CN105606333A - Small-deformation wind tunnel train balance - Google Patents
Small-deformation wind tunnel train balance Download PDFInfo
- Publication number
- CN105606333A CN105606333A CN201610126091.2A CN201610126091A CN105606333A CN 105606333 A CN105606333 A CN 105606333A CN 201610126091 A CN201610126091 A CN 201610126091A CN 105606333 A CN105606333 A CN 105606333A
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- balance
- rod
- type
- pole
- small deformation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
Abstract
Provided is a small deformation wind tunnel train balance, comprising a rod-type balance and a support pole. Two ends of the rod-type balance have a conical structure. A balance element is arranged between the two ends of the rod-type balance. The balance element has a conical structure, which is provided thereon with a five-component element adjacent to the large-end part and a resistance element adjacent to the small-end part. The support pole comprises a conical front end and a straight segment. The rod-type balance and the conical front end of the support pole are matched via a conical surface and are tensioned via a wedge. The rod-type balance is arranged in an inner cavity of a tested model. The minimum diameter of the inner cavity of the tested model is greater than the maximum diameter of the rod-type balance. The invention breaks through the traditional equal-diameter balance support rod design method and the three-segment type rod-type balance structure, increases the diameter of the balance, shortens the balance length, realizes little deformation of the balance, improves the rigidity and the bearing ability of the balance, is applicable to balance development for wind tunnel experiments with large impact load or severe vibration, and achieves good practicability and popularization values.
Description
Technical field
The invention belongs to Aero-Space dynamometer check aerodynamic force field of measuring technique, especially for rush temporarily formula at a high speed and when hypervelocity wind tunnel dynamometer check starts and cut-offs model and rod-type balance prop up lever system high vibration problem, utilize taper balance component structure and measuring cell compact layout to improve balance and pole integral rigidity, strengthen model supporting system anti-vibration ability, carry out the accurate six component aerodynamic force of dummy vehicle of safety and stability more and measure.
Background technology
Rush temporarily in the dynamometer check of formula high-speed wind tunnel, start and cut-off process gas and shock wave to scan the shock loading causing may be several times even tens times of balance range, and decentralization is very large, is difficult to measure and control. The rigidity of the Oscillation Amplitude that shock loading causes and balance and pole, model weight, blowing mode have substantial connection, and to constituting a serious threat the service life of experimental safe, certainty of measurement and balance. Can reduce certain shock loading by modes such as model loss of weight, reduction ram compressions, but be subject to structure and wind-tunnel facilities restriction, effect is unsatisfactory. The rigidity and the bearing capacity that in limited design space, improve balance and pole are another kind of effective methods.
Common rod-type balance diameter general with the straight section equal diameters such as pole, and have enough gaps with mould impression, to ensure being subject to aerodynamic loading balance and pole distortion by model, model and balance pole do not produce space interference afterwards. Be subject to model trailing space size restrictions and enough gap requirements, balance and a shank diameter are less, support system insufficient rigidity. And model central space abundance, sometimes for loss of weight also can remove model cavity in unnecessary material. Due to balance and pole front end equal diameter, the excesssive gap of mould impression and balance, does not make full use of the space in model cavity when balance and pole design, causes balance rigidity and bearing capacity deficiency. In addition, rod-type balance is general adopt before in rear three sections of measuring cells, length and material cutting are serious, further loss balance rigidity.
Summary of the invention
The present invention underuses the defect in mould impression space in order to solve equal diameter syllogic rod-type balance rigidity and bearing capacity deficiency and balance design, a kind of small deformation wind-tunnel balance and pole are provided, adopt unique mentality of designing and rod-type balance and branching rod structure to strengthen rigidity and the bearing capacity of system, improve the safety and stability of wind-tunnel balance, extend the service life of balance.
To achieve these goals, the technical solution used in the present invention is:
A kind of small deformation wind-tunnel balance, comprises the gentle pole in rod-type sky:
Described rod-type balance two ends are pyramidal structure, and the centre at rod-type balance two ends is a day flat elements,
Within described day, flat elements is pyramidal structure, in pyramidal structure, is provided with five component elements near position, large end, is provided with resistance element near small end position,
Described pole comprises tapered front end and straight section such as grade, and described rod-type balance mates by the conical surface with the tapered front end of pole and utilizes chock tension, and described rod-type balance is arranged in the inner chamber of tested model,
The minimum diameter of described tested mould impression is greater than the maximum gauge of rod-type balance.
In technique scheme, the tapering of the tapered front end of described pole equates with the tapering of the sky flat elements of rod-type balance.
In technique scheme, the maximum gauge of the tapered front end of described pole equates with a day minimum diameter for flat elements pyramidal structure.
In technique scheme, the equal diameters of the straight section such as minimum diameter and pole of the tapered front end of described rod-type balance.
In technique scheme, described five component elements comprise symmetrically arranged girder construction more than four groups, and the sheet beam being positioned on axis is measuring cell, and the post beam that is positioned at all quadrants is carrier bar.
In technique scheme, the resistance element of described rod-type balance comprises a pair of Y shape measuring cell and the two groups of resistance support shell fragments that are symmetrical in balance axis arranged.
In technique scheme, described resistance support shell fragment is two groups of variable cross-section shell fragments that are symmetrical in balance axis arranged.
In technique scheme, every group is supported shell fragment equal strength, and width matches with a day flat elements tapering profile.
Operation principle of the present invention is: utilize model balance pole system variant feature, make full use of mould impression adequate space, increase balance diameter as far as possible, shorten balance length, reduce the cutting of balance material, reach the object that strengthens system stiffness and bearing capacity. Specifically, model is subject to after aerodynamic loading, and it is substantially indeformable that model main body itself can be regarded rigid body as, and distortion is mainly produced by balance and pole. Produce after distortion, what most probable and model were touched is the straight sections such as model afterbody inner chamber and pole, and mould impression inner space is more sufficient. Therefore, can make full use of mould impression remaining space, increase balance diameter, to reduce the distortion of balance stand under load. In addition, two other key factor that affects balance distortion is balance length and material cutting degree, therefore can shorten balance leement duration, adopts the topology layout of two-part balance further to improve rigidity.
Effect of the present invention and benefit are: the one, develop unique model balance pole system thought, and break through traditional equal diameter balance pole method for designing and syllogic rod-type sky flat structure. The 2nd, increase balance diameter, shorten balance length, balance distortion is little, has improved rigidity and the bearing capacity of balance. The 3rd, effectively suppress system vibration, improve the safety and stability of test, extend balance service life, improve the overall performance of balance pole. The 4th, expand balance design space, reduce balance design difficulty, be conducive to balance component structure and layout optimization design. The 5th, can be widely used in shock loading greatly or vibrate in violent wind tunnel test balance development, there is good practicality and promotional value.
Brief description of the drawings
Fig. 1 is a kind of small deformation wind-tunnel balance assembling schematic diagram of the present invention;
Fig. 2 is a kind of small deformation wind-tunnel balance structural representation of the present invention;
Fig. 3 is the A-A cutaway view of Fig. 2;
Fig. 4 is the B-B cutaway view of Fig. 2;
In figure: 1. model, 11. inner chambers, 12. afterbody inner chambers, 2. rod-type sky flat elements, 21. hold greatly, 22. 5 component elements, 221. measuring cells, 222. carrier bars, 23. resistance elements, 231. elastic support sheets, 232. " Y " shape measuring cell, 24. small ends, 3. pole, 31. tapered front end, 32. straight sections such as grade.
Detailed description of the invention
Fig. 1 is a kind of small deformation wind-tunnel balance assembling schematic diagram of the present invention. A kind of small deformation wind-tunnel balance of the present invention mainly comprises the gentle pole in rod-type sky, and described rod-type balance and pole are strained by cone match chock, and bullet is positioned at mould impression inside. Described rod-type sky flat elements maximum gauge is slightly less than model afterbody inner chamber minimum diameter, in increasing rod-type balance element diameter, facilitates the installation and removal of model. Described rod-type sky flat elements tapering part minimum diameter is greater than the straight section diameters such as pole, and numerical value calculates by tapering constraintss such as balance and pole front ends.
Fig. 2 is a kind of small deformation wind-tunnel balance structural representation of the present invention. Described rod-type sky flat elements is tapered, is greater than the end diameter near model afterbody near the outside diameter of model head, in large end one side of described rod-type sky flat elements, five component elements is set, and small end one side arranges resistance element.
Fig. 3 is the A-A cutaway view of Fig. 2, and described rod-type balance five component elements are for being symmetrical arranged girder construction more than four groups, and the sheet beam being positioned on axis is measuring cell, and the post beam that is positioned at all quadrants is carrier bar.
Fig. 4 is the B-B cutaway view of Fig. 2, and the resistance element of described rod-type balance is be symmetrical in balance axis arranged a pair of " Y " shape measuring cell. The resistance support shell fragment of described rod-type balance is two groups of variable cross-section shell fragments that are symmetrical in balance axis arranged, and every group is supported shell fragment and press the principle of equal strength design, width and a day flat elements tapering profile adaptation.
Further illustrate the implementation step of a kind of small deformation wind-tunnel balance of the present invention below with reference to Fig. 1-4:
Can estimate the maximum gauge of the straight sections such as pole according to the minimum diameter of model afterbody inner chamber and aerodynamic loading, guarantee to have enough gaps that the straight sections such as afterbody inner chamber and pole can not be touched in process of the test. Meanwhile, can determine the maximum gauge of the large end of rod-type sky flat elements according to the minimum diameter of model afterbody inner chamber, guarantee that rod-type sky flat elements can insert mould impression, the installation and removal of implementation model smoothly. Can calculate rod-type sky flat elements and the identical tapering of pole tapered front end according to above-mentioned two preliminary diameter dimensions and the length of mould impression, its length is less than the length of mould impression, to do not affect model afterbody inner chamber aerodynamic characteristic.
Further, can estimate other suitable size of mould impression, guarantee that rod-type sky flat elements and pole tapered front end inside have enough gaps can not touch with mould impression after stand under load. Because pole tapered front end and rod-type sky flat elements are the slow increases of variable cross-section, entire system rigidity and combination property under the prerequisite that does not affect dismounting, are significantly improved on the one hand; The cross section slowly changing is on the other hand optimized balance stress distribution, has strengthened the security of balance and pole coupling part.
As shown in Figure 2, in conjunction with Fig. 3 and Fig. 4, be the typical structure of rod-type balance of the present invention, according to balance design load and other technical indicator, determine length, the five component elements of rod-type sky flat elements, the physical dimension of resistance element, make a day flat elements compactness, further to improve balance rigidity as far as possible. Five component elements adopt many girder constructions, and in Fig. 3, each beam section is arranged on away from the position of centre of form main shaft to improve cross section bending rigidity as far as possible. Preferentially, can select four sheet beams that are positioned at reference axis as measuring cell, select the root post beam that is arranged symmetrically with as carrier bar, so that process and paste strain gauge.
" Y " shape measuring cell transition of resistance element is round and smooth, prevents that stress is concentrated; Strain gauge sticks on the inclined-plane of the beam of uniform strength, the impact bringing to reduce strain gauge paste position. It is definite that each physical dimension of every group of elastic support sheet pressed the principle of equal strength, and proof stress distributes more even, without obviously stress is concentrated.
According to Load Characteristics and specific design index, five described component elements and resistance element can be replaced by the flexible member of other version.
Balance complex structure, Traditional calculating methods is difficult to be out of shape more accurately and displacement result, wants the space interference situation after the stand under load of serious analysis and forecast model and pole before processing, reserved certain surplus. Therefore, model balance after having designed props up lever system need to carry out deformation simulation by finite element emulation software, and adjust relative dimensions, mould impression is made full use of, and gap is enough, guarantee that space interference does not occur the straight sections such as model afterbody inner chamber and pole in the situation that being subject to limit aerodynamic loading.
The present invention is not limited to aforesaid detailed description of the invention. The present invention expands to any new feature or any new combination disclosing in this manual, and the arbitrary new method disclosing or step or any new combination of process.
Claims (8)
1. a small deformation wind-tunnel balance, comprises the gentle pole in rod-type sky, it is characterized in that:
Described rod-type balance two ends are pyramidal structure, and the centre at rod-type balance two ends is a day flat elements,
Within described day, flat elements is pyramidal structure, in pyramidal structure, is provided with five component elements near position, large end, is provided with resistance element near small end position,
Described pole comprises tapered front end and straight section such as grade, and described rod-type balance mates by the conical surface with the tapered front end of pole and utilizes chock tension, and described rod-type balance is arranged in the inner chamber of tested model,
The minimum diameter of described tested mould impression is greater than the maximum gauge of rod-type balance.
2. a kind of small deformation wind-tunnel balance according to claim 1, is characterized in that the tapering of tapered front end of described pole and the tapering of the sky flat elements of rod-type balance equate.
3. a kind of small deformation wind-tunnel balance according to claim 2, is characterized in that the maximum gauge of the tapered front end of described pole equates with a day minimum diameter for flat elements pyramidal structure.
4. a kind of small deformation wind-tunnel balance according to claim 3, is characterized in that the equal diameters of the straight section such as minimum diameter and pole of the tapered front end of described rod-type balance.
5. a kind of small deformation wind-tunnel balance according to claim 1, is characterized in that described five component elements comprise symmetrically arranged girder construction more than four groups, and the sheet beam being positioned on axis is measuring cell, and the post beam that is positioned at all quadrants is carrier bar.
6. a kind of small deformation wind-tunnel balance according to claim 1, is characterized in that the resistance element of described rod-type balance comprises a pair of Y shape measuring cell and the two groups of resistance support shell fragments that are symmetrical in balance axis arranged.
7. a kind of small deformation wind-tunnel balance according to claim 6, is characterized in that described resistance support shell fragment is two groups of variable cross-section shell fragments that are symmetrical in balance axis arranged.
8. a kind of small deformation wind-tunnel balance according to claim 6, is characterized in that every group is supported shell fragment equal strength, and width matches with a day flat elements tapering profile.
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| CN201610126091.2A CN105606333B (en) | 2016-03-07 | 2016-03-07 | A kind of small deformation wind-tunnel balance |
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| CN201610126091.2A CN105606333B (en) | 2016-03-07 | 2016-03-07 | A kind of small deformation wind-tunnel balance |
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| CN105606333A true CN105606333A (en) | 2016-05-25 |
| CN105606333B CN105606333B (en) | 2018-04-13 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644367A (en) * | 2017-01-13 | 2017-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Compound large-resistance wind-tunnel strain balance |
| CN107121258A (en) * | 2017-06-07 | 2017-09-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of balance resistance element structure of stress distribution optimization |
| CN107796593A (en) * | 2017-11-30 | 2018-03-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of general rod-type wind-tunnel balance pastes quantitative compression system |
| CN108709714A (en) * | 2018-08-08 | 2018-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of small lateral force balance of big rolling moment |
| CN108801581A (en) * | 2018-09-04 | 2018-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement model vibration damping strut based on constrained damping structure |
| CN108896266A (en) * | 2018-07-17 | 2018-11-27 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of method for arranging of balance measurement route |
| CN110441025A (en) * | 2019-08-19 | 2019-11-12 | 中国航空工业集团公司沈阳空气动力研究所 | One kind is for the full machine dynamometric system of the modified double balances of civil aircraft support interference and method |
| CN111157220A (en) * | 2020-03-13 | 2020-05-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Strain type two-component surface friction resistance measuring balance |
| CN112798218A (en) * | 2021-04-12 | 2021-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Model and rod balance connecting structure for wind tunnel test |
| CN114323546A (en) * | 2022-03-07 | 2022-04-12 | 中国空气动力研究与发展中心高速空气动力研究所 | High-sensitivity rod-type six-component wind tunnel test balance inlaid with different materials |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644367A (en) * | 2017-01-13 | 2017-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Compound large-resistance wind-tunnel strain balance |
| CN107121258B (en) * | 2017-06-07 | 2023-03-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Balance resistance element structure with optimized stress distribution |
| CN107121258A (en) * | 2017-06-07 | 2017-09-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of balance resistance element structure of stress distribution optimization |
| CN107796593A (en) * | 2017-11-30 | 2018-03-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of general rod-type wind-tunnel balance pastes quantitative compression system |
| CN107796593B (en) * | 2017-11-30 | 2023-09-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Universal rod type wind tunnel strain balance pasting quantitative pressurizing system |
| CN108896266A (en) * | 2018-07-17 | 2018-11-27 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of method for arranging of balance measurement route |
| CN108709714A (en) * | 2018-08-08 | 2018-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of small lateral force balance of big rolling moment |
| CN108709714B (en) * | 2018-08-08 | 2023-08-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Balance with large rolling moment and small lateral force |
| CN108801581A (en) * | 2018-09-04 | 2018-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement model vibration damping strut based on constrained damping structure |
| CN110441025A (en) * | 2019-08-19 | 2019-11-12 | 中国航空工业集团公司沈阳空气动力研究所 | One kind is for the full machine dynamometric system of the modified double balances of civil aircraft support interference and method |
| CN111157220A (en) * | 2020-03-13 | 2020-05-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Strain type two-component surface friction resistance measuring balance |
| CN111157220B (en) * | 2020-03-13 | 2024-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Strain type two-component surface friction resistance measuring balance |
| CN112798218A (en) * | 2021-04-12 | 2021-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Model and rod balance connecting structure for wind tunnel test |
| CN114323546A (en) * | 2022-03-07 | 2022-04-12 | 中国空气动力研究与发展中心高速空气动力研究所 | High-sensitivity rod-type six-component wind tunnel test balance inlaid with different materials |
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