MAE 161A 2009 - Lecture 6

MAE 161A 2009 - Lecture 6 - News: Lecture 6 Homework Office...

Info iconThis preview shows pages 1–11. Sign up to view the full content.

View Full Document Right Arrow Icon
Slide 1 © Wirz MAE 161A Lecture 6 News: Homework HW #3 will be posted today Office Hours (upcoming) Tuesday (2-3) Wednesday (10-11:30) STK Certification Voucher Code is “EDUCERT09” Reading Assignment: BMW 4.1-4.2 (focus on 181-186) Chobotov 3.5, 4.1-4.2 (pages 35-41)
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Slide 2 © Wirz MAE 161A Last Lecture Orbit Transfers Impulsive Low Thrust Plane Change Keplerian Orbital Elements
Background image of page 2
Slide 3 © Wirz MAE 161A Hohmann Transfer “orbit raising”
Background image of page 3

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Slide 4 © Wirz MAE 161A What’s Wrong with this Picture?
Background image of page 4
Slide 5 © Wirz MAE 161A Impulsive V Requirements
Background image of page 5

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Slide 6 © Wirz MAE 161A Keplerian Orbital Elements (Note: all scalars) a , semi-major axis: size of orbit e , eccentricity: shape of the orbit , true anomaly at epoch angle of the satellite w.r.t. perigee i , inclination: the angle between the equatorial plane and the plane of the orbit , argument of periapsis angle of perigee w.r.t. the line of nodes , right ascension of the ascending node (RAAN) The angle between the X-axis and the line of nodes (where the satellite crosses through the equatorial plane in the northerly direction) Describe orbit (in- plane) Locate orbit plane
Background image of page 6
Slide 7 © Wirz MAE 161A Today’s Lecture V Rockets Thrust Impulse and Specific Impulse Simplified Rocket Equation
Background image of page 7

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Slide 8 © Wirz MAE 161A V (Delta-V) In astrodynamics we must change the velocity (apply a V) to: 1. Change the energy of the orbit Launch Descent/Landing Orbit Change Orbit Insertion Station Keeping (a.k.a. orbit maintenance) Drag compensation Interplanetary (Escape) 2. Other Attitude Control Disturbance reduction Formation Flying 2 22 v ra  11 Specific Mechanical Energy related to “a” 2 2 2 1 H e 10 Eccentricity (gives type of conic orbit) Launch Orbit Insertion
Background image of page 8
Slide 9 © Wirz MAE 161A V (Delta-V) V can be delivered by : Rockets Swing-by a.k.a. gravity assist Drag Other EM field solar wind collision etc.
Background image of page 9

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Slide 10 © Wirz MAE 161A Rockets Rockets carry their reaction mass (propellant) with them Two main ways to accelerate propellant: 1.
Background image of page 10
Image of page 11
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 10/17/2010 for the course MAE 161 taught by Professor Richard during the Spring '10 term at UCLA.

Page1 / 27

MAE 161A 2009 - Lecture 6 - News: Lecture 6 Homework Office...

This preview shows document pages 1 - 11. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online