Code covered by the BSD License
- [fid, alt1, alt2, inc1, i...read orbital elements and simulation
- atan3 (a, b)
four quadrant inverse tangent
- brent (f, x1, x2, rtol)
solve for a single real root of a nonlinear equation
- ceqm1 (t, y)
first order form of Cowell's equations of orbital motion
- eci2mee(mu, reci, veci)
convert eci state vector to
- eci2orb1 (mu, r, v)
convert eci state vector to six classical orbital
- gast1 (jdate)
Greenwich apparent sidereal time
- gdate (jdate)
convert Julian date to Gregorian (calendar) date
- gravity (t, y)
first order equations of orbital motion
- hohmfunc (x)
inclination objective function
- j2eqm (t, y)
first order equations of orbital motion
- j4eqm(t, y)
first order equations of orbital motion
- julian (month, day, year)
Julian date
- mee2eci(mu, mee)
convert modified equinoctial orbital
- nc_event(t, y)
nodal crossing event function
- oeprint1(mu, oev, ittype)
print six classical orbital elements
- om_constants
astrodynamic and utility constants
- orb2eci(mu, oev)
convert classical orbital elements to eci state vector
- readgm(fname)
read gravity model data file
- rkf78 (deq, neq, ti, tf, ...solve first order system of differential equations
- svprint(r, v)
print position and velocity vectors and magnitudes
- tpbvp(x)
two point boundary value objective function and
- twobody2 (mu, tau, ri, vi)solve the two body initial value problem
- ueci2angles(reci, veci, u...convect eci unit vector to rtn angles
- hohmann.m
- phohmann.m
-
View all files
The Gravity Perturbed Hohmann Transfer
by David Eagle
28 Feb 2013
(Updated 22 Jul 2013)
MATLAB script for solving the Hohmann transfer problem perturbed by non-spherical Earth gravity.
|
Watch this File
|
| File Information |
| Description |
PDF document and a MATLAB script named phohmann which can be used to solve the gravity perturbed Hohmann transfer between coplanar and non-coplanar circular Earth orbits. The algorithm starts with a two-body Hohmann transfer initial guess and then uses the SNOPT nonlinear programming (NLP) method to determine the optimum two impulse orbit transfer subject to non-spherical Earth gravity perturbations.
The phohmann script uses modified equinoctial orbital elements to solve the gravity perturbed orbit transfer problem. Additional information about these orbital elements can be found in Appendix B. That appendix also explains how to use components and combinations of these non-singular elements to calculate a variety of orbital element “targets”. |
| MATLAB release |
MATLAB 7.14 (R2012a)
|
| Other requirements |
Requires the platform specific SNOPT mex file and additional MATLAB support functions available at http://scicomp.ucsd.edu/~peg/. |
|
Tags for This File
|
| Everyone's Tags |
|
| Tags I've Applied |
|
| Add New Tags |
Please login to tag files.
|
| Updates |
| 22 Jul 2013 |
Added three-dimensional trajectory graphics. Updated PDF document to reflect this change. |
|
Contact us