CN115165296B - Device and method for measuring aerodynamic force load of hinge moment of long and narrow control surface - Google Patents
Device and method for measuring aerodynamic force load of hinge moment of long and narrow control surface Download PDFInfo
- Publication number
- CN115165296B CN115165296B CN202211086973.2A CN202211086973A CN115165296B CN 115165296 B CN115165296 B CN 115165296B CN 202211086973 A CN202211086973 A CN 202211086973A CN 115165296 B CN115165296 B CN 115165296B
- Authority
- CN
- China
- Prior art keywords
- moment
- balance
- side connecting
- rudder
- measuring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a device and a method for measuring aerodynamic force load of hinge moment of a long and narrow control surface, belongs to the field of aerospace aerodynamic force test measuring equipment, and aims to solve the problem that when aerodynamic force load is measured by using a measuring rudder with a long and narrow control surface, one end far away from a balance element generates large displacement, so that measured data is inaccurate. The device comprises a moment balance and a long and narrow measuring rudder, wherein a connecting sleeve is arranged at one end of the long and narrow measuring rudder in the width direction, one ends of two moment balances are respectively connected with two ends of the connecting sleeve, the two moment balances and the connecting sleeve are arranged in a mounting groove of a model airfoil, and the other ends of the two moment balances are respectively connected with the model airfoil. Two moment balances are adopted to be connected with the measuring rudder, the supporting rigidity can be greatly improved by double-end support, the loaded deformation of the control surface is greatly reduced, the aerodynamic loads of the two moment balances are synthesized to obtain the total aerodynamic load of the control surface, the normal operation of test measurement can be ensured, and the problem of simulation distortion caused by the deformation of the control surface is avoided.
Description
Technical Field
The invention belongs to the field of aerospace aerodynamic force test measuring equipment, and particularly relates to a device and a method for measuring aerodynamic force load of hinge moment of a long and narrow control surface.
Background
The wind tunnel balance is used for measuring aerodynamic load acting on an aircraft in a wind tunnel test and can be divided into a mechanical balance, an optical fiber balance, a piezoelectric balance and the like according to a working principle. At present, a strain balance is commonly used, a strain gauge is adhered to a balance element by adopting a strain electric measurement principle to form an electric bridge, and strain of the load deformation of the balance element is converted into an electric signal to be measured. And calibrating the mapping relation between the load and the electric signal in advance, and calculating the aerodynamic load of the aircraft according to the measured electric signal according to the mapping relation.
The sheet type hinge moment balance is one of strain balances, is mainly used for measuring aerodynamic load of an aircraft model airfoil, and one end of the sheet type hinge moment balance is connected with a measuring rudder while the other end of the sheet type hinge moment balance is connected with the airfoil of the model. During wind tunnel test, the balance element is deformed under load, and for a measuring rudder with a shorter control surface, the change of the whole pneumatic displacement of the model caused by the deformation of the balance element is within an error allowable range, so that the test data cannot be greatly influenced. However, for the measuring rudder with a long and narrow rudder surface, the deformation of the balance element can cause a large displacement of one end of the measuring rudder far away from the moment balance, so that a large scissors fork is formed between the rudder surface of the measuring rudder and the airfoil surface of the model, serious simulation distortion is caused, the difference between the measured data and the real state is large, and the measured data is inaccurate.
Disclosure of Invention
The invention aims to provide a device and a method for measuring aerodynamic load of hinge moment of a long and narrow control surface, which are used for solving the problems that when aerodynamic load acting on an aircraft is measured by using a long and narrow measuring rudder of a control surface, one end of the measuring rudder, which is far away from a balance element, generates large displacement, so that serious simulation distortion is caused, and measurement data is inaccurate. The technical scheme adopted by the invention is as follows:
a moment aerodynamic force load measuring device for a long and narrow control surface hinge comprises a moment balance and a long and narrow measuring rudder, wherein a first T-shaped groove, a balance element groove and a second T-shaped groove which are communicated from left to right are formed in a model wing surface;
the moment balance comprises a wing side connecting part, a balance element and a rudder side connecting part, wherein the balance element consists of a plurality of beam-shaped components which are arranged at intervals, the wing side connecting part is a T-shaped straight beam, the rudder side connecting part is a rectangular plate, one end of the balance element is connected with a middle protruding end of the wing side connecting part, and the other end of the balance element is connected with one side edge of the rudder side connecting part;
a connecting sleeve is arranged in the middle of one end of the long and narrow rudder in the width direction, and the circumferential direction of an inner hole of the connecting sleeve is matched with the circumferential direction of the connecting part at the side of the rudder;
the rudder side connecting parts of the two torque balances are inserted into inner holes of the connecting sleeves respectively from two ends of the connecting sleeves and are fixed through a plurality of pins, the wing side connecting part of the left-end torque balance is inserted into the first T-shaped groove, the periphery of the wing side connecting part of the left-end torque balance is matched with the inner periphery of the first T-shaped groove, the wing side connecting part of the left-end torque balance is fixed with the model airfoil through a plurality of pins, the wing side connecting part of the right-end torque balance is inserted into the second T-shaped groove, the periphery of the wing side connecting part of the right-end torque balance is matched with the inner periphery of the second T-shaped groove, the wing side connecting part of the right-end torque balance is fixed with the model airfoil through a plurality of pins, the connecting sleeves are arranged in grooves of the balance elements, and a working space is arranged between the connecting sleeves and the groove walls of the balance elements.
Further, the number of the beam-shaped members is three.
Further, the beam-like member is a rectangular straight beam.
Furthermore, the periphery of one end, close to the balance element, of the rudder side connecting part is provided with a limiting convex strip.
Furthermore, the first T-shaped groove and the second T-shaped groove are in transition fit with the corresponding wing side connecting parts respectively.
Furthermore, the connecting sleeve is in transition fit with the rudder side connecting parts of the two moment balances respectively.
The invention also provides a method for measuring the aerodynamic load of the hinge moment of the long and narrow control surface, which is completed by adopting the device for measuring the aerodynamic load of the hinge moment of the long and narrow control surface and comprises the following steps:
step 1: adhering 4 strain gauges which are subjected to deformation to balance elements of the moment balance to form an electric bridge, calibrating and calibrating the moment balance to respectively obtain the relation coefficients of the load and the output voltage of the two moment balances, and taking the geometric center of the balance elements as the reference center of the calibration and calibration of the moment balance;
and 2, step: assembling all parts according to the connection relation of the measuring device and carrying out test measurement, and recording the output voltage of the left-end moment balance as delta u 1 、△u 2 、△u 3 The output voltage of the right-hand moment balance is recorded as Deltau 4 、△u 5 、△u 6 ；
And step 3: calculating the aerodynamic loads of the two moment balances, and recording the aerodynamic load of the left moment balance as N 1 、Mz 1 、Mj 1 The aerodynamic load of the right-hand moment balance is recorded as N 2 、Mz 2 、Mj 2 Of a loadThe reference center is the reference center of the two moment balances in the step 1 during self calibration and calibration;
and 4, step 4: synthesizing aerodynamic load, wherein the normal component, the bending moment and the hinge moment of the aerodynamic load of the model airfoil are determined by the following formula:
N=N 1 +N 2
Mz=Mz 1 +Mz 2 +（N 2 -N 1 ）*L
Mj=Mj 1 +Mj 2
in the formula: n is the normal component of the model airfoil aerodynamic load;
mz is a model airfoil aerodynamic load bending moment;
mj is the aerodynamic load hinge moment of the model airfoil;
l is the distance between the measuring centers of the two moment balances.
Compared with the prior art, the invention has the beneficial effects that:
for the measuring rudder with the long and narrow rudder surface, the stress structure is a cantilever beam structure, and as the deformation of the balance element can enable one end of the measuring rudder, which is far away from the moment balance, to generate larger displacement, the measuring rudder surface and the model airfoil surface can form larger scissors and forks, so that larger simulation distortion is caused, and the difference between the measured data and the real state is larger. And two moment balances are connected with the measuring rudder, the support rigidity can be greatly improved by double-end support, the loaded deformation of the control surface is greatly reduced, the aerodynamic loads of the two moment balances are synthesized to obtain the total aerodynamic load of the control surface, the normal operation of test measurement can be ensured, and the problem of simulation distortion caused by the deformation of the control surface is avoided.
Drawings
FIG. 1 is a schematic view of the assembly of the present invention with a model airfoil;
FIG. 2 is an isometric view of a model airfoil;
FIG. 3 is an enlarged view at A of FIG. 2;
FIG. 4 is an isometric view of a measuring rudder;
FIG. 5 is an isometric view of a moment balance;
FIG. 6 is a schematic illustration of a partial installation of a model airfoil with two moment-scales and an elongated measurement rudder.
In the figure: 1-model airfoil surface, 11-first T-shaped groove, 12-balance element groove, 13-second T-shaped groove, 2-moment balance, 21-wing side connecting part, 22-balance element, 23-rudder side connecting part, 24-limiting convex strip, 3-measuring rudder and 31-connecting sleeve.
Detailed Description
In order that the objects, aspects and advantages of the invention will become more apparent, the invention will be described by way of example only, and with reference to the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The connection mentioned in the invention is divided into fixed connection and detachable connection, the fixed connection is non-detachable connection and comprises but is not limited to folding edge connection, rivet connection, bonding connection, welding connection and other conventional fixed connection modes, the detachable connection comprises but is not limited to bolt connection, buckle connection, pin connection, hinge connection and other conventional detaching modes, when the specific connection mode is not clearly limited, the skilled person can select at least one connection mode from the existing connection modes to realize the function by default, and the skilled person can select the connection mode according to the needs. For example: the fixed connection selects welded connection, and the detachable connection selects bolted connection.
The present invention will be described in further detail with reference to the accompanying drawings, and the following examples are illustrative of the present invention, but the present invention is not limited to the following examples.
Example 1: as shown in fig. 1-6, the moment aerodynamic load measuring device of the hinge of the long and narrow control surface comprises a moment balance 2 and a long and narrow measuring rudder 3, wherein a model airfoil 1 is provided with a first T-shaped groove 11, a balance element groove 12 and a second T-shaped groove 13 which are communicated from left to right;
the moment balance 2 comprises a wing side connecting part 21, a balance element 22 and a rudder side connecting part 23, wherein the balance element 22 consists of a plurality of beam-shaped components which are arranged at intervals, the wing side connecting part 21 is a T-shaped straight beam, the rudder side connecting part 23 is a rectangular plate, one end of the balance element 22 is connected with a middle convex end of the wing side connecting part 21, and the other end of the balance element 22 is connected with one side edge of the rudder side connecting part 23;
a connecting sleeve 31 is arranged in the middle of one end of the long and narrow measuring rudder 3 in the width direction, and the circumferential direction of an inner hole of the connecting sleeve 31 is matched with the circumferential direction of the rudder side connecting part 23;
the rudder side connecting parts 23 of the two torque balances 2 are respectively inserted into inner holes of the connecting sleeves 31 from two ends and are fixed through a plurality of pins, the wing side connecting part 21 of the left-end torque balance 2 is inserted into the first T-shaped groove 11, the periphery of the wing side connecting part 21 of the left-end torque balance 2 is matched with the inner periphery of the first T-shaped groove 11, the wing side connecting part 21 of the left-end torque balance 2 is fixed with the model airfoil 1 through a plurality of pins, the wing side connecting part 21 of the right-end torque balance 2 is inserted into the second T-shaped groove 13, the periphery of the wing side connecting part 21 of the right-end torque balance 2 is matched with the inner periphery of the second T-shaped groove 13, the wing side connecting part 21 of the right-end torque balance 2 is fixed with the model airfoil 1 through a plurality of pins, the connecting sleeves 31 are arranged in the balance element grooves 12, and a working space is arranged between the connecting sleeves 31 and the groove walls of the balance element grooves 12.
The number of the beam-shaped members is three.
The beam-like member is a rectangular straight beam.
The periphery of one end of the rudder side connecting part 23 close to the balance element 22 is provided with a limiting convex strip 24.
The first T-shaped groove 11 and the second T-shaped groove 13 are respectively in transition fit with the corresponding wing-side connecting portion 21.
The connecting sleeves 31 are respectively in transition fit with the rudder-side connecting portions 23 of the two moment balances 2.
For the measuring rudder with a long and narrow rudder surface, the stress structure is a cantilever beam structure, and as the deformation of the balance element 22 can cause the end of the measuring rudder 3 far away from the moment balance to generate larger displacement, the measuring rudder surface and the model airfoil surface can form larger scissors fork, so that larger simulation distortion is caused, and the difference between the measured data and the real state is larger. And adopt two moment balances 2 to link to each other with measuring rudder 3, the bi-polar is supported and then can improve support rigidity greatly, and the loaded deflection of reduction rudder face of great amplitude is by a wide margin, synthesizes the aerodynamic force load of two moment balances 2 and obtains total rudder face aerodynamic load, both can guarantee that experimental measurement is normally gone on, has avoided the simulation distortion problem that the rudder face warp and bring simultaneously again.
Example 2: the invention also provides a method for measuring the aerodynamic load of the hinge moment of the long and narrow control surface, which is completed by adopting the device for measuring the aerodynamic load of the hinge moment of the long and narrow control surface and comprises the following steps:
step 1: 4 strain gauges which are subjected to deformation are adhered to the balance elements 22 of the moment balance 2 to form an electric bridge, the moment balance 2 is calibrated, the relation coefficients of the load and the output voltage of the two moment balances 2 are respectively obtained, and the geometric center of the balance elements 22 is used as the reference center of the moment balance 2 for calibration;
and 2, step: assembling all parts according to the connection relation of the measuring devices and carrying out test measurement, and recording the output voltage of the left-end moment balance 2 as delta u 1 、△u 2 、△u 3 The output voltage of the right-hand moment balance 2 is recorded as Deltau 4 、△u 5 、△u 6 ；
And step 3: calculating the aerodynamic loads of the two moment balances 2, and recording the aerodynamic load of the left moment balance 2 as N 1 、Mz 1 、Mj 1 And the aerodynamic load of the right-hand moment balance 2 is recorded as N 2 、Mz 2 、Mj 2 The reference center of the load is the reference center of the two moment balances 2 in the step 1 during self calibration and calibration;
and 4, step 4: synthesizing aerodynamic load, and determining the normal component, bending moment and hinge moment of the aerodynamic load of the model airfoil 1 according to the following formulas:
N=N 1 +N 2
Mz=Mz 1 +Mz 2 +（N 2 -N 1 ）*L
Mj=Mj 1 +Mj 2
in the formula: n is the normal component of the aerodynamic force load of the model airfoil;
mz is aerodynamic load bending moment of the model airfoil;
mj is the aerodynamic load hinge moment of the model airfoil;
and L is the distance between the measuring centers of the two moment balances.
The above embodiments are merely illustrative of the present patent and do not limit the scope of the patent, and those skilled in the art can make modifications to the parts thereof without departing from the spirit and scope of the patent.
Claims (4)
1. A method for measuring aerodynamic force load of a long and narrow control surface hinge moment is realized by relying on a device for measuring the aerodynamic force load of the long and narrow control surface hinge moment, and comprises a moment balance (2) and a long and narrow measuring rudder (3), wherein a model airfoil (1) is provided with a first T-shaped groove (11), a balance element groove (12) and a second T-shaped groove (13) which are communicated from left to right;
the moment balance (2) comprises wing side connecting parts (21), balance elements (22) and rudder side connecting parts (23), each balance element (22) consists of a plurality of beam-shaped components which are arranged at intervals, each wing side connecting part (21) is a T-shaped straight beam, each rudder side connecting part (23) is a rectangular plate, one end of each balance element (22) is connected with a middle protruding end of each wing side connecting part (21), and the other end of each balance element (22) is connected with one side edge of each rudder side connecting part (23);
a connecting sleeve (31) is arranged in the middle of one end of the long and narrow measuring rudder (3) in the width direction, and the circumferential direction of an inner hole of the connecting sleeve (31) is matched with the circumferential direction of the rudder side connecting part (23);
the rudder side connecting parts (23) of the two moment balances (2) are respectively inserted into inner holes of the connecting sleeves (31) through two ends of the connecting sleeves and are fixed through a plurality of pins, the wing side connecting part (21) of the left moment balance (2) is inserted into the first T-shaped groove (11), the periphery of the wing side connecting part (21) of the left moment balance (2) is matched with the inner periphery of the first T-shaped groove (11), the wing side connecting part (21) of the left moment balance (2) is fixed with the model airfoil surface (1) through a plurality of pins, the wing side connecting part (21) of the right moment balance (2) is inserted into the second T-shaped groove (13), the periphery of the wing side connecting part (21) of the right moment balance (2) is matched with the inner periphery of the second T-shaped groove (13), the wing side connecting part (21) of the right moment balance (2) is fixed with the model airfoil surface (1) through a plurality of pins, the first T-shaped groove (11) and the second T-shaped groove (13) are respectively in transition fit with the corresponding wing side connecting parts (21), the connecting parts (31) of the connecting parts of the connecting sleeves (2), and the rudder side connecting parts (31) are respectively arranged between the rudder side connecting parts (31) and the rudder side connecting parts (12) and are arranged in the grooves of the balance grooves of the connecting parts of the connecting grooves;
the method is characterized in that: the method comprises the following steps:
step 1: 4 strain gauges which are subjected to deformation are adhered to balance elements (22) of the moment balance (2) to form an electric bridge, calibration and calibration of the moment balance (2) are carried out, relation coefficients of loads and output voltages of the two moment balances (2) are obtained respectively, and the geometric center of the balance elements (22) is used as a reference center of the calibration and calibration of the moment balances (2);
step 2: assembling all parts according to the connection relation of the measuring device and carrying out test measurement, and recording the output voltage of the left-end moment balance (2) as delta u 1 、△u 2 、△u 3 And the output voltage of the right-end moment balance (2) is recorded as delta u 4 、△u 5 、△u 6 ；
And step 3: calculating the aerodynamic loads of the two moment balances (2), and recording the aerodynamic load of the left end moment balance (2) as N 1 、Mz 1 、Mj 1 And the aerodynamic load of the right-end moment balance (2) is recorded as N 2 、Mz 2 、Mj 2 The reference center of the load is the reference center of the two moment balances (2) in the step 1 during self calibration and calibration;
and 4, step 4: synthesizing aerodynamic load, and determining the normal component, bending moment and hinge moment of the aerodynamic load of the model airfoil (1) by the following formula:
N＝N 1 +N 2
Mz＝Mz 1 +Mz 2 +(N 2 -N 1 )*L
Mj＝Mj 1 +Mj 2
in the formula: n is the normal component of the aerodynamic force load of the model airfoil;
mz is a model airfoil aerodynamic load bending moment;
mj is the aerodynamic load hinge moment of the model airfoil;
and L is the distance between the measuring centers of the two moment balances.
2. An elongated control surface hinge moment aerodynamic force load measurement method as claimed in claim 1, characterized in that: the number of the beam-shaped members is three.
3. An elongated control surface hinge moment aerodynamic force load measurement method as claimed in claim 2, characterized in that: the beam-like member is a rectangular straight beam.
4. An elongated control surface hinge moment aerodynamic force load measurement method as claimed in claim 1, characterized in that: the periphery of one end of the rudder side connecting part (23) close to the balance element (22) is provided with a limiting convex strip (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211086973.2A CN115165296B (en) | 2022-09-07 | 2022-09-07 | Device and method for measuring aerodynamic force load of hinge moment of long and narrow control surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211086973.2A CN115165296B (en) | 2022-09-07 | 2022-09-07 | Device and method for measuring aerodynamic force load of hinge moment of long and narrow control surface |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115165296A CN115165296A (en) | 2022-10-11 |
| CN115165296B true CN115165296B (en) | 2022-12-13 |
Family
ID=83481389
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211086973.2A Active CN115165296B (en) | 2022-09-07 | 2022-09-07 | Device and method for measuring aerodynamic force load of hinge moment of long and narrow control surface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115165296B (en) |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN105115694B (en) * | 2015-07-21 | 2017-11-14 | 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 chip hinge moment balance |
| CN204988678U (en) * | 2015-07-21 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Piece formula hinge moment balance |
| CN106092498B (en) * | 2016-08-19 | 2019-03-05 | 大连理工大学 | A kind of five component piezoelectric types " double balances " |
| CN111504596B (en) * | 2020-04-07 | 2020-12-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Hinge moment balance |
| CN113670560B (en) * | 2021-10-21 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN114370990A (en) * | 2022-01-20 | 2022-04-19 | 重庆大学 | Complex section three-dimensional buffeting force identification method based on double-balance synchronous force measurement technology |
-
2022
- 2022-09-07 CN CN202211086973.2A patent/CN115165296B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN115165296A (en) | 2022-10-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2997479C (en) | Systems and methods for mounting landing gear strain sensors | |
| CN115144151B (en) | Rod type hinge moment balance for small rolling moment measurement and measurement method | |
| CN101532817B (en) | Resistance strain gauge and sensor using resistance strain gauge to change stress transfer mode | |
| CA1115985A (en) | Load cell | |
| CN115655641B (en) | High-precision loading force application device and method for wind tunnel balance calibration | |
| CN111175016B (en) | Surface friction resistance wind tunnel measuring method based on box type friction resistance balance | |
| CN115165296B (en) | Device and method for measuring aerodynamic force load of hinge moment of long and narrow control surface | |
| JP3796245B2 (en) | Modular load measuring cell and measuring instrument used for measuring instrument | |
| US7155348B2 (en) | Force-measuring cell for a weighing scale, and weighing scale | |
| CN112629748A (en) | Combined synchronous calibration device and method for reference type multi-dimensional force sensor | |
| KR101137027B1 (en) | Measurement Apparatus of Aerodynamic Load for Rotor Blade and Calibration Method of the Same | |
| CN109632240B (en) | Control surface force measuring balance in unfolding process of folding rudder | |
| CN110987271B (en) | Three-component force sensor for measuring load at joint of automotive suspension bush | |
| CN111649907A (en) | Rib strip type micro-axial force annular two-component strain balance | |
| US5591944A (en) | Overload stop assembly for a load cell | |
| CN112362216B (en) | Engine six-component force measuring device adopting double measuring systems | |
| JP2006047118A (en) | Load cell | |
| CN212159002U (en) | Six-component ring type wind tunnel balance | |
| CN115165297B (en) | Mortise-tenon joint structure sheet type hinge moment balance | |
| CN114646451B (en) | Balance with double fixed supporting parts | |
| Hufnagel | Wind Tunnel Balances | |
| CN215296402U (en) | Novel section difference resistant unbalance loading resistant overlong plate type pressure sensor | |
| CN203169161U (en) | Anti-overloading transducer for pulse beating blood pressure wave strength | |
| CN116242577B (en) | Wind tunnel cluster special balance and wind tunnel system for cluster measurement | |
| US20020157477A1 (en) | Load transducers |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |