CN201138281Y - Wind tunnel experimental device with parallel typed stamping intake duct of bi-support great attack angle and great lateral slide - Google Patents
Wind tunnel experimental device with parallel typed stamping intake duct of bi-support great attack angle and great lateral slide Download PDFInfo
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- CN201138281Y CN201138281Y CNU2007203106785U CN200720310678U CN201138281Y CN 201138281 Y CN201138281 Y CN 201138281Y CN U2007203106785 U CNU2007203106785 U CN U2007203106785U CN 200720310678 U CN200720310678 U CN 200720310678U CN 201138281 Y CN201138281 Y CN 201138281Y
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Abstract
The utility model relates to an experimental apparatus used for pressing an inlet wind tunnel, which consists of a mechanical part and a control part. The mechanical part comprises a bracing part and a throttle part. The inner part of the throttle part is a rounded air channel. The outer part of the throttle part is connected with an up-and-down machete supporting arm to achieve the change of great angle of sideslip and the accurate regulation of the angle of sideslip. The throttle part provides a back pressure apparatus for pressing the inlet wind tunnel by the fore-and-aft movement of a throttle cone. The throttle cone is connected with the electronic motor in parallel, so the experimental apparatus has a greater operating range of an angle of attack. The electric motor leads the throttle cone to the fore-and-aft movement by the drive of a gear and a lead screw. The lead screw of the throttle cone has double bracing, so the throttle cone is able to bear strong impact and vibration from heavy loading under high-Mach. The control part adopts an automatic closed loop feedback intelligent control system to achieve the retraction control of the throttle cone, the stable time control of pressure measurement and the auto-negotiation and integrating control of throttle cone regulation and data acquisition. Compared with the prior experimental apparatus of inlet tunnel, the experimental apparatus of the utility model has the advantages of larger range of the angles of attack and sideslip, high precision and easy operation. In addition, the throttle apparatus with high precision of regulating flow can resist vibration and is applied to the larger range of Mach numbers. So the experimental apparatus used for pressing the inlet wind tunnel is applicable for the experiment of pressing the inlet wind tunnel.
Description
Technical field
The present invention relates to a kind of experimental provision that is used for the ram air duct wind tunnel experiment.
Background technology
Ram air duct has multiple in carry-on position, air inlet etc. under forward type air inlet, rear-mounted air inlet, head air inlet, side air inlet, belly air inlet, the jaw is arranged; The shape of ram air duct also has multiple, axialsymmetrical inlet, two dimensional inlet, semicircle air intake duct or lower jaw formula air intake duct etc.Each uses punching engine all to be unable to do without the form slection of air intake duct as the aircraft development of power, purpose be to make select air intake duct and aircraft aerodynamic configuration and punching engine matching performance with the best.Also will select ram air duct design Mach number and relay Mach number in addition, purpose is to improve the overall performance of punching engine, satisfies the requirement of aircraft better.The research of the every aspect of above air intake duct all be unable to do without air intake duct wind tunnel test checking, though air intake duct numerical simulation design means has been arranged now, but data also will be verified by wind tunnel test reliably, especially some factors that are difficult to determine in calculating all must be determined through test as air intake duct exit flow field, stall margin etc.
On ram air duct development this point, the U.S. is comparatively leading, after the World War II, the U.S. carries out overtesting to polytype ram air duct, begin from the nineties in 20th century, the U.S. drops into supersonic speed and hypersonic cruise missile that huge funds are greatly developed the ram air duct air inlet when further equipping and improving ballistic missile and subsonic speed cruise missile.
Except the U.S., other country also all pays much attention in supersonic speed ram air duct application facet, and since the 1950's, the Soviet Union (Russia) pays much attention to the research with the supersonic speed cruising missile of punching press air inlet.Russia has guided missiles such as X-31, MAERSK spy, jewel all to adopt ram air duct.It is said, it is the guided missile development of power, flight Mach number 4.0～4.5 that Russia is carrying out with the punching engine, and this guided missile adopts integrated design, and air intake duct is a head air inlet ram air duct, the forebody lower surface has successfully carried out flight test as the pre-pressure surface of ram air duct.
Abroad ram air duct successful Application on model, but research at the beginning of all carried out a large amount of wind tunnel experiments.
Though the research of domestic ram air duct is started late, but development is very fast, and about tens units are carrying out the research of this respect, has successively proposed multiple scheme, and carried out preliminary wind tunnel test, but also has big gap apart from complete independent development and the target that satisfies the model demand.
Compare with conventional air intake duct wind tunnel experiment, the ram air duct wind tunnel experiment has special requirement to experimental facilities, at first is that the experiment Mach number is higher, generally all more than M=2.0, shock load is big, and experimental facilities not only will have rigidity and intensity preferably, also better anti will be arranged.Secondly, it is big that the test angle of attack and yaw angle are wanted, and during M=4.0, the test angle of attack wants to reach 10 degree.Also have, relatively more responsive in the ram air duct venturi to back-pressure, require to provide the throttling awl positional precision of back-pressure to want high.
Domestic existing air inlet experimental facility all has its weak point at present:
(1) yaw angle is realized by the hinge axis form, and the size of yaw angle gets from conversion from the hole span by the measurement model head, because the error of range observation is bigger, the yaw angle of Huan Suaning is also not accurate enough thus, and the scope of yaw angle is also big inadequately.
(2) the throttling awl is connected with motor, and when walking the angle of attack, the model of support arm front comes back, and the restriction device of support arm back is bowed, and motor can bump the second diffuser lower wall of wind-tunnel, thereby has limited test angle of attack scope, and during M=4.01, the angle of attack also can only reach 8 degree.
(3) traditional leading screw is single the support, and similar cantilever beam structure has the angle of attack at model, the throttling awl is subjected under the situation of transverse load, the easy deflection of leading screw, thus cause colliding of throttling awl and outer wall, friction force increases, even the phenomenon that the contrary air-flow of throttling awl can't walk any longer occurs.
(4) traditional control method is open loop control, and the position of throttling awl is moved with data acquisition and coordinated by making a gesture, and not only wastes blow-time, also often occurs coordinating improper and phenomenon that scrap.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, the big sideslip ram air duct of a kind of big angle of attack wind tunnel experiment device is provided and can realizes intelligent closed-loop control, be used for the ram air duct wind tunnel experiment of 0.6 meter X0.6 rice magnitude wind-tunnel.
Technical solution of the present invention: the big big sideslip ram air duct of angle of attack wind tunnel experiment device, its characteristics are: motor is in parallel with the throttling awl, and rotating disc type becomes sideslip structure, leading screw dual-gripper, intelligent closed-loop control.
The present invention's advantage compared with prior art is as follows:
(1) change sideslip of the present invention mechanism has replaced traditional linkage by rotating disc type mechanism, and is not only easy to operate, and the yaw angle scope is big, precision is high, accurate positioning.The yaw angle scope can reach 7 degree, and precision can reach 3 ' in, the time that becomes yaw angle had original two hours to taper to 20 minutes, had improved work efficiency greatly.
(2) consider from increasing angle of attack scope, motor and the parallel connection of throttling awl have been replaced traditional form of connecting, motor has been avoided the second diffuser lower wall position of wind-tunnel, avoided two collide, broken through the restriction that traditional air intake test angle of attack increases, the test angle of attack can reach 13 degree during M=4.0, and when Mach number hanged down, the angle of attack can also be big again.
(3) bore the leading screw dual-gripper that connects firmly from the motion and the throttling of throttling awl, replaced traditional single supporting form, reduced friction, the motion of envoy's flow cone is more steady, and the thrust of contrary air-flow is bigger.
(4) from control mode, become present closed-loop control by original open loop control, realized the intellectuality of control.Can feed back, regulate, show the position of throttling awl; Can realize the control of throttling awl advance and retreat; Can realize tonometric control stabilization time; Can realize that the throttling awl is regulated and the unified control of data acquisition automatic synchronization; Throttling awl precision is 0.1 millimeter.
(5) from the scope of suitable experiment Mach number, the present invention is applicable to M=0.6～4.5, has covered the velocity range of ram air duct.
Description of drawings
Fig. 1 always schemes for structure of the present invention;
Fig. 2 is the annexation figure of supporting section
Fig. 3 becomes the concave station synoptic diagram of sideslip mechanism for rotating disc type;
Fig. 4 becomes the boss synoptic diagram of sideslip mechanism for rotating disc type
Fig. 5 control principle figure
Embodiment
As shown in Figure 1, the present invention bores (4), leading screw (5), bearing (6), bearing (7) from gear (8), main drive gear (9), scrambler (10), motor (11), limit switch (12) by supporting section (1), last lower branch arm (2), restriction portion (3), throttling, leading screw support (13), " L " shape rigidity rectangular (14), angle wedge compositions such as (15).
As depicted in figs. 1 and 2, supporting section (1) is the rectangular parallelepiped of interior round foreign side, its annexation: front end links to each other with the air intake duct model, the rear end links to each other with restriction portion (3), top and bottom are connected with last lower branch arm (1) respectively by the convex-concave round platform, the supporting section top and bottom are the convex round platform, and last lower branch arm joint face is for being the spill round platform.The other end of last lower branch arm can be connected with wind-tunnel, and supporting section then can be around the rotation of the center line of convex-concave round platform, similar rotating disk, thus can change yaw angle, so be called rotating disc type change sideslip mechanism again, the illustrating of its convex-concave round platform in Fig. 3 and Fig. 4.Fixed " L " shape rigidity rectangular (14) in a side of supporting section, when yaw angle is zero, " L " shape rigidity is rectangular, the side of the link of upper branch arm is parallel, when yaw angle is non-vanishing, the side shape of the rectangular link with upper branch arm of " L " shape rigidity at an angle, and the voussoir of an available band angle is filled, wedge angle is exactly the yaw angle of mechanism just, during test, the adjusting of yaw angle only need be changed the voussoir of different angles and just can realize, this voussoir is called angle wedge (15) again.Yaw angle fixedly is by screw retention between the top and bottom of supporting section and last lower branch arm joint face.Respectively there is the screw hole of 6 M5 the top and bottom of supporting section, and the hole site is shown in Fig. 3, and last lower branch arm joint face then has the annular through-hole of 6 M5, and the hole site is shown in Fig. 4.
Restriction portion (3) front end links to each other with supporting section (1), the rear end links to each other with bearing (6), in throttling awl (4), leading screw (5) are arranged, outer wall has fluting, the internal gas flow of coming from supporting section can flow out at fluting, throttling awl can move forward and backward under the drive of leading screw, and correspondingly the air flow stream at fluting place goes out area and changes, thereby regulates flow.The leading screw front end has a leading screw support (13), sliding fit, and the rear end has bearing bearing (7) to support, and claims the leading screw dual-gripper again.The rear portion of leading screw is connected with scrambler (10), can write down the revolution of leading screw rotation.Fixed two limit switches (12) on restriction portion (3) outer wall, be used for limiting throttling and bore the scope that seesaws.When the throttling awl surpassed its range of movement, the throttling awl bumped limit switch (12), and the motor outage stops to move, and plays the effect of support equipment safety.
The rear end of restriction portion connects a bearing (6), and its effect has two, one, the bearing of fixed support leading screw (7), and the 2nd, fixed electrical machinery (11), motor (11) and leading screw (5) are by number of teeth gear (8), (9) transmissions such as two.
Principle of work is as follows
2 rotations (9) of motor (11) driven gear, 1 (8) rotation of gear 2 (9) driven gears, gear 1 (8) drives leading screw (5) rotation, and leading screw (5) rotation drive throttling awl (4) moves forward and backward and scrambler (10) rotation, and throttling awl (4) moves forward and backward the adjusting air flow rate.
As shown in Figure 5, Based Intelligent Control of the present invention comprises throttling awl operation control, data acquisition control two parts.The operation of throttling awl is controlled by stepper motor, motor driver, scrambler, and the signal integrated circuit board, control computer, the position display card, the position display screen is formed.Data acquisition control comprises that electron scanning valve, data acquisition process computing machine and the dynamic pressure transducer of measuring dynamic pressure, amplifier, wave filter, the data acquisition process of measuring steady state pressure show computing machine.This two large divisions is connected by cable, forms complete unified closed-loop control.Write software and adopt the visual Basic 6.0 of Microsoft company.
Control method is as follows:
The awl position of pre-set needs, master control PC calculates the step number that stepper motor will walk and the direction of operation according to given awl position, and sends corresponding pulse signal to stepper motor driver, the drive stepping motor running by servomechanism installation.Stepper motor drives the throttling awl and runs to given position.By grating encoder position feedback is formed closed-loop control to computing machine, up to the difference of position that throttling awl arrives and given position in ± 0.1 millimeter.Simultaneously, the position that shows the throttling awl with the position display panel in real time.
The pressure of static pressure measuring point changes the measurement by the electron scanning valve, all the time be under the monitoring of static acquisition process PC, to controlling tonometric stabilization time, when throttling awl put in place and the pressure stability of static pressure measuring point after, computer-automatic collection also writes down each relevant pressure data.After acquisition and recording finished, information feedback was to master control PC, and next throttling awl position brings into operation.
Need to prove that stepper motor rotates a circle, the throttling awl moves 2 millimeters, and 200 pulses of photoelectric encoder output, the resolution that is to say the position is 0.01 millimeter.Consider actual needs, we are 0.1 millimeter of positional precision location.
For the sake of security, in mechanism, installed limit switch additional,, can in time cut off control loop, the safety of support equipment just in case control is malfunctioning.
Claims (10)
1, be used for the air intake duct wind tunnel experiment device of ram air duct wind tunnel experiment, it is characterized in that comprising: experimental provision comprises machinery and control two parts, and mechanical part is made up of for two sections supporting section and restriction portion,
(1) in the supporting section be circular gas channel, pass through the convex-concave round platform outward and link to each other, can realize the accurate adjusting of the angle of attack and yaw angle with tulwar support arm up and down;
(2) restriction portion is the device that back-pressure is provided for air intake duct that moves forward and backward by the throttling awl, throttling awl and motor parallel, and motor drives the throttling awl by gear and lead screw transmission and moves forward and backward, and the leading screw that connects the throttling awl is dual-gripper;
(3) control section adopts the automatic feedback intelligent control system of closed loop.
2, the air intake duct wind tunnel experiment device that is used for according to claim 1 is characterized in that: the rotating disc type that described yaw angle mapping mode constitutes for the convex-concave round platform.
3, the air intake duct wind tunnel experiment device that is used for according to claim 1 is characterized in that: throttling awl and motor parallel.
4, the air intake duct wind tunnel experiment device that is used for according to claim 1 is characterized in that: the leading screw dual-gripper.
5, the air intake duct wind tunnel experiment device that is used for according to claim 1 is characterized in that: can realize the control of throttling awl advance and retreat.
6, the air intake duct wind tunnel experiment device that is used for according to claim 1 is characterized in that: can realize tonometric control stabilization time.
7, the air intake duct wind tunnel experiment device that is used for according to claim 1 is characterized in that: can realize that the throttling awl is regulated and the unified control of data acquisition automatic synchronization
8, the air intake duct wind tunnel experiment device that is used for according to claim 2, it is characterized in that: described yaw angle mapping mode is a rotating disc type, accurately locatees by angle block gauge.
9, the air intake duct wind tunnel experiment device that is used for according to claim 3 is characterized in that: throttling awl and motor parallel, motor drives the throttling awl by gear and lead screw transmission and moves forward and backward.
10, the air intake duct wind tunnel experiment device that is used for according to claim 4, it is characterized in that: the leading screw dual-gripper, support place has bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007203106785U CN201138281Y (en) | 2007-12-17 | 2007-12-17 | Wind tunnel experimental device with parallel typed stamping intake duct of bi-support great attack angle and great lateral slide |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007203106785U CN201138281Y (en) | 2007-12-17 | 2007-12-17 | Wind tunnel experimental device with parallel typed stamping intake duct of bi-support great attack angle and great lateral slide |
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| CN201138281Y true CN201138281Y (en) | 2008-10-22 |
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| CNU2007203106785U Expired - Fee Related CN201138281Y (en) | 2007-12-17 | 2007-12-17 | Wind tunnel experimental device with parallel typed stamping intake duct of bi-support great attack angle and great lateral slide |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN103089444A (en) * | 2013-01-25 | 2013-05-08 | 西北工业大学 | Structure for reducing back pressure of air inlet channel of inspiration type impulse knocking engine |
| CN104132811A (en) * | 2014-05-04 | 2014-11-05 | 中国航天空气动力技术研究院 | Ramjet air inlet starting hysteresis characteristics test device |
| CN104266817A (en) * | 2014-09-17 | 2015-01-07 | 北京动力机械研究所 | Air inlet channel test throttling cone |
| CN106706257A (en) * | 2017-02-24 | 2017-05-24 | 中国航天空气动力技术研究院 | Wind tunnel back support mechanism capable of achieving continuous change of sideslip angle |
| CN112903232A (en) * | 2021-01-22 | 2021-06-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Flow regulating device for wind tunnel test of aircraft atmospheric data system |
| CN113049211A (en) * | 2021-06-01 | 2021-06-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device |
| CN113945355A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Air inlet duct wind tunnel test simulation system under shock wave |
| CN115266000A (en) * | 2022-09-28 | 2022-11-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Combined dynamic air inlet duct wind tunnel test device |
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2007
- 2007-12-17 CN CNU2007203106785U patent/CN201138281Y/en not_active Expired - Fee Related
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102288381B (en) * | 2011-05-05 | 2013-04-17 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN103089444A (en) * | 2013-01-25 | 2013-05-08 | 西北工业大学 | Structure for reducing back pressure of air inlet channel of inspiration type impulse knocking engine |
| CN103089444B (en) * | 2013-01-25 | 2014-10-15 | 西北工业大学 | Structure for reducing back pressure of air inlet channel of inspiration type impulse knocking engine |
| CN104132811B (en) * | 2014-05-04 | 2016-08-24 | 中国航天空气动力技术研究院 | Ramjet engine air inlet starting hesitation characteristic test apparatus |
| CN104132811A (en) * | 2014-05-04 | 2014-11-05 | 中国航天空气动力技术研究院 | Ramjet air inlet starting hysteresis characteristics test device |
| CN104266817A (en) * | 2014-09-17 | 2015-01-07 | 北京动力机械研究所 | Air inlet channel test throttling cone |
| CN106706257A (en) * | 2017-02-24 | 2017-05-24 | 中国航天空气动力技术研究院 | Wind tunnel back support mechanism capable of achieving continuous change of sideslip angle |
| CN106706257B (en) * | 2017-02-24 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of wind-tunnel back support mechanism of achievable yaw angle consecutive variations |
| CN112903232A (en) * | 2021-01-22 | 2021-06-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Flow regulating device for wind tunnel test of aircraft atmospheric data system |
| CN113049211A (en) * | 2021-06-01 | 2021-06-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device |
| CN113049211B (en) * | 2021-06-01 | 2021-08-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device |
| CN113945355A (en) * | 2021-09-21 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Air inlet duct wind tunnel test simulation system under shock wave |
| CN113945355B (en) * | 2021-09-21 | 2024-01-30 | 中国航空工业集团公司西安飞机设计研究所 | Air inlet channel wind tunnel test simulation system under shock wave |
| CN115266000A (en) * | 2022-09-28 | 2022-11-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Combined dynamic air inlet duct wind tunnel test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: The gloomy wind-tunnel engineering of Beijing space flight benefit Co., Ltd Assignor: China Aerospace Aerodynamic Technology Institute Contract record no.: 2014990000609 Denomination of utility model: Wind tunnel experimental device with parallel typed stamping intake duct of bi-support great attack angle and great lateral slide Granted publication date: 20081022 License type: Exclusive License Record date: 20140801 |
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| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20081022 Termination date: 20161217 |