CN112325985B - A device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank - Google Patents
A device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank Download PDFInfo
- Publication number
- CN112325985B CN112325985B CN202011138932.4A CN202011138932A CN112325985B CN 112325985 B CN112325985 B CN 112325985B CN 202011138932 A CN202011138932 A CN 202011138932A CN 112325985 B CN112325985 B CN 112325985B
- Authority
- CN
- China
- Prior art keywords
- ultrasonic
- tank
- sidewall
- ultrasonic sensor
- signal
- 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
- 239000003380 propellant Substances 0.000 title claims abstract description 35
- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000007788 liquid Substances 0.000 claims abstract description 25
- 239000000446 fuel Substances 0.000 claims abstract description 20
- 230000005284 excitation Effects 0.000 claims description 22
- 238000005259 measurement Methods 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 4
- 230000001788 irregular Effects 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000001514 detection method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 206010028980 Neoplasm Diseases 0.000 description 2
- 201000011510 cancer Diseases 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
- 238000013507 mapping Methods 0.000 description 2
- 230000005486 microgravity Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000009774 resonance method Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000002604 ultrasonography Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F23/00—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
- G01F23/22—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
- G01F23/28—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring the variations of parameters of electromagnetic or acoustic waves applied directly to the liquid or fluent solid material
- G01F23/296—Acoustic waves
- G01F23/2962—Measuring transit time of reflected waves
Landscapes
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Electromagnetism (AREA)
- Thermal Sciences (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
- Measurement Of Levels Of Liquids Or Fluent Solid Materials (AREA)
Abstract
本申请提供一种在轨航天器贮箱推进剂剩余量测量装置及方法，包括顶部超声模块、侧壁超声模块、旋转机构、信号发生器、信号放大器、采集卡、多路切换开关及计算单元；旋转机构安装在贮箱顶部，顶部超声模块安装在旋转机构上；顶部超声模块包括一个顶部超声传感器；侧壁超声模块设在贮箱外壁上，侧壁超声模块包括多组超声单元，每组超声单元包括多个侧壁超声传感器，顶部超声传感器与各个侧壁超声传感器均设为收发一体型超声传感器；多路切换开关与顶部超声模块及侧壁超声模块信号连接。本申请的有益效果是：通过顶部超声模块测量贮箱内不规则液面燃料的体积，通过侧壁超声模块测量燃料内的气泡的体积及位置，从而得到贮箱内燃料的真实体积。
The present application provides a device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank, including a top ultrasonic module, a sidewall ultrasonic module, a rotating mechanism, a signal generator, a signal amplifier, an acquisition card, a multiplexer switch, and a computing unit The rotating mechanism is installed on the top of the tank, and the top ultrasonic module is installed on the rotating mechanism; the top ultrasonic module includes a top ultrasonic sensor; the sidewall ultrasonic module is arranged on the outer wall of the tank, and the sidewall ultrasonic module includes multiple groups of ultrasonic units, each group The ultrasonic unit includes a plurality of sidewall ultrasonic sensors, and the top ultrasonic sensor and each sidewall ultrasonic sensor are set as a transceiver-integrated ultrasonic sensor; the multi-way switch is signal-connected to the top ultrasonic module and the sidewall ultrasonic module. The beneficial effect of the present application is that the volume of the fuel with irregular liquid surface in the tank is measured by the top ultrasonic module, and the volume and position of the air bubbles in the fuel are measured by the side wall ultrasonic module, so as to obtain the real volume of the fuel in the tank.
Description
Technical Field
The disclosure relates to the technical field of on-orbit measurement and test of a spacecraft propulsion system, in particular to a device and a method for measuring the propellant surplus of an on-orbit spacecraft storage tank.
Background
With the ever-increasing on-orbit life of spacecraft, on-orbit life assessment and on-orbit fueling are becoming increasingly hot topics. However, a prerequisite for on-orbit life assessment and on-orbit refueling is accurate measurement of on-orbit spacecraft tank propellant residuals. These constraints require that the measurement method is not affected by the interface between gas and liquid in the tank, which is very complex due to the effect of microgravity. When the gas-liquid interface in the tank is obvious (the propulsion system performs accelerated propulsion), the traditional liquid level method can be applied to the measurement of the propellant residual quantity of the space tank. Research on a storage tank propellant residual quantity measuring technology in a microgravity environment starts as early as 60 s in the 20 th century, and a volume excitation method, a heat capacity method, an X-wave imaging method, an electromagnetic wave resonance method, an acoustic method and the like are successively proposed in addition to a traditional PVT method and a BK method. However, the BK method cannot adapt to the self-evaporation of the low-temperature propellant, the detection accuracy of the PVT method and the thermal capacitance method is not high, and the detection equipment of the X-wave imaging method and the electromagnetic wave resonance method is too complex to be applied in the orbit. Therefore, the acoustic detection method has certain advantages, the NASA Ames research center provides a method for measuring the residual quantity based on the acoustic resonance mode, and ground principle tests are carried out, but the method cannot detect large bubbles in liquid, so that the measured residual quantity is too much. The method for measuring the residual quantity based on sound wave reflection can solve the problem of measuring the residual quantity of the liquid propellant containing large bubbles in an on-orbit weightless state, and has a good application prospect.
Disclosure of Invention
The invention aims to solve the problems and provides a device and a method for measuring the propellant surplus of an in-orbit spacecraft storage tank.
In a first aspect, the application provides a device for measuring the propellant surplus of an in-orbit spacecraft storage tank, which comprises a top ultrasonic module, a side wall ultrasonic module, a rotating mechanism, a signal generator, a signal amplifier, an acquisition card, a multi-path selector switch and a calculating unit; the rotating mechanism is arranged at the top of the storage box, and the top ultrasonic module is arranged on the rotating mechanism; the top ultrasonic module comprises a top ultrasonic sensor; the side wall ultrasonic module is arranged on the outer wall of the storage box and comprises a plurality of groups of ultrasonic units, each group of ultrasonic units comprises a plurality of side wall ultrasonic sensors, and the top ultrasonic sensor and each side wall ultrasonic sensor are respectively arranged as a receiving-transmitting integrated ultrasonic sensor; all side wall ultrasonic sensors of each group of ultrasonic units are arranged along the axis direction of the storage tank at set intervals; each group of ultrasonic units are arranged along the circumferential direction of the storage box according to a set included angle; the multi-path change-over switch is in signal connection with the top ultrasonic module and the side wall ultrasonic module, and is in signal connection with the signal generator and the signal amplifier respectively; the signal amplifier is used for acquiring ultrasonic signals sent by the top ultrasonic module and the side wall ultrasonic module and sending the ultrasonic signals to the acquisition card, and the acquisition card is used for sending the received signals to the computing unit for computing.
According to the technical scheme provided by the embodiment of the application, the beam angle of the top ultrasonic sensor is set to be larger than 60 degrees.
According to the technical scheme provided by the embodiment of the application, the set distance range is 20cm-30 cm.
According to the technical scheme provided by the embodiment of the application, the degree of the set included angle is 45 degrees or 60 degrees.
According to the technical scheme provided by the embodiment of the application, the rotating mechanism is used for performing 360-degree circumferential rotation and 180-degree pitching rotation on the top sensing module.
According to the technical scheme provided by the embodiment of the application, each side wall ultrasonic sensor is pasted on the outer wall of the storage box.
According to the technical scheme provided by the embodiment of the application, the top ultrasonic sensor is installed on the rotating mechanism through a screw.
According to the technical scheme provided by the embodiment of the application, the rotating mechanism is arranged at the joint of the liquid inlet pipe and the storage tank.
In a second aspect, the application provides a method for measuring the residual quantity of a propellant in a storage tank of an in-orbit spacecraft, which comprises the following steps:
(1) adjusting the rotating mechanism to make the included angle between the rotating mechanism and the liquid inlet pipe of the storage tank be thetai(0°≤θi≤360°)，ti1At the moment, a pulse excitation signal is sent to the top ultrasonic sensor by the signal generator through the multi-way selector switch, the ultrasonic signal is reflected when encountering the fuel liquid level in the storage tank, the returned ultrasonic wave is received by the top ultrasonic sensor, and the returned receiving moment t is recordedi2；
(2) Calculating thetaiDistance of the top ultrasonic sensor from the liquid level of the fuel in the storage tank at the angle:
wherein c is the speed of sound of ultrasonic waves in air;
(3) and calculating the volume of the residual amount of the propellant of the storage tank as follows:
wherein VPot for storing foodThe total volume of the tank body of the storage tank, s is the cross section area of the storage tank, and n is the measurement times;
(4) sending a pulse excitation signal to the side wall ultrasonic sensor i by using the signal generator through the multi-way selector switch to be used as an excitation sensor, and receiving the ultrasonic signal sent by the side wall ultrasonic sensor i by using each side wall ultrasonic sensor j of other groups outside the group where the side wall ultrasonic sensor i is located as a receiving sensor to obtain a signal Si，jAnd recording the reception time ti,jAccording to the linear distance d between the side wall ultrasonic sensor i and the side wall ultrasonic sensor ji,jCalculating the wave speed of the i-j channel signal:
(5) to thereby
Plotting a gray scale as pixel intensity and mapping each sidewall ultrasonic sensor i to
Superposing the gray level graphs to obtain the position and the diameter of the air bubble in the fuel with the current section;
(6) and (5) repeating the steps (4) to (5), so that all the side wall ultrasonic sensors of the side wall ultrasonic module traverse to be used as excitation sensors to obtain the positions and diameters of bubbles in all the sections, and calculating the total volume V of the bubbles in the fuel in the storage tankBubble；
(7) Calculating the real volume of the residual amount of the propellant of the storage tank: vSolid preparation＝VAgent for treating cancer-VBubble。
The invention has the beneficial effects that: the application provides a device and a method for measuring propellant surplus in a storage tank of an on-orbit spacecraft, wherein the position of an irregular liquid level in the storage tank is detected through a top ultrasonic module, so that the volume of propellant fuel in the storage tank is obtained through calculation, the volume and the position of bubbles in the propellant fuel in the storage tank are measured through a side wall ultrasonic module, the actual volume of the fuel in the storage tank is obtained by subtracting the volume of the bubbles from the fuel volume measured at the liquid level position, and the propellant surplus in the storage tank of the spacecraft is more accurately calculated and obtained.
Drawings
FIG. 1 is a schematic structural diagram of a first embodiment of the present application;
FIG. 2 is a flow chart of a second embodiment of the present application;
FIG. 3 is a schematic illustration of a grayscale overlay according to a second embodiment of the present application;
the text labels in the figures are represented as: 1. a top ultrasonic sensor; 2. a sidewall ultrasonic sensor; 3. a rotation mechanism; 4. a signal generator; 5. a signal amplifier; 6. collecting cards; 7. a multi-way selector switch; 8. a calculation unit; 9. a propellant; 10. air bubbles.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the following detailed description of the present invention is provided in conjunction with the accompanying drawings, and the description of the present section is only exemplary and explanatory, and should not be construed as limiting the scope of the present invention in any way.
Fig. 1 is a schematic diagram of a first embodiment of the present application, which includes a top ultrasonic module, a sidewall ultrasonic module, a rotating mechanism 3, a signal generator 4, a signal amplifier 5, an acquisition card 6, a multi-way switch 7 and a computing unit 8; the rotating mechanism 3 is arranged at the top of the storage box, and the top ultrasonic module is arranged on the rotating mechanism 3; the top ultrasonic module comprises a top ultrasonic sensor 1; the side wall ultrasonic module sets up on the outer wall of storage tank, and side wall ultrasonic module includes multiunit supersound unit, and every group supersound unit includes a plurality of lateral wall ultrasonic sensor 2, top ultrasonic sensor 1 all sets up to receiving and dispatching integral type ultrasonic sensor with each lateral wall ultrasonic sensor 2. Preferably, each of the side wall ultrasonic sensors 2 is adhered to the outer wall of the tank by 914 adhesive.
In this embodiment, the top ultrasound module is used to measure the position of each collection point in the irregular surface of the liquid level in the tank, and the sidewall ultrasound module is used to detect the position and volume of the bubble 10 in the liquid in the tank.
The ultrasonic sensors 2 on the side walls of each group of ultrasonic units are arranged at set intervals along the axial direction of the storage tank; each group of ultrasonic units are arranged along the circumferential direction of the storage box according to a set included angle; the multi-path selector switch 7 is in signal connection with the top ultrasonic module and the side wall ultrasonic module, and the multi-path selector switch 7 is in signal connection with the signal generator 4 and the signal amplifier 5 respectively; the signal generator 4 is used for sending an excitation source to the top ultrasonic module and the side wall ultrasonic module, the signal amplifier 5 is used for collecting ultrasonic signals sent by the top ultrasonic module and the side wall ultrasonic module and sending the ultrasonic signals to the collecting card 6, and the collecting card 6 is used for sending the received signals to the calculating unit 8 for calculation.
In this embodiment, each sidewall ultrasonic sensor 2 is a group of ultrasonic units arranged along the axial direction of the storage tank, and two adjacent groups of ultrasonic units are arranged according to a set included angle. The multi-way switch 7 is used for switching between the signal generator 4 and the signal amplifier 5 and the top ultrasonic sensor 1 or each side wall ultrasonic sensor 2.
In a preferred embodiment, the beam angle of the top ultrasonic sensor 1 is set to be greater than 60 °, and the rotating mechanism 3 is used for performing 360 ° circumferential rotation and 180 ° pitch rotation on the top sensing module. In the preferred embodiment, the top ultrasonic sensor 1 is installed on the rotating mechanism 3 through a screw, the rotating mechanism 3 is installed at the joint of a liquid inlet pipe and a storage tank, the rotating mechanism 3 drives the top ultrasonic sensor 1 to perform 360-degree circumferential rotation and 180-degree pitching rotation, and the top ultrasonic sensor 1 is matched with the beam angle setting of the top ultrasonic sensor 1, so that the top ultrasonic sensor 1 can realize full-scanning coverage on the space in the storage tank, the volume of the residual amount of the propellant 9 in the storage tank can be accurately calculated according to the position of each acquisition point obtained by the top ultrasonic sensor 1, and the volume contains the volume of the bubbles 10, so that the residual amount of the propellant 9 in the storage tank calculated by the top ultrasonic sensor 1 is larger than the true value.
In a preferred embodiment, the set distance range is 25 cm. In the preferred embodiment, the distance between the adjacent sidewall ultrasonic sensors 2 in each group of ultrasonic units is 25cm, and in other preferred embodiments, the distance between the adjacent sidewall ultrasonic sensors 2 in each group of ultrasonic units can also be set to be 20cm, 30cm or any value within the range of 20cm-30 cm.
In a preferred embodiment, the set angle is 45 °. In the preferred embodiment, the horizontal included angle of two adjacent groups of ultrasonic units on the same horizontal plane is 45 °, and in other preferred embodiments, the set included angle degree can also be set to be 60 °.
Fig. 2 is a flowchart illustrating a second embodiment of the present application, and the present embodiment is a method for measuring remaining capacity by using the measuring device of the first embodiment, and the method includes the following steps:
s1, adjusting the rotating mechanism to make the included angle between the rotating mechanism and the liquid inlet pipe of the storage tank be thetai(0°≤θiLess than or equal to 360 degrees, through a multi-way change-over switch ti1At any moment, a signal generator is utilized to send a pulse excitation signal to the top ultrasonic sensor, the ultrasonic signal is reflected when encountering the fuel liquid level in the storage tank, the top ultrasonic sensor receives the returned ultrasonic wave, and the returned receiving moment t is recordedi2。
In the step, the top ultrasonic sensor is connected with the signal generator and the signal amplifier through the multi-way selector switch, the signal generator sends a pulse excitation signal to the top ultrasonic sensor to excite a section of ultrasonic wave, the ultrasonic wave is reflected when meeting the liquid level, and the top ultrasonic sensor receives the ultrasonic waveThe echo after the ultrasonic wave reaches the fuel liquid level is transmitted to a computing unit through a signal amplifier, and the computing unit records the echo receiving time ti2。
S2, calculating thetaiDistance of the top ultrasonic sensor from the liquid level of the fuel in the storage tank at the angle:
where c is the speed of sound of the ultrasonic waves in air.
In this step, the calculation unit is based on ti1And ti2And calculating the distance from the top ultrasonic sensor to the liquid level of the storage tank at the angle.
S3, calculating the volume of the residual amount of the storage tank propellant as follows:
wherein VPot for storing foodIs the total volume of the tank body of the storage tank, s is the cross section area of the storage tank, and n is the measurement times.
In this embodiment, the rotating mechanism drives the top ultrasonic sensor to rotate 360 degrees in the circumferential direction and 180 degrees in the pitch direction, so that the top ultrasonic sensor can fully scan the liquid level of the storage tank, and the distance d between the top ultrasonic sensor and the liquid level is acquired at each angleiAre accumulated by a formula
The volume of propellant remaining in the reservoir containing the volume of bubbles can be calculated.
S4, sending a pulse excitation signal to the side wall ultrasonic sensor i as an excitation sensor by using the signal generator through the multi-way selector switch, and receiving the ultrasonic signal sent by the side wall ultrasonic sensor i by using each side wall ultrasonic sensor j of other groups except the group where the side wall ultrasonic sensor i is located as a receiving sensor to obtain a signal Si，jAnd recording the reception time ti,jAccording to the linear distance d between the side wall ultrasonic sensor i and the side wall ultrasonic sensor ji,jCalculating the wave speed of the i-j channel signal:
in this step, the multi-way switch connects the sidewall ultrasonic sensor i with the signal generator, so that the signal generator sends a pulse excitation signal to the sidewall ultrasonic sensor i to make the pulse excitation signal act as an excitation sensor, each sidewall ultrasonic sensor j in the other groups of ultrasonic units outside the group where the sidewall ultrasonic sensor i is located is respectively used as a receiving sensor, receives ultrasonic waves sent by the sidewall ultrasonic sensor i, and records the received signal as Si，jAnd recording the reception time ti,jDue to the linear distance d between the ultrasonic sensor i and the ultrasonic sensor ji,jMust be and are known, so that the calculating unit is based on the formula
The signal transmission speed between the side wall ultrasonic sensor i and the side wall ultrasonic sensor j can be calculated.
S5, and
plotting a gray scale as pixel intensity and mapping each sidewall ultrasonic sensor i to
And overlapping the gray-scale maps to obtain the position and the diameter of the bubbles in the fuel at the current section.
S6, repeating the steps S4 to S5, enabling each side wall ultrasonic sensor of the side wall ultrasonic module to traverse to be used as an excitation sensor, obtaining the position and the diameter of the bubbles in each section, and calculating the total volume V of the bubbles in the fuel in the storage tankBubble. Fig. 3 is a schematic diagram showing the principle of superposition when two side-wall ultrasonic sensors are respectively used as excitation sensors.
Repeating the steps S4 to S5 until all the side wall ultrasonic sensors traverse as excitation sensors and all the side wall ultrasonic sensors are used as the excitation ultrasonic sensors to obtain ci,jDrawing and superposing gray level maps to obtain the position and volume V of the air bubble in the liquid in the space rangeBubble。
S7, calculating the actual volume of the residual amount of the storage tank propellant: vSolid preparation＝VAgent for treating cancer-VBubble。
The principles and embodiments of the present application are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present application, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its spirit and scope, as defined by the claims, may be directed to other uses and embodiments, or may be learned by practice of the invention.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011138932.4A CN112325985B (en) | 2020-10-22 | 2020-10-22 | A device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011138932.4A CN112325985B (en) | 2020-10-22 | 2020-10-22 | A device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112325985A CN112325985A (en) | 2021-02-05 |
| CN112325985B true CN112325985B (en) | 2021-09-07 |
Family
ID=74311418
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011138932.4A Active CN112325985B (en) | 2020-10-22 | 2020-10-22 | A device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112325985B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09229748A (en) * | 1996-02-28 | 1997-09-05 | Yazaki Corp | Ultrasonic liquid level sensor |
| US5793705A (en) * | 1996-09-18 | 1998-08-11 | International Business Machines Corporation | Ultrasonic liquid level gauge for tanks subject to movement and vibration |
| CN103674181A (en) * | 2013-12-04 | 2014-03-26 | 江苏大学 | Dynamic liquid level ultrasonic detection device and method |
| CN111505648A (en) * | 2020-04-25 | 2020-08-07 | 西安交通大学 | Space coding ultrasonic array ultrafast detection and positioning system and method |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5774469B2 (en) * | 2011-12-28 | 2015-09-09 | 株式会社東芝 | Liquid level measuring device, method and program |
| CA2987851A1 (en) * | 2015-06-01 | 2016-12-08 | Cetamax Ventures Ltd. | Systems and methods for processing fluids |
-
2020
- 2020-10-22 CN CN202011138932.4A patent/CN112325985B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09229748A (en) * | 1996-02-28 | 1997-09-05 | Yazaki Corp | Ultrasonic liquid level sensor |
| US5793705A (en) * | 1996-09-18 | 1998-08-11 | International Business Machines Corporation | Ultrasonic liquid level gauge for tanks subject to movement and vibration |
| CN103674181A (en) * | 2013-12-04 | 2014-03-26 | 江苏大学 | Dynamic liquid level ultrasonic detection device and method |
| CN111505648A (en) * | 2020-04-25 | 2020-08-07 | 西安交通大学 | Space coding ultrasonic array ultrafast detection and positioning system and method |
Non-Patent Citations (1)
| Title |
|---|
| 《一种用于超声波检漏探头激励的任意波形发生器》;綦磊等;《电子测量技术》;20170831;第40卷(第8期);90-93 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112325985A (en) | 2021-02-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110609287B (en) | Double-frequency radar scatterometer and method for simultaneously measuring sea surface wind field and flow field | |
| CN103189719B (en) | For the method for the acoustic characteristic of the fluid of non-intrusion type determination pipe interior | |
| CN110146895A (en) | Inversion Method of Sound Velocity Profile Based on Inverted Multi-beam Echometer | |
| US20230061816A1 (en) | Air-coupled Ultrasonic Detection Method and Device Based on Defect Probability Reconstruction Algorithm | |
| CN101097161A (en) | Device for ultrasonic measuring liquid level and method thereof | |
| CN111189922B (en) | Three-dimensional visual detection method and device for sleeve grouting compactness | |
| CN102288781A (en) | Reflective ultrasonic anemoscope and measuring method thereof | |
| CN110045019A (en) | A kind of thin plate Air Coupling ultrasonic Lamb waves total focus imaging detection method | |
| CN103499374B (en) | A kind of ultrasound wave dynamic liquid level detection method based on neutral net and system | |
| CN110261485A (en) | A kind of ultrasonic measurement material internal method of elasticity modulus and Poisson's ratio everywhere | |
| CN100520441C (en) | Phase measuring system of 8-element ultrashort base positioning system and calibration thereof | |
| CN105158339A (en) | Longitudinal and transverse wave integrated ultrasonic probe as well as testing system and method of elastic modulus and distribution | |
| CN103837608A (en) | Method and system for receiving dynamic focusing compensation through phased array | |
| CN105842477A (en) | Current surveying method by means of acoustic Doppler current meter | |
| CN102697524B (en) | Full-focus ultrasonic imaging method and application of method in blood flow imaging | |
| CN103018481A (en) | Three-dimensional ultrasonic wind meter with temperature correction and measurement method thereof | |
| US6028547A (en) | Method and device for processing signals representative of waves reflected, transmitted or refracted by a volume structure with a view to exploring and analyzing this structure | |
| CN110836981A (en) | Layered water flow high-resolution radial acoustic Doppler frequency measurement method | |
| CN114088972B (en) | Ultrasonic wind speed and direction measurement system and method based on phase double-frequency method | |
| CN109490906A (en) | A kind of boat-carrying wave dynamic measurement device based on laser radar | |
| BRPI0010911B1 (en) | process for measuring thickness distribution of material to be measured over a selected continuous area of an object, and apparatus for performing global measurement of thickness distribution in material of an object to be measured over a chosen continuous area | |
| CN108363063A (en) | A kind of posture and the parallel multimetering method and apparatus of the self-alignment ultrasound of velocity of wave | |
| CN112162036B (en) | A equilateral triangle phased array bolt fastening structure health monitoring system and method | |
| CN112325985B (en) | A device and method for measuring the remaining amount of propellant in an on-orbit spacecraft tank | |
| CN111880185A (en) | Underwater target surveying processing method and system |
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 |