CN118150117B - Test device and method suitable for measuring force of tiny load of thin gas wind tunnel - Google Patents
Test device and method suitable for measuring force of tiny load of thin gas wind tunnel Download PDFInfo
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- 238000010998 test method Methods 0.000 claims description 5
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Abstract
The invention discloses a test device and a method suitable for measuring force of a tiny load of a thin gas wind tunnel, belongs to the technical field of aerospace force measurement tests, and aims to solve the problem that the dead weight of a tiny load force measurement test model exceeds the balance range. The device includes model, branch, balance and supporting pedestal, and the balance is vertical to be set up on supporting pedestal, and the balance includes the second axial section, and the right-hand member of branch passes second axial section grafting cooperation, and the axial lead is perpendicular crossing, and load cartridge filter offsets closely with the model, and the one end that the model was kept away from to the branch is equipped with the spout that vertically link up, and the axis of spout along the branch extends, balancing weight and spout sliding fit. By adjusting the position of the balancing weight relative to the supporting rod, the gravity bending moment generated by the combination of the model and the supporting rod is equal to the gravity bending moment generated by the balancing weight, and the balance only bears the tensile and compressive normal stress, but does not bear the bending stress, so that the bearing capacity of the balance is improved.
Description
Technical Field
The invention belongs to the technical field of aerospace force measurement tests, and particularly relates to a test device and method suitable for measuring force of tiny load of a thin gas wind tunnel.
Background
The strain balance used in the wind tunnel force test can directly measure aerodynamic force and moment acting on an aviation model, and is one of the most critical high-precision sensors in the force measurement wind tunnel test. With the development of aerospace technology, higher and higher requirements are put forward on the flying height and flying speed of an aircraft, and further higher accuracy requirements are put forward on a balance of a force measurement test, however, for a thin gas wind tunnel force measurement test, under certain test working conditions, the total load of the working conditions born by a model is in milli-newton level, the traditional force measurement test device cannot be adopted, the weight of the model exceeds the balance measurement allowable range, in order to ensure that the balance has enough sensitivity under milli-newton level load, the size of the balance elastic element needs to be designed to be very small, and the size of the balance elastic element which is too small cannot meet the size requirement of strain gauge adhesion.
At present, research and development technologies for milli-bovine-level thin gas force measurement tests are few, high-sensitivity coefficient strain gauges such as large-range balance adhesive semiconductor strain gauges are generally used for realizing measurement of milli-bovine-level micro loads, however, the measurement of the test loads is still extremely difficult due to the influence of the dead weight of a model and a balance, and although related patents are used for technical exploration, various technical defects still exist for the measurement difficult, such as the following main steps:
The Chinese patent with the publication number of CN106768791B discloses a micro wind tunnel balance, wherein the micro wind tunnel balance adopts a cross beam to reduce the weight of the balance, and elastic beams in different areas are arranged to measure six component forces, however, for measuring micro load, the elastic elements of the balance need to be processed to be far smaller than the size requirement of the strain gauge adhesion, so that the adhesion of the strain gauge cannot be realized, and the problems that the self weight of parts such as a model exceeds the balance range and the aerodynamic force measurement is influenced cannot be solved;
The Chinese patent publication No. CN104849016B discloses a micro wind tunnel balance and a test method thereof, and in practice mainly discloses a balance formula calculating method, which can not solve the problem of measuring micro load, including how to solve the problem that the elastic element of the balance needs to be processed to be far smaller than the size requirement of the strain gauge adhesion, so that the adhesion of the strain gauge can not be realized, and the problem that the self weight of the parts such as a model exceeds the balance range, so that the aerodynamic force measurement is influenced can not be solved.
Disclosure of Invention
The invention aims to provide a test device and a test method suitable for measuring the force of a tiny load of a thin gas wind tunnel, so as to solve the problem that the dead weight of a tiny load measuring test model exceeds the balance range. The technical scheme adopted by the invention is as follows:
The utility model provides a test device suitable for little load dynamometry of rarefaction gas wind tunnel, including the model, branch, balance and supporting pedestal, the vertical setting of balance is on supporting pedestal, the outside of supporting pedestal is equipped with the load filter cartridge, the left side of load filter cartridge is equipped with, the balance includes the first axle section that from top to bottom coaxial continuous in proper order, first elastic element, the second axle section, the second elastic element, the third axle section, third elastic element and fourth axle section, first elastic element comprises first post roof beam and second post roof beam, the second elastic element comprises third post roof beam and fourth post roof beam, the third elastic element comprises fifth post Liang Hedi six post roof beams, first post roof beam, the second post roof beam, the third post roof beam, the fourth post roof beam, the six post roof beams of fifth post roof beam are the same rectangle cross-section columnar member, first post roof beam and second post roof beam are symmetrical about the axis of balance, the axis bilateral symmetry of third post roof beam and fourth post roof beam relative to the balance, the left end of model and branch establish the connection with the right-hand member of branch, the support post is established to the support post, the support post is equipped with the load spout is crossed with the parallel connection in proper order to the second post, the filter cartridge is equipped with the load spout, the filter cartridge is equipped with near the vertical clearance is crossed with the model to the load spout, the filter cartridge is equipped with the vertical clearance to the load spout.
Further, the support base comprises an upper connecting block and a lower connecting block, the upper connecting block is connected with the lower connecting block through a stand column, the upper end of the balance is connected with the upper connecting block, and the lower end of the balance is connected with the lower connecting block.
Further, a round hole is formed in the load filter cover, the load filter cylinder comprises a straight sleeve section, a taper sleeve section and a connecting sleeve section which are connected in sequence, the outer diameter of the small-diameter end of the taper sleeve section is equal to that of the straight sleeve section, the outer diameter of the connecting sleeve section is smaller than that of the large-diameter end of the taper sleeve section, and the periphery of the connecting sleeve section is connected with the round hole in an inserting and sealing mode.
The invention also provides a test method suitable for the small load force measurement of the thin gas wind tunnel, which is realized by the test device suitable for the small load force measurement of the thin gas wind tunnel, and comprises the following steps:
The method comprises the steps that firstly, a first strain gauge is stuck on the left end face of a first column beam, a second strain gauge is stuck on the right end face of the first column beam, a third strain gauge is stuck on the left end face of the second column beam, a fourth strain gauge is stuck on the right end face of the second column beam, and the first strain gauge, the second strain gauge, the third strain gauge and the fourth strain gauge are electrically connected in sequence to form an electric bridge and are defined as U 1;
A fifth strain gauge is stuck on the left end face of the fifth column beam, a sixth strain gauge is stuck on the right end face of the fifth column beam, a seventh strain gauge is stuck on the left end face of the sixth column beam, an eighth strain gauge is stuck on the right end face of the sixth column beam, and the fifth strain gauge, the sixth strain gauge, the seventh strain gauge and the eighth strain gauge are sequentially and electrically connected to form a bridge and are defined as U 2;
A ninth strain gauge and a twelfth strain gauge are stuck on the front end face of the third column beam up and down, an eleventh strain gauge and a tenth strain gauge are stuck on the rear end face of the fourth column beam up and down, a sixteenth strain gauge and a thirteenth strain gauge are stuck on the front end face of the fourth column beam up and down, a fourteenth strain gauge and a fifteenth strain gauge are stuck on the rear end face of the fourth column beam up and down, the ninth strain gauge and the tenth strain gauge are connected in series to form a first bridge, the eleventh strain gauge and the twelfth strain gauge are connected in series to form a second bridge, the thirteenth strain gauge and the fourteenth strain gauge are connected in series to form a third bridge, the fifteenth strain gauge and the sixteenth strain gauge are connected in series to form a fourth bridge, and the first bridge, the second bridge, the third bridge and the fourth bridge are sequentially and electrically connected to form a U 3;
Measuring bending moments born by the first elastic element, the second elastic element and the third elastic element through U 1、U2 and U 3, adjusting the positions of the balancing weights relative to the supporting rods, and judging that the gravity bending moment generated by the combination of the model and the supporting rods is equal to the gravity bending moment generated by the balancing weights when the bending moments born by the first elastic element, the second elastic element and the third elastic element are zero, wherein the balance only bears tensile and compressive positive stress, and the balance reaches a state of zero bearing the gravity bending moment;
Step three, defining the bending moment measured by a U 1 bridge circuit as M U1, the bending moment measured by the U 2 bridge circuit as N.m, the bending moment measured by the U 2 bridge circuit as M U2, the bending moment measured by the U 3 bridge circuit as N.m, and the bending moment measured by the U 3 bridge circuit as M U3, wherein the unit is N.m;
the lift force born by the definition model is F X, the unit is N, and F X is calculated by the following formula:
FX=（MU2- MU1）/（L1- L2）
The model was subjected to a resistance of F Y in N, F Y calculated by:
FY= [MU1+（MU2- MU1）L1/（L1- L2）]/L Pressing core
The model was subjected to a lateral force of F Z in N, F Z calculated by:
FZ= MU3/ L Pressing core
Wherein:
L 1 is the distance between the center of the first elastic element and the center of the second shaft section, and the unit is m;
L 2 is the distance between the center of the third elastic element and the center of the second shaft section, and the unit is m;
L Pressing core is the distance between the press core of the model and the center of the second shaft section, and the unit is m.
Compared with the prior art, the invention has the beneficial effects that:
1. The balancing weight can slide along the axial lead of the supporting rod, the magnitude of the balancing weight force arm can be changed by adjusting the position of the balancing weight relative to the supporting rod, and when the gravity bending moment generated by the combination of the model and the supporting rod is equal to the gravity bending moment generated by the balancing weight, the balance only bears the tensile and compressive normal stress, so that the stressed gravity bending moment is in a zero state. Because the bending moment generated by the gravity of the model and the support rod does not generate bending moment on the balance any more, the elastic element of the balance only bears tensile stress and compressive stress, but does not bear bending stress, the bearing capacity of the balance is improved, the damage of the dead weight of the model to the balance is reduced, the natural frequency is improved, the measuring range of the balance is not limited any more, and the problem that the dead weight of the micro load force measuring test model exceeds the measuring range of the balance is solved.
2. In the invention, the pressing core of the model and the balance correcting core are eccentrically arranged, a force arm L Pressing core exists between the two points, and aerodynamic force is amplified and measured by a moment principle, so that the size specification of the balance elastic element can be increased, and the design of the balance elastic element and the pasting of a strain gauge can be realized.
3. According to the invention, the balance is vertically arranged, and a double-support fixed mode is adopted, so that the rigidity of the balance is improved, and the elastic angular deformation and data correction of the model in the test process can be reduced.
Drawings
FIG. 1 is a schematic view of the structure of the device of the present invention;
FIG. 2 is a schematic view of the structure of a support base;
FIG. 3 is a schematic view of a strut with a chute;
FIG. 4 is a schematic view of a load cartridge;
FIG. 5 is a schematic view of the balance;
FIG. 6 is a cross-sectional view A-A of FIG. 5;
FIG. 7 is a B-B cross-sectional view of FIG. 5;
FIG. 8 is a cross-sectional view of C-C of FIG. 5;
FIG. 9 is a schematic diagram of a method step one of the present invention for attaching a strain gauge to a balance in a front view;
FIG. 10 is a schematic diagram of a method step of the present invention for bonding strain gauges to a balance left view;
FIG. 11 is a schematic illustration of the method of the present invention for adjusting the bending moment of a balance in step two;
FIG. 12 is a schematic diagram of the method of the present invention for calculating model lift, drag and lateral forces;
FIG. 13 is a U 1 bridge diagram of the method of the present invention;
FIG. 14 is a U 2 bridge diagram of the method of the present invention;
Fig. 15 is a U 3 bridge diagram of the method of the present invention.
In the drawings, 1, model, 2, strut, 21, runner, 3, load filter housing, 31, load filter cartridge, 32, straight sleeve section, 33, cone sleeve section, 34, connecting sleeve section, 4, balance, 41, first shaft section, 42, first elastic element, 43, second shaft section, 44, second elastic element, 45, third shaft section, 46, third elastic element, 47, fourth shaft section, 48, first column beam, 49, second column beam, 410, fifth column beam, 411, sixth column beam, 412, third column beam, 413, fourth column beam, 5, weight, 6, support base, 61, lower connecting block, 62, upright, 63, upper connecting block, 71, first strain gauge, 72, second strain gauge, 73, third strain gauge, 74, fourth strain gauge, 75, fifth strain gauge, 76, sixth strain gauge, 77, seventh strain gauge, 78, eighth strain gauge, 79 strain gauge, ninth strain gauge, 710, tenth strain gauge, 711, eleventh strain gauge, 712, thirteenth strain gauge, 713, thirteenth strain gauge, 714, fifteen strain gauge, 715 strain gauge.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The connection mentioned in the invention is divided into fixed connection and detachable connection, wherein the fixed connection is a conventional fixed connection mode such as folding connection, rivet connection, bonding connection, welding connection and the like, the detachable connection comprises a conventional detachable mode such as bolt connection, buckle connection, pin connection, hinge connection and the like, and when a specific connection mode is not limited, at least one connection mode can be found in the conventional connection mode by default to realize the function, and the person skilled in the art can select the function according to the needs. For example: the fixed connection is welded connection, and the detachable connection is bolted connection.
The present invention will be described in further detail below with reference to the accompanying drawings, the following examples being illustrative of the present invention and the present invention is not limited to the following examples.
Embodiment one: as shown in fig. 1 to 8, a test device suitable for measuring the tiny load of a thin gas wind tunnel comprises a model 1, a supporting rod 2, a balance 4 and a supporting base 6, wherein the balance 4 is vertically arranged on the supporting base 6, a load filter cover 3 is arranged outside the supporting base 6, a load filter cylinder 31 is arranged on the left side of the load filter cover 3, the balance 4 comprises a first shaft section 41, a first elastic element 42, a second shaft section 43, a second elastic element 44, a third shaft section 45, a third elastic element 46 and a fourth shaft section 47 which are coaxially connected from top to bottom in sequence, the first elastic element 42 is composed of a first column beam 48 and a second column beam 49, the second elastic element 44 is composed of a third column beam 412 and a fourth column beam 413, the third elastic element 46 is composed of a fifth column beam 410 and a sixth column beam 411, the first column beam 48, the second column beam 49, the third column beam 412, the fourth column beam 413, the fifth column beam 410 and the sixth column beam 411 are rectangular components with the same section, the first column beam 48 and the second column beam 49 are symmetrical back and forth relative to the axis of the balance 4, the third column beam 412 and the fourth column beam 413 are symmetrical left and right relative to the axis of the balance 4, the fifth column beam 410 and the sixth column beam 411 are symmetrical back and forth relative to the axis of the balance 4, the relatively wide sides of the first column beam 48, the second column beam 49, the fifth column beam 410 and the sixth column beam 411 face left, the relatively wide sides of the third column beam 412 and the fourth column beam 413 face forward, the spacing between the first column beam 48 and the second column beam 49, the spacing between the third column beam 412 and the fourth column beam 413, the spacing between the fifth column beam 410 and the sixth column beam 411 are equal, the model 1 establishes connection with the left end of the strut 2, the second shaft section 43 is provided with a hole matched with the outer Zhou Shi of the strut 2, the right end of the strut 2 sequentially passes through the load filter cartridge 31 and the second shaft section 43, the support rod 2 is in plug-in fit with the second shaft section 43, the axial leads are vertically intersected, a gap is arranged between the support rod 2 and the load filter cartridge 31, the load filter cartridge 31 is propped against the model 1, one end, away from the model 1, of the support rod 2 is provided with a vertically through sliding groove 21, the sliding groove 21 extends along the axis of the support rod 2, and the balancing weight 5 is in sliding fit with the sliding groove 21.
The support base 6 includes an upper connection block 63 and a lower connection block 61, the upper connection block 63 and the lower connection block 61 are connected through a column 62, the upper end of the balance 4 is connected with the upper connection block 63, and the lower end of the balance 4 is connected with the lower connection block 61. The balance 4 is connected with the support base 6 in a double-support fixing mode, so that deformation of the balance 4 can be reduced, and a large elastic angle is prevented from being generated.
The load filter cover 3 is provided with a round hole, the load filter cylinder 31 comprises a straight sleeve section 32, a taper sleeve section 33 and a connecting sleeve section 34 which are connected in sequence, the outer diameter of the small diameter end of the taper sleeve section 33 is equal to that of the straight sleeve section 32, the outer diameter of the connecting sleeve section 34 is smaller than that of the large diameter end of the taper sleeve section 33, and the periphery of the connecting sleeve section 34 is connected with the round hole in an inserting and sealing mode.
In a second embodiment, as shown in fig. 1 to 15, a test method suitable for measuring the force of a weak load of a thin gas wind tunnel is implemented by the test device suitable for measuring the force of the weak load of the thin gas wind tunnel according to the first embodiment, and includes the following steps:
step one, a first strain gauge 71 is stuck on the left end face of the first column beam 48, a second strain gauge 72 is stuck on the right end face, a third strain gauge 73 is stuck on the left end face of the second column beam 49, a fourth strain gauge 74 is stuck on the right end face, and the first strain gauge 71, the second strain gauge 72, the third strain gauge 73 and the fourth strain gauge 74 are electrically connected in sequence to form a bridge and are defined as U 1;
A fifth strain gauge 75 is stuck on the left end face of the fifth column beam 410, a sixth strain gauge 76 is stuck on the right end face, a seventh strain gauge 77 is stuck on the left end face of the sixth column beam 411, an eighth strain gauge 78 is stuck on the right end face, and the fifth strain gauge 75, the sixth strain gauge 76, the seventh strain gauge 77 and the eighth strain gauge 78 are electrically connected in sequence to form a bridge and are defined as U 2;
A ninth strain gauge 79 and a twelfth strain gauge 712 are stuck on the front end surface of the third column beam 412, an eleventh strain gauge 711 and a tenth strain gauge 710 are stuck on the rear end surface of the third column beam 413, a sixteenth strain gauge 716 and a thirteenth strain gauge 713 are stuck on the front end surface of the fourth column beam 413, a fourteenth strain gauge 714 and a fifteenth strain gauge 715 are stuck on the rear end surface of the fourth column beam, the ninth strain gauge 79 and the tenth strain gauge 710 are connected in series to form a first bridge, the eleventh strain gauge 711 and the twelfth strain gauge 712 are connected in series to form a second bridge, the thirteenth strain gauge 713 and the fourteenth strain gauge 714 are connected in series to form a third bridge, the fifteenth strain gauge 715 and the sixteenth strain gauge 716 are connected in series to form a fourth bridge, and the first bridge, the second bridge, the third bridge and the fourth bridge are sequentially electrically connected to form a U 3;
Measuring bending moments borne by the first elastic element 42, the second elastic element 44 and the third elastic element 46 through the U 1、U2 and the U 3, adjusting the position of the balancing weight 5 relative to the supporting rod 2, and judging that the gravity bending moment generated by the combination of the model 1 and the supporting rod 2 is equal to the gravity bending moment generated by the balancing weight 5 when the bending moments borne by the first elastic element 42, the second elastic element 44 and the third elastic element 46 are zero, wherein the balance 4 only bears tensile and compressive normal stress, and the balance 4 achieves the state that the borne gravity bending moment is zero;
Step three, defining the bending moment measured by a U 1 bridge circuit as M U1, the bending moment measured by the U 2 bridge circuit as N.m, the bending moment measured by the U 2 bridge circuit as M U2, the bending moment measured by the U 3 bridge circuit as N.m, and the bending moment measured by the U 3 bridge circuit as M U3, wherein the unit is N.m;
Defining model 1 to be subjected to a lift force of F X in N, F X is calculated by:
FX=MU2- MU1/L1- L2
Model 1 was subjected to a resistance of F Y in N, F Y calculated by:
FY= [MU1+MU2- MU1L1/L1- L2]/L Pressing core
Model 1 was subjected to a lateral force of F Z in N, F Z calculated by:
FZ= MU3/ L Pressing core
Wherein:
l 1 is the distance between the center of the first elastic element 42 and the center of the second shaft section 43, in m;
L 2 is the distance between the center of the third elastic element 46 and the center of the second shaft section 43 in m;
l Pressing core is the distance between the centre of the mould 1 and the centre of the second shaft section 43, in m.
The device is arranged in the wind tunnel test section, and the model 1 is arranged against the air flow.
In fig. 11, G M represents the center of gravity of the combination of the model 1 and the strut 2, G P represents the center of gravity of the counterweight 5, the distance between G M and the balance center is L M,GP and the distance between G M and the balance center is L P, the counterweight 5 can slide along the axis of the strut 2, the size of L P can be changed by adjusting the position of the counterweight 5 relative to the strut 2, and when the gravity bending moment generated by the combination of the model 1 and the strut 2 is equal to the gravity bending moment generated by the counterweight 5, namely G M×LM=GP×LP, the balance 4 only bears the tensile and compressive normal stress, so as to achieve the zero gravity bending moment. Because the bending moment generated by the gravity of the model 1 and the supporting rod 2 does not generate bending moment on the balance 4 any more, the elastic element of the balance 4 only bears tensile stress and compressive stress, but not bending stress, the bearing capacity of the balance is improved, the damage of the self weight of the model to the balance is reduced, the natural frequency is improved, the measuring range of the balance 4 is not limited any more, and the problem that the self weight of the micro load force measurement test model exceeds the measuring range of the balance is solved.
In the invention, the pressing center of the model 1 and the balance correction center are eccentrically arranged, a force arm L Pressing core exists between the two points, and aerodynamic force is amplified and measured by a force moment principle, so that the size specification of the balance elastic element can be increased, and the design of the balance elastic element and the pasting of a strain gauge can be realized.
According to the invention, the balance 4 is vertically arranged, and adopts a double-support fixing mode, so that the rigidity of the balance is improved, and the elastic angular deformation and data correction of the model 1 in the test process can be reduced.
The above embodiments are only illustrative of the present invention and do not limit the scope thereof, and those skilled in the art may also make modifications to parts thereof without departing from the spirit of the invention.
Claims (4)
1. The utility model provides a test device suitable for thin gas wind tunnel tiny load dynamometry which characterized in that: comprises a model (1), a support rod (2), a balance (4) and a support base (6), wherein the balance (4) is vertically arranged on the support base (6), a load filter cover (3) is arranged outside the support base (6), a load filter cylinder (31) is arranged on the left side of the load filter cover (3), the balance (4) comprises a first shaft section (41), a first elastic element (42), a second shaft section (43), a second elastic element (44), a third shaft section (45), a third elastic element (46) and a fourth shaft section (47) which are coaxially connected from top to bottom in sequence, the first elastic element (42) is composed of a first column beam (48) and a second column beam (49), the second elastic element (44) is composed of a third column beam (412) and a fourth column beam (413), the third elastic element (46) is composed of a fifth column beam (410) and a sixth column beam (411), the first column beam (48), the second column beam (49), the fourth column beam (413), the fifth column beam (410) and the sixth column beam (410) are symmetrical relative to the front column beam (49) of the same column member (4), the third column beam (412) and the fourth column beam (413) are symmetrical left and right relative to the axis of the balance (4), the fifth column beam (410) and the sixth column beam (411) are symmetrical front and back relative to the axis of the balance (4), the model (1) is connected with the left end of the supporting rod (2), the right end of the supporting rod (2) sequentially penetrates through the load filter cylinder (31) and the second shaft section (43), the supporting rod (2) is in splicing fit with the second shaft section (43) and the axis line is vertically intersected, a gap is reserved between the supporting rod (2) and the load filter cylinder (31), the load filter cylinder (31) is abutted against the model (1), one end, far away from the model (1), of the supporting rod (2) is provided with a vertically through sliding groove (21), the sliding groove (21) extends along the axis of the supporting rod (2), and the balancing weight (5) is in sliding fit with the sliding groove (21).
2. The test device for measuring force of micro load of thin gas wind tunnel according to claim 1, wherein: the support base (6) comprises an upper connecting block (63) and a lower connecting block (61), the upper connecting block (63) is connected with the lower connecting block (61) through a stand column (62), the upper end of the balance (4) is connected with the upper connecting block (63), and the lower end of the balance (4) is connected with the lower connecting block (61).
3. The test device for measuring force of micro load of thin gas wind tunnel according to claim 2, wherein: the load filter cover (3) is provided with a round hole, the load filter cylinder (31) comprises a straight sleeve section (32), a taper sleeve section (33) and a connecting sleeve section (34) which are connected in sequence, the outer diameter of the small-diameter end of the taper sleeve section (33) is equal to that of the straight sleeve section (32), the outer diameter of the connecting sleeve section (34) is smaller than that of the large-diameter end of the taper sleeve section (33), and the periphery of the connecting sleeve section (34) is connected with the round hole in an inserting and sealing mode.
4. A test method suitable for measuring the force of a tiny load of a thin gas wind tunnel, which is realized by the test device suitable for measuring the force of the tiny load of the thin gas wind tunnel according to any one of claims 1 to 3, and is characterized by comprising the following steps:
the method comprises the steps that firstly, a first strain gauge (71) is stuck on the left end face of a first column beam (48), a second strain gauge (72) is stuck on the right end face of the first column beam, a third strain gauge (73) is stuck on the left end face of a second column beam (49), a fourth strain gauge (74) is stuck on the right end face of the second column beam, and the first strain gauge (71), the second strain gauge (72), the third strain gauge (73) and the fourth strain gauge (74) are electrically connected in sequence to form a bridge and are defined as U 1;
a fifth strain gauge (75) is stuck on the left end face of the fifth column beam (410), a sixth strain gauge (76) is stuck on the right end face of the fifth column beam (411), a seventh strain gauge (77) is stuck on the left end face of the sixth column beam, an eighth strain gauge (78) is stuck on the right end face of the sixth column beam, and the fifth strain gauge (75), the sixth strain gauge (76), the seventh strain gauge (77) and the eighth strain gauge (78) are electrically connected in sequence to form a bridge and are defined as U 2;
A ninth strain gauge (79) and a twelfth strain gauge (712) are stuck on the front end face of the third column beam (412), an eleventh strain gauge (711) and a tenth strain gauge (710) are stuck on the rear end face of the third column beam (413), a sixteenth strain gauge (716) and a thirteenth strain gauge (713) are stuck on the front end face of the fourth column beam, a fourteenth strain gauge (714) and a fifteenth strain gauge (715) are stuck on the rear end face of the fourth column beam, the ninth strain gauge (79) and the tenth strain gauge (710) are connected in series to form a first bridge, the eleventh strain gauge (711) and the twelfth strain gauge (712) are connected in series to form a second bridge, the thirteenth strain gauge (713) and the fourteenth strain gauge (714) are connected in series to form a fourth bridge, and the first bridge, the second bridge, the third bridge and the fourth bridge are sequentially and electrically connected to form a U 3;
Measuring the bending moment born by the first elastic element (42), the second elastic element (44) and the third elastic element (46) through U 1、U2 and U 3, adjusting the position of the balancing weight (5) relative to the supporting rod (2), judging that the gravity bending moment generated by the combination of the model (1) and the supporting rod (2) is equal to the gravity bending moment generated by the balancing weight (5) when the bending moment born by the first elastic element (42), the second elastic element (44) and the third elastic element (46) is zero, and only bearing the tensile and compressive normal stress by the balance (4), wherein the gravity bending moment born by the balance (4) is zero;
Step three, defining the bending moment measured by a U 1 bridge circuit as M U1, the bending moment measured by the U 2 bridge circuit as N.m, the bending moment measured by the U 2 bridge circuit as M U2, the bending moment measured by the U 3 bridge circuit as N.m, and the bending moment measured by the U 3 bridge circuit as M U3, wherein the unit is N.m;
defining the lift force exerted by the model (1) to be F X, wherein the unit is N, and F X is calculated by the following formula:
FX=（MU2- MU1）/（L1- L2）
Model (1) receives a resistance of F Y in N, F Y calculated by:
FY= [MU1+（MU2- MU1）L1/（L1- L2）]/L Pressing core
Model (1) is subjected to a lateral force of F Z in N, F Z calculated by:
FZ= MU3/ L Pressing core
Wherein:
L 1 is the distance between the centre of the first elastic element (42) and the centre of the second shaft section (43), in m;
l 2 is the distance between the centre of the third elastic element (46) and the centre of the second shaft section (43), in m;
L Pressing core is the distance between the centre of the press core of the model (1) and the centre of the second shaft section (43), and the unit is m.
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| 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 |
| CN108181083A (en) * | 2018-01-16 | 2018-06-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Small-range high lift-drag ratio force balance applied to low density wind tunnel |
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| 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 |
| CN108181083A (en) * | 2018-01-16 | 2018-06-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Small-range high lift-drag ratio force balance applied to low density wind tunnel |
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