A Design and Implementation of Bootloader Based on MPC8280

2014 ◽  
Vol 668-669 ◽  
pp. 592-597
Author(s):  
Ling Wang ◽  
Xin Chen
Keyword(s):  
Operating System ◽  
Flight Control ◽  
Vital Role ◽  
Processing Unit ◽  
Flight Control System ◽  
Central Processing ◽  
Control Computer ◽  
Aerial Vehicle ◽  
Software Code ◽  
The Stability

The core unit of the flight control system being the central part of the Unmanned Aerial Vehicle (UAV) system is the flight control computer playing a vital role in the stability and security of the entire system, which has fast and reliable requirements for system startup. Bootloader is the first section of software code that runs after powering on, mainly responsible for initializing hardware devices. By loading an application or operating system kernel, the bootloader completes the system startup. Based on MPC8280 processor’s hardware platform of the central processing unit of distributed flight control computer, this paper designs and implements a non-operating system boot scheme. Under the boot scheme, an optimal boot scheme aiming at increasing efficiency of software development for VxWorks operating system is provide.

The Design and Simulation of Low-Cost and Super-Applicability Flight Control System of Super-Size UAV

2012 ◽  
Vol 466-467 ◽  
pp. 1156-1161
Author(s):  
Liu Rong ◽  
Yu Ping Lu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Low Cost ◽  
Control Technique ◽  
Flight Control System ◽  
Flight Curve ◽  
Aerial Vehicle ◽  
The Stability ◽  
High Flexibility ◽  
The Cost

In this paper, considering the stability and robustness of the aircraft, the flight control system is designed following the aspect of high flexibility and low cost. Comparing with the flight control system of super-size high-subsonic Unmanned Aerial Vehicle (UAV) in the world, the system presented in this paper has adopted the inimitable control technique of flying-off course、low-cost combinatorial navigation strategy and the advanced safety scheme, which can guarantee the performance, degrade the cost and extend the airspace and groundspace of the aircraft.Through quite a few simulations, the results show that this system can guarantee the attitude and altitude stable. The error between the flight path and programming path is very small. Flight curve is prefect; and the system performances can be achieved completely.

Research on Internal Communication of Redundant Flight Control Computer for UAV

2011 ◽  
Vol 383-390 ◽  
pp. 1578-1583
Author(s):  
Lei Zheng ◽  
Xin Chen ◽  
Xun Hong Lv
Keyword(s):  
Flight Control ◽  
Control Area ◽  
Internal Communication ◽  
Area Network ◽  
Processing Unit ◽  
Frame Synchronization ◽  
Redundancy Management ◽  
Central Processing ◽  
Control Computer ◽  
Function Unit

Regarding the characteristic of the architecture of the sample redundant flight control computer based on CAN (control area network) bus, a bus protocol of internal communication based on time-triggered is presented. The protocol-frame, data-frame, synchronization arithmetic of internal communication are designed. According to the protocol, the communication between the CPU (central processing unit) and each other function unit can be reliable. At the same time, if some node of the network were failure, CPU can check it reliably and then carry through relevant switch logic to realize the redundancy management. The results of the experimentation show that according to the bus protocol designed in this paper, the internal communication of the FCC (flight control computer) was reliable, at the same time, the fault-detect and redundancy management can be realized.

PID Control Based Missile Sub-Channel Simulation

2012 ◽  
Vol 433-440 ◽  
pp. 7011-7016 ◽  
Author(s):  
Chao Bo Chen ◽  
Bing Liu ◽  
Ning He ◽  
Song Gao ◽  
Quan Pan
Keyword(s):  
Control System ◽  
Real Time ◽  
Flight Control ◽  
Pid Control ◽  
Pid Controller ◽  
Channel Model ◽  
Control Method ◽  
Flight Control System ◽  
Aerodynamic Control ◽  
The Stability

The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.

scholarly journals Safety risk assessment of navigation and flight control computer system of unmanned aerial vehicle

2015 ◽  
Vol 0 (13) ◽  
pp. 77-85
Author(s):  
B. Y. Volochiy ◽  
L. D. Ozirkovskyi ◽  
Y. M. Pashchuk ◽  
A. V. Mashchak ◽  
V. A. Onyshchenko
Keyword(s):  
Risk Assessment ◽  
Computer System ◽  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Safety Risk ◽  
Control Computer ◽  
Aerial Vehicle

scholarly journals Robust dynamic inversion control of flight control system based on L1 adaptive structure

2021 ◽  
Vol 39 (5) ◽  
pp. 995-1004
Author(s):  
Yu LI ◽  
Xiaoxiong LIU ◽  
Ruichen MING ◽  
Shaoshan SUN ◽  
Weiguo ZHANG
Keyword(s):  
Control System ◽  
Flight Control ◽  
Dynamic Performance ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
Parameter Uncertainties ◽  
Strong Robustness ◽  
Adaptive Structure ◽  
The Stability

Nonlinear Dynamic Inversion(NDI) control has excellent rapidity and decoupling ability, unfortunately it lacks the essential robustness to disturbance. From the perspective of enhancing the robustness, an adaptive NDI method based on L1 adaptive structure is proposed. The L1 adaptive structure is introduced into the NDI control to enhance its robustness, which also guarantees the stability and expected dynamic performance of the system suffering from the disturbance influence. Secondly, the flight control law of the advanced aircraft is designed based on the present method to improve the robustness and fault tolerance of the flight control system. Finally, the effectiveness of the flight control law based on the present approach is verified under the fault disturbance. The results showed that the flight control law based on L1 adaptive NDI has excellent dynamic performance and strong robustness to parameter uncertainties and disturbances.

LQG-Based Robustifying Flight Control System

2003 ◽  
Author(s):  
D. Griffin ◽  
A. G. Kelkar
Keyword(s):  
Control System ◽  
Flight Control ◽  
Controller Design ◽  
Second Step ◽  
Flight Control System ◽  
Robust Controller ◽  
Fighter Aircraft ◽  
Stability Robustness ◽  
Uncertainty Model ◽  
The Stability

This paper presents a robust controller design for an automatic flight control system (AFCS) for a fighter aircraft model with eight inputs and seven outputs. The controller is designed based on McFarlane-Glover robustifying technique using a simple baseline LQG design. Controllers designed purely based on traditional LQG techniques are known to have no guaranteed robustness margins. The McFarlane-Glover technique can be used to enhance the stability robustness of the baseline LQG design using a two-step design process. In the first step, an LQG controller is designed which is optimized only for performance without any consideration to robustness. In the second step, the performance optimized LQG design is rendered robust using McFarlane-Glover procedure. The robustifying procedure uses a coprime factor uncertainty model and H∞ optimization. An important advantage of this procedure is that no problem dependent uncertainty modelling or weight selection is required in the second step of the process. The robustifying procedure also yields the quantitative estimate of the robustness.

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