CN103674475B - For the hatch door operating mechanism of full machine wind tunnel experiment - Google Patents
For the hatch door operating mechanism of full machine wind tunnel experiment Download PDFInfo
- Publication number
- CN103674475B CN103674475B CN201310722297.8A CN201310722297A CN103674475B CN 103674475 B CN103674475 B CN 103674475B CN 201310722297 A CN201310722297 A CN 201310722297A CN 103674475 B CN103674475 B CN 103674475B
- Authority
- CN
- China
- Prior art keywords
- hatch door
- control lever
- operating mechanism
- lever shaft
- motor
- 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 - Fee Related
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention proposes a kind of hatch door operating mechanism for full machine wind tunnel experiment, described hatch door is hinged on the fuselage of model aircraft rotationally by a rotating shaft, wherein, described operating mechanism has a control lever shaft being fixedly connected with the rotating shaft of described hatch door, a motor that drives described control lever shaft to rotate, is provided with at least one reduction gearing between described motor and described control lever shaft. Hatch door operating mechanism for full machine wind tunnel experiment of the present invention, provides a kind of hatch door operating mechanism of opening and closing of the hatch door handled for full machine wind tunnel experiment.
Description
Technical field
The present invention relates to a kind of aviation aerodynamics testing equipment, especially a kind of for full machine wind-tunnel examinationTest in process, handle the mechanism of hatch door opening and closing.
Background technology
Full machine wind tunnel test is according to aerodynamic principle, whole dummy vehicle is fixed in wind-tunnel,Flow through dummy vehicle by applying artificial airflow, with the state of flight of various complexity in this analog space, obtainGet test data. The main purpose of full machine wind tunnel test is to obtain the various air force ginsengs of model aircraftChanging Pattern and the maneuvering performance of simulated aircraft under different flow fields, flow condition of number.
Under normal circumstances, the size of wind-tunnel can cause certain restriction to the size of model aircraft, namelySay the size in order to adapt to wind-tunnel, the model aircraft adopting in full machine wind tunnel experiment process all can not be tooTherefore many times can only once blow experiment for one or several parts, remaining part greatly,Can only make stationary state. For example, each control surface of aircraft, for example flaperon, elevator, completeMoving horizontal tail, rudder, front wing etc. are all the critical pieces of manipulation aircraft, and therefore these parts need emphasisConsider its impact of different states on aircraft. Now, due to the restriction of model aircraft size, aircraft mouldOther parts of type, the parts such as such as undercarriage door are set as closure state conventionally, therefore general aircraftOn model, be all the profile that is provided with hatch door, this hatch door not can be opened in fact, for hatch doorGenerally all do not set special wind tunnel experiment project Deng the parts that need under normal circumstances opening and closing.
Reality is, under aircraft normal condition, take off and landing process in undercarriage door be all needsOpen closed, in addition, other hatch door of some that also may exist on aircraft is also in flight courseNeeding opening and closing, aerodynamics state is now also to need the problem paid close attention to. But,In full machine wind tunnel experiment process, a real aircraft can not be placed in wind-tunnel and dry. And conventionallyFull machine wind tunnel experiment in, model aircraft is very little, also can not be by the true operating mechanism of hatch door in proportionDwindle and be arranged in model aircraft, such cost is too high and structural strength is also inadequate, therefore, is badly in need of providingA kind of hatch door operating mechanism of opening and closing of the hatch door handled for full machine wind tunnel experiment.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of hatch door for full machine wind tunnel experiment and handles machineStructure, to reduce or to avoid problem noted earlier.
For solving the problems of the technologies described above, the present invention proposes a kind of hatch door for full machine wind tunnel experiment and handleMechanism, for handle the opening and closing of hatch door in full machine wind tunnel experiment process, described hatch door is by oneIndividual rotating shaft is hinged on the fuselage of model aircraft rotationally, wherein, described operating mechanism have one withThe control lever shaft that the rotating shaft of described hatch door is fixedly connected with, a motor that drives described control lever shaft to rotate, described inBetween motor and described control lever shaft, be provided with at least one reduction gearing.
Preferably, between described reduction gearing and described motor, be provided with a clutch controller.
Preferably, described rotating shaft is fixedly connected with described hatch door.
Preferably, described rotating shaft extends to form described control lever shaft from described hatch door.
Preferably, described control lever shaft is fixedly mounted on described fuselage interior by a support, described manipulationThe end of axle is provided with a steerage gear, and described steerage gear engages with described reduction gearing, described in subtractSpeed gear is supported on described support.
Preferably, described support is strip, has been arranged side by side multiple through holes on it, each described through holeIn be provided with a bearing, the outer ring of described bearing and described through hole interference fit, in described bearingCircle is fixedly connected with the rotating shaft of described control lever shaft and described reduction gearing respectively.
Preferably, described motor and described clutch controller one are supported on described support.
Preferably, described support is L shaped, wherein on a L shaped arm, has been arranged side by side multiple through holes,In each described through hole, be provided with a bearing, the outer ring of described bearing and described through hole interference fit,The inner ring of described bearing is fixedly connected with the rotating shaft of described control lever shaft and described reduction gearing respectively, described electricityMachine and described clutch controller are fixedly connected on another arm of described L bracket.
Preferably, described steerage gear, reduction gearing, clutch controller and motor are arranged on describedAngle between two L shaped arms of frame inner side, described support with plane that two arm was formedOne side is fixedly mounted on described fuselage interior.
Hatch door operating mechanism for full machine wind tunnel experiment of the present invention, provides a kind of for full machine wind-tunnelThe hatch door operating mechanism of the opening and closing of the hatch door handled of experiment.
Brief description of the drawings
The following drawings is only intended to the present invention to schematically illustrate and explain, does not limit model of the present inventionEnclose. Wherein,
What Fig. 1 showed is the hatch door for full machine wind tunnel experiment according to a specific embodiment of the present inventionStructural representation;
What Fig. 2 showed is according to a specific embodiment of the present invention a kind of for full machine wind tunnel experimentThe structural representation of hatch door operating mechanism;
What Fig. 3 showed is for full machine wind tunnel experiment according to the one of another specific embodiment of the present inventionThe structural representation of hatch door operating mechanism.
Detailed description of the invention
Understand for technical characterictic of the present invention, object and effect being had more clearly, now contrast accompanying drawingThe specific embodiment of the present invention is described. Wherein, identical parts adopt identical label.
What Fig. 1 showed is the hatch door for full machine wind tunnel experiment according to a specific embodiment of the present invention1 structural representation. What in figure, show is the partial structurtes schematic diagram of a model aircraft, its demonstrationBe on fuselage 2, to be provided with an opening, be coated with a hatch door 1 at aperture position, this hatch door 1 canTo be undercarriage door, can be also any can be in true aircraft flight process opening and closingHatch door structure, that is to say, the hatch door 1 on this model aircraft is that one can be handled it by operating mechanismThe structure of opening and closing.
Hatch door 1 is hinged on rotationally by a rotating shaft 11 on the fuselage 2 of model aircraft, specifically showsFor, be provided with a rotating shaft 11 being connected to one with hatch door 1 in a side edge of hatch door 1,Be provided with the hinged auricle of the described rotating shaft 11 of multiple supports at the edge of opening of fuselage 2. By of the present inventionOperating mechanism, can handle rotating shaft 11 and rotate, thereby controls the opening and closing of hatch door 1. Below to thisDescribe in detail.
What wherein show as shown in Figure 2, is used for full machine according to the one of a specific embodiment of the present inventionThe structural representation of the hatch door operating mechanism of wind tunnel experiment, it is real that described operating mechanism is used in full machine wind-tunnelTest the opening and closing of handling hatch door 1 in process. Described operating mechanism have one with the rotating shaft of hatch door 121, one motors that drive described control lever shaft 21 to rotate of control lever shaft that 11 (referring to Fig. 1) are fixedly connected with22, between described motor 22 and described control lever shaft 21, be provided with at least one reduction gearing 23.
In a specific embodiment, although the manipulation rotating shaft 11 shown in control lever shaft 21 and Fig. 1 can be led toCross the structures such as mandrel connector and link together, still, due in full machine wind tunnel experiment, model aircraft phaseBe very little for true aircraft, the limited space in fuselage 2, does not often have additional space settingMandrel connector, or very little for the opening of hatch door 1, be inconvenient to install the structures such as mandrel connector is set,Therefore, in the present embodiment, in fact control lever shaft 21 is exactly that rotating shaft 11 extends to form from hatch door 1,That is to say, in fact control lever shaft 21 shown in Fig. 2 is exactly the prolongation of rotating shaft 11.
In another specific embodiment, between reduction gearing 23 and motor 22, can also arrange one fromHop controller 24. In conventionally true aircraft, handle the hydraulic mechanism often of hatch door opening and closing, itsSteering force is fine control all, but in full machine wind tunnel experiment process, because model aircraft is too little, certainlyCan not operating mechanism be set according to the pattern of true aircraft, therefore, what the present invention adopted is electrically-energizedPattern. But, for motor 22, except need to slowing down to the rotating speed of motor 22,After also will considering that hatch door 1 is opened to its maximum rating, motor 22 continues to drive hatch door 1 to produceCertain bounce-back (even if cut off motor power at once, but because the rotary inertia of hatch door exists, hatch doorThen 1 still can continue its opening operation rebounds), this does not exist true aircraftProblem, for the model of an airplane of wind tunnel experiment, although this bounce seem not quite, butBe that gear 23, motor 22 in model is but too large, be easy to be damaged, for keeping awayExempt from this problem, be provided with in the present embodiment clutch controller 24, for being opened to necessarily at hatch door 1When degree, for example, when being opened to maximum state, the power of motor 22 and gear 23 are cutDisconnected, make the bounce of hatch door 1 can driven gear 23 freely-movables, but but not can with motor 22Have an effect, bounce can be discharged.
Certainly, for a person skilled in the art, any existing machinery or electronics mode are setClutch controller be all fine, for example, can adopt the clutch controller of mechanical system, make cabinWhen door 1 reaches certain angle, motor 22 is understood automatic trips from being connected with gear 23, or can adoptElectrically-energized clutch controller, in the time that hatch door 1 reaches certain angle, the power supply of automatic cut-off motor 22,Cut off the connection between motor 22 and gear 23 simultaneously.
In embodiment illustrated in fig. 2, control lever shaft 21 is fixedly mounted in fuselage 2 by a support 25Portion, the end of control lever shaft 21 is provided with a steerage gear 26, steerage gear 26 and reduction gearing 23Engagement (reduction gearing 23 showing in figure has two, and multi-stage speed-reducing namely can be provided), reducing gearWheel 23 is supported on support 25.
In a specific embodiment, support 25 is strip, has been arranged side by side multiple through holes on it, everyIn individual through hole, be provided with a bearing 251, the outer ring of described bearing 251 and through hole interference fit, instituteThe inner ring of stating bearing 251 is fixedly connected with the rotating shaft of control lever shaft 21 and reduction gearing 23 respectively.
In another specific embodiment, also motor 22 and clutch controller 24 one can be supported onOn described support 25. As shown in Figure 3, wherein show according to another specific embodiment of the present inventionA kind of structural representation of the hatch door operating mechanism for full machine wind tunnel experiment.
Specifically, the described support 25 of this enforcement is L shaped, wherein on a L shaped arm, establishes side by sideBe equipped with multiple through holes, in each through hole, be provided with a bearing 251, the outer ring of described bearing 251 withThrough hole interference fit, the inner ring of described bearing 251 respectively with the turning of control lever shaft 21 and reduction gearing 23Axle is fixedly connected with, and motor 22 and clutch controller 24 are fixedly connected on another of described L bracket 25On arm.
In the structure of the L bracket 25 showing in figure, all handle structure is all arranged on L shapedTwo arm angle inner sides of frame 25, that is to say steerage gear 26, reduction gearing 23, clutch for clutch controlDevice 24 and motor 22 are arranged on the angle inner side between two L shaped arms of support 25, support 25Be fixedly mounted on fuselage 2 inside with a side of the plane that two arm was formed. This at the present embodimentIn structure, the entire infrastructure of operating mechanism can be assembled on support 25 in advance, then put into fuselage 2Inside, be screwed into support 25 from the outside of fuselage 2 by screw etc., thus support 25 is fixingInstall, compare previous embodiment, saved additionally in the inner connection motor 22 of fuselage 2, clutch controlThe isostructural trouble of device 24 processed, further fixes and (flies after connection nor be used in fuselage 2The fuselage interior space of machine model is very little, is difficult to operation).
The foregoing is only the schematic detailed description of the invention of the present invention, not in order to limit model of the present inventionEnclose. Any those skilled in the art does under the prerequisite that does not depart from design of the present invention and principleEquivalent variations, amendment and combination, all should belong to the scope of protection of the invention.
Claims (4)
1. the hatch door operating mechanism for full machine wind tunnel experiment, for handle the opening and closing of hatch door (1) in full machine wind tunnel experiment process, described hatch door (1) is hinged on rotationally by a rotating shaft (11) on the fuselage (2) of model aircraft, it is characterized in that, described operating mechanism has a control lever shaft (21), and described control lever shaft (21) is extended to form from described hatch door (1) by described rotating shaft (11); A motor (22) that drives described control lever shaft (21) to rotate, is provided with at least one reduction gearing (23) between described motor (22) and described control lever shaft (21); Described rotating shaft (11) is fixedly connected with described hatch door (1); Between described reduction gearing (23) and described motor (22), be provided with a clutch controller (24); Described motor (22) is supported on a support (25) with described clutch controller (24) one, described control lever shaft (21) is fixedly mounted on described fuselage (2) inside by described support (25), the end of described control lever shaft (21) is provided with a steerage gear (26), described steerage gear (26) engages with described reduction gearing (23), and described reduction gearing (23) is supported on described support (25).
2. hatch door operating mechanism according to claim 1, it is characterized in that, described support (25) is strip, multiple through holes on it, are arranged side by side, in each described through hole, be provided with a bearing (251), the outer ring of described bearing (251) and described through hole interference fit, the inner ring of described bearing (251) is fixedly connected with the rotating shaft of described control lever shaft (21) and described reduction gearing (23) respectively.
3. hatch door operating mechanism according to claim 1, it is characterized in that, described support (25) is L shaped, wherein on a L shaped arm, multiple through holes are arranged side by side, in each described through hole, be provided with a bearing (251), the outer ring of described bearing (251) and described through hole interference fit, the inner ring of described bearing (251) is fixedly connected with the rotating shaft of described control lever shaft (21) and described reduction gearing (23) respectively, described motor (22) is fixedly connected on another arm of described L bracket (25) with described clutch controller (24).
4. hatch door operating mechanism according to claim 3, it is characterized in that, described steerage gear (26), reduction gearing (23), clutch controller (24) and motor (22) are arranged on the angle inner side between two L shaped arms of described support (25), and the side with the plane that two arm was formed of described support (25) is fixedly mounted on described fuselage (2) inside.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610243020.0A CN105758615B (en) | 2013-12-23 | 2013-12-23 | A kind of landing gear compartment gate operator for model aircraft |
| CN201610243031.9A CN105699047B (en) | 2013-12-23 | 2013-12-23 | Hatch door operating mechanism for model aircraft |
| CN201310722297.8A CN103674475B (en) | 2013-12-23 | 2013-12-23 | For the hatch door operating mechanism of full machine wind tunnel experiment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310722297.8A CN103674475B (en) | 2013-12-23 | 2013-12-23 | For the hatch door operating mechanism of full machine wind tunnel experiment |
Related Child Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610243031.9A Division CN105699047B (en) | 2013-12-23 | 2013-12-23 | Hatch door operating mechanism for model aircraft |
| CN201610243020.0A Division CN105758615B (en) | 2013-12-23 | 2013-12-23 | A kind of landing gear compartment gate operator for model aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103674475A CN103674475A (en) | 2014-03-26 |
| CN103674475B true CN103674475B (en) | 2016-05-25 |
Family
ID=50312703
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310722297.8A Expired - Fee Related CN103674475B (en) | 2013-12-23 | 2013-12-23 | For the hatch door operating mechanism of full machine wind tunnel experiment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103674475B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5881973A (en) * | 1996-09-04 | 1999-03-16 | Mcdonnell Douglas Corporation | Passenger door operation control set |
| CN103105259A (en) * | 2011-11-14 | 2013-05-15 | 中国航空工业集团公司沈阳空气动力研究所 | Device for motion simulation and load measurement of weapon cabin door and method |
| CN102980738B (en) * | 2012-12-28 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Cabin door opening device for hypersonic velocity wind tunnel experiment cabin |
| CN103291190B (en) * | 2013-06-25 | 2016-01-20 | 江苏金秋竹集团有限公司 | A kind of lateral sliding door |
-
2013
- 2013-12-23 CN CN201310722297.8A patent/CN103674475B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN103674475A (en) | 2014-03-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2947003B1 (en) | Rotary drive assembly for aircarft wing tip and assembling method | |
| CN204916182U (en) | High -speed vertical take -off and landing aircraft | |
| CN207157515U (en) | A kind of patrol unmanned machine control system | |
| CN105241631A (en) | Helicopter tail rotor vortex ring state testing system | |
| CN103895853A (en) | Design method for opening embedded cabin | |
| CN105818971A (en) | Unmanned gyroplane | |
| CN105059537A (en) | UAV (unmanned aerial vehicle) | |
| CA2893341C (en) | Casing opening/closing system of an unmanned helicopter | |
| US10830210B2 (en) | Emergency wind turbine system comprising a device for rotatably locking the turbine | |
| CN208412092U (en) | A kind of more power fixed wing aircrafts | |
| CN103674474B (en) | Full machine wind tunnel experiment rudder face operating control crash simulation device | |
| CN103674475B (en) | For the hatch door operating mechanism of full machine wind tunnel experiment | |
| CN203845012U (en) | Rotary flapping wing type driving airplane | |
| CN105035324B (en) | Coaxial two wheels robot is jettisoninged cabin | |
| CN105699047B (en) | Hatch door operating mechanism for model aircraft | |
| CN105758615B (en) | A kind of landing gear compartment gate operator for model aircraft | |
| CN107444632A (en) | It is a kind of can VTOL dalta wing unmanned plane | |
| CN108639333B (en) | Multi-power fixed wing aircraft with vertical lifting function | |
| CN108750113A (en) | A kind of annular wing unmanned vehicle | |
| CN104760694A (en) | Dual rotor aircraft provided with foldable and dangling lower blades | |
| CN107933889A (en) | A kind of unmanned aerial vehicle body deceleration panel assembly | |
| CN210707863U (en) | Electric rudder system for large-sized unmanned aerial vehicle | |
| CN210015559U (en) | Flap control device for simulated aircraft | |
| CN102923302A (en) | Flexible connection rotating lifting airfoil of helicopter | |
| CN210116640U (en) | High-lift device and short-distance lifting conveyor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160525 Termination date: 20171223 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |