Guidance Strategies for Planetary Ascent

The purpose of this course is to develop theoretical and applied skills in optimization and control for spacecraft guidance.

This video introduces two rocket ascent problems. The first is Goddard’s problem from 1919. This problem maximizes the rocket’s final altitude, and we see that optimal solutions involve a singular arc. The second problem is to maximize the rocket’s final energy. The analysis results in the linear tangent law, which was used to guide the Saturn V rocket to orbit during the Apollo days.

——————–

This video presents a recent modification of the Shuttle era ascent guidance algorithm known as Powered Explicit Guidance or PEG. Through various approximations, the guidance problem is reduced to a boundary value problem with five unknowns – 3 can be solved analytically and 2 numerically. A final observation leads to an approximation so that the modified PEG method is completely analytical.

Leave a Reply

Fill in your details below or click an icon to log in:

WordPress.com Logo

You are commenting using your WordPress.com account. Log Out /  Change )

Google photo

You are commenting using your Google account. Log Out /  Change )

Twitter picture

You are commenting using your Twitter account. Log Out /  Change )

Facebook photo

You are commenting using your Facebook account. Log Out /  Change )

Connecting to %s