CN207114130U - A kind of pulse-combustion wind-tunnel suspension type dynamometric system - Google Patents
A kind of pulse-combustion wind-tunnel suspension type dynamometric system Download PDFInfo
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- CN207114130U CN207114130U CN201720748235.8U CN201720748235U CN207114130U CN 207114130 U CN207114130 U CN 207114130U CN 201720748235 U CN201720748235 U CN 201720748235U CN 207114130 U CN207114130 U CN 207114130U
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- pull bar
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Abstract
The utility model provides a kind of pulse-combustion wind-tunnel suspension type dynamometric system, is related to the hollow aerodynamics force measurement technical field of pulse-combustion wind tunnel test.Including test model, support frame and pedestal.The back front end of test model is provided with a blind hole, and tail end is provided with two through holes, and affixed with the free end of three Y-direction response pull bars respectively, two vertical planes of tail end are provided with two through holes, affixed with the free end of resistance X to response pull bar respectively；It is affixed with the free end of two Z-direction response pull bars respectively；In the middle part of the preceding back timber of support frame and rear back timber and the forward and backward base for being equipped with a draw rod positions adjustment mechanism of right side beam, draw rod positions adjustment mechanism are affixed with Y-direction response pull bar fixing end and Z-direction response pull bar fixing end respectively by sliding block；Resistance X supports the strut ends of stand affixed with tail respectively to response pull bar fixing end；The bottom of support frame and pedestal are affixed；It is fixed between the base on ground and pedestal and is provided with angle board.It is mainly used in air force measurement.
Description
Technical field
It the utility model is related to the hollow aerodynamics force measurement technical field of pulse-combustion wind tunnel test.
Background technology
Hypersonic aircraft uses integrated configuration, and body and the method for engine Separation Research are no longer applicable, flight
Device integration dynamometer check, model quality increase, measuring system frequency response reduce, for short-time pulse wind tunnel force measurement, will cause to try
Test accuracy of measurement and accuracy are reduced, and very big difficulty is brought to hypersonic aircraft integration performance prediction.
Domestic hypersonic wind tunnel experiment model support mode mainly includes shoe formula, side wall support formula, belly stay formula and back up
Formula, but interference of the support section to result of the test with upper type be present.With the raising of test Mach number, incoming feature is by making
With the time it is long, always force down and be changed into that action time is extremely short, stagnation pressure is high, effect of the air-flow to model is changed into impacting from quasi-static loads
Process, therefore the amendment to support interferences also becomes more difficult, there is larger error in force measurements, seriously reduce experiment knot
The degree of accuracy of fruit.In addition, test model is mostly slender bodies, can be by test chamber size when test model yardstick is larger
Limitation, mode supported above are difficult to the big angle of attack and high angles of side slip experiment, it is also difficult to make test model barycenter, balance part school
True centric and carriage rotational center are located at same point, it is seen that mode supported above is uncomfortable in the experiment of High Mach number drive
With.Therefore, research and development can be greatly reduced support interference, the similitude for improving experimental enviroment and real space environment, the increase angle of attack with
The pulse-combustion wind-tunnel suspension type dynamometric system of side slip angle range, raising wind tunnel test efficiency and result of the test accuracy is especially aobvious must
Will.
Utility model content
The purpose of this utility model is to provide a kind of pulse-combustion wind-tunnel suspension type dynamometric system, and it can efficiently solve wind
The technical problems such as air force accuracy of measurement is low caused by hole experiment medium-height trestle interference.
The purpose of this utility model is achieved through the following technical solutions：A kind of pulse-combustion wind-tunnel suspension type dynamometry
System, including test model, support frame and pedestal.The back front end of test model is provided with a blind hole, and tail end is provided with two
Through hole, affixed with the free end of three Y-direction response pull bars respectively, two vertical planes of test model tail end are provided with two through holes, point
It is not affixed with the free end of resistance X to response pull bar；Test model right flank front portion is provided with a blind hole, and rear portion is provided with one and led to
Hole, it is affixed with the free end of two Z-direction response pull bars respectively；A draw rod positions are provided with the middle part of the preceding back timber of support frame to adjust
The base of mechanism, the rear back timber middle part both sides of support frame are respectively provided with the base of a draw rod positions adjustment mechanism, support frame
The forward and backward base for being equipped with a draw rod positions adjustment mechanism of right side beam, draw rod positions adjustment mechanism by sliding block respectively with Y
It is affixed to response pull bar fixing end and Z-direction response pull bar fixing end；Two resistance X support to response pull bar fixing end and two tails
The strut ends of stand are affixed；The base of tail support stand and pedestal rear end are affixed；The bottom of support frame and pedestal are affixed；It is fixed
Angle board is provided between the base and pedestal on ground.
The base edge of the draw rod positions adjustment mechanism is respectively equipped with the screw of eight insertions, and each of the edges respectively sets two
Screw, the position of sliding block are adjusted by caging bolt.
The Y-direction response pull bar and Z-direction response pull bar are provided with the pull bar windscreen of corresponding length.
The front end of the pedestal and the joint face of support frame are provided with three T-slots, and rear end supports stand with two tails
Joint face is provided with four T-slots.
The upper and lower surface of the angle board is provided with the differential seat angle of the test requirements document angle of attack.
Uniform four T-slots of base upper surface, it is affixed with angle board lower surface.
The support frame is former and later two main mount structures of annular, and connection top is provided between the back timber of the forward and backward main frame of annular
Beam, on the basis of X-axis forward direction, left, the lower both sides of two main frames of annular are connected by structural beams respectively, on the right of the main frame of two annulars
Connected by right side beam, the connection back timber and right side beam of the main frame of two of which annular are provided with boss structure, and connection back timber is additionally provided with
Through slot.
The bottom of tail support stand and pedestal rear end T-slot are affixed, tail support stand top provided with resistance X to sound
The through hole that pull bar is affixed is answered, resistance X is to response pull bar and test model drag direction diameter parallel and is in same level.
The X responds pull bar to response pull bar, Y-direction and Z-direction response Tiebar structure is identical, is monolithic construction, thereon
High-precision sensor is equipped with, the Y-direction response pull bar and Z-direction response pull bar are provided with the pull bar windscreen of corresponding length.
The T-slot bar number can rationally be set as the case may be.Base lower surface is provided with four padded rod structures, effect
To ensure that the axis of aircraft is consistent with wind-tunnel axis, post has been connected effect of contraction, booster structure, quantity and size root with ground
Designed according to specific test situation.
The support frame structure form and size design according to specific test chamber Sizes are tested, it is desirable to are easy to
Processing and testing ground installation.Because test chamber space is limited, support frame be designed as by two main frames of annular and up and down
The Vierendeel girder composition of left and right four, to be transported into test chamber assembling.All support frame assemblies are monolithic construction, wherein
Connection back timber, right side beam and two respective connecting portions of ring frame back timber are designed as plateau form, in order to reduce finishing
Area and reduction processing cost.Back timber is provided with through slot, so that the loading steel band of lift Y-direction in calibration test passes through.
Described two tail support stand bottoms and pedestal rear portion T-slot are affixed, and each tail support stand top is provided with through hole
One, affixed to response pull bar with resistance X, tail support stand structure snd size design according to specific test situation, ensure two
Resistance X is to response pull bar and test model diameter parallel and is in same level.
The response pull bar is process for integral material, is furnished with sensing element thereon.
Working process and principle of the present utility model：The system base is connected as whole with ground below test chamber
The constraint of system, fix all component in addition to test model and response pull bar, response pull bar turns into fixing end as the outstanding of constraint
Arm beam.Before wind tunnel test, field calibration experiment need to be carried out to dynamometric system in test chamber, to obtain input load and output
Relation between response signal, the air force solution formula of dynamometric system is obtained accordingly.In wind tunnel test, air incoming acts on examination
Test on model, test model generation displacement and vibration, the pull bar to be played a supportive role to test model is used as Bernoulli Jacob-Europe therewith
Vibration and elastic deformation response occur for the form of straining beam, are arranged at response signal corresponding to the sensor output on response pull bar.
The aerodynamic load that the anti-push out test model of air force solution formula obtained by signal transacting and calibration test is subject to, it is real
Aerodynamic measurement in existing wind tunnel test.
Compared with prior art, the beneficial effects of the utility model are：Existing test model supporting way is improved,
First, the utility model and pulse-combustion test chamber volume matched, are easy to the installation, debugging and school of testing ground
It is accurate.
2nd, complex-curved or internal structure is not present in the utility model, is easy to process, and Stability Analysis of Structures is reliable, and system is overall
Easy to maintain and maintenance.
3rd, the utility model have effectively achieved the air acted in hypersonic pulsed combustion wind tunnel on test model
Dynamometry, the change of the test model angle of attack can be realized by changing the angle board of different angle.
4th, the utility model effectively reduces the influence of support stream field, improves ground wind tunnel test and flight test
Similarity.
Further, for the utility model in addition to resistance X can be not provided with windscreen to pull bar, other pull bars are provided with windscreen, disappear
Except influence of the incoming to response bar, the requirement of pulse-combustion wind-tunnel air force dynamometry is preferably met.
Secondly, system base is fixedly connected with the ground provides constraint for the miscellaneous part in addition to test model and response pull bar,
These parts are made to collectively constitute the fixing end of system.And test model and response pull bar constitute the floating end of system, meet wind
The requirement of hole dynamometry.
Brief description of the drawings
Fig. 1 is the utility model dynamometric system dimensional structure diagram
Fig. 2 is that the utility model responds pull bar schematic diagram
Fig. 3 is the utility model support frame schematic diagram
Fig. 4 is the utility model pedestal schematic diagram
Fig. 5 is the utility model windscreen schematic diagram
Fig. 6 is that the utility model tail supports stand schematic diagram
Fig. 7 is the utility model draw rod positions adjustment mechanism schematic diagram
Embodiment
The utility model is described in further detail with reference to the accompanying drawings and detailed description.
A kind of pulse-combustion wind-tunnel suspension type dynamometric system, the back front end of test model 1 are provided with a blind hole, and tail end is set
There are two through holes, it is affixed with the free end of three Y-direction response pull bars 7 respectively, rationally number can be also set according to specific test situation
Buried via hole, blind hole or the through hole of amount, rational deployment and the response pull bar for matching respective numbers；The vertical plane of the afterbody of test model 1 is set
There are two through holes, affixed to response pull bar 6 free end with two resistance X respectively, it is reasonable also to be set according to specific test situation
Buried via hole, blind hole or the through hole of quantity, rational deployment and the response pull bar for matching respective numbers；The right flank front portion of test model 1 is set
There is a blind hole, rear portion is provided with a through hole, affixed with two Z-direction response pull bar 8 free ends respectively, also can be according to specific experiment
Situation sets buried via hole, blind hole or through hole, rational deployment and the response pull bar for matching respective numbers of fair amount；The Y-direction is rung
Pull bar 7 and Z-direction is answered to respond the pull bar windscreen 4 that pull bar 8 is provided with corresponding length.The base of five draw rod positions adjustment mechanisms 3 point
Not affixed with the forward and backward back timber and right side beam of support frame 2, the sliding block 15 of draw rod positions adjustment mechanism 3 responds with Y-direction respectively to be drawn
The fixing end of bar 7, the Z-direction response fixing end of pull bar 8 are affixed；Fixing ends and the pole of tail support stand 5 of the resistance X to response pull bar 6
Hold affixed；The support frame 2 is former and later two main mount structures of annular, and back timber 12 is provided between the top of two main frames of annular,
On the basis of X-axis forward direction, left, the lower both sides of two main frames of annular are connected by structural beams 14 respectively, on the right of the main frame of two annulars
Connected by right side beam 13, the back timber 12 and right side beam 13 of the main frame 2 of two of which annular are provided with boss structure, and back timber 12 is additionally provided with
Through slot.The tail support base end of stand 5 is affixed with pedestal 11 respectively；Pedestal 11 and angle board 10 are affixed；Angle board 10 and base 9
It is affixed；Support frame 2 and the leading portion of pedestal 11 are affixed；Base 9 is fixedly connected with the ground；The pedestal edge of the draw rod positions adjustment mechanism 3
Edge is respectively equipped with the screw provided with caging bolt 16 of eight insertions, and each of the edges respectively sets two screws, and the position of sliding block 15 leads to
Caging bolt 16 is crossed to adjust.
The response Tiebar structure in wherein tri- directions of X, Y, Z is identical., need to be in test chamber pair first before wind tunnel test
Dynamometric system carries out in-site installation, debugging and calibration test, to obtain the relation between input load and output response signal, accordingly
The air force solution formula of dynamometric system is obtained, needs to adjust five draw rod positions adjustment mechanisms before calibration test and before wind tunnel test
3, ensure that pull bar is in orthogonal or parallel state, ensure the correct decomposition of power and torque.In actual wind tunnel test, air first
Incoming acts on test model 1 by test section and is allowed to produce displacement and vibratory response, and this response is transmitted to seven all responses
Pull bar, seven response pull bars bend elastic deformation and vibratory response as Bernoulli-Euler beam, are arranged at each response and draw
High-precision sensor 17 on bar exports corresponding response signal.Second step, by gathering to response signal and being tried according to calibration
Resistance that the anti-push out test model of air force solution formula for testing to obtain is subject to, lift, side force, pitching moment, rolling moment
And yawing, realize aerodynamic measurement in wind tunnel test.
Claims (9)
1. a kind of pulse-combustion wind-tunnel suspension type dynamometric system, including test model (1), support frame (2) and pedestal (11), its
It is characterised by：The back front end of test model (1) is provided with a blind hole, and tail end is provided with two through holes, is responded respectively with three Y-directions
The free end of pull bar (7) is affixed, and two vertical planes of test model (1) tail end are provided with two through holes, is drawn respectively with resistance X to response
The free end of bar (6) is affixed；Test model (1) right flank front portion is provided with a blind hole, and rear portion is provided with a through hole, respectively with two
The free end of individual Z-direction response pull bar (8) is affixed；A draw rod positions adjustment mechanism is provided with the middle part of the preceding back timber of support frame (2)
(3) base, the rear back timber middle part both sides of support frame (2) are respectively provided with the base of a draw rod positions adjustment mechanism (3), support
The forward and backward base for being equipped with a draw rod positions adjustment mechanism (3) of right side beam (13) of framework (2), draw rod positions adjustment mechanism
(3) pull bar (7) fixing end is responded with Y-direction respectively by sliding block (15) and Z-direction response pull bar (8) fixing end is affixed；Resistance X is to sound
Pull bar (6) fixing end is answered to support the strut ends of stand (5) affixed with tail；The base of tail support stand (5) and pedestal (11) rear end
It is affixed；The bottom of support frame (2) and pedestal (11) are affixed；It is fixed between the base (9) on ground and pedestal (11) and is provided with angle
Spend plate (10).
A kind of 2. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The pull bar position
The base edge for putting adjustment mechanism (3) is respectively equipped with the screw of eight insertions, and each of the edges respectively sets two screws, sliding block (15)
Position is adjusted by caging bolt (16).
A kind of 3. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The Y-direction is rung
Pull bar (7) and Z-direction is answered to respond the pull bar windscreen (4) that pull bar (8) is provided with corresponding length.
A kind of 4. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The pedestal
(11) joint face of front end and support frame (2) is provided with three T-slots, and rear end supports the joint face of stand (5) with two tails
Provided with four T-slots.
A kind of 5. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The angle board
(10) upper and lower surface is provided with the differential seat angle of the test requirements document angle of attack.
A kind of 6. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The base
(9) four T-slots are evenly distributed in the upper surface, it is affixed with angle board (10) lower surface.
A kind of 7. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The carriage
Frame (2) is former and later two main mount structures of annular, is provided with connection back timber (12) between the back timber of the forward and backward main frame of annular, with X-axis just
On the basis of, left, the lower both sides of two main frames of annular are connected by structural beams (14) respectively, pass through the right side on the right of the main frame of two annulars
Curb girder (13) connects, and the connection back timber (12) and right side beam (13) of the main frame (2) of two of which annular are provided with boss structure, connection top
Beam (12) is additionally provided with through slot.
A kind of 8. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The tail support
The bottom of stand (5) and pedestal (11) rear end T-slot are affixed, tail support stand (5) top be provided with resistance X to response pull bar
(6) affixed through hole, resistance X is to response pull bar (6) and test model drag direction diameter parallel and is in same level.
A kind of 9. pulse-combustion wind-tunnel suspension type dynamometric system according to claim 1, it is characterised in that：The X is to sound
Answer pull bar (6), Y-direction response pull bar (7) identical with Z-direction response pull bar (8) structure, be monolithic construction, be equipped with height thereon
Accurate sensor (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720748235.8U CN207114130U (en) | 2017-06-26 | 2017-06-26 | A kind of pulse-combustion wind-tunnel suspension type dynamometric system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720748235.8U CN207114130U (en) | 2017-06-26 | 2017-06-26 | A kind of pulse-combustion wind-tunnel suspension type dynamometric system |
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| Publication Number | Publication Date |
|---|---|
| CN207114130U true CN207114130U (en) | 2018-03-16 |
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| CN201720748235.8U Expired - Fee Related CN207114130U (en) | 2017-06-26 | 2017-06-26 | A kind of pulse-combustion wind-tunnel suspension type dynamometric system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107290124A (en) * | 2017-06-26 | 2017-10-24 | 西南交通大学 | A kind of pulse-combustion wind-tunnel suspension type dynamometric system |
| CN109596305A (en) * | 2018-12-13 | 2019-04-09 | 南京航空航天大学 | The integrated dynamic test system of pneumatic and kinematic parameter and method based on wind tunnel free-flight |
| CN113504026A (en) * | 2021-09-13 | 2021-10-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device based on sonic boom test technology |
| CN114166458A (en) * | 2021-11-30 | 2022-03-11 | 中国航天空气动力技术研究院 | Wind tunnel body part suspension system and method |
| CN117740312A (en) * | 2024-02-21 | 2024-03-22 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
-
2017
- 2017-06-26 CN CN201720748235.8U patent/CN207114130U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107290124A (en) * | 2017-06-26 | 2017-10-24 | 西南交通大学 | A kind of pulse-combustion wind-tunnel suspension type dynamometric system |
| CN109596305A (en) * | 2018-12-13 | 2019-04-09 | 南京航空航天大学 | The integrated dynamic test system of pneumatic and kinematic parameter and method based on wind tunnel free-flight |
| CN113504026A (en) * | 2021-09-13 | 2021-10-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device based on sonic boom test technology |
| CN113504026B (en) * | 2021-09-13 | 2021-11-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device based on sonic boom test technology |
| CN114166458A (en) * | 2021-11-30 | 2022-03-11 | 中国航天空气动力技术研究院 | Wind tunnel body part suspension system and method |
| CN117740312A (en) * | 2024-02-21 | 2024-03-22 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
| CN117740312B (en) * | 2024-02-21 | 2024-05-07 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
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Granted publication date: 20180316 Termination date: 20190626 |