CN114142454B - Aircraft power supply control system - Google Patents
Aircraft power supply control system Download PDFInfo
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- CN114142454B CN114142454B CN202111467657.5A CN202111467657A CN114142454B CN 114142454 B CN114142454 B CN 114142454B CN 202111467657 A CN202111467657 A CN 202111467657A CN 114142454 B CN114142454 B CN 114142454B
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- power supply
- generator
- connector
- armature
- relay
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/42—Devices characterised by the use of electric or magnetic means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
- G01R1/04—Housings; Supporting members; Arrangements of terminals
- G01R1/0408—Test fixtures or contact fields; Connectors or connecting adaptors; Test clips; Test sockets
- G01R1/0416—Connectors, terminals
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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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- 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
- G01R31/346—Testing of armature or field windings
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
- H02J1/106—Parallel operation of dc sources for load balancing, symmetrisation, or sharing
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
- H02J1/109—Scheduling or re-scheduling the operation of the DC sources in a particular order, e.g. connecting or disconnecting the sources in sequential, alternating or in subsets, to meet a given demand
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Control Of Charge By Means Of Generators (AREA)
- Control Of Eletrric Generators (AREA)
Abstract
The application relates to an aircraft power supply control system, which belongs to the technical field of aircraft electrical systems, and comprises: the control device comprises a control device, a first relay, a second relay, an external power supply, a main battery, a first generator armature output power supply, a second generator armature output power supply and a direct current bus; the external power supply, the main battery and the armature output power supply of the first generator supply power to the direct current bus; the direct current bus is directly connected with a stable working condition load; the armature output power supply of the second generator is connected with a high-power variable-working-condition load; the coil control ends of the first relay and the second relay are connected with the control equipment and are used for realizing switching action according to a control instruction sent by the control equipment; the first relay is connected between the positive electrode of the direct current bus and the positive electrode of the armature output power supply of the second generator, and the second relay is connected between the negative electrode of the direct current bus and the negative electrode of the armature output power supply of the second generator. The control system realizes stable power supply and is convenient for detecting the rotating speed signal acquisition circuit.
Description
Technical Field
The application relates to the technical field of aircraft electrical systems, in particular to an aircraft power supply control system.
Background
During long flight of an aircraft during an airborne cruise phase, a continuous power supply is required to power the electronic devices onboard the aircraft. In order to solve the functions of uninterrupted power supply of key equipment, power quality control of a large-load energy source supplementing stage and the like during long-time flight, a solution of a power supply control system is needed. In order to solve the above-mentioned needs, a common power supply system scheme is to utilize an engine to drag a generator to generate power so as to realize power supply of a power bus. For reliability redundancy and the expansion requirement of the total capacity of the power supply, two sets of power generation armature windings are usually adopted for outputting the power supply by the same power generator. Two sets of power supplies supply power to the same bus system at the same time, and the output of the two sets of windings is mutually backed up. Due to the variety of aircraft system load types. When the same power bus supplies power to computer-type equipment, high-power motor-type loads or instantaneous high-energy-consumption load equipment, the influence of load adjustment on the power bus inevitably occurs. The common practice of the power supply system scheme is to increase the capacity design and power design index of the power supply system after determining the conditions such as the total capacity and power demand of the system. On the other hand, the load end adopts a secondary power supply to isolate the influence of load adjustment. However, in the application of the aircraft field, due to the limitation of the empty and load indexes, the generator is often limited by the structural condition of an engine system, the power supply capacity cannot be infinitely enlarged, the output power of the power generation system has the voltage stabilizing function with a certain condition although the power generation system has the regulating capability, and the time period of excitation regulation of the generator cannot keep up with the instantaneous requirement of load change under the condition of instantaneous high-power load demand. In addition, the method of adding secondary power sources at all load equipment ends is not realistic enough, and especially adding isolation circuits at the power source ends of some high-power electromechanical products inevitably brings extra cost to the volume, weight and cost of the products. Therefore, when the power supply system is used, other power supplies are introduced as supplements of the direct current bus to ensure the stability of the voltage of the power bus. The scheme schematic diagram of the conventional double-armature output power generation system is shown in detail in fig. 1.
The conventional power supply scheme forms a closed loop feedback link of voltage stabilizing control by sampling bus voltage signals. The output of the exciting voltage signal is converted through the comparison with the reference voltage, so that the control output of the exciting current generated by the generator is realized, and the excitation regulation control function is achieved. But the signal sampling rate and the response period of the circuit control are insufficient to meet the requirement of rapid adjustment of instantaneous changes of loads of motors. Therefore, the dc bus also has relatively large voltage fluctuations. In order to restrain the voltage fluctuation, a large-capacity battery is designed in a traditional mode and is always mounted on a direct current bus end to be used as an auxiliary power supply of the direct current bus to supplement energy source for adjusting instantaneous conditions of loads at any time, so that the voltage stabilizing effect is achieved. If the aircraft is operated for a long time, the capacity of the battery, the long-time operation guarantee conditions and the like need to be correspondingly improved, and therefore additional system cost is brought. The other mode is similar to that of arranging a large-capacity capacitor at the input end of a motor load power supply, so that the voltage stabilizing capability is ensured, and besides the volume weight and cost of a large-capacity capacitor product, the current impact on the power supply in the power-on starting stage of the system power supply is increased. Even though the load-bearing capacity of the power supply system is enlarged to meet the voltage stabilizing requirement of instantaneous condition load adjustment, the power supply capacity or the power capacity increased by the conventional power supply system is not used for most of the time, and the power supply system only works in the short time of the instantaneous load adjustment, has low cost performance and is not suitable for being applied to the aviation fields of aircrafts and the like.
In addition, the key rotating speed feedback signal of the engine control system is also realized through the voltage signal sampling of the power generation link of the power supply system. Because the aircraft is in ground test and maintenance stage, the state of high-speed rotation of the generator rotor is not easy to realize. Therefore, the generated voltage signal cannot be directly measured to judge the integrity of the related line state. In order to ensure that a rotational speed signal can be effectively checked in an aircraft engine or a power generation system installation link circuit, a rotational speed signal switching circuit is specially designed in the power supply system, so that the shunt connection of a generator power supply and a rotational speed feedback signal is realized, and the requirements of testability and circuit isolation of a rotational speed signal circuit are realized through the switching design of a two-stage connector.
Therefore, in order to solve the problems, the application provides the power supply control system for the aircraft power supply, which utilizes the same double-armature generator and realizes staged power supply combination or shunt power supply through the design of a power supply system circuit, thereby isolating high-power loads with low requirements on the stability of the power supply voltage and realizing the voltage stabilizing function of a direct current bus power supply. The rotational speed signal switching circuit with the two-stage connector is used for realizing effective detection of the state of the generator rotor in the ground test and maintenance stage.
Disclosure of Invention
In view of the above analysis, the embodiment of the application aims to provide an aircraft power supply control system, which is used for solving the problems that the power supply of the existing aircraft power supply is interfered by a high-power variable working condition load, the power supply is unstable, and a rotating speed acquisition circuit cannot be detected in a ground test stage. The power supply control system includes: the control device comprises a control device, a first relay, a second relay, an external power supply, a main battery, a first generator armature output power supply, a second generator armature output power supply and a direct current bus;
the external power supply, the main battery and the armature output power supply of the first generator supply power to the direct current bus; the direct current bus is directly connected with a stable working condition load;
the armature output power supply of the second generator is connected with a high-power variable-working-condition load;
the coil control ends of the first relay and the second relay are connected with the control equipment and are used for realizing switching action according to a control instruction sent by the control equipment;
the first relay is connected between the positive electrode of the direct current bus and the positive electrode of the armature output power supply of the second generator, and the second relay is connected between the negative electrode of the direct current bus and the negative electrode of the armature output power supply of the second generator.
Further, a normally closed contact of the first relay is connected with the positive electrode of the direct current bus, and the midpoint of the switch is connected with the positive electrode of the armature output power supply of the second generator; and the normally closed contact of the second relay is connected with the negative electrode of the direct current bus, and the midpoint of the switch is connected with the negative electrode of the armature output power supply of the second generator.
Further, when the control instructions sent by the control equipment are received by the first relay and the second relay coil control ends, the normally-closed contacts are disconnected, so that the direct-current bus is disconnected with the armature output power supply of the second generator and the high-power variable-working-condition load.
Further, the external power supply includes a power supply DC1 and a power supply DC-fl; the power supply DC-fl is connected with the direct current bus and used for supplying power to the direct current bus, and the power supply DC1 is connected with the stable working condition load and used for supplying power to the stable working condition load.
Further, the first generator armature output power supply comprises a first generator armature and a first full-wave rectifying circuit; the second generator armature output power supply comprises a second generator armature and a second full-wave rectifying circuit; the first generator armature and the second generator armature are two independent armatures on the same rotor, and the alternating current power supplies output by the two armatures are converted by the respective full-wave rectifying circuits and then output two paths of direct current power supplies.
Further, the power supply control system also comprises a first connector and a parallel connection joint; one end of the first connector is connected with three-phase output ports of the first generator armature and the second generator armature, the other end of the first connector is connected with a parallel line connector, and the first generator armature and the second generator armature output alternating current power sources through the first connector.
Further, the first connector comprises a connector socket and a connector plug, the connector plug is connected with three-phase output ports of the first generator armature and the second generator armature, and the connector socket is connected with a parallel joint; the parallel connection is used for converting thick wires of the three-phase power line into a plurality of thin wires.
Further, the number of the connector plugs is 6, and 6 connector sockets are arranged corresponding to the 6 plugs; 3 plugs in the connector plugs are connected with the three-phase output port of the first generator armature, and the other 3 plugs are connected with the three-phase output port of the second generator armature; each connector socket is connected with one parallel connection joint, 6 parallel connection joints are arranged, and each parallel connection joint corresponds to one phase of the first generator armature and the second generator armature.
Further, the power supply control system further comprises a second connector, the second connector comprises a connector plug and a connector socket, the connector socket is connected with the parallel connection joint and used for collecting an alternating voltage signal output by an armature of the generator to serve as an engine rotating speed feedback signal, and the connector plug is connected with the interface of the control equipment and used for transmitting the engine rotating speed feedback signal to a rotating speed sampling circuit inside the control equipment.
Further, the second connector comprises 4 connector plugs and 4 connector sockets; the 4 connector sockets are respectively connected with one parallel connection joint, and the 4 parallel connection joints connected with the 4 connector sockets correspond to any two-phase output ports of the first generator armature and any two-phase output ports of the second generator armature.
Compared with the prior art, the application has at least one of the following beneficial effects:
1. the power supply control system of the application utilizes two power type relays to realize the on-off control of the direct current bus power supply and the steering engine power supply circuit, and has simple structure and single device.
2. The power supply control system adopts 1 relay to realize the control of the direct current power supply plus terminal, 1 relay to realize the control of the direct current power supply minus terminal, and independent devices are adopted to respectively control the two poles of the power supply, so that unreliable factors of the short circuit of the positive pole and the negative pole in the devices can be avoided.
3. The relay adopts the form of 3 groups of switch contacts, so that the redundancy capability of switch control can be increased, and when one group of contacts of the relay are effectively connected, the power supply of the steering engine can be ensured to be effective.
4. The normally closed contact of the relay is connected with the power end of the direct current bus, the midpoint of the relay switch is connected with the armature output power of the second generator and the circuit form of the power end of the steering engine, and when the switching of the on-off control of the relay is abnormal, the direct current bus can be at least ensured to supply power to the steering engine, and the power supply function of the steering engine can be ensured to be effective.
5. The shunt power supply of the direct current bus power supply and the steering engine power supply is realized by utilizing two groups of armature output power supplies of the generator, and the direct current bus power supply supplies power to computer equipment. The armature output power supply of the second generator supplies power to the steering engine. And the multi-power combination of the direct current bus power supply is realized by connecting an external power supply and a battery power supply in parallel with the direct current bus power supply end. The combined control circuit can realize the multi-power supply hybrid connection power supply function and simultaneously achieve the aims of isolating two power supply circuits and realizing anti-interference design.
6. The difference of power supply working time sequence is utilized to realize the power supply continuous power supply of the steering engine power supply in a time-sharing mode, and the shunt isolation of the power supply is realized in the power supply stage of the generator. Before the generator stably supplies power, the same group of relays are utilized to realize the starting control of the power supply of the steering engine.
7. The power supply signal output by the synchronous operation generator of the engine is used as a feedback signal for monitoring the rotating speed of the engine, and the circuit is connected with the power supply circuit through a circuit connection design to realize the connection of the rotating speed signal sampling front-end circuit of the control equipment.
8. And the connection of the armature coil circuit of the generator, the sampling front-end circuit of the rotating speed signal and the two armature power supply circuits of the generator is realized by using the two-stage connector. Independent testing of the power generating first generator armature and the second generator armature coils can be achieved through the first connector plug. The independent test of the rotating speed signal sampling front-end circuit can be realized through the second connector plug, and the rotating speed signal sampling front-end circuit comprises a primary coil of the transformer 1 and a primary coil of the transformer 2. During testing, the open circuit isolation of the armature coil of the generator, the sampling front-end circuit of the rotating speed signal and the power supply end circuit of the power conversion equipment can be realized under the state of separating the first connector from the second connector, so that the state of small resistance can be effectively identified.
9. The switching circuit is used for realizing reliable parallel connection of the generator power supply circuit and the rotating speed signal thick and thin cable after conversion. Through the switching design of the first connector, on the basis of not damaging an armature circuit of the generator, a thick wire with the diameter of 2.0mm 2 in each phase of power supply circuit is switched into 3 thin wires with the diameter of 0.5mm 2 by using a parallel joint in the switching circuit. Meanwhile, a thin wire with the diameter of 0.5mm 2 is connected to the second connector in parallel, so that the shunt extraction of the rotating speed sampling signal is realized.
In the application, the technical schemes can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application. The objectives and other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the application, like reference numerals being used to refer to like parts throughout the several views.
FIG. 1 is a schematic diagram of a prior art dual armature output power generation system;
FIG. 2 is a schematic diagram of power switching of a power supply control system according to an embodiment of the present application;
FIG. 3 is a schematic circuit diagram of a power supply control system according to an embodiment of the present application;
Detailed Description
The following detailed description of preferred embodiments of the application is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the application, are used to explain the principles of the application and are not intended to limit the scope of the application.
In one embodiment of the present application, an aircraft power supply control system is disclosed, as shown in fig. 2, the power supply control system includes: the control device comprises a control device, a first relay, a second relay, an external power supply, a main battery, a first generator armature output power supply, a second generator armature output power supply and a direct current bus;
the external power supply, the main battery and the armature output power supply of the first generator supply power to the direct current bus; the direct current bus is directly connected with a stable working condition load;
the armature output power supply of the second generator is connected with a high-power variable-working-condition load;
the coil control ends of the first relay and the second relay are connected with the control equipment and are used for realizing switching action according to a control instruction sent by the control equipment;
the first relay is connected between the positive electrode of the direct current bus and the positive electrode of the armature output power supply of the second generator, and the second relay is connected between the negative electrode of the direct current bus and the negative electrode of the armature output power supply of the second generator.
First, the power supply in the system is described:
the external power supply is a power supply which does not belong to an aircraft and is a ground power supply; the external power supply comprises a power supply DC1 and a power supply DC-fl; the power supply DC-fl is connected with the direct current bus and used for supplying power to the direct current bus, and the power supply DC1 is connected with the stable working condition load and independently supplies power to the stable working condition load. The external power supply DC1 and the external power supply DC-fl are ground power supplies for supplying power to the aircraft before the aircraft takes off, and the external power supplies are disconnected from the power supply to the aircraft before the aircraft takes off.
The main battery is a self-contained power supply in the aircraft, and is fully charged before the aircraft takes off.
The first generator armature output power supply comprises a first generator armature and a first full-wave rectifying circuit; the second generator armature output power supply comprises a second generator armature and a second full-wave rectifying circuit; the first generator armature and the second generator armature are two independent armatures on the same rotor, and the alternating current power supplies output by the first generator armature and the second generator armature are converted by respective full-wave rectifying circuits and then output two paths of direct current power supplies DC-o1 and DC-o2.
The DC-o1 power supply and the DC-o2 power supply which are output by the two paths of armatures of the external power supply DC1, the DC-fl, the main battery DC-ba and the generator after full-wave rectification are all direct current power supplies with rated working voltage of 28V.
During implementation, the first relay and the second relay are high-power relays of the same type, and the electric performance requirements of steering engine loads under various working conditions are met.
Loads in aircraft can be divided into two categories: high power variable operating mode load and steady operating mode load. The typical high-power variable-working-condition load is represented by a steering engine driving circuit and a corresponding motor forming circuit. The steady state load is represented in the form of a block diagram of a "computer-like device power circuit".
The external power supply DC-fl, the main battery DC-ba and the DC-o1 of the first generator armature after full-wave rectification are directly connected in parallel to form a direct current bus power supply. The direct current bus power supply directly supplies power to the power supply circuit of the computer equipment without setting an on-off circuit.
Specifically, a normally closed contact of the first relay is connected with a positive electrode of a direct current bus, and a switch midpoint is connected with a positive electrode of an armature output power supply of the second generator; and the normally closed contact of the second relay is connected with the negative electrode of the direct current bus, and the midpoint of the switch is connected with the negative electrode of the armature output power supply of the second generator.
The normal close contact A3, the normal close contact B3 and the normal close contact C3 of the first relay are respectively communicated with the switch midpoints A2, B2 and C2, so that the connection between the direct current bus power supply plus and the DC-o2 power supply plus of the second generator armature after full-wave rectification is realized. The normal close contact A3, the normal close contact B3 and the normal close contact C3 of the second relay are respectively communicated with the switch midpoints A2, B2 and C2, so that the connection of the direct current bus power supply with the DC-o2 power supply of the second generator armature after full-wave rectification is realized.
The normally closed point connection design has the advantages that in the battery power supply stage before the generator is started, the relay drives and commands are in a low-power-consumption working state with effective power failure, and compared with the design in the power-on working state, the normally closed point connection design can ensure continuous and effective power supply of the steering engine in the stage.
The DC-o2 power supply of the second generator armature after full-wave rectification is connected with a power supply driving circuit of the steering engine in parallel.
Specifically, when the control command sent by the control equipment is received by the first relay and the second relay coil control end, the normally-closed contact is disconnected, so that the direct-current bus is disconnected with the armature output power supply of the second generator and the high-power variable-working-condition load.
Illustratively, the aircraft is not started during initial operation with the generators, DC-o1 and DC-o2 having no voltage output. The power is supplied to the aircraft system devices in the order of the external power source DC-fl, the main battery DC-ba and the power output of the generator armature. Before the external power source DC-fl supplies power, the control device sends a rudder system power supply switching instruction to disconnect the normally closed point A3, the normally closed point B3 and the normally closed point C3 of the first relay and the second relay, so that the steering engine load, the DC-o2 power supply and the direct current bus power supply are disconnected. After the external power supply DC-fl finishes the power-on stabilization, the direct current bus power supply can supply power to the steering engine by canceling the voltage signals of the driving instructions (the power supply switching instructions of the steering system) of the control coils of the first relay and the second relay. The main battery DC-ba power supply can also supply power to the steering engine through the first relay and the second relay. When the generator is started normally, the control equipment sends out driving instructions (rudder system power supply switching instructions) of the control coils of the first relay and the second relay again, so that the direct-current bus power supply is disconnected from the steering engine power supply circuit, and at the moment, the steering engine driving power supply circuit is independently powered by the DC-o2 of the second generator armature through full-wave rectification. In the cruising flight phase of the power supply of the aircraft generator, the steering engine works under various conversion working conditions, and the voltage change generated by the steering engine on the power supply line cannot cross the direct current bus power supply line, so that the anti-interference purpose is realized.
Before the external power supply DC-fl supplies power to the direct current bus power supply, an independent external power supply DC1 is used for ensuring that the control equipment is electrified and started first, and after the control equipment is started normally, electric control is implemented to complete system initialization, wherein the method comprises the steps of sending a steering engine power supply switching instruction to drive normally closed points (A3, B3 and C3) of the first relay and the second relay to be disconnected, and switching the contacts to normally open points (A1, B1 and C1). The switch contact midpoints (A2, B2 and C2) of the first relay and the second relay are always connected with a steering engine load and a DC-o2 power supply. Because the generator runs to generate electricity along with the start of the engine, the power supply of the steering engine power supply in a time-sharing mode is continuously supplied by utilizing the difference of the power supply working time sequence, and the shunt of the power supply is achieved in the power supply stage of the generator. Before the generator stably supplies power, the same group of relays are utilized to realize the starting control of the power supply of the steering engine.
The application relates to a circuit for realizing a power supply switching control function by utilizing a group of power type relays. The control circuit is connected with multiple power supplies to form a power supply system circuit with an anti-interference function. The power supply system is composed of a plurality of power supplies, wherein one power supply is used for supplying power to computer equipment, and the other power supply is used for supplying power to the steering engine. The power supply switching control circuit is arranged between the steering engine special power supply and the steering engine to realize the combination and isolation of the two types of power supplies. The power supplies have different load adjustment resistance at different stages of time-sharing power supply. The power supply of the computer control equipment before the take-off of the aircraft can be controlled within a certain fluctuation limit range through the ground power shunt arrangement or the design of the high power capacity of the ground power supply, so that the quality of the power supply at the stage is ensured. At this stage, the steering engine power supply and the computer equipment power supply can be located in the same power supply circuit, and once the power supply fluctuation causes the abnormality, the influence can be eliminated through troubleshooting under the ground condition. However, after the aircraft takes off, in the stage of power supply of the generator, the power supply capacity of the power generation system of the aircraft is limited, and the load adjustment generated by the operation of the steering engine can cause large-amplitude fluctuation of the power supply voltage. If the computer equipment and the steering engine are also on the same power line, the power adjustment caused by the operation of the steering engine can be transmitted to the computer equipment through the line. Increasing the power supply capacity in a ground-based manner can place a burden on the design of the power supply system on the aircraft. In addition, under the condition of flying in the air, the power source of the aircraft is limited, and if two completely independent power systems are adopted to respectively supply power to the computer equipment and the steering engine, the additional power cost is also unacceptable for some aircraft.
The design core of the application is to utilize the simplest circuit switching control, and the used control has the least specification and quantity of executing devices, thereby achieving the following design functions. Comprising the following steps: before the aircraft takes off, the power supply starting of the steering engine load is independently realized; the aircraft is powered in stages by controlling the power supply time sequence of the power supply; in the independent power supply stage of the generator for the long-time cruising of the aircraft, the isolation conversion between the steering engine power supply and the bus power supply of the control equipment is realized through circuit switching, so that the instantaneous amplitude change of the power consumption during the starting or reversing of the steering engine can not cause the interference of voltage fluctuation on the bus power supply.
In addition, the high-speed generator is utilized to provide power for the power supply system of the aircraft, and meanwhile, the high-speed engine rotating speed signal can be identified through the rotating speed feedback signal sampling circuit by sampling and processing the signal voltage and frequency between the power supply lines. Providing a key feedback signal for control of engine speed conditions and aircraft thrust conditions.
Before the rotation speed signal sampling circuit works, the internal connection of the circuit is detected, and the detection of the rotation speed is carried out after the internal connection of the circuit is ensured to be normal, so that the measurement accuracy can be ensured. In the aspect of line connection, a conductive and insulating measurement method is generally adopted for a tested line, and the state of the line is judged according to a measured resistance value. The inter-phase circuit resistance itself belongs to a small resistance state under the static condition of the generator coil. The front end of the rotating speed signal is isolated by adopting a transformer mode, and the static resistance of the primary coil of the transformer also belongs to a small resistance state. The power supply line cable of the aircraft generator is made of a large-section wire, and the line resistance of the power supply line cable also belongs to a small-resistance state. In the direct connection state of the lines, whether faults such as abnormal short circuit or wrong connection of the armature coils of the generator exist between the detected signal lines or not cannot be accurately identified only through measuring the resistance value of the lines. In addition, because the output power of the generator is larger, the wires led out from the armature of the generator are thick-wire cables in order to meet the output of large current of the power supply. And the wire used for sampling the rotating speed signal is a thin cable. The diameters of the two cable wires are greatly different, so that the connection of the rotating speed signals can not meet the technological requirements of the parallel processing of aviation products by directly doubling the output cable at the generator end. In order to meet the requirements, a switching link is designed between the aircraft power supply control system and the rotating speed feedback signal sampling circuit, so that the generator power supply and the rotating speed signal are connected in a shunt way. The requirements of testability and circuit isolation of the rotating speed signal circuit are realized through the switching design of the two-stage connector.
Specifically, as shown in fig. 3, the power supply control system further includes a first connector and a parallel connection joint; one end of the first connector is connected with three-phase output ports of the first generator armature and the second generator armature, and the other end of the first connector is connected with a parallel joint. The first and second generator armatures output an alternating current power source through a first connector.
The first connector comprises a connector socket and a connector plug, the connector plug is connected with three-phase output ports of the first generator armature and the second generator armature, and the connector socket is connected with the parallel connection joint; the parallel connection is used for converting thick wires of the three-phase power line into a plurality of thin wires.
For example, the connector plugs have 6 connector sockets 1, 2, 3, 4, 5 and 6 corresponding to the 6 plugs, wherein the connector sockets are A, B, C, A1, B1 and C1 respectively; 3 plugs (A, B, C) of the connector plugs are connected with the three-phase output ports of the first generator armature, and the other 3 plugs (A1, B1 and C1) are connected with the three-phase output ports of the second generator armature; each connector socket is connected with one parallel connection joint, 6 parallel connection joints are arranged, namely JT-A, JT-B, JT-C, JT-A1, JT-B1 and JT-C1, each parallel connection joint corresponds to one phase of the first generator armature and one phase of the second generator armature, and specifically, the parallel connection joints JT-A, JT-B, JT-C correspond to three phases of the first generator armature, and the parallel connection joints JT-A1, JT-B1 and JT-C1 correspond to three phases of the second generator armature.
The three-phase power line is respectively converted from a thick wire with the wire diameter of 2.0mm 2 to a plurality of thin wires with the wire diameter of 0.5mm 2 through JT-A, JT-B, JT-C, JT-A1, JT-B1 and JT-C1 parallel joints, so that the non-compliance process condition that the thin wires are directly connected on the thick wires in parallel is avoided.
Specifically, the power supply control system further comprises a second connector, the second connector comprises a connector plug and a connector socket, the connector socket is connected with the parallel connection joint and used for collecting an alternating voltage signal output by an armature of the generator to serve as an engine rotating speed feedback signal, and the connector plug is connected with the interface of the control equipment and used for transmitting the engine rotating speed feedback signal to a rotating speed sampling circuit inside the control equipment.
Illustratively, the second connector comprises 4 connector plugs (A, B, A, B1), 4 connector receptacles (1, 2, 3, 4); the 4 connector sockets are respectively connected with one parallel connection joint, and the 4 parallel connection joints connected with the 4 connector sockets correspond to any two-phase output ports of the first generator armature and any two-phase output ports of the second generator armature.
Illustratively, 4 connector receptacles 1, 2, 3, 4 are connected with parallel connectors JT-A, JT-B, JT-A1, JT-B1, respectively; the power supply signal of the armature of the first generator is led out to be a rotating speed feedback signal 1 through the parallel connection joint of the JT-A and the JT-B. And the power supply signal of the armature of the second generator is led out to be a rotating speed feedback signal 2 through a parallel joint of JT-A1 and JT-B1.
For measuring the engine speed signal, it is necessary to obtain at least two phase voltage signals in the three phase ac of the generator armature, but it is also possible to choose to connect 4 connector sockets 1, 2, 3, 4 with JT-A, JT-C, JT-A1 and JT-C1, or with JT-B, JT-C, JT-B1 and JT-C1, respectively.
The parallel switching design can realize the sampling of the rotating speed feedback signals of the two independent armature coils, thereby achieving the redundant measurement of the rotating speed feedback signals of the engine and improving the reliability of the control system.
And the collected rotating speed feedback signal is transmitted to a rotating speed feedback signal sampling circuit inside the control equipment through the interface connection of the second connector and the control equipment.
The rotating speed feedback signal sampling circuit mainly comprises a transformer (front-end circuit), a detection circuit, photoelectric isolation, an FPGA and a DSP;
the transformer in the control equipment isolates the input alternating voltage signal, so that the external circuit and the internal circuit of the control equipment are not connected with direct current signals. The alternating voltage signal obtained by the back stage of the transformer is converted into a standard square wave signal by a detection circuit. And then the signals are converted into digital signals which can be processed by the FPGA circuit through photoelectric isolation. The FPGA is a programmable logic device adopted in the controller, and is an integrated device for comprehensively processing various signals of the controller. One of the functions is to count the frequency of the square wave signal which is digitally processed, and then obtain a voltage value result through frequency-voltage conversion. The voltage result obtained by the sampling processing is used by an application program operated by the DSP processor to carry out rotation speed identification and control on the engine.
The front-end circuit of the rotating speed sampling circuit realizes the switching of the rotating speed feedback signal through the second connector, so that the open-circuit isolation of the rotating speed sampling circuit is realized under the test condition;
by separating the connection of the first connector plug and the receptacle, the coil resistances of the first generator armature and the second generator armature can be independently measured from the first connector plug side;
by separating the connection of the second connector plug and the socket, the primary coil resistance of the sampling transformer of the rotating speed feedback signal 1 and the rotating speed feedback signal 2 can be independently measured from the side of the second connector plug;
by separating the connection of the first connector and the connection of the second connector, the transit cabling resistance can be measured independently from the first connector receptacle side and the second connector receptacle side.
And judging whether short circuit or open circuit exists in the circuit according to all the resistance values, and ensuring that the rotating speed sampling circuit and the front end acquisition circuit are in a normal state so as to ensure that an engine rotating speed signal can be accurately acquired after the aircraft takes off.
The circuit of the application relates to an aircraft generator power supply circuit, and in the early design, a rotating speed signal is directly connected in parallel with an armature output cable end of a generator. Because the switching connector is not designed, after the rotating speed signal sampling equipment is installed on the aircraft, whether short circuit faults exist in the rotating speed transmission circuit cannot be judged by measuring the line resistance state. Because the line diameter of the rotating speed signal line is too small, the signal line breaks under the condition of stress concentration after the rotating speed signal line is connected with the generator power line in parallel. Therefore, the application achieves the aim of three-aspect line isolation test through improvement, and is convenient for line inspection. On the other hand, the purpose of leading out the rotating speed signal is achieved by utilizing the design of a parallel connection joint from the thick line to the thin line of the power line.
Those skilled in the art will appreciate that all or part of the flow of the methods of the embodiments described above may be accomplished by way of a computer program to instruct associated hardware, where the program may be stored on a computer readable storage medium. Wherein the computer readable storage medium is a magnetic disk, an optical disk, a read-only memory or a random access memory, etc.
The present application is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present application are intended to be included in the scope of the present application.
Claims (8)
1. An aircraft power supply control system, the power supply control system comprising: the control device comprises a control device, a first relay, a second relay, an external power supply, a main battery, a first generator armature output power supply, a second generator armature output power supply and a direct current bus;
the external power supply, the main battery and the armature output power supply of the first generator supply power to the direct current bus; the direct current bus is directly connected with a stable working condition load;
the armature output power supply of the second generator is connected with a high-power variable-working-condition load;
the coil control ends of the first relay and the second relay are connected with the control equipment and are used for realizing switching action according to a control instruction sent by the control equipment;
the first relay is connected between the positive electrode of the direct current bus and the positive electrode of the armature output power supply of the second generator, and the second relay is connected between the negative electrode of the direct current bus and the negative electrode of the armature output power supply of the second generator;
the normally closed contact of the first relay is connected with the positive electrode of the direct current bus, and the midpoint of the switch is connected with the positive electrode of the armature output power supply of the second generator; the normally closed contact of the second relay is connected with the negative electrode of the direct current bus, and the midpoint of the switch is connected with the negative electrode of the armature output power supply of the second generator;
when the first relay and the second relay coil control end receive the control instruction sent by the control equipment, the normally closed contact is opened, so that the direct current bus is disconnected with the armature output power supply of the second generator and the high-power variable-working-condition load.
2. An aircraft power supply control system according to claim 1, wherein the external power source comprises a power source DC1 and a power source DC-fl; the power supply DC-fl is connected with the direct current bus and used for supplying power to the direct current bus, and the power supply DC1 is connected with the stable working condition load and used for supplying power to the stable working condition load.
3. The aircraft power supply control system of claim 1, wherein the first generator armature output power source comprises a first generator armature, a first full wave rectifier circuit; the second generator armature output power supply comprises a second generator armature and a second full-wave rectifying circuit; the first generator armature and the second generator armature are two independent armatures on the same rotor, and the alternating current power supplies output by the two armatures are converted by the respective full-wave rectifying circuits and then output two paths of direct current power supplies.
4. The aircraft power supply control system of claim 1, further comprising a first connector, a parallel connection; one end of the first connector is connected with three-phase output ports of the first generator armature and the second generator armature, the other end of the first connector is connected with a parallel line connector, and the first generator armature and the second generator armature output alternating current power sources through the first connector.
5. The aircraft power supply control system of claim 4, wherein the first connector comprises a connector receptacle and a connector plug, the connector plug being connected to the three-phase output ports of the first generator armature and the second generator armature, the connector receptacle being connected to the parallel connection; the parallel connection is used for converting thick wires of the three-phase power line into a plurality of thin wires.
6. An aircraft power supply control system according to claim 5, wherein there are 6 connector plugs, and 6 connector sockets corresponding to the 6 plugs are provided; 3 plugs in the connector plugs are connected with the three-phase output port of the first generator armature, and the other 3 plugs are connected with the three-phase output port of the second generator armature; each connector socket is connected with one parallel connection joint, 6 parallel connection joints are arranged, and each parallel connection joint corresponds to one phase of the first generator armature and the second generator armature.
7. The aircraft power supply control system of claim 6, further comprising a second connector including a connector plug and a connector socket, the connector socket being connected to the parallel connection for collecting an ac voltage signal output by the generator armature as an engine speed feedback signal, the connector plug being interfaced with the control device for transmitting the engine speed feedback signal to a speed sampling circuit within the control device.
8. The aircraft power supply control system of claim 7, wherein the second connector comprises 4 connector plugs, 4 connector receptacles; the 4 connector sockets are respectively connected with one parallel connection joint, and the 4 parallel connection joints connected with the 4 connector sockets correspond to any two-phase output ports of the first generator armature and any two-phase output ports of the second generator armature.
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| CN105353682A (en) * | 2015-11-20 | 2016-02-24 | 泉州装备制造研究所 | Airplane power supply system experiment platform device |
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