An aircraft power supply parameter correction method for realizing full temperature range

Abstract

This invention discloses a method for correcting aircraft power parameters across the entire temperature range, belonging to the field of parameter acquisition and processing technology. The method continuously divides the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments, calculates multiple sets of correction coefficients corresponding to the nodes of each temperature segment, and then uses linear interpolation to calculate the current temperature correction coefficient based on the current temperature value and the corresponding set of correction coefficients, thus achieving correction across the entire temperature range. Finally, the output voltage value is obtained using the formula for calculating the final output voltage value of the power parameter acquisition and processing system. This ensures that the power parameter values ​​calculated by the aircraft power parameter acquisition and processing system are smooth, and the output value does not jump at temperature critical points, enabling high-precision data acquisition and calculation.

Description

Technical Field

[0001] This invention relates to the field of parameter acquisition and processing technology, and in particular to a method for correcting aircraft power parameters across the entire temperature range. Background Technology

[0002] The aircraft power parameter acquisition and processing system is mainly used to collect power system parameters such as the three-phase current / voltage / frequency of the left / right AC generator A / B / C phases, the three-phase current / voltage / frequency of the auxiliary AC generator A / B / C phases, the current / voltage of the DC generator, the current / voltage of the auxiliary DC generator, and the current / voltage of the battery. After processing the collected power system parameters, the system sends them to the display via RS422 bus format for display, and simultaneously to the flight parameter recording system via ARINC429 bus format.

[0003] In the process of processing aircraft power parameters, due to the temperature drift of electronic components, the power parameters acquired and output will differ from the actual input power parameters under different temperature environments. Therefore, temperature correction of the parameters is essential. Currently, the most common temperature correction method is three-segment linear fitting correction. This involves dividing the temperature range into three segments: low temperature, normal temperature, and high temperature. A temperature sensor is used to determine which segment the current temperature falls into, and then the correction coefficient for that segment is read to calculate the corrected parameter value. For example, if the current temperature is determined to be normal temperature, the normal temperature correction coefficient is read. K 常 , B 常 The collected voltage is U 采 The final output voltage value is U = K 常 U 采 + B 常 The advantages of this method are its simplicity in calculation and small capacity requirement for the memory chip. However, due to the different correction coefficients for the two temperature ranges, the correction value calculated by this temperature correction method will jump at the critical point between the two temperature ranges. Summary of the Invention

[0004] To address the aforementioned shortcomings of existing technologies, this invention provides a method for correcting aircraft power parameters across the entire temperature range, solving the problem that the correction values ​​calculated by existing temperature correction methods jump at the critical points between two temperature ranges.

[0005] To achieve the above-mentioned objectives, the technical solution adopted by this invention is as follows:

[0006] A method for correcting aircraft power parameters across the entire temperature range is provided, comprising:

[0007] Step 1: Divide the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments.

[0008] Step 2: Place the aircraft power parameter acquisition and processing system in multiple temperature chambers, with the temperatures of the multiple temperature chambers representing nodes of multiple temperature segments.

[0009] Step 3: After the temperatures of multiple temperature chambers have stabilized, adjust the settings according to the actual input power supply parameters. U 实 Parameters collected by the power parameter acquisition and processing system U 采 Calculate multiple sets of correction coefficients corresponding to the nodes of multiple temperature segments;

[0010] Step 4: Write the calculated correction coefficients into the storage chip of the power parameter acquisition and processing system;

[0011] Step 5: When processing power system parameters, the power parameter acquisition and processing system converts temperature information into temperature-voltage signals and calculates the current temperature value based on the temperature-voltage signals.

[0012] Step 6: The power parameter acquisition and processing system calculates the current temperature correction factor based on the current temperature value and a set of correction factors corresponding to the current temperature, and outputs the final voltage value based on the current temperature correction factor.

[0013] Furthermore, in step 1, the operating temperature range of the aircraft power parameter acquisition and processing system is -55℃ to 85℃, and the number of temperature segments is 4, namely -55℃ to -20℃, -20℃ to 15℃, 15℃ to 50℃ and 50℃ to 85℃.

[0014] Furthermore, in step 2, the nodes of the multiple temperature segments are -55℃, -20℃, 15℃, 50℃ and 85℃, and there are 5 temperature chambers, with temperatures of -55℃, -20℃, 15℃, 50℃ and 85℃ respectively.

[0015] Furthermore, in step 3, the number of sets of correction coefficients is 5, and the 5 sets of correction coefficients are as follows: K 1, B 1) ( K 2, B 2), ( K 3, B 3), ( K 4, B 4) and ( K 5, B 5);

[0016] The formula for calculating the correction factor is:

[0017]

[0018]

[0019] in, and This represents the correction coefficients for the power parameter acquisition and processing system at five temperature range nodes. U 实1 It is the actual input voltage at the first temperature node. U 实2 It is the actual input voltage at the second temperature node; U 采1 The voltage was collected at the first temperature node. U 采2 The voltage was collected at the second temperature node; i The values ​​are 1, 2, 3, 4, and 5.

[0020] Furthermore, in step 6, the method for calculating the current temperature correction factor based on the current temperature value and a set of correction factors corresponding to the current temperature value includes:

[0021] If the current temperature value T =-55℃, then K = K 1, B = B 1;

[0022] If the current temperature value T ∈ (-55℃, -20℃), then , , T 1 and T 2 are -55℃ and -20℃ respectively;

[0023] If the current temperature value T =-20℃, then K = K 2, B = B 2;

[0024] If the current temperature value T ∈ (-20℃, 15℃), then , , T 2 and T 3 are -20℃ and 15℃ respectively;

[0025] If the current temperature value T =15℃, then K = K 3, B= B 3;

[0026] If the current temperature value T ∈ (15℃, 50℃), then , , T 3 and T 4 represents 15℃ and 50℃ respectively;

[0027] If the current temperature value T =50℃, then K = K 4, B = B 4;

[0028] If the current temperature value T ∈ (50℃, 85℃), then , , T 4 and T 5 represents 50℃ and 85℃ respectively;

[0029] If the current temperature value T =85℃, then K = K 5, B = B 5.

[0030] Furthermore, in step 6, the formula for calculating the final voltage value output by the power parameter acquisition and processing system is as follows:

[0031] V = KV 采 + B

[0032] in, V The power parameter acquisition and processing system outputs the final voltage value. K and B All are temperature correction factors; V 采 This refers to the actual voltage value acquired by the power parameter acquisition and processing system.

[0033] Furthermore, in step 5, the power parameter acquisition and processing system is equipped with a temperature sensor, a platinum resistance thermometer, a temperature calculation circuit, and an A / D conversion circuit.

[0034] The beneficial effects of this invention are as follows: Compared with the temperature correction methods in the prior art, the aircraft power parameter correction method in this solution, which realizes the correction of aircraft power parameters across the entire temperature range, continuously divides the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments, and uses linear interpolation to calculate the temperature correction coefficient corresponding to each temperature point in the temperature segment, thereby realizing the correction of the entire temperature range. This ensures that the power parameter values ​​finally calculated by the aircraft power parameter acquisition and processing system are smooth, and the output values ​​will not jump at the temperature critical point, enabling high-precision data acquisition and calculation. Attached Figure Description

[0035] Figure 1 This is a flowchart of a method for correcting aircraft power parameters across the entire temperature range.

[0036] Figure 2 This is the circuit diagram for the temperature calculation circuit.

[0037] Figure 3 This is a circuit diagram of an A / D conversion circuit. Detailed Implementation

[0038] The specific embodiments of the present invention are described below to enable those skilled in the art to understand the present invention. However, it should be understood that the present invention is not limited to the scope of the specific embodiments. For those skilled in the art, various changes are obvious as long as they are within the spirit and scope of the present invention as defined and determined by the appended claims. All inventions utilizing the concept of the present invention are protected.

[0039] like Figure 1 As shown, the present invention provides a method for correcting aircraft power parameters across the entire temperature range, comprising:

[0040] Step 1: Divide the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments. In actual use, more temperature segments can be divided; the more segments, the higher the accuracy, but the larger the required hardware storage space, the higher the cost, and the longer the product debugging time. Considering the allowable error range, economic cost, and time cost of the aircraft power parameter acquisition and processing system, this invention divides the temperature segments into four segments: -55℃ to -20℃, -20℃ to 15℃, 15℃ to 50℃, and 50℃ to 85℃.

[0041] Step 2: Place the aircraft power parameter acquisition and processing system in multiple temperature chambers. The temperatures of the multiple temperature chambers are nodes of multiple temperature segments. Specifically, the nodes of the multiple temperature segments are -55℃, -20℃, 15℃, 50℃ and 85℃. There are 5 temperature chambers, and the temperatures of the 5 temperature chambers are -55℃, -20℃, 15℃, 50℃ and 85℃ respectively.

[0042] Step 3: After the temperatures of multiple temperature chambers have stabilized, adjust the settings according to the actual input power supply parameters. U 实 Parameters collected by the power parameter acquisition and processing system U 采 Calculate multiple sets of correction coefficients corresponding to the nodes of multiple temperature segments; in step 3, the number of sets of correction coefficients is 5, and the 5 sets of correction coefficients are as follows ( K 1, B 1) ( K 2, B 2), ( K 3, B 3), ( K 4, B 4) and ( K 5, B 5);

[0043] The formula for calculating the correction factor is:

[0044]

[0045]

[0046] in, and This represents the correction coefficients for the power parameter acquisition and processing system at five temperature range nodes. U 实1 It is the actual input voltage at the first temperature node. U 实2 It is the actual input voltage at the second temperature node; U 采1 The voltage was collected at the first temperature node. U 采2 The voltage was collected at the second temperature node; i The values ​​are 1, 2, 3, 4, and 5.

[0047] by T Taking the voltage value collected at -55℃ as an example, if U 实1 =10V U 采1 =10.5V; U 实2 =20V, U 采2 =21V, then calculate , The same principle applies to the remaining temperature range nodes, resulting in 5 sets of correction factors ( K 1, B 1) (K 2, B 2), ( K 3, B 3), ( K 4, B 4) and ( K 5, B 5).

[0048] Step 4: Write the calculated correction coefficients into the storage chip of the power parameter acquisition and processing system;

[0049] Step 5: When processing power system parameters, the power parameter acquisition and processing system converts temperature information into temperature-voltage signals and calculates the current temperature value based on the temperature-voltage signals.

[0050] Specifically, the power parameter acquisition and processing system includes a temperature sensor, a platinum resistance thermometer, a temperature calculation circuit, and an A / D conversion circuit. For example... Figure 2 and Figure 3 As shown, in the temperature calculation circuit, the voltage drop across the PN junction of diode V1 changes linearly with temperature. This voltage drop is amplified to obtain the temperature voltage VTEMP. VTEMP is then sent to the A / D conversion circuit to obtain the temperature voltage signal. Finally, the central processing chip (CPU) calculates the current temperature value based on the temperature voltage signal. T .

[0051] Step 6: The power parameter acquisition and processing system calculates the current temperature correction factor based on the current temperature value and a set of correction factors corresponding to the current temperature, and outputs the final voltage value based on the current temperature correction factor.

[0052] Specifically, the temperature correction coefficient corresponding to each temperature node in the temperature range is calculated using linear interpolation, thus achieving correction for the entire temperature range.

[0053] The detailed calculation method is as follows:

[0054] If the current temperature value T =-55℃, then K = K 1, B = B 1;

[0055] If the current temperature value T ∈ (-55℃, -20℃), then , , T 1 and T 2 are -55℃ and -20℃ respectively;

[0056] If the current temperature value T =-20℃, thenK = K 2, B = B 2;

[0057] If the current temperature value T ∈ (-20℃, 15℃), then , , T 2 and T 3 are -20℃ and 15℃ respectively;

[0058] If the current temperature value T =15℃, then K = K 3, B = B 3;

[0059] If the current temperature value T ∈ (15℃, 50℃), then , , T 3 and T 4 represents 15℃ and 50℃ respectively;

[0060] If the current temperature value T =50℃, then K = K 4, B = B 4;

[0061] If the current temperature value T ∈ (50℃, 85℃), then , , T 4 and T 5 represents 50℃ and 85℃ respectively;

[0062] If the current temperature value T =85℃, then K = K 5, B = B 5.

[0063] Specifically, the formula for calculating the final voltage value output by the power parameter acquisition and processing system is as follows:

[0064] V = KV 采 + B

[0065] in, V The power parameter acquisition and processing system outputs the final voltage value. K and B All are temperature correction factors;V 采 This refers to the actual voltage value acquired by the power parameter acquisition and processing system.

[0066] In summary, compared with existing temperature correction methods, the proposed method for correcting aircraft power parameters across the entire temperature range divides the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments. By using linear interpolation to calculate the temperature correction coefficient for each temperature point within a segment, the method achieves correction across the entire temperature range. This ensures that the final calculated power parameter values ​​from the aircraft power parameter acquisition and processing system are smooth, and the output values ​​do not jump at temperature critical points, enabling high-precision data acquisition and calculation.

Claims

1. A method for correcting aircraft power parameters across the entire temperature range, characterized in that, include: Step 1: Divide the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments. Step 2: Place the aircraft power parameter acquisition and processing system in multiple temperature chambers, with the temperatures of the multiple temperature chambers representing nodes of multiple temperature segments. Step 3: After the temperatures of multiple temperature chambers have stabilized, adjust the settings according to the actual input power supply parameters. U 实 Parameters collected by the power parameter acquisition and processing system U 采 Calculate multiple sets of correction coefficients corresponding to the nodes of multiple temperature segments; In step 3, there are 5 sets of correction coefficients, and the 5 sets of correction coefficients are as follows: K 1, B 1), ( K 2, B 2), ( K 3, B 3), ( K 4, B 4) and ( K 5, B 5); The formula for calculating the correction factor is: in, and This represents the correction coefficients for the power parameter acquisition and processing system at five temperature range nodes. U 实1 It is the actual input voltage at the first temperature node. U 实2 It is the actual input voltage at the second temperature node; U 采1 The voltage was collected at the first temperature node. U 采2 The voltage was collected at the second temperature node; i The values ​​are 1, 2, 3, 4, and 5. Step 4: Write the calculated correction coefficients into the storage chip of the power parameter acquisition and processing system; Step 5: When processing power system parameters, the power parameter acquisition and processing system converts temperature information into temperature-voltage signals and calculates the current temperature value based on the temperature-voltage signals. Step 6: The power parameter acquisition and processing system calculates the current temperature correction coefficient based on the current temperature value and a set of correction coefficients corresponding to the current temperature, and outputs the final voltage value based on the current temperature correction coefficient. In Step 6, the method for calculating the current temperature correction coefficient based on the current temperature value and a set of correction coefficients corresponding to the current temperature includes: If the current temperature value T =-55℃, then K = K 1, B = B 1; If the current temperature value T ∈ (-55℃, -20℃), then , , T 1 and T 2 are -55℃ and -20℃ respectively; If the current temperature value T =-20℃, then K = K 2, B = B 2; If the current temperature value T ∈ (-20℃, 15℃), then , , T 2 and T 3 are -20℃ and 15℃ respectively; If the current temperature value T =15℃, then K = K 3, B = B 3; If the current temperature value T ∈ (15℃, 50℃), then , , T 3 and T 4 represents 15℃ and 50℃ respectively; If the current temperature value T =50℃, then K = K 4, B = B 4; If the current temperature value T ∈ (50℃, 85℃), then , , T 4 and T 5 represents 50℃ and 85℃ respectively; If the current temperature value T =85℃, then K = K 5, B = B 5.

2. The method for correcting aircraft power parameters across the entire temperature range according to claim 1, characterized in that, In step 1, the operating temperature range of the aircraft power parameter acquisition and processing system is -55℃ to 85℃, with four temperature segments: -55℃ to -20℃, -20℃ to 15℃, 15℃ to 50℃, and 50℃ to 85℃.

3. The method for correcting aircraft power parameters across the entire temperature range according to claim 2, characterized in that, In step 2, the nodes of the multiple temperature segments are -55℃, -20℃, 15℃, 50℃ and 85℃, and there are 5 temperature chambers with temperatures of -55℃, -20℃, 15℃, 50℃ and 85℃ respectively.

4. The method for correcting aircraft power parameters across the entire temperature range according to claim 3, characterized in that, In step 6, the formula for calculating the final voltage value output by the power parameter acquisition and processing system is as follows: V = KV 采 + B in, V The power parameter acquisition and processing system outputs the final voltage value. K and B All are temperature correction factors; V 采 This refers to the actual voltage value acquired by the power parameter acquisition and processing system.

5. The method for correcting aircraft power parameters across the entire temperature range according to claim 4, characterized in that, In step 5, the power parameter acquisition and processing system is equipped with a temperature sensor, a platinum resistance thermometer, a temperature calculation circuit, and an A / D conversion circuit.

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