Banerjee, Avijit and Padhi, Radhakant (2015) Inverse Polynomial Based Explicit Guidance for Lunar Soft Landing During Powered Braking. In: IEEE Conference on Control and Applications (CCA), SEP 21-23, 2015, Sydney, AUSTRALIA, pp. 768-773.
2015_IEEE_Con_Con_App_768_2015.pdf - Published Version
Restricted to Registered users only
Download (598Kb) | Request a copy
In this paper an explicit guidance law for the powered descent phase of the soft lunar landing is presented. The descent trajectory, expressed in polynomial form is fixed based on the boundary conditions imposed by the precise soft landing mission. Adapting an inverse model based approach, the guidance command is computed from the known spacecraft trajectory. The guidance formulation ensures the vertical orientation of the spacecraft during touchdown. Also a closed form relation for the final flight time is proposed. The final time is expressed as a function of initial position and velocity of the spacecraft ( at the start of descent) and also depends on the desired landing site. To ensure the fuel minimum descent the proposed explicit method is extended to optimal guidance formulation. The effectiveness of the proposed guidance laws are demonstrated with simulation results.
|Item Type:||Conference Proceedings|
|Additional Information:||Copy right for this article belongs to the IEEE, 345 E 47TH ST, NEW YORK, NY 10017 USA|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||04 Mar 2016 06:04|
|Last Modified:||04 Mar 2016 06:04|
Actions (login required)