CN112067236B - Double-balance synchronous rigid force-measuring wind tunnel test device - Google Patents
Double-balance synchronous rigid force-measuring wind tunnel test device Download PDFInfo
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Abstract
The invention provides a double-balance synchronous rigid force measurement wind tunnel test device which comprises a test bed, a force measurement connecting device and a force measurement model, wherein the force measurement connecting device comprises two force measurement section supporting systems which are arranged at intervals, and end supporting systems are respectively arranged on the opposite sides of the two force measurement section supporting systems; the dynamometry model includes dynamometry section model and ordinary model, dynamometry section model and dynamometry section braced system are connected, ordinary model and tip braced system are connected, dynamometry section braced system is including being used for measuring balance and the support component of trembling the power, the lower extreme and the balance of support component are connected, the upper end is connected with dynamometry section model, the balance is installed on the test bench, can carry out the dynamometry test convenient and fast, the effect of comprehensive reaction wind load to the model, and measure the air inertia force of model vibration in-process, make the aerodynamic force result that the reality that obtains arouses by the wind more accurate.
Description
Technical Field
The invention relates to the technical field of wind tunnel test equipment, in particular to a double-balance synchronous rigid force-measuring wind tunnel test device.
Background
When designing a large-span bridge or a super high-rise building, the wind load borne by the structure is a factor which needs to be considered in the design process, so when designing the large-span bridge or the super high-rise building, a wind tunnel test is needed to research the wind load borne by a test model.
Among the prior art, the test device function that can be used to the wind-induced effect of research test model is all comparatively single, for example, the used test device of common wind-tunnel pressure measurement test, it can only carry out the pressure measurement test to current closed bridge structure section, but if we consider bridge floor system railing, perhaps when the influence of bridge bottom overhaul car track to bridge aerodynamic force, because these structures are too meticulous, the pressure-measuring pipe can't accurately arrange, probably leads to the test result error to be bigger than the beginning, some operating modes can't measure even. In addition, in the existing engineering, various complex bridge sections are frequently used, such as the section forms of a split type double box girder, a steel truss girder, a pi-shaped girder and the like, and due to the characteristics of openings, pressure measuring pipelines cannot be arranged on the sections, so that the pressure measuring test cannot be carried out. Therefore, the measuring method cannot comprehensively meet the requirement of evaluating the influence of wind load on different bridge sections, and has certain limitation.
As a common test device used in a wind tunnel force measurement test, most of the existing force measurement test devices are single-balance force measurement tests, and the test method can only obtain the integral force of one force measurement beam section at a time and cannot analyze the spatial distribution characteristic of the vibration shaking force. Therefore, the test precision is not high, and the effect is not ideal. The other force measurement test method is to place a force measurement balance in a test model to directly measure the vibration force, but the method has limitation and is suitable for a structure with a large scale ratio. And a balance can not be even put into the split box girder model section. Therefore, a test apparatus capable of analyzing the spatial distribution characteristics of the buffeting force is needed.
Disclosure of Invention
In view of the above, the present invention provides a dual-balance synchronous rigid force-measuring wind tunnel test device, which can conveniently and quickly perform a force-measuring test, comprehensively reflect the effect of wind load on a model, and measure the air inertia force in the vibration process of the model, so that the obtained aerodynamic force result caused by wind is more accurate.
In order to achieve the purpose, the invention provides the following technical scheme:
the invention provides a double-balance synchronous rigid force measurement wind tunnel test device which comprises a test bed, a force measurement connecting device and a force measurement model, wherein the force measurement connecting device comprises two force measurement section supporting systems which are arranged at intervals, and end supporting systems are respectively arranged on the opposite sides of the two force measurement section supporting systems; the force measuring model comprises a force measuring section model and a common model, the force measuring section model is connected with the force measuring section supporting system, and the common model is connected with the end supporting system;
the force measuring section supporting system comprises a balance and a supporting part, the balance is used for measuring vibration force, the lower end of the supporting part is connected with the balance, the upper end of the supporting part is connected with the force measuring section model, and the balance is installed on the test bed.
Furthermore, a windproof fairing is arranged outside the balance, a through hole is formed in the top of the windproof fairing, and the supporting component penetrates through the through hole and then is connected with the balance.
Furthermore, a first lower base plate is arranged below the windproof fairing, two sides of the first lower base plate are respectively connected with the test bed and the balance, an upper base plate is arranged above the balance, and two sides of the upper base plate are respectively connected with the top of the balance and the supporting component.
Further, the support component is a first airfoil support rod; the end supporting system comprises a second wing-shaped supporting rod, the upper end of the second wing-shaped supporting rod is connected with the common model, and the lower end of the second wing-shaped supporting rod is installed on the test bed.
Furthermore, be equipped with on the first wing section bracing piece be used for with the connecting shim that the section of dynamometry model links to each other, be equipped with on the second wing section bracing piece be used for with the connecting shim that ordinary model links to each other.
Further, the test bench includes riser and diaphragm, be equipped with first spout on the diaphragm, the lower extreme of second wing type bracing piece is equipped with the second lower bolster, first lower bolster and second lower bolster all with first spout sliding fit.
Furthermore, vertical slide holes are formed in the vertical plate, and mounting screws penetrating through the vertical slide holes are respectively arranged at two ends of the transverse plate, so that the transverse plate can slide along the vertical slide holes and can rotate around the mounting screws.
Further, an end plate system for reducing the marginal effect of turbulence is included.
Further, the end plate system includes end plate, vertical connecting rod and bottom gasket, the bottom gasket is the L type, just the one end level of bottom gasket and with the test bench is connected, the other end is vertical and its side with vertical connecting rod connects, vertical connecting rod with the end plate is connected, be equipped with on the vertical connecting rod and be used for the adjustment the slide mechanism of end plate height.
Furthermore, slide mechanism including set up second spout on the vertical connecting rod and with second spout sliding fit's slide bar, the one end of slide bar with the bottom gasket is connected.
The invention has the beneficial effects that:
the invention provides a double-balance synchronous rigid force-measuring wind tunnel test device, which can analyze the spatial distribution characteristic of the shaking force of a force-measuring model in a wind tunnel test through the shaking force of two balances arranged at intervals on the shaking force of the force-measuring model, thereby improving the test precision.
In addition, the device can utilize the transverse plate to be provided with the sliding groove, so that the distance of the test model can be conveniently adjusted. The vertical plates on the two sides of the test bed are provided with sliding holes from top to bottom, and can slide up and down to adjust the height of the test bed so as to adjust the height of the test platform for tests under different working conditions. The transverse plate can rotate around the mounting screw, so that the attack angle is adjusted, and the wind tunnel force measurement test under various working conditions is simulated.
Drawings
In order to make the object, technical scheme and beneficial effect of the invention more clear, the invention provides the following drawings for explanation:
FIG. 1 is a schematic view of an embodiment of a dual balance synchronous rigid force-measuring wind tunnel test device of the present invention;
FIG. 2 is a top view of a transverse plate in the test bed;
FIG. 3 is a front view of a neutral plate in the test stand;
FIG. 4 is a schematic view of an end plate system;
FIG. 5 is a schematic view of an airfoil support bar;
FIG. 6 is a schematic view of two end faces of an airfoil support bar;
FIG. 7 is a schematic view of a bottom gasket;
FIG. 8 is a schematic view of a connection pad;
FIG. 9 is a top view of the airfoil support rods in connection with the wind fairing;
FIG. 10 is a side view of the wind fairing.
Description of reference numerals:
1-test bed; 2-a force measuring section model; 3-common model; 4-a balance; 5-wind-proof fairing; 6-a first lower backing plate; 7-standing the plate; 8-a transverse plate; 9-a first chute; 10-vertical slide hole; 11-a first airfoil support bar; 12-a second wing support bar; 13-an end plate; 14-vertical connecting rods; 15-bottom gasket; 16-a slide bar; 17 a second runner; 18-a connection pad; 19-upper backing plate; 20-second lower backing plate.
Detailed Description
The present invention is further described with reference to the following drawings and specific examples so that those skilled in the art can better understand the present invention and can practice the present invention, but the examples are not intended to limit the present invention.
As shown in fig. 1, which is a schematic diagram of an embodiment of the dual-balance synchronous rigid force-measuring wind tunnel test device of the present invention, the dual-balance synchronous rigid force-measuring wind tunnel test device includes a test bed 1, a force-measuring connecting device and a force-measuring model, the force-measuring connecting device includes two force-measuring section support systems arranged at intervals, and end support systems are respectively arranged on opposite sides of the two force-measuring section support systems; the force measuring model comprises a force measuring section model 2 and a common model 3, the force measuring section model 2 is connected with the force measuring section supporting system, and the common model 3 is connected with the end supporting system;
the force measuring section supporting system comprises a balance 4 and a supporting component, the balance 4 is used for measuring vibration force, the lower end of the supporting component is connected with the balance 4, the upper end of the supporting component is connected with the force measuring section model 2, and the balance 4 is installed on the test bed 1. Specifically, the balance 4 is a high-frequency dynamic balance, the test bed 1 is 190cm long, 16cm wide and 61cm high, the force measurement model is made of high-strength light materials, and the length of the force measurement section model is 4 types, such as 5cm, 10cm, 15cm, 20cm and the like.
Further, the balance 4 of this embodiment is further provided with a wind-proof fairing 5, the top of the wind-proof fairing 5 is provided with a through hole, and the support member is connected with the high-frequency dynamic balance after penetrating through the through hole. The high-frequency dynamic balance is arranged in the windproof fairing 5, so that the influence of incoming flow on the supporting rod or the high-frequency dynamic balance on the test result can be eliminated, and the test precision is improved.
Further, the windproof fairing of the embodiment is provided with a first lower cushion plate 6 below, two surfaces of the first lower cushion plate 6 are respectively connected with the test bed 1 and the high-frequency dynamic balance, an upper cushion plate 19 is arranged above the high-frequency dynamic balance, and two surfaces of the upper cushion plate 19 are respectively connected with the top of the high-frequency dynamic balance and the supporting component. Specifically, the first lower bolster 6 of this embodiment is placed in test bench 1, and bolted connection is used with test bench 1 and high frequency dynamic balance bottom respectively on two sides for fixed and regulation high frequency dynamic balance position, the 4 tops of balance of this embodiment still are equipped with upper padding plate 19, and the 19 two sides of upper padding plate link to each other with high frequency dynamic balance top and support component respectively, and wherein first lower bolster 6 and upper padding plate 19 all adopt the flange.
Further, the support member of the present embodiment is a first airfoil support bar 11; the end part supporting system comprises a second wing-shaped supporting rod 12, the upper end of the second wing-shaped supporting rod 12 is connected with the common model 3, and the lower end of the second wing-shaped supporting rod is installed on the test bed 1. Specifically, as shown in fig. 7, the first wing-shaped support rod 11 and the second wing-shaped support rod are both NACA0015 wing-shaped cross sections, so as to reduce the interference effect of the wind tunnel incoming flow on the support rods.
Further, the first airfoil support bar 11 and the second airfoil support bar 12 of the present embodiment are both provided with a connection gasket 18 for connecting with the force measuring section model 2. The connecting gasket is arranged between the supporting rod and the model, so that the connecting stability between the supporting rod and the force measuring model can be improved, and the force transmission precision is improved.
Further, the test bench of this embodiment includes riser 7 and diaphragm 8, is equipped with first spout 9 on the diaphragm 8, and the lower extreme of second wing type bracing piece 12 is equipped with second lower bolster 20, and first lower bolster 6 and second lower bolster 20 all with first spout 9 sliding fit. Specifically, set up two wide 7 mm's spouts on diaphragm 8 in this embodiment, wherein the spout does not communicate completely but does not open the slot at spout intermediate position 30mm to promote the rigidity of the whole, 6 bottom corresponding positions of first lower bolster are equipped with the slide rail with 9 sliding fit of first spout, and wherein test bench 1 still includes the bottom plate that both ends and coexistence board 7 bottoms are connected, is used for increasing the stability of test bench.
Further, a vertical sliding hole 10 is formed in the vertical plate 7 of the embodiment, and mounting screws penetrating through the vertical sliding hole 10 are respectively arranged at two ends of the horizontal plate 8, so that the horizontal plate can slide along the vertical sliding hole and can rotate around the mounting screws. Specifically, the vertical sliding hole 10 and the mounting screw are matched with each other, so that the transverse plate 8 and the vertical plate 7 can slide up and down relatively, and the transverse plate 8 can rotate relatively around the mounting screw, so that the effect of adjusting the attack angle is realized.
Further, the synchronous rigidity dynamometry wind-tunnel test device of two balances of this embodiment still includes the end plate system that is used for reducing turbulent marginal effect, and the end plate system includes end plate 13, vertical connecting rod 14 and bottom gasket 15, and bottom gasket 15 is the L type, and the one end level of bottom gasket 15 is connected with test bench 1, the other end is vertical and its side is connected with vertical connecting rod 14, and vertical connecting rod 14 is connected with end plate 13, is equipped with the slide mechanism who is used for adjusting end plate 13 height on the vertical connecting rod 14. Specifically, as shown in fig. 4, the bottom gasket 15 is connected with the test bed 1 through screws, the vertical connecting rod 14 is connected with the end plate 13 through a bolt, and the bottom gasket 15 is connected through a bolt, so that the end plate system can effectively reduce the turbulence marginal effect in the wind tunnel test.
Further, the slide mechanism of this embodiment is including setting up the second spout on vertical connecting rod and with second spout sliding fit's slide bar, the one end and the bottom gasket of slide bar are connected. Wherein, slide bar 16 one end is fixed as an organic whole with bottom gasket 15 to with the mutual sliding fit of second spout 17, can make adaptability adjustment to the height of end plate 13 according to experimental demand.
The test process of the double-balance synchronous rigid force-measuring wind tunnel test device is as follows:
when the test is started, the test position of the test force measuring table is determined according to different inflow characteristics, after the test table is erected, devices such as a lower backing plate, a high-frequency dynamic balance, an upper backing plate, a supporting rod, a windproof fairing, a test model and the like are connected in sequence, and the connected test device is shown in fig. 1.
When testing, can be according to setting up different operating modes, the model interval can be adjusted to the lower bolster of sliding on test bench diaphragm spout, can test the atress condition of dynamometry section model under the different interval operating modes. The attack angle can be adjusted by rotating the sliding groove plate surface of the test bed through adjusting screws at the joint of the sliding groove plate at the top of the test bed and the side surface of the test bed, wind tunnel force measurement tests under various working conditions can be performed through adjusting the height and the distance between test models, and a test device does not need to be replaced.
In the test process, taking the buffeting lift force as an example, the test turbulent flow wind speed characteristic and the integral buffeting lift force spectrum of the force measuring beam section can be directly measured through a wind tunnel test. Through a formula I, a buffeting lift force spectrum of the equivalent pressure measuring strip can be obtained through calculation.
Wherein S isL(k1,k2) The integral buffeting lift spectrum of the force-measuring beam section is sinc (x) which is a sine function.
Then, the two wave number pneumatic admittances on the equivalent strips can be identified by the formula II. Wherein
Is equivalent to two wave number pneumatic admittance, SuSwTwo wave number spectra, k, of turbulent flow of wind1，k2Representing wave number, C is the half length of the force measurement model, CL，CDThe lift coefficient and the drag coefficient are respectively expressed and can be directly measured by experiments.
Based on the above formula, other buffeting force characteristics of the complex force-measuring section can be obtained. The method for identifying the buffeting lift force characteristics suitable for the complex section is explained above. The identification modes of the buffeting resistance and the buffeting lifting moment are close to the lifting force, and the buffeting resistance and the buffeting lifting moment can be obtained through measurement and identification of the device.
The above-mentioned embodiments are merely preferred embodiments for fully illustrating the present invention, and the scope of the present invention is not limited thereto. The equivalent substitution or change made by the technical personnel in the technical field on the basis of the invention is all within the protection scope of the invention. The protection scope of the invention is subject to the claims.
Claims (7)
1. A double-balance synchronous rigid force-measuring wind tunnel test device is characterized in that: the device comprises a test bed (1), a force measuring connecting device and a force measuring model, wherein the force measuring connecting device comprises two force measuring section supporting systems which are arranged at intervals, and end supporting systems are respectively arranged on the opposite sides of the two force measuring section supporting systems; the force measuring model comprises a force measuring section model (2) and a common model (3), the force measuring section model (2) is connected with the force measuring section supporting system, and the common model (3) is connected with the end supporting system;
the force measuring section supporting system comprises a balance (4) and a supporting component, the balance (4) is used for measuring vibration force, the lower end of the supporting component is connected with the balance (4), the upper end of the supporting component is connected with the force measuring section model (2), and the balance (4) is installed on the test bed (1);
the test bed is characterized by further comprising an end plate system used for reducing the marginal effect of turbulent flow, wherein the end plate system comprises an end plate (13), a vertical connecting rod (14) and a bottom gasket (15), the bottom gasket (15) is L-shaped, one end of the bottom gasket (15) is horizontal and connected with the test bed (1), the other end of the bottom gasket is vertical, the side face of the bottom gasket is connected with the vertical connecting rod (14), the vertical connecting rod (14) is connected with the end plate (13), a sliding mechanism used for adjusting the height of the end plate (13) is arranged on the vertical connecting rod (14), the sliding mechanism comprises a second sliding groove (17) arranged on the vertical connecting rod (14) and a sliding rod (16) in sliding fit with the second sliding groove (17), and one end of the sliding rod (16) is connected with the bottom gasket (15);
the double-balance synchronous rigid force-measuring wind tunnel test device is used for a wind tunnel test and comprises the following steps:
erecting a test bed, and installing the force measuring connecting device, the balance, the force measuring section model (2) and the common model (3);
testing the stress condition of the force measuring section model;
calculating a buffeting lift force spectrum of the equivalent pressure measuring strip;
measuring the test turbulent flow wind speed characteristic and the integral buffeting lift spectrum of the force measuring beam section;
calculating the wave number pneumatic admittance on the equivalent pressure measuring strip by using the buffeting lift force spectrum obtained by calculation;
the formula for calculating the buffeting lift force spectrum of the equivalent pressure measuring strip is as follows:
wherein,
the integral buffeting lift spectrum of the force-measuring beam section, sinc (x) is a sine function,
，
the number of waves is expressed in terms of,cis half-length of the force measuring section model (2);
the formula for calculating the wave number pneumatic admittance on the equivalent pressure measuring strip is as follows:
wherein
For the pneumatic admittance of two wave numbers of the equivalent pressure measuring strip,
two wave number spectra of turbulent flow, respectively of wind
，
The number of waves is expressed in terms of,cis half-long of the force measuring section model (2),
、
the lift coefficient and the drag coefficient of the model are respectively.
2. The dual-balance synchronous rigid force-measuring wind tunnel test device according to claim 1, characterized in that: the balance is characterized in that a windproof fairing (5) is further arranged outside the balance (4), a through hole is formed in the top of the windproof fairing (5), and the supporting component penetrates through the through hole and then is connected with the balance (4).
3. The dual-balance synchronous rigid force-measuring wind tunnel test device according to claim 2, characterized in that: prevent wind radome fairing (5) below and be equipped with first lower bolster (6), the two sides of first lower bolster (6) respectively with test bench (1) with balance (4) are connected, balance (4) top is equipped with upper padding plate (19), upper padding plate (19) two sides respectively with balance (4) top with the support component links to each other.
4. The dual-balance synchronous rigid force-measuring wind tunnel test device according to claim 3, characterized in that: the supporting component is a first airfoil supporting rod (11); the end supporting system comprises a second wing-shaped supporting rod (12), the upper end of the second wing-shaped supporting rod (12) is connected with the common model (3), and the lower end of the second wing-shaped supporting rod is installed on the test bed (1).
5. The dual-balance synchronous rigid force-measuring wind tunnel test device according to claim 4, characterized in that: the first airfoil type bracing piece (11) is provided with a connecting gasket (18) used for connecting with the force measuring section model (2), and the second airfoil type bracing piece (12) is provided with a connecting gasket (18) used for connecting with the common model (3).
6. The dual-balance synchronous rigid force-measuring wind tunnel test device according to claim 4, characterized in that: the test bench (1) comprises a vertical plate (7) and a transverse plate (8), a first sliding groove (9) is formed in the transverse plate (8), a second lower base plate (20) is arranged at the lower end of the second wing-shaped supporting rod (12), and the first lower base plate (6) and the second lower base plate (20) are in sliding fit with the first sliding groove (9).
7. The dual-balance synchronous rigid force-measuring wind tunnel test device according to claim 6, characterized in that: vertical slide holes (10) are formed in the vertical plate (7), and mounting screws penetrating through the vertical slide holes (10) are respectively arranged at two ends of the horizontal plate (8) so that the horizontal plate (8) can slide along the vertical slide holes (10) and can rotate around the mounting screws.
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