000 description 6
- 238000005859 coupling reaction Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model belongs to a 300 kilogram helicopter comprehensive test platform, which comprises a base (1), and is characterized in that leveling supporting legs (2) are arranged on the base (1), and a horizontal platform (3) is fixed on the upper ends of each of the leveling supporting legs (2); the left end of the horizontal platform (3) is provided with a tilting supporting base (4), and the right end is provided with a tilting screw rod (27); a tilting platform (5) is arranged on the upper ends of each of the tilting supporting base (4) and the tilting screw rod (27), and three vertical tension-compression sensors (6) and two horizontal tension-compression sensors (8) are arranged on the tilting platform (5); and an equipment bottom plate (24) is provided with an equipment supporting base (23) and an upper rack (17), a tail transmission torque sensor (19) is arranged on a tail beam (21) of a helicopter, and a transmission system (13) is provided with a rotor wing torque sensor (14). The 300 kilogram helicopter comprehensive test platform can accurately test characteristics of external forces, including lift force, pitching moment, rolling moment and yaw (turning) moment; and the internal forces include torque and power of the rotor wing system and the engine.
Description
Technical field
The utility model belongs to test unit, particularly a kind of 300 kilograms of helicopter multi-function test stands.
Background technology
The performance of lifting airscrew system, power system and the performance and the safety that the manipulation of these two large systems have been determined to helicopter.Therefore before installation, must test rotor system, power system, the reliability of check system, measures rotor system control response and power demand, measures power system power output capacity and control response.Current testing table, complex structure, tests loaded down with trivial detailsly, and degree of accuracy is not ideal enough.
Summary of the invention
The object of the invention is to overcome above-mentioned technical deficiency, provide a kind of simple in structure, test is convenient, 300 kilograms of helicopter multi-function test stands that can accurately test out lifting airscrew system and the every technical parameter of power system.
The technical scheme that technical solution problem of the present invention adopts is: a kind of 300 kilograms of helicopter multi-function test stands, comprise base, and it is characterized in that being equipped with leveling supporting legs on base, in leveling supporting legs upper end, fix a horizontal stand; Left end at horizontal stand is equipped with the bearing that verts, and right-hand member is equipped with the leading screw that verts; Swivel angle plate is equipped with in upper end at vert bearing and the leading screw that verts, three vertical pull pressure sensor is housed, a longitudinal pull pressure sensor, two horizontal pull pressure sensor above swivel angle plate; In vertical pull pressure sensor with above horizontal pull pressure sensor, fill an equipment bay; Equipment support and upper stage are housed on equipment bay, tail driving torque sensor is housed on the tail boom of helicopter, rotor torque sensor is housed in kinematic train, engine torque sensor is housed in power system; Tail boom pull bar is housed between upper stage and tail boom.
The beneficial effects of the utility model are: this utility model can test out external force feature accurately, comprise lift, pitching moment, rolling moment and driftage (revolution) moment; Internal force comprises moment of torsion, the power of rotor system and engine.Thereby determine performance and the control response characteristic of rotor and engine.Simple in structure, convenient test.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, with embodiment, illustrate.
Fig. 1 is the front view of 300 kilograms of helicopter multi-function test stands;
Fig. 2 is the left side view of Fig. 1.
In figure: 1-base; 2-leveling supporting legs; 3-horizontal stand; The 4-bearing that verts; 5-swivel angle plate; The vertical pull pressure sensor of 6-; The longitudinal pull pressure sensor of 7-; The horizontal pull pressure sensor of 8-; 9-power system; 10-clutch coupling; 11-shaft coupling; 12-engine torque sensor; 13-kinematic train; 14-rotor torque sensor; 15-control system; 16-rotor system; 17-upper stage; 18-diaphragm coupling; 19-tail driving torque sensor; 20-tail boom pull bar; 21-tail boom; 22-tail-rotor; 23-equipment support; 24-equipment bay; Stand in 25-; 26-platform; The 27-leading screw that verts.
Embodiment
Embodiment, with reference to accompanying drawing, a kind of 300 kilograms of helicopter multi-function test stands, comprise base 1, it is characterized in that being equipped with leveling supporting legs 2 on base 1, in leveling supporting legs 2 upper ends, fix a horizontal stand 3; Left end at horizontal stand 3 is equipped with the bearing 4 that verts, and right-hand member is equipped with the leading screw 27 that verts; Swivel angle plate 5 is equipped with in upper end at vert bearing 4 and the leading screw 27 that verts, and swivel angle plate 5 is equipped with 6, two horizontal pull pressure sensor 8 of three vertical pull pressure sensor above; In vertical pull pressure sensor 6 with above horizontal pull pressure sensor 8, fill an equipment bay 24; Equipment support 23 and upper stage 17 are housed on equipment bay 24, tail driving torque sensor 19 is housed on the tail boom 21 of helicopter, rotor torque sensor 14 is housed in kinematic train 13, engine torque sensor 12 is housed in power system 9; Between upper stage 17 and tail boom 21, tail boom pull bar 20 is housed, at tail boom 21 right-hand members, tail-rotor 22 is housed, control system 15 is housed above upper stage 17, control system 15 is equipped with rotor system 16 above; Kinematic train 9 right sides are connected with clutch coupling 10, and clutch coupling 10 is connected with shaft coupling 11.
During test, helicopter is contained on experiment table, by vertical pull pressure sensor 6, longitudinal pull pressure sensor 7, horizontal pull pressure sensor 8, engine torque sensor 12, rotor torque sensor 14 and tail driving torque sensor 19, can measure every technical data, measure performance and the control response feature of rotor and engine.
Claims (1)
1. 300 kilograms of helicopter multi-function test stands, comprise base (1), it is characterized in that being equipped with leveling supporting legs (2) on base (1), in leveling supporting legs (2) upper end, fix a horizontal stand (3); Left end at horizontal stand (3) is equipped with the bearing that verts (4), and right-hand member is equipped with the leading screw that verts (27); Swivel angle plate (5) is equipped with in upper end at the bearing that verts (4) and the leading screw that verts (27), and swivel angle plate (5) is equipped with three vertical pull pressure sensor (6) above, two horizontal pull pressure sensor (8); In vertical pull pressure sensor (6) with above horizontal pull pressure sensor (8), fill an equipment bay (24); Equipment support (23) and upper stage (17) are housed on equipment bay (24), on the tail boom (21) of helicopter, tail driving torque sensor (19) is housed, rotor torque sensor (14) is housed in kinematic train (13), engine torque sensor (12) is housed in power system (9); Between upper stage (17) and tail boom (21), tail-rotor pull bar (20) is housed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320713310.9U CN203572672U (en) | 2013-11-12 | 2013-11-12 | 300 kilogram helicopter comprehensive test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320713310.9U CN203572672U (en) | 2013-11-12 | 2013-11-12 | 300 kilogram helicopter comprehensive test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203572672U true CN203572672U (en) | 2014-04-30 |
Family
ID=50540399
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320713310.9U Expired - Lifetime CN203572672U (en) | 2013-11-12 | 2013-11-12 | 300 kilogram helicopter comprehensive test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203572672U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483139A (en) * | 2014-12-19 | 2015-04-01 | 中国南方航空工业(集团)有限公司 | Test method and test system of aerocar |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN106428630A (en) * | 2016-12-06 | 2017-02-22 | 北京航空航天大学 | Rotation platform for helicopter rotor anti-icing/de-icing test in ice wind tunnel |
| CN106596030A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | Full-size helicopter rotor test tower |
| RU176079U1 (en) * | 2017-06-08 | 2017-12-27 | Закрытое Акционерное Общество "Весоизмерительная Компания "Тензо-М" | DEVICE FOR MEASURING LIFT POWER AND TORQUE CREATED BY SCREWS OF THE HELICOPTER |
| CN108181034A (en) * | 2018-02-01 | 2018-06-19 | 顺丰科技有限公司 | A kind of dynamic test integrated system and test method |
| CN109141859A (en) * | 2018-09-28 | 2019-01-04 | 南京航空航天大学 | A kind of helicopter circular rector tail boom experiment test device |
-
2013
- 2013-11-12 CN CN201320713310.9U patent/CN203572672U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483139A (en) * | 2014-12-19 | 2015-04-01 | 中国南方航空工业(集团)有限公司 | Test method and test system of aerocar |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN105547676B (en) * | 2015-12-25 | 2018-01-12 | 北京航空航天大学 | A kind of arm-type rotor model.test system of multifunctional rotary |
| CN106596030A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | Full-size helicopter rotor test tower |
| CN106596030B (en) * | 2016-11-30 | 2019-05-07 | 中国直升机设计研究所 | A kind of full-scale helicopter tower |
| CN106428630A (en) * | 2016-12-06 | 2017-02-22 | 北京航空航天大学 | Rotation platform for helicopter rotor anti-icing/de-icing test in ice wind tunnel |
| CN106428630B (en) * | 2016-12-06 | 2019-09-06 | 北京航空航天大学 | It is a kind of for lifting airscrew in icing tunnel it is anti-/ rotating platform of deicing test |
| RU176079U1 (en) * | 2017-06-08 | 2017-12-27 | Закрытое Акционерное Общество "Весоизмерительная Компания "Тензо-М" | DEVICE FOR MEASURING LIFT POWER AND TORQUE CREATED BY SCREWS OF THE HELICOPTER |
| CN108181034A (en) * | 2018-02-01 | 2018-06-19 | 顺丰科技有限公司 | A kind of dynamic test integrated system and test method |
| CN109141859A (en) * | 2018-09-28 | 2019-01-04 | 南京航空航天大学 | A kind of helicopter circular rector tail boom experiment test device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203572672U (en) | 300 kilogram helicopter comprehensive test platform | |
| CN102680236B (en) | Structural strength test loading device for aircraft wing-mounted engine | |
| CN103344495B (en) | Rigid bearing plate center pit method servocontrol deep rock-mass deformation test unit and method thereof | |
| CN104390687A (en) | Intelligent tester for weight and center of gravity of aircraft | |
| CN103631266A (en) | Five-degree-of-freedom full-aircraft drop test aircraft posture follow-up control device | |
| CN204149890U (en) | A kind of contact system ratchet compensator angle measurement unit | |
| CN109506919A (en) | A kind of aircraft takeoffs and landings rack loading device and loading method | |
| CN102135461B (en) | Undercarriage load calibration device and method for calibrating load of undercarriage by using device | |
| CN103969003A (en) | Measuring device for center of gravity of micro mobile robot | |
| CN202501836U (en) | Aerial hydraulic accessory linear displacement load test device | |
| CN102840433A (en) | Free elevating tripod head system for three-dimensional camera of ground unmanned reconnaissance car | |
| CN105083585A (en) | Balance test system of four-rotor aircraft | |
| CN202558448U (en) | Electrohydraulic balance hoisting beam | |
| CN104359613B (en) | Multi-functional super large torque standard device | |
| CN204211371U (en) | A kind of high precision driving electronic scales | |
| CN106017891B (en) | A kind of propeller dynamic characteristics test device | |
| CN202109968U (en) | Weighing system for detecting load condition of climbing operation equipment | |
| CN101881675B (en) | Device and method for measuring horizontal shear of support | |
| CN214333978U (en) | Height adjusting device of electronic truck scale | |
| CN112141359B (en) | Tilt rotor unmanned aerial vehicle test bench | |
| CN203551057U (en) | Weigh sensing module | |
| CN203924144U (en) | A kind of displacement transducer installation auxiliary device | |
| CN204008296U (en) | Rigid bearing plate center pit method servocontrol deep rock mass deformation testing device | |
| CN102680392A (en) | Paper and paperboard static friction coefficient tester | |
| CN103171997A (en) | Floating-beam-type weighing forklift |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140430 |
|
| CX01 | Expiry of patent term |