Integrated electronic system mounted on aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-013/00
B64D-047/00
H04L-012/40
출원번호
US-0514140
(2010-12-14)
등록번호
US-8977798
(2015-03-10)
우선권정보
JP-2009-284953 (2009-12-16)
국제출원번호
PCT/JP2010/007253
(2010-12-14)
§371/§102 date
20120723
(20120723)
국제공개번호
WO2011/074245
(2011-06-23)
발명자
/ 주소
Mitani, Yoichi
Tamaru, Masahiro
Ikarashi, Reiichi
Isobe, Taisei
출원인 / 주소
Kawasaki Jukogyo Kabushiki Kaisha
대리인 / 주소
Oliff PLC
인용정보
피인용 횟수 :
0인용 특허 :
10
초록▼
The present invention provides an electronic system mounted on an aircraft which can effectively reduce electronic devices and wires by integration of control systems. Specifically, a fuselage (80) of an aircraft (100) is divided into a nose part (80a), a center part (80b), and an aft part (80c), an
The present invention provides an electronic system mounted on an aircraft which can effectively reduce electronic devices and wires by integration of control systems. Specifically, a fuselage (80) of an aircraft (100) is divided into a nose part (80a), a center part (80b), and an aft part (80c), and two IMAs (integrated modular avionics units) (50a to 50c) are provided in each of these parts. The IMA units (50a to 50c) are interconnected via an integrated data bus (53) to construct an integrated electronic system mounted on the aircraft. The system is suitably used for integrating utility systems except for avionics systems, among a plurality of control systems mounted on the aircraft, and is also applicable to integration of the avionics systems.
대표청구항▼
1. An integrated electronic system mounted on an aircraft which integrates at least control systems of functions of a fuselage, among a plurality of control systems mounted on the aircraft, the integrated electronic system mounted on the aircraft comprising an integrated modular avionics unit; the i
1. An integrated electronic system mounted on an aircraft which integrates at least control systems of functions of a fuselage, among a plurality of control systems mounted on the aircraft, the integrated electronic system mounted on the aircraft comprising an integrated modular avionics unit; the integrated modular avionics unit including: a plurality of functional modules;a module casing for accommodating the plurality of functional modules in a mounted state; andin-casing data buses connected to the plurality of functional modules accommodated in the module casing;wherein the plurality of functional modules include a bus switch module connected to the functional modules via the in-casing data buses, respectively, to enable data transfer between the functional modules, the bus switch module being connected to an integrated data bus in the integrated electronic system mounted on the aircraft, directly or via an integrated data bus connection module, to enable data transfer between the functional modules and the integrated data bus,wherein an identical transmission protocol is set for the integrated data bus and the in-casing data buses. 2. An integrated electronic system mounted on an aircraft which integrates at least control systems of functions of a fuselage, among a plurality of control systems mounted on the aircraft, the integrated electronic system mounted on the aircraft comprising an integrated modular avionics unit; the integrated modular avionics unit including; a plurality of functional modules;a module casing for accommodating the plurality of functional modules in a mounted state; andin-casing data buses connected to the plurality of functional modules accommodated in the module casing;wherein the plurality of functional modules include a bus switch module connected to the functional modules via the in-casing data buses respectively, to enable data transfer between the functional modules, the bus switch module being connected to an integrated data bus in the integrated electronic system mounted on the aircraft, directly or via an integrated data bus connection module, to enable data transfer between the functional modules and the integrated data bus,wherein the plurality of functional modules in the integrated modular avionics unit include:a processor module for performing processing to control the control systems;a signal conversion module for converting input/output signals input/output to/from terminal devices in the control systems into processed signals in a predetermined format; anda digital data conversion module for performing mutual conversion between the processed signals converted by the signal conversion module and digital data which can be processed by the processor module;wherein the signal conversion module is constituted by an analog circuit and is connected to the in-casing data bus in the integrated modular avionics unit via the digital data conversion module. 3. The integrated electronic system mounted on the aircraft according to claim 2, wherein the functional modules include an aircraft communication module standardized exclusively for the aircraft. 4. An integrated electronic system mounted on an aircraft which integrates at least control systems of functions of a fuselage, among a plurality of control systems mounted on the aircraft, comprising: integrated modular avionics units provided in a nose part, a center part, and an aft part of the fuselage of the aircraft, respectively; andan integrated data bus for mutually connecting the integrated modular avionics units,wherein functional modules in each of the integrated modular avionics units include: a processor module for performing processing to control the control systems;a signal conversion module for converting input/output signals input/output to/from terminal devices in the controls systems into processed signals in a predetermined format; anda digital data conversion module for performing mutual conversion between the processed signals converted by the signal conversion module and digital data which can be processed by the processor module;wherein the signal conversion module is constituted by an analog circuit and is connected to an in-casing data bus in the integrated modular avionics unit via the digital data conversion module. 5. The integrated electronic system mounted on the aircraft according to claim 4, wherein the integrated modular avionics units are configured such that two or more integrated modular avionics units are provided in each of the nose part, the center part, and the aft part of the fuselage. 6. The integrated electronic system mounted on the aircraft according to claim 4, wherein the functional modules include an aircraft communication module standardized exclusively for the aircraft.
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이 특허에 인용된 특허 (10)
Birkedahl Byron F. ; Endrud Douglas G., Aircraft display and control system with virtual backplane architecture.
Lee Stephen Y. ; Drake Jeffrey K. ; Sherwin Greg J. ; Deloe Derek E., Method and apparatus for an avionics system utilizing both ARINC 429 and ARINC 629 compliant systems.
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