CN114323546B - High-sensitivity rod-type six-component wind tunnel test balance embedded with different materials - Google Patents
High-sensitivity rod-type six-component wind tunnel test balance embedded with different materials Download PDFInfo
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Abstract
The invention discloses a high-sensitivity rod-type six-component wind tunnel test balance embedded with different materials, which relates to the technical field of force and moment measuring equipment and comprises the following components: mounting embedded torque element structures on two sides of a balance main body structure in an embedded mounting mode, wherein the embedded torque element structures are made of materials different from the balance main body structure; the embedded torque element structure realizes high-sensitivity measurement of roll torque. The embedded torque element structure with another material is embedded and installed on the balance main body structure, the contradiction between the integral strength and rigidity of the balance element and the sensitivity of the rolling torque element is solved, the test accurate measurement of great difference of the pneumatic force and torque load values of the aircraft is realized, the accuracy, the safety and the reliability of wind tunnel test data of the 'micro rolling torque' aircraft are greatly improved, and the embedded torque element structure can be applied to the measurement of the pneumatic force and the torque of the aircraft with different layouts and similar pneumatic loads.
Description
Technical Field
The invention belongs to the technical field of multi-component aerodynamic load measuring sensors and force and moment measuring equipment, and particularly relates to a high-sensitivity rod-type six-component wind tunnel test balance embedded with different materials.
Background
The wind tunnel strain balance is not only an elastic element for measuring aerodynamic load, but also a stressed component for bearing the aerodynamic load. At present, the wind tunnel test balance technical field of multi-component aerodynamic load measurement adopts the same material unfolding design. In terms of material selection, the strain balance material is generally selected from low-carbon alloy steel with high strength, mainly high-quality chrome-manganese-silicon alloy steel, precipitation hardening stainless steel, maraging steel and the like. Of the above materials, maraging steel is most commonly used because of its own material properties. In a wind tunnel test of a certain type of aircraft, the aerodynamic force and the moment of the model are greatly different in magnitude (the rolling moment is about 0.01N.m, and the normal force is about 100N), and the design range of a required test balance is difficult to match. By adopting the traditional maraging steel (namely 250-grade F141) for structural design, on the premise of meeting the strength and rigidity and ensuring that the balance has higher sensitivity under the action of normal force load (the micro-strain of the torque measuring element is 230), the micro-strain of the torque measuring element is only 70 under the action of roll torque design load, and the sensitivity is lower. If the conventional strain balance design method is adopted, the contradiction between the integral rigidity of the balance element and the sensitivity of the rolling moment element is difficult to completely solve. This problem will bring errors to the measurement accuracy and accuracy of the balance in actual operation. Therefore, a new method or structure is urgently needed to be searched, the sensitivity of each measurement component of the balance is improved on the premise that the requirements on the strength and the rigidity of the balance are met, and the load of each measurement component of the balance is better matched.
At present, the micro-rolling torque measurement is not available in the worldMxA (0.01 N.m magnitude) hyperstatic, six-component internal strain balance with a composite structure. With existing small roll torqueMxFor the six-component internal strain balance, the measurement range of the rolling torque is about 0.2 Nm, the aerodynamic force measurement requirements of some special aircrafts cannot be met, and the main reason of the problem is thatMxCaused by small measuring loadsMxThe contradiction between the undersize of the measuring beam and the high rigidity of the balance directly causes the problems of model 'shaking' and 'assembling' and the like in the wind tunnel test. In recent years, an air-floating balance is an emerging technical means, which can solve the technical problem of accurate measurement of micro-rolling torque to a certain extent, but the complexity and the characteristics of the air-floating bearing structure of the key component determine the complexity of the work in the design stage and the calibration stage, so that the specific operability of the air-floating balance is still to be improved.
The invention patent refers to a different materialThe embedded high-sensitivity rod type six-component wind tunnel test balance can improve the sensitivity of a rolling torque element by more than 60 percent (the micro strain at the patch of the strain gauge is increased from 70 to 113) on the premise of ensuring that the overall strength, the rigidity and the sensitivity of a normal force load measuring element are not changed, so that the sensitivity of each measuring element of the balance is more reasonably matched and output. The method well meets the application requirements of the wind tunnel test, provides a new design idea for the design of the wind tunnel strain balance with the load mismatch, and also provides technical support for the development of the aircraft measurement technology in the wind tunnel test. According to the invention, a plurality of single elastic structure measuring units are connected and combined, so that the realizability and operability of a wind tunnel test are ensured; meanwhile, by acquiring micro rolling torque of the aircraftMxThe related wind tunnel test research of the load data verifies that the measure of the micro-rolling torque of the aircraft is realized by combining a simple elastic structure body and multiple safe limit linkagesMxThe realizability and the reliability of the load lay a technical foundation for the development of the measuring technology of the multi-component aerodynamic load measuring sensor in China.
Disclosure of Invention
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter.
To achieve these objects and other advantages in accordance with the present invention, there is provided a rod-type six-component wind tunnel test balance with high sensitivity inlaid with different materials, the rod-type six-component wind tunnel test balance is a split structure, roll torque measuring elements are separately designed and then connected in parallel with a main structure of the balance, specifically:
mounting embedded torque element structures on two sides of a balance main body structure in an embedded mounting mode, wherein the embedded torque element structures are made of materials different from the balance main body structure; the roll torque is measured independently through the embedded torque element structure which is arranged independently, and high-sensitivity measurement of small roll torque is achieved.
Preferably, the balance main body structure is made of one of chrome-manganese-silicon alloy steel, precipitation hardening stainless steel or maraging steel, and the embedded torque element structure is made of one of aluminum alloy 7075, copper or titanium alloy.
Preferably, the structure of the rod-type six-component wind tunnel test balance comprises:
the balance comprises a balance main body structure, a plurality of measuring beams and a balance body, wherein the balance main body structure is a hollow nested structure, two sides of the balance main body structure are symmetrically embedded with embedded torque element structures, and the balance main body structure is also provided with the measuring beams;
the safety shaft is detachably mounted at the center inside the balance main body structure, and the fixed end of the balance main body structure is connected with a balance supporting structure in series.
Preferably, two ends of the embedded torque element structure are fixedly arranged on two sides of the balance main body structure in a pin positioning and screw pressing mode;
the embedded torque element is structurally provided with a sensor for measuring roll torqueMxComponent and yaw momentMyThe embedded torque element structure is also provided with two limit structure beams which are respectively arranged above and below the single measuring beam;
one end of the limiting structure beam is connected with one mounting end part of the embedded torque element structure, and a gap is reserved between the other end of the limiting structure beam and the other mounting end part of the embedded torque element structure.
Preferably, wherein the plurality of measuring beams comprises:
four-piece pitching momentMzComponent measuring beam, four said pitching momentsMzThe component measuring beams are arranged in a 'meter' -shaped beam structure in the circumferential direction of the balance main body structure;
multi-plate normal forceYThe component measuring beams are integrally processed on the upper side and the lower side of the balance main body structure respectively;
multiple sheet side forceZThe component measuring beams are integrally processed on the left side and the right side of the balance main body structure respectively;
multi-disc axial forceXA component measuring beam integrally machined on the left side and the right side of the balance main body structure respectively,The right side;
the balance main body structure comprises a first section, a second section and a third section, wherein the second section is positioned between the first section and the third section;
the pitching momentMzThe component measuring beam and the embedded moment element structure are coaxially arranged at the first section;
said normal forceYComponent measurement beam and lateral forceZThe component measuring beam is coaxially arranged at the second section, and the normal forceYOne end of the component measuring beam is connected with the first section, and a gap is reserved between the other end of the component measuring beam and the end face of the third section; the lateral forceZOne end of the component measuring beam is connected with the third section, and a gap is reserved between the other end of the component measuring beam and the end face of the first section;
the axial forceXThe component measuring beam is coaxially arranged at the third section.
Preferably, the upper side and the lower side of the first section of the balance main body structure are respectively provided with an embedded limiting block in a detachable mode, and the embedded torque element structures are respectively embedded in the left side and the right side of the balance main body structure.
Preferably, wherein the normal forceYComponent measurement beam and lateral forceZThe component measuring beam is of a multi-sheet laminated beam structure.
The invention at least comprises the following beneficial effects: the method well meets the design requirements of special wind tunnel tests with great differences of pneumatic force and moment magnitude of the hypersonic wind tunnel model on the strain balance, provides good technical support for the development of a load matching technology and a wind tunnel pneumatic force testing technology of the wind tunnel balance, has good practicability and popularization value, widens the design thought of future related designs, fills the technical blank of related methods in balance design, and is beneficial to improving the accuracy and reliability of the measurement of the wind tunnel test data of the aircraft with the mismatching of pneumatic load;
the rod-type six-component wind tunnel test balance provided by the invention adopts an embedded structure design of different materials, solves the difficulty of difficult load matching in the balance design, realizes test accurate measurement of great magnitude difference between aerodynamic force and moment load of an aircraft, and provides a new idea for the design of the balance in the same industry; the balance has the same overall dimension as a conventional rod balance structure, can be applied to measurement of aerodynamic force and moment of aircrafts with different layouts and similar aerodynamic loads, has good universality, and can be popularized and applied to wind tunnel tests of the same type and model; thirdly, the accuracy, the safety and the reliability of wind tunnel test data of the 'micro-rolling torque' aircraft can be greatly improved, and the engineering application value is huge;
in order to solve the problem of unmatched load of the wind tunnel strain balance, the embedded torque element structure made of another material is embedded in the balance main body structure, and finally the contradiction between the overall strength and rigidity of the balance element and the sensitivity of the rolling torque element is solved.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a high-sensitivity rod-type six-component wind tunnel test balance with different materials embedded according to the present invention;
FIG. 2 is a schematic structural view of a balance body structure and a mosaic torque element structure;
FIG. 3 is a schematic diagram of the structure of the balance body and the structure of the mosaic torque element on the left side;
FIG. 4 is a schematic top view of the balance body structure and the mosaic torque element structure;
FIG. 5 is a schematic structural view of the main body structure of the balance;
FIG. 6 is a schematic structural diagram of a damascene torque element structure;
fig. 7 is a schematic sectional structure view of the main body structure of the balance.
Wherein, each part corresponds the mark respectively: balance main body structure 1, balance supporting structure 2, embedded torque element structure 3, embedded limiting block 4, safety shaft 5 and pitching torqueMzComponent measuring beam 7, monolithic measuring beam 8, normal forceYComponent(s) ofMeasuring beam 9, lateral forceZComponent measuring beam 10, axial forceXThe component measuring beam 11, the limit structure beam 12, the first section 100, the second section 200, the third section 300, the front end 101, and the rear end 102.
Detailed Description
The present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
It is to be understood that in the description of the present invention, the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are used only for convenience in describing the present invention and for simplification of the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless otherwise specifically stated or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are used broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, or a communication between two elements, and those skilled in the art will understand the specific meaning of the terms in the present invention specifically.
Further, in the present invention, unless otherwise explicitly specified or limited, a first feature "on" or "under" a second feature may be directly contacted with the first and second features, or indirectly contacted with the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
The aerodynamic loads acting on the aircraft model are measured by the measuring elements determined by the design method of the invention, and the measuring elements are respectively sensitive to the aerodynamic loads of the respective measuring components and generate relatively obvious deformation, are insensitive to the aerodynamic loads of other components and do not generate or generate deformation as small as possible, thereby realizing the mechanical decomposition of the force and moment loads of the aerodynamic loads acting on the balance. The method of the invention is described in detail by taking a wind tunnel test of a certain type of aircraft as an example, and the details are as follows.
In a wind tunnel test of a certain type of aircraft, the roll moment of the aircraft is not matched with the design range of other components (the roll moment of the aircraft is 0.010 N.m, and the normal force is 100N).
To the above-mentioned circumstances, provided a high sensitivity rod-type six components wind-tunnel test balance that different materials were inlayed, and set up rod-type six components wind-tunnel test balance into split type structure, design alone the moment measuring element that rolls over, connect in parallel with balance major structure again, the purpose of doing so has two: firstly, load matching and processing are convenient; secondly, for the convenience of future use (because the roll torque is not matched with other components, the balance matched with other loads can be obtained by replacing the measuring element for application), the rod type six-component wind tunnel test balance has the following structure:
mounting embedded torque element structures on two sides of a balance main body structure in an embedded mounting mode, wherein the embedded torque element structures are made of materials different from the balance main body structure; the roll torque is measured independently through the embedded torque element structure which is arranged independently, and high-sensitivity measurement of small roll torque is achieved.
As shown in fig. 1-7: the invention relates to a high-sensitivity rod-type six-component wind tunnel test balance inlaid with different materials, which comprises:
one end of the limiting structure beam is connected with one mounting end part of the embedded torque element structure, and a gap is reserved between the other end of the limiting structure beam and the other mounting end part of the embedded torque element structure.
The safety shaft 5 is detachably mounted at the center inside the balance main body structure 1, and the fixed end of the balance main body structure is connected with a balance supporting structure in series.
The balance main body structure 1 and the embedded torque element structure 3 form a key technical part of the whole set of test balance, namely a balance element, and the measurement of model pneumatic force and torque data is completed; the balance support structure 2 plays a supporting role and is used for realizing the connection between the balance and the wind tunnel; the safety shaft 5 is inserted into a center hole of the balance and connected with the main structure of the balance, so that after the strain beam of the balance is broken in the wind tunnel test process, the model arranged at the front end of the main structure of the balance is prevented from being separated from the balance, and danger is avoided. The invention adopts the design of an embedded structure of different materials, and aims to solve the problems of load matching of each measuring element of the balance and the strength, rigidity and sensitivity of the whole balance. The balance is mainly applied to a hypersonic wind tunnel ablation warhead micro-roll aerodynamic torque measurement test. In the test of the type, the most reported literature data is a test scheme of supporting and superposing a strain balance by using an air bearing, but the test scheme has the difficulties of complex system and more uncertain factors; rod balance testing schemes have also been reported, but have greater limitations in matching normal load capacity to roll sensitivity. The rod type strain balance is adopted to measure the micro rolling moment of the aircraft model, and the pneumatic force and the moment are greatly different in magnitude, so that the strength, the rigidity and the sensitivity of the balance required to be measured are difficult to match, and the method is a problem recognized in the industry. Therefore, the invention provides a design scheme of a rod type six-component strain balance with embedded structures made of different materials, and the main body structure of the balance is made of materials with better strength and rigidity so as to bear larger normal load of a model; meanwhile, a detachable torque element of the balance is made of a material with high sensitivity, so that the measurement of the micro-aerodynamic torque is realized. The balance element of the invention is a core component consisting of a balance main body structure 1 and an embedded torque element structure 3, the rolling torque is small, the lifting load is 100N, the rolling torque load is 0.010 N.m, and the measurement of the conventional small rolling torque balance with the same size and magnitude can only reach about 0.15 N.m. In the aspect of balance design, the invention divides the balance into two parts by the design idea of combining 'series connection and embedded multiple limit linkage': the balance comprises a balance main body structure 1 and an embedded torque element structure 3, wherein the main body structure design of the balance adopts a series structure of all measuring units for measuring pneumatic loads in different directions; meanwhile, the operability and feasibility of the wind tunnel test are ensured by means of superposing multiple limiting safety linkage structures on the basis of the original elastic structure beam. In addition, in the whole design stage, the structural size of each part is reasonably selected according to the finite element analysis result, so that the sensitivity, the strength and the rigidity of each part meet the test requirements.
In the above technical solution, the balance body structure 1 includes a first section 100, a second section 200 and a third section 300, wherein the second section 200 is located between the first section 100 and the third section 300;
still be provided with the multi-disc measuring beam on the balance major structure, include:
four-piece pitching momentMzComponent measuring beam 7, four pieces of said pitching momentMzThe component measuring beams 7 are arranged in a 'meter' -shaped beam structure in the circumferential direction of the balance main body structure 1; the structure of the beam shaped like a Chinese character 'mi' refers to four pitching momentsMzThe component measuring beam 7 extends towards the central axis of the balance body structure 1 to form a structure shaped like a Chinese character 'mi'.
Two normal forcesYComponent measuring beams 9 integrally formed on the respective membersThe upper side and the lower side of the balance main body structure 1;
two lateral forcesZThe component measuring beams 10 are respectively and integrally processed at the left side and the right side of the balance main body structure 1,
two axial forcesXThe component measuring beams 11 are integrally processed on the left side and the right side of the balance main body structure 1 respectively;
the pitching momentMzThe component measuring beam 7 and the embedded moment element structure 3 are coaxially arranged at the first section;
said normal forceYComponent measuring beam 9 and lateral forcesZThe component measuring beam 10 is arranged coaxially at the second section and the normal force isYOne end of the component measuring beam 9 is connected with the first section, and a gap is reserved between the other end of the component measuring beam and the end face of the third section; the lateral forceZOne end of the component measuring beam 10 is connected with the third section, and a gap is reserved between the other end of the component measuring beam and the end face of the first section;
the axial forceXThe component measuring beam 11 is coaxially arranged at the third section.
In the technical scheme, the balance main body structure 1 and the embedded torque element structure 3 are made of different materials, specifically, the balance main body structure 1 is made of a 250-grade F141 material, the embedded torque element structure 3 is made of an aluminum alloy material 7075, the measurement sensitivity of the balance rolling torque is appropriate, and the specific magnitude of the rolling torque micro-strain is 113; under the condition that the balance main body structure 1 and the embedded torque element structure 3 both adopt 250-grade F141 materials, the embedded torque element structure 3 and the balance main body structure have the same size, and the position average micro strain of the rolling torque pasting strain gauge is about 50; but the axial dimensions of the embedded element and the balance are different by changing the axial dimensions of the embedded element, so that the overall strength and rigidity of each measuring unit of the balance main body structure and the balance are not influenced, the sensitivity of the rolling torque is increased, and the micro strain of the rolling torque is improved from 50 to 70 by the method. Therefore, through the key steps and the method used in the design stage, the micro strain at the position where the embedded element rolling torque is adhered to the strain gauge is increased from 50 at the beginning to 70, and finally to 113, the measurement requirement is met, and the accurate measurement of the related aerodynamic load in the wind tunnel test process is realized.
In the above technical solution, the normal forceYComponent measuring beam 9 and lateral forcesZThe component measuring beam 10 is a multi-piece stacked beam structure.
In the design of the balance, the front end is a connecting end between the balance and the model, and the connecting end is fixedly connected with the model and the force application device through a cylindrical matching surface with the diameter of 28mm and the length of 50 mm. In order to facilitate load matching and improve rigidity, the balance main body structure 1 adopts a series connection mode, and pitching moments are sequentially arranged from left to rightMzComponent measuring beam 7, normal forceYComponent measuring beam 9, lateral forceZComponent measuring beam 10, axial forceXMeasuring the beam 11 in terms of components, while at the moment of pitchingMzThe two sides of the component measuring beam 7 are provided with a mosaic torque element structure 3, namely a yaw torque, by a symmetrical mosaic structureMyComponent, roll momentMxA component measuring beam. The component measuring beams are selected in terms of structure, and in order to improve rigidity and normal forceYComponent measuring beam 9, lateral forceZThe component measuring beam 10 adopts a multi-piece laminated beam structure in order to improve the rolling momentMxSensitivity of component in pitching momentMzThe component measuring beam 7 is selected from a'm' -shaped beam structure, and the embedded moment element structure 3 is in a single-piece beam form. It should be mentioned that the specific dimensions of the above-mentioned structure are determined by finite element analysis optimization results. Meanwhile, in actual work, a Wheatstone full-bridge circuit is formed by sticking strain gauges on each measuring beam: and converting the resistance change in work into voltage signal increment, and calculating the increment to realize accurate measurement of each component. The rod type six-component wind tunnel test balance provided by the invention has the design load of normal forceYComponent measurement beam and lateral forceZComponent measuring beam is 100N, axial forceXComponent measuring beam is 120N, pitching momentMzThe component measuring beam is 2 N.m, and the yawing momentMyComponent measuring beam of 1.5 Nm, rolling momentMxThe component measuring beam is 0.010 N.m, the moment reference point is near the geometric center of the balance moment element, and the matching of the balance normal force and the roll moment load is 1000: 1, far-exceedingConventional balance far beyond traditional smallMxBalance 200: 1-300: 1, in the above range.
In the technical scheme, the upper side and the lower side of the first section of the balance main body structure 1 are respectively provided with the embedded limiting blocks 4 in a detachable mode, and the embedded torque element structures 3 are respectively embedded on the left side and the right side of the balance main body structure 1. The embedded limiting block 4 plays a role in limiting elastic deformation of the balance, and prevents the balance strain beam from generating large deformation under the action of external force to cause damage to the balance.
The connection between the embedded torque element structure 3 and the balance main body structure 1 adopts the modes of pin positioning and bolt pressing. In addition, in order to avoid the model shake that probably appears in the test process to cause the balance to damage, adopt "clearance spacing"'s mode, will multiple safe spacing linkage structure stack on the balance component in the design, specifically include: firstly, on the design of the embedded torque element structure 3, on the basis of the original single-chip beam, the limiting structure beam 12 is symmetrically arranged at the upper and lower positions, and the distance between the limiting structure beam 12 and the fixed end is designed through the idea of 'clearance limitation' for axial forceXSelf-protection of the axial force measuring unit in case of overload; secondly, on the design of the balance main structure 1, the embedded limiting blocks 4 are symmetrically arranged at the upper and lower positions on the basis of the beam shaped like a Chinese character 'mi', the distance between the embedded limiting blocks 4 and the fixed end is designed by the idea of 'gap limiting', and the structure can realize the removal of axial forceXSelf-protection of the measuring unit in case of overload with other components (emphasis is placed on pitching moment)MzProtection of the component measuring beam 7 and the embedded moment element structure 3); thirdly, install safe axle 5 additional at balance major structure center, safe axle 5 has spacing effect simultaneously: the safety shaft 5 being located at the pitching momentMzThe transition section of the component measuring beam 7 connected with the multi-piece laminated beam is used for ensuring the test after the overload or jitter phenomenon occurs, and the structure is used for preventing the jitter and the extreme phenomenon occurring in the actual work: the balance is damaged. The safety shaft 5 is arranged in the manner shown in fig. 7, the balance body structure 1 is provided with a front end 101 and a rear end 102, and four pitching moment platesMzComponent(s) ofThe measuring beam 7 is arranged axially between the front end 101 and the rear end 102, and the front end 101 and the rear end 102 are provided with center holes into which both ends of the safety shaft 5 are inserted, respectively, when pitching moment occursMzAfter the component measuring beam 7 is broken, the safety shaft 5 can still ensure that the front end portion 101 and the rear end portion 102 are in a stable connection state.
The number of apparatuses and the scale of the process described herein are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be apparent to those skilled in the art.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (6)
1. The utility model provides a high sensitivity rod-type six components wind-tunnel test balance that different materials are inlayed which characterized in that, rod-type six components wind-tunnel test balance is split type structure, designs alone roll moment measuring element, connects in parallel with balance major structure again, specifically does:
mounting embedded torque element structures on two sides of a balance main body structure in an embedded mounting mode, wherein the embedded torque element structures are made of materials different from the balance main body structure; the roll torque is measured independently through the embedded torque element structure which is arranged independently, so that high-sensitivity measurement of small roll torque is realized;
two ends of the embedded torque element structure are fixedly arranged on two sides of the balance main body structure in a pin positioning and screw pressing mode;
the embedded torque element is structurally provided with a sensor for measuring roll torqueMxComponent and yaw momentMyThe single-chip measuring beam of the component, the embedded torque element structure is also provided with two limit structure beamsThe structural beam is arranged above and below the single-chip measuring beam;
one end of the limiting structure beam is connected with one mounting end part of the embedded torque element structure, and a gap is reserved between the other end of the limiting structure beam and the other mounting end part of the embedded torque element structure.
2. The different-material-inlaid high-sensitivity rod-type six-component wind tunnel test balance according to claim 1, wherein the balance main body structure is made of one of chrome-manganese-silicon alloy steel, precipitation hardening stainless steel or maraging steel, and the inlaid torque element structure is made of one of aluminum alloy material 7075, copper or titanium alloy.
3. The different-material-inlaid high-sensitivity rod-type six-component wind tunnel test balance according to claim 1, comprising:
the balance comprises a balance main body structure, a plurality of measuring beams and a balance body, wherein the balance main body structure is a hollow nested structure, two sides of the balance main body structure are symmetrically embedded with embedded torque element structures, and the balance main body structure is also provided with the measuring beams;
the safety shaft is detachably mounted at the center inside the balance main body structure, and the fixed end of the balance main body structure is connected with a balance supporting structure in series.
4. The different-material-inlaid high-sensitivity rod-type six-component wind tunnel test balance of claim 3, wherein said plurality of measurement beams comprises:
four-piece pitching momentMzComponent measuring beam, four said pitching momentsMzThe component measuring beams are arranged in a 'meter' -shaped beam structure in the circumferential direction of the balance main body structure;
multi-plate normal forceYThe component measuring beams are integrally processed on the upper side and the lower side of the balance main body structure respectively;
multiple sheet side forceZThe component measuring beams are integrally processed on the left side and the right side of the balance main body structure respectively;
multi-disc axial forceXThe component measuring beams are integrally processed on the left side and the right side of the balance main body structure respectively;
the balance main body structure comprises a first section, a second section and a third section, wherein the second section is positioned between the first section and the third section;
the pitching momentMzThe component measuring beam and the embedded moment element structure are coaxially arranged at the first section;
said normal forceYComponent measurement beam and lateral forceZThe component measuring beam is coaxially arranged at the second section, and the normal forceYOne end of the component measuring beam is connected with the first section, and a gap is reserved between the other end of the component measuring beam and the end face of the third section; the lateral forceZOne end of the component measuring beam is connected with the third section, and a gap is reserved between the other end of the component measuring beam and the end face of the first section;
the axial forceXThe component measuring beam is coaxially arranged at the third section.
5. The high-sensitivity rod-type six-component wind tunnel test balance inlaid with different materials according to claim 4, wherein inlaid limiting blocks are detachably mounted on the upper side and the lower side of the first section of the balance main body structure respectively, and the two inlaid torque element structures are inlaid on the left side and the right side of the balance main body structure respectively.
6. The different-material-inlaid high-sensitivity rod-type six-component wind tunnel test balance according to claim 4, wherein said normal force isYComponent measurement beam and lateral forceZThe component measuring beam is of a multi-sheet laminated beam structure.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210214632.2A CN114323546B (en) | 2022-03-07 | 2022-03-07 | High-sensitivity rod-type six-component wind tunnel test balance embedded with different materials |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210214632.2A CN114323546B (en) | 2022-03-07 | 2022-03-07 | High-sensitivity rod-type six-component wind tunnel test balance embedded with different materials |
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| CN114993543B (en) * | 2022-05-24 | 2023-06-27 | 马洪文 | Dual multidimensional force measurement system |
| CN115144151B (en) * | 2022-08-31 | 2022-11-04 | 中国航空工业集团公司沈阳空气动力研究所 | Rod type hinge moment balance for small rolling moment measurement and measurement method |
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| CN101183039A (en) * | 2007-11-30 | 2008-05-21 | 中国航天空气动力技术研究院 | Balance system with inhibition structure |
| CN106441788A (en) * | 2016-10-27 | 2017-02-22 | 中国航天空气动力技术研究院 | Rotating disk apparatus for wind tunnel jet pipe |
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| JPH0961288A (en) * | 1995-08-29 | 1997-03-07 | Mitsubishi Heavy Ind Ltd | Balance for wind tunnel |
| US5663497A (en) * | 1996-07-22 | 1997-09-02 | Mole; Philip J. | Six component wind tunnel balance |
| CN105606333B (en) * | 2016-03-07 | 2018-04-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of small deformation wind-tunnel balance |
| CN108195554B (en) * | 2018-01-16 | 2023-08-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Six-component optical fiber aerodynamic force measurement balance and output signal combination method |
| CN207717327U (en) * | 2018-01-16 | 2018-08-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | Small-range high lift-drag ratio force balance applied to low density wind tunnel |
| RU2717746C1 (en) * | 2019-08-08 | 2020-03-25 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ)" | Multicomponent tensometric balance |
| CN111521369A (en) * | 2020-04-24 | 2020-08-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Six-component ring type wind tunnel balance |
| CN112362294B (en) * | 2020-11-27 | 2022-07-29 | 中国航天空气动力技术研究院 | Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance |
| CN113834626B (en) * | 2021-08-27 | 2023-06-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Six-component high-torque balance with unmatched loads |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101183039A (en) * | 2007-11-30 | 2008-05-21 | 中国航天空气动力技术研究院 | Balance system with inhibition structure |
| CN106441788A (en) * | 2016-10-27 | 2017-02-22 | 中国航天空气动力技术研究院 | Rotating disk apparatus for wind tunnel jet pipe |
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