CN114815709A - Automatic loading and unloading method and system for improving utilization rate of airplane power supply - Google Patents
Automatic loading and unloading method and system for improving utilization rate of airplane power supply Download PDFInfo
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- CN114815709A CN114815709A CN202210544952.4A CN202210544952A CN114815709A CN 114815709 A CN114815709 A CN 114815709A CN 202210544952 A CN202210544952 A CN 202210544952A CN 114815709 A CN114815709 A CN 114815709A
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- G05B19/00—Programme-control systems
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Abstract
The invention discloses an automatic loading and unloading method and system for improving the utilization rate of an airplane power supply; the method comprises the following steps: when the aircraft power supply fails, detecting the current power supply system architecture, the power supply state, the flight stage, the control equipment state and the power supply channel; judging whether the power supply channel fails or not according to the detection result, if so, carrying out power distribution reconstruction, detecting whether the power supply channel is overloaded or not after power distribution reconstruction, and if not, directly detecting whether the power supply channel is overloaded or not; judging whether a power supply channel is overloaded or not according to the detection result, finishing the process if the power supply channel is not overloaded, and starting a load management program to finish the automatic loading and unloading of the overloaded power supply channel if the power supply channel is overloaded; and after the automatic unloading of the overload channel is completed, re-detecting and judging whether the power supply channel is invalid or not until the power supply reconfiguration of the power supply is completed. The invention improves the utilization rate and the reliability of the airplane power supply system.
Description
Technical Field
The invention belongs to the technical field of airplane power supply management, and particularly relates to an automatic loading and unloading method and system for improving the utilization rate of an airplane power supply.
Background
With the application of the multi-electric aircraft related art, the aircraft will consume more electric energy using more electrical loads. The increase in electrical loads has made aircraft power distribution systems more and more complex, while also presenting new difficulties and challenges to the load management of the aircraft. When the power supply of an aircraft power distribution system is insufficient or the fault of a load per se does not meet the power supply request, how to carry out intelligent dynamic management on the electrical load on the aircraft is a problem needing continuous research and innovation.
The multi-electrochemical process puts new requirements on two aspects of the management of the electrical load: under the conditions of power supply capacity and allowable working state, the power supply requirement of the load is met as much as possible; the motor with high power and multiple electric loads can cause the electric power to be multiplied at the moment of starting and braking, so that the fatal impact on a power grid when the multiple high-power loads are started is reduced. Therefore, it is of great research interest to develop load management studies.
The power supply system normally has the capability to supply all loads. When an aircraft power supply system or power transmission and distribution system fails, the load management system must perform electrical load management. For example, when one or even all of the main generators fail, the power system can only partially supply power. Therefore, some of the load needs to be taken off.
At present, the conventional load management is to manage loads in groups, the loads in an aircraft are divided into dozens of groups, and when a fault occurs, the loads are loaded and unloaded according to different working conditions according to the groups of the loads.
Disclosure of Invention
The invention aims to solve the technical problem of providing an automatic loading and unloading method and system for improving the utilization rate of an aircraft power supply aiming at the defects of the prior art.
In order to achieve the technical purpose, the technical scheme adopted by the invention is as follows:
an automatic loading and unloading method for improving the utilization rate of an aircraft power supply comprises the following steps:
s1: when the aircraft power supply fails, detecting the current power supply system architecture, the power supply state, the flight stage, the control equipment state and the power supply channel;
s2: judging whether the power supply channel fails according to the detection result in the S1, if so, carrying out power distribution reconstruction, detecting whether the power supply channel is overloaded or not after power distribution reconstruction, and if not, directly detecting whether the power supply channel is overloaded or not;
s3: judging whether the power supply channel is overloaded or not according to the detection result in the S2, finishing the process if the power supply channel is not overloaded, and starting a load management program to finish the automatic loading and unloading of the overloaded power supply channel if the power supply channel is overloaded;
s4: after the automatic unloading of the overload channel is completed, the process goes to the step S2, and the power supply channel is detected again and judged whether to fail.
Preferably, the load management program in S3 includes the following steps:
s3.1: determining dynamic priority setting of the aircraft load in a single-power failure, a double-power failure, an APU-only power supply, a storage battery-only power supply and an RAT-only power supply mode by using a traversal method or a knapsack transmission to form a load configuration table;
s3.2: and according to the load configuration table, combining with the power supply power limitation, setting a target function and a constraint function for switches which are not configured in the load configuration table according to the overall load management target, and completing the automatic loading and unloading of all the overload power supply channels.
Preferably, the aircraft load prioritization comprises the steps of:
s3.1.1: classifying different loads, and establishing a control equation and a power supply request equation of the electrical load; the method comprises the steps of converting the problems of load shedding and power distribution of an airplane into a multi-objective optimization problem, introducing a threshold parameter of a control switch to solve, realizing priority power supply of important loads, and dynamically setting the priority of multiple loads under a full flight envelope on the basis of a flight stage, power supply capacity and load power consumption requirements;
the basic principles for powering a load are: when the total capacity of the power supply meets the current load request, the load management should ensure that all loads are reliably powered; when the total capacity of the power supply does not meet the load request, preferentially loading a load with high priority according to the load priority and a related algorithm; when the power supply system fails and the total power supply capacity of the power supply can not guarantee the power consumption requirement of the load working normally, part of the load is unloaded according to the priority, and the power consumed by the load and the power supply power of the power supply system are matched again.
Preferably, the load management algorithm is a combination of a traditional traversal algorithm and an intelligent algorithm, and the power utilization rate is improved on the basis of reducing load loading and unloading time.
Preferably, the automatic loading and unloading of the overload power supply channel comprises the following steps:
s3.2.1: calculating current state parameters, acquiring logic control signal states, solving a power request equation, reading a Solid State Power Controller (SSPC), a contactor feedback state signal, an unloading control signal, a load override equation, a load control equation and an output negative control signal;
s3.2.2: the process of S3.2.1 is repeated until the automatic loading and unloading of all overloaded power supply channels is completed.
Preferably, the objective function of the load management algorithm is (if k is used) l Indicating whether the load is on or off at a time):
wherein the content of the first and second substances,
F l as a fault signal of the load, F l 1 denotes load failure, F l 0 indicates that the load is working normally，D l For the unload signal of the load, D l 1 indicates that the unload signal is active and no power is supplied to the load, D l 0 indicates that the unload signal is invalid; s l Is an override signal of the load, S l 1 indicates that the override signal is active (supplying power to the load), S l 0 indicates that the override signal is invalid;
indicating the priority of a certain load for a certain flight phase.
Preferably, the constraint function of the load management algorithm is:
U min ≤U b ≤U max ；
I b ≤I max ；
wherein P is l Power of the load, P s Capacity of the motor, U b Bus bar voltage, I b The bus bar current.
The invention also discloses an automatic loading and unloading system for improving the utilization rate of the airplane power supply, which at least comprises a storage and a processor; the method is characterized in that: said memory storing an executable program of the method of any of claims 1 to 7; the processor may execute an executable program for performing the method of claims 1-7.
The invention has the following beneficial effects:
the invention provides an automatic loading and unloading method and system for improving the utilization rate of an airplane power supply, which dynamically set the priority of multiple electric loads under a full flight envelope on the basis of conditions such as different flight stages, power supply capacity of the power supply, power consumption requirements of the loads and the like. When the total capacity of the power supply does not meet the load request, the load is automatically loaded and unloaded according to the load priority and the load management algorithm, and the load power supply request is met as much as possible on the premise of ensuring the power supply of the key load, so that the utilization rate of the power supply is improved.
Drawings
Fig. 1 is a flowchart of the automatic loading and unloading method for improving the utilization rate of the aircraft power supply according to the present invention.
Fig. 2 is a flowchart of a load management algorithm of an automatic loading and unloading method for improving the utilization rate of an aircraft power supply according to the present invention.
Fig. 3 is a table of load definitions in all directions of the automatic loading and unloading method for improving the utilization rate of the aircraft power supply according to the present invention.
Fig. 4 is a comparison table of the results of the load management algorithm and the intelligent algorithm of the automatic loading and unloading method for improving the utilization rate of the aircraft power supply, and the load loading time and the optimizing time of the traversal algorithm.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, an automatic loading and unloading method for improving the utilization rate of an aircraft power supply includes the following steps:
s1: when the aircraft power supply fails, detecting the current power supply system architecture, the power supply state, the flight stage, the control equipment state and the power supply channel;
s2: judging whether the power supply channel fails according to the detection result in the S1, if so, carrying out power distribution reconstruction (the power distribution reconstruction mainly changes the topological structure of a power distribution network), detecting whether the power supply channel is overloaded after the power distribution reconstruction, and if not, directly detecting whether the power supply channel is overloaded;
s3: judging whether the power supply channel is overloaded or not according to the detection result in the S2, finishing the process if the power supply channel is not overloaded, and starting a load management program to finish the automatic loading and unloading of the overloaded power supply channel if the power supply channel is overloaded;
s4: after the automatic unloading of the overload channel is completed, the process goes to the step S2, and the power supply channel is detected again and judged whether to fail.
Referring to fig. 2, in a specific implementation, the load management program in S3 includes the following steps:
s3.1: determining dynamic priority setting of the aircraft load in a single-power failure, a double-power failure, an APU-only power supply, a storage battery-only power supply and an RAT-only power supply mode by using a traversal method or a knapsack transmission to form a load configuration table;
s3.2: and according to the load configuration table, combining with the power supply power limitation, setting a target function and a constraint function for switches which are not configured in the load configuration table according to the overall load management target, and completing the automatic loading and unloading of all the overload power supply channels.
In specific implementation, the setting of the aircraft load priority comprises the following steps:
s3.1.1: classifying different loads, and establishing a control equation and a power supply request equation of the electrical load; the method comprises the steps of converting the problems of load shedding and power distribution of an airplane into a multi-objective optimization problem, introducing a threshold parameter of a control switch to solve, realizing priority power supply of important loads, and dynamically setting the priority of multiple loads under a full flight envelope on the basis of a flight stage, power supply capacity and load power consumption requirements; referring to fig. 3, a table of results of load priority configuration for a model of aircraft is shown.
The basic principle of supplying power to a load is as follows: when the total capacity of the power supply meets the current load request, the load management should ensure that all loads are reliably powered; when the total capacity of the power supply does not meet the load request, preferentially loading a load with high priority according to the load priority and a related algorithm, and meeting the load power supply request as much as possible on the premise of ensuring the power supply of a key load; when the power supply system fails and the total power supply capacity of the power supply can not guarantee the power consumption requirement of the load in normal work, part of the load is unloaded according to the priority, the power consumed by the load and the power supply power of the power supply system are matched again, and the flight task is guaranteed to be completed as much as possible.
In specific implementation, the load management algorithm combines a traditional traversal algorithm and an intelligent algorithm, loads with high priority as much as possible on the basis of reducing load loading and unloading time to improve the power utilization rate, and as shown in fig. 4, the load management algorithm is a comparison table of load loading time and optimizing time results of an airplane adopting the load management algorithm, and test comparison results prove that the load management algorithm has obvious advantages (in the figure, P0, P1 and P2 indicate different generator states, the configuration indicates specific motors are available, 1 represents normal, and 0 represents unavailable).
In specific implementation, the automatic loading and unloading of the overload power supply channel comprises the following steps:
s3.2.1: calculating current state parameters (such as the state of a generator), acquiring the state of a logic control signal, solving a power supply request equation, reading a Solid State Power Controller (SSPC), a contactor feedback state signal, an unloading control signal, a load override equation, a load control equation and an output negative control signal;
s3.2.2: the process of S3.2.1 is repeated until the automatic loading and unloading of all overloaded power supply channels is completed.
In particular, the objective function of the load management algorithm is (if k is used) l Indicating whether the load is on or off at a time):
wherein, the first and the second end of the pipe are connected with each other,
F l as a fault signal of the load, F l 1 denotes load failure, F l 0 indicates that the load is working normally, D l For the unload signal of the load, D l 1 indicates that the unload signal is active and no power is supplied to the load, D l 0 indicates that the unload signal is invalid; s l Is an override signal of the load, S l 1 indicates that the override signal is active (supplying power to the load), S l 0 indicates that the override signal is invalid;
indicating the priority of a load for a flight phase.
In specific implementation, the constraint function of the load management algorithm is as follows:
U min ≤U b ≤U max ；
I b ≤I max ；
wherein P is l Power of the load, P s Capacity of the motor, U b Bus bar voltage, I b The bus bar current.
The invention also discloses an automatic loading and unloading system for improving the utilization rate of the airplane power supply, which at least comprises a storage and a processor; in specific implementation, the memory stores an executable program of the method; the processor may run an executable program of the method.
The invention provides an automatic loading and unloading method and system for improving the utilization rate of an airplane power supply, which dynamically set the priority of multiple electric loads under a full flight envelope on the basis of conditions such as different flight stages, power supply capacity of the power supply, power consumption requirements of the loads and the like. When the total capacity of the power supply does not meet the load request, the load is automatically loaded and unloaded according to the load priority and the load management algorithm, and the load power supply request is met as much as possible on the premise of ensuring the power supply of the key load, so that the utilization rate of the power supply is improved.
Although the invention has been described in detail above with reference to a general description and specific examples, it will be apparent to one skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (8)
1. An automatic loading and unloading method for improving the utilization rate of an airplane power supply is characterized in that: the method comprises the following steps:
s1: when the aircraft power supply fails, detecting the current power supply system architecture, the power supply state, the flight stage, the control equipment state and the power supply channel;
s2: judging whether the power supply channel fails according to the detection result in the S1, if so, carrying out power distribution reconstruction, detecting whether the power supply channel is overloaded or not after power distribution reconstruction, and if not, directly detecting whether the power supply channel is overloaded or not;
s3: judging whether the power supply channel is overloaded or not according to the detection result in the S2, finishing the process if the power supply channel is not overloaded, and starting a load management program to finish the automatic loading and unloading of the overloaded power supply channel if the power supply channel is overloaded;
s4: after the automatic unloading of the overload channel is completed, the process goes to the step S2, and the power supply channel is detected again and judged whether to fail.
2. The automatic loading and unloading method for improving the utilization rate of the power supply of the airplane as claimed in claim 1, wherein: the load management program in S3 includes the following steps:
s3.1: determining dynamic priority setting of the aircraft load in a single-power failure, a double-power failure, an APU-only power supply, a storage battery-only power supply and an RAT-only power supply mode by using a traversal method or a knapsack transmission to form a load configuration table;
s3.2: and according to the load configuration table, combining with the power supply power limitation, setting a target function and a constraint function for switches which are not configured in the load configuration table according to the overall load management target, and completing the automatic loading and unloading of all the overload power supply channels.
3. The automatic loading and unloading method for improving the utilization rate of the power supply of the airplane as claimed in claim 2, wherein: the aircraft load priority setting comprises the following steps:
s3.1.1: classifying different loads, and establishing a control equation and a power supply request equation of the electrical load; the method comprises the steps of converting the problems of load shedding and power distribution of an airplane into a multi-objective optimization problem, introducing a threshold parameter of a control switch to solve, realizing priority power supply of important loads, and dynamically setting the priority of multiple loads under a full flight envelope on the basis of a flight stage, power supply capacity and load power consumption requirements;
the basic principles for powering a load are: when the total capacity of the power supply meets the current load request, the load management should ensure that all loads are reliably powered; when the total capacity of the power supply does not meet the load request, preferentially loading a load with high priority according to the load priority and a related algorithm; when the power supply system fails and the total power supply capacity of the power supply can not guarantee the power consumption requirement of the load working normally, part of the load is unloaded according to the priority, and the power consumed by the load and the power supply power of the power supply system are matched again.
4. The automatic loading and unloading method for improving the utilization rate of the power supply of the airplane as claimed in claim 2, wherein: the load management algorithm combines a traditional traversal algorithm and an intelligent algorithm, and improves the power utilization rate on the basis of reducing the load loading and unloading time.
5. The automatic loading and unloading method for improving the utilization rate of the power supply of the airplane as claimed in claim 2, wherein: the automatic loading and unloading of the overload power supply channel comprises the following steps:
s3.2.1: calculating current state parameters, acquiring logic control signal states, solving a power request equation, reading a Solid State Power Controller (SSPC), a contactor feedback state signal, an unloading control signal, a load override equation, a load control equation and an output negative control signal;
s3.2.2: the process of S3.2.1 is repeated until the automatic loading and unloading of all overloaded power supply channels is completed.
6. The automatic loading and unloading method for improving the utilization rate of the power supply of the airplane as claimed in claim 2, wherein: the objective function of the load management algorithm is (if k is used) l Indicating whether the load is on or off at a time):
wherein the content of the first and second substances,
F l as a fault signal of the load, F l 1 denotes load failure, F l 0 indicates that the load is working normally, D l For the unload signal of the load, D l 1 indicates that the unload signal is active and no power is supplied to the load, D l 0 indicates that the unload signal is invalid; s l For override signals of the load, S l 1 indicates that the override signal is active (supplying power to the load), S l 0 indicates that the override signal is invalid;
indicating the priority of a certain load for a certain flight phase.
7. The automatic loading and unloading method for improving the utilization rate of the power supply of the airplane as claimed in claim 2, wherein: the constraint function of the load management algorithm is:
U min ≤U b ≤U max ；
I b ≤I max ；
wherein P is l Power of the load, P s Capacity of the motor, U b Bus bar voltage, I b The bus bar current.
8. An automatic loading and unloading system for improving the utilization rate of an aircraft power supply at least comprises a storage and a processor; the method is characterized in that: said memory storing an executable program of the method of any of claims 1 to 7; the processor may execute an executable program for performing the method of claims 1-7.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116031989A (en) * | 2023-03-29 | 2023-04-28 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Multi-source electric energy control method and architecture |
| CN117891156A (en) * | 2024-03-15 | 2024-04-16 | 美通重工有限公司 | Control system and method for dual-energy aerial work platform |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116031989A (en) * | 2023-03-29 | 2023-04-28 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Multi-source electric energy control method and architecture |
| CN117891156A (en) * | 2024-03-15 | 2024-04-16 | 美通重工有限公司 | Control system and method for dual-energy aerial work platform |
| CN117891156B (en) * | 2024-03-15 | 2024-05-14 | 美通重工有限公司 | Control system and method for dual-energy aerial work platform |
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