Three-redundancy fault-tolerant computer platform based on modular structure
A fault-tolerant computer and three-redundancy technology, applied in computing and hardware redundancy for data error detection, response error generation, etc. Beneficial to upgrade and expand the effect
Active Publication Date: 2012-12-19
AVIC NO 631 RES INST
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Problems solved by technology
The active aircraft adopts a joint architecture, and various functions related to aircraft platform management are distributed in various subsystems (one subsystem corresponds to one function), such as inertial navigation device, flight control system, air data system, engine control system, navigation system, etc. System, power management, fuel system, etc., each subsystem uses an independent computer to realize control and management, and the subsystems are independent of each other. The objective disadvantages are that there are too many equipments for aircraft platform management, heavy weight, large volume and large space occupation. , complex wiring, heavy cables, high maintenance costs, low degree of information integration between subsystems, unable to maximize the performance of the aircraft platform, and unable to optimize flight quality
At the same time, the computer microprocessors in each subsystem have limited capabilities and independent resources. The aircraft platform has to expand new functions by adding equipment. However, it is limited by the limited space and load-bearing capacity of the platform itself. It hinders the development of the aircraft platform itself, and it is not conducive to the application to the UAV system
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[0028] According to the content of the invention, an example of building a three-redundancy comprehensive management computer platform for a certain type of unmanned aerial vehicle: as a three-channel cross-comparison monitoring system, it is composed of three functional channels with the same hardware structure and two three-redundancy power supplies. Independent of each other, it is divided into three LRM mechanical structures by means of physical centralized electrical isolation. The channels exchange information through CCDL (transmitted with 2Mbit Manchester code), and the channels use hardware synchronization instructions to ensure the synchronous operation of the three channels. The standard PCI bus is used in the functional channel, and the functional sub-board conforms to the PMC specification. The functional channel includes CPU module (sub-board), SIO module (sub-board), CAN module (sub-board), DIO module (main substrate), AIO module (slave substrate).
[0029]CPU ...
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The invention provides a three-redundancy fault-tolerant computer platform based on a modular structure, aiming to realize comprehensive control and management of a computer system and construct a three-redundancy fault fault-tolerant computer platform based on a modular structure to solve the inherent problems of a combined structure from the point of a processor platform. The computer platform mainly comprises three functional channels which have same hardware structure and are mutually independent, and two power modules respectively supplying power for digital signal processing and analog signal processing, and is integrated in a box by a physical concentration mode; and each functional channel serves as a computer, and is internally provided with a substrate, a master processor and one or more functional modules which are crosslinked through an open standard internal bus. The three-redundancy fault-tolerant computer platform based on the modular structure can ensure that the comprehensive control and management of the computer system are realized, has higher safety and reliability, and meets the requirements on miniaturization and environment adaptability.
Description
technical field [0001] The invention relates to a computer platform based on a modular structure, in particular to a three-redundancy fault-tolerant computer platform based on a modular structure commonly used in aviation airborne systems. Background technique [0002] The functions of the aircraft are divided into "payload functions" directly related to the aircraft's mission completion and "aircraft management functions" that help the aircraft support the execution of mission functions. The "aircraft management functions" include: flight control, thrust control, inertial navigation, engine Control, air data, fuel system, route management, integrated navigation, hydraulic control, health monitoring and other functions. The active aircraft adopts a joint architecture, and various functions related to aircraft platform management are distributed in various subsystems (one subsystem corresponds to one function), such as inertial navigation device, flight control system, air da...
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IPC IPC(8): G06F11/16G06F1/16
Inventor 赵刚王萌徐奡南雁田龙成书锋李亚锋程俊强王国静夏德天姜红明董伟董妍杨菊平
Owner AVIC NO 631 RES INST