MA 4362 Astrodynamics - PowerPoint PPT Presentation

1 / 19
About This Presentation
Title:

MA 4362 Astrodynamics

Description:

Next Compute DV Required to. Insert Spacecraft onto. Elliptical ... 70.4 % DV savings, WOW! Postscript. So That's how they were able to salvage the satellite! ... – PowerPoint PPT presentation

Number of Views:39
Avg rating:3.0/5.0
Slides: 20
Provided by: tonywh
Category:

less

Transcript and Presenter's Notes

Title: MA 4362 Astrodynamics


1
MA 4362Astrodynamics
The Bi-Elliptic Orbital Transfer Homework 10
Solution Vallado, Chapter 6, Sections 6.3.1,
6.3.2, 6.3.3
2
Bi-Elliptic "Lunar-Boost" Transfer used to
Salvage HughesCommunication Satellite, 1998
Exploited Energy Gains from Bi-Elliptic Transfer
3
Homework 10
Lets do some calculations on this problem
4
Orbit Parameters
Radius!
Altitude!
44,250 km
Intercept At Lunar Perigee
Radius!
5
Initial Orbit Parameters
Semi Major Axis and Eccentricity
(
Normalizing Velocity
6
First Compute HohmannTransfer DV
7
Calculate DV1 for Hohmann Transfer
Energy (Magnitude) of Initial orbit
Initial Orbit Outside Final Orbit
Burn 1 at Apogee
8
Calculate DV2 for Hohmann Transfer
Energy (Magnitude) of Initial orbit
Initial Orbit Outside Final Orbit
Burn 2 at Perigee
9
DV1, DV2, DVTotal Hohmann Transfer
10
Next Compute DV Required toInsert Spacecraft
ontoElliptical Lunar Trajectory
Altitude!
Burn at Perigee Why?
Radius!
44,250 km
Intercept At Lunar Perigee
Radius!
11
Compute DV1 forElliptical Lunar Trajectory
a1 , e1 -gt Initial (Useless) orbit Semi-Major
Axis, eccentricity aT -gt Lunar Trajectory
Semi-Major Axis
1
12
Parameters of Trans-Lunar Orbit
DV1
13
Compute DV2 Requiredby Lunar Gravity Assist
Well learn more about This later when we study
Three-body problems
1
due
14
DV2 Requiredfrom Lunar Gravity Assist
aT , eT -gt Lunar Trajectory Semi-Major Axis,
eccentricity aT -gt Earth-Return
Trajectory Semi-Major Axis
1
1
2
15
Parameters of Earth-Return Orbit
DV2 gravity assist
16
Calculate DV required to Circularize Final orbit
aT -gt Earth-Return Trajectory Semi-Major
Axis Rc -gt Final Orbit Radius, 42241 km
2
final
17
Finally,Compare Total DV requiredfor Hohmann
Transferto DV Required for Bi-EllipticLunar
Gravity Assist Transfer
Assume that DV due to Gravity Assist is
Free .. I.e. dont count it
18
Total DV Comparison
Hohmann Transfer
DVTotal DV1 DV2 5.468 km/sec
Bi-Elliptic (including DV2 gravity assist)
Transfer
DVTotal DV1 DV2 DVfinal 1.88184
km/sec
Bi-Elliptic (excluding DV2 gravity assist)
Transfer
DVTotal DV1 DV2 DVfinal 1.61726
km/sec
70.4 DV savings, WOW!
19
Postscript
So Thats how they were able to salvage the
satellite!
Write a Comment
User Comments (0)
About PowerShow.com