CN112362216B - Engine six-component force measuring device adopting double measuring systems - Google Patents
Engine six-component force measuring device adopting double measuring systems Download PDFInfo
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- CN112362216B CN112362216B CN202011271707.8A CN202011271707A CN112362216B CN 112362216 B CN112362216 B CN 112362216B CN 202011271707 A CN202011271707 A CN 202011271707A CN 112362216 B CN112362216 B CN 112362216B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/16—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
Abstract
The invention provides an engine six-component force measuring device adopting a double-measuring system, which solves the problems of large measuring error and incomplete force measurement in the existing rack type force measuring system for measuring the stress of an engine. The device comprises a fixed frame, a movable frame and a force measuring assembly arranged between the fixed frame and the movable frame; the fixed frame comprises a bottom plate, and 2 lateral force bearing seats and 1 thrust force bearing seat which are arranged on the bottom plate; lifting elastic connecting rod bearing seats are arranged at 4 corners of the bottom plate, strain beams are arranged on the 2 lateral force bearing seats, the 1 thrust bearing seat and the 4 lifting elastic connecting rod bearing seats, and strain sheets are arranged on the lifting strain beams, the lateral force strain beams and the thrust strain beams; the force measuring assembly comprises 4 first force measuring elements arranged between the lifting elastic connecting rod bearing seat and the movable frame, 1 second force measuring element arranged between the thrust bearing seat and the movable frame, and 2 third force measuring elements arranged between the lateral force bearing seat and the movable frame; the load cell includes a load cell and a flexure coupled to opposite ends of the load cell.
Description
Technical Field
The invention belongs to the field of wind tunnel free jet tests, relates to a six-component measuring device, and particularly relates to an engine six-component measuring device adopting a double-measuring system.
Background
In the wind tunnel free jet test, the stress of an engine needs to be measured. In the current test process, a rack type force measuring system which is arranged on the outer part of the engine and has larger size is generally adopted to measure the stress of the engine. However, as the platform type force measuring system is far away from the engine, and the force measuring center is far away from the center of the engine, additional torque is generated, the force measuring range of the whole force measuring system is large, so that the torque measuring error is large, and the force measuring precision requirement cannot be met; the existing bench type force measuring system can only measure the axial force, the normal force and the pitching moment (three-component force) of the engine.
Disclosure of Invention
In order to solve the technical problems of large measurement error and incomplete force measurement (lack of lateral force, rolling moment and yawing moment) in the existing bench type force measurement system for measuring the stress of the engine, the invention provides a six-component engine force measurement device adopting a double measurement system.
In order to achieve the purpose, the technical scheme provided by the invention is as follows:
a six-component force measuring device of an engine adopting a double measuring system is characterized in that: comprises a fixed frame, a movable frame arranged above the fixed frame in parallel and a force measuring assembly arranged between the fixed frame and the movable frame;
the fixed frame comprises a bottom plate, and 2 lateral force bearing seats and 1 thrust force bearing seat which are arranged on the bottom plate;
the bottom plate is a rectangular flat plate, the length direction of the bottom plate is defined as the X-axis direction, the width direction of the bottom plate is defined as the Y-axis direction, and the plane perpendicular to the bottom plate is the Z-axis direction;
lifting elastic connecting rod bearing seats are arranged at 4 corners of the bottom plate, each lifting elastic connecting rod bearing seat comprises a lifting strain beam and a lifting mounting block which are sequentially connected, the lifting strain beams are connected to the bottom plate, and the plane where the lifting strain beams are located is vertical to the Z axis;
the 2 lateral force bearing seats are arranged on the bottom plate in a centrosymmetric manner, each lateral force bearing seat comprises a lateral force mounting seat, a lateral force strain beam and a lateral force mounting block which are sequentially connected, the lateral force mounting seats are arranged on the bottom plate, and the plane of the lateral force strain beam is vertical to the Y axis;
the thrust bearing seats are positioned among the 2 lateral force bearing seats and comprise a thrust mounting seat, a thrust strain beam and a thrust mounting block which are sequentially connected, the thrust mounting seat is arranged on the bottom plate, and the plane of the thrust strain beam is vertical to the X axis;
strain gauges are arranged on the lift force strain beam, the lateral force strain beam and the thrust strain beam;
the force measuring assembly comprises 4 first force measuring elements arranged in parallel with the Z axis, 1 second force measuring element arranged in parallel with the X axis and 2 third force measuring elements arranged in parallel with the Y axis; the lower ends of 4 first force measuring elements are respectively arranged on a lift force mounting block of 4 lift force elastic connecting rod force bearing seats, one end of 1 second force measuring element is arranged on a thrust force mounting block of the thrust force bearing seat, one end of 2 third force measuring elements is respectively arranged on a lateral force mounting block of 2 lateral force bearing seats, and the upper ends of 4 first force measuring elements, the other ends of 1 second force measuring element and the other ends of 2 third force measuring elements are all arranged on a movable frame;
the first force measuring element, the second force measuring element and the third force measuring element have the same structure and respectively comprise a force measuring sensor in the middle and flexible parts connected to two ends of the force measuring sensor.
Further, the force sensor is an s-shaped tension-compression bidirectional force sensor.
Further, the flexure is a gimbal flexure.
Furthermore, the lower end face of the movable frame is provided with 2 lateral force connecting plates matched with the other ends of the 2 third force measuring elements and a thrust connecting plate matched with the other end of the 1 second force measuring element.
Furthermore, 4 strain gauges are pasted on the root parts of the two surfaces of the lift force strain beam, the lateral force strain beam and the thrust strain beam side by side.
Further, the second load cell is located above the centre line of the base plate.
Compared with the prior art, the invention has the advantages that:
1. the measuring device can realize the measurement of six components of force, and simultaneously has double measuring functions: the load cell and strain gauge are measured simultaneously. The six-component measurement can be realized by 7 force measuring sensors, or by a measurement system consisting of strain gauges on 7 strain beams, and the results of the two measurements can be compared with each other and backed up with each other, so that the force and moment measurement accuracy is improved.
2. The flexible part of the invention adopts a universal flexible part which has great rigidity along the axis, can well transfer the stress in the axis direction and has great flexibility along other two orthogonal directions. Therefore, the stress in the axial direction can be effectively transferred, the interference of the force in other directions is avoided, and the accuracy of the measuring result is improved.
3. The measuring device can realize six-component measurement of the free jet test engine, can be an external rack six-component measuring system arranged outside a tested piece after being enlarged, and can also be an internal six-component measuring system arranged inside the tested piece after being miniaturized.
Drawings
FIG. 1 is a schematic structural diagram of a six-component measurement device of an engine using a dual measurement system according to the present invention;
FIG. 2 is a schematic structural diagram of a force measuring assembly mounted on a fixed frame in the engine six-component force measuring device adopting a double measuring system;
FIG. 3 is a schematic perspective view of a fixed frame in the six-component measuring device of the engine using a dual measuring system according to the present invention;
FIG. 4 is a front view of a fixed frame of the engine six-component force measuring device adopting a double measuring system (a strain gauge is arranged on the fixed frame);
FIG. 5 is a top view of a fixed frame of the engine six-component force measuring device using a dual measuring system according to the present invention (a strain gauge is mounted on the fixed frame);
FIG. 6 is a left side view of a fixed frame of the engine six-component force measuring device adopting a double measuring system (a strain gauge is mounted on the fixed frame);
FIG. 7 is a schematic structural diagram of a movable frame in the six-component measurement device of the engine using a double measurement system according to the present invention;
FIG. 8 is a schematic diagram of a force measuring cell of a six-component force measuring device of an engine using a dual measuring system according to the present invention;
FIG. 9 is a schematic view of a measuring bridge formed by 8 strain gauges on a strain beam in the six-component force measuring device of the engine adopting a double measuring system according to the present invention;
wherein the reference numbers are as follows:
1-fixed frame, 11-bottom plate, 12-lateral force bearing seat, 121-lateral force mounting seat, 122-lateral force strain beam, 123-lateral force mounting block, 13-thrust bearing seat, 131-thrust mounting seat, 132-thrust strain beam, 133-thrust mounting block, 14-lift elastic connecting rod bearing seat, 141-lift strain beam and 142-lift mounting block;
2-moving frame, 21-lateral force connecting plate, 22-thrust connecting plate;
31-first load cell, 32-second load cell, 33-third load cell, 301-load cell, 302-flexure;
4-strain gauge.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
As shown in FIG. 1, the six-component measuring device of the engine adopting the double measuring system comprises a fixed frame 1, a movable frame 2 arranged above the fixed frame 1 in parallel, and a force measuring assembly arranged between the fixed frame 1 and the movable frame 2; the force measuring assembly connects the movable frame 2 and the fixed frame 1 to be used as constraint on a force interface between the movable frame 2 and the fixed frame 1, and mechanical decomposition of multi-directional force is realized.
As shown in fig. 3, the fixed frame 1 includes a bottom plate 11, and 2 lateral force bearing seats 12 and 1 thrust force bearing seat 13 arranged on the bottom plate 11, and is used for supporting the movable frame 2 and the force measuring assembly, and bearing the acting force transmitted by the movable frame 2; the bottom plate 11 is of a plate structure, specifically, a rectangular flat plate, and defines that the length direction of the bottom plate 11 in fig. 3 is the X-axis direction, the width direction of the bottom plate 11 is the Y-axis direction, and the plane perpendicular to the bottom plate 11 is the Z-axis direction.
Lifting elastic connecting rod bearing seats 14 are arranged at 4 corners of the bottom plate 11, each lifting elastic connecting rod bearing seat 14 comprises a lifting strain beam 141 and a lifting mounting block 142 which are sequentially and fixedly connected along the X-axis direction, the lifting strain beam 141 is connected on the bottom plate 11, and the plane where the lifting strain beam 141 is located is vertical to the Z axis; the lift elastic connecting rod bearing seat 14 and the bottom plate 11 can adopt an integrated design.
The 2 lateral force bearing seats 12 are arranged on two diagonal corners of the bottom plate 11 in a central symmetry manner, each lateral force bearing seat 12 comprises a lateral force mounting seat 121, a lateral force strain beam 122 and a lateral force mounting block 123 which are fixedly connected into a whole from bottom to top in sequence, and the lateral force mounting seats 121 are fixed on the bottom plate 11 through bolts; the plane in which the lateral force strain beams 122 lie is perpendicular to the Y-axis.
The thrust bearing seats 13 are arranged on the bottom plate 11 and are positioned among the 2 lateral force bearing seats 12, each thrust bearing seat 13 comprises a thrust mounting seat 131, a thrust strain beam 132 and a thrust mounting block 133 which are fixedly connected into a whole from bottom to top, and the thrust mounting seats 131 are fixed on the bottom plate 11 through bolts; the plane of the thrust strain beams 132 is perpendicular to the X-axis.
The bottom plate 11 is provided with a circular through hole and a rectangular through hole in the middle, the rectangular through hole is used for installing and positioning the bottom plate 11, and the circular through hole is used for fastening the bottom plate 11.
The movable frame 2 is used for mounting a tested piece and transmitting the force generated by the tested piece, the force of the tested piece is transmitted to the movable frame 2 through the switching frame, and the movable frame 2 is transmitted to the fixed frame 1 through the force measuring assembly. In the checking process, the standard force is transmitted to the movable frame 2 through the standard force loading head and then transmitted to the fixed frame 1.
As shown in fig. 7, the movable frame 2 is integrally formed by steel, the upper mounting plane of the movable frame 2 is used for mounting the adapter frame, the lower mounting plane of the movable frame 2 is used for connecting the force measuring assembly and the calibration loading system, and the calibration loading system is used for applying force to the movable frame 2. The lower end face of the movable frame 2 is provided with 2 lateral force connecting plates 21 matched with the lateral force mounting blocks 123 of the 2 lateral force bearing seats 12 and a thrust connecting plate 22 matched with the thrust mounting blocks 133 of the 1 thrust force bearing seat 13.
As shown in fig. 2, the force-measuring assembly comprises 7 force-measuring cells, respectively 4 first force-measuring cells 31 arranged parallel to the Z-axis, 1 second force-measuring cell 32 arranged parallel to the X-axis and 2 third force-measuring cells 33 arranged parallel to the Y-axis; the lower ends of the 4 first force measuring elements 31 are respectively fixed on the lift force mounting blocks 142 of the 4 lift force elastic connecting rod force bearing seats 14, and the upper ends of the 4 first force measuring elements 31 are respectively fixed on 4 corners of the movable frame 2; one end of each of the 1 second force measuring elements 32 is fixedly connected to the thrust mounting block 133 of the thrust bearing seat 13, the other end thereof is fixedly connected to the thrust connecting plate 22, and the second force measuring elements 32 are positioned above the central line of the bottom plate 11; one end of each of the 2 third force measuring elements 33 is fixedly connected to the lateral force mounting block 123 of the 2 lateral force bearing seats 12, and the other end of each of the 2 third force measuring elements 33 is fixedly connected to the 2 lateral force connecting plates 21.
In this embodiment, the first force measuring cell 31, the second force measuring cell 32, and the third force measuring cell 33 have the same structure, and as shown in fig. 8, each of them is composed of a force measuring sensor 301 and universal flexible parts 302 connected to both ends of the force measuring sensor 301; the force measuring sensor 301 adopts an s-shaped pull-press bidirectional force measuring sensor, both ends of the force measuring sensor are provided with threaded holes, the universal flexible part 302 is an integrated structure hinge with an arc notch, and consists of two pairs of arc notch revolute pairs in x and y orthogonal directions, a central shaft and threaded structures at both ends of the shaft, the threaded structures are used for being connected with the threaded holes at the end parts of the s-shaped pull-press bidirectional force measuring sensor, and the universal flexible part 302 can be used for carrying out limited angular displacement around the shaft. The gimbal flexure 302 is very stiff along the axis and is very flexible along the other two orthogonal directions, while it is very stiff along the axis to transmit forces in the axial direction. Therefore, the axial force can be effectively transmitted to avoid the interference of forces in other directions. The force acting on the test piece is measured by the load cell 301.
4 first force measuring elements 31 are used for measuring the normal force Fyb, the pitch moment Mzb and the roll moment Mxb,2 third force measuring elements 33 arranged parallel to the Y axis are used for measuring the transverse force (lateral force) Fzb and the yaw moment Myb, and 1 second force measuring element 32 is used for measuring the axial force Fxb.
As shown in fig. 4 to 6, the sections of the lift strain beam 141, the lateral force strain beam 122, and the thrust strain beam 132 of this embodiment are all rectangular, and a plurality of strain gauges are adhered to the lift strain beam 141, the lateral force strain beam 122, and the thrust strain beam 132, in this embodiment, 8 strain gauges are adhered to 7 strain beams (4 lift strain beams 141, 2 lateral force strain beams 122, and 1 thrust strain beam 132), wherein 4 strain gauges are arranged side by side on one surface of the strain beam, and the remaining 4 strain gauges are arranged side by side on the other surface of the strain beam; in order to increase the voltage output model, the strain gauge should be adhered close to the root of the strain beam and the length of the sensitive grid of the strain gauge should be reduced as much as possible. The 8 strain gages on each strain beam each form a measurement bridge as shown in fig. 9, with the 8 strain gages on the 7 strain beams (4 lifting strain beams 141, 2 lateral force strain beams 122 and 1 thrust strain beam 132) forming 7 measurement bridges, respectively, and the desired six components are obtained by different combinations of the outputs of the 7 measurement bridges. The measuring circuit generally adopts a full bridge circuit.
The measuring device can realize six-component measurement of the free jet test engine, can be an external rack six-component measuring system arranged outside a tested piece after being large-sized, can also be an internal rack six-component measuring system arranged inside the tested piece after being small-sized, is small-sized, improves the measuring capacity, and extends from three-component measurement to six-component measurement. The measuring device of the embodiment has double measuring functions: the load cell 301 and strain gauge measure simultaneously. Namely, a measurement matrix can be obtained by a measurement system composed of 7 force sensors 301, and the relationship between the thrust, the lift force, the lateral force, the pitching moment, the rolling moment, the yawing moment and the measurement matrix can be obtained through verification. Six-component measurement can also be realized by a measuring system consisting of strain gauges on 7 strain beams. The results of the two measurements can be compared with each other and backed up with each other, so that the force and moment measurement accuracy is improved.
The measuring device of the embodiment not only can be used for measuring the force and the moment of the wind tunnel free jet test engine, but also can be applied to measuring the force and the moment of tests such as free jet of a near space flight device and measuring the force and the moment of the rocket engine. The method can also be popularized to other fields, such as force and moment measurement for related supersonic and hypersonic wind tunnel tests in the aviation field, force and moment measurement for automobile wind tunnel tests in the automobile field and the like.
The above description is only for the purpose of describing the preferred embodiments of the present invention and does not limit the technical solutions of the present invention, and any known modifications made by those skilled in the art based on the main technical concepts of the present invention fall within the technical scope of the present invention.
Claims (3)
1. The utility model provides an adopt six component force measuring device of engine of two measurement system which characterized in that: comprises a fixed frame (1), a movable frame (2) arranged above the fixed frame (1) in parallel and a force measuring assembly arranged between the fixed frame (1) and the movable frame (2);
the fixed frame (1) comprises a bottom plate (11), and 2 lateral force bearing seats (12) and 1 thrust force bearing seat (13) which are arranged on the bottom plate (11);
the bottom plate (11) is a rectangular flat plate, the length direction of the bottom plate (11) is defined as an X-axis direction, the width direction of the bottom plate (11) is a Y-axis direction, and the plane perpendicular to the bottom plate (11) is a Z-axis direction;
lifting elastic connecting rod bearing seats (14) are arranged at 4 corners of the bottom plate (11), each lifting elastic connecting rod bearing seat (14) comprises a lifting strain beam (141) and a lifting mounting block (142) which are sequentially connected, the lifting strain beams (141) are connected to the bottom plate (11), and the plane where the lifting strain beams (141) are located is perpendicular to the Z axis;
the 2 lateral force bearing seats (12) are arranged on the bottom plate (11) in a centrosymmetric manner, each lateral force bearing seat (12) comprises a lateral force mounting seat (121), a lateral force strain beam (122) and a lateral force mounting block (123) which are sequentially connected, the lateral force mounting seats (121) are arranged on the bottom plate (11), and the plane where the lateral force strain beams (122) are located is vertical to the Y axis;
the thrust bearing seats (13) are positioned among the 2 lateral force bearing seats (12), each thrust bearing seat (13) comprises a thrust mounting seat (131), a thrust strain beam (132) and a thrust mounting block (133) which are sequentially connected, each thrust mounting seat (131) is arranged on the bottom plate (11), and the plane where each thrust strain beam (132) is positioned is vertical to the X axis;
strain sheets (4) are arranged on the lifting force strain beam (141), the lateral force strain beam (122) and the thrust strain beam (132);
the force measuring assembly comprises 4 first force measuring elements (31) arranged in parallel with the Z axis, 1 second force measuring element (32) arranged in parallel with the X axis and 2 third force measuring elements (33) arranged in parallel with the Y axis; the lower ends of 4 first force measuring elements (31) are respectively arranged on a force lifting mounting block (142) of 4 force lifting elastic connecting rod bearing seats (14), one end of 1 second force measuring element (32) is arranged on a force pushing mounting block (133) of a force pushing bearing seat (13), one end of 2 third force measuring elements (33) is respectively arranged on a lateral force mounting block (123) of 2 lateral force bearing seats (12), and the upper ends of 4 first force measuring elements (31), the other ends of 1 second force measuring element (32) and the other ends of 2 third force measuring elements (33) are respectively arranged on a movable frame (2);
the first force measuring element (31), the second force measuring element (32) and the third force measuring element (33) are identical in structure and respectively comprise a force measuring sensor (301) in the middle and flexible pieces (302) connected to two ends of the force measuring sensor (301), and the force measuring sensor (301) is an s-shaped pull-press bidirectional force measuring sensor; the flexible part (302) is a universal flexible part, the universal flexible part is an integrated structure hinge with an arc notch, and consists of an x and y pair of arc notch rotating pairs in orthogonal directions, a central shaft and thread structures at two ends of the shaft, the thread structures are used for being connected with threaded holes at the end part of an s-shaped tension and compression bidirectional force measuring sensor, and the universal flexible part is used for performing limited angular displacement around the shaft;
4 first force measuring elements (31) are used for measuring normal force, pitching moment and rolling moment, 2 third force measuring elements (33) are used for measuring transverse force and yawing moment, and 1 second force measuring element (32) is used for measuring axial force;
4 strain gauges (4) are pasted on two faces of the lift force strain beam (141), the lateral force strain beam (122) and the thrust force strain beam (132) side by side, 8 strain gauges on each strain beam form a measuring bridge circuit respectively, 8 strain gauges on 7 strain beams form 7 measuring bridge circuits respectively, and six required components are obtained through different combinations of outputs of the 7 measuring bridge circuits.
2. The six-component engine force measuring device with a double measuring system according to claim 1, wherein: the lower end face of the movable frame (2) is provided with 2 lateral force connecting plates (21) matched with the other ends of the 2 third force measuring elements (33) and a thrust connecting plate (22) matched with the other end of the 1 second force measuring element (32).
3. The six-component measuring device of the engine using the dual measuring system according to claim 2, wherein: the second force measuring element (32) is located above the centre line of the base plate (11).
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| CN206038194U (en) * | 2016-08-31 | 2017-03-22 | 北京华横新技术开发公司 | Combination force cell sensor |
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| US6032545A (en) * | 1998-04-17 | 2000-03-07 | California Polytechnic State University Foundation | Nozzle flow thrust vector measurement |
| KR101481784B1 (en) * | 2013-07-29 | 2015-01-13 | 충북대학교 산학협력단 | 6-component Loadcell |
| CN103983393B (en) * | 2014-05-21 | 2016-08-17 | 中国航天空气动力技术研究院 | A kind of large-scale determination of six components of foree and varied angle support means |
| CN106595935B (en) * | 2016-12-14 | 2019-10-18 | 中国燃气涡轮研究院 | Rack can be measured from uncoupled aero-engine vectorial force |
| CN111256942B (en) * | 2020-04-27 | 2020-08-18 | 北京清航紫荆装备科技有限公司 | Unmanned helicopter rotor balance |
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| CN204269281U (en) * | 2014-11-20 | 2015-04-15 | 武汉中航传感技术有限责任公司 | A kind of two remaining pressure sensor structure |
| CN206038194U (en) * | 2016-08-31 | 2017-03-22 | 北京华横新技术开发公司 | Combination force cell sensor |
| CN110514341A (en) * | 2019-08-30 | 2019-11-29 | 中国科学院长春光学精密机械与物理研究所 | A kind of six-dimensional force and torque sensor of the space flight mechanical arm with fault-tolerant ability |
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