CN113670407B - Fuel oil level measuring method - Google Patents
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- CN113670407B CN113670407B CN202110926486.1A CN202110926486A CN113670407B CN 113670407 B CN113670407 B CN 113670407B CN 202110926486 A CN202110926486 A CN 202110926486A CN 113670407 B CN113670407 B CN 113670407B
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- 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
- G01F23/26—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 variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
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- 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
Abstract
The invention belongs to the technical field of aviation, and discloses a fuel oil level measuring method, wherein a plurality of fuel oil sensors are arranged in a fuel tank, and the fuel oil sensors are capacitive fuel oil sensors; the measuring method comprises the following steps: acquiring aircraft overload information, and acquiring an oil level angle under an ideal state according to the aircraft overload information; for any three oil mass sensors capable of forming three-point surfaces, calculating oil surface angles according to the three-point surfaces formed by the oil mass sensors to obtain a plurality of oil surface angle information; removing information with errors larger than a preset value from the oil level angle information; and sequencing the plurality of effective oil level angle information from large to small according to the corresponding three-point surface areas, and averaging the oil level angles corresponding to the first N three-point surfaces to obtain a final oil level angle, thereby solving the hysteresis problem of judging the oil level angle through the aircraft overload information and furthest eliminating the measurement error caused by oil level shaking.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a fuel oil level measuring method.
Background
The capacitive oil quantity measuring system is used for measuring and calculating the residual oil quantity in the oil tank by utilizing the oil level angle and the immersion oil height of the capacitive sensor.
The method for measuring the fuel oil level angle in actual application comprises the following steps of calculating oil level angle information through the attitude of an airplane and overload information, wherein the overload information of the airplane is generally an overload coefficient in the three directions of X, Y, Z (the Y direction does not contain gravity coefficient), the overload coefficient is provided for a fuel oil measuring processor through a bus by an airplane system, the method is to indirectly obtain the fuel oil level angle, when the airplane flies at a uniform speed, the obtained oil level angle is reliable, but when the acceleration of the airplane is high, the oil level can shake, the change of the oil level angle is delayed from the change of the overload information of the airplane, and the overload information of the airplane cannot represent the actual oil level angle in an oil tank.
Disclosure of Invention
The invention overcomes the defects in the prior art, provides a fuel oil level measuring method, solves the problem of hysteresis of judging the fuel oil level angle through the overload information of the airplane, and furthest eliminates the measuring error caused by the shaking of the fuel oil level.
In order to achieve the above purpose, the invention is realized by adopting the following technical scheme.
A fuel oil level measuring method includes that a plurality of fuel oil sensors are arranged in a fuel tank, and the fuel oil sensors are capacitive fuel oil sensors; the measuring method comprises the following steps:
s1, acquiring aircraft overload information, and acquiring an oil level angle in an ideal state according to the aircraft overload information; the aircraft overload information comprises: aircraft roll angle, pitch angle, and triaxial acceleration;
s2, calculating oil level angles according to any three oil level sensors capable of forming three-point surfaces, and obtaining a plurality of oil level angle information;
s3, removing information with errors larger than a preset value from the oil surface angle information according to the aircraft overload information to obtain effective oil surface angle information;
s4, sorting the plurality of effective oil surface angle information from large to small according to the corresponding three-point surface areas to respectively obtain oil surface angles corresponding to the first N three-point surfaces;
and S5, averaging the oil surface angles corresponding to the first N three-point surfaces to obtain a final oil surface angle.
The technical scheme of the invention is characterized in that:
(1) S2 specifically comprises the following steps:
s21, acquiring coordinates of oil level information points of any three oil level sensors capable of forming three-point surfaces as (x) 1 、y 1 、z 1 )、(x 2 、y 2 、z 2 ) And (x) 3 、y 3 、z 3 ) The coordinates of the oil level information points are relative to an aircraft coordinate system;
s22, first, the oil level equation is determined from coordinates of three oil level information points as follows:
wherein: (x, y, z) is the coordinate value of any point on the oil plane;
converting it into a point French equation:
converting the point French equation into a planar point French equation standard form:
A(x-x 1 )+B(y-y 1 )+C(z-z 1 )＝0
wherein:
(x 1 、y 1 、z 1 ) Coordinates of an oil level information point of a known oil level sensor on the oil plane, (A, B, C) is a normal vector of the oil plane;
s23, according to the formula, the oil surface angle is obtained as follows:
wherein, alpha and beta respectively represent the rolling angle and the pitch angle of the oil surface.
(2) S21, acquiring coordinates of oil level information points of any three oil level sensors capable of forming three-point surfaces, wherein the coordinates are specifically as follows: for one of the oil mass sensors,
the oil quantity sensor is arranged in the oil tank, so that the top end coordinate and the bottom end coordinate of the oil quantity sensor are known;
determining a full oil capacitance value of the oil quantity sensor when the oil tank is full of oil and an empty oil capacitance value of the oil quantity sensor when the oil tank is empty of oil;
determining the current capacitance value of the fuel sensor when the fuel in the fuel tank is at any interface in the flying state;
and determining the induction height of the current oil mass sensor according to the ratio of the current capacitance value to the full oil capacitance value and the coordinate point of the bottom end and the top end of the oil mass sensor, and further solving the coordinate of the intersection point A of the current oil surface and the oil mass sensor to serve as the coordinate of the oil level information point of the oil mass sensor.
(3) According to the ratio of the current capacitance value to the full oil capacitance value and the coordinate point of the bottom end and the top end of the oil quantity sensor, the sensing height of the current oil quantity sensor is determined, specifically:
determining the current capacitance value of the fuel sensor when the fuel in the fuel tank is at any interface in the flying state:
the capacitance increment during partial oil immersion is as follows:
the calculation formula of the sensing height H of the current oil quantity sensor is as follows:
wherein: c is the capacitance of the oil sensor, e is the vacuum dielectric constant, K is the relative dielectric constant of the medium between the inner electrode tube and the outer electrode tube of the oil sensor, L is the length of the oil sensor, b is the radius of the outer electrode tube of the capacitance of the oil sensor, a is the radius of the inner electrode tube of the capacitance of the oil sensor, C a The capacitance value of the oil quantity sensor is the capacitance value when the oil quantity sensor is not immersed in oil at all.
(4) The sensing height of the current oil level sensor is determined, and then the coordinate of the intersection point A of the current oil level and the oil level sensor is obtained and used as the coordinate of the oil level information point of the oil level sensor, specifically:
wherein:
x C1 、y C1 、z C1 -coordinates of the highest sensing point of the oil mass sensor;
x C2 、y C2 、z C2 -coordinates of the lowest sensing point of the oil mass sensor;
x CA 、y CA 、z CA -coordinates of the intersection of the fuel sensor axis and the fuel level;
h-oil mass sensor to sense the oil level;
the L-oil sensor may sense a partial length.
(5) S3, specifically: and comparing any oil level angle information with the aircraft overload information, and removing the oil level angle information with the error of the oil level angle information and the aircraft overload information being more than +/-5 degrees.
(6) S1, acquiring aircraft overload information, and acquiring an oil level angle under an ideal state according to the aircraft overload information, wherein the oil level angle is specifically as follows:
aircraft overload angle:
wherein n is x The X-direction overload coefficient of the airplane is represented, and the X-direction overload coefficient is positive opposite to the flying speed direction; n is n y The Y-direction overload coefficient of the airplane is represented, and the upward direction is positive; n is n z The Z-direction overload coefficient of the airplane is represented, and the forward direction is positive to the right;
the oil level angle is the sum of the attitude angle and the overload angle of the airplane, and the calculation formula of the oil level angle is:
α＝α n +α m
β＝β n +β m
wherein:
alpha and beta are the oil surface roll angle and pitch angle respectively;
α m 、β m the aircraft roll angle and pitch angle, respectively.
(7) In S4, N is greater than or equal to 5.
According to the technical scheme, the oil level angle information is changed on the basis of judging the oil level angle information through overload information, the oil level angle with overlarge error is eliminated through the overload information, then the oil level angles measured by three-point surfaces with the first five areas are selected to obtain the average value according to the three-point surface area sequence, the error caused by oil level shaking is effectively improved, and the problem that the oil level angle lags behind a measured value is solved.
Drawings
FIG. 1 is a schematic diagram of solving overload directions and overload angles according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of oil level sensor sensing height crossing an oil level;
fig. 3 is a schematic view of effective oil level information point selection demonstration;
FIG. 4 is a schematic diagram of a tank sensor layout;
fig. 5 is a schematic diagram of sensor immersion.
Detailed Description
The embodiment of the invention provides a fuel oil level measuring method, wherein a plurality of oil mass sensors are arranged in an oil tank, and the oil mass sensors are capacitance type oil mass sensors; the measuring method comprises the following steps:
s1, acquiring aircraft overload information, and acquiring an oil level angle in an ideal state according to the aircraft overload information; the aircraft overload information comprises: aircraft roll angle, pitch angle, and triaxial acceleration;
s1, acquiring aircraft overload information, and acquiring an oil level angle under an ideal state according to the aircraft overload information, wherein the oil level angle is specifically as follows:
α n for the longitudinal overload angle, n x Negative then alpha n Positive (the oil level descends towards the machine head direction, and the oil level ascends towards the machine tail direction and is positive, and vice versa);
β n for the transverse overload angle, n y Is regular beta n Positive (clockwise direction decreases to right oil level positive and vice versa);
from fig. 1, it can be obtained that: aircraft overload angle:
wherein n is x The X-direction overload coefficient of the airplane is represented, and the X-direction overload coefficient is positive opposite to the flying speed direction; n is n y The Y-direction overload coefficient of the airplane is represented, and the upward direction is positive; n is n z The Z-direction overload coefficient of the airplane is represented, and the forward direction is positive to the right;
the oil level angle is the sum of the attitude angle and the overload angle of the airplane, and the calculation formula of the oil level angle is:
α＝α n +α m
β＝β n +β m
wherein:
alpha and beta are the oil surface roll angle and pitch angle respectively;
α m 、β m the aircraft roll angle and pitch angle, respectively.
S2, calculating oil level angles according to any three oil level sensors capable of forming three-point surfaces, and obtaining a plurality of oil level angle information;
s2 specifically comprises the following steps:
s21, acquiring coordinates of oil level information points of any three oil level sensors capable of forming three-point surfaces as (x) 1 、y 1 、z 1 )、(x 2 、y 2 、z 2 ) And (x) 3 、y 3 、z 3 ) The coordinates of the oil level information points are relative to an aircraft coordinate system;
the coordinates of the oil level information points of any three oil level sensors capable of forming three-point surfaces are obtained, and the coordinates are specifically as follows: for one of the oil mass sensors,
the oil quantity sensor is arranged in the oil tank, so that the top end coordinate and the bottom end coordinate of the oil quantity sensor are known;
determining a full oil capacitance value of the oil quantity sensor when the oil tank is full of oil and an empty oil capacitance value of the oil quantity sensor when the oil tank is empty of oil;
determining the current capacitance value of the fuel sensor when the fuel in the fuel tank is at any interface in the flying state;
and determining the induction height of the current oil mass sensor according to the ratio of the current capacitance value to the full oil capacitance value and the coordinate point of the bottom end and the top end of the oil mass sensor, and further solving the coordinate of the intersection point A of the current oil surface and the oil mass sensor to serve as the coordinate of the oil level information point of the oil mass sensor.
S22, first, the oil level equation is determined from coordinates of three oil level information points as follows:
wherein: (x, y, z) is the coordinate value of any point on the oil plane;
converting it into a point French equation:
converting the point French equation into a planar point French equation standard form:
A(x-x 1 )+B(y-y 1 )+C(z-z 1 )＝0
wherein:
(x 1 、y 1 、z 1 ) Coordinates of an oil level information point of a known oil level sensor on the oil plane, (A, B, C) is a normal vector of the oil plane;
s23, according to the formula, the oil surface angle is obtained as follows:
wherein, alpha and beta respectively represent the rolling angle and the pitch angle of the oil surface.
According to the ratio of the current capacitance value to the full oil capacitance value and the coordinate point of the bottom end and the top end of the oil quantity sensor, the sensing height of the current oil quantity sensor is determined, specifically:
determining the current capacitance value of the fuel sensor when the fuel in the fuel tank is at any interface in the flying state:
the capacitance increment during partial oil immersion is as follows:
the calculation formula of the sensing height H of the current oil quantity sensor is as follows:
wherein: c is the capacitance of the oil sensor, e is the vacuum dielectric constant, K is the relative dielectric constant of the medium between the inner pole tube and the outer pole tube of the oil sensor, L is the length of the oil sensor, b is the radius of the outer pole tube of the capacitance of the oil sensor, a is the radius of the inner pole tube of the capacitance of the oil sensor，C a The capacitance value of the oil quantity sensor is the capacitance value when the oil quantity sensor is not immersed in oil at all.
The sensing height of the current oil level sensor is determined, and then the coordinate of the intersection point A of the current oil level and the oil level sensor is obtained and used as the coordinate of the oil level information point of the oil level sensor, as shown in fig. 2, specifically:
wherein:
x C1 、y C1 、z C1 -coordinates of the highest sensing point of the oil mass sensor;
x C2 、y C2 、z C2 -coordinates of the lowest sensing point of the oil mass sensor;
x CA 、y CA 、z CA -coordinates of the intersection of the fuel sensor axis and the fuel level;
h-oil mass sensor to sense the oil level;
the L-oil sensor may sense a partial length.
The oil level information is sensed by the 3 oil level sensors immersed in the fuel oil, when the 3 oil level sensors are intersected with the oil level to form 3 points, the oil level angle can be calculated according to the 3 points, as shown in fig. 3, when the area enclosed by the three points is large, the influence of the oil level height measurement error on the oil level angle calculation result is small, and the measurement accuracy is improved.
The method can directly obtain the oil level angle, but the oil level is not completely a plane, the oil level is swaying, and when the oil level is fluctuated, particularly when the oil level is fluctuated near a sensor, the oil level angle can be measured inaccurately, so that the invention can solve the defect that when one sensor cannot be immersed into fuel oil, 3 points for measuring the oil level cannot be formed and the oil level cannot be measured by a three-point method by solving the average value of a plurality of oil level angles.
S3, removing information with errors larger than a preset value from the oil surface angle information according to the aircraft overload information to obtain effective oil surface angle information;
s3, specifically: and comparing any oil level angle information with the aircraft overload information, and removing the oil level angle information with the error of the oil level angle information and the aircraft overload information being more than +/-5 degrees.
S4, sorting the plurality of effective oil surface angle information from large to small according to the corresponding three-point surface areas to respectively obtain oil surface angles corresponding to the first N three-point surfaces;
and S5, averaging the oil surface angles corresponding to the first N three-point surfaces to obtain a final oil surface angle.
When a plurality of sensors are immersed in fuel oil, a plurality of three-point surfaces are formed, the oil surface angles measured by the three-point surfaces are compared with overload signals transmitted by an airplane, when the oil surface angles measured by the three-point surfaces are greater than +/-5 degrees with the overload signals, because the oil surface near the three-point surface sensors has shaking, the oil surface angles measured by the three-point surfaces have larger errors, the three-point surfaces are required to be eliminated, if the oil surface i formed by the remaining effective oil level information points is greater than or equal to 5, according to the conclusion, the larger the area formed by the three-point surfaces is, the smaller the errors caused by shaking the oil surface are, the oil surface formed by the three-point surfaces are ordered according to the area size, the oil surface corresponding to the 5 largest three-point surface areas is obtained, and the corresponding oil surface angles alpha of the 5 three-point surfaces are calculated respectively i And beta i When 0 is<i<5, taking the average of the oil levels.
The three-point oil surface angle measuring method adopted by the invention is still applicable under the conditions as shown in fig. 4 and 5, a total of 6 effective measuring points A1 to A6 can form 20 three-point surface combinations, firstly three-point surfaces with extremely large errors compared with the overload information of the aircraft are eliminated, then the rest planes are ordered according to the area size, the oil surface angles obtained by the three-point surfaces with the first five areas are averaged, and the errors caused by oil surface shaking can be effectively eliminated. Compared with a method for calculating the oil level angle through the aircraft overload information, the method adopts the oil level sensor to directly sense the oil level, so that the problem that the oil level change lags behind the aircraft overload information is solved, the oil level angle sensed by the oil level sensor is the real-time oil level angle, and the oil level jump in the stage of relatively large acceleration such as climbing, landing and the like can be reduced.
Claims (7)
1. The fuel oil level measuring method is characterized in that a plurality of fuel oil sensors are arranged in a fuel tank, and the fuel oil sensors are capacitive fuel oil sensors; the measuring method comprises the following steps:
s1, acquiring aircraft overload information, and acquiring an oil level angle in an ideal state according to the aircraft overload information; the aircraft overload information comprises: aircraft roll angle, pitch angle, and triaxial acceleration;
s2, calculating oil level angles according to any three oil level sensors capable of forming three-point surfaces, and obtaining a plurality of oil level angle information; s2 specifically comprises the following steps:
s21, acquiring coordinates of oil level information points of any three oil level sensors capable of forming three-point surfaces as (x) 1 、y 1 、z 1 )、(x 2 、y 2 、z 2 ) And (x) 3 、y 3 、z 3 ) The coordinates of the oil level information points are relative to an aircraft coordinate system;
s22, first, the oil level equation is determined from coordinates of three oil level information points as follows:
wherein: (x, y, z) is the coordinate value of any point on the oil plane;
converting it into a point French equation:
converting the point French equation into a planar point French equation standard form:
A(x-x 1 )+B(y-y 1 )+C(z-z 1 )＝0
wherein:
(x 1 、y 1 、z 1 ) Coordinates of oil level information points of a known oil level sensor on the oil level, (A, B, C) being the oil levelA normal vector;
s23, according to the formula, the oil surface angle is obtained as follows:
wherein alpha and beta respectively represent the rolling angle and the pitch angle of the oil surface;
s3, removing information with errors larger than a preset value from the oil surface angle information according to the aircraft overload information to obtain effective oil surface angle information;
s4, sorting the plurality of effective oil surface angle information from large to small according to the corresponding three-point surface areas to respectively obtain oil surface angles corresponding to the first N three-point surfaces;
and S5, averaging the oil surface angles corresponding to the first N three-point surfaces to obtain a final oil surface angle.
2. The fuel level measuring method according to claim 1, wherein S21, coordinates of oil level information points of any three oil level sensors that can constitute a three-point surface are obtained, specifically: for one of the oil mass sensors,
the oil quantity sensor is arranged in the oil tank, so that the top end coordinate and the bottom end coordinate of the oil quantity sensor are known;
determining a full oil capacitance value of the oil quantity sensor when the oil tank is full of oil and an empty oil capacitance value of the oil quantity sensor when the oil tank is empty of oil;
determining the current capacitance value of the fuel sensor when the fuel in the fuel tank is at any interface in the flying state;
and determining the induction height of the current oil mass sensor according to the ratio of the current capacitance value to the full oil capacitance value and the coordinate point of the bottom end and the top end of the oil mass sensor, and further solving the coordinate of the intersection point A of the current oil surface and the oil mass sensor to serve as the coordinate of the oil level information point of the oil mass sensor.
3. The method for measuring the fuel level according to claim 2, wherein the sensing height of the current fuel sensor is determined according to the ratio of the current capacitance value to the full-fuel capacitance value and the coordinate point of the bottom end and the top end of the fuel sensor, and specifically comprises the following steps:
determining the current capacitance value of the fuel sensor when the fuel in the fuel tank is at any interface in the flying state:
the capacitance increment during partial oil immersion is as follows:
the calculation formula of the sensing height H of the current oil quantity sensor is as follows:
wherein: c is the capacitance of the oil sensor, e is the vacuum dielectric constant, K is the relative dielectric constant of the medium between the inner electrode tube and the outer electrode tube of the oil sensor, L is the length of the oil sensor, b is the radius of the outer electrode tube of the capacitance of the oil sensor, a is the radius of the inner electrode tube of the capacitance of the oil sensor, C a The capacitance value of the oil quantity sensor is the capacitance value when the oil quantity sensor is not immersed in oil at all.
4. A fuel level measuring method according to claim 3, wherein the sensing height of the current fuel level sensor is determined, and the coordinate of the intersection point a of the current fuel level and the fuel level sensor is obtained as the coordinate of the fuel level information point of the fuel level sensor, specifically:
wherein:
x C1 、y C1 、z C1 -coordinates of the highest sensing point of the oil mass sensor;
x C2 、y C2 、z C2 -coordinates of the lowest sensing point of the oil mass sensor;
x CA 、y CA 、z CA -coordinates of the intersection of the fuel sensor axis and the fuel level.
5. The fuel level measurement method according to claim 1, wherein S3 is specifically: and comparing any oil level angle information with the aircraft overload information, and removing the oil level angle information with the error of the oil level angle information and the aircraft overload information being more than +/-5 degrees.
6. A fuel level measuring method according to claim 1, wherein,
s1, acquiring aircraft overload information, and acquiring an oil level angle under an ideal state according to the aircraft overload information, wherein the oil level angle is specifically as follows:
aircraft overload angle:
wherein n is x The X-direction overload coefficient of the airplane is represented, and the X-direction overload coefficient is positive opposite to the flying speed direction; n is n y Representing an aircraft
The Y-direction overload coefficient is positive upwards; n is n z The Z-direction overload coefficient of the airplane is represented, and the forward direction is positive to the right;
the oil level angle is the sum of the attitude angle and the overload angle of the airplane, and the calculation formula of the oil level angle is:
α＝α n +α m
β＝β n +β m
wherein:
alpha and beta are the oil surface roll angle and pitch angle respectively;
α m 、β m the aircraft roll angle and pitch angle, respectively.
7. The method of claim 1, wherein N is greater than or equal to 5 in S4.
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