[go: up one dir, main page]

CN101916111A - A fly-by-wire flight control system structure - Google Patents

A fly-by-wire flight control system structure Download PDF

Info

Publication number
CN101916111A
CN101916111A CN201010260070.2A CN201010260070A CN101916111A CN 101916111 A CN101916111 A CN 101916111A CN 201010260070 A CN201010260070 A CN 201010260070A CN 101916111 A CN101916111 A CN 101916111A
Authority
CN
China
Prior art keywords
flight control
digital
main
control system
emergency backup
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201010260070.2A
Other languages
Chinese (zh)
Inventor
周成
樊战旗
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
No 618 Research Institute of China Aviation Industry
Original Assignee
No 618 Research Institute of China Aviation Industry
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by No 618 Research Institute of China Aviation Industry filed Critical No 618 Research Institute of China Aviation Industry
Priority to CN201010260070.2A priority Critical patent/CN101916111A/en
Publication of CN101916111A publication Critical patent/CN101916111A/en
Pending legal-status Critical Current

Links

Images

Landscapes

  • Control By Computers (AREA)

Abstract

本发明属于飞行控制技术，涉及对电传飞行控制系统结构的改进。它由飞行控制计算机[1]、指令传感器[6]、反馈传感器[7]、离散开关[8]和舵机[9]组成，飞行控制计算机[1]由信号调理电路[4]、DFCS主数字飞行控制系统[2]和数字伺服控制器[5]组成，数字伺服控制器[5]包括伺服放大器[10]和主/备切换开关[11]；其特征在于，所说的数字伺服控制器[5]中有一个DEFCS数字应急备份飞行控制模块[12]，信号调理电路[4]的信号输出端与DEFCS数字应急备份飞行控制模块[12]的输入端连接，DEFCS数字应急备份飞行控制模块[12]的输出端与主/备切换开关[11]的常开触点连接。本发明的结构简单，体积小，成本低，便于调试，可靠性高。

Figure 201010260070

The invention belongs to the flight control technology and relates to the improvement of the structure of the fly-by-wire flight control system. It consists of flight control computer [1], command sensor [6], feedback sensor [7], discrete switch [8] and steering gear [9]. The flight control computer [1] is composed of signal conditioning circuit [4], DFCS main A digital flight control system [2] and a digital servo controller [5] are composed, and the digital servo controller [5] includes a servo amplifier [10] and a main/standby switch [11]; it is characterized in that said digital servo control There is a DEFCS digital emergency backup flight control module [12] in the device [5], the signal output end of the signal conditioning circuit [4] is connected with the input end of the DEFCS digital emergency backup flight control module [12], and the DEFCS digital emergency backup flight control module The output terminal of the module [12] is connected with the normally open contact of the master/standby changeover switch [11]. The invention has the advantages of simple structure, small volume, low cost, convenient debugging and high reliability.

Figure 201010260070

Description

一种电传飞行控制系统结构 A fly-by-wire flight control system structure

技术领域technical field

本发明属于飞行控制技术，涉及对电传飞行控制系统结构的改进。The invention belongs to the flight control technology and relates to the improvement of the structure of the fly-by-wire flight control system.

背景技术Background technique

目前一个通道的电传飞行控制系统结构参见图1，它由它由飞行控制计算机1、指令传感器6、反馈传感器7、离散开关8和舵机9组成。飞行控制计算机1由信号调理电路4、DFCS主数字飞行控制系统2、AEFCS模拟应急备份飞行控制模块3和数字伺服控制器5组成。数字伺服控制器5由伺服放大器10和主/备切换开关11组成。指令传感器6、反馈传感器7和离散开关8的信号输出端分别与信号调理电路4的相应输入端连接，信号调理电路4的信号输出端分别与DFCS主数字飞行控制系统2和AEFCS模拟应急备份飞行控制模块3的信号输入端连接，主/备切换开关11是一个单刀双掷开关，DFCS主数字飞行控制系统2的信号输出端与主/备切换开关11的常闭触点连接，AEFCS模拟应急备份飞行控制模块3的信号输出端与主/备切换开关11的常开触点连接，主/备切换开关11的公共端与伺服放大器10的输入端连接，伺服放大器10的输出端与舵机9连接。上述结构的工作原理是：正常状态下，来自指令传感器6、反馈传感器7和离散开关8的信号经信号调理电路4进行调理后同时输入DFCS主数字飞行控制系统2和AEFCS模拟应急备份飞行控制模块3对上述信号进行解算处理，得到舵机控制信号。但AEFCS模拟应急备份飞行控制模块3的输出被断开，DFCS主数字飞行控制系统2经主/备切换开关11输出舵机控制信号给伺服放大器控制舵机工作。当DFCS主数字飞行控制系统2出现故障时，可以手动操纵主/备切换开关11进行主/备切换；也可以自动进行主/备切换。当需要自动进行主/备切换时，主/备切换开关11的控制信号输入端与DFCS主数字飞行控制系统2的主/备切换开关控制信号输出端连接。当DFCS主数字飞行控制系统2的主/备切换开关控制信号输出端输出主/备切换信号时，主/备切换开关11进行主/备切换。在应急备份工作状态下，AEFCS模拟应急备份飞行控制模块3输出舵机控制信号给伺服放大器控制舵机工作。其缺点是：AEFCS模拟应急备份飞行控制模块3是用硬件实现的模拟电路，结构复杂，体积大，成本高，调试工作量大，可靠性低。The fly-by-wire flight control system structure of a current channel is shown in FIG. 1 , which consists of a flight control computer 1 , a command sensor 6 , a feedback sensor 7 , a discrete switch 8 and a steering gear 9 . Flight control computer 1 is composed of signal conditioning circuit 4 , DFCS main digital flight control system 2 , AEFCS analog emergency backup flight control module 3 and digital servo controller 5 . The digital servo controller 5 is composed of a servo amplifier 10 and a main/standby switch 11 . The signal output terminals of the command sensor 6, the feedback sensor 7 and the discrete switch 8 are respectively connected with the corresponding input terminals of the signal conditioning circuit 4, and the signal output terminals of the signal conditioning circuit 4 are respectively connected with the DFCS main digital flight control system 2 and the AEFCS simulated emergency backup flight The signal input terminal of the control module 3 is connected, the main/standby switch 11 is a single-pole double-throw switch, the signal output terminal of the DFCS main digital flight control system 2 is connected with the normally closed contact of the main/standby switch 11, and the AEFCS simulates the emergency The signal output end of the backup flight control module 3 is connected to the normally open contact of the master/standby switch 11, the common end of the master/standby switch 11 is connected to the input end of the servo amplifier 10, and the output end of the servo amplifier 10 is connected to the steering gear 9 connections. The working principle of the above structure is: under normal conditions, the signals from the command sensor 6, the feedback sensor 7 and the discrete switch 8 are conditioned by the signal conditioning circuit 4 and then simultaneously input into the DFCS main digital flight control system 2 and the AEFCS analog emergency backup flight control module 3. Calculate and process the above signals to obtain steering gear control signals. However, the output of the AEFCS analog emergency backup flight control module 3 is disconnected, and the DFCS main digital flight control system 2 outputs the steering gear control signal to the servo amplifier to control the steering gear through the main/standby switch 11 . When the DFCS main digital flight control system 2 fails, the main/standby switch 11 can be manually operated to perform the main/standby switch; the main/standby switch can also be automatically performed. When automatic master/standby switching is required, the control signal input end of the master/standby switch 11 is connected to the control signal output end of the master/standby switch 2 of the DFCS main digital flight control system 2 . When the master/standby switch control signal output terminal of DFCS main digital flight control system 2 outputs a master/standby switch signal, the master/standby switch 11 performs master/standby switch. In the emergency backup working state, the AEFCS simulates the emergency backup flight control module 3 to output the steering gear control signal to the servo amplifier to control the steering gear to work. Its disadvantages are: the AEFCS analog emergency backup flight control module 3 is an analog circuit implemented by hardware, with complex structure, large volume, high cost, heavy debugging workload and low reliability.

发明内容Contents of the invention

本发明的目的是：提出一种结构简单、体积小、成本低、便于调试、可靠性高的电传飞行控制系统结构。The object of the present invention is to propose a fly-by-wire flight control system structure with simple structure, small volume, low cost, easy debugging and high reliability.

本发明的技术方案是：一种电传飞行控制系统结构，它由飞行控制计算机1、指令传感器6、反馈传感器7、离散开关8和舵机9组成，飞行控制计算机1由信号调理电路4、DFCS主数字飞行控制系统2和数字伺服控制器5组成，数字伺服控制器5包括伺服放大器10和主/备切换开关11；指令传感器6、反馈传感器7和离散开关8的信号输出端分别与信号调理电路4的相应输入端连接，信号调理电路4的信号输出端与DFCS主数字飞行控制系统2的信号输入端连接，主/备切换开关11是一个单刀双掷开关，DFCS主数字飞行控制系统2的信号输出端与主/备切换开关11的常闭触点连接，主/备切换开关11的公共端与伺服放大器10的输入端连接，伺服放大器10的输出端与舵机9连接；其特征在于，所说的数字伺服控制器5中有一个DEFCS数字应急备份飞行控制模块12，在DEFCS数字应急备份飞行控制模块12中储存有应急备份控制律程序，信号调理电路4的信号输出端与DEFCS数字应急备份飞行控制模块12的输入端连接，DEFCS数字应急备份飞行控制模块12的输出端与主/备切换开关11的常开触点连接。The technical scheme of the present invention is: a kind of fly-by-wire flight control system structure, and it is made up of flight control computer 1, instruction sensor 6, feedback sensor 7, discrete switch 8 and steering gear 9, and flight control computer 1 is made up of signal conditioning circuit 4, The DFCS main digital flight control system 2 is composed of a digital servo controller 5, and the digital servo controller 5 includes a servo amplifier 10 and a main/standby switch 11; The corresponding input terminal of the conditioning circuit 4 is connected, the signal output terminal of the signal conditioning circuit 4 is connected with the signal input terminal of the DFCS main digital flight control system 2, the main/standby switch 11 is a single-pole double-throw switch, and the DFCS main digital flight control system The signal output end of 2 is connected with the normally closed contact of main/standby switch 11, and the common end of main/standby switch 11 is connected with the input end of servo amplifier 10, and the output end of servo amplifier 10 is connected with steering gear 9; It is characterized in that there is a DEFCS digital emergency backup flight control module 12 in the said digital servo controller 5, and an emergency backup control law program is stored in the DEFCS digital emergency backup flight control module 12, and the signal output terminal of the signal conditioning circuit 4 is connected to the The input end of the DEFCS digital emergency backup flight control module 12 is connected, and the output end of the DEFCS digital emergency backup flight control module 12 is connected with the normally open contact of the main/standby switch 11 .

本发明的优点是：结构简单，体积小，成本低，便于调试，可靠性高。本发明的一个实施例，体积减少了10％以上，成本下降了10％以上。The invention has the advantages of simple structure, small volume, low cost, convenient debugging and high reliability. In an embodiment of the present invention, the volume is reduced by more than 10%, and the cost is reduced by more than 10%.

附图说明Description of drawings

图1是现有的一个通道的电传飞行控制系统结构框图。Figure 1 is a structural block diagram of an existing fly-by-wire flight control system for one channel.

图2是本发明的系统结构框图。Fig. 2 is a system structure block diagram of the present invention.

具体实施方式Detailed ways

下面对本发明做进一步详细说明。参见图2，一种电传飞行控制系统结构，它由飞行控制计算机1、指令传感器6、反馈传感器7、离散开关8和舵机9组成，飞行控制计算机1由信号调理电路4、DFCS主数字飞行控制系统2和数字伺服控制器5组成，数字伺服控制器5包括伺服放大器10和主/备切换开关11；指令传感器6、反馈传感器7和离散开关8的信号输出端分别与信号调理电路4的相应输入端连接，信号调理电路4的信号输出端与DFCS主数字飞行控制系统2的信号输入端连接，主/备切换开关11是一个单刀双掷开关，DFCS主数字飞行控制系统2的信号输出端与主/备切换开关11的常闭触点连接，主/备切换开关11的公共端与伺服放大器10的输入端连接，伺服放大器10的输出端与舵机9连接；其特征在于，所说的数字伺服控制器5中有一个DEFCS数字应急备份飞行控制模块12，DEFCS数字应急备份飞行控制模块12中储存有应急备份控制律程序，信号调理电路4的信号输出端与DEFCS数字应急备份飞行控制模块12的输入端连接，DEFCS数字应急备份飞行控制模块12的输出端与主/备切换开关11的常开触点连接。The present invention will be described in further detail below. Referring to Fig. 2, a fly-by-wire flight control system structure is composed of flight control computer 1, command sensor 6, feedback sensor 7, discrete switch 8 and steering gear 9, flight control computer 1 is composed of signal conditioning circuit 4, DFCS main digital The flight control system 2 is composed of a digital servo controller 5, and the digital servo controller 5 includes a servo amplifier 10 and a main/standby switch 11; the signal output terminals of the command sensor 6, the feedback sensor 7 and the discrete switch 8 are respectively connected with the signal conditioning circuit 4 The signal output terminal of the signal conditioning circuit 4 is connected to the signal input terminal of the DFCS main digital flight control system 2, the main/standby switch 11 is a single-pole double-throw switch, and the signal of the DFCS main digital flight control system 2 The output end is connected with the normally closed contact of main/standby switch 11, and the common end of main/standby switch 11 is connected with the input end of servo amplifier 10, and the output end of servo amplifier 10 is connected with steering gear 9; It is characterized in that, There is a DEFCS digital emergency backup flight control module 12 in the said digital servo controller 5, and the emergency backup control law program is stored in the DEFCS digital emergency backup flight control module 12, and the signal output terminal of the signal conditioning circuit 4 is connected to the DEFCS digital emergency backup flight control module 12. The input end of the flight control module 12 is connected, and the output end of the DEFCS digital emergency backup flight control module 12 is connected with the normally open contact of the main/standby switch 11 .

本发明的工作原理是：取消了AEFCS模拟应急备份飞行控制模块3，在数字伺服控制器5中增加设计了DEFCS数字应急备份飞行控制模块12，信号调理电路4的输出的来自指令传感器6、反馈传感器7、离散开关8的信号直接输入数字伺服控制器5中的DEFCS数字应急备份飞行控制模块12，当主/备切换开关11转换到应急备份状态时，由DEFCS数字应急备份飞行控制模块12中的应急备份控制律解算并输出舵机控制信号。DEFCS数字应急备份飞行控制模块12可以由硬件或者软件组成。在本发明的一个实施例中，将AEFCS模拟应急备份飞行控制模块3需要实现的功能以软件的形式存储在数字伺服控制器5的CPU中。The working principle of the present invention is: the AEFCS analog emergency backup flight control module 3 is canceled, and the DEFCS digital emergency backup flight control module 12 is designed in the digital servo controller 5, and the output of the signal conditioning circuit 4 comes from the command sensor 6, feedback The signals of sensors 7 and discrete switches 8 are directly input to the DEFCS digital emergency backup flight control module 12 in the digital servo controller 5. The emergency backup control law is solved and the steering gear control signal is output. The DEFCS digital emergency backup flight control module 12 can be composed of hardware or software. In one embodiment of the present invention, the functions to be realized by the AEFCS analog emergency backup flight control module 3 are stored in the CPU of the digital servo controller 5 in the form of software.

Claims (1)

1.一种电传飞行控制系统结构，它由飞控计算机[1]、指令传感器[6]、反馈传感器[7]、离散开关[8]和舵机[9]组成，飞行控制计算机[1]由信号调理电路[4]、DFCS主数字飞行控制系统[2]和数字伺服控制器[5]组成，数字伺服控制器[5]包括伺服放大器[10]和主/备切换开关[11]；指令传感器[6]、反馈传感器[7]和离散开关[8]的信号输出端分别与信号调理电路[4]的相应输入端连接，信号调理电路[4]的信号输出端与DFCS主数字飞行控制系统[2]的信号输入端连接，主/备切换开关[11]是一个单刀双掷开关，DFCS主数字飞行控制系统[2]的信号输出端与主/备切换开关[11]的常闭触点连接，主/备切换开关[11]的公共端与伺服放大器[10]的输入端连接，伺服放大器[10]的输出端与舵机[9]连接；其特征在于，所说的数字伺服控制器[5]中有一个DEFCS数字应急备份飞行控制模块[12]，在DEFCS数字应急备份飞行控制模块[12]中储存有应急备份控制律程序，信号调理电路[4]的信号输出端与DEFCS数字应急备份飞行控制模块[12]的输入端连接，DEFCS数字应急备份飞行控制模块[12]的输出端与主/备切换开关[11]的常开触点连接。1. A fly-by-wire flight control system structure, which is composed of flight control computer [1], command sensor [6], feedback sensor [7], discrete switch [8] and steering gear [9]. The flight control computer [1] ] consists of signal conditioning circuit [4], DFCS main digital flight control system [2] and digital servo controller [5], digital servo controller [5] includes servo amplifier [10] and master/standby switch [11] ; The signal output terminals of the command sensor [6], the feedback sensor [7] and the discrete switch [8] are respectively connected with the corresponding input terminals of the signal conditioning circuit [4], and the signal output terminals of the signal conditioning circuit [4] are connected with the DFCS main digital The signal input terminal of the flight control system [2] is connected, the main/standby switch [11] is a single-pole double-throw switch, and the signal output terminal of the DFCS main digital flight control system [2] is connected to the main/standby switch [11]. The normally closed contact is connected, the common end of the main/standby switch [11] is connected with the input end of the servo amplifier [10], and the output end of the servo amplifier [10] is connected with the steering gear [9]; it is characterized in that, said There is a DEFCS digital emergency backup flight control module [12] in the digital servo controller [5], and the emergency backup control law program and the signal of the signal conditioning circuit [4] are stored in the DEFCS digital emergency backup flight control module [12]. The output end is connected with the input end of the DEFCS digital emergency backup flight control module [12], and the output end of the DEFCS digital emergency backup flight control module [12] is connected with the normally open contact of the main/standby switch [11].
CN201010260070.2A 2010-08-19 2010-08-19 A fly-by-wire flight control system structure Pending CN101916111A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201010260070.2A CN101916111A (en) 2010-08-19 2010-08-19 A fly-by-wire flight control system structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201010260070.2A CN101916111A (en) 2010-08-19 2010-08-19 A fly-by-wire flight control system structure

Publications (1)

Publication Number Publication Date
CN101916111A true CN101916111A (en) 2010-12-15

Family

ID=43323637

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201010260070.2A Pending CN101916111A (en) 2010-08-19 2010-08-19 A fly-by-wire flight control system structure

Country Status (1)

Country Link
CN (1) CN101916111A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105807761A (en) * 2015-09-02 2016-07-27 南京乐朋电子科技有限公司 Control system of bionic intelligent robotic fish
CN107406137A (en) * 2014-11-26 2017-11-28 埃姆普里萨有限公司 System and method for exchanging the flight control executor in aircraft flight control system and driving cabin
CN113386951A (en) * 2021-08-17 2021-09-14 中国商用飞机有限责任公司 Turning control system, method and computer-readable storage medium for aircraft
CN113534655A (en) * 2021-09-07 2021-10-22 中国商用飞机有限责任公司 Telex flight backup control system and starting method thereof

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5330131A (en) * 1992-05-28 1994-07-19 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Engines-only flight control system
CN1358649A (en) * 2002-01-29 2002-07-17 北京航空航天大学 Self-check test for test-control and electronic system of axle-shared double-rotary wing pilotless helicopter
US20070164166A1 (en) * 2006-01-17 2007-07-19 Jukka Matti Hirvonen Apparatus and method for backup control in a distributed flight control system
CN201000576Y (en) * 2007-01-26 2008-01-02 青岛天骄无人机遥感技术有限公司 Flight control system for unmanned plane
CN101799689A (en) * 2010-04-08 2010-08-11 中国电子科技集团公司第三十八研究所 Dual-redundancy steering engine controller

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5330131A (en) * 1992-05-28 1994-07-19 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Engines-only flight control system
CN1358649A (en) * 2002-01-29 2002-07-17 北京航空航天大学 Self-check test for test-control and electronic system of axle-shared double-rotary wing pilotless helicopter
US20070164166A1 (en) * 2006-01-17 2007-07-19 Jukka Matti Hirvonen Apparatus and method for backup control in a distributed flight control system
CN201000576Y (en) * 2007-01-26 2008-01-02 青岛天骄无人机遥感技术有限公司 Flight control system for unmanned plane
CN101799689A (en) * 2010-04-08 2010-08-11 中国电子科技集团公司第三十八研究所 Dual-redundancy steering engine controller

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
《中国优秀硕士学位论文全文数据库》 20070101 杨林芳 无人机容错飞行控制系统研究 , 2 *
《中国制造业信息化》 20060201 屈蔷 刘建业 梅劲松 自主无人机导航及数字飞行控制系统的研制 第35卷, 第3期 2 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107406137A (en) * 2014-11-26 2017-11-28 埃姆普里萨有限公司 System and method for exchanging the flight control executor in aircraft flight control system and driving cabin
CN107406137B (en) * 2014-11-26 2020-04-28 埃姆普里萨有限公司 System and method for interchanging flight control manipulators in an aircraft flight control system and cockpit
CN105807761A (en) * 2015-09-02 2016-07-27 南京乐朋电子科技有限公司 Control system of bionic intelligent robotic fish
CN105807761B (en) * 2015-09-02 2019-07-12 南京乐朋电子科技有限公司 A kind of control system of bionic intelligence machine fish
CN113386951A (en) * 2021-08-17 2021-09-14 中国商用飞机有限责任公司 Turning control system, method and computer-readable storage medium for aircraft
CN113386951B (en) * 2021-08-17 2024-04-02 中国商用飞机有限责任公司 Turn control system, method and computer-readable storage medium for aircraft
CN113534655A (en) * 2021-09-07 2021-10-22 中国商用飞机有限责任公司 Telex flight backup control system and starting method thereof

Similar Documents

Publication Publication Date Title
CN101916111A (en) A fly-by-wire flight control system structure
CN204731634U (en) A kind of aviation landing system performance detection apparatus
CN103499986A (en) Multichannel vacuum positive and negative pressure output control device
CN206115261U (en) Trying on clothes from dynamic testing of flight control is put
CN203133592U (en) Remote control system
CN201527571U (en) A Microcomputer Teaching Servo Control System
CN203084500U (en) Programmable logic controller (PLC) application equipment based on bus form
CN205620739U (en) Interface circuit is planned to general section mould of input/output
CN104578377B (en) Cabinet power-supply system, power supply method for handover control and cabinet
CN103605328A (en) STC single chip microcomputer-based embedded programmable logic controller (PLC) industrial control board
CN109976313A (en) A kind of automatically controlled test macro and diagnostic device of liquid electricity retarder
CN208092510U (en) Experiment device for teaching based on touch screen and PLC
CN207686952U (en) Fire pump controller
CN201789297U (en) Switch output unit in high voltage reactive power compensation device
CN201527565U (en) A Locomotive Logic Control Device Based on DSP
CN203350652U (en) Arbitrarily extensible multi-relay circuit control system
CN202018613U (en) Boiler controller having boiler state data man-machine interaction function
CN204009576U (en) A kind of AC servo driver element proving installation
CN204101645U (en) A kind of verification test device of backup auto-activating device
CN203745856U (en) An embedded PLC industrial control board based on STC microcontroller
CN201029022Y (en) Production and teaching dual-purpose numerical control machine tool
CN203331449U (en) System for controlling stationarity of numerically-controlled hydraulic machine
CN204643402U (en) Based on the novel elevator master controller of FPGA device
CN105911484B (en) The secondary power supply simulation system and method for aircraft power supply ground system test
CN103713602B (en) Remote control two-channel control system

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C02 Deemed withdrawal of patent application after publication (patent law 2001)
WD01 Invention patent application deemed withdrawn after publication

Open date: 20101215