DATO (Descent & Ascent Trajectory Optimisation): From the Launch Pad to Orbit and Back
- Paper number
IAC-06-D1.P.1.04
- Author
Mr. Davide Starnone, STAR N ONE Engineering, Italy
- Coauthor
Mr. Robin Biesbroek, European Space Agency (ESA)/ESTEC, The Netherlands
- Year
2006
- Abstract
The JAQAR Astrodynamics Package contains a set of tools dedicated to the optimisation of interplanetary, Lunar and planetary orbit transfers. The tools are widely used by both students and professionals, and focus on easy to use interfaces combined with global optimisation methods such as genetic algorithms and differential evolution. In order to decrease optimisation time, new techniques were developed combining numerical methods with analytical ones. In the frame of the space system engineering consultancy and engineering tools development, this paper deals with some aspects related to launch vehicle flight trajectory optimisation, presenting the new DATO (Descent and Ascent Trajectory Optimisation) software tool. This tool has the capability to evaluate a preliminary assessment of both launch and re-entry two dimensional trajectories from a generic planet, including launch site location, vehicle’s configuration, such as the possibility to choose the number of stages of the vehicle, the structural ratio, the pitch law and some other features. A user interface has been also built to make intuitive and fast the configuration of the initial vehicle’s parameters. In contrast to most existing software packages, DATO optimises the launch vehicle configuration, making it ideal for assessment studies on launcher or ascent vehicle design. Fundamental aspect is the opportunity to optimise, via differential evolution algorithms, the vehicle performance and to test some mission critical aspects, implementing the integration of the equations of motion of the centre of mass of the vehicle’s body related to the second order ordinary Cauchy problem under specified initial conditions on position and velocity. Such integration adopts the numerical Runge-Kutta method. The outputs are the evolution in time of the main flight parameters such as position, velocity, acceleration, vehicle’s mass, dynamic pressure, heat flux and other relevant features, as well as graphical trajectory outputs. Examples are given for a heavy-lift launch vehicle and Lunar ascent/descent vehicles.
- Abstract document
- Manuscript document
IAC-06-D1.P.1.04.pdf (🔒 authorized access only).
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