JPS6181132A - Multiple power supply system for aircraft - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed Description of the Invention] [Industrial Application Field] This invention provides a power supply system for an aircraft with two or more generators, so that even if one part fails, the power will not be cut off. This invention relates to a multiple power supply system for aircraft configured to ensure reliability.

[Conventional technology]

Power supply systems for aircraft with two or more generators include a split bus system and a parallel bus system. The first and second type will be explained below.

(1) Split bus system FIG. 2 is a system diagram showing the circuit configuration of the split bus system. In Figure 2, one generator system has two or more systems (
(This diagram shows an example of two systems), each of the two engines 59a
, 08D (Constant
5peed Drive constant speed drive device) 50a,
50b drives wound rotor type generators 51a and 51b at a constant speed, and V/L (voltage regulator) 52a,
AC power is transferred to the power converter 53a via 52b.
, 53b, and failure disconnection relay contacts (normally closed type) 54a, 54b. Power converters 58a and 53b convert alternating current to direct current, and have a relay contact (normally closed type) 55a that disconnects in the event of a failure.
, 55b, DC power is supplied to the DCC paths 57-1 and 57-2 and the DC bus 2. The AC power is connected to the AC bus 1.58-2 from the failure disconnection relay contacts 54a, 54b. A.C.
It is supplied to bus 2. 54a, 54b, 5
The failure disconnection relay contacts 5a and 55b are normally closed, but if a failure occurs in the 8 circuits, the system is opened and disconnected.1. At the same time, bus tie relay contacts (normally open type) 56a and 56h are closed to connect the circuit. From the above configuration, the sprint bus system has two or more engine-driven generator systems.

Under normal conditions, one system's generators supply power to one bus load, while the other systems' generators supply power.

This is a backup for that bus. That is, 1
In the event of a grid failure, a backup grid is connected to continue supplying power.

(2) Parallel bus system FIG. 3 is a system diagram showing the circuit configuration of the parallel bus system. In Figure 3, there are two or more 1 generator system Vi systems (
This figure shows an example of two systems), each of the two engines 69a
C8D 60a, 60b driven by , 69b
The wound rotor type generators 61a and 61b are driven at a constant speed, and v,'n 62a.

62b to power converters 63a, 6
1b, and relay contacts (normally closed type) 64a and 64b that disconnect at the time of failure. Power Conover Taro 3a, 63b converts alternating current to direct current, disconnects in case of failure, relay contact (normally closed type) 65a,
65b to the DC bus 1.67-1.67-2. It supplies DC power to DC bus 2. AC power is supplied from the fault disconnection relay contacts 64a+64b to 68-
1.68-2 indicates fAC path 1. It is supplied to AC bus 2.

The failure disconnection relay contacts 64a, 64b, 65a, and 65b are normally closed, but when a failure occurs in one circuit, that system is opened and disconnected, and at the same time, the past tie relay contacts (normally closed type) 66
a and 66b are also opened to isolate the faulty system. Reference numeral 70 denotes a frequency tuning device that tunes the frequency in order to operate the two generators 61a and 61b in parallel.

Based on the above configuration, the parallel bus system has two or more engine-driven generator systems, and during normal operation, power is supplied to one bus from all generator systems, and in the event of a failure, only that generator system can be disconnected. This method supplies power from the remaining generator system without causing momentary power outages.

[Problem that the invention seeks to solve]

The split bus system and parallel bus system described above have the following problems.

(1) Split bus system (a) When switching to the standby system due to a failure, the power supplied to the load is temporarily interrupted.

(Hereinafter referred to as a momentary power outage.) (B) Since the constituent systems are connected in series, a failure in any part of the system may result in loss of all or part of the DC or AC power supply functions of that system. cause a stoppage.

(c) V△ to create stable DC, current/AC power
, a control device like C8D is required.

This is a factor that hinders weight and reliability.

(2) Parallel bus system (a) Due to a bus short circuit failure, the entire generator system stops functioning.

(b) To operate two or more generators in parallel.

A special frequency tuning device is required, which is a factor that hinders weight and reliability.

(c) Unable to produce stable DC/AC power.

Control equipment such as V/R and CSN is required.

This is a factor that hinders weight and reliability.

The present invention is based on the fact that aircraft are becoming more computerized and equipped with digital computer computers, displays, electric control devices, etc., and systems directly related to flight safety are becoming electronic devices that operate using electric power as energy. In view of this, the objective was to stabilize and increase the reliability of the power source system and increase flight safety.

[Failure to solve the problem]

In contrast to the conventional standby redundant system (split bus system) and partially parallel redundant system (parallel bus system), the present invention constructs a parallel redundant system with one power generation section and a bus section, and provides a protection circuit against bus short circuits. This is one source of multiple parallel redundancy system, and its characteristics are as follows.

(1) Once the output of the generator is set to DC, 1. This is a power supply system in which a multiple parallel redundant system is constructed in this part, and a multiple parallel redundant system is also constructed in one bus part.

(2) In order to prevent the entire power system from shutting down in the event of a bus short-circuit failure, a power source system with multiple parallel redundant systems equipped with current limiting and backflow prevention functions converts AC power generated by a system generator into DC power. a power converter section that converts the DC power of the power generation section into a predetermined DC voltage and an AC voltage; A current limit protection circuit provided on each output side, a power transmission section that connects the output sides of multiple power generation sections in parallel, a power transmission section that connects in parallel to multiple power converter sections, and a power transmission section that connects the output sides of multiple power converter sections in parallel. The present invention provides a multiple power supply system for an aircraft characterized by comprising a bus connection section that is connected in parallel and multiplexed to a plurality of DC buses and AC buses.

[Effect]

The function of the aircraft multiple power supply of the present invention is that AC power generated three times in a power generation unit provided corresponding to a generator driven by an aircraft engine is converted into DC power. The DC outputs of these plurality of power generation sections are connected in multiple parallel to a plurality of power converter sections and inputted to the power transmission section. The DC power and AC power converted by the power converter section are connected in parallel to multiple DC buses and AC buses at the bus connection section to supply power in parallel, so even if a partial failure occurs in any of the 9 circuits, the power supply will be maintained. No momentary interruptions occur. In addition, in the event of a short circuit on the bus, it is protected by current limiting protection circuits installed on the DC output side of the first power generation section and the DC output side and AC output side of the power converter section, making it safe, compact, lightweight, and reliable. It becomes a power source with

〔Example〕

FIG. 1 is a system diagram showing the circuit configuration of the aircraft multiple power supply system of the present invention. Although FIG. 1 shows a multiple power source system, it is shown as an example of duplication.Although it is not limited to duplication, since the functions are the same, it is shown as an example of duplication. The main configuration of FIG. 1 is two engines 20a and 20.
power generation units 1a and 1b driven by power generation units 1a and lb, and a power transmission unit 8 that transmits their outputs. Power converter sections 9a and 9b convert power from the power transmission section 8 into direct current (DC) and alternating current (AC) power sources for the aircraft, and a helical connection section 1g.
.

It consists of a DC bus 1 and a DC bus 2 indicated by 21a and 21b, and an AC bus 1 and an AC bus 2 indicated by 22a and 22b.

The generator section 1a includes a generator (wound rotor type or PM rotor type) 2, which is driven by an engine 20a.

The A O/D O converter 3 converts the generated AC power into high voltage DC power (approximately 270V), and the current limiter (
C! L: current limiter) 4a, 4b.

Backflow preventers 5a, 5b connected in series thereto,
It is comprised of a BIT (Built in Te5t) circuit 6 that detects an abnormality in the AO/Do converter 3 and disconnects one circuit, and a disconnection relay 7. The power generation section 1b also has a first
In the figure, since it is the same as 1a, the inside is omitted and not shown, but it is firmly operated by the engine 20b.
It has exactly the same configuration.

The power transmission unit 8 is composed of multiple parallel redundant system wiring for transmitting the electric power generated in one power generation unit 1a and 1b to power converter units 9a and 9b.

The power converter unit 9a includes a DC/D O converter 10, a current limiter (CL: current limiter) lla, llb for the output thereof, and a DC/D O converter 10, which converts the sent electric power into a 28 VDO system for aircraft, and serially connected to them. Also connected backflow preventers 12a, 12b. D.C.
When the /DO converter 10 is abnormal, a BIT circuit 13 that detects it and disconnects the circuit, a disconnection relay 14, and an aircraft 4
00Hz, 115VAC system part D (E/A
C converter 15 and its current limiter 16a, 1-6b
It is composed of two parts: a BIT circuit 17 that detects an abnormality in the DC/AC converter 15 and disconnects the circuit, and a disconnection relay 18. Although the inside of the power converter section 9b is not shown, it has exactly the same configuration as the power converter section 9a. The bus connection section 19 is a power converter section 9a.

DC power converted by 9b is shown by 21a, 21b
A shown as bus 1 and DC bus 2, 22a, 22b
This is multiple parallel redundant system wiring for sending data to C bus 1 and AC bus 2.

Next, the operation of the embodiment having the above configuration will be explained.

The DC power converted by the power generation units 1a and lb is transferred to the power transmission unit 8.
The power is connected in parallel and supplied to the power converters 9a and 9b from each power generation section. The direct current and alternating current powers not converted by the power converters 9a and 9b are multiplexed and connected in parallel by the bus connection unit 19 to form four types of buses.

DC buses 1.21a and 21b. DC bus 2,2
AC bus 1. shown as 2a and 22b. They are each connected to and supplied to the AC bus 2. Due to this circuit configuration, the overall configuration is a multiple parallel redundant system (parallel bus system), and there is no momentary interruption. In addition, the power transmission section 8 after 6 power generation,
DC buses 1.21a, 21b, 22a, 22b; DC pass 2. AC bus 1. Because a multiple parallel redundant system was constructed with the bus connection section 19 of the Aye bus 2 to the aircraft power supply bus, even in conventional dual systems, the power converter section of one system and the power generation section of the other system failed. When DC
This resulted in the loss of the power supply system.

In this configuration, as long as one power converter section in the duplex (multiplex) system and one of the generator systems are active, power can be supplied to the entire aircraft power system.

In addition, regarding the drawback of the conventional multiple parallel redundant system (parallel bus system), which is that the entire aircraft power supply system is lost due to a path short circuit, the current is limited before setting up the multiple parallel redundant system in the power transmission section 8 4a and 4b, and the current limiters 11a and 11 before constructing a multiple parallel redundant system using the bus connection section 19.
b, 16a, 16b, and a backflow preventer 5a in series with these.

Connect 5b, 12a, and 12b to create a configuration.

A short circuit in one system does not seem to affect other systems, greatly improving reliability. or.

The AC power from the generator 2 is not directly used as a power source for the aircraft, but is converted into high-voltage DC at the power generation section 1a. (The same applies to the system of the power generation unit 1b). In addition, in order to stabilize the first frequency, mechanical parts (frequency tuning device 70 and C3D60a in Fig.
, part 60b) is no longer needed and can be made entirely electronic.

A small and lightweight system can be created.

9 In this embodiment, the explanation was made as a power source for an aircraft, but
It can be applied to power supplies for other plants, such as atomic couplants, computer systems, and other systems that would be seriously affected by a momentary power outage.

〔Effect of the invention〕

According to the aircraft multiple power supply system of the present invention described above, the AC output of one generator is converted to DC in the power generation section, and the outputs of multiple power generation sections are connected in parallel in the power transmission section to create a plurality of power converters. Connect to the section. The power converter section converts the DC output from the power generation section into specified AC and DC power.

By connecting the outputs of a plurality of power converters in parallel to the DC bus and AC bus, a remarkable effect of the ninth order is produced.

(1) The system has no interruption even if a partial failure occurs.

(2) Because multiple parallel redundancy is used and the structure is made safe against bassinyotes, it is not possible to obtain higher reliability than in the past.

(3) Since it can be fully electronic, it can be made smaller and lighter. Moreover, it has been indispensable in the past because high reliability cannot be obtained.

A system that does not require a backup battery is conceivable.

(4) The generator can have an irregular period and an irregular voltage.

For example, PM (PARMAN) has a simple structure and high efficiency.
ENT MAGNET) rotor generator etc. can be used.

Additionally, since power is transmitted using high DC voltage midway through the system, the amount of current flowing can be reduced, reducing transmission loss and reducing the weight of the system as the wire length can be made thinner.

[Brief explanation of drawings]

Figure 1 is a system diagram showing the circuit configuration of the aircraft multiple power supply system of the present invention, Figure 2 is a system diagram showing the circuit configuration of the conventional aircraft power supply system, the split bus system, and Figure 3 is the same (conventional FIG. 1 is a system diagram showing a circuit configuration of a parallel bus system that is an aircraft power source. la, lb: power generation section, 2: generator, 3: AC/DC conversion 5, 4a, 4b: current limiter, 5a, 5b:
Backflow preventer, 8: Power transmission section, 9a, 9b: Power converter section, 1o: Do/Do converter, lla
, llb: flow restrictor, 12a, 12b:
Backflow preventer, 15: Do/AO converter, 16a
, 16b: current limiter, 19: bus connection section, 21a:
DO Babasu, 21b: DC! Bus 2.22a: Ao Babas, 22b: AO Babas. 4,1-Yu!

Claims (1)

[Claims] A power generation unit that converts AC power generated by a generator into DC power, a power converter unit that converts the DC power of the power generation unit into predetermined DC voltage and AC voltage, a DC output side of the power generation unit, and a power converter. A power transmission section that connects the output sides of multiple power generation sections in parallel and connects them in parallel to multiple power converter sections; A multiple power supply system for an aircraft, comprising: a bus connection section that connects output sides of converter sections in parallel and multiplexes connections to a plurality of DC buses and AC buses.