Optimizing 3-D PN Guidance Law for Accelerated Reentry Vehicles

2009 ◽  
Author(s):  
Amir Adami ◽  
Mehran Nosratolahi
Keyword(s):  
Guidance Law ◽  
Reentry Vehicles

Research on High Accuracy Guidance Law for Reentry Vehicles

2013 ◽  
Vol 427-429 ◽  
pp. 81-84 ◽  
Author(s):  
Zhi Gang Wang ◽  
Shen Yan
Keyword(s):  
High Accuracy ◽  
Guidance Law ◽  
Initial Stage ◽  
Reentry Vehicles ◽  
Simulation Results ◽  
Trajectory Guidance

The problem of low accuracy for classic guidance law is considered in this paper. Based on the mature theory used in missiles, this paper presents an integrated guidance law for reentry vehicles. At the initial stage of reentry flight, standard trajectory guidance law is employed, and then converts to 3dof proportional guidance law when this vehicle is close to the target. Simulation results are provided to demonstrate the accuracy of the proposed integrated guidance law.

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.

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