Method for correcting aircraft power supply parameters in full temperature range

Abstract

The invention discloses an aircraft power supply parameter correction method for realizing a full temperature section, and belongs to the technical field of parameter acquisition and processing, and the aircraft power supply parameter correction method comprises the following steps: continuously dividing the working temperature range of an aircraft power supply parameter acquisition and processing system into a plurality of temperature sections; and calculating a plurality of groups of correction coefficients corresponding to the plurality of temperature section nodes, and then calculating a current temperature correction coefficient according to a current temperature value and a group of correction coefficients corresponding to the current temperature by utilizing a linear interpolation method, thereby realizing the correction of the whole temperature section. And finally, an output voltage value is obtained by using a calculation formula of a final voltage value output by the power supply parameter acquisition and processing system, so that the power supply parameter values finally calculated by the airplane power supply parameter acquisition and processing system are smooth, the output value does not jump at a temperature critical point, and relatively high-precision data acquisition and calculation can be performed.

Description

Technical Field

[0001] The present invention relates to the technical field of parameter acquisition and processing, and in particular to a method for correcting aircraft power supply parameters in a full temperature range. Background Art

[0002] The aircraft power supply parameter acquisition and processing system is mainly used to collect the aircraft left / right AC A / B / C three-phase current / voltage / frequency, auxiliary AC A / B / C three-phase current / voltage / frequency, DC generator current / voltage, auxiliary DC current / voltage, battery current / voltage and other power supply system parameters, and after processing the various parameters of the collected power supply system, send them to the display through the RS422 bus format for display, and send them to the flight parameter recording system through the ARINC429 bus format.

[0003] In the process of processing aircraft power parameters, due to the temperature drift of electronic components, the collected output power parameters will be different from the actual input power parameters under different temperature environments, so temperature correction of the parameters is essential. At present, the most common temperature correction method is three-segment linear fitting correction, which divides the temperature range into three segments: low temperature, normal temperature, and high temperature. The temperature sensor is used to determine which stage the current temperature is in, and then the correction coefficient of the current temperature segment is read to calculate the corrected parameter value. For example, if the current temperature is judged to be normal temperature, the normal temperature correction coefficient K is read. 常 , B 常 , the collected voltage is U 采 , then the final output voltage value is U=K 常 U 采 +B 常 The advantage of this method is that the calculation is simple and the required capacity of the memory chip is small. However, due to the different correction coefficients of the two temperature sections, the correction value calculated by this temperature correction method at the critical point of the two temperature sections will jump. Summary of the invention

[0004] In view of the above-mentioned deficiencies in the prior art, the present invention provides a method for correcting aircraft power supply parameters in all temperature ranges, which solves the problem that the correction value calculated by the temperature correction method in the prior art at the critical point of two temperature ranges will jump.

[0005] In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is:

[0006] A method for correcting aircraft power supply parameters in a full temperature range is provided, comprising:

[0007] Step 1, continuously dividing the operating temperature range of the aircraft power supply parameter acquisition and processing system into multiple temperature segments;

[0008] Step 2, placing the aircraft power supply parameter acquisition and processing system in a plurality of temperature boxes respectively, wherein the temperatures of the plurality of temperature boxes are nodes of a plurality of temperature sections respectively;

[0009] Step 3: After the temperatures of multiple temperature boxes are stable, input the power supply parameter value U according to the actual 实 And the parameters U collected by the power supply parameter acquisition and processing system 采 Calculate multiple groups of correction coefficients corresponding to multiple temperature segment nodes;

[0010] Step 4, writing the calculated multiple groups of correction coefficients into the storage chip of the power supply parameter acquisition and processing system;

[0011] Step 5: When the power supply parameter acquisition and processing system is performing power supply system parameters, the power supply parameter acquisition and processing system converts the temperature information into a temperature voltage signal, and calculates the current temperature value according to the temperature voltage signal;

[0012] Step 6: The power supply parameter acquisition and processing system calculates the current temperature correction coefficient according to the current temperature value and a set of correction coefficients corresponding to the current temperature, and outputs the final voltage value according to the current temperature correction coefficient.

[0013] Further, in step 1, the operating temperature range of the aircraft power supply parameter acquisition and processing system is -55°C to 85°C, the number of temperature sections is 4, and the 4 temperature sections are respectively -55°C to -20°C, -20°C to 15°C, 15°C to 50°C and 50°C to 85°C.

[0014] Furthermore, in step 2, the nodes of the multiple temperature sections are -55°C, -20°C, 15°C, 50°C and 85°C, respectively, the number of temperature boxes is 5, and the temperatures of the 5 temperature boxes are -55°C, -20°C, 15°C, 50°C and 85°C, respectively.

[0015] Further, in step 3, the number of the multiple groups of correction coefficients is 5 groups, and the 5 groups of correction coefficients are (K1, B1), (K2, B2), (K3, B3), (K4, B4) and (K5, B5);

[0016] The calculation formula of the correction factor is:

[0017]

[0018] Among them, K i and B i It is expressed as the correction coefficient of the power supply parameter acquisition and processing system at the 5 temperature segment nodes, U 实1 is the actual input voltage at the first temperature node, U 实2 is the actual input voltage at the first temperature node; U 采1is the voltage collected at the first temperature node, U 采2 is the voltage collected at the second temperature node; i takes values ​​of 1, 2, 3, 4, and 5.

[0019] Further, in step 6, the method of calculating the current temperature correction coefficient according to the current temperature value and a set of correction coefficients corresponding to the current temperature value includes:

[0020] If the current temperature value T=-55℃, then K=K1, B=B1;

[0021] If the current temperature value T∈(-55℃, -20℃), then T1 and T2 were -55°C and -20°C, respectively;

[0022] If the current temperature value T=-20℃, then K=K2, B=B2;

[0023] If the current temperature value T∈(-20℃, 15℃), then T2 and T3 were -20°C and 15°C, respectively;

[0024] If the current temperature value T=15℃, then K=K3, B=B3;

[0025] If the current temperature value T∈(15℃, 50℃), then T3 and T4 are 15°C and 50°C, respectively;

[0026] If the current temperature value T=40℃, then K=K4, B=B4;

[0027] If the current temperature value T∈(40℃, 85℃), then T4 and T5 are 40°C and 85°C, respectively;

[0028] If the current temperature value T=85°C, then K=K5, B=B5.

[0029] Furthermore, in step 6, the calculation formula for the final voltage value output by the power supply parameter acquisition and processing system is:

[0030] V=KV 采 +B

[0031] Among them, V is the final voltage value output by the power supply parameter acquisition and processing system, K and B are both temperature correction coefficients; V 采 The voltage value actually collected by the power supply parameter acquisition processing system.

[0032] Furthermore, in step 5, the power supply parameter acquisition and processing system is provided with a temperature sensor, a platinum resistor, a temperature calculation circuit and an A / D conversion circuit.

[0033] The beneficial effects of the present invention are as follows: compared with the temperature correction method in the prior art, the present invention realizes a correction method for aircraft power parameters in the full temperature range, by continuously dividing the working temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments, and using the linear interpolation method to calculate the temperature correction coefficient corresponding to each temperature point in the temperature segment, thereby realizing the correction of the full temperature segment, so that the power parameter values ​​finally calculated by the aircraft power parameter acquisition and processing system are smooth, the output value will not jump at the temperature critical point, and high-precision data acquisition calculation can be performed. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The present invention is a flow chart of a method for correcting aircraft power supply parameters in the full temperature range.

[0035] Figure 2 This is the circuit diagram of the temperature calculation circuit.

[0036] Figure 3 This is the circuit diagram of the A / D conversion circuit. DETAILED DESCRIPTION

[0037] The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0038] like Figure 1 As shown, the present invention provides a method for correcting aircraft power supply parameters in the full temperature range, which includes:

[0039] Step 1: Continuously divide the operating temperature range of the aircraft power supply parameter acquisition and processing system into multiple temperature segments; in actual use, the temperature segments can be divided into more segments, the more the temperature segments are divided, the higher the accuracy is, but the required hardware storage space is larger, the cost is higher, and the product debugging takes longer. According to the error range allowed by the aircraft power supply parameter acquisition and processing system, the economic cost, the time cost and other aspects are comprehensively considered, the temperature segment is divided into 4 segments in the present invention, and the 4 temperature segments are respectively -55℃~-20℃, -20℃~15℃, 15℃~50℃ and 50℃~85℃.

[0040] Step 2: Place the aircraft power supply parameter acquisition and processing system in multiple temperature boxes respectively, and the temperatures of the multiple temperature boxes are nodes of multiple temperature sections respectively; specifically, the nodes of the multiple temperature sections are -55°C, -20°C, 15°C, 50°C and 85°C, the number of temperature boxes is 5, and the temperatures of the 5 temperature boxes are -55°C, -20°C, 15°C, 50°C and 85°C respectively.

[0041] Step 3: After the temperatures of multiple temperature boxes are stable, input the power supply parameter value U according to the actual 实 And the parameters U collected by the power supply parameter acquisition and processing system 采 Calculate multiple groups of correction coefficients corresponding to multiple temperature segment nodes; in step 3, the number of groups of correction coefficients is 5, and the 5 groups of correction coefficients are (K1, B1), (K2, B2), (K3, B3), (K4, B4) and (K5, B5);

[0042] The calculation formula of the correction factor is:

[0043]

[0044] Among them, K i and B i It is expressed as the correction coefficient of the power supply parameter acquisition and processing system at the 5 temperature segment nodes, U 实1 is the actual input voltage at the first temperature node, U 实2 is the actual input voltage at the first temperature node; U 采1 is the voltage collected at the first temperature node, U 采2 is the voltage collected at the second temperature node; i takes values ​​of 1, 2, 3, 4, and 5.

[0045] Take the voltage value collected when T1 = -55°C as an example. 实1 =10V, U 采1 =10.5V; U 实2 =20V, U 采2 =21V, then calculate The same applies to the remaining temperature segment nodes, resulting in five sets of correction coefficients (K1, B1), (K2, B2), (K3, B3), (K4, B4) and (K5, B5).

[0046] Step 4, writing the calculated multiple groups of correction coefficients into the storage chip of the power supply parameter acquisition and processing system;

[0047] Step 5: When the power supply parameter acquisition and processing system is performing power supply system parameters, the power supply parameter acquisition and processing system converts the temperature information into a temperature voltage signal, and calculates the current temperature value according to the temperature voltage signal;

[0048] Specifically, the power supply parameter acquisition and processing system is provided with a temperature sensor, a platinum resistor, a temperature calculation circuit and an A / D conversion circuit. Figure 2 and Figure 3 As shown, in the temperature calculation circuit, the voltage drop of the diode V1 is amplified based on the principle that the voltage drop of the PN junction of the diode V1 changes linearly with the temperature to obtain the temperature voltage VTEMP, and VTEMP is sent to the A / D conversion circuit to obtain the temperature voltage signal. Finally, the central processing chip (CPU) calculates the current temperature value T based on the temperature voltage signal.

[0049] Step 6: The power supply parameter acquisition and processing system calculates the current temperature correction coefficient according to the current temperature value and a set of correction coefficients corresponding to the current temperature, and outputs the final voltage value according to the current temperature correction coefficient.

[0050] Specifically, the temperature correction coefficient corresponding to each temperature segment node in the temperature segment is calculated using the linear interpolation method, thereby achieving correction of the entire temperature segment.

[0051] The detailed calculation method is:

[0052] If the current temperature value T=-55℃, then K=K1, B=B1;

[0053] If the current temperature value T∈(-55℃, -20℃), then T1 and T2 were -55°C and -20°C, respectively;

[0054] If the current temperature value T=-20℃, then K=K2, B=B2;

[0055] If the current temperature value T∈(-20℃, 15℃), then T2 and T3 were -20°C and 15°C, respectively;

[0056] If the current temperature value T=15℃, then K=K3, B=B3;

[0057] If the current temperature value T∈(15℃, 50℃), then T3 and T4 are 15°C and 50°C, respectively;

[0058] If the current temperature value T=40℃, then K=K4, B=B4;

[0059] If the current temperature value T∈(40℃, 85℃), then T4 and T5 are 40°C and 85°C, respectively;

[0060] If the current temperature value T=85°C, then K=K5, B=B5.

[0061] Specifically, the calculation formula for the final voltage value output by the power supply parameter acquisition and processing system is:

[0062] V=KV 采 +B

[0063] Among them, V is the final voltage value output by the power supply parameter acquisition and processing system, K and B are both temperature correction coefficients; V 采 The voltage value actually collected by the power supply parameter acquisition processing system.

[0064] In summary, compared with the temperature correction method in the prior art, the present invention provides a method for correcting aircraft power parameters in the entire temperature range, by continuously dividing the operating temperature range of the aircraft power parameter acquisition and processing system into multiple temperature segments, and using a linear interpolation method to calculate the temperature correction coefficient corresponding to each temperature point in the temperature segment, thereby achieving correction in the entire temperature segment, so that the power parameter values ​​finally calculated by the aircraft power parameter acquisition and processing system are smooth, the output value will not jump at the temperature critical point, and a higher-precision data acquisition calculation can be performed.

Claims

1. A method for correcting aircraft power supply parameters in the full temperature range, characterized in that: include: Step 1, continuously dividing the operating temperature range of the aircraft power supply parameter acquisition and processing system into multiple temperature segments; Step 2, placing the aircraft power supply parameter acquisition and processing system in a plurality of temperature boxes respectively, wherein the temperatures of the plurality of temperature boxes are nodes of a plurality of temperature sections respectively; Step 3: After the temperatures of multiple temperature boxes are stable, input the power supply parameter value U according to the actual 实 And the parameters U collected by the power supply parameter acquisition and processing system 采 Calculate multiple groups of correction coefficients corresponding to multiple temperature segment nodes; Step 4, writing the calculated multiple groups of correction coefficients into the storage chip of the power supply parameter acquisition and processing system; Step 5: When the power supply parameter acquisition and processing system is performing power supply system parameters, the power supply parameter acquisition and processing system converts the temperature information into a temperature voltage signal, and calculates the current temperature value according to the temperature voltage signal; Step 6: The power supply parameter acquisition and processing system calculates the current temperature correction coefficient according to the current temperature value and a set of correction coefficients corresponding to the current temperature, and outputs the final voltage value according to the current temperature correction coefficient.

2. The method for correcting aircraft power supply parameters in all temperature ranges according to claim 1, characterized in that: In step 1, the operating temperature range of the aircraft power supply parameter acquisition and processing system is -55°C to 85°C, the number of temperature sections is 4, and the 4 temperature sections are respectively -55°C to -20°C, -20°C to 15°C, 15°C to 50°C and 50°C to 85°C.

3. The method for correcting aircraft power supply parameters in all temperature ranges according to claim 2, characterized in that: In step 2, the nodes of the multiple temperature sections are -55°C, -20°C, 15°C, 50°C and 85°C, the number of temperature boxes is 5, and the temperatures of the 5 temperature boxes are -55°C, -20°C, 15°C, 50°C and 85°C, respectively.

4. The method for correcting aircraft power supply parameters in all temperature ranges according to claim 3, characterized in that: In step 3, the number of the multiple correction coefficient groups is 5, and the 5 correction coefficient groups are (K1, B1), (K2, B2), (K3, B3), (K4, B4) and (K5, B5); The calculation formula of the correction factor is: Among them, K i and B i It is expressed as the correction coefficient of the power supply parameter acquisition and processing system at the 5 temperature segment nodes, U 实1 is the actual input voltage at the first temperature node, U 实2 is the actual input voltage at the first temperature node; U 采1 is the voltage collected at the first temperature node, U 采2 is the voltage collected at the second temperature node; i takes values ​​of 1, 2, 3, 4, and 5.

5. The method for correcting aircraft power supply parameters in all temperature ranges according to claim 4, characterized in that: In step 6, the method of calculating the current temperature correction coefficient according to the current temperature value and a set of correction coefficients corresponding to the current temperature value includes: If the current temperature value T=-55℃, then K=K1, B=B1; If the current temperature value T∈(-55℃, -20℃), then T1 and T2 were -55°C and -20°C, respectively; If the current temperature value T=-20℃, then K=K2, B=B2; If the current temperature value T∈(-20℃, 15℃), then T2 and T3 were -20°C and 15°C, respectively; If the current temperature value T=15℃, then K=K3, B=B3; If the current temperature value T∈(15℃, 50℃), then T3 and T4 are 15°C and 50°C, respectively; If the current temperature value T=40℃, then K=K4, B=B4; If the current temperature value T∈(40℃, 85℃), then T4 and T5 are 40°C and 85°C, respectively; If the current temperature value T=85°C, then K=K5, B=B5.

6. The method for correcting aircraft power supply parameters in all temperature ranges according to claim 5, characterized in that: In step 6, the calculation formula of the final voltage value output by the power supply parameter acquisition and processing system is: V=KV 采 +B Among them, V is the final voltage value output by the power supply parameter acquisition and processing system, K and B are both temperature correction coefficients; V 采 The voltage value actually collected by the power supply parameter acquisition processing system.

7. The method for correcting aircraft power supply parameters in all temperature ranges according to claim 6, characterized in that: In step 5, a temperature sensor, a platinum resistor, a temperature calculation circuit and an A / D conversion circuit are provided in the power supply parameter acquisition and processing system.

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