CN111174845A - MEMS accelerometer-based aircraft oil quantity measuring system and measuring method - Google Patents
MEMS accelerometer-based aircraft oil quantity measuring system and measuring method Download PDFInfo
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- 239000000295 fuel oil Substances 0.000 claims description 11
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- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F9/00—Measuring volume flow relative to another variable, e.g. of liquid fuel for an engine
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Abstract
The invention relates to the technical field of aircraft oil quantity measurement, and discloses an aircraft oil quantity measurement system based on an MEMS accelerometer, which is connected with a capacitive oil quantity sensor and is characterized in that: the system comprises a capacitance conversion module, an MEMS accelerometer measuring module, a data processing module and a communication module, wherein the capacitance conversion module is connected with a capacitive oil mass sensor; the MEMS accelerometer measuring module and the communication module are respectively connected with the data processing module; calculating to obtain an oil level angle by acquiring the oil level height and the three-axis acceleration of the airplane and combining the attitude angle of the airplane, and inquiring an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil quantity; and finally, calculating through linear interpolation to obtain the volume information of the residual oil quantity of the oil tank. The method has the advantages that the three-axis acceleration of the airplane can be directly acquired while the inductive oil level height of the capacitive oil quantity sensor is acquired, the synchronism of the oil level height and the three-axis acceleration is ensured, and the oil quantity measurement precision under different airplane acceleration conditions is improved.
Description
Technical Field
The invention relates to the technical field of aircraft oil quantity measurement, in particular to an aircraft oil quantity measurement system and method based on an MEMS accelerometer.
Background
The measurement accuracy of the fuel quantity measuring system has a significant influence on the performance of the aircraft. For military aircraft, the fuel measurement accuracy is improved, which means that the effective load, the voyage and the combat radius of the aircraft can be improved; for civil transport plane, it can greatly improve its economy, and as long as the fuel oil measuring accuracy is raised by 0.5%, several passengers can be added.
The most common method for measuring the oil quantity of the aircraft at home and abroad comprises the following steps: firstly, acquiring the oil level height by using an oil quantity sensor (the most common existing capacitive oil quantity sensor) arranged on an oil tank; calculating to obtain an oil level angle by combining the attitude angle of the airplane and the triaxial acceleration, and inquiring an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil quantity; and finally, obtaining the residual oil quantity information of the oil tank through interpolation calculation.
However, the aircraft oil level measurement method is to receive the triaxial acceleration output by the inertial navigation equipment and other equipment on the aircraft through a digital communication bus to calculate the oil level angle, the triaxial acceleration acquired by the oil level measurement system is aircraft triaxial acceleration data before a communication period, and the change of the triaxial acceleration of the aircraft is obvious, so that the difference between the triaxial acceleration acquired by the oil level measurement system and the oil level height sensed by the oil level sensor is large in time synchronization, the calculated oil level angle cannot reflect the actual oil level angle, the oil level measurement error is increased, and the performance of the aircraft is affected.
Disclosure of Invention
The invention aims to provide an aircraft oil quantity measuring system and a measuring method based on an MEMS accelerometer, and provides a novel inductance type rotating speed sensor signal measuring device which is high in reliability and small in size.
The invention is realized by the following technical scheme:
an aircraft oil quantity measuring system based on an MEMS accelerometer is connected with a capacitive oil quantity sensor and comprises a capacitance conversion module, an MEMS accelerometer measuring module, a data processing module and a communication module, wherein the capacitance conversion module, the MEMS accelerometer measuring module, the data processing module and the communication module are connected with the capacitive oil quantity sensor; the MEMS accelerometer measuring module and the communication module are respectively connected with the data processing module.
Furthermore, in order to better implement the present invention, the capacitance conversion module includes a BIT capacitor, a first multi-way switch having an output end respectively connected to the input end of the capacitive oil quantity sensor and the input end of the BIT capacitor, an excitation circuit having an output end connected to the input end of the first multi-way switch, a phase shift adjusting circuit having an input end connected to the output end of the excitation circuit, a DAC digital-to-analog converter having an input end connected to the output end of the phase shift adjusting circuit, a balance capacitor connected to the output end of the DAC digital-to-analog converter, a summing circuit, a filtering and amplifying circuit, a zero-bound detector, and a second multi-way switch;
the input end of the second multi-way switch is respectively connected with the output end of the BIT capacitor, the output end of the capacitive oil quantity sensor and the digital processing module;
the output end of the second multi-way switch is connected with the input end of the summing circuit;
the output end of the balance capacitor is sequentially connected with a summing circuit, a filtering amplification circuit, a zero-bound detector and a data processing module;
the input end of the DAC is connected with the data processing module;
and the input end of the first multi-way switch is connected with the data processing module.
Further, in order to better implement the present invention, the communication module includes a level conversion chip and an ARINC429 chip which are sequentially connected with the data processing module.
Further, in order to better implement the invention, the model of the MEMS accelerometer measuring module is ADXL 362.
Furthermore, in order to better realize the invention, the invention also comprises a power supply conversion module which is respectively connected with the capacitance conversion module, the MEMS accelerometer measurement module and the data processing module.
Furthermore, in order to better realize the invention, the power conversion module comprises an LC filter circuit, an energy storage circuit, an EMI filter, a DC/DC converter and an LDO power conversion module which are sequentially connected with a 28V direct-current power supply; and the output of the LDO power supply conversion module is connected with the data processing module.
A measuring method of an aircraft oil level measuring system based on an MEMS accelerometer is characterized in that an oil level angle is obtained through calculation by acquiring the height of an oil level and the three-axis acceleration of an aircraft and combining the attitude angle of the aircraft, and an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil quantity is inquired; and finally, calculating through linear interpolation to obtain the volume information of the residual oil quantity of the oil tank.
Further, in order to better implement the invention, the method specifically comprises the following steps:
step S1: acquiring the height h of the oil level through a capacitive oil mass sensor arranged in an oil tank, and acquiring the triaxial acceleration n of the airplane through an MEMS accelerometerx、ny、nz(ii) a Wherein: n isxRepresents the X-direction acceleration of the airplane, and is positive opposite to the flying speed direction; n isyThe acceleration of the plane in the Y direction is shown, and the forward heading is positive to the right; n isyRepresents the Z-direction acceleration of the airplane, and the upward direction is positive;
step S2, calculating an aircraft attitude angle to obtain an aircraft fuel oil surface angle, wherein the aircraft fuel oil surface angle comprises an oil surface pitch angle α and an oil surface roll angle β;
and step S3, searching a plurality of groups of data adjacent to the oil quantity curve from the oil quantity curve, and linearly interpolating oil for seven times including h four times, α times and beta one time to obtain the volume information of the residual fuel oil quantity in the tank.
Further, in order to better implement the invention, the method specifically comprises the following steps: the step S2 specifically includes the following steps:
step S21, calculating to obtain an additional pitch angle α generated by the triaxial acceleration on the oil level of the oil in the oil tanknadditional roll angle βn(ii) a Acceleration n in X directionxwhen the pitch angle is negative, the oil level is decreased towards the head and increased towards the tail, and the pitch angle α is addednPositive, otherwise negative; when acceleration n in Y directionyto be correct, the oil level descends to the right along the heading direction, and the roll angle beta is addednPositive, otherwise negative; wherein
step S22, adding a pitch angle alphanadditional roll angle βncalculating to obtain the pitch angle α and roll angle β of the plane fuel oil surface angle, where α is αn+αplane；β＝βn+βplane。
Further, in order to better implement the present invention, the model of the data processing module is TMS320F 2812.
Compared with the prior art, the invention has the following advantages and beneficial effects:
(1) the invention improves the synchronism and the measurement precision.
(2) The capacitance type oil quantity sensor can directly acquire the triaxial acceleration of the airplane while acquiring the induction oil level height of the capacitance type oil quantity sensor, ensures the synchronism of the oil level height and the triaxial acceleration, and improves the oil quantity measurement precision under different airplane acceleration conditions.
(3) The invention has simple structure and strong practicability.
Drawings
FIG. 1 is a connection block diagram of the present invention;
FIG. 2 is a schematic circuit diagram of the present invention;
FIG. 3 is a schematic diagram of the operation of the present invention;
FIG. 4 is a graph illustrating the calculation of the oil surface angle in the measurement method of the present invention;
FIG. 5 is a graph of a fuel volume linear interpolation algorithm.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Example 1:
the invention is realized by the following technical scheme, as shown in figures 1-3, an aircraft oil quantity measuring system based on an MEMS accelerometer is connected with a capacitive oil quantity sensor and comprises a capacitance conversion module, an MEMS accelerometer measuring module, a data processing module and a communication module, wherein the capacitance conversion module, the MEMS accelerometer measuring module, the data processing module and the communication module are connected with the capacitive oil quantity sensor; the MEMS accelerometer measuring module and the communication module are respectively connected with the data processing module.
It should be noted that, through the above improvement, the three-axis acceleration of the aircraft can be directly obtained while the oil level sensor senses the oil level height, instead of indirectly obtaining the three-axis acceleration of the aircraft by receiving signals output by equipment such as inertial navigation equipment on the aircraft through a digital communication bus, so that the synchronism of the oil level height and the three-axis acceleration is ensured, and the oil quantity measurement accuracy under different aircraft acceleration conditions is improved.
A capacitance conversion module: the capacitance value of the capacitance type oil quantity sensor is converted in real time;
MEMS accelerometer measurement module: the device is used for measuring the triaxial acceleration of the airplane in real time;
a data processing module: the system is used for calculating the oil level height in real time, calculating to obtain an oil level angle by combining the aircraft attitude angle and the triaxial acceleration, inquiring an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil quantity, and finally obtaining the residual oil quantity information of the oil tank;
a communication module: the aircraft fuel tank residual fuel quantity display system is used for receiving the aircraft attitude angle in real time and periodically outputting the residual fuel quantity information of the fuel tank to the aircraft display system. The communication module is connected with the airplane display system and the airplane inertial navigation system. Therefore, the fuel quantity information is displayed on the aircraft display system, the aircraft inertial navigation system transmits the aircraft roll angle and the aircraft pitch angle of the aircraft to the data processing module through the communication module in real time, and the data processing module calculates to obtain the volume information of the residual fuel quantity of the fuel tank by combining the triaxial acceleration of the aircraft received in real time.
Such as: MEMS accelerometer measurement module for obtaining airplane triaxial acceleration nx、ny、nzcombining the calculation of the attitude angle of the airplane, wherein the attitude angle of the airplane comprises the roll angle alpha of the airplanenand a pitch angle betanObtaining the oil surface angle by applying a formula
Inquiring an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil quantity; and finally, calculating through linear interpolation to obtain the volume information of the residual oil quantity of the oil tank.
Example 2:
in this embodiment, a further optimization is performed on the basis of the above embodiments, as shown in fig. 1 and fig. 2, and further, in order to better implement the present invention, the capacitance conversion module includes a BIT capacitor, a first multi-way switch whose output end is respectively connected to the input end of the capacitive oil quantity sensor and the input end of the BIT capacitor, an excitation circuit whose output end is connected to the input end of the first multi-way switch, a phase shift adjusting circuit whose input end is connected to the output end of the excitation circuit, a DAC digital-to-analog converter whose input end is connected to the output end of the phase shift adjusting circuit, a balance capacitor connected to the output end of the DAC digital-to-analog converter, a summing circuit, a filter amplifying circuit, a zero-bound detector;
the input end of the second multi-way switch is respectively connected with the output end of the BIT capacitor, the output end of the capacitive oil quantity sensor and the digital processing module;
the output end of the second multi-way switch is connected with the input end of the summing circuit;
the output end of the balance capacitor is sequentially connected with a summing circuit, a filtering amplification circuit, a zero-bound detector and a data processing module;
the input end of the DAC is connected with the data processing module;
and the input end of the first multi-way switch is connected with the data processing module.
It should be noted that, through the above improvement, the capacitance conversion module measures the capacitive sensor by using a digital balance bridge, the digital balance bridge converts the oil level signal sensed by the capacitive sensor into a digital voltage signal, and the data processing module performs digital voltage signal collection to calculate the height of the oil level of the fuel tank. Meanwhile, the capacitance conversion module is provided with a BIT self-checking channel, an excitation signal drives the BIT capacitance in a time-sharing mode, the BIT capacitance is balanced through a bridge arm, and after summation, filtering and amplification, a rebalance monitoring signal is generated by a zero-boundary value detector to achieve BIT self-checking, and the maintenance level is improved.
The capacitance conversion module measures the capacitance sensor in a digital balance bridge mode, converts an oil level signal sensed by the capacitance sensor into a digital voltage signal, and the data processing module is used for calculating the height of the oil level of the fuel tank.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 3:
the present embodiment is further optimized based on the above embodiment, as shown in fig. 1, and further, in order to better implement the present invention, the communication module includes a level conversion chip and an ARINC429 chip, which are sequentially connected to the data processing module.
The communication module adopts an ARINC429 bus to transmit data, and the data processing module controls the communication module to receive the aircraft attitude angle in real time to calculate the oil surface angle and periodically output the residual oil quantity information of the oil tank to an onboard display system.
Further, in order to better implement the invention, the model of the MEMS accelerometer measuring module is ADXL 362.
The MEMS accelerometer measuring module outputs the triaxial acceleration of the airplane to the data processing module in the form of an SPI serial peripheral bus for calculating the oil surface angle; but not limited to, SPI serial peripheral bus, including2C and SCI serial peripheral bus.
The ADXL362 is a triaxial acceleration measuring system, is communicated with a CPU through an SPI protocol, and outputs the triaxial acceleration of the airplane to a data processing module in a digital mode, so that the triaxial acceleration of the airplane is obtained in real time in a direct mode, and the problem of synchronism of the triaxial acceleration obtained from other equipment on the airplane is solved.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 4:
the present embodiment is further optimized on the basis of the above embodiments, and as shown in fig. 1, to better implement the present invention, the present embodiment further includes a power conversion module respectively connected to the capacitance conversion module, the MEMS accelerometer measurement module, and the data processing module. The power supply module converts an external 28V direct-current power supply into an internal device working power supply, and normal operation of the device is guaranteed.
Furthermore, in order to better realize the invention, the power conversion module comprises an LC filter circuit, an energy storage circuit, an EMI filter, a DC/DC converter and an LDO power conversion module which are sequentially connected with a 28V direct-current power supply; and the output of the LDO power supply conversion module is connected with the data processing module.
It should be noted that, through the above improvement, the power conversion module circuit converts the 28V dc power into ± 15V, +5V required inside, and meets the requirements of power supply characteristics, electromagnetic compatibility and lightning protection; the +5V power supply is converted into 3.3V and 1.9V voltage required by the chip operation through the LDO.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 5:
the present embodiment is further optimized based on the above embodiment, as shown in fig. 1, and further, in order to better implement the present invention, the model of the data processing module is TMS320F 2812.
The data processing module consists of a TI company CPU chip TMS320F2812, a crystal oscillator circuit, a reset circuit and a JTAG interface compatible with an IEEE1149.1 international standard test protocol, and controls a digital-to-analog converter of the capacitance conversion module to excite the capacitance type oil quantity sensor to obtain a digital capacitance signal and convert the digital capacitance signal into a digital oil level height; meanwhile, the data processing module receives triaxial acceleration information output by the MEMS accelerometer measuring module and calculates an oil surface angle by combining the attitude angle received by the communication module; and finally, inquiring an oil tank curve which is stored in the CPU and represents the corresponding relation between the oil level height, the oil level angle and the oil quantity, obtaining the residual oil quantity information of the oil tank through interpolation operation, and controlling the communication module to send the oil quantity information to an on-board display system.
And a CPU program of the data processing module is provided with a power-on BIT, a period BIT and a maintenance BIT, so that the maintainability level of the measuring system is improved.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 6:
the embodiment is a measuring method of an aircraft oil level measuring system based on an MEMS accelerometer, which is based on embodiments 1 to 5, and comprises the steps of obtaining the oil level height and the three-axis acceleration of an aircraft, calculating an oil level angle by combining an aircraft attitude angle, and inquiring an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil amount; and finally, calculating through linear interpolation to obtain the volume information of the residual oil quantity of the oil tank.
Further, in order to better implement the invention, the method specifically comprises the following steps:
step S1: acquiring the height h of the oil level through a capacitive oil mass sensor arranged in an oil tank, and acquiring the triaxial acceleration n of the airplane through an MEMS accelerometerx、ny、nz(ii) a Wherein: n isxRepresents the X-direction acceleration of the airplane, and is positive opposite to the flying speed direction; n isyThe acceleration of the plane in the Y direction is shown, and the forward heading is positive to the right; n isyRepresents the Z-direction acceleration of the airplane, and the upward direction is positive;
step S2, calculating an aircraft attitude angle to obtain an aircraft fuel oil surface angle, wherein the aircraft fuel oil surface angle comprises an oil surface pitch angle α and an oil surface roll angle β;
further, in order to better implement the invention, the method specifically comprises the following steps: the step S2 specifically includes the following steps:
step S21, calculating to obtain an additional pitch angle α generated by the triaxial acceleration on the oil level of the oil in the oil tanknadditional roll angle βn(ii) a Acceleration n in X directionxwhen the pitch angle is negative, the oil level is decreased towards the head and increased towards the tail, and the pitch angle α is addednPositive, otherwise negative; when acceleration n in Y directionyto be correct, the oil level descends to the right along the heading direction, and the roll angle beta is addednPositive, otherwise negative; wherein
step S22, adding a pitch angle alphanadditional roll angle βncalculating to obtain the pitch angle α and roll angle β of the plane fuel oil surface angle, where α is αn+αplane；β＝βn+βplane。
Step S3: searching eight groups of data adjacent to the fuel quantity curve from the fuel quantity curve, wherein the eight groups of data are respectively (h)i,αi,βi)、(hi,αi+1,βi)、(hi,αi,βi+1)、(hi,αi+1,βi+1)、(hi+1,αi,βi)、(hi+1,αi+1,βi)、(hi+1,αi,βi+1)、(hi+1,αi+1,βi+1) Which satisfies the condition hi≤h≤hi+1、αi≤α≤αi+1、βi≤β≤βi+1and obtaining the volume information of the residual fuel quantity in the tank by a linear interpolation method for h four times, α two times and beta one time for seven times.
According to the method, the three-axis acceleration of the airplane can be directly obtained while the oil quantity sensor senses the height of the oil level, instead of indirectly obtaining the three-axis acceleration of the airplane by receiving signals output by inertial navigation equipment and the like on the airplane through a digital communication bus, so that the synchronism of the height of the oil level and the three-axis acceleration is ensured, and the oil quantity measurement precision under different airplane acceleration conditions is improved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (10)
1. The utility model provides an aircraft oil mass measuring system based on MEMS accelerometer, is connected with capacitanc oil mass sensor, its characterized in that: the system comprises a capacitance conversion module, an MEMS accelerometer measuring module, a data processing module and a communication module, wherein the capacitance conversion module is connected with a capacitive oil mass sensor; the MEMS accelerometer measuring module and the communication module are respectively connected with the data processing module.
2. An aircraft oil content measuring system based on MEMS accelerometer according to claim 1, characterized by: the capacitance conversion module comprises a BIT capacitor, a first multi-way switch, an excitation circuit, a phase shift adjusting circuit, a DAC (digital-to-analog converter), a balance capacitor, a summing circuit, a filtering amplifying circuit, a zero-boundary detector and a second multi-way switch, wherein the output end of the first multi-way switch is respectively connected with the input end of the capacitance oil quantity sensor and the input end of the BIT capacitor;
the input end of the second multi-way switch is respectively connected with the output end of the BIT capacitor, the output end of the capacitive oil quantity sensor and the digital processing module;
the output end of the second multi-way switch is connected with the input end of the summing circuit;
the output end of the balance capacitor is sequentially connected with a summing circuit, a filtering amplification circuit, a zero-bound detector and a data processing module;
the input end of the DAC is connected with the data processing module;
and the input end of the first multi-way switch is connected with the data processing module.
3. An aircraft oil content measuring system based on MEMS accelerometer according to claim 2, characterized by: the communication module comprises a level conversion chip and an ARINC429 chip which are sequentially connected with the data processing module.
4. An aircraft oil content measuring system based on MEMS accelerometer according to claim 1, characterized by: the model of the MEMS accelerometer measuring module is ADXL 362.
5. An aircraft oil content measuring system based on MEMS accelerometer according to claim 1, characterized by: the power supply conversion module is respectively connected with the capacitance conversion module, the MEMS accelerometer measurement module and the data processing module.
6. An aircraft oil content measuring system based on a MEMS accelerometer as claimed in claim 5, wherein: the power conversion module comprises an LC filter circuit, an energy storage circuit, an EMI filter, a DC/DC converter and an LDO power conversion module which are sequentially connected with a 28V direct-current power supply; and the output of the LDO power supply conversion module is connected with the data processing module.
7. An aircraft oil content measuring system based on MEMS accelerometer according to any of claims 1-6, characterized by: the model of the data processing module is TMS320F 2812.
8. A measuring method of an aircraft oil quantity measuring system based on MEMS accelerometer according to any of claims 1-7, characterized by: calculating to obtain an oil level angle by acquiring the oil level height and the three-axis acceleration of the airplane and combining the attitude angle of the airplane, and inquiring an oil tank curve representing the corresponding relation between the oil level height, the oil level angle and the oil quantity; and finally, calculating through linear interpolation to obtain the volume information of the residual oil quantity of the oil tank.
9. The measurement method of the MEMS accelerometer-based aircraft oil content measurement system of claim 8, wherein: the method specifically comprises the following steps:
step S1: acquiring the height h of the oil level through a capacitive oil mass sensor arranged in an oil tank, and acquiring the triaxial acceleration n of the airplane through an MEMS accelerometerx、ny、nz(ii) a Wherein: n isxRepresents the X-direction acceleration of the airplane, and is positive opposite to the flying speed direction; n isyThe acceleration of the plane in the Y direction is shown, and the forward heading is positive to the right; n isyRepresents the Z-direction acceleration of the airplane, and the upward direction is positive;
step S2, calculating an aircraft attitude angle to obtain an aircraft fuel oil surface angle, wherein the aircraft fuel oil surface angle comprises an oil surface pitch angle α and an oil surface roll angle β;
and step S3, searching a plurality of groups of data adjacent to the oil quantity curve from the oil quantity curve, and linearly interpolating oil for seven times including h four times, α times and beta one time to obtain the volume information of the residual fuel oil quantity in the tank.
Are respectively (h)i,αi,βi)、(hi,αi+1,βi)、(hi,αi,βi+1)、(hi,αi+1,βi+1)、(hi+1,αi,βi)、(hi+1,αi+1,βi)、(hi+1,αi,βi+1)、(hi+1,αi+1,βi+1) Which satisfies the condition hi≤h≤hi+1、αi≤α≤αi+1、βi≤β≤βi+1。
10. The measurement method of the MEMS accelerometer-based aircraft oil content measurement system according to claim 9, wherein: the method specifically comprises the following steps: the step S2 specifically includes the following steps:
step S21: calculating to obtain three-axis acceleration in the oil tankadditional pitch angle alpha generated by fuel oil levelnadditional roll angle βn(ii) a Acceleration n in X directionxwhen the pitch angle is negative, the oil level is decreased towards the head and increased towards the tail, and the pitch angle α is addednPositive, otherwise negative; when acceleration n in Y directionyto be correct, the oil level descends to the right along the heading direction, and the roll angle beta is addednPositive, otherwise negative; wherein
step S22, adding a pitch angle alphanadditional roll angle βncalculating to obtain the pitch angle α and roll angle β of the plane fuel oil surface angle, where α is αn+αplane；β＝βn+βplane。
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112229464A (en) * | 2020-10-10 | 2021-01-15 | 江西洪都航空工业集团有限责任公司 | Fuel oil measuring system comprehensively utilizing flight large attitude change |
| CN113670407A (en) * | 2021-08-12 | 2021-11-19 | 陕西飞机工业有限责任公司 | Fuel oil level measuring method |
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| CN114812730A (en) * | 2022-04-28 | 2022-07-29 | 四川泛华航空仪表电器有限公司 | A high-precision real-time fuel quantity calculation device and method for aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112229464A (en) * | 2020-10-10 | 2021-01-15 | 江西洪都航空工业集团有限责任公司 | Fuel oil measuring system comprehensively utilizing flight large attitude change |
| CN113670407A (en) * | 2021-08-12 | 2021-11-19 | 陕西飞机工业有限责任公司 | Fuel oil level measuring method |
| CN113670407B (en) * | 2021-08-12 | 2023-05-26 | 陕西飞机工业有限责任公司 | Fuel oil level measuring method |
| CN114047093A (en) * | 2021-11-11 | 2022-02-15 | 四川泛华航空仪表电器有限公司 | Oil quantity measuring and converting circuit and working method thereof |
| CN114812730A (en) * | 2022-04-28 | 2022-07-29 | 四川泛华航空仪表电器有限公司 | A high-precision real-time fuel quantity calculation device and method for aircraft |
| CN116659611A (en) * | 2023-06-14 | 2023-08-29 | 中煤科工集团上海有限公司 | Oil level detection system and oil tank of submerged mobile gear oil tank |
| CN118836942A (en) * | 2024-06-26 | 2024-10-25 | 四川泛华航空仪表电器有限公司 | Aircraft water quantity measurement method and system |
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