CN112763911B - Power calculation and filtering method for aircraft electric load power supply - Google Patents
Power calculation and filtering method for aircraft electric load power supply Download PDFInfo
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- CN112763911B CN112763911B CN202011641567.9A CN202011641567A CN112763911B CN 112763911 B CN112763911 B CN 112763911B CN 202011641567 A CN202011641567 A CN 202011641567A CN 112763911 B CN112763911 B CN 112763911B
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- 238000001914 filtration Methods 0.000 title claims abstract description 62
- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000004364 calculation method Methods 0.000 title claims abstract description 34
- 238000012544 monitoring process Methods 0.000 claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 15
- 230000008569 process Effects 0.000 claims description 10
- 230000002457 bidirectional effect Effects 0.000 claims description 8
- 238000004088 simulation Methods 0.000 claims description 5
- 238000007599 discharging Methods 0.000 claims description 4
- 238000010248 power generation Methods 0.000 claims description 2
- 230000002035 prolonged effect Effects 0.000 claims description 2
- 238000007493 shaping process Methods 0.000 abstract description 3
- 230000009466 transformation Effects 0.000 abstract description 3
- 238000004422 calculation algorithm Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 4
- 238000011217 control strategy Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
- G01R31/343—Testing dynamo-electric machines in operation
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/10—Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
- H02P9/10—Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
- H02P9/107—Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load for limiting effects of overloads
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P2101/00—Special adaptation of control arrangements for generators
- H02P2101/30—Special adaptation of control arrangements for generators for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E40/00—Technologies for an efficient electrical power generation, transmission or distribution
- Y02E40/40—Arrangements for reducing harmonics
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Supply And Distribution Of Alternating Current (AREA)
Abstract
The invention relates to a power calculation and filtering method for an aircraft electric load power supply. The invention relates to the technical field of simulated electric loads of airplane shaping test subjects; collecting voltage and current information of an aircraft generator, and determining real-time power; filtering and tracking the current according to the real-time power; the output of the compensation power calculation module is provided for the contactor execution module, and the execution module outputs a contactor control command; the control module reads the power monitoring result and feeds back the power monitoring result to the processor, and simultaneously receives the commands of the processor and an external unloading switch, so that the analog electric load is ready to be interrupted at any time. The invention adopts a strategy of tracking current, the core of the power output of the generator is current, and the voltage directly influences the power, but when different currents are output, different transformation can occur due to line loss. In addition, due to the three-phase unbalance of the alternating current, the current tracking can follow the characteristics of the generator, and the three-phase unbalance is effectively restrained.
Description
Technical Field
The invention relates to the technical field of aircraft shaping test subjects simulation electric loads, in particular to a method for calculating and filtering power of an aircraft electric load power supply.
Background
The generator is the core power source of the aircraft and is also the highest priority power supply equipment on the aircraft. The test of the aircraft generator is an indispensable link in the test flight shaping of the aircraft. Because the electric power consumed by the electric equipment on the aircraft is less in the actual test flight process, the test flight requirements of high load and full load of a single generator are difficult to meet, and therefore, a set of simulation electric load system is required to be designed for enabling the output power of the generator of the power supply system of the aircraft to reach a specific state so as to meet the requirements of partial test flight subjects. The simulated electric load system automatically configures the external load quantity, and ensures that the generator is maintained at a specific target loading value under the condition of load change of the aircraft body, so that the test of the working state of the designated power point of the generator is realized. The principle of equivalent configuration of the simulated electrical load is shown in fig. 1; the control cabinet monitors the output power of the aircraft generator, performs processing such as filtering and the like, and calculates and tracks the state of the contactor according to a control strategy. And outputting control signals to the contactor module to switch on loads with different powers to enter the aircraft power supply system.
The design difficulty of the analog electric load system is that the amplitude of the load fluctuation of the airplane body is large, the frequency is high and the tracking difficulty is high in the airplane flight process; and secondly, the simulation electric load directly influences the power supply safety of the aircraft, and the risk of the flying subjects is high.
Disclosure of Invention
The invention provides a filtering algorithm for calculating power supply power of an airplane in order to ensure that the load of a power system is stabilized at a preset value in the process of airplane test flight and realize optimal tracking speed under different states.
An aircraft electrical load power calculation filtering method, the method being based on an analog electrical load automatic load shedding system, the system comprising: the power monitoring module, the compensation power calculation module, the contactor execution module and the control module comprise the following steps:
Step 1: collecting voltage and current information of an aircraft generator, and determining real-time power;
Step 2: filtering and tracking the current according to the real-time power;
Step 3: the output of the compensation power calculation module is provided for the contactor execution module, and the execution module outputs a contactor control command;
Step 4: the control module reads the power monitoring result and feeds back the power monitoring result to the processor, and simultaneously receives the commands of the processor and an external unloading switch, so that the analog electric load is ready to be interrupted at any time.
Preferably, the required target loading capacity is set, the current total loading capacity of the aircraft is calculated according to real-time data obtained by the voltage and current sensors in the load test unit, the target loading capacity and the current loading capacity are differed by a negative feedback method, a difference result is used as input of a load control system, the control system realizes automatic loading and unloading of equal power until the difference value between the current loading capacity and the target loading capacity is within a margin range delta, and finally the total loading capacity of the generator is maintained at a preset value.
Preferably, the bidirectional RC filtering method adopts different filtering circuits in the directions of increasing or decreasing the load of the airplane body, the RC filtering is similar to an RC filtering circuit in an analog circuit, and the function of the RC filtering is equivalent to a formula of digital calculation in the filter, so that the digitization of all the controls is realized.
Preferably, the filtering method executes different filtering modes, and the specific filtering process is as follows: when the power of the aircraft is monitored within the upper limit and the lower limit, RC filter parameters with approximate average values are selected to adapt to the frequent jump characteristic of the power grid of the aircraft, so that the tracking stability is ensured, the switching times of contactors are reduced, and the service life of a system is prolonged;
When the power is monitored to break through the upper limit value and reach a certain period of time, switching to quickly track RC filter parameters so as to reduce the load of the generator and prevent the generator from actively discharging due to overload;
When the power is monitored to break through the lower limit value and reach a certain period of time, the control circuit is switched to slowly track the RC filter parameters, so that the power of the generator steadily increases to a target value between the upper limit value and the lower limit value, and the slowly increasing is to prevent the airplane from having a body load which is rapidly increased.
Preferably, different upper and lower values are set.
The invention has the following beneficial effects:
The FPGA-based analog electrical load system has high calculation timeliness, can ensure the control precision and the effectiveness, and can effectively improve the precision and the safety of power supply tracking. The current tracking strategy is adopted, so that the tracking efficiency and the tracking precision are higher, the core of the power output of the generator is current, and the voltage directly influences the power, but when different currents are output, different changes can occur due to line loss. In addition, because of the three-phase unbalance of the alternating current, the current tracking can follow the characteristics of the generator, and the three-phase unbalance is effectively restrained. The bidirectional RC filter algorithm is based on the advantages of a digital circuit, can integrate various functions which are difficult to realize in an analog circuit, and can realize the digitization of all controls by equivalent functions in the RC filter to digital calculation formulas. Three tracking filtering modes specific to the system: an average RC filter mode, a fast track RC filter mode, and a slow track RC filter mode; the average RC filter mode tracks the filtered average value so as to adapt to the frequent jump characteristic of an aircraft power grid, thereby ensuring that the switching times of a contactor can be effectively reduced during loading and unloading so as to prolong the service life of the system; the fast tracking RC filtering mode is to quickly reduce the load of the generator after detecting that the power breaks through the upper limit value and reaches a certain time length (ms precision), so as to prevent the generator from actively discharging due to overload; the slow tracking RC filtering mode is to slowly increase the load when the power breaks through the lower limit value and reaches a certain time period, so that the power of the generator steadily increases to a target value between the upper limit range and the lower limit range, and the slow increase is to prevent the airplane from having a body load which is rapidly increased.
Drawings
FIG. 1 is a schematic diagram of an analog electrical load system;
FIG. 2 is a block diagram of a system load-reducing structure;
FIG. 3 is a system load shedding workflow diagram;
Fig. 4 is a flowchart of filtering mode selection.
Detailed Description
The present invention will be described in detail with reference to specific examples.
First embodiment:
In the process of development and test flight of an aircraft, an analog electric load is used for providing a third party load except for aircraft body equipment for an aircraft power supply system, and the load of the power system is ensured to be stabilized at a preset value in the process of test flight. The FPGA-based analog electrical load system has high calculation timeliness, can ensure the control precision and effectiveness, and has higher tracking precision and efficiency by adopting a tracking strategy for current; the core idea of the bidirectional RC filtering algorithm is to integrate various functions which are difficult to realize in an analog circuit by utilizing the advantages of a digital circuit, and realize the digitization of all controls by equivalent functions of the RC filter to formulas of digital calculation; the system monitors the state of the real-time power of the aircraft generator, and operates corresponding control logic according to different states, so that the load of the power system is stabilized at a set value.
According to the invention, as shown in fig. 1 to 4, the invention provides a power calculation and filtering method of an aircraft electric load power supply, which comprises the following steps:
An aircraft electrical load power calculation filtering method, the method being based on an analog electrical load automatic load shedding system, the system comprising: the power monitoring module, the compensation power calculation module, the contactor execution module and the control module comprise the following steps:
Step 1: collecting voltage and current information of an aircraft generator, and determining real-time power;
Step 2: filtering and tracking the current according to the real-time power;
Step 3: the output of the compensation power calculation module is provided for the contactor execution module, and the execution module outputs a contactor control command;
Step 4: the control module reads the power monitoring result and feeds back the power monitoring result to the processor, and simultaneously receives the commands of the processor and an external unloading switch, so that the analog electric load is ready to be interrupted at any time.
The system load-reducing and load-increasing structural block diagram is shown in fig. 2, the FPGA in the control cabinet realizes all calculation and bottom control, the CPU only provides advanced commands such as information display and starting and stopping of a user, the calculation timeliness is high by adopting the FPGA-based analog electric load system, the control precision and effectiveness can be ensured, and the power supply tracking precision and safety can be effectively improved.
Each module running in the FPGA is divided into four parts according to functions: the device comprises a power monitoring module, a compensation power calculation module, a contactor execution module and a control module; the functions of each part are as follows:
(1) The power monitoring module is used for completing acquisition of voltage and current information of the aircraft generator and calculating power in real time;
(2) Providing the power value calculated by the power monitoring module to a power compensation calculation module, wherein the module realizes filtering and current tracking; the tracking strategy of the current is adopted, so that the tracking precision and the efficiency are higher, the core of the power output of the generator is the current, and the voltage directly influences the power, but when different currents are output, different transformation can occur due to line loss; in addition, as the three phases of the alternating current are unbalanced, the current tracking can follow the characteristics of the generator, and the unbalance is effectively restrained;
(3) The output of the compensation power calculation module is provided to the contactor execution module, and the contactor control command in fig. 1 is output by the execution module;
(4) The control module reads the power monitoring result and feeds back the power monitoring result to the CPU, and simultaneously receives the commands of the CPU and an external unloading switch, so that the simulation electric load is ready to be interrupted at any time.
The system loading and unloading workflow is shown in figure 3, and the working process is as follows: firstly, setting a required target loading capacity at a software interface, calculating the current total loading capacity of the aircraft according to real-time data obtained by voltage and current sensors in a load test unit, utilizing a negative feedback principle, and taking the result as the input of a load control system, wherein the control system realizes automatic loading and unloading of equal power until the difference value between the current loading capacity and the target loading capacity is within a margin range delta, and finally, keeping the total loading capacity of the generator at a preset value.
Setting a required target loading amount, calculating the current total loading amount of the aircraft according to real-time data obtained by the voltage and current sensors in the load test unit, utilizing a negative feedback method, taking the difference between the target loading amount and the current loading amount as the input of a load control system, and realizing the automatic loading and unloading of equal power by the control system until the difference between the current loading amount and the target loading amount is within a margin range delta, and finally, keeping the total loading amount of the generator at a preset value.
The bidirectional RC filtering method adopts different filtering circuits in the directions of increasing or reducing the load of the airplane body, the RC filtering is similar to an RC filtering circuit in an analog circuit, and the function of the RC filtering is equivalent to a formula of digital calculation in the filter, so that the digitization of all the controls is realized.
The filtering method executes different filtering modes, and the specific filtering process is as follows: when the power of the aircraft is monitored within the upper limit range and the lower limit range, RC filter parameters with approximate average values are selected, so that the method is suitable for the frequent jump characteristic of the power grid of the aircraft, ensures the tracking stability, reduces the switching times of contactors, and prolongs the service life of a system;
when the power breakthrough upper limit is monitored to reach a certain time period, switching to quickly track RC filter parameters, reducing the load of the generator, and preventing the generator from actively discharging due to overload;
When the power is monitored to break through the lower limit for a certain period of time, the control circuit is switched to slowly track the RC filter parameters, so that the power of the generator steadily increases to a target value between the upper limit and the lower limit, and the slowly increasing is to prevent the airplane from having a rapidly increasing body load.
Preferably, different upper and lower values are set, for example, an upper value of 121kVA and a lower value of 115kVA for generator capacity.
The aircraft power supply power filtering algorithm is a core of the whole analog electric load control system, and in order to realize the optimal tracking speed of the power supply under different states, the adopted technical scheme is as follows: the power output core current of the aircraft generator is tracked and monitored, three different RC circuits are equivalent by utilizing the advantages of a digital circuit, and the optimal tracking speed of the power supply in different states is realized by running a bidirectional RC filtering algorithm on the FPGA.
In the simulated electric load flight subject, the aircraft generator always works near the upper and lower edges of the power generation capacity. Neither the upper limit of the capacity is exceeded nor the lower limit of the technical requirements is exceeded. The real-time power of the aircraft generator may be in three states of upper and lower limits, upper limit and lower limit, and the filtering algorithm executes different filtering modes corresponding to different states, and the filtering mode selection flow is shown in fig. 4, and the specific process is as follows: when the power of the aircraft is monitored within the upper limit range and the lower limit range, RC filter parameters with approximate average values are selected so as to adapt to the frequent jump characteristic of the power grid of the aircraft, ensure the tracking stability, reduce the switching times of contactors and prolong the service life of the system. When the power breakthrough upper limit is monitored to reach a certain time period (ms precision), the power breakthrough upper limit is switched to quickly track RC filter parameters, so that the load of the generator is quickly reduced, and the active power off of the generator due to overload is prevented. When the power is monitored to break through the lower limit for a certain period of time, the control circuit is switched to slowly track the RC filter parameters, so that the power of the generator steadily increases to a target value between the upper limit and the lower limit, and the slowly increasing is to prevent the airplane from having a rapidly increasing body load.
The control algorithm is realized based on the Field Programmable Gate Array (FPGA) design, fully utilizes the rapidity and stability of the FPGA in complete reconfiguration and hardware timing, ensures the real-time performance of the algorithm, and effectively improves the tracking precision and the safety of the power supply.
The invention adopts a strategy of tracking current, the core of the power output of the generator is current, and the voltage directly influences the power, but when different currents are output, different transformation can occur due to line loss. In addition, due to the three-phase unbalance of the alternating current, current tracking can follow the characteristics of the generator, and unbalance is effectively restrained.
The invention adopts the bidirectional RC filtering algorithm based on the advantages of the digital circuit, and can integrate various functions which are difficult to realize in the analog circuit, wherein the bidirectional filtering is that different filtering circuits are adopted in the two directions of increasing or reducing the load of the airplane body, the RC filtering is similar to the RC filtering circuit in the analog circuit, and the functions of the RC filter are equivalent to a digital calculation formula in the filter, so that the digitization of all the controls is realized.
The control strategy adopted by the invention is based on three state parameters, namely three states of possibly being between the upper line and the lower line, breaking through the upper limit and breaking through the lower limit of the real-time power of the aircraft generator. When the power of the aircraft is monitored within the upper limit range and the lower limit range, the filtering algorithm selects RC filtering parameters with approximate average values so as to adapt to the frequent jump characteristic of the power grid of the aircraft, ensure the tracking stability, reduce the switching times of contactors and prolong the service life of the system. When the power breakthrough upper limit is monitored to reach a certain time period (ms precision), the power breakthrough upper limit is switched to quickly track RC filter parameters, so that the load of the generator is quickly reduced, and the active power off of the generator due to overload is prevented. When the power is monitored to break through the lower limit for a certain period of time, the control circuit is switched to slowly track the RC filter parameters, so that the power of the generator steadily increases to a target value between the upper limit and the lower limit, and the slowly increasing is to prevent the airplane from having a rapidly increasing body load.
The above description is only a preferred implementation manner of the power calculation and filtering method of the aircraft electrical load power supply, and the protection scope of the power calculation and filtering method of the aircraft electrical load power supply is not limited to the above embodiments, and all technical solutions belonging to the concept belong to the protection scope of the invention. It should be noted that modifications and variations can be made by those skilled in the art without departing from the principles of the present invention, which is also considered to be within the scope of the present invention.
Claims (4)
1. An aircraft electrical load power supply power calculation filtering method, the method is based on an automatic load and unload realization system of an analog electrical load system based on an FPGA, and the system comprises: the system comprises an aircraft body load, an analog electric load, a power monitoring module, a compensation power calculation module, a contactor execution module and a control module; the aircraft body load and the analog electric load are respectively connected with the power monitoring module;
The power monitoring module is used for completing acquisition of voltage and current information of the aircraft generator and calculating power in real time;
Providing the power value calculated by the power monitoring module to a compensation power calculation module, wherein the module realizes filtering and current tracking; the output of the compensation power calculation module is provided for the contactor execution module, and is characterized in that: the method comprises the following steps:
Step 1: collecting voltage and current information of an aircraft generator, and determining real-time power;
Step 2: filtering and tracking the current according to the real-time power;
Step 3: the output of the compensation power calculation module is provided for the contactor execution module, and the execution module outputs a contactor control command;
Step 4: the control module reads the power monitoring result and feeds back the power monitoring result to the processor, and simultaneously receives the commands of the processor and an external unloading switch, so that the simulation electric load is ready to be interrupted at any time;
The filtering method executes different filtering modes, and the specific filtering process is as follows: when the power of the aircraft is monitored within the upper limit and the lower limit, RC filter parameters with approximate average values are selected to adapt to the frequent jump characteristic of the power grid of the aircraft, so that the tracking stability is ensured, the switching times of the contactor are reduced, and the service life is prolonged;
When the power is monitored to break through the upper limit value and reach a certain period of time, switching to quickly track RC filter parameters, quickly reducing the load of the generator, and preventing the generator from actively discharging due to overload;
When the power is monitored to break through the lower limit value and reach a certain period of time, the control circuit is switched to slowly track the RC filter parameters, so that the power of the generator steadily increases to a target value between the upper limit value and the lower limit value, and the slowly increasing is to prevent the airplane from having a body load which is rapidly increased.
2. The aircraft electrical load power calculation filtering method according to claim 1, wherein: setting a required target loading amount, calculating the current total loading amount of the aircraft according to real-time data obtained by the voltage and current sensors in the load test unit, utilizing a negative feedback method, taking the difference between the target loading amount and the current loading amount as the input of a load control system, and realizing the automatic loading and unloading of equal power by the control system until the difference between the current loading amount and the target loading amount is within a margin range delta, and finally, keeping the total loading amount of the generator at a preset value.
3. An aircraft electrical load power calculation filtering method according to claim 2, characterized in that: the bidirectional RC filtering method adopts different filtering circuits in the directions of increasing or reducing the load of the airplane body, the RC filtering is similar to an RC filtering circuit in an analog circuit, and the function of the RC filtering is equivalent to a formula of digital calculation in the filter, so that the digitization of all the controls is realized.
4. The aircraft electrical load power calculation filtering method according to claim 1, wherein: different upper limit values and lower limit values are set, the upper limit value of the power generation capacity of the generator is 121kVA, and the lower limit value is 115kVA.
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