Alarm error correction method of aviation power comprehensive instrument controller

Abstract

The invention belongs to the technical field of instrument display error correction, and particularly relates to an alarm error correction method of an aviation power comprehensive instrument controller. The method specifically comprises the following steps that S1, the temperature of the controller is calculated through testing; s2, performing cubic polynomial fitting on the temperature of the controller, and correcting the temperature of the controller; and S3, the controller carries out display setting on temperature early warning of the IGBT and carries out display setting when the temperature of the IGBT is too high and reaches a protection threshold value. According to the invention, fitting is carried out on the temperature of the controller by adopting a cubic polynomial; the controller reasonably sets the display of the temperature early warning of the IGBT; and the controller is used for displaying and setting when the temperature of the IGBT is too high and reaches a protection threshold value. The display and alarm errors of the aviation power comprehensive instrument are corrected, and the flight efficiency and safety of the electric aircraft are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of instrument display error correction, and in particular relates to an alarm error correction method for an aviation power integrated instrument controller. Background Art

[0002] The power integrated display instrument is a key component of electric aircraft, and the display accuracy of its controller directly affects the safe operation of the aircraft. The controller contains an insulated gate bipolar transistor IGBT, which will still generate heat when the contact surface state and tightening degree are adjusted during use, causing the thermistor to produce temperature errors. For example, a set of thermistors can make the actual 100℃ displayed as 95℃-105℃, while multiple sets of thermistors in the IGBT will make the error even greater. This seriously affects the accuracy of the instrument display value, which in turn affects the pilot's flight and may even cause flight accidents.

[0003] When the temperature of the controller displayed by the power integrated display instrument cannot be displayed correctly, the alarm threshold will be uncertain and the pilot will not be able to assess the working status of the power system. As electric aircraft enter the mass production stage, this problem needs to be solved urgently. Summary of the invention

[0004] The present invention aims to provide an alarm error correction method for an aviation power integrated instrument controller, correct the error between the displayed temperature value and the actual value of the controller in the instrument, overcome the error problem of the display of the existing electric aircraft power integrated instrument, and improve the flight efficiency and safety of the pilot.

[0005] To achieve the above object, the present invention adopts the following specific technical scheme: an alarm error correction method for an aviation power integrated instrument controller, specifically comprising the following steps:

[0006] S1. Calculate the temperature of the controller through testing;

[0007] S2, fitting the temperature of the controller with a cubic polynomial to correct the temperature of the controller;

[0008] S3. The controller sets a display for the temperature warning of the IGBT, and sets a display when the temperature of the IGBT is too high and reaches the protection threshold.

[0009] Furthermore, it is characterized in that, in step S1, the relationship between the resistance value and temperature change of the NTC resistor built into the IGBT module is:

[0010] R T =R N exp[B(1 / T-1 / T N )] (1)

[0011] In formula (1), R TIndicates the resistance of the NTC thermistor at temperature T; T indicates the temperature of the controller; T N Indicates rated temperature; R N Indicates that at rated temperature T N The resistance value of the NTC thermistor at this time; B represents the material constant of the NTC thermistor;

[0012] Formula (1) is an empirical formula. The material constant B itself is also a function of temperature T, where T and T N It refers to K degree, that is, Kelvin temperature. Formula (2) is derived from formula (1):

[0013]

[0014] There are two main parameters of NTC thermistor: nominal resistance R 25 , they are at standard temperature 25℃T 25 =273.15+25℃=298.15K resistance and constant B 25100 , using these parameters, equations (3) and (4) can be calculated:

[0015]

[0016] NTC's B 25100 The constant can be determined by measuring the resistance at two different temperatures T1 and T2; knowing the corresponding resistances R1 and R2 the constant can be calculated as follows:

[0017]

[0018] U1 is a constant voltage power supply, and the resistance value of R1 is selected according to the limited power. R After the value is calculated, R T The value of is shown in formula (6).

[0019]

[0020] Further, in step S2, the temperature of the controller is fitted using a cubic polynomial, including the following steps:

[0021] Read the temperature parameter value from the CAN bus, convert the hexadecimal value into decimal, and substitute it into the formula

[0022] T 拟合 =aN 十进制 3 +bN 十进制 2 +cN 十进制 +d (7)

[0023] Get the temperature of the controller IGBT expressed in degrees Celsius, where T拟合 The corrected controller temperature displayed on the instrument, expressed in degrees Celsius, N 十进制 is the controller temperature parameter value read from the CAN bus, expressed in decimal, where a, b, c, and d are polynomial coefficients and constants.

[0024] Furthermore, in step S3, the controller displays the temperature warning of the IGBT in the following steps:

[0025] When the IGBT temperature reaches 87% of the protection value, the controller temperature bar corresponding to the power display instrument should flash yellow as a warning. The pilot should immediately reduce the throttle to reduce the output power of the controller.

[0026] Furthermore, in step S3, the controller displays the temperature of the IGBT when it reaches the protection threshold, including the following steps:

[0027] When the motor temperature reaches the protective shutdown temperature, the controller temperature bar corresponding to the power display instrument should flash red.

[0028] The present invention can achieve the following technical effects:

[0029] The invention has a simple principle and is easy to implement. It corrects the error between the displayed temperature value and the actual value, overcomes the error problem of the display of the existing electric aircraft power integrated instrument, and improves the flight efficiency and safety of the pilot.

[0030] The alarm error correction method of the aviation power integrated instrument controller provided by the present invention has the key core of correcting the display and alarm errors of the aviation power integrated instrument, thereby improving the efficiency and safety of the electric aircraft flight. Then the key core of correcting the display and alarm errors of the aviation power integrated instrument is to use the variability of the thermistor (NTC) of the IGBT module to accurately measure the temperature, and use a cubic polynomial to fit the temperature of the controller; the controller reasonably sets the display of the temperature warning of the IGBT; the controller displays and sets when the temperature of the IGBT is too high and reaches the protection threshold. Therefore, the display and alarm error correction of the aviation power integrated instrument can be realized, so that the display value of the power integrated instrument is basically consistent with the actual value. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 A specific flow chart of the method of the present invention;

[0032] Figure 2 A dual IGBT module diagram in an embodiment of the present invention;

[0033] Figure 3 is a temperature measurement circuit diagram in an embodiment of the present invention;

[0034] Figure 4 is a curve diagram of the actual measured value and the fitted value of the controller temperature in an embodiment of the present invention;

[0035] Figure 5 The present invention is a method flow chart of the method. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation of the present invention.

[0037] refer to Figure 1-5 , the alarm error correction method of the aviation power integrated instrument controller specifically includes the following steps:

[0038] S1. Calculate the temperature of the controller through testing;

[0039] Furthermore, in step S1, the relationship between the resistance value and temperature change of the NTC resistor built into the IGBT module is:

[0040] R T =R N exp[B(1 / T-1 / T N )] (1)

[0041] In formula (1), R T Indicates the resistance of the NTC thermistor at temperature T; T indicates the temperature of the controller; T N Indicates rated temperature; R N Indicates that at rated temperature T N The resistance value of the NTC thermistor when ; B represents the material constant of the NTC thermistor, also called the thermal index; exp represents the exponent (function) with the natural number e as the base (e = 2.71828L);

[0042] Formula (1) is an empirical formula and is only valid at rated temperature T N Or rated resistance R N The accuracy is limited to a certain range because the material constant B itself is also a function of temperature T, where T and T N K refers to Kelvin temperature, K = 273.15 (absolute temperature) + Celsius. Formula (2) is derived from formula (1):

[0043]

[0044] There are two main parameters of NTC thermistor: nominal resistance R 25 , they are at standard temperature 25℃(T 25=273.15+25℃=298.15K) and its constant B 25100 , which somehow expresses the "temperature coefficient"; using these parameters, equations (3) and (4) can be calculated:

[0045]

[0046] NTC's B 25100 The constant can be determined by measuring the resistance at two different temperatures T1 and T2; knowing the corresponding resistances R1 and R2 the constant can be calculated as follows:

[0047]

[0048] Figure 2 It is a temperature measurement circuit, where U1 is a constant voltage power supply, and the resistance value of R1 is selected according to the limited power (the table requires no more than 20mW). R After the value is calculated, R T The value of is shown in formula (6).

[0049]

[0050] Further, in step S2, the temperature of the controller is fitted using a cubic polynomial, including the following steps:

[0051] The temperature-value curve of the controller is measured through temperature test, and the curve can be fitted by cubic polynomial.

[0052] Read the temperature parameter value of 0x4a from the CAN bus, convert the hexadecimal value into decimal, and substitute it into the formula

[0053] T 拟合 =aN 十进制 3 +bN 十进制 2 +cN 十进制 +d (7)

[0054] Get the temperature of the controller IGBT expressed in degrees Celsius, where T 拟合 The corrected controller temperature displayed on the instrument, expressed in degrees Celsius, N 十进制 is the controller temperature parameter value read from the CAN bus, expressed in decimal. a, b, c, d are polynomial coefficients, which are constants. They are different for each controller, and the number of effective digits needs to be 10-15 digits.

[0055] For example, for a certain controller, the calculation formula is known to be y = 0.000000000109026x3-0.000007129711980x2+0.163051991370739x-1,235.426309155500000. When the decimal temperature parameter value read is N 十进制 The temperature value displayed on the instrument can be calculated.

[0056] S3. The controller sets a display for a temperature warning of an insulated gate bipolar transistor (IGBT), and sets a display when the temperature of the IGBT is too high and reaches a protection threshold.

[0057] Furthermore, in step S3, the controller displays the temperature warning of the IGBT in the following steps:

[0058] When the IGBT temperature protection value reaches 87%, the 23rd bit (bit23) of 0x8f will jump from a value of 0 to a value of 1. At this time, the controller temperature bar corresponding to the power display instrument should flash yellow as a warning. The pilot should immediately reduce the throttle to reduce the output power of the controller.

[0059] Furthermore, in step S3, the controller displays the temperature of the IGBT when it reaches the protection threshold, including the following steps:

[0060] When the temperature reaches the protective shutdown level, bit 7 of 0x8f will jump from a value of 0 to a value of 1. At this time, the controller temperature bar corresponding to the power display instrument should flash red.

[0061] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0062] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and cannot be understood as limiting the present invention. Those skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

[0063] The above specific implementations of the present invention do not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and modifications made based on the technical concept of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. An alarm error correction method for an aviation power integrated instrument controller, characterized in that: The specific steps include: S1. Calculate the temperature of the controller through testing; S2, fitting the temperature of the controller with a cubic polynomial to correct the temperature of the controller; S3. The controller sets a display for the temperature warning of the IGBT, and sets a display when the temperature of the IGBT is too high and reaches the protection threshold.

2. The alarm error correction method of the aviation power integrated instrument controller according to claim 1 is characterized in that: In step S1, the relationship between the resistance value and temperature change of the NTC resistor built into the IGBT module is: R T =R N exp[B(1 / T-1 / T N )] (1) In formula (1), R T Indicates the resistance of the NTC thermistor at temperature T; T indicates the temperature of the controller; T N Indicates rated temperature; R N Indicates that at rated temperature T N The resistance value of the NTC thermistor at this time; B represents the material constant of the NTC thermistor; Formula (1) is an empirical formula. The material constant B itself is also a function of temperature T, where T and T N It refers to K degree, that is, Kelvin temperature. Formula (2) is derived from formula (1): There are two main parameters of NTC thermistor: nominal resistance R 25 , they are at standard temperature 25℃T 25 =273.15+25℃=298.15K resistance and its constant B 25100 , using these parameters, equations (3) and (4) can be calculated: NTC's B 25100 The constant can be determined by measuring the resistance at two different temperatures T1 and T2; knowing the corresponding resistances R1 and R2 the constant can be calculated as follows: According to the temperature measurement circuit, U1 is a constant voltage power supply, and the resistance value of R1 is selected according to the limited power to measure U R After the value is calculated, R T The value of is shown in formula (6).

3. The alarm error correction method of the aviation power integrated instrument controller according to claim 2 is characterized in that: In step S2, the temperature of the controller is fitted using a cubic polynomial, including the following steps: Read the temperature parameter value from the CAN bus, convert the hexadecimal value into decimal, and substitute it into the formula T 拟合 =aN 十进制 3 +bN 十进制 2 +cN 十进制 +d (7) Get the temperature of the controller IGBT expressed in degrees Celsius, where T 拟合 The corrected controller temperature displayed on the instrument, expressed in degrees Celsius, N 十进制 is the controller temperature parameter value read from the CAN bus, expressed in decimal, where a, b, c, and d are polynomial coefficients and constants.

4. The alarm error correction method of the aviation power integrated instrument controller according to claim 1 is characterized in that: In step S3, the controller displays the temperature warning of the IGBT, including the following steps: When the IGBT temperature reaches 87% of the protection value, the controller temperature bar corresponding to the power display instrument should flash yellow as a warning. The pilot should immediately reduce the throttle to reduce the output power of the controller.

5. The alarm error correction method of the aviation power integrated instrument controller according to claim 1 is characterized in that: In step S3, the controller displays the temperature of the IGBT when it reaches the protection threshold, including the following steps: When the motor temperature reaches the protective shutdown temperature, the controller temperature bar corresponding to the power display instrument should flash red.

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