CN118347690A - Aerodynamic force measuring balance for rotor wing wind tunnel test - Google Patents
Aerodynamic force measuring balance for rotor wing wind tunnel test Download PDFInfo
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- CN118347690A CN118347690A CN202410784594.3A CN202410784594A CN118347690A CN 118347690 A CN118347690 A CN 118347690A CN 202410784594 A CN202410784594 A CN 202410784594A CN 118347690 A CN118347690 A CN 118347690A
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- 238000005259 measurement Methods 0.000 claims abstract description 31
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- 238000011161 development Methods 0.000 description 2
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The invention discloses a aerodynamic force measuring balance for a rotor wing wind tunnel test, which belongs to the technical field of wind tunnel tests and mainly comprises a fixed ring, a floating ring, a Y-direction measuring element, a Z-direction measuring element, an X-direction measuring element and a measuring circuit; the floating ring is nested in the fixed ring, the floating ring and the fixed ring are connected into an integral structure only through measuring elements in the Y direction, the Z direction and the X direction, and the measuring circuit comprises a strain gauge stuck on the measuring element and a bridge formed by the strain gauge. The integrated rotor balance has the advantages that the integrated structure is adopted, each part of the rotor balance is compactly arranged and skillfully designed, the six-component load measuring capability is realized, and the requirement of miniaturization of the external dimension of the rotor balance in certain rotor aircraft wind tunnel tests is met; meanwhile, the problems of nonlinearity, hysteresis and non-return to zero caused by manufacturing errors of the rotor balance with the assembled structure are avoided. The rotor balance is convenient to install and use, accurate and reliable in load measurement and low in manufacturing cost.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests, in particular to a aerodynamic force measuring balance for a rotor wing wind tunnel test.
Background
Because of the complexity of helicopter rotor aerodynamics, wind tunnel tests are an important means for rotor aerodynamic performance evaluation and novel rotor aerodynamic layout design, and play an important role in the development process of a rotor aircraft. When the wind tunnel test of the aerodynamic performance of the rotor is carried out, a rotor balance, a torque balance and an elastic coupling assembly are generally used for measuring six-component load of the rotor, physical quantities such as the tension and the torque of the rotor are obtained, and a basis is provided for calculating the tension coefficient and the hovering efficiency of the rotor.
Patent CN 111175014a discloses a rotor balance system solution most commonly used at present. The rotor balance adopts an assembled structure, and consists of a floating end, a fixed end, a vertical measuring element, a transverse measuring element, a longitudinal measuring element and the like; with a 6-component measuring capability, the tensile force Fy, the pitch moment Mz, the roll moment Mx are measured by the vertical measuring element, the lateral force Fz, the yaw moment My are measured by the lateral measuring element, and the resistance Fx is measured by the longitudinal measuring element.
The problems of the conventional rotor balance scheme mainly include:
(1) The existing assembled rotor balance is formed by assembling a plurality of parts, the overall dimension is larger, miniaturization is difficult, and when the space dimension of a rotor balance system is strictly limited, the installation and use requirements are not met.
(2) The existing assembled rotor balance is formed by assembling a plurality of parts, and the machining errors of the parts and the assembly errors of an assembly body can finally introduce nonlinearity, hysteresis and zero return resistance, so that the measurement performance of the rotor balance is reduced, and sometimes the rotor balance cannot be used normally even.
(3) The existing assembled rotor balance has room for improvement in terms of manufacturing cost and manufacturing time.
Disclosure of Invention
The invention aims to provide a technical scheme of a rotor wing wind tunnel test aerodynamic force measurement balance aiming at the defects, and solves the problems that in the prior art, a rotor wing balance adopts an assembled structure and is assembled by a plurality of parts, the overall appearance size is large, and miniaturization is difficult; meanwhile, the problems of nonlinearity, hysteresis, no return to zero and the like caused by manufacturing errors of the rotor balance with the assembled structure are avoided, and the accuracy and the reliability of rotor load measurement are improved.
The invention is realized by the following scheme:
The aerodynamic force measuring balance for the rotor wing wind tunnel test comprises a fixed ring, a floating ring, a Y-direction measuring element, a Z-direction measuring element, an X-direction measuring element and a measuring circuit, wherein the floating ring is nested in the fixed ring, a connecting groove matched with the measuring element is formed in the fixed ring, the floating ring and the fixed ring are connected into an integral structure only through the Y-direction measuring element, the Z-direction measuring element and the X-direction measuring element, and the measuring circuit comprises a strain gauge stuck on the measuring element and eight groups of Wheatstone bridges formed by the strain gauge and the measuring element.
Based on the aerodynamic force measurement balance for the rotor wing wind tunnel test, the outer ring of the fixed ring is circular, and the inner ring of the fixed ring is octagonal; the inner ring of the floating ring is circular, and the outer ring of the floating ring is octagonal; the floating ring is nested in the fixed ring; the annular surface of the inner ring of the fixed ring is alternately provided with a first groove and a second groove; the octagons of the outer ring of the floating ring are opposite to the octagons of the inner ring of the fixed ring respectively; the first grooves and the second grooves are rectangular grooves, the length of the first grooves is not larger than that of the second grooves, and the first grooves and the second grooves are arranged at the center of each annular surface of the fixing ring.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the Y-direction measuring element is arranged in a first groove arranged in a diagonal, and the Z-direction measuring element and the X-direction measuring element are respectively arranged in a second groove.
Based on the aerodynamic force measurement balance for the rotor wing wind tunnel test, the Y-direction measurement element comprises a first long column beam, a first short column beam and a first connecting rod section; the first long column beam is arranged on the side wall of the first connecting rod section, which is close to the floating ring, and the first short column beam is arranged on the side wall of the first connecting rod section, which is close to the fixed ring; the first long column beams are symmetrically arranged at the upper end part and the lower end part of the side wall of the first connecting rod section; the first stub beam is disposed at a center of the first link segment sidewall.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the first connecting rod section is vertically arranged on the outer side wall of the floating ring, and the contact surface of the Y-direction measuring element and the floating ring is a rectangular surface; the first connecting rod section is arranged along the length direction of the rectangular surface, and the first connecting rod section is arranged at the center position of the rectangular surface in the width direction; a strain gauge is stuck on the first long column beam; the junction of first long post roof beam and first link section is first contact lever, the junction of first short post roof beam and first link section is the second contact lever, is the third contact lever between first contact lever and second contact lever, and the tip that the third contact lever is close to first contact lever is provided with first "cross" hinge.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the first cross hinge specifically comprises a first hinge round hole and a second hinge round hole, the third contact rod is a rectangular rod, and the rectangular rod comprises a first side surface parallel to the rectangular surface and a second side surface perpendicular to the rectangular surface; the first hinge round holes are symmetrically arranged on the two first side surfaces along the center position of the rectangular rod; the second hinge round holes are symmetrically arranged on the two second side surfaces along the center position of the rectangular rod; the round hole axes of the first hinge round hole and the second hinge round hole are perpendicular to the axis of the connecting rod section, and the round hole axes of the first hinge round hole and the second hinge round hole are perpendicular to each other.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the Y-direction measuring elements are four groups, each group of elements is provided with a group of electric bridges, and the total of four groups of electric bridges B1, B2, B3 and B4; four strain gauges are stuck on two first long column beams of the Y-direction measuring element in total, and a group of Wheatstone full bridges are formed; the four strain gauges are respectively a first strain gauge, a second strain gauge, a third strain gauge and a fourth strain gauge; the first strain gauge and the second strain gauge are respectively symmetrically stuck on the upper end face and the lower end face of the first long column beam at the upper end; and the third strain gauge and the fourth strain gauge are symmetrically stuck to the upper end face and the lower end face of the first long column beam at the lower end.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the X-direction measuring element comprises a second long column beam and a second connecting rod section; two ends of the second connecting rod section are respectively connected with two side walls of the second groove, and the second long column beam is arranged between the second connecting rod section and the floating ring; second cross hinges are arranged at the two end parts of the second connecting rod section; and strain gauges are stuck on the side surfaces of the second long column beams.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the second cross hinge specifically comprises a third hinge round hole and a fourth hinge round hole, the second connecting rod section is a rectangular rod, and the second connecting rod section comprises a third side surface parallel to the rectangular surface and a fourth side surface perpendicular to the rectangular surface; the third hinge round holes are symmetrically arranged on the two third side surfaces along the center position of the second connecting rod section; the fourth hinge round holes are symmetrically arranged on the two fourth side surfaces along the center position of the second connecting rod section; the round hole axes of the third hinge round hole and the fourth hinge round hole are perpendicular to the axes of the two connecting rod sections, and the round hole axes of the third hinge round hole and the fourth hinge round hole are perpendicular to each other.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the X-direction measuring elements are provided with two groups, each group of elements is provided with a group of electric bridges, and the two groups of electric bridges B7 and B8 are arranged; four strain gauges are stuck on a second long column beam of the X-direction measuring element in total, and a group of Wheatstone full bridges are formed; the four strain gauges are respectively a fifth strain gauge, a sixth strain gauge, a seventh strain gauge and an eighth strain gauge; the fifth strain gauge and the seventh strain gauge are stuck to the right side surface of the second long column beam, and the sixth strain gauge and the eighth strain gauge are stuck to the left side surface of the second long column beam; the fifth strain gauge and the seventh strain gauge are stuck on the right side surface at intervals, and the sixth strain gauge and the eighth strain gauge are stuck on the left side surface at intervals.
Based on the aerodynamic force measuring balance for the rotor wing wind tunnel test, the Z-direction measuring elements are provided with two groups, each group of elements is provided with a group of electric bridges, and the two groups of electric bridges B5 and B6 are all arranged; the bonding method of the strain gauge on the Z-direction measuring element is the same as that of the X-direction.
Based on the aerodynamic force measurement balance for the rotor wing wind tunnel test, the corresponding relation between the eight groups of bridges and the six-component load of the rotor wing is as follows:
Based on the aerodynamic force measurement balance for the rotor wing wind tunnel test, performance indexes such as component measuring range, component sensitivity, strength safety margin and the like of the rotor wing balance can be realized by adjusting thickness dimensions of a first long column beam and a second long column beam or thickness of a first connecting rod section and a second connecting rod section in Y-direction, Z-direction and X-direction measuring elements.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
1. according to the scheme, an integrated structure is adopted, the measuring element is ingeniously arranged between the fixed ring and the floating ring, the measurement of six component loads of the rotor wing pulling force Fy, the pitching moment Mz and the rolling moment Mx, the lateral force Fz, the yaw moment My and the resistance force Fx is realized, the structure is compact, the appearance is small, and the requirement of miniaturization of the appearance size of a rotor wing balance in a certain rotor wing aircraft wind tunnel test is met.
2. The rotor balance adopts an integrated structure, so that the problems of nonlinearity, hysteresis, no return to zero and the like caused by manufacturing errors of the rotor balance of an assembled structure are avoided, and the accuracy and the reliability of rotor load measurement are improved.
3. The rotor balance is low in manufacturing cost and lower in manufacturing cost than a conventional rotor balance.
Drawings
FIG. 1 is a schematic perspective view of a rotor balance according to the present invention;
FIG. 2 is a schematic top view of a rotor balance according to the present invention;
FIG. 3 is a cross-sectional view of A-A of FIG. 2;
FIG. 4 is a cross-sectional view of B-B of FIG. 2;
FIG. 5 is a perspective view of the measuring device of FIG. 2;
FIG. 6 is a perspective view of the X-direction measuring element of FIG. 2;
FIG. 7 is a schematic illustration of the positions of a first strain gauge and a third strain gauge;
FIG. 8 is a schematic diagram of the positions of a fifth strain gauge and a sixth strain gauge;
FIG. 9 is a schematic diagram of the locations of the seventh and eighth strain gauges;
FIG. 10 is a schematic view of a rotor balance installation employing the present invention;
The marks in the figure: 1. a fixing ring; 2. a floating ring; 3. a Y-direction measuring element; 4. a Z-direction measuring element; 5. an X-direction measuring element; 6. a measurement circuit; 11. a first groove, 12, a second groove; 101. a connecting plate; 102. a rotor balance; 103. a bearing seat; 104. an automatic inclinator; 105. a rotor; 31. a first long column beam; 32. a first stub beam; 33. a first link segment; 34. a first contact lever; 35. a second contact lever; 36. a third contact lever; 37. a first cross hinge; 38. a first side; 39. a second side; 311. a first strain gauge; 312. a second strain gauge; 313. a third strain gauge; 314. a fourth strain gauge; 371. a first hinge circular hole; 372. a second hinge circular hole; 51. a second long column beam; 52. a second link segment; 53. a second cross hinge; 54. a third side; 55. a fourth side; 511. a fifth strain gauge; 512. a sixth strain gauge; 513. a seventh strain gauge; 514. an eighth strain gauge; 531. a third hinge round hole; 532. and a fourth hinge round hole.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification (including any accompanying claims, abstract) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
In the description of the present invention, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element in question must have a predetermined orientation, be constructed and operated in a predetermined orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may include one or more of the feature, either explicitly or implicitly.
Examples
As shown in fig. 1 to 10, the present invention provides a technical solution:
The aerodynamic force measuring balance for the rotor wing wind tunnel test comprises a fixed ring 1, a floating ring 2, a Y-direction measuring element 3, a Z-direction measuring element 4, an X-direction measuring element 5 and a measuring circuit 6, wherein the floating ring 2 is nested in the fixed ring 1, the floating ring 2 and the fixed ring 1 are connected into an integral structure only through the Y-direction measuring element 3, the Z-direction measuring element 4 and the X-direction measuring element 5, and the measuring circuit 6 comprises a strain gauge stuck on the measuring element and eight groups of Wheatstone bridges formed by the strain gauge and the strain gauge.
Based on the above structure, the fixed ring 1 is connected with the rotor test stand, the floating ring 2 is connected with the rotor model, and as shown in fig. 10, the measurement of the six-component load of the rotor is realized by the measuring element between the fixed ring 1 and the floating ring 2. The six-component load of the rotor wing is specifically tension force Fy, pitching moment Mz, rolling moment Mx, lateral force Fz, resistance force Fx and yaw moment My.
According to the scheme, through integrated arrangement, all parts of the rotor balance 102 are compactly arranged and skillfully designed, so that the requirement of the wind tunnel test of certain rotor aircrafts on the limitation of the external dimensions of the balance is met; meanwhile, the integrated structure is adopted, so that the problems of nonlinearity, hysteresis, no return to zero and the like caused by manufacturing errors of the rotor balance 102 with the assembled structure are avoided, and the accuracy and the reliability of rotor load measurement are improved.
As an example, the outer ring of the fixed ring 1 is circular, and the inner ring of the fixed ring 1 is octagonal; the inner ring of the floating ring 2 is circular, and the outer ring of the floating ring 2 is octagonal; the floating ring 2 is nested in the fixed ring 1; the annular surface of the inner ring of the fixed ring 1 is alternately provided with a first groove 11 and a second groove 12; the octagons of the outer ring of the floating ring 2 are opposite to the octagons of the inner ring of the fixed ring 1 respectively.
The first grooves 11 and the second grooves 12 are rectangular grooves, the length of the first grooves 11 is not larger than that of the second grooves 12, the first grooves 11 and the second grooves 12 are arranged at the central position of each annular surface of the fixing ring 1, the first grooves 11 and the second grooves 12 are alternately arranged, and eight grooves are arranged in total.
The Y-direction measuring elements 3 are arranged in the first grooves 11 arranged diagonally, the Z-direction measuring elements 4 and the X-direction measuring elements 5 are respectively arranged in the second grooves 12, the total number of the Y-direction measuring elements 3 is four, and the number of the Z-direction measuring elements 4 and the X-direction measuring elements 5 is two.
Based on the structure, the rotor balance has the advantages that the external dimension of the rotor balance is reduced through the special groove arrangement and the special measuring element structure, the decoupling and the measurement of six component loads are realized, the manufacturing cost is low, and the use is more convenient.
As an example, the entire length of the floating ring 2 is not smaller than the entire thickness of the fixed ring 1, and when the assembly is completed, both ends of the floating ring 2 protrude out of the fixed ring 1, and the center position in the vertical direction of the floating ring 2 is collinear with the center position in the vertical direction of the fixed ring 1. The floating ring 2 is arranged at the center of the fixed ring 1, so that the whole rotor balance structure is centrosymmetric, decoupling between components is more thorough, and measurement is more accurate.
As an example, the Y-direction measuring element 3 comprises a first long stub beam 31, a first short stub beam 32 and a first link segment 33; the first long column beam 31 is arranged on the side wall of the first connecting rod section 33 close to the floating ring 2, and the first short column beam 32 is arranged on the side wall of the first connecting rod section 33 close to the fixed ring 1; the first long column beams 31 are symmetrically arranged at the upper end and the lower end of the side wall of the first connecting rod section 33; the first stub beam 32 is disposed at a central location of the side wall of the first stub section 33.
The first connecting rod section 33 is vertically arranged on the outer side wall of the floating ring 2, and the contact surface of the Y-direction measuring element and the floating ring 2 is a rectangular surface; the first link segment 33 is disposed along the length direction of the rectangular face, and the first link segment 33 is disposed at the center position in the width direction of the rectangular face; strain gauges are attached to the first long beam 31.
Based on the above structure, the Y-direction measuring element 3 is provided between the floating ring 2 and the fixed ring 1, and the Y-direction measuring element 3 is connected through the first long column beam 31 with a small contact portion, and meanwhile, a strain gauge is attached to the first long column beam 31, so that the Y-direction load applied to the floating ring 2 can be measured.
As an example, the connection between the first long beam 31 and the first link segment 33 is a first contact lever 34, the connection between the first short beam 32 and the first link segment 33 is a second contact lever 35, a third contact lever 36 is between the first contact lever 34 and the second contact lever 35, and a first cross hinge 37 is provided at the end of the third contact lever 36 near the first contact lever 34.
Based on the above-described structure, by providing the first cross hinge 37, it can be approximately considered that only the load along the axial direction of the first link segment 33 is transmitted, and the interference of the loads in other directions is avoided.
As an example, the first cross hinge 37 may specifically include a first hinge circular hole 371 and a second hinge circular hole 372, and the third contact lever 36 is a rectangular lever that may include a first side 38 parallel to the rectangular face and a second side 39 perpendicular to the rectangular face; the first hinge circular holes 371 are symmetrically arranged on the two first side surfaces 38 along the center position of the rectangular bar; the second hinge round holes 372 are symmetrically arranged on the two second side surfaces 39 along the center position of the rectangular rod; the round hole axes of the first hinge round hole 371 and the second hinge round hole 372 are perpendicular to the axis of the connecting rod section, and the round hole axes of the first hinge round hole 371 and the second hinge round hole 372 are perpendicular to each other.
Based on the above structure, the first cross hinge 37 is formed by the first hinge round hole 371 and the second hinge round hole 372 which are perpendicular to each other, so that only the load along the axial direction of the connecting rod can be approximately considered to be transmitted, and the interference of the load in other directions can be avoided. The technical principle is a conventional technical means in the field, and details are not described herein, and specific reference can be made to the following prior art documents: ma Chengcong, wang Weiying (university of aerospace, university of aviation, south of Jiangsu, 210016) of the general university of aerospace, a development of a six-component balance with overload protection; and He Dexin, wind tunnel balance [ M ] national defense industry Press, 2002.
As an example, four groups of bridges B1, B2, B3, B4 are arranged on the Y-direction measuring element 3 in total, one group being arranged on each group of elements; four strain gauges are adhered on the upper and lower surfaces of the two first long column beams 31 of the Y-direction measuring element 3, and a group of Wheatstone full bridges are formed; the four strain gauges are a first strain gauge 311, a second strain gauge 312, a third strain gauge 313, and a fourth strain gauge 314, respectively; the first strain gauge 311 and the second strain gauge 312 are symmetrically adhered to the upper and lower end surfaces of the upper first long column beam, respectively, and the third strain gauge 313 and the fourth strain gauge 314 are symmetrically adhered to the upper and lower end surfaces of the lower first long column beam, respectively.
Based on the above structure, when the floating ring 2 is subjected to the load of the tension force Fy, the pitch moment Mz, and the roll moment Mx, the first long column beam 31 is elastically deformed, the deformation amount thereof is sensed by the first strain gauge 311, the second strain gauge 312, the third strain gauge 313, and the fourth strain gauge 314, and the measurement signals are outputted through the bridges B1, B2, B3, and B4.
As an example, the X-direction measuring element 5 comprises a second long column beam 51 and a second link segment 52; two ends of the second connecting rod section 52 are respectively connected with two side walls of the first groove 11, and the second long column beam 51 is arranged between the second connecting rod section 52 and the floating ring 2; second cross hinges 53 are provided on both ends of the second link segment 52; strain gauges are attached to both side surfaces of the second long beam 51.
Based on the above structure, an X-direction measuring element 5 is arranged between the floating ring 2 and the fixed ring 1, and the X-direction measuring element 5 is connected through a second long column beam 51 with a smaller contact part, and meanwhile, a strain gauge is attached to the second long column beam 51, so that when the floating ring 2 receives an X-direction load, the load can be accurately measured.
As an example, the second cross hinge 53 may specifically include a third hinge circular hole 531 and a fourth hinge circular hole 532, the second link segment 52 is a rectangular bar, and the second link segment 52 may include a third side 54 parallel to the rectangular face and a fourth side 55 perpendicular to the rectangular face; the third hinge round holes 531 are symmetrically arranged on the two third side surfaces 54 along the center position of the second link segment 52; the fourth hinge circular holes 532 are symmetrically disposed on the two fourth side surfaces 55 along the center position of the second link segment 52; the round hole axes of the third hinge round hole 531 and the fourth hinge round hole 532 are perpendicular to the axes of the two connecting rod sections, and the round hole axes of the third hinge round hole 531 and the fourth hinge round hole 532 are perpendicular to each other.
Based on the above structure, the second cross hinge 53 is formed by the third hinge round hole 531 and the fourth hinge round hole 532 which are perpendicular to each other, so that only the load along the axial direction of the link can be considered to be transmitted approximately, and the interference of the load in other directions can be avoided.
As an example, two groups of bridges B7, B8 are arranged on the X-direction measuring element 5 in total, one group being arranged on each group of elements; four strain gauges are stuck on the second long column beam 51 of the X-direction measuring element 5 in total, and the four strain gauges form a group of Wheatstone full bridges; the four strain gauges are a fifth strain gauge 511, a sixth strain gauge 512, a seventh strain gauge 513, and an eighth strain gauge 514, respectively; the fifth and seventh strain gauges 511 and 513 are attached to the right side of the second long column beam 51, and the sixth and eighth strain gauges 512 and 514 are attached to the left side of the second long column beam 51; the fifth and seventh strain gauges 511 and 513 are attached to the right side surface at a spacing, and the sixth and eighth strain gauges 512 and 514 are attached to the left side surface at a spacing.
With the above configuration, when the floating ring 2 receives the load of the resistance Fx, the second long column beam 51 is elastically deformed, and the deformation amount thereof is sensed by the fifth strain gauge 511, the sixth strain gauge 512, the seventh strain gauge 513, and the eighth strain gauge 514, and the measurement signals are outputted through the bridges B7, B8.
As an example, two groups of bridges B5, B6 are arranged on the Z-direction measuring element 4 in total, one group is arranged on each group of elements, and the bridge arrangement method is consistent with the X-direction measuring element 5.
With the above configuration, when a side force Fz load is applied, the measurement signals are output through the bridges B5 and B6.
As an example, two sets of bridges B7, B8 are arranged on the X-direction measuring element 5 in total, and two sets of bridges B5, B6 are arranged on the Z-direction measuring element 4 in total.
Based on the above configuration, when the floating ring 2 receives the yaw moment My load, the measurement signals are output through the bridges B5, B6, B7, B8.
In the scheme, the method comprises the following steps: the cross-shaped hinges in two directions are arranged on the connecting rod section of the measuring element, so that only the load along the axial direction of the connecting rod can be approximately considered to be transmitted; the strain sensitive element adopts a cantilever beam form; decoupling between the longitudinal forces (Fx, mx, mz components) and the transverse forces (Fx, fz, my components) is achieved by decoupling links; and electric decoupling is adopted between the components of the longitudinal force and the components of the transverse force.
The rotor balance 102 component load corresponds to eight sets of bridge output signals:
Performance indexes such as component measurement range, component sensitivity, strength safety margin and the like of the rotor balance 102 can be realized by adjusting thickness dimensions of the first long column beam 31 and the second long column beam 51 or thicknesses of the first connecting rod section 33 and the second connecting rod section 52 in the Y-direction, the Z-direction and the X-direction measuring elements 5.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (10)
1. The aerodynamic force measurement balance for the rotor wing wind tunnel test is characterized in that: the measuring device comprises a fixed ring, a floating ring, a Y-direction measuring element, a Z-direction measuring element, an X-direction measuring element and a measuring circuit, wherein the floating ring is nested in the fixed ring, a connecting groove matched with the measuring element is formed in the fixed ring, the floating ring and the fixed ring are connected into an integral structure only through the Y-direction measuring element, the Z-direction measuring element and the X-direction measuring element, and the measuring circuit comprises a strain gauge stuck on the measuring element and eight groups of Wheatstone bridges formed by the strain gauge and the measuring element.
2. A rotor wind tunnel test aerodynamic force measurement balance according to claim 1, characterized in that: the outer ring of the fixed ring is circular, and the inner ring of the fixed ring is octagonal; the inner ring of the floating ring is circular, and the outer ring of the floating ring is octagonal; the floating ring is nested in the fixed ring; the annular surface of the inner ring of the fixed ring is alternately provided with a first groove and a second groove; the octagons of the outer ring of the floating ring are opposite to the octagons of the inner ring of the fixed ring respectively; the first grooves and the second grooves are rectangular grooves, the length of the first grooves is not smaller than that of the second grooves, and the first grooves and the second grooves are arranged at the center of each annular surface of the fixing ring.
3. The rotor wind tunnel test aerodynamic force measurement balance according to any one of claims 1-2, characterized in that: the Y-direction measuring element is arranged in a first groove arranged in a diagonal line, and the Z-direction measuring element and the X-direction measuring element are respectively arranged in a second groove.
4. The rotor wind tunnel test aerodynamic force measurement balance according to any one of claims 1-2, characterized in that: the Y-direction measuring element comprises a first long column beam, a first short column beam and a first connecting rod section; the first long column beam is arranged on the side wall of the first connecting rod section, which is close to the floating ring, and the first short column beam is arranged on the side wall of the first connecting rod section, which is close to the fixed ring; the first long column beams are symmetrically arranged at the upper end part and the lower end part of the side wall of the first connecting rod section; the first stub beam is disposed at a center of the first link segment sidewall.
5. A rotor wind tunnel test aerodynamic force measurement balance according to claim 4, characterized by: the first connecting rod section is vertically arranged on the outer side wall of the floating ring, and the contact surface of the Y-direction measuring element and the floating ring is a rectangular surface; the first connecting rod section is arranged along the length direction of the rectangular surface, and the first connecting rod section is arranged at the center position of the rectangular surface in the width direction; a strain gauge is stuck on the first long column beam; the junction of first long post roof beam and first link section is first contact lever, the junction of first short post roof beam and first link section is the second contact lever, is the third contact lever between first contact lever and second contact lever, and the tip that the third contact lever is close to first contact lever is provided with first "cross" hinge.
6. A rotor wind tunnel test aerodynamic force measurement balance according to claim 5, characterized by: the first cross hinge specifically comprises a first hinge round hole and a second hinge round hole, the third contact rod is a rectangular rod, and the rectangular rod comprises a first side surface parallel to the rectangular surface and a second side surface perpendicular to the rectangular surface; the first hinge round holes are symmetrically arranged on the two first side surfaces along the center position of the rectangular rod; the second hinge round holes are symmetrically arranged on the two second side surfaces along the center position of the rectangular rod; the round hole axes of the first hinge round hole and the second hinge round hole are perpendicular to the axis of the connecting rod section, and the round hole axes of the first hinge round hole and the second hinge round hole are perpendicular to each other.
7. The rotor wind tunnel test aerodynamic force measurement balance of claim 6, wherein: the Y-direction measuring elements are provided with four groups, each group of elements is provided with a group of electric bridges, and the total of four groups of electric bridges B1, B2, B3 and B4; four strain gauges are stuck on two first long column beams of the Y-direction measuring element in total, and a group of Wheatstone full bridges are formed; the four strain gauges are respectively a first strain gauge, a second strain gauge, a third strain gauge and a fourth strain gauge; the first strain gauge and the second strain gauge are respectively symmetrically stuck on the upper end face and the lower end face of the first long column beam at the upper end; and the third strain gauge and the fourth strain gauge are symmetrically stuck to the upper end face and the lower end face of the first long column beam at the lower end.
8. The rotor wind tunnel test aerodynamic force measurement balance according to any one of claims 1-2, characterized in that: the X-direction measuring element comprises a second long column beam and a second connecting rod section; two ends of the second connecting rod section are respectively connected with two side walls of the first groove, and the second long column beam is arranged between the second connecting rod section and the floating ring; second cross hinges are arranged at the two end parts of the second connecting rod section; and strain gauges are stuck on the side surfaces of the second long column beams.
9. The rotor wind tunnel test aerodynamic force measurement balance of claim 8, wherein: the second cross hinge specifically comprises a third hinge round hole and a fourth hinge round hole, the second connecting rod section is a rectangular rod, and the second connecting rod section comprises a third side surface parallel to the rectangular surface and a fourth side surface perpendicular to the rectangular surface; the third hinge round holes are symmetrically arranged on the two third side surfaces along the center position of the second connecting rod section; the fourth hinge round holes are symmetrically arranged on the two fourth side surfaces along the center position of the second connecting rod section; the round hole axes of the third hinge round hole and the fourth hinge round hole are perpendicular to the axes of the two connecting rod sections, and the round hole axes of the third hinge round hole and the fourth hinge round hole are perpendicular to each other.
10. A rotor wind tunnel test aerodynamic force measurement balance according to claim 9, characterized in that: the X-direction measuring elements are provided with two groups, each group of elements is provided with a group of electric bridges, and the two groups of electric bridges B7 and B8 are arranged; four strain gauges are stuck on a second long column beam of the X-direction measuring element in total, and a group of Wheatstone full bridges are formed; the four strain gauges are respectively a fifth strain gauge, a sixth strain gauge, a seventh strain gauge and an eighth strain gauge; the fifth strain gauge and the seventh strain gauge are stuck to the right side surface of the second long column beam, and the sixth strain gauge and the eighth strain gauge are stuck to the left side surface of the second long column beam; the fifth strain gauge and the seventh strain gauge are stuck on the right side surface at intervals, and the sixth strain gauge and the eighth strain gauge are stuck on the left side surface at intervals; the Z-direction measuring elements are provided with two groups, each group of elements is provided with a group of electric bridges, and the two groups of electric bridges B5 and B6 are arranged; the pasting method of the strain gauge on the Z-direction measuring element is the same as that of the X-direction; the corresponding relation between eight groups of bridges and six-component loads of the rotor wing is as follows:
。
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