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CourseAerospace, UAM, Drones & Space Applications open

Astrodynamics fundamentals course

Online course of 300 hours in astrodynamics fundamentals, structured in 6 modules covering classical celestial mechanics, reference systems and time, orbital elements, orbit propagation and basic orbit determination, with an assigned technical tutor.

Duration3 months
ModeOnline
LanguageEnglish
Start datesSet by the faculty
AwardSEIUM Institute certificate
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Learning outcomes

What you will be able to do

01

Understand the fundamentals of the two-body problem.

02

Use astronomical reference systems and time scales.

03

Calculate orbital elements from state vectors.

04

Propagate orbits using analytical and numerical methods.

05

Solve Lambert's problem.

06

Apply basic orbit determination methods.

07

Carry out a complete orbital analysis with professional tools.

Profile

Who it's for

  • Flight dynamics engineers at satellite operators and agencies.
  • Mission analysts designing orbits and transfers.
  • Satellite operations engineers who work with TLEs and ephemerides.
  • Aerospace software engineers building propagation tools.
  • Orbital mechanics researchers.
  • Space tracking technicians working at ground stations.
  • Engineering or science graduates looking to enter the space industry.
Standards & tools

What you'll work with

  • ECSS-E-ST-10-09C (reference coordinate system)
  • CCSDS 502.0-B (Orbit Data Messages) (standard formats for orbit data exchange)
  • IERS Conventions 2010 (IERS Technical Note 36) (Earth rotation and reference frame models)
  • IAU 2006/2000A precession-nutation resolutions (precession and nutation models)
  • ECSS-E-ST-10-04C (space environment)
  • ISO 27852 (estimation of orbit lifetime)
  • GMAT
  • Orekit
  • Ansys STK
  • Python with poliastro
  • MATLAB Aerospace Toolbox
Syllabus

6 modules

  1. 1.1Kepler's laws and Newton's gravitation
  2. 1.2The two-body problem
  3. 1.3Energy and angular momentum integrals
  4. 1.4The orbit conic equation
  5. 1.5Orbital and escape velocities
  6. 1.6The vis-viva equation
  7. 1.7True, eccentric and mean anomalies
  8. 1.8Kepler's equation and its solution
  9. 1.9Parabolic and hyperbolic orbits
  10. 1.10Workshop: numerical solution of Kepler's equation
  1. 2.1Inertial and geocentric systems
  2. 2.2ECI, ECEF and perifocal frames
  3. 2.3Precession, nutation and polar motion
  4. 2.4Time scales: TAI, UTC, TT and GPS
  5. 2.5Julian date
  6. 2.6Topocentric systems
  7. 2.7Coordinate transformations
  8. 2.8IERS conventions
  9. 2.9JPL planetary ephemerides
  10. 2.10Practical: ECI to ECEF transformation
  1. 3.1Classical Keplerian elements
  2. 3.2Conversion between state vector and elements
  3. 3.3Equinoctial elements
  4. 3.4Special orbits: circular and equatorial
  5. 3.5Ground track
  6. 3.6Visibility from ground stations
  7. 3.7TLE elements and the SGP4 model
  8. 3.8Orbit data messages
  9. 3.9Transfer and parking orbits
  10. 3.10Lab: propagating a TLE with SGP4
  1. 4.1Analytical Keplerian propagation
  2. 4.2Numerical integration of the equations of motion
  3. 4.3Runge-Kutta methods and adaptive step size
  4. 4.4Cowell and Encke formulations
  5. 4.5Numerical errors and energy conservation
  6. 4.6Lagrange f and g functions
  7. 4.7Lambert's problem
  8. 4.8Comparison of propagators
  9. 4.9Accuracy and truncation error
  10. 4.10Case study: propagating an orbit with Orekit
  1. 5.1Range, angle and Doppler measurements
  2. 5.2Gibbs method
  3. 5.3Gauss method
  4. 5.4Batch least squares
  5. 5.5Introduction to the Kalman filter
  6. 5.6Covariance and error ellipsoid
  7. 5.7Tracking with on-board GNSS
  8. 5.8Quality of the orbit solution
  9. 5.9Laplace initial orbit determination
  10. 5.10Case study: orbit determination from angular observations
  1. 6.1Definition of the orbital scenario
  2. 6.2Selection of frames and time scales
  3. 6.3Calculation of orbital elements
  4. 6.4Propagation and comparison of models
  5. 6.5Visibility analysis
  6. 6.6Orbit determination with simulated data
  7. 6.7Error assessment
  8. 6.8Conclusions and recommendations
  9. 6.9Report and presentation
  10. 6.10Final project: final review with the tutor
Methodology, software & labs

How you'll learn

100% online training on the SEIUM campus, with downloadable material, recorded classes and an assigned technical tutor. There are no fixed timetables: you progress at your own pace within each intake, so the programme is compatible with work.

Each module combines theory, guided reading of the original standard and applied exercises. The working software is GMAT, Orekit, Ansys STK, Python with poliastro and MATLAB Aerospace Toolbox, in free, academic or evaluation versions. Testing is studied through real procedures: orbit propagation with different models and comparison of results, orbit determination from simulated observations, and calculation of visibility windows from ground stations. Assessment is continuous by module, plus the final project.

Standards covered: ECSS-E-ST-10-09C, CCSDS 502.0-B (Orbit Data Messages), IERS Conventions 2010 (IERS Technical Note 36), IAU 2006/2000A precession-nutation resolutions, ECSS-E-ST-10-04C, ISO 27852.

Assigned technical tutor:every module ends with a deliverable that your tutor marks individually.
Standards-based learning:guided reading of ECSS-E-ST-10-09C, CCSDS 502.0-B (Orbit Data Messages) and IERS Conventions 2010 applied to real cases, not as a theoretical annex.
Industry software:GMAT, Orekit, Ansys STK, Python with poliastro and MATLAB Aerospace Toolbox, in free, academic or evaluation versions.
Final project:a complete orbital analysis, from frames and orbital elements to propagation model comparison, visibility analysis and orbit determination with simulated data, reviewed by your tutor.
Flexible format:100% online, no fixed timetables, compatible with full-time work.
Capstone project

Build it end to end

Your final project follows the real engineering workflow, step by step, reviewed by your tutor.

Kepler solver
Implement a numerical solver for Kepler's equation.
Frame transformation
Transform state vectors between ECI and ECEF frames.
TLE propagation
Propagate a TLE with SGP4 and compare propagators with Orekit.
Orbit determination
Determine an orbit from simulated angular observations.
Final project
Carry out a complete orbital analysis, reviewed by your tutor.
Career opportunities

Where this takes you

Flight dynamics engineerMission analystSatellite operations engineerAerospace software engineerOrbital mechanics researcherSpace tracking technician
Admissions & scholarships

Requirements

  • No prior qualification is required.
  • Internet connection and a computer capable of running the programme software.
  • English sufficient to read technical standards.

Ready to start?

Send your application today. Our admissions team replies within 72 hours with your study plan and funding options.

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FAQ

Frequently asked questions

The programme totals 300 hours over 3 months. You set your own pace within each intake, and your tutor helps you plan the workload around your job.

You work with GMAT, Orekit, Ansys STK, Python with poliastro and MATLAB Aerospace Toolbox, using free, academic or evaluation versions. Your tutor indicates the free alternative wherever one exists.

A SEIUM Institute certificate, awarded on passing the continuous assessment and the final project. It is SEIUM's own qualification, not an official state degree; its recognition depends on the programme completed and the regulations of each country.

Yes. Modules passed are recognised in a higher programme in the same area (postgraduate diploma or master's). Ask about the recognition policy when you enrol.

No prior qualification is required; you need a computer able to run the programme software and English sufficient to read technical standards.

Start dates are set by SEIUM's faculty for each intake. Our admissions team will confirm the next available date when you apply.

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