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Launch Vehicle Applications

One of the main topic of launcher design is trajectory optimization: the process of designing a trajectory that minimizes or maximizes some measure of performance. While not exactly the same, the goal of solving a trajectory optimization problem is essentially the same as solving an optimal control problem.

Apart from this, the solutions provided by our company cover various aspects in the mission analysis and design of launch vehicles:

  • Feasibility studies and concept validation of the launcher (phase 0)
  • Reference trajectory computation for phase A
  • Update of the performance due to the consolidation of the subsystems (phase B)
  • Computation of exotic target orbits (phase C)
  • Disposal of the launcher upper stage (see Re-entry)

Classical mission analysis tasks are performed with the support of our software and expertize, departure window, delta-V budget, maneuver planning and ground station visibility.

Success Story

Several industrial and university projects have benefited from our services, this list is not complete and to be intended just as an overview:

Feasibility Study and Concept Validation

  • Skylon: a single-stage, turbojet-based, airbreathing orbital spaceplane
  • Optimization of multiple vehicles for launcher with fly-back boosters
  • Micro and small launcher (Sounding Rockets)
  • Heavy Lift Launch Vehicle
  • Mars Ascent Vehicle
  • Socrates RLV Demonstrator
  • Crew Exploration Vehicle

Reference Trajectory

  • Hopper, horizontal and vertical version

Update of Performance and Exotic Orbit Computation

  • Ariane 5 family
  • Vega: first flight, electric upper stage, et al.