CN114735231B - Flight data acquisition device - Google Patents
Flight data acquisition device Download PDFInfo
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- CN114735231B CN114735231B CN202111680287.3A CN202111680287A CN114735231B CN 114735231 B CN114735231 B CN 114735231B CN 202111680287 A CN202111680287 A CN 202111680287A CN 114735231 B CN114735231 B CN 114735231B
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- 238000005303 weighing Methods 0.000 claims abstract description 97
- 238000003825 pressing Methods 0.000 claims abstract description 25
- 230000008859 change Effects 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 10
- 230000008569 process Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 5
- 230000000452 restraining effect Effects 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 13
- 239000000725 suspension Substances 0.000 abstract description 10
- 238000009826 distribution Methods 0.000 abstract description 4
- 238000005096 rolling process Methods 0.000 abstract description 3
- 238000013461 design Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 2
- 238000007405 data analysis Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000013142 basic testing Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The application provides a flight data acquisition device, which belongs to the technical field of aviation, wherein a cover plate of the device is fixedly connected with a shell to form a closed space; the weighing sensors are all positioned in the closed space and fixed on the shell, wherein 1 weighing sensor is positioned at the front part of the closed space; the rest weighing sensors are divided into two groups, and the weighing sensors in each group are electrically connected with the main board; the quick pressing piece is positioned at the front end of the shell and is electrically connected with the first weighing sensor, and the quick pressing piece transmits wind resistance pressure to the first weighing sensor and then to the main board; five planes are arranged on each ball of the two weight dumbbells, and each plane is in contact with the sensing surface of the weighing sensor. Six degrees of freedom of force in flight can be tested; the rotating axle center in the flying rolling process can be tested; the speed pressing piece can test real data of working conditions and can better know the speed pressure distribution of the aircraft in various speed states; the optimal windward section form of each type of aircraft airborne suspension device can be found out through the shape of the quick-pressing piece.
Description
Technical Field
The application belongs to the technical field of aviation, and particularly relates to a flight data acquisition device.
Background
In the flight process of the aircraft platform, the stress condition is complex, and various stresses in the environment are considered in the design of the airborne suspension device, which is different from the functions of an aircraft travel recorder, including recording the changes of the flight working conditions and the like, and mainly comprises speed, height, temperature acceleration and the like.
In the related art, the design standard of the airborne suspension device refers to the army standard, all theoretical calculations are quite comprehensive, but aiming at overload values of various environments defined in the standard, basic test data support is lacked. The current design standard needs to be further verified: 1. the difference between the fuselage suspension and the wing overload is large; 2. the stress of the wing and the wing tip is calculated according to consistency, and the impact of each hanging point from the root to the wing tip is reduced under the influence of the elasticity of the wing under the normal condition; 3. the rapid pressure is a given reference value, and the changes of the flight flow field, the influence of the shock wave of the aircraft nose and the like are not considered; 4. the wind tunnel test flow field is the difference between the high-density compressed air and the actual flight environment. To meet the current requirements, the mechanical structure of the on-board suspension device is less scientific and conservative, which results in a low on-board suspension device load ratio (the load ratio is the ratio of the weight carried by the mechanism to its own weight). And the thrust-weight ratio of the flying key component engine is about 10.
Problems with conventional airborne suspension devices affect the performance of the aircraft such as payload, maneuverability, flight speed, and lift. Therefore, the flight data acquisition device is required to acquire flight data, and the calculation result of the related formulas is verified, so that design redundancy is scientifically reduced. In addition, the sensor for the airborne platform is limited by the principle of the sensor, has directivity, and cannot meet six-degree-of-freedom tests of stress, such as the test of torsion moment. And the measurement of the rapid pressure of a single sensor in the form of a windward section is not taken into account, as a result of which there is a large deviation.
Disclosure of Invention
In order to solve the problem that the related art cannot collect flight data, the invention provides a flight data collecting device, which comprises the following technical scheme:
A flight data acquisition device comprising: the shell, the cover plate, the two weight dumbbells, the quick-pressing piece, the main board and the weighing sensors,
The cover plate is fixedly connected with the shell to form a closed space;
The weighing sensors are all positioned in the closed space and fixed on the shell, wherein 1 weighing sensor is positioned at the front part of the closed space and used for supporting the quick press piece, and the other weighing sensors are positioned in the closed space; the rest weighing sensors are divided into two groups, the weighing sensors in each group are electrically connected with a main board, and the main board is used for reading and storing data acquired by the weighing sensors and determining the real overload condition of each hanging point through the data change of each weighing sensor in the flying process;
the quick pressing piece is positioned at the front end of the shell and is electrically connected with the first weighing sensor, the first weighing sensor is electrically connected with the main board, the quick pressing piece transmits wind resistance pressure to the first weighing sensor, the first weighing sensor transmits wind resistance pressure to the main board, and the first weighing sensor is positioned at the front part of the closed space;
The two weight dumbbells are placed in a staggered mode, five planes are arranged on each ball of the weight dumbbells, each plane is in contact with the sensing surface of the weighing sensor, and the weighing sensor is used for measuring pressure change of the weight dumbbells and transmitting measured data to the main board.
Optionally, the device comprises two main boards,
The rest weighing sensors are divided into two groups, and the weighing sensors in each group are electrically connected with a main board; each weighing sensor has an identifier for uniquely indicating the weighing sensor, the identifier of the weighing sensor corresponding to the corresponding motherboard interface.
Optionally, the housing is provided with a mounting hole fixedly connected with the aircraft,
The inside of the shell is also provided with a plurality of weighing sensor bases, and each weighing sensor base is provided with a plurality of weighing sensor fixing holes for fixing one weighing sensor;
each of the two side surfaces of the shell is provided with a plurality of weighing sensor fixing holes for fixing a weighing sensor;
the front end of the shell is provided with a quick-pressing piece mounting hole for restraining the quick-pressing piece, so that the quick-pressing piece can only horizontally displace.
Optionally, each weight dumbbell is composed of two balls and a connecting rod, the connecting rod is located between the two balls, a notch is formed in the middle of the connecting rod, the weight of the weight dumbbell is a multiple of 3, the balls and the connecting rod are equal in weight, and the ball distances of the two weight dumbbell are constant.
Optionally, the main board includes an electrical component, a port connected to the aircraft host, and a port electrically connected to the load cell.
Optionally, the weighing sensor is provided with a weighing surface, a supporting surface, a mounting fixing hole and a data line interface, and the data line interface is electrically connected with the port of the main board through a data line; the weighing surface is contacted with a plane on the ball of the weight dumbbell; the supporting surface is fixedly arranged on the weighing sensor base or the side surface of the shell; the installation fixing hole is connected and fixed with a weighing sensor fixing hole arranged on the side face of the shell in a matched mode.
Optionally, the installation direction of the flight data acquisition device is vertical or horizontal, and the direction data in each weighing sensor data is marked according to the installation direction of the flight data acquisition device.
Optionally, a clock synchronization unit is disposed between the two mainboards.
The beneficial effects of the invention are as follows:
1. Six degrees of freedom of force in the flight state, namely axial force and torsion moment of an x axis, a y axis and a z axis can be tested;
2. the method can test the rotation axis in the flying rolling process, the rotation axis is the key of theoretical calculation, and the difference between the actual and the theoretical can be determined through data analysis;
3. the speed pressing piece can test real data of working conditions and can know the speed pressure distribution of the airplane in various speed states;
4. the design of the speed pressing piece can determine the optimal windward section form of the airborne suspension device of various airplanes.
Drawings
FIG. 1 is a schematic diagram of a flight data acquisition device according to an embodiment of the present invention;
FIG. 2 is a schematic view of a housing structure according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a weight dumbbell according to an embodiment of the present application;
fig. 4 is a schematic diagram of a motherboard structure according to an embodiment of the present application;
fig. 5 is a schematic diagram of a weighing sensor according to an embodiment of the present application.
Detailed Description
The application is described in further detail below with reference to specific embodiments and figures.
Problems with conventional airborne suspension devices affect the performance of the aircraft such as payload, maneuverability, flight speed, and lift. Therefore, the flight data acquisition device is required to acquire flight data, and the calculation result of the related formulas is verified, so that design redundancy is scientifically reduced. In addition, the sensor for the airborne platform is limited by the principle of the sensor, has directivity, and cannot meet six-degree-of-freedom tests of stress, such as the test of torsion moment. And the measurement of the rapid pressure of a single sensor in the form of a windward section is not taken into account, as a result of which there is a large deviation. Based on the above, the invention provides a flight data acquisition device which can complete the test of six degrees of freedom of constraint, can test various overload parameters of various hanging points of an airplane body and a wing, and provides a basis for scientifically designing the hanging device of various hanging points of the airplane. The device can detect the acceleration change in each direction caused by the action of the aircraft in the flight process, the weight dumbbell has the pressures of different sizes on each weighing sensor in different directions, the main board records the numerical change of each weighing sensor, and then the overload change of each hanging point of the aircraft is deduced.
Only the load cell of the quick press member reacts to wind resistance changes, and other load cell data are adjusted according to the mass of the weight dumbbell. Meanwhile, according to the actual design, the windward section form of the rapid pressing part on the device can accurately measure the rapid pressing of each hanging point, and further the distribution requirement of various aircraft flow fields on the airborne hanging device can be deduced; and finding out the lowest windage cross section scheme of each aircraft and each hanging point according to the relation between the rapid compression and the speed.
As shown in fig. 1, a flight data acquisition device provided by an embodiment of the present invention includes: the device comprises a shell 1, a cover plate 2, two weight dumbbells 3, 1 quick-press parts 4, two main boards 5, 21 weighing sensors 6, connecting wires and power wires.
Wherein, the cover plate 2 and the shell 1 are fixed by screws to form a closed space.
The 21 weighing sensors 6 are all positioned in the closed space and fixed on the shell 1, wherein 1 weighing sensor 6 is positioned at the front part of the closed space to form a support for the quick press; the remaining load cells 6 are divided into two groups, the load cells 6 in each group being electrically connected to one main board 5. The main board 5 is used for timely reading and storing data acquired by the corresponding weighing sensors 6, and determining the real overload condition of each hanging point through the data change of each weighing sensor 6 in the flight process.
Each load cell 6 has an identifier for uniquely indicating the load cell 6, the identifier of the load cell 6 corresponding to the motherboard interface, avoiding errors. For example, the interfaces of one of the main boards are A, B, C, respectively, and the identifiers of the load cells 6 electrically connected thereto may be A1, B1, C1, respectively, and the like.
The embodiment of the present invention refers to the load cell 6 located at the front of the closed space as the first load cell 6.
The quick pressing part 4 is positioned at the front end of the shell 1 and is electrically connected with the first weighing sensor 6, the first weighing sensor 6 is electrically connected with one main board 5, the quick pressing part 4 transmits wind resistance pressure to the first weighing sensor 6, and the first weighing sensor 6 transmits wind resistance pressure to the main board 5 electrically connected with the quick pressing part;
each weight dumbbell 3 consists of two balls and a connecting rod, the connecting rod is positioned between the two balls, and a notch is formed in the middle of the connecting rod. The two weight dumbbell 3 are placed in a crossed way through the notch in the middle of the connecting rod, so that no contact stress is ensured between the two weight dumbbell. Five flat surfaces 301 are provided on each ball, each flat surface 301 being in contact with the sensing surface of the load cell 6. The weighing sensor 6 is used for measuring the pressure change of the weight dumbbell 3 and transmitting measured data to a main board electrically connected with the weight dumbbell 3, and the weighing range and the precision are matched with those of the weight dumbbell 3.
As shown in fig. 2, the housing 1 is provided with a mounting hole 101 fixedly connected to the aircraft.
Also provided within the housing 1 are 13 load cell bases 102 for providing support for the load cells 6. Each load cell base 102 is provided with 4 load cell fixing holes 103 for fixing one load cell 6.
Each of the two side surfaces of the housing 1 is provided with 16 load cell fixing holes 103, and one load cell 6 is fixed to each of the four load cell fixing holes 103.
The front end of the housing 1 is provided with a quick press mounting hole 104 for fixing the quick press 4, and the quick press 4 transmits wind resistance pressure to the weighing sensor 6. The weighing sensor (6) transmits the windage pressure to a main board electrically connected with the weighing sensor.
As shown in fig. 3, each weight dumbbell 3 is composed of two balls and a connecting rod, the connecting rod is located between the two balls, and a notch is formed in the middle of the connecting rod. The weight of the balance weight dumbbell 3 is a multiple of 3, and the weight of the ball is equal to that of the connecting rod. The ball spacing of the two weight dumbbells 3 is a constant number.
Five planes 301 are arranged on each ball, one plane is opposite to the connecting end of the ball and the connecting rod, the other four planes are arranged in pairs and are positioned at the two ends of the diameter of the ball, and the connecting line between every two planes is perpendicular to the connecting end and the connecting line of the corresponding planes. Each plane 301 is in contact with the sensing surface of the weighing sensor 6, uneven deviation can be avoided due to the arrangement of the planes, and the gap 302 in the middle of the connecting rod can prevent the two weight dumbbells 3 from being in contact when placed in an intersecting manner.
As shown in fig. 4, the main board 5 is configured to timely read and store data collected by each weighing sensor 6, and the real overload condition of each hanging point can be known through the data change of each weighing sensor 6 in the flight process. The main board 5 comprises electrical components, a port 501 connected to the aircraft host, and a port 502 connected to the load cell 6.
As shown in fig. 5, the weighing sensor 6 is a high-frequency high-precision pressure sensor, and is mainly used for measuring the pressure change of the weight dumbbell 3, and the weighing range and the precision are matched with those of the weight dumbbell 3.
The load cell 6 is provided with a weighing surface 601, a supporting surface 602, a mounting fixing hole 603 and a data line interface 604. The data line interface 604 is electrically connected to the port 502 via a data line; the weighing surface 601 is in contact with the flat surface 301 on the ball of the weight dumbbell 3; the supporting surface 602 is fixedly arranged on the weighing sensor base 102 or the side surface of the shell 1; the mounting and fixing hole 603 is connected and fixed with the weighing sensor fixing hole 103 arranged on the side face of the shell 1 in a matching way.
In the embodiment of the invention, the direction data in the data of each weighing sensor is required to be marked or trimmed according to the installation direction of the flight data acquisition device. For example, when the flight data acquisition device is installed from vertical to horizontal, the direction data in the weighing sensor data can change, and at this time, the direction data needs to be marked to avoid directional deviation.
In the embodiment of the invention, a clock synchronization unit is arranged between two mainboards. The clock synchronization technique is used to ensure time synchronicity of the two mainboards 5 and the mainboards 5 with the host. The clock synchronization technique may refer to the related art and will not be described herein.
A slight gap is provided after the load cell 6 is installed to accommodate the weight dumbbell 3, ensuring that no external force is applied between the load cell 6 and the weight dumbbell 3.
The flight data acquisition device provided by the invention can acquire stress data of each hanging point of various flight states of the aircraft, various overload data and wind resistance data of each point, and provides basic data for design and selection of various aircraft hanging frames. However, the data derived from theoretical calculation is basically taken as the design basis.
In summary, the flight data acquisition device provided by the invention can test six degrees of freedom of force in the flight state of an aircraft, namely axial force and torsion moment of an x axis, a y axis and a z axis; the method can test the rotation axis in the flying rolling process, the rotation axis is the key of theoretical calculation, and the difference between the actual and the theoretical can be determined through data analysis; the speed pressing piece can test real data of working conditions and can know the speed pressure distribution of the airplane in various speed states; the design of the speed pressing piece can determine the optimal windward section form of the airborne suspension device of various airplanes.
The foregoing has outlined rather broadly the more detailed description of the application in order that the detailed description thereof that follows may be better understood, and in order that the present application may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application.
Claims (8)
1. A flight data acquisition device, comprising: the shell, the cover plate, the two weight dumbbells, the quick-pressing piece, the main board and the weighing sensors,
The cover plate is fixedly connected with the shell to form a closed space;
The weighing sensors are all positioned in the closed space and fixed on the shell, 1 weighing sensor is positioned at the front part of the closed space and used for supporting the quick-press part, the other weighing sensors are divided into two groups, the weighing sensors in each group are electrically connected with the main board, the main board is used for reading and storing data acquired by the weighing sensors, and the real overload condition of each hanging point is determined through the data change of each weighing sensor in the flying process;
the quick pressing piece is positioned at the front end of the shell and is electrically connected with the first weighing sensor, the first weighing sensor is electrically connected with the main board, the quick pressing piece transmits wind resistance pressure to the first weighing sensor, the first weighing sensor transmits wind resistance pressure to the main board, and the first weighing sensor is positioned at the front part of the closed space;
The two weight dumbbells are placed in a staggered mode, five planes are arranged on each ball of the weight dumbbells, each plane is in contact with the sensing surface of the weighing sensor, and the weighing sensor is used for measuring pressure change of the weight dumbbells and transmitting measured data to the main board.
2. The device of claim 1, wherein the device comprises two main boards,
The rest weighing sensors are divided into two groups, and the weighing sensors in each group are electrically connected with a main board; each weighing sensor has an identifier for uniquely indicating the weighing sensor, the identifier of the weighing sensor corresponding to the corresponding motherboard interface.
3. The device of claim 1, wherein the housing is provided with mounting holes for fixedly connecting to the aircraft,
The inside of the shell is also provided with a plurality of weighing sensor bases, and each weighing sensor base is provided with a plurality of weighing sensor fixing holes for fixing one weighing sensor;
each of the two side surfaces of the shell is provided with a plurality of weighing sensor fixing holes for fixing a weighing sensor;
the front end of the shell is provided with a quick-pressing piece mounting hole for restraining the quick-pressing piece, so that the quick-pressing piece can only horizontally displace.
4. A device according to claim 3, wherein each weight dumbbell is formed by two balls and a connecting rod, the connecting rod is located between the two balls, a gap is formed in the middle of the connecting rod, the weight of the weight dumbbell is a multiple of 3, the balls and the connecting rod are equal in weight, and the ball spacing between the two weight dumbbell is constant.
5. The device of claim 4, wherein the main board comprises electrical components, a port for connection with an aircraft host, and a port for electrical connection with a load cell.
6. The device of claim 5, wherein the weighing sensor is provided with a weighing surface, a supporting surface, a mounting fixing hole and a data line interface, and the data line interface is electrically connected with the main board port through a data line; the weighing surface is contacted with a plane on the ball of the weight dumbbell; the supporting surface is fixedly arranged on the weighing sensor base or the side surface of the shell; the installation fixing hole is connected and fixed with a weighing sensor fixing hole arranged on the side face of the shell in a matched mode.
7. The device of claim 1, wherein the mounting direction of the flight data acquisition device is vertical or horizontal, and the direction data in each load cell data is marked according to the mounting direction of the flight data acquisition device.
8. The device according to claim 2, characterized in that a clock synchronization unit is arranged between the two main boards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111680287.3A CN114735231B (en) | 2021-12-30 | 2021-12-30 | Flight data acquisition device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111680287.3A CN114735231B (en) | 2021-12-30 | 2021-12-30 | Flight data acquisition device |
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| CN114735231A CN114735231A (en) | 2022-07-12 |
| CN114735231B true CN114735231B (en) | 2024-06-18 |
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Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NZ190374A (en) * | 1978-05-10 | 1982-08-17 | Res Analysis & Dev | Aircraft structure deflection measurement and detection |
| CN103175646B (en) * | 2010-07-19 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | The device of a kind of survey aircraft pedal power and brake weight and measuring method thereof |
| US9418705B2 (en) * | 2010-08-26 | 2016-08-16 | Blast Motion Inc. | Sensor and media event detection system |
| US9378601B2 (en) * | 2012-03-14 | 2016-06-28 | Autoconnect Holdings Llc | Providing home automation information via communication with a vehicle |
| EP2705935A1 (en) * | 2012-09-11 | 2014-03-12 | Hexagon Technology Center GmbH | Coordinate measuring machine |
| CN203479823U (en) * | 2013-08-26 | 2014-03-12 | 吴俊毅 | Sensor apparatus for measuring flow velocity |
| US11001379B2 (en) * | 2016-10-17 | 2021-05-11 | Robert Matthew Panas | Airborne data farming |
| US11566892B2 (en) * | 2016-10-27 | 2023-01-31 | Ohio University | Air data probe |
| KR20200037816A (en) * | 2017-08-02 | 2020-04-09 | 스트롱 포스 아이오티 포트폴리오 2016, 엘엘씨 | Methods and systems for detection in an industrial Internet of Things data collection environment with large data sets |
| KR20200090786A (en) * | 2017-10-27 | 2020-07-29 | 플루이더티 테크놀로지스 인코포레이티드 | Dynamically balanced multi-purpose handheld controller |
| CN108645425B (en) * | 2018-03-14 | 2022-03-08 | 东南大学 | Small-size rotor unmanned aerial vehicle gyroscope structure test system based on six-dimensional force sensor |
| CN110588980A (en) * | 2019-09-12 | 2019-12-20 | 南京奎道科技有限公司 | Plate-frame type module aviation hanger |
| CN110987284A (en) * | 2019-11-20 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | High-reliability full-embedded atmospheric data system for flying wing type airplane |
| GB2589920A (en) * | 2019-12-13 | 2021-06-16 | Skye Crew Ltd | Pressure altering surface for a dynamic pressure sensing apparatus |
| CN211954243U (en) * | 2020-04-11 | 2020-11-17 | 济南慧中灵恩电子科技有限公司 | Miniature multi-element data acquisition recorder |
-
2021
- 2021-12-30 CN CN202111680287.3A patent/CN114735231B/en active Active
Non-Patent Citations (2)
| Title |
|---|
| 内埋武器舱***气动特性研究;吴继飞;中国博士学位论文全文数据库 (工程科技Ⅱ辑);20140415;第C031-1页 * |
| 基于NI-CRIO的风洞模型姿态控制***数据采集设备研制;曹宇等;计算机测量与控制;20131031;第2878-2881页 * |
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