scholarly journals Minimum Acceleration Guidance Law for Spaceplane in Ascent Phase via Exact Linearization

2005 ◽  
Vol 48 (161) ◽  
pp. 135-142
Author(s):  
Akio ABE ◽  
Yuzo SHIMADA ◽  
Kenji UCHIYAMA
Keyword(s):  
Exact Linearization ◽  
Guidance Law ◽  
Ascent Phase ◽  
Acceleration Guidance

A New Angular Acceleration Guidance Law with Estimation Approach Based on Sliding Mode Observer against High Maneuvering Target

2011 ◽  
Vol 110-116 ◽  
pp. 5249-5256 ◽  
Author(s):  
Yuan Yun Song ◽  
Wan Chun Chen ◽  
Xing Liang Yin
Keyword(s):  
Sliding Mode ◽  
Angular Acceleration ◽  
Sliding Mode Observer ◽  
Line Of Sight ◽  
Primary Input ◽  
Input Quantity ◽  
Maneuvering Target ◽  
Guidance Law ◽  
New Type ◽  
Acceleration Guidance

A new type of guidance law is developed for intercepting high maneuvering target. The law takes angular acceleration of line-of-sight as a primary input in place of the acceleration of target. As the significant required input quantity of the angular acceleration guidance (AAG), the angular acceleration of line-of-sight is estimated by a developed estimation approach based on sliding mode observer (SMO). Simulation results demonstrates advantages of this AAG guidance with the estimation approach based on SMO by comparing with the conventional guidance techniques and extended Kalman filter.

A GENERALIZED LINEAR GUIDANCE LAW FOR AEROSPACE VEHICLES

1966 ◽  
Author(s):  
R. JOHNSON ◽  
C. LEONDES ◽  
J. PAYNE
Keyword(s):  
Aerospace Vehicles ◽  
Guidance Law

Fault Tolerant Guidance of Under-Actuated Satellite Formation Flying Using Inter-Vehicle Coulomb Force

2019 ◽  
Vol 2 (1) ◽  
pp. 43-52
Author(s):  
Alireza Alikhani ◽  
Safa Dehghan M ◽  
Iman Shafieenejad
Keyword(s):  
Fault Tolerance ◽  
Formation Flying ◽  
Fault Tolerant ◽  
Coulomb Force ◽  
Control Law ◽  
Triangular Form ◽  
Satellite Formation Flying ◽  
Satellite Formation ◽  
Guidance Law ◽  
Tolerance Approach

In this study, satellite formation flying guidance in the presence of under actuation using inter-vehicle Coulomb force is investigated. The Coulomb forces are used to stabilize the formation flying mission. For this purpose, the charge of satellites is determined to create appropriate attraction and repulsion and also, to maintain the distance between satellites. Static Coulomb formation of satellites equations including three satellites in triangular form was developed. Furthermore, the charge value of the Coulomb propulsion system required for such formation was obtained. Considering Under actuation of one of the formation satellites, the fault-tolerance approach is proposed for achieving mission goals. Following this approach, in the first step fault-tolerant guidance law is designed. Accordingly, the obtained results show stationary formation. In the next step, tomaintain the formation shape and dimension, a fault-tolerant control law is designed.

Control of the Lorenz chaos by the exact linearization

1998 ◽  
Vol 19 (1) ◽  
pp. 67-73 ◽  
Author(s):  
Chen Liqun ◽  
Liu Yanzhu
Keyword(s):  
Exact Linearization

A non-overshooting controller for vehicle path following

2021 ◽  
pp. 014233122199438
Author(s):  
Tong Xu ◽  
Dong Wang ◽  
Weigong Zhang
Keyword(s):  
Field Experiments ◽  
Fitness Function ◽  
Path Following ◽  
Settling Time ◽  
Distribution Model ◽  
Positioning Errors ◽  
Guidance Law ◽  
Initial Control ◽  
Vehicle Path ◽  
Pavement Construction

Unmanned pavement construction is of great significance in China, and one of the most important issues is how to follow the designed path near the boundary of the pavement construction area to avoid curbs or railings. In this paper, we raise a simple yet effective controller, named the proportional-integral-radius and improved particle swarm optimization (PIR-IPSO) controller, for fast non-overshooting path-following control of an unmanned articulated vehicle (UAV). Firstly, UAV kinematics model is introduced and segmented UAV steering dynamics model is built through field experiments; then, the raw data collected by differential global positioning system (DGPS) is used to build the measurement error distribution model that simulates positioning errors. Next, line of sight (LOS) guidance law is introduced and the LOS initial parameter is assigned based on human driving behavior. Besides, the initial control parameters tuned by the Ziegler-Nichols (ZN) method are used as the initial iterative parameters of the PSO controller. An improved PSO fitness function is also designed to achieve fast non-overshoot control performance. Experiments show that compared with the PSO, ZN and ZN-PSO controller, the PIR-PSO-based controller has significantly less settling time and almost no overshoot in various UAV initial states. Furthermore, compared with other controllers, the proposed PIR-IPSO-based controller achieves precise non-overshoot control, relatively less settling time and centimeter-level positioning error in various initial deviations.

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