CN106289627B - A kind of air cushion pressure monitoring method of aircushion vehicle - Google Patents

A kind of air cushion pressure monitoring method of aircushion vehicle Download PDF

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Publication number
CN106289627B
CN106289627B CN201610824920.4A CN201610824920A CN106289627B CN 106289627 B CN106289627 B CN 106289627B CN 201610824920 A CN201610824920 A CN 201610824920A CN 106289627 B CN106289627 B CN 106289627B
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air pressure
hovercraft
value
pressure value
primary
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CN106289627A (en
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陈得民
杨素军
高嵩
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BEIJING WILL CREATE TECHNOLOGY Co Ltd
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BEIJING WILL CREATE TECHNOLOGY Co Ltd
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01LMEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L17/00Devices or apparatus for measuring tyre pressure or the pressure in other inflated bodies
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B60VEHICLES IN GENERAL
    • B60VAIR-CUSHION VEHICLES
    • B60V3/00Land vehicles, waterborne vessels, or aircraft, adapted or modified to travel on air cushions
    • B60V3/06Waterborne vessels

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Measuring Fluid Pressure (AREA)

Abstract

The invention discloses a kind of air cushion pressure monitoring methods of aircushion vehicle, comprising: multiple pressure sensors is equably arranged in the hull bottom of the aircushion vehicle, to measure the atmospheric pressure value of the hull bottom everywhere;For do not arrange the pressure sensor position and damage and the pressure sensor position of atmospheric pressure value measurement can not be carried out, use compensation pressure to calculate to obtain corresponding atmospheric pressure value;According to hull bottom everywhere measured atmospheric pressure value calculate hull bottom each section air pressure average value and entire hull bottom air pressure average value;According to the air pressure average value of hull bottom each section and the air pressure average value of entire hull bottom, the degree of stability of the aircushion vehicle is judged.The present invention equably arranges the atmospheric pressure value of multiple pressure sensors everywhere with surveying vessel bottom in the hull bottom of aircushion vehicle, and then can get the atmospheric pressure value of entire hull bottom any position by compensation calculation in the way of, so as to the timely quick obtaining aircushion vehicle hull bottom pressure condition of part and entirety everywhere.

Description

Air cushion pressure monitoring method for hovercraft
Technical Field
The invention relates to the field of ship detection, in particular to a method for monitoring air cushion pressure of a hovercraft.
Background
The hovercraft is a ship which uses high-pressure air to form an air cushion between the bottom of the ship and the water surface (or the ground) to lift all or part of the ship body, thereby greatly reducing the resistance of the ship body during navigation and realizing high-speed navigation. The air cushion is formed by pressing air into the bottom of the ship by a high-power blower and limiting the air to escape by an air sealing device such as a flexible apron or a rigid side wall around the bottom of the ship.
The air pressure in the air cushion, i.e. the air pressure, thus plays a crucial role in the stability of the hovercraft.
The hull structure of the hovercraft is complex, the movement speed is extremely fast, and various running states of the hull need to be monitored during design, running and maintenance, particularly the air pressure in the air cushion, so as to ensure the balance of the hull.
For monitoring the air pressure in the air cushion, the most traditional monitoring mode is manual monitoring, but for the hovercraft with a complex structure and extremely high movement speed, the manual monitoring precision is low, the real-time observation is inconvenient, each part needing to be monitored is respectively positioned at different parts of the hovercraft, and the data at each part can not be simultaneously obtained in the manual monitoring process.
Disclosure of Invention
In view of the above, the present invention provides a method for monitoring an air cushion pressure of a hovercraft, which is used for monitoring an air pressure value in an air cushion of the hovercraft in real time, and further feeding back the air pressure in the air cushion in real time, so that potential safety hazards can be found in time, and the potential safety hazards can be avoided.
The technical scheme of the invention is realized as follows:
a method of monitoring cushion pressure of a hovercraft, comprising:
uniformly arranging a plurality of pressure sensors at the bottom of the hovercraft to measure air pressure values at all positions of the bottom of the hovercraft;
adopting compensation pressure calculation to obtain a corresponding air pressure value for the position where the pressure sensor is not arranged and the position where the pressure sensor which is damaged and cannot measure the air pressure value is located;
calculating the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom according to the measured air pressure values of all parts of the ship bottom;
and judging the stability of the hovercraft according to the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom.
Further, the evenly arranging the plurality of pressure sensors at the bottom of the hovercraft comprises:
dividing the bottom of the hovercraft into four primary areas according to the center line;
dividing each primary area into four small areas according to the central line;
repeating the division mode, and dividing each small area for multiple times, so as to divide the ship bottom of the hovercraft into a plurality of equal basic square areas;
a plurality of pressure sensors are arranged at the four corners of all substantially square areas.
Further, for a location where the pressure sensor is not disposed, a compensation pressure calculation is employed to obtain a corresponding air pressure value, including obtaining using the following formula:
p(1,2)=(p1+p2)/2
p(1,3)=(p1+p3)/2
p(3,4)=(p3+p4)/2
p(2,4)=(p2+p4)/2
wherein,
p1is the air pressure value at one angular position in the substantially square region;
p2is the sum of p in the substantially square region1A pressure value at an angular position adjacent to the angular position;
p3is the sum of p in the substantially square region1A value of air pressure at another angular position adjacent to the angular position;
p4is the sum of p in the substantially square region1The air pressure value at the opposite angular position at that angular position;
p(1,2)is p1At position and p2A pressure value at a midpoint position between the positions;
p(1,3)is p1At position and p3A pressure value at a midpoint position between the positions;
p(3,4)is p3At position and p4A pressure value at a midpoint position between the positions;
p(2,4)is p2At position and p4A pressure value at a midpoint position between the positions;
is the air pressure value at the center position of the substantially square area;
is composed of p1At position p(1,2)At position p(1,3)At the position andthe air pressure value at the central position of the square area formed by the position of the air compressor;
is composed of p(1,2)At position p2At position p(2,4)At the position andthe air pressure value at the central position of the square area formed by the position of the air compressor;
is composed of p3At position p(1,3)At position p(3,4)At the position andthe air pressure value at the central position of the square area formed by the position of the air compressor;
is composed of p4At position p(2,4)At position p(3,4)At the position andthe air pressure value at the central position of the square area formed by the position.
Further, to damaging and can't carry out the pressure sensor position that the atmospheric pressure value measured, adopt the compensation pressure to calculate in order to obtain corresponding atmospheric pressure value, include:
and (3) averaging the air pressure values of four adjacent pressure sensors at the position of the pressure sensor which is damaged and can not measure the air pressure value by adopting a principle of proximity, and taking the average as the air pressure value at the position of the pressure sensor which is damaged and can not measure the air pressure value.
Further, calculating the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom according to the measured air pressure values of all parts of the ship bottom, and the method comprises the following steps:
the average air pressure values of four primary areas at the bottom of the hovercraft are obtained by adopting the following formula:
wherein,
is the air pressure value at the center position of the ith substantially square area in the primary area a,
is the air pressure value at the center position of the ith substantially square area in the primary area B,
is the air pressure value at the center position of the ith substantially square area in the primary area C,
is the air pressure value at the center position of the ith substantially square area in the primary area D,
is the average air pressure value of the primary region a,is the average air pressure value of the primary region B,is the average air pressure value of the primary region C,is the average air pressure value of the primary region D,
n is the number of substantially square regions in each primary region, i is an integer from 1 to N,
the primary area A, the primary area B, the primary area C and the primary area D are four primary areas;
and acquiring the average value of the air pressure of the whole ship bottom of the hovercraft by adopting the following formula:
wherein,is the average value of the air pressure of the whole ship bottom of the hovercraft.
Further, the step of judging the stability of the hovercraft according to the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom comprises the following steps:
determining the four primary zone average barometric pressure deviations according to the following formula:
wherein,
SAis the average degree of deviation of the air pressure in the primary region a,
SBis the average degree of deviation of the air pressure of the primary region B,
SCis the average degree of deviation of the air pressure in the primary region C,
SDis the average barometric deviation of the primary region D;
setting an instability grade threshold value of the hull of the hovercraft when S isA、SB、SC、SDAnd when any one of the unstable levels reaches the unstable level threshold value, judging that the hovercraft is unstable, and reporting the unstable level.
Further, setting an instability grade threshold value of the hovercraft hull when S is reachedA、SB、SC、SDWhen any one of the items reaches the instability level threshold value, judging that the hovercraft is unstable,and reporting the instability level, including:
setting an unstable grade threshold of a hull of the hovercraft to be three levels, namely an unbalanced grade threshold, a serious grade threshold and a ship-stopping maintenance grade threshold;
when S isA、SB、SC、SDIf any one item reaches the threshold value of the ship stopping overhaul level, reporting the ship stopping overhaul level;
when S isA、SB、SC、SDIf any one item reaches the severity level threshold and is smaller than the ship stopping overhaul level threshold, reporting the severity level;
when S isA、SB、SC、SDIf any of the terms reaches the imbalance level threshold and is less than the severity level threshold, an imbalance level is reported.
Further, setting an instability grade threshold value of the hovercraft hull when S is reachedA、SB、SC、SDWhen any one of the parameters reaches the instability level threshold value, judging that the hovercraft is unstable, and reporting the instability level, wherein the instability level comprises the following steps:
setting an unstable grade threshold of a hull of the hovercraft to be three levels, namely an unbalanced grade threshold, a serious grade threshold and a ship-stopping maintenance grade threshold;
the imbalance level threshold is 3%;
the severity level threshold is 5%;
the ship stopping overhaul grade threshold value is 8%.
Further, when S isA、SB、SC、SDAnd when the stability level is not greater than the instability level threshold, reporting that the hull of the hovercraft is stable.
According to the scheme, the method for monitoring the air cushion pressure of the hovercraft comprises the steps of uniformly arranging the pressure sensors at the bottom of the hovercraft to measure the air pressure values at all positions of the bottom of the hovercraft, obtaining the air pressure value at any position of the whole bottom of the hovercraft in a compensation calculation mode, timely and quickly obtaining the local and overall pressure conditions at all positions of the bottom of the hovercraft, and timely feeding back when the air pressure value changes excessively in a certain area. The invention realizes that the pressure values at all positions at the bottom of the whole hovercraft are obtained by measuring and calculating each discrete point, so that the hovercraft can check the pressure condition of the hovercraft in the process of sailing, the trouble of manual inspection is avoided, and the danger of the hovercraft in the process of sailing is avoided.
Drawings
Fig. 1 is a structural view of an air cushion pressure monitoring apparatus of a hovercraft according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a panel of an air cushion pressure monitoring device of a hovercraft according to an embodiment of the present invention;
FIG. 3 is a flow chart of a method for monitoring cushion pressure of a hovercraft, in accordance with an embodiment of the present invention;
FIG. 4 is a schematic diagram of the arrangement distribution of pressure sensors in an embodiment of the present invention;
FIG. 5 is a schematic illustration of a compensated pressure calculation for a substantially square area in an embodiment of the present invention;
fig. 6 is a schematic diagram of an alarm interface in an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and examples.
As shown in fig. 1, the air cushion pressure monitoring apparatus of a hovercraft according to the embodiment of the present invention includes a pressure sensor 101 and a control and data processing unit 102. The number of the pressure sensors 101 is multiple, and the multiple pressure sensors 101 are uniformly arranged at the bottom of the hovercraft to measure the air pressure value at all positions of the bottom. The control and data processing unit 102 controls the pressure sensor 101 to be turned on and off, receives the air pressure value measured by the pressure sensor 101, and calculates air pressure distribution data of the bottom of the hovercraft according to the received air pressure value.
In the embodiment of the invention, the pressure sensor 101 is a wireless pressure sensor, so that the trouble of wiring on the hull of the hovercraft can be saved, and the trouble of overhauling can be avoided. In order to cooperate with the wireless pressure sensor, in the present invention, the air cushion pressure monitoring apparatus of the hovercraft further includes a wireless communication unit 103, the wireless communication unit 103 is electrically connected to the control and data processing unit 102, and the wireless communication unit 103 wirelessly communicates with the pressure sensor 101, that is, the wireless pressure sensor, so that the control and data processing unit 102 controls the pressure sensor 101 to be turned on and off and receives the air pressure value measured by the pressure sensor 101 through the wireless communication unit 103.
In the embodiment of the present invention, the air cushion pressure monitoring apparatus of the hovercraft further includes a storage unit 104, and the storage unit 104 is electrically connected to the control and data processing unit 102 to store the air pressure value and the air pressure distribution data.
In order that the ground station can timely receive the state of the hovercraft during driving, the hovercraft monitoring device according to the embodiment of the invention needs to provide a function of information interaction with the ground station, and further comprises a satellite communication unit 105, wherein the satellite communication unit 105 is electrically connected to the control and data processing unit 102 and performs data communication with the ground monitoring station through a satellite. Correspondingly, the control and data processing unit 102 transmits the air pressure value and the air pressure distribution data to the ground monitoring station through the satellite communication unit.
In addition, for the convenience of viewing and control, the hovercraft air cushion pressure monitoring device further comprises a display screen 106 and a data acquisition control key 107. The display screen 106 is electrically connected to the control and data processing unit 102 to display the air pressure value and the air pressure distribution data. The data acquisition control key 107 is electrically connected to the control and data processing unit 102 to instruct the control and data processing unit 102 to control the on and off of the pressure sensor 101 and perform the acquisition of the air pressure value and the calculation of the air pressure distribution data.
In the present invention, the air cushion pressure monitoring apparatus of the hovercraft further includes a USB interface 108, the USB interface 108 is electrically connected to the control and data processing unit 102, and the USB interface 108 can be connected to an external device, so that the control and data processing unit 102 performs data transmission with the external device through the USB interface 108, for example, the air pressure value and the air pressure distribution data are transmitted to the external device through the USB interface 108, or a calculation program is obtained from the external device through the USB interface 108.
In addition, in order to report the air pressure state of the hovercraft more intuitively and simply, the air pressure monitoring device of the hovercraft further comprises a state indicating unit 109, wherein the state indicating unit 109 is electrically connected to the control and data processing unit 102, and the control and data processing unit 102 indicates the air pressure monitoring state of the hovercraft through the state indicating unit 109. In the embodiment of the present invention, the status indication unit 109 includes a status indicator light and a buzzer.
In the embodiment of the present invention, a power management unit (not shown in the figure) is further included, and is used for supplying power to each unit. In order to master the position information of the hovercraft at any time, in the embodiment of the present invention, a GPS unit may be further added, and the GPS unit is electrically connected to the control and data processing unit 102 to obtain the current position of the hovercraft, so that the control and data processing unit 102 may combine and store the current position of the hovercraft, the current barometric pressure value, and the barometric pressure distribution data, and further may provide a hand of data for later data collection, analysis, and diagnosis.
Fig. 2 shows a control panel layout of an embodiment of an air cushion pressure monitoring device panel of a hovercraft, although other layouts may be used. As shown in fig. 2, the control panel has a housing 201, and the display screen 106, the switch button 202, the acquisition control button 203, the wireless control button 204, the wireless communication unit antenna 205, the satellite communication unit antenna 206, the status indicator lamp 207, the buzzer 208, the USB interface 108 and the power supply interface 209 are all mounted on the panel, so that the whole panel is very simple and easy to operate and monitor.
In order to be able to obtain the barometric pressure information of the entire bottom and the respective local portions of the hovercraft, a plurality of pressure sensors 101 need to be arranged elaborately on the bottom of the hovercraft. In the embodiment of the present invention, the pressure sensors 101 are symmetrically arranged at the bottom of the hovercraft, so that the air pressure value at each position of the bottom of the hovercraft can be obtained in a manner.
According to the device for monitoring the air cushion pressure of the hovercraft, the plurality of pressure sensors are uniformly arranged at the bottom of the hovercraft to measure the air pressure values at all positions of the bottom of the hovercraft, the air pressure values at all positions of the bottom of the hovercraft can be monitored and calculated in real time in the running process of the hovercraft, if the air pressure values at all positions of the bottom of the hovercraft are not uniform, an alarm can be given in time, and further dangers can be avoided.
An embodiment of the present invention further provides a method for monitoring an air cushion pressure of a hovercraft, as shown in fig. 3, including:
step 1, uniformly arranging a plurality of pressure sensors at the bottom of the hovercraft to measure the air pressure value at each position of the bottom of the hovercraft;
step 2, adopting compensation pressure calculation to obtain a corresponding air pressure value for the position where the pressure sensor is not arranged and the position where the pressure sensor which is damaged and cannot measure the air pressure value is located;
step 3, calculating the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom according to the measured air pressure values of all parts of the ship bottom;
and 4, judging the stability of the hovercraft according to the average air pressure value of each part of the bottom of the hovercraft and the average air pressure value of the whole bottom of the hovercraft.
Wherein the uniformly arranging the plurality of pressure sensors at the bottom of the hovercraft in step 1 comprises:
dividing the bottom of the hovercraft into four primary areas according to the center line;
dividing each primary area into four small areas according to the central line;
repeating the division mode, and dividing each small area for multiple times, so as to divide the ship bottom of the hovercraft into a plurality of equal basic square areas;
a plurality of pressure sensors are arranged at the four corners of all substantially square areas.
For example, as shown in fig. 4, in the embodiment of the present invention, the bottom of the hovercraft is divided into four primary regions, which are a region a, a region B, a region C, and a region D, according to a center line; for the area a, the area a is divided into four small areas according to the central line, namely an area a1, an area a2, an area A3 and an area a4, and the area B, the area C and the area D are also divided in the same way, and are not described again in the following; by repeating the above division, the region a1 is divided into the region a11, the region a12, the region a13, and the region a14 again, the region B1 is divided into the region B11, the region B12, the region B13, and the region B14 again, the region C1 is divided into the region C11, the region C12, the region C13, and the region C14 again, and the region D1 is divided into the region D11, the region D12, the region D13, and the region D14 again, and the division may be further performed a plurality of times.
A plurality of pressure sensors are arranged at four corners of all the substantially square regions, as shown by the black dots in fig. 4, one pressure sensor is arranged at each of the four corners of each substantially square region, and for any one substantially square region, there are at least three adjacent substantially square regions, so that the four corners of each substantially square region share one pressure sensor with the corresponding corner of each adjacent substantially square region, for example, for the region a14 in fig. 4, the upper left corner thereof is adjacent to the region a11, the region a12 and the region a13, and then the pressure sensor at the upper left corner of the region a14 is also the lower right corner of the region a11, the lower left corner of the region a12 and the upper right corner of the region a 13.
As shown in fig. 5, which is a substantially square area, in the present invention, the air pressure value at any point of the bottom of the ship is obtained by the following method, that is, in step 2, for the position where the pressure sensor is not arranged, the compensation pressure calculation is used to obtain the corresponding air pressure value, which includes the following formula:
p(1,2)=(p1+p2)/2
p(1,3)=(p1+p3)/2
p(3,4)=(p3+p4)/2
p(2,4)=(p2+p4)/2
wherein,
p1is the air pressure value, p, at one angular position in said substantially square area2Is the sum of p in the substantially square region1The value of the air pressure p at an angular position adjacent to the angular position3Is the sum of p in the substantially square region1The value of the air pressure p at another angular position adjacent to the angular position4Is the sum of p in the substantially square region1The value of the air pressure at the opposite angular position at that angular position, p(1,2)Is p1At position and p2The value of the air pressure at the position of the middle point between the positions, p(1,3)Is p1At position and p3The value of the air pressure at the position of the middle point between the positions, p(3,4)Is p3At position and p4The value of the air pressure at the position of the middle point between the positions, p(2,4)Is p2At position and p4The value of the air pressure at the midpoint between the locations,is the value of the air pressure at the central position of the substantially square area,is composed of p1At position p(1,2)At position p(1,3)At the position andat the positionThe air pressure value at the center position of the square area,is composed of p(1,2)At position p2At position p(2,4)At the position andthe air pressure value at the center position of the square area formed at the position,is composed of p3At position p(1,3)At position p(3,4)At the position andthe air pressure value at the center position of the square area formed at the position,is composed of p4At position p(2,4)At position p(3,4)At the position andthe air pressure value at the central position of the square area formed by the position.
It can be seen that by adopting the method, the basically square area can be infinitely subdivided by a calculation mode, and further, detailed hovercraft bottom air pressure value data can be obtained.
In step 2, for the position of the pressure sensor which is damaged and can not measure the air pressure value, the compensation pressure is calculated to obtain the corresponding air pressure value, which comprises the following steps:
and (3) averaging the air pressure values of four adjacent pressure sensors at the position of the pressure sensor which is damaged and can not measure the air pressure value by adopting a principle of proximity, and taking the average as the air pressure value at the position of the pressure sensor which is damaged and can not measure the air pressure value.
The method may be calculated by following the above-mentioned formula for obtaining the air pressure value of the position where the pressure sensor is not arranged, for example, in fig. 4, if the pressure sensor at the lower left corner of the area a14 is damaged, the air pressure values of the pressure sensors at the four positions of the upper left corner of the area a14, the lower right corner of the area a14, the upper left corner of the area a31 and the lower right corner of the area a31 may be averaged to be approximated as the air pressure value at the lower left corner of a 14.
In step 3 of the embodiment of the present invention, the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom are calculated according to the measured air pressure values at each part of the ship bottom, and the following calculation method is adopted:
the average air pressure values of four primary areas at the bottom of the hovercraft are obtained by adopting the following formula:
wherein,is the air pressure value at the center position of the ith substantially square area in the primary area a (i.e. the area a described above),is the air pressure value at the center position of the i-th substantially square area in the primary area B (i.e. the above-mentioned area B),is the air pressure value at the center position of the i-th substantially square area in the primary area C (i.e. the above-mentioned area C),is the air pressure value at the center position of the i-th substantially square area in the primary area D (i.e. the above-mentioned area D),is the average air pressure value of the primary region a,is the average air pressure value of the primary region B,is the average air pressure value of the primary region C,is the average air pressure value of the primary region D, N is the number of substantially square regions in each primary region, i is an integer from 1 to N, and the primary region a, the primary region B, the primary region C, and the primary region D are the four primary regions, i.e., the region a, the region B, the region C, and the region D. If three-level division is performed, that is, each primary region is further divided into four sub-regions, and each sub-region is further divided into four basic regions (that is, basic square regions), then N is 4 × 4 × 4 is 64, as shown in fig. 4, if more levels of division are performed, the number of basic square regions will increase in a geometric progression, and the accuracy of measurement and calculation will be more accurate.
And acquiring the average value of the air pressure of the whole ship bottom of the hovercraft by adopting the following formula:
wherein,is the average value of the air pressure of the whole ship bottom of the hovercraft.
In step 4, the stability of the hovercraft is judged according to the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom, and the method comprises the following steps:
determining the four primary zone average barometric pressure deviations according to the following formula:
wherein S isAIs the mean barometric deviation, S, of the primary region ABIs the mean barometric deviation, S, of the primary region BCIs the mean barometric deviation, S, of the primary region CDIs the average barometric deviation for primary region D.
Setting an instability grade threshold value of the hull of the hovercraft when S isA、SB、SC、SDAnd when any one of the unstable levels reaches the unstable level threshold value, judging that the hovercraft is unstable, and reporting the unstable level.
More specifically, in the embodiment of the invention, the multi-level hovercraft hull instability level threshold is set so as to realize multi-level early warning. For example, the hovercraft hull instability level threshold is set to be three levels, namely an unbalance level threshold, a severity level threshold and a ship-stopping maintenance level threshold.
Wherein when SA、SB、SC、SDIf any one of the items reaches the threshold value of the ship stopping overhaul level, the ship stopping overhaul level is reported, namely if any one of the items reaches the threshold value of the ship stopping overhaul level
max{SA,SB,SC,SD}≥η3
A ship-down service level is reported, wherein η3% is the shut-down maintenance level threshold.
When S isA、SB、SC、SDAny one of which reaches the severity level threshold and is less than the ship stopping overhaul level threshold, reporting the severity level, i.e. if
η2%≤max{SA,SB,SC,SD}<η3
Then a severity level is reported, wherein η2% is the severity level threshold.
When S isA、SB、SC、SDIf any of the terms reaches the imbalance level threshold and is less than the severity level threshold, the imbalance level is reported, i.e., if
η1%≤max{SA,SB,SC,SD}<η2
In an embodiment of the present invention, the imbalance level threshold is 3%, η13%, the severity level threshold is 5%, η25%, the ship-stopping maintenance grade threshold value is 8%, namely η3%=8%。
When S isA、SB、SC、SDAre not greater than the instability level threshold (i.e., η)1% 3%), the hovercraft hull is reported to be stable.
Fig. 6 is a schematic diagram of an alarm interface in an embodiment of the present invention, in order to visually display the air pressure distribution state at the bottom of the hovercraft, the alarm interface may be approximately modeled as a ship bottom profile, and color changes of bright spots (light spots) are used in various areas of the ship bottom to indicate the air pressure value conditions at various places (areas) of the ship bottom, for example, green is used to indicate the air pressure value not greater than the unstable level threshold, that is, green is used to indicate the normal air pressure value range, and red with different color depths is used to indicate unstable levels with different levels to indicate abnormal conditions of the ship bottom air pressure value. If the air pressure value of the whole ship bottom is in the normal air pressure value range, a large green dot (or a circle, a round cake and the like) is used for indicating that the air pressure of the ship bottom is normal in the center of the alarm interface.
According to the method for monitoring the air cushion pressure of the hovercraft, the plurality of pressure sensors are uniformly arranged at the bottom of the hovercraft to measure the air pressure values at all positions of the bottom of the hovercraft, so that the air pressure value at any position of the whole bottom of the hovercraft can be obtained in a compensation calculation mode, the local and overall pressure conditions at all positions of the bottom of the hovercraft can be timely and quickly obtained, and when the air pressure value changes excessively in a certain area, the local and overall pressure conditions can be timely fed back. The invention realizes that the pressure values at all positions at the bottom of the whole hovercraft are obtained by measuring and calculating each discrete point, so that the hovercraft can check the pressure condition of the hovercraft in the process of sailing, the trouble of manual inspection is avoided, and the danger of the hovercraft in the process of sailing is avoided.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims (8)

1. A method for monitoring the air cushion pressure of a hovercraft is characterized by comprising the following steps:
uniformly arranging a plurality of pressure sensors at the bottom of the hovercraft to measure air pressure values at all positions of the bottom of the hovercraft;
adopting compensation pressure calculation to obtain a corresponding air pressure value for the position where the pressure sensor is not arranged and the position where the pressure sensor which is damaged and cannot measure the air pressure value is located;
calculating the average value of the air pressure of each part of the ship bottom and the average value of the air pressure of the whole ship bottom according to the measured air pressure values of all parts of the ship bottom;
judging the stability of the hovercraft according to the average air pressure value of each part of the bottom of the hovercraft and the average air pressure value of the whole bottom of the hovercraft; wherein,
the step of judging the stability of the hovercraft according to the average air pressure value of each part of the bottom of the hovercraft and the average air pressure value of the whole bottom of the hovercraft comprises the following steps:
determining the average air pressure deviation degree of four primary areas divided by the center line at the bottom of the hovercraft according to the following formula:
wherein,
SAis the average degree of deviation of the air pressure in the primary region a,
SBis the average degree of deviation of the air pressure of the primary region B,
SCis the average degree of deviation of the air pressure in the primary region C,
SDis the average degree of deviation of the air pressure in the primary region D,
is the average air pressure value of the primary area a,is the average air pressure value of the primary region B,is the average air pressure value of the primary zone C,is the average air pressure value of the primary region D,the average value of the air pressure of the whole ship bottom of the hovercraft is obtained;
setting an instability grade threshold value of the hull of the hovercraft when S isA、SB、SC、SDAnd when any one of the unstable levels reaches the unstable level threshold value, judging that the hovercraft is unstable, and reporting the unstable level.
2. The hovercraft cushion pressure monitoring method as recited in claim 1, wherein uniformly arranging a plurality of pressure sensors at a bottom of the hovercraft comprises:
dividing the ship bottom of the hovercraft into the four primary areas;
dividing each primary area into four small areas according to the central line;
repeating the division mode, and dividing each small area for multiple times, so as to divide the ship bottom of the hovercraft into a plurality of equal basic square areas;
a plurality of pressure sensors are arranged at the four corners of all substantially square areas.
3. The hovercraft air cushion pressure monitoring method according to claim 2, wherein for positions where said pressure sensors are not located, using a compensated pressure calculation to obtain a corresponding barometric pressure value comprises using the following equation:
p(1,2)=(p1+p2)/2
p(1,3)=(p1+p3)/2
p(3,4)=(p3+p4)/2
p(2,4)=(p2+p4)/2
wherein,
p1is the air pressure value at one angular position in the substantially square region;
p2is the sum of p in the substantially square region1A pressure value at an angular position adjacent to the angular position;
p3is the sum of p in the substantially square region1A value of air pressure at another angular position adjacent to the angular position;
p4is the sum of p in the substantially square region1The air pressure value at the opposite angular position at that angular position;
p(1,2)is p1At position and p2A pressure value at a midpoint position between the positions;
p(1,3)is p1At position and p3A pressure value at a midpoint position between the positions;
p(3,4)is p3At position and p4A pressure value at a midpoint position between the positions;
p(2,4)is p2At position and p4A pressure value at a midpoint position between the positions;
is the air pressure value at the center position of the substantially square area;
is composed of p1At position p(1,2)At position p(1,3)At the position andthe air pressure value at the central position of the square area formed by the position of the air compressor;
is composed of p(1,2)At position p2At position p(2,4)At the position andthe air pressure value at the central position of the square area formed by the position of the air compressor;
is composed of p3At position p(1,3)At position p(3,4)At the position andthe air pressure value at the central position of the square area formed by the position of the air compressor;
is composed of p4At position p(2,4)At position p(3,4)At the position andthe air pressure value at the central position of the square area formed by the position.
4. The hovercraft air cushion pressure monitoring method according to claim 2, wherein the step of calculating the compensated pressure for the location of the damaged pressure sensor that cannot measure the air pressure value to obtain the corresponding air pressure value comprises:
and (3) averaging the air pressure values of four adjacent pressure sensors at the position of the pressure sensor which is damaged and can not measure the air pressure value by adopting a principle of proximity, and taking the average as the air pressure value at the position of the pressure sensor which is damaged and can not measure the air pressure value.
5. The hovercraft air cushion pressure monitoring method according to claim 3, wherein the step of calculating the average value of the air pressure in each part of the bottom of the vessel and the average value of the air pressure in the whole bottom of the vessel from the measured air pressure values at all parts of the bottom of the vessel comprises:
obtaining the average air pressure values of the four primary areas at the bottom of the hovercraft by adopting the following formula:
wherein,
is the air pressure value at the central position of the ith substantially square area in the primary area a,
is the air pressure value at the central position of the ith substantially square area in the primary area B,
is the air pressure value at the central position of the ith substantially square area in the primary area C,
is the air pressure value at the central position of the ith substantially square area in the primary area D,
n is the number of substantially square regions in each primary region, i is an integer from 1 to N,
the primary area A, the primary area B, the primary area C and the primary area D are four primary areas;
and acquiring the average value of the air pressure of the whole ship bottom of the hovercraft by adopting the following formula:
6. the hovercraft cushion pressure monitoring method as recited in claim 1, wherein a hovercraft hull instability level threshold is set when SA、SB、SC、SDWhen any one of the parameters reaches the instability level threshold value, judging that the hovercraft is unstable, and reporting the instability level, wherein the instability level comprises the following steps:
setting an unstable grade threshold of a hull of the hovercraft to be three levels, namely an unbalanced grade threshold, a serious grade threshold and a ship-stopping maintenance grade threshold;
when S isA、SB、SC、SDIf any one item reaches the threshold value of the ship stopping overhaul level, reporting the ship stopping overhaul level;
when S isA、SB、SC、SDIf any one item reaches the severity level threshold and is smaller than the ship stopping overhaul level threshold, reporting the severity level;
when S isA、SB、SC、SDIf any of the terms reaches the imbalance level threshold and is less than the severity level threshold, an imbalance level is reported.
7. The hovercraft cushion pressure monitoring method as defined in claim 6, wherein a hovercraft hull instability level threshold is set when S isA、SB、SC、SDWhen any one of the parameters reaches the instability level threshold value, judging that the hovercraft is unstable, and reporting the instability level, wherein the instability level comprises the following steps:
setting an unstable grade threshold of a hull of the hovercraft to be three levels, namely an unbalanced grade threshold, a serious grade threshold and a ship-stopping maintenance grade threshold;
the imbalance level threshold is 3%;
the severity level threshold is 5%;
the ship stopping overhaul grade threshold value is 8%.
8. Method for monitoring the cushion pressure of a hovercraft according to claim 6, wherein S is the time SA、SB、SC、SDAnd when the stability level is not greater than the instability level threshold, reporting that the hull of the hovercraft is stable.
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