CN1731124A - Test bench for testing flight performance of small-sized helicopter - Google Patents
Test bench for testing flight performance of small-sized helicopter Download PDFInfo
- Publication number
- CN1731124A CN1731124A CN 200510050551 CN200510050551A CN1731124A CN 1731124 A CN1731124 A CN 1731124A CN 200510050551 CN200510050551 CN 200510050551 CN 200510050551 A CN200510050551 A CN 200510050551A CN 1731124 A CN1731124 A CN 1731124A
- Authority
- CN
- China
- Prior art keywords
- fixed
- platform
- test
- depopulated helicopter
- top base
- 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.)
- Granted
Links
Images
Abstract
The invention discloses a test board for testing small type pilotless gyroplane flight performance, which mainly comprises a frame, an all-around steering mechanism and a balanced weight mechanism, wherein the pilotless gyroplane is fixed on the plate of the test board; when the pilotless gyroplane with all-around steering mechanism and arm brace gets off, it uses the top end of the arm brace as the center of the ball to do a limited spherical movement to achieve leaning, crabbing and rotating and so on.
Description
Technical field
The present invention relates to test the test platform of small-sized depopulated helicopter flying quality.
Background technology
Small-sized depopulated helicopter (hereinafter to be referred as depopulated helicopter) but be meant by the vertical takeoff and landing (VTOL) of radio ground remote control flight or Autonomous Control flight manned vehicle not, on structural form, belong to rotor craft, on function, belong to vertically taking off and landing flyer.In recent ten years, along with Study on Technology such as compound substance, power system, sensor, especially flight control progress, depopulated helicopter has obtained development rapidly, becomes the focus that people pay close attention to just day by day.Depopulated helicopter has unique flying quality and use value.Compare with people's helicopter is arranged, depopulated helicopter is because characteristics such as no one was injured, volume is little, cost is low, the battlefield viability is strong have incomparable superiority in many aspects.Compare with the fixed-wing unmanned plane, but depopulated helicopter vertical takeoff and landing, hovering, and the landing place of taking off is little, needn't be equipped with to resemble emission recovery system complicated the fixed-wing unmanned plane, large volume; And it can fly towards any direction, can with horizontally fly, flying method such as inverted flight shuttles back and forth between buildings, finish and take photo by plane, rescue and relief work, topographical surveying etc. suchlike task.Depopulated helicopter also is with a wide range of applications at aspects such as atmospheric surveillance, traffic monitoring, resource exploration, power circuit detection, forest fire protections.Aspect military, depopulated helicopter can be carried out various non-lethal tasks, can carry out the lethal task of various soft or hards again, comprises scouting, supervision, target acquisition, bait, attack, communication repeating etc.
But the function of depopulated helicopter is also very limited at present, and flight is mainly finished at ground remote control by operator, does not also possess the autonomous flight ability mostly.Following the most promising application of depopulated helicopter is exactly the over the horizon autonomous flight, and its airborne flight control system just seems particularly important for autonomous flight.At present, the autonomous flight research of depopulated helicopter also is the unusual problem in forward position in the world.Domestic method for designing, majority are to adjust the flight control parameter by a large amount of flight tests, finally find suitable control law.But flight test is in case failure, and depopulated helicopter has the danger of air crash, is easy to the damage of going to wreck property, will cause experimentation cost to increase considerably lengthening with the lead time.Therefore, developmental flight control test platform becomes an important step of unmanned helicopter flight Control System Design.
In addition, current domestic model plane motor development is like a raging fire, has a large amount of airplane hobbyists to select model copter for use.And the manipulation of model copter is very difficult for the beginner, owing to handle error, through regular meeting the air crash accident takes place, and not only causes economic loss, even the threat personal safety.
Summary of the invention
The purpose of this invention is to provide a kind of within the specific limits can be by the free flight of practical flight attitude, when breaking down, can guarantee the depopulated helicopter safe landing, the test platform of the test small-sized depopulated helicopter flying quality that simple in structurely be easy to realize, cost is low.
The present invention solves the technical scheme that its technical matters takes: the test platform of test small-sized depopulated helicopter flying quality mainly comprises frame, universal rotation mechanism and balance weight mechanism, frame comprises by top base, cylindrical stent and platform that bottom base and vertical rod constitute, top base has axially extending bore, platform has center pit, the lower surface of platform is fixed with the location cylinder with the center pit coaxial cable, the location cylinder places the axially extending bore of top base, and fix with top base, universal rotation mechanism comprises the bearing seat cavity that is made of top chock and step, be fixed on rolling ball bearing and support bar in the bearing seat cavity, the lower end of bearing seat cavity is loudspeaker opening shape, the center pit of support bar spanning platform and location cylinder, form sliding pair with the setting circle tube, the inner ring of post upper and rolling ball bearing is fastening, the lower end links to each other with horizontal cross bar, upper surface at top chock is fixed with flat board, balance weight mechanism comprises that two groups of symmetries are fixed on the fixed pulley group of platform lower surface center pit both sides, two flexible wire ropes and weight, every group of fixed pulley comprises two fixed pulleys at least, two wire rope are walked around two groups of fixed pulleys respectively, one end of every wire rope hangs weight, and the other end and horizontal cross bar are connected to vertical line.
Principle of work of the present invention: when testing, depopulated helicopter is fixed on the flat board of test platform, after related universal rotation mechanism of depopulated helicopter and support bar take off, can with the supporting bar top centre of sphere, do a limited spheric motion, realize various attitudes such as inclination, driftage, lift-over, satisfy the helicopter free flight within the specific limits.In flight course, the flying height of helicopter is by the length of support bar and the height decision of support.Support bar rises with helicopter, and the horizontal cross bar of support bar lower end had both limited the lifting height of helicopter, can guarantee that again helicopter can not fly away from test platform.When support bar rose, bolt also can rise at the wire rope of horizontal cross bar thereupon, and the weight that the wire rope other end hangs then can descend, thus the unnecessary load during balancing helicopter flight.When flight control lost efficacy or during test failure,, make the helicopter can safe landing because the position-limiting action of the horn-like opening in bearing seat cavity bottom can guarantee that rolling can not appear in helicopter.
Beneficial effect of the present invention: this invention has advantages such as simple in structurely be easy to realize, cost is low, be easy to move, be applicable to the various flight tests of small-sized depopulated helicopter, it offers attitudes such as the needed inclination of unmanned helicopter flight, driftage, lift-over, guarantees that depopulated helicopter within the specific limits can free flight.Utilize the present invention, can under laboratory condition, reappear the real flight conditions of depopulated helicopter, carry out scientific researches such as attitude control, flight control, navigation very easily, guaranteed the security of unmanned helicopter flight test.The present invention also provides the platform of a familiar models helicopter flight performance for vast airplane hobbyist in addition.Especially beginner can be familiar with on test platform earlier and handles model copter, treats to carry out practical flight again after skilled, is very helpful for reducing the model copter damage and improving manipulation technology.
Description of drawings
Fig. 1 is the test platform structural representation of test small-sized depopulated helicopter flying quality of the present invention;
Fig. 2 is the universal rotation mechanism enlarged drawing;
Fig. 3 is the top base enlarged drawing;
Fig. 4 is the vertical view of Fig. 3.
Embodiment
With reference to Fig. 1, the test platform of test small-sized depopulated helicopter flying quality mainly comprises frame, universal rotation mechanism and balance weight mechanism, frame comprises by top base 13, cylindrical stent and platform 7 that bottom base 20 and vertical rod 17 constitute, and top base has axially extending bore 9, platform has center pit 8, the lower surface of platform is fixed with the location cylinder 15 with center pit 8 coaxial cables, and location cylinder 15 places the axially extending bore 9 of top base, and fixing with top base 13.In the diagram instantiation, cylindrical stent is an A-frame, top base 13 as shown in Figure 3 and Figure 4, it is the right cylinder that axially has through hole, the right cylinder middle part is provided with the regular triangular prism 18 of fixed support vertical rod 17, the cylindrical threaded hole 14 that radially is provided with, location cylinder 15 is fixing by twisting the holding screw and the top base 13 that are connected on threaded hole, perhaps also can weld with top base 13.A-frame is fixing by bolt and bottom base 20, also can weld with bottom base 20.Four limits of bottom base 20 are provided with handle 19, convenient carrying and mobile.
Universal rotation mechanism, its enlarged drawing as shown in Figure 2, comprise the bearing seat cavity that constitutes by top chock 2 and step 3, be fixed on rolling ball bearing 5 and support bar 6 in the bearing seat cavity, the lower end of bearing seat cavity is loudspeaker opening shape, so that make depopulated helicopter have bigger rotational angle.Upper surface at top chock 2 is fixed with flat board 1, and the center pit 8 of support bar 6 spanning platforms 7 and location cylinder 15 form sliding pairs with location cylinder 15, and the inner ring of support bar 6 upper ends and rolling ball bearing 5 is fastening, and the lower end links to each other with horizontal cross bar 16.Support bar 6 can be a solid hopkinson bar, also can be hollow stem, and for ease of installing and fixing and alleviate the load of helicopter, support bar 6 generally is made up of hollow tubular and the right cylinder 4 that is connected the hollow tubular upper end.Dull and stereotyped, upper and lower bearing seat, right cylinder can aluminums, and hollow tubular can adopt stainless-steel tube.The size of rolling ball bearing is selected according to the size of depopulated helicopter.
Balance weight mechanism comprises that two groups of symmetries are fixed on the fixed pulley group 10 of platform lower surface center pit both sides, two flexible wire ropes 12 and weight 11, every group of fixed pulley comprises two fixed pulleys at least, in the legend, every group of fixed pulley contains two fixed pulleys, and every wire rope is walked around two fixed pulleys respectively, and its end hangs weight 11, the other end and horizontal cross bar 16 are connected to vertical line, have avoided wire rope to change the variation that causes equilibrant owing to inclination causes angle in uphill process.Weight of heavy equates with the unnecessary load of taking off with depopulated helicopter.Utilize balance weight mechanism, can offset the unnecessary load that test platform brings depopulated helicopter, guaranteed the authenticity of flight test.
Claims (3)
1. test the test platform of small-sized depopulated helicopter flying quality, it is characterized in that mainly comprising frame, universal rotation mechanism and balance weight mechanism, frame comprises by top base (13), cylindrical stent and platform (7) that bottom base (20) and vertical rod (17) constitute, top base has axially extending bore (9), platform has center pit (8), the lower surface of platform is fixed with the location cylinder (15) with center pit (8) coaxial cable, location cylinder (15) places the axially extending bore (9) of top base, and it is fixing with top base (13), universal rotation mechanism comprises the bearing seat cavity that is made of top chock (2) and step (3), be fixed on rolling ball bearing (5) and support bar (6) in the bearing seat cavity, the lower end of bearing seat cavity is loudspeaker opening shape, the center pit (8) of support bar (6) spanning platform and location cylinder (15), form sliding pair with location cylinder (15), support bar (6) upper end is fastening with the inner ring of rolling ball bearing (5), the lower end links to each other with horizontal cross bar (16), upper surface at top chock (2) is fixed with flat board (1), balance weight mechanism comprises that two groups of symmetries are fixed on the fixed pulley group (10) of platform lower surface center pit both sides, two flexible wire ropes (12) and weight (11), every group of fixed pulley comprises two fixed pulleys at least, two wire rope are walked around two groups of fixed pulleys respectively, one end of every wire rope hangs weight (11), and the other end and horizontal cross bar (16) are connected to vertical line.
2. the test platform of test small-sized depopulated helicopter flying quality according to claim 1 is characterized in that support bar (6) is made up of hollow tubular and the right cylinder (4) that is connected hollow tubular upper end.
3. the test platform of test small-sized depopulated helicopter flying quality according to claim 1, it is characterized in that said cylindrical stent is an A-frame, top base (13) is the right cylinder that axially has through hole, the right cylinder middle part is provided with the regular triangular prism (18) of fixed support vertical rod (17), the cylindrical threaded hole (14) that radially is useful on stationary positioned cylinder (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200510050551XA CN100368789C (en) | 2005-07-04 | 2005-07-04 | Test bench for testing flight performance of small-sized helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200510050551XA CN100368789C (en) | 2005-07-04 | 2005-07-04 | Test bench for testing flight performance of small-sized helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1731124A true CN1731124A (en) | 2006-02-08 |
| CN100368789C CN100368789C (en) | 2008-02-13 |
Family
ID=35963520
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB200510050551XA Expired - Fee Related CN100368789C (en) | 2005-07-04 | 2005-07-04 | Test bench for testing flight performance of small-sized helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100368789C (en) |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100447550C (en) * | 2006-03-17 | 2008-12-31 | 燕山大学 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
| CN101620033B (en) * | 2008-07-02 | 2011-08-10 | 中国科学院自动化研究所 | Micro air vehicle experimental device |
| CN102779438A (en) * | 2012-07-10 | 2012-11-14 | 黄力红 | Flight simulated mechanical execution system simulating full-motion of airplane |
| CN103487277A (en) * | 2013-10-11 | 2014-01-01 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
| CN103863576A (en) * | 2013-12-26 | 2014-06-18 | 吉林大学 | Unmanned helicopter performance testing platform |
| CN103930940A (en) * | 2011-07-18 | 2014-07-16 | 奥格斯塔韦斯兰股份公司 | Real-time simulation system of the effects of rotor-wake generated aerodynamic loads of a hover-capable aircraft on the aircraft itself, and method thereof |
| CN103983403A (en) * | 2014-01-21 | 2014-08-13 | 浙江大学 | Apparatus and method for measuring operating performance and parameters of motor propeller system |
| CN103984241A (en) * | 2014-04-30 | 2014-08-13 | 北京理工大学 | Small unmanned helicopter test stand and test simulation method |
| CN104494840A (en) * | 2014-12-03 | 2015-04-08 | 中国人民解放军海军航空工程学院 | Unmanned helicopter ground testing console and application method thereof |
| CN104793628A (en) * | 2015-04-24 | 2015-07-22 | 西北农林科技大学 | Flight control debugging protecting device of multi-rotor-wing unmanned plane |
| CN104990719A (en) * | 2015-07-08 | 2015-10-21 | 国网山东省电力公司电力科学研究院 | Unmanned aerial vehicle test bed system for inspection and detection |
| CN105158004A (en) * | 2015-09-29 | 2015-12-16 | 华东师范大学 | Rotor aircraft test platform |
| CN105999711A (en) * | 2016-07-04 | 2016-10-12 | 雷壹 | Manipulable simulated helicopter |
| 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 |
| CN107021245A (en) * | 2017-03-08 | 2017-08-08 | 贾杰 | Light-duty depopulated helicopter is taken a flight test debugging apparatus |
| CN107085989A (en) * | 2017-06-23 | 2017-08-22 | 许多 | A kind of helicopter instructional device that driving experience is carried out based on supporting surface |
| CN107230421A (en) * | 2017-04-13 | 2017-10-03 | 沈阳华人风电科技有限公司 | Blade rotation test platform and experimental method |
| CN107651213A (en) * | 2017-04-26 | 2018-02-02 | 天津中德应用技术大学 | Dynamic equilibrium machinery arm |
| CN108415442A (en) * | 2018-01-23 | 2018-08-17 | 歌尔股份有限公司 | Unmanned plane adjusts test device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3238235B2 (en) * | 1993-04-09 | 2001-12-10 | ヤマハ発動機株式会社 | Altitude sensor for remote-controlled helicopter |
| CN1161677C (en) * | 2002-01-29 | 2004-08-11 | 北京航空航天大学 | Telemetry system for coaxial double-rotary wing pilotless helicopter |
| CN2630800Y (en) * | 2003-06-18 | 2004-08-04 | 哈尔滨飞机工业(集团)有限责任公司 | Helicopter dynamic balance simulation test apparatus |
| CN2816871Y (en) * | 2005-07-04 | 2006-09-13 | 浙江大学 | Flight coutrol test platform for small-sized unmanned helicopter |
-
2005
- 2005-07-04 CN CNB200510050551XA patent/CN100368789C/en not_active Expired - Fee Related
Cited By (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100447550C (en) * | 2006-03-17 | 2008-12-31 | 燕山大学 | Externally swing joint-bearing fatigue experimental apparatus of automatic rotor oblique device for helicopter |
| CN101620033B (en) * | 2008-07-02 | 2011-08-10 | 中国科学院自动化研究所 | Micro air vehicle experimental device |
| CN103930940A (en) * | 2011-07-18 | 2014-07-16 | 奥格斯塔韦斯兰股份公司 | Real-time simulation system of the effects of rotor-wake generated aerodynamic loads of a hover-capable aircraft on the aircraft itself, and method thereof |
| CN103930940B (en) * | 2011-07-18 | 2016-03-30 | 奥格斯塔韦斯兰股份公司 | The Real-time Simulation System of the effect of the aerodynamic load that the rotor wake that can hover aircraft originally produces with it at aircraft and method thereof |
| CN102779438A (en) * | 2012-07-10 | 2012-11-14 | 黄力红 | Flight simulated mechanical execution system simulating full-motion of airplane |
| CN102779438B (en) * | 2012-07-10 | 2014-06-25 | 黄力红 | Flight simulated mechanical execution system simulating full-motion of airplane |
| CN103487277B (en) * | 2013-10-11 | 2015-11-04 | 沈阳航空航天大学 | A kind of multifunctional universal test-bed for light aerocraft slow test |
| CN103487277A (en) * | 2013-10-11 | 2014-01-01 | 沈阳航空航天大学 | Multifunctional universal test bed for static test on light airplane |
| CN103863576A (en) * | 2013-12-26 | 2014-06-18 | 吉林大学 | Unmanned helicopter performance testing platform |
| CN103863576B (en) * | 2013-12-26 | 2016-02-24 | 吉林大学 | Depopulated helicopter performance detecting platform |
| CN103983403A (en) * | 2014-01-21 | 2014-08-13 | 浙江大学 | Apparatus and method for measuring operating performance and parameters of motor propeller system |
| CN103983403B (en) * | 2014-01-21 | 2016-05-11 | 浙江大学 | Measure the apparatus and method of motor propeller system service behaviour and parameter |
| CN103984241A (en) * | 2014-04-30 | 2014-08-13 | 北京理工大学 | Small unmanned helicopter test stand and test simulation method |
| CN103984241B (en) * | 2014-04-30 | 2017-01-11 | 北京理工大学 | Small unmanned helicopter test stand and test simulation method |
| CN104494840A (en) * | 2014-12-03 | 2015-04-08 | 中国人民解放军海军航空工程学院 | Unmanned helicopter ground testing console and application method thereof |
| CN104793628A (en) * | 2015-04-24 | 2015-07-22 | 西北农林科技大学 | Flight control debugging protecting device of multi-rotor-wing unmanned plane |
| CN104990719B (en) * | 2015-07-08 | 2018-04-27 | 国网山东省电力公司电力科学研究院 | A kind of unmanned plane test bench system for being used to examine detection |
| CN104990719A (en) * | 2015-07-08 | 2015-10-21 | 国网山东省电力公司电力科学研究院 | Unmanned aerial vehicle test bed system for inspection and detection |
| CN105158004A (en) * | 2015-09-29 | 2015-12-16 | 华东师范大学 | Rotor aircraft test platform |
| CN105999711A (en) * | 2016-07-04 | 2016-10-12 | 雷壹 | Manipulable simulated helicopter |
| 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 |
| CN107021245A (en) * | 2017-03-08 | 2017-08-08 | 贾杰 | Light-duty depopulated helicopter is taken a flight test debugging apparatus |
| CN107230421A (en) * | 2017-04-13 | 2017-10-03 | 沈阳华人风电科技有限公司 | Blade rotation test platform and experimental method |
| CN107651213A (en) * | 2017-04-26 | 2018-02-02 | 天津中德应用技术大学 | Dynamic equilibrium machinery arm |
| CN107085989A (en) * | 2017-06-23 | 2017-08-22 | 许多 | A kind of helicopter instructional device that driving experience is carried out based on supporting surface |
| CN108415442A (en) * | 2018-01-23 | 2018-08-17 | 歌尔股份有限公司 | Unmanned plane adjusts test device |
| CN108415442B (en) * | 2018-01-23 | 2021-04-13 | 歌尔股份有限公司 | Unmanned aerial vehicle adjusts testing arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100368789C (en) | 2008-02-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100368789C (en) | Test bench for testing flight performance of small-sized helicopter | |
| RU195445U1 (en) | EXTERNAL SUSPENSION LOAD STABILITY DEVICE | |
| CA1045611A (en) | Helicopters | |
| CN101298283B (en) | Airborne tripod head apparatus for collecting aerial information and use thereof | |
| US20150136897A1 (en) | Aircraft, preferably unmanned | |
| KR101103846B1 (en) | Floating on the unmanned aerial vehicles and their systems of information collection and transmit methods | |
| CN107856840B (en) | Aircraft with high takeoff and landing stability | |
| GB2455374A (en) | Unmanned aerial vehicle comprising a triangular array of rotors | |
| CN112003190B (en) | Aerial work robot for maintaining power transmission line | |
| Shah et al. | Quadrotor–an unmanned aerial vehicle | |
| WO2019032167A1 (en) | Spin-landing drone | |
| CN2816871Y (en) | Flight coutrol test platform for small-sized unmanned helicopter | |
| JP5871508B2 (en) | Fluid machinery using parallel rotor blades | |
| CN108583867B (en) | Torque self-balancing three-duct fan bionic aircraft | |
| CN107985574B (en) | Buoyancy assisted lifting unmanned aerial vehicle | |
| CN212220590U (en) | Rotor unmanned aerial vehicle helps platform of falling and control system thereof | |
| Ioppo | The design, modelling and control of an autonomous tethered multirotor UAV | |
| JP6798729B2 (en) | An air vehicle with a long body | |
| CN110615092A (en) | Forestry is unmanned aerial vehicle undercarriage for fire prevention | |
| JP6904627B1 (en) | An air vehicle with a long body | |
| KR100860786B1 (en) | A radio controlled helicopter tranining simulation system | |
| JP2007314095A (en) | Airship type aerial crane | |
| JPH0740897A (en) | Radio control aircraft | |
| CN206141824U (en) | Novel unmanned aerial vehicle | |
| CN116096634A (en) | Flying body |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080213 |