JPH11117811A - Engine for aircraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To load engine data down to ground equipment positively with excellent workability by providing a radiocommunication device for radio-transmitting engine data on the basis of a transmit command radio-received from the ground equipment. SOLUTION: A radiocommunication device 6 transmits engine data to ground equipment B on the basis of a transmit command radio-received from the ground equipment B. This radiocommunication device 6 is composed of an MPU, a memory stored with a communication program for putting the MPU in specified communicating action, and a transmit-receive circuit for modulating/ demodulating carrier wave. Upon receiving a transmit command assigning the control number of an engine A from the ground equipment, data is read out of an engine function diagnostic device 5 and transmitted to the ground equipment B. Engine data can therefore be loaded down to the ground equipment positively with excellent workability.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft engine, and more particularly to a technique for maintenance and inspection thereof.

[0002]

2. Description of the Related Art Current aircraft engines (hereinafter simply referred to as engines) are required to operate stably.
Some include an engine function diagnostic device that monitors the operating state of the engine and sequentially stores it. This engine function diagnostic device receives various data (engine data) indicating the operation state of the engine from an engine control device that controls the operation of the engine, and stores the engine data for use in maintenance and inspection of the engine. It is.

In a conventional engine having such an engine function diagnosis device, when the engine data is used for maintenance and inspection of the engine, the engine function diagnosis device is provided with a display for displaying the engine data. Has been adopted in which the display of the image is read visually by an operator. Alternatively, a means has been used in which a cable for reading engine data is connected to the engine function diagnosis device, and the engine data is downloaded to a computer or the like on the ground.

[0004]

However, in the case of the former means, an engine data reading error, a separate recording sheet needs to be prepared, or the engine data written on the recording sheet needs to be sorted out. There was a problem in the reliability and operability of data reading operations. In the case of the latter means, a small window or the like provided in a part of the engine exterior for cable connection is opened,
The connector of the cable is connected to the connector provided in the engine function diagnosis device. However, there are problems such as the necessity of ancillary equipment called the cable, and deterioration of the connector due to attachment / detachment and poor contact. . Particularly, in the case of an engine for an aircraft, since a use environment such as a pressure and an ambient temperature greatly changes, connectors and the like that require physical contact are easily deteriorated.

The present invention has been made in view of the above-mentioned problems, and has the following objects. (1) To provide an aircraft engine capable of downloading engine data reliably and with good workability. (2) To provide an aircraft engine capable of downloading engine data without requiring physical contact.

[0006]

In order to achieve the above object, according to the present invention, there is provided, as a first means, an aircraft engine provided with a storage means for sequentially storing operating conditions as engine data. Means is provided that includes a wireless communication device that wirelessly transmits the engine data based on the received transmission instruction. As a second means, in the present invention, the first means employs a means in which a wireless communication apparatus is configured to assign an engine management number to engine data and transmit the engine data to ground equipment. Further, as a third means, in the present invention, in the second means, the engine data is wirelessly transmitted to the ground equipment only when the reception command includes the management number of the engine designating the engine. Means for configuring a wireless communication device.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of an aircraft engine according to the present invention will be described below with reference to the drawings.

FIG. 1 is a block diagram showing the configuration of the present embodiment. In this figure, reference numeral A denotes an engine mounted on an aircraft, and B denotes a ground facility provided on the ground for maintenance and inspection of the engine A. In the engine A, 1 is an engine main body, 3 is an engine control device, 4 is a sensor, 5 is an engine function diagnostic device, and 6 is a wireless communication device.

The engine body 1 is composed of a compressor for compressing air sucked from the front, a turbine for rotating the compressor and discharging the compressed air to the rear. Various accessories related to the engine A are provided on the outer periphery of the engine body 1.

[0010] The engine control device 3 includes one of the auxiliary machines.
That is, the operation of the engine body 1 is electrically controlled. For example, this engine control device 3 includes MP
This is a digital engine control device including a U (microprocessor) and a memory storing a control program for causing the MPU to perform a predetermined control operation. The sensor 4 is provided in each part of the engine main body 1, detects an operation state of each part, and outputs the operation state to the engine control device 3. For example, the sensor 4 detects the number of revolutions of the engine body 1, the fuel supply amount, the temperature, and the like, and outputs them to the engine control device 3. The engine control device 3 controls the operation of the engine main body 1 based on the various information input from the sensor 4 and the control program.

Further, such an engine control device 3
Various information input from the sensor 4, the engine body 1
, The control information relating to its own control operation, and the information relating to the failure of each part of the engine main body 1 and the like are sequentially supplied to the engine function diagnosis device 5.
The engine function diagnosis device 5 sequentially stores these pieces of information supplied from the engine control device 3 in a time-series manner as engine data. Further, the management number of the engine A is registered and stored in the engine function diagnosis device 5 in advance.

The wireless communication device 6 transmits the above-described engine data to the ground equipment B based on a transmission command wirelessly received from the ground equipment B. This wireless communication device 6
Is composed of, for example, an MPU, a memory storing a communication program for causing the MPU to perform a predetermined communication operation, a transmission / reception circuit for modulating / demodulating a carrier wave, and the like. When the transmission command specifying the management number is received, the engine function diagnostic device 5
The engine data is read out from and transmitted to the ground equipment B.

Next, from the wireless communication device 6 to the ground equipment B
The operation of transmitting engine data to the server will be described.

A plurality of aircraft have their respective engines A
The management number is assigned to each of the engine function diagnosis devices 5
Is stored in In such a situation, the ground equipment B sequentially downloads the engine data of each engine A by designating a management number for the aircraft whose maintenance and inspection has come.

For example, when there are aircraft K1 to K5 for which engine data needs to be downloaded, the ground equipment B receives the management numbers a1 to a5 of the engines A1 to A5 of the aircraft K1 to K5. The ground equipment B first transmits a command to transmit engine data by designating the first management number a1. Then, in response to this transmission command, the wireless communication device 6 of the engine A 1 reads out the engine data from the engine function diagnosis device 5 and transmits it to the ground equipment B. At this time, the wireless communication device 6 adds the management number a1 to the engine data and transmits the engine data to the ground equipment B.

When receiving the engine data of the engine A1 and the control number a1, the ground equipment B registers the engine data in the database in correspondence with the control number a1. Then, when the registration in the database is completed, a transmission command of engine data is transmitted by designating the management number a2, and the engine data of the engine A2 corresponding to the management number a2 is downloaded, and the engine data corresponding to the management number a2 is downloaded. And register it in the database.

Similarly, management numbers a3 to a5 are sequentially designated and engine data of the engines A3 to A5 are registered in the database. Thus, each engine A1
Each engine data registered in the database for A5 is used as reference information for maintenance and inspection.

[0018]

As described above, the aircraft engine according to the present invention has the following effects. (1) An aircraft engine provided with a storage unit for sequentially storing an operating state as engine data, the aircraft engine including a wireless communication device for wirelessly transmitting the engine data based on a transmission command wirelessly received from ground equipment, that is, wireless Since the engine data is downloaded to the ground equipment by communication, the engine data is downloaded to the ground equipment more reliably and with better workability than when the engine data is downloaded via a human or a cable using a cable as before. Can be downloaded. (2) Since the engine data is transmitted to the ground equipment by radio, the engine data can be downloaded to the ground equipment without requiring physical contact such as a connector. (3) Since the wireless communication device assigns the engine management number to the engine data and transmits the engine data to the ground equipment, the ground equipment can organize the engine data for each management number. (4) The wireless communication device wirelessly transmits engine data to the ground equipment only when the reception command includes the management number of the engine designating the engine. Can specify a desired engine and download engine data.

[Brief description of the drawings]

FIG. 1 is a block diagram showing a configuration of an embodiment of an aircraft engine according to the present invention.

[Explanation of symbols]

 A ... engine B ... ground equipment 1 ... engine body 3 ... engine control device 4 ... sensor 5 ... engine function diagnostic device 6 ... wireless communication device

Claims (3)

[Claims] 1. An aircraft engine comprising storage means for sequentially storing operating conditions as engine data, comprising: a wireless communication device for wirelessly transmitting the engine data based on a transmission command wirelessly received from ground equipment. An aircraft engine characterized by: 2. The aircraft engine according to claim 1, wherein the wireless communication device assigns an engine management number to the engine data and transmits the engine data to ground equipment. 3. The aircraft engine according to claim 2, wherein the wireless communication device wirelessly transmits the engine data to the ground equipment only when the reception command includes the management number of the engine designating the engine. An aircraft engine, characterized in that: