CN112758345A - Design method of aircraft universal power distribution system - Google Patents
Design method of aircraft universal power distribution system Download PDFInfo
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- CN112758345A CN112758345A CN202011400118.5A CN202011400118A CN112758345A CN 112758345 A CN112758345 A CN 112758345A CN 202011400118 A CN202011400118 A CN 202011400118A CN 112758345 A CN112758345 A CN 112758345A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
Abstract
The invention belongs to the technical field of power distribution systems of aviation aircrafts and discloses a design method of a universal power distribution system of an airplane, which comprises the steps of firstly carrying out statistics on power consumption requirements in a scheme stage to obtain preliminary power consumption requirements of a whole airplane; designing a power supply system scheme, and determining a voltage system adopted by the power supply system, and the configuration of a power supply and a power distribution device; carrying out power demand statistics in a detailed stage and carrying out load distribution; carrying out detailed design on a power supply system; setting the power distribution device in detail; counting current data actually measured by the electric equipment and the power supply system, and checking the design value of the power distribution system; and finally, managing the power utilization requirement of each airplane in the whole life cycle, thereby ensuring that the power utilization requirement of each airplane is clear and controllable. The invention obviously improves the universality of the airplane power distribution system, reduces the use and maintenance cost of the airplane, and also enables designers to clearly master the capacity requirements of the power utilization equipment of each airplane on the power distribution system.
Description
Technical Field
The invention belongs to the technical field of power distribution systems of aviation aircrafts, relates to a method for designing a power distribution system of an airplane, and particularly relates to a method for designing a universal power distribution system of an airplane.
Background
In recent years, unmanned aerial vehicles are developed at a high speed and widely applied to various fields such as national defense, forest fire prevention, high-voltage line inspection, mobile communication and the like. The practical situation that the number of airplanes is large, the types of users are multiple, and the user demands are changing at any time provides higher requirements for the generalization and the module design of the power supply and distribution system of the unmanned aerial vehicle.
The following problems of the current unmanned aerial vehicle power distribution system design are more ubiquitous:
1. the interfaces of the power distribution system to power the consumer lack versatility. For unmanned aerial vehicles, the task devices of different batches are different, and the tasks installed by the same aircraft each time a flight task is performed are also different. If the design of the power distribution interface lacks versatility, changes to the mission equipment may cause the power distribution equipment to change.
2. There is no design margin for on-load capability within the power distribution system. The design loading capacity of the power distribution system can only meet the power demand in the design stage, but the airplane involves a great deal of power utilization equipment change in the use process, and the addition of any larger power utilization equipment can cause the power distribution system to be changed.
3. The power supply requirements of the electrical equipment to the power distribution system are not managed efficiently. The load capacity of the power distribution system needs to be evaluated when the increase and decrease of the electric equipment or the change of the power consumption of the electric equipment occur each time according to a normal design flow. Due to the lack of effective power demand management, designers need to re-evaluate the capacity of the power distribution system every time the power utilization equipment changes, and a great deal of energy of the designers is consumed.
The design problem of the power distribution system can increase the use and maintenance cost of users, reduce the perfectness rate of the airplane and consume a large amount of resources of host places and finished product supporting units.
Disclosure of Invention
In order to solve the problems, the invention provides a design method of a universal power distribution system of an airplane, which standardizes the design of the loading capacity of the power distribution system and the power supply demand management of power utilization equipment to the power distribution system, thereby effectively avoiding or reducing the change of power distribution equipment and the change of on-board circuits caused by the change of the power utilization equipment and effectively reducing the use cost of the airplane.
The technical scheme of the invention is as follows:
a design method of a universal power distribution system of an airplane comprises the following steps:
step one, carrying out statistics on power consumption requirements in a scheme stage to obtain the initial power consumption requirements of the whole machine;
step two, designing a power supply system scheme, and determining a voltage system adopted by the power supply system and the configuration of a power supply and a power distribution device;
step three, carrying out power demand statistics in a detailed stage and carrying out load distribution;
fourthly, designing the power supply system in detail;
step five, the power distribution device is set in detail;
counting current data actually measured by the electric equipment and the power supply system, and checking the design value of the power distribution system;
and seventhly, managing the power consumption requirement of each airplane in the whole life cycle, thereby ensuring that the power consumption requirement of each airplane is clear and controllable.
Further, in the first step, the power utilization information included in each power utilization device at least includes: the system comprises a power utilization equipment name, a subsystem name, a working voltage type, rated power and working time of each flight task stage.
Further, the third step specifically comprises the following steps:
a) on the basis of load statistics in the scheme stage, further analyzing the power consumption requirement of the power consumption equipment, thereby obtaining more accurate power consumption and importance degree of the power consumption equipment and more detailed working state of each flight stage;
b) distributing each electric device into the bus bar of each power distribution device according to the importance degree;
c) and counting the power consumption of the electric equipment according to the bus bars to obtain a distribution graph of the power distribution capacity and the power consumption requirement.
Further, in the step c) of the third step, the distribution capacity and power consumption demand distribution maps are stored and recorded, and different power supply states correspond to one distribution capacity and power consumption demand distribution map.
Further, the fourth step is specifically: the power of each bus bar is designed, and then an electric interface is distributed to each electric device.
Further, in step five, the principle followed when the power distribution device is designed in detail is as follows:
1) the output capacity of each distribution device bus bar is greater than the maximum value of the statistical load in the design stage;
2) under different power supply states, the output capacity of all the power distribution device bus bars is larger than the power supply capacity of the related power supply;
3) the information of the related power supply channel on the power distribution device is irrelevant to the electric equipment at the rear end, and the power distribution device can be used for different electric equipment to realize generalization;
4) the power supply interface of the task equipment arranged on the power distribution device not only meets the power supply requirement of the task equipment in the design stage, but also reserves the power supply interface of the task equipment which is possibly newly added on the airplane in the future.
Furthermore, in the sixth step, after the current data actually measured by the electric equipment and the power supply system are counted, the current data are reflected to the distribution capacity and the power consumption demand distribution map.
Further, the seventh step specifically comprises: real-time recording of electricity demand is performed for each aircraft and continues for the full life cycle of the aircraft.
Has the advantages that:
the design method and the design idea of the invention are implemented on a plurality of airplane models, and the continuous verification of a plurality of airplanes for years shows that:
1. the universality of the airplane power distribution system is remarkably improved, the line change and the power distribution device change of the power distribution system caused by the change of electric equipment are greatly reduced, the use and maintenance cost of the airplane is reduced, a large amount of manpower and financial resources are saved for customers, airplane general units and finished product matching units, and the utilization rate of the airplane is improved.
2. The designer can clearly master the capability requirement of the electrical equipment of each airplane on the power distribution system, the actual power utilization requirement and the service condition of the power distribution interface, a large amount of state cleaning time is saved, and reliable guarantee is provided for safe flight.
Drawings
FIG. 1 is a flow chart of a design method of an embodiment of the present invention;
FIG. 2 is a distribution diagram of power distribution capability and power demand when the power supply system of the embodiment of the invention is normal;
fig. 3 is a graph of power distribution capability versus power demand profiles for various power distribution configurations in accordance with embodiments of the present invention.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A design method of a universal power distribution system of an airplane comprises the following steps:
step one, carrying out statistics on power consumption requirements in a scheme stage to obtain the initial power consumption requirements of the whole machine;
step two, designing a power supply system scheme, and determining a voltage system adopted by the power supply system and the configuration of a power supply and a power distribution device;
step three, carrying out power demand statistics in a detailed stage and carrying out load distribution;
fourthly, designing the power supply system in detail;
step five, the power distribution device is set in detail;
counting current data actually measured by the electric equipment and the power supply system, and checking the design value of the power distribution system;
and seventhly, managing the power consumption requirement of each airplane in the whole life cycle, thereby ensuring that the power consumption requirement of each airplane is clear and controllable.
In the first step, the power consumption information included in each piece of power consumption equipment at least comprises: the method comprises the following steps of using the name of the electric equipment, the name of a subsystem to which the electric equipment belongs, the type of working voltage, the rated power and the working time of each flight task stage.
The third step specifically comprises the following steps:
a) on the basis of load statistics in the scheme stage, further analyzing the power consumption requirement of the power consumption equipment, thereby obtaining more accurate power consumption and importance degree of the power consumption equipment and more detailed working state of each flight stage;
b) distributing each electric device into the bus bar of each power distribution device according to the importance degree;
c) and counting the power consumption of the electric equipment according to the bus bars to obtain a distribution graph of the power distribution capacity and the power consumption requirement.
In the step c), the distribution capacity and the power consumption demand distribution map are stored and recorded, and different power supply states correspond to one distribution capacity and power consumption demand distribution map.
The fourth step is specifically as follows: the power level of each bus bar is designed and then an electrical interface is assigned to each consumer.
In the fifth step, the principle followed during the detailed design of the power distribution device is as follows:
1) the output capacity of each distribution device bus bar is greater than the maximum value of the statistical load in the design stage;
2) under different power supply states, the output capacity of all the power distribution device bus bars is larger than the power supply capacity of the related power supply;
3) the information of the related power supply channel on the power distribution device is irrelevant to the electric equipment at the rear end, and the power distribution device can be used for different electric equipment to realize generalization;
4) the power supply interface of the task equipment arranged on the power distribution device not only meets the power supply requirement of the task equipment in the design stage, but also reserves the power supply interface of the task equipment which is possibly newly added on the airplane in the future.
And step six, after the current data actually measured by the electric equipment and the power supply system are counted, the current data are reflected to a distribution capacity and power consumption demand distribution diagram.
The seventh step is specifically as follows: real-time recording of electricity demand is performed for each aircraft and continues for the full life cycle of the aircraft.
The principle of the design method of the invention is as follows:
the technical scheme mainly comprises three aspects of the design of the loading capacity of the power distribution system, the management of the power consumption requirement of the full life cycle and the evaluation of the loading capacity of the power distribution system. The power distribution system load capacity is designed to ensure that the capacity of the power source can be fully utilized and to avoid or reduce power distribution system changes caused by changes to the electrical equipment. The full-life-cycle power demand management and the power distribution system on-load capacity evaluation are used for managing and evaluating whether the on-load capacity of the power distribution system meets the power demand of the power utilization equipment.
1. Power distribution system load capacity design
In the design stage of the power distribution system, the on-load capacity of the power distribution system should meet the power demand of the known power utilization equipment, and a certain margin should be provided for meeting the power demand which may increase or change in the future, so as to ensure that the capacity of the power supply in the future can be fully utilized.
The load capacity of the power distribution system includes the associated power lines within the power distribution system, the load capacity of the power distribution equipment, and the load capacity of the power distribution equipment that interfaces with the powered device. Only if the capacities in both aspects have reasonable margins, does the on-load capacity of the distribution system have margins
2. Full lifecycle electricity demand management
Statistics, analysis and management are carried out on the statistics power consumption requirement and the actual measurement power consumption requirement of the power consumption equipment in the whole life cycle of the airplane through configuration management, and the power consumption requirement of each airplane can be clearly checked in each use stage.
And the demand of the electric equipment on the power line of the power distribution system and the capacity of the power distribution device is obtained according to the power demand of the electric equipment. The capacity requirements of the corresponding power distribution system are also incorporated into the configuration management.
3. Power distribution system load capacity assessment
The design capability of the power distribution system is compared with the power distribution system capability requirement of the electric equipment, the use condition of each aircraft power distribution interface can be clearly mastered, and whether the power transmission requirement of each aircraft power distribution system internal power line can be met or not is effectively evaluated.
The flow chart of the invention is shown in figure 1:
a) and carrying out the statistics of the power consumption requirements at the scheme stage to obtain the initial power consumption requirements of the whole machine. The power utilization information contained in each power utilization device at least comprises: the method comprises the following steps of (1) using the name of electric equipment, the name of a subsystem to which the electric equipment belongs, the type of working voltage, rated power and working duration of each flight task stage;
b) designing a power supply system scheme, and determining a voltage system adopted by the power supply system, and the configuration of a power supply and a power distribution device;
c) and carrying out power demand statistics in a detailed stage and carrying out load distribution. The method comprises the following implementation steps:
1) and further analyzing the electricity utilization requirements of the electric equipment on the basis of the load statistics in the scheme stage. Therefore, more accurate power consumption, importance degree, more detailed working state of each flight stage and the like of the power utilization equipment are obtained.
2) Distributing each electric device into the bus bar of each power distribution device according to the importance degree;
3) and counting the power consumption of the electric equipment according to the bus bars to obtain a distribution capacity and power consumption demand distribution diagram. Different power supply states all correspond to a distribution capacity and power consumption demand distribution diagram.
Fig. 2 is a distribution diagram of power distribution capacity and power demand when the power supply system is normal.
d) Carrying out detailed design on a power supply system;
e) the power distribution device is set in detail. The principle followed by the detailed design time of the power distribution device is as follows:
1) the output capacity of each distribution device bus bar is greater than the maximum value of the statistical load in the design stage;
2) under different power supply states, the output capacity of all the power distribution device bus bars is larger than the power supply capacity of the related power supply
3) The information of the related power supply channel on the power distribution device is irrelevant to the electric equipment at the rear end, and the power distribution device can be used for different electric equipment to realize generalization;
4) the power supply interface of the task equipment arranged on the power distribution device not only meets the power supply requirement of the task equipment in the design stage, but also reserves the power supply interface of the task equipment which is possibly newly added on the airplane in the future.
f) Counting current data actually measured by the electric equipment and the power supply system, reflecting the current data on the distribution capacity and the power consumption demand distribution diagram, and checking the design value of the distribution system;
the power utilization requirements of each airplane in the whole life cycle are managed, so that the power utilization requirements of each airplane are clear and controllable. Fig. 3 is a diagram of a distribution diagram of different power distribution configurations and power distribution capacity versus power demand after configuration management.
Claims (8)
1. A design method of a universal power distribution system of an airplane is characterized by comprising the following steps:
step one, carrying out statistics on power consumption requirements in a scheme stage to obtain the initial power consumption requirements of the whole machine;
designing a power supply system scheme, and determining a voltage system adopted by the power supply system and the configuration of a power supply and a power distribution device;
step three, carrying out power demand statistics in a detailed stage and carrying out load distribution;
fourthly, designing the power supply system in detail;
step five, the power distribution device is set in detail;
counting current data actually measured by the electric equipment and the power supply system, and checking the design value of the power distribution system;
and seventhly, managing the power consumption requirement of each airplane in the whole life cycle, thereby ensuring that the power consumption requirement of each airplane is clear and controllable.
2. The design method of a universal power distribution system for aircraft according to claim 1, wherein in the first step, the power utilization information included in each power utilization device at least includes: the method comprises the following steps of using the name of the electric equipment, the name of the subsystem to which the electric equipment belongs, the type of working voltage, the rated power and the working time of each flight mission stage.
3. The design method of the aircraft generalized power distribution system according to claim 1, wherein the third step specifically comprises the following steps:
a) on the basis of load statistics in the scheme stage, further analyzing the power consumption requirement of the power consumption equipment, thereby obtaining more accurate power consumption and importance degree of the power consumption equipment and more detailed working state of each flight stage;
b) distributing each electric device into the bus bar of each power distribution device according to the importance degree;
c) and counting the power consumption of the electric equipment according to the bus bars to obtain a distribution capacity and power consumption demand distribution diagram.
4. The method as claimed in claim 3, wherein in step c), the power distribution capability and power demand distribution map is stored and recorded, and different power supply states correspond to one power distribution capability and power demand distribution map.
5. The design method of the aircraft generalized power distribution system according to claim 1, wherein the fourth step is specifically: the power of each bus bar is designed, and then an electric interface is distributed to each electric device.
6. The design method of the aircraft universal power distribution system according to claim 1, wherein in the fifth step, the detailed design of the power distribution device complies with the following principles:
1) the output capacity of each distribution device bus bar is greater than the maximum value of the statistical load in the design stage;
2) under different power supply states, the output capacity of all the power distribution device bus bars is larger than the power supply capacity of the related power supply;
3) the information of the related power supply channel on the power distribution device is irrelevant to the electric equipment at the rear end, and the power distribution device can be used for different electric equipment to realize generalization;
4) the power supply interface of the task equipment arranged on the power distribution device not only meets the power supply requirement of the task equipment in the design stage, but also reserves the power supply interface of the task equipment which is possibly newly added on the airplane in the future.
7. The design method of the aircraft universal power distribution system according to claim 4, wherein in the sixth step, after statistics of current data measured by the electric equipment and the power supply system, the current data are reflected on the distribution capability and the power demand distribution map.
8. The design method of the aircraft generalized power distribution system according to claim 1, wherein the seventh step is specifically as follows: real-time recording of electricity demand is performed for each aircraft and continues for the full life cycle of the aircraft.
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