CN108398228B - Air-floating strain balance - Google Patents
Air-floating strain balance Download PDFInfo
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- CN108398228B CN108398228B CN201711445475.1A CN201711445475A CN108398228B CN 108398228 B CN108398228 B CN 108398228B CN 201711445475 A CN201711445475 A CN 201711445475A CN 108398228 B CN108398228 B CN 108398228B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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Abstract
The invention discloses an air-floating type strain balance which is a combined balance and comprises a mandrel, an axial force component, a five-component and a protective sleeve, wherein the mandrel comprises a conical connecting section and an equal straight section, the mandrel and the axial force component are installed in a matched mode, the axial force component and the five-component are installed in a matched mode, the fixed end of the axial force component is fixed with the mandrel, the movable end of the axial force component is fixed with the fixed end of the five-component, and the movable end of the five-component is fixed with a measured model. The shaft, axial force assembly and five component assembly are coaxial. Compressed gas is filled from the fixed end of the mandrel, and the air holes in the front end of the mandrel enable the movable end of the axial force assembly and the mandrel to be filled with the compressed gas to form an air bearing, so that frictional resistance between the axial force assembly and the mandrel can be ignored, and the measurement sensitivity and precision of the axial force are improved.
Description
Technical Field
The invention relates to an air-floating strain balance, belongs to the field of aerodynamic force measurement of aerospace force measurement tests, and is particularly suitable for sub-span, span and supersonic high-precision resistance measurement wind tunnel tests.
Background
The wind tunnel test is a key research means in the design of the appearance of a flying aircraft, a high-precision aerodynamic force measuring balance is necessary for acquiring high-precision aerodynamic force data in the wind tunnel test process, for a general aircraft measuring balance, an axial force (X component) is a small quantity relative to forces in other directions and is the most difficult quantity to measure in aerodynamic force measurement, and it is more difficult to measure the variation of the appearance of the aircraft corresponding to the variation of the axial force. Six components of the traditional strain balance are on one measuring element, the full-scale strain of the axial force is small during measurement, the interference deformation of other aerodynamic force components to the axial force is larger than the main strain of an axial force assembly, the interference coefficient of other components to the axial force is also large during balance static correction, and the measurement precision of the axial force of the balance is difficult to improve.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the air-floating strain balance overcomes the defects of the prior art, can directly transmit the loads of lateral force, normal force, pitching moment, rolling moment and yawing moment to the mandrel without influencing the load of the axial force, improves the signal-to-noise ratio and sensitivity of the axial force measurement, and realizes the high-precision measurement of the axial force.
The technical solution of the invention is as follows: the utility model provides an air supporting formula balance that meets an emergency, this balance include the dabber and be used for measuring the axial force's axial force subassembly, and the pot head of dabber is inside the axial force subassembly, and its middle part and the tip fixed connection of axial force subassembly, the other end stretch out the axial force outward with test fixture fixed connection, the dabber is inside to be equipped with the cavity through-hole, and this cavity through-hole is located the inside tip of axial force subassembly and blocks up, and other end opening is equipped with a plurality of gas pockets and links to each other with the cavity through-hole on the dabber lateral wall, and compressed gas fills in along dabber cavity through-hole, forms the suspension because of being full of compressed gas between axial.
The mandrel comprises a conical connecting section and an equal straight section, the equal straight section is fixedly connected with the axial force assembly at a position close to the conical section, and the conical connecting section is connected with the test support in a matched manner through a conical surface and is tightened by a wedge.
The axial force assembly measures axial forces through an axial force measuring element mounted on a vertical beam structure on a sidewall of the axial force assembly in a plane perpendicular to an axis of the axial force assembly.
The air-floating strain balance further comprises five-component components for measuring lateral force, normal force, pitching moment, rolling moment and yawing moment, wherein the axial force component is sleeved inside the five-component components, and the five-component components are sleeved inside a measured model; one end of the five-component assembly is fixedly connected with the measured model, the other end of the five-component assembly is fixedly connected with the other end, opposite to the end part fixedly connected with the mandrel, of the axial force assembly sleeved in the five-component assembly, compressed gas is filled in the hollow through hole of the mandrel, suspension is formed between the axial force assembly and the five-component assembly due to the fact that the compressed gas is filled in the five-component assembly, and the five-component assembly does not influence loads of the axial force when measuring lateral force, normal force, pitching moment, rolling moment and yawing moment.
The mandrel, the axial force assembly and the five-component assembly are coaxially arranged.
The five-component assembly and the tested model are fixed through pins; the five-component assembly and the axial force assembly are fixed through pins; the axial force component and the mandrel are fixed through pins.
The five-component assembly respectively measures lateral force, normal force, pitching moment, rolling moment and yawing moment through a lateral force measuring element, a normal force measuring element, a pitching moment measuring element, a rolling moment measuring element and a yawing moment measuring element, the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element are arranged on a plurality of rectangular beams, and the mounting surface is parallel to the axis of the five-component assembly.
The mounting surfaces of the pitching moment measuring elements, the normal force measuring elements and the rolling moment measuring elements are positioned on a plane which passes through the axis of the five-component assembly and is vertical to the cross section of the five-component assembly, the pitching moment measuring elements, the normal force measuring elements and the rolling moment measuring elements are all 1 pair, and each pair of pitching moment measuring elements, normal force measuring elements and rolling moment measuring elements are symmetrically arranged relative to the axis of the five-component assembly; the yaw moment element and the side force measuring element are arranged on a plane perpendicular to the pitching moment measuring element, the normal force measuring element and the rolling moment measuring element, the yaw moment measuring element and the normal force measuring element are 1 pair, and each pair of the yaw moment measuring element and the normal force measuring element are symmetrically arranged relative to the five-component axis.
And a plurality of wire outlet holes are distributed in the position, which is parallel to the axis and avoids the air holes and the through holes, in the mandrel and are used for wire outlet of the axial force measuring element, the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element.
The air-floating strain balance further comprises a protective sleeve, the protective sleeve is fixed with the fixed end of the five-component assembly and covers all the measuring elements, and the outer surface of the protective sleeve is parallel to the outer surface of the five-component assembly.
Compared with the prior art, the invention has the following advantages:
(1) the invention adopts the principle that air floatation is formed in the balance device by compressed gas, the strain balance is designed into a combined sleeve structure, the axial force measuring element and other forces (lateral force, normal force, pitching force, rolling force and yawing force) are arranged on two different sleeves, the compressed gas is filled from the fixed end of the mandrel, the pressure relief air hole is small, the suspension generated between the fixed end of the axial force component and the mandrel and between the five-component and the axial force component due to the filling of the compressed gas is ensured, the structure can ensure that the five-component of the axial force component does not bear the load of force in other directions except for measurement during the wind tunnel test, can ensure that the load on other four components is directly transmitted to the mandrel, the load of the axial force is not influenced, the signal-to-noise ratio and the sensitivity of the axial force measurement are improved, and the high-precision measurement of the axial force is realized.
Drawings
FIG. 1 is a schematic view of an assembly of an air-floating strain balance according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of an assembly of an air-floating strain balance according to an embodiment of the present invention;
FIG. 3(a) is a schematic structural view of a mandrel according to an embodiment of the present invention;
FIG. 3(b) is a cross-sectional view of a mandrel in accordance with an embodiment of the present invention;
FIG. 4 is a schematic structural view of an axial force assembly according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a five-component assembly according to an embodiment of the present invention;
FIG. 6 is a schematic view of a protective cover according to the present invention;
in the figure: 1. a mandrel; 2. an axial force assembly; 3. a five component assembly; 4. a protective sleeve; 5. an axial force measuring element; 6. a pitching moment measuring element; 7. a normal force measuring element; 8. a roll torque measuring element; 9. a yaw moment measuring element; 10. a lateral force measuring element.
Detailed Description
The invention will now be further described with reference to the accompanying drawings.
As shown in fig. 1 and 2, the air-floating strain balance provided by the invention is a combined balance, and comprises a protective sleeve 4, a mandrel 1, a five-component assembly 3 for measuring lateral force, normal force, pitching moment, rolling moment and yawing moment, an axial force assembly 2 for measuring axial force, the five-component assembly 3 sleeved inside a measured model, the axial force assembly 2 sleeved inside the five-component assembly 3, one end of the mandrel 1 sleeved inside the axial force assembly 2, and the other end extending out of the axial force assembly 2. One end and the measured model fixed connection of five weight subassemblies 3, the other end and the cover are at its inside axial force subassembly 2 and one end fixed connection, and the other end and the 1 middle part fixed connection of dabber of axial force subassembly 2, dabber 1 stretch out outside tip and the test support fixed connection of axial force subassembly, dabber 1, axial force subassembly 2 and five weight subassemblies 3 are coaxial to be placed.
As shown in fig. 3(a) and 3(b), the mandrel 1 comprises a conical connecting section and an equal straight section, the conical connecting section is matched with the fixed end to be tested through a conical surface and is tightened by a wedge, and the fixed end of the equal straight section is connected with the axial force component 2 through a pin; the inside cavity through-hole that is equipped with of dabber 1, and this cavity through-hole is located the inside tip of axial force subassembly and blocks up with the jackscrew, and other end opening is equipped with a plurality of gas pockets and links to each other with the cavity through-hole on the dabber 1 lateral wall, and compressed gas lets in from toper linkage segment afterbody, and inside the gas pocket through the equal straight section front end sent into whole device with gas, all formed the suspension because of being full of compressed gas between axial force subassembly and the dabber 1 and between axial force subassembly and the five components of weight subassembly 3. The air bearing structure can enable the frictional resistance between the axial force component and the mandrel to be ignored, the five-component 3 does not influence the load of the axial force when measuring the lateral force, the normal force, the pitching moment, the rolling moment and the yawing moment, and compared with a common strain balance, the air bearing structure can enable the loads of other four components to be directly transmitted to the mandrel without influencing the load of the axial force, so that the signal-to-noise ratio and the sensitivity of the axial force measurement are improved, and the high-precision measurement of the axial force is realized.
In addition, a plurality of wire outlet holes are distributed in the position, which is parallel to the axis and avoids the air holes and the through holes, in the mandrel 1 and are used for wire outlet of the axial force measuring element, the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element.
The axial force assembly 2 measures the axial force by means of an axial force measuring element. Fig. 4 is a schematic structural view of an axial force assembly, as shown in fig. 4, the axial force assembly 2 is hollow cylindrical, the axial force measuring element 5 is mounted on a vertical beam structure on the side wall of the axial force assembly, the plane of the axial force measuring element is perpendicular to the axis of the axial force assembly 2, and the axial force is measured by force transmission through a parallelogram structure.
The five-component assembly 3 and the tested model are fixed through pins; the five-component assembly 3 and the axial force assembly 2 are fixed through pins; the axial force component 2 and the mandrel 1 are fixed through pins.
The five-component assembly 3 respectively measures lateral force, normal force, pitching moment, rolling moment and yawing moment through a lateral force measuring element, a normal force measuring element, a pitching moment measuring element, a rolling moment measuring element and a yawing moment measuring element, the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element are arranged on a plurality of rectangular beams, and the mounting surface is parallel to the axis of the five-component assembly 3.
The mounting surfaces of the pitching moment measuring elements, the normal force measuring elements and the rolling moment measuring elements are positioned on a plane which passes through the axis of the five-component assembly and is vertical to the cross section of the five-component assembly, the pitching moment measuring elements, the normal force measuring elements and the rolling moment measuring elements are all 1 pair, and each pair of pitching moment measuring elements, normal force measuring elements and rolling moment measuring elements are symmetrically arranged relative to the axis of the five-component assembly; the yaw moment measuring elements and the normal force measuring elements are arranged on a plane perpendicular to the pitching moment measuring elements, the normal force measuring elements and the rolling moment measuring elements, the yaw moment measuring elements and the normal force measuring elements are 1 pair, and each pair of the yaw moment measuring elements and the normal force measuring elements are symmetrically arranged relative to the five-component axis.
Figure 5 is a schematic diagram of the structure of a five-part assembly. As shown in fig. 5, the five-component assembly 3 is hollow and cylindrical, and the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element are distributed on the side wall of the five-component assembly 3 along the direction parallel to the five-component axis. Five component subassembly 3 are respectively distributed from top to bottom monolithic rectangular beam, and monolithic rectangular beam cross-section broadside extension line is perpendicular with through five component subassembly axes, and the broadside is perpendicular with five component subassembly axes, and pitching moment measuring element 6, normal force measuring element 7 are placed to monolithic rectangular beam broadside place plane for measuring pitching moment, normal force, and rolling moment measuring element 8 is placed to narrow limit place plane for measuring roll moment. Three-piece rectangular beams are distributed on the left and the right, and a yawing moment 9 and a lateral force measuring element 10 are placed on the middle beam along the outer side of the five-component assembly and used for measuring the yawing moment and the lateral force.
The protective sheath 4 is fixed with the fixed end of the five-component assembly 3, covers all lateral force elements, and is parallel to the outer surface of the five-component assembly 3. Fig. 6 is a schematic view of a protective sheath structure which is screwed to the five-component assembly 3 for protecting the measuring element.
The working principle is as follows: the air-floating high-precision axial force strain balance comprises a mandrel 1, an axial force component 2, a five-component 3 and a protective sleeve 4 which are coaxially matched, wherein the fixed end of the mandrel 1 is fixed on a test support, and the movable end of the five-component is fixedly connected with a tested model, so that the aerodynamic force borne by the tested model is transmitted to the five-component 3, the five-component 3 transmits the aerodynamic force to the axial force component 2, and the axial force component 2 transmits the aerodynamic force to the support through being fixed with the mandrel 1; through filling compressed gas into the fixed end of the mandrel 1, the axial force component 2, the five-component 3 and the measured model can be suspended due to the fact that the compressed gas is filled in the mandrel 1, the axial force component 2, the five-component 3 and the measured model, mutual influence is avoided, under the assembly structure, the whole set of balance can achieve accurate measurement of 6 components of aerodynamic load acting on the model, and particularly has high measurement accuracy on axial force.
The measuring element of the axial force component 2 is an axial force measuring element 5, the structure of the side wall of the axial force component 2 adopts a vertical beam type, and the axial force is measured through force transmission of a parallelogram structure; the measuring elements of the five-component assembly 3 comprise pitching moment 6, normal force 7, rolling moment 8, yawing moment 9 and lateral force 10 measuring elements which are all positioned on the side wall of the five-component assembly 3, wherein the pitching moment 6, normal force 7 and rolling moment 8 measuring elements are two groups of single-chip rectangular beams which are arranged symmetrically up and down; the yawing moment 9 and the side force 10 are two groups of three-piece rectangular beams which are arranged symmetrically left and right. The forces and moments in six directions to which the measured model is subjected are measured by measuring the magnitude of the strain in six different measuring elements.
The invention is not described in detail and is within the knowledge of a person skilled in the art.
Claims (8)
1. An air-floating strain balance, which is characterized in that: the device comprises a mandrel (1), an axial force component (2) for measuring axial force and a five-component (3) for measuring lateral force, normal force, pitching moment, rolling moment and yawing moment, wherein one end of the mandrel (1) is sleeved inside the axial force component (2), the middle part of the mandrel is fixedly connected with the end part of the axial force component (2), the other end of the mandrel extends out of the axial force component and is fixedly connected with a test support, a hollow through hole is formed inside the mandrel (1), the hollow through hole is positioned at the end part inside the axial force component and is blocked, the other end of the mandrel is opened, a plurality of air holes are formed in the side wall of the mandrel (1) and are connected with the hollow through hole, compressed air is filled into the hollow through hole of the mandrel (1), the axial force component and the mandrel (1) are suspended due to the fact that the compressed air is; the axial force component (2) is sleeved inside the five-component (3), and the five-component (3) is sleeved inside the measured model; one end of the five-component assembly (3) is fixedly connected with a measured model, the other end of the five-component assembly is fixedly connected with the other end, opposite to the end part fixedly connected with the mandrel (1), of the axial force assembly (2) sleeved in the five-component assembly, compressed gas is filled into the mandrel (1) along a hollow through hole, suspension is formed between the axial force assembly (2) and the five-component assembly (3) due to the fact that the compressed gas is filled in the axial force assembly, and the five-component assembly (3) does not influence loads of the axial force when measuring lateral force, normal force, pitching moment, rolling moment and yawing moment.
2. The air-floating strain balance of claim 1, wherein: the core shaft (1) comprises a conical connecting section and an equal straight section, the equal straight section is fixedly connected with the axial force assembly (2) at a position close to the conical connecting section, and the conical connecting section is matched and connected with the test support through a conical surface and is tensioned by a wedge.
3. The air-floating strain balance of claim 1, wherein: the axial force assembly (2) measures the axial force by means of an axial force measuring element mounted on a vertical beam structure on the side wall of the axial force assembly, the plane of the axial force measuring element being perpendicular to the axis of the axial force assembly (2).
4. The air-floating strain balance of claim 1, wherein: the mandrel (1), the axial force component (2) and the five-component (3) are coaxially arranged.
5. The air-floating strain balance of claim 1, wherein: the five-component assembly (3) is fixed with the tested model through a pin; the five-component assembly (3) and the axial force assembly (2) are fixed through pins; the axial force component (2) is fixed with the mandrel (1) through a pin.
6. The air-floating strain balance of claim 1, wherein: the five-component assembly (3) measures lateral force through a lateral force measuring element, measures normal force through a normal force measuring element, measures pitching moment through a pitching moment measuring element, measures rolling moment through a rolling moment measuring element, and measures yawing moment through a yawing moment measuring element; the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element are arranged on a plurality of rectangular beams, and the mounting surface is parallel to the axis of the five-component assembly (3);
the installation surfaces of the pitching moment measuring element, the normal force measuring element and the rolling moment measuring element are positioned on a plane which passes through the axis of the five-component assembly and is vertical to the cross section of the five-component assembly, the pitching moment measuring element, the normal force measuring element and the rolling moment measuring element are all 1 pair, and each pair of pitching moment measuring element, normal force measuring element and rolling moment measuring element are symmetrically arranged relative to the axis of the five-component assembly; the yaw moment measuring elements and the lateral force measuring elements are arranged on a plane perpendicular to the pitching moment measuring elements, the normal force measuring elements and the rolling moment measuring elements, the yaw moment measuring elements and the lateral force measuring elements are 1 pair, and each pair of yaw moment measuring elements and each pair of lateral force measuring elements are symmetrically arranged relative to the axis of the five-component assembly.
7. The air-floating strain balance of claim 6, wherein: a plurality of wire outlet holes are distributed in the position, which is parallel to the axis and avoids the air holes and the hollow through holes, in the mandrel (1) and are used for the wire outlet of the axial force measuring element, the lateral force measuring element, the normal force measuring element, the pitching moment measuring element, the rolling moment measuring element and the yawing moment measuring element.
8. An air-floating strain balance according to any one of claims 1 to 7, wherein: still include protective sheath (4), protective sheath (4) are fixed with five weight of subassembly (3) fixed ends, cover all measuring element, and its surface is parallel with five weight of subassembly (3) surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711445475.1A CN108398228B (en) | 2017-12-27 | 2017-12-27 | Air-floating strain balance |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711445475.1A CN108398228B (en) | 2017-12-27 | 2017-12-27 | Air-floating strain balance |
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| CN108398228B true CN108398228B (en) | 2020-03-24 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110132526B (en) * | 2019-05-29 | 2020-09-15 | 中国科学院力学研究所 | Low-interference pulse type shock tunnel strain profile friction drag balance |
| CN110207944B (en) * | 2019-06-26 | 2021-04-13 | 中国航天空气动力技术研究院 | High-precision resistance measuring method and device for wind tunnel experiment |
| CN110333120B (en) * | 2019-07-24 | 2022-01-25 | 合肥工业大学 | Method and device for rapidly detecting cleanliness of mechanical part |
| CN112461494B (en) * | 2020-11-09 | 2022-09-02 | 中国空气动力研究与发展中心 | Pulse combustion wind tunnel model support-balance integrated force measuring device |
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| JP2011252830A (en) * | 2010-06-03 | 2011-12-15 | Toshiba Corp | Support equipment for wind tunnel test model |
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| CN205748868U (en) * | 2016-05-11 | 2016-11-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | The little asymmetric reentry body aerodynamics force measurement device that a kind of air-bearing supports |
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| KR101250258B1 (en) * | 2012-03-19 | 2013-04-05 | 국방과학연구소 | Apparatus for measuring rotation velocity and method of measuring rotation velocity and wind tunnel testing machine having ratus for measuring rotation velocity |
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| JP2011252830A (en) * | 2010-06-03 | 2011-12-15 | Toshiba Corp | Support equipment for wind tunnel test model |
| CN102062630A (en) * | 2010-12-06 | 2011-05-18 | 中国航天空气动力技术研究院 | Floating frame type axial force strain balance |
| CN105758611A (en) * | 2016-03-07 | 2016-07-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Impact resisting device for wind-tunnel balance |
| CN105806586A (en) * | 2016-05-11 | 2016-07-27 | 中国空气动力研究与发展中心超高速空气动力研究所 | Small asymmetrical reentry body aerodynamic force measuring device supported by air bearing |
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