RRDD – OteSpace

Timeline

Stone Age
Propellants tests

Bronze Age
First hot tests

Iron Age
First successful test

Middle Age
Ablative chamber tests

Renaissance
PEPEk1 - 1kN pump-fed bi-propellant engine development

Early Modern History
PEPEk1 - 1kN pump-fed bi-propellant engine successful test

RRDD - Reusable Rocket Drone Demonstrator
small, low cost testing platform for functionality verification and optimization

PEPEk-30
Rocket Engine

Czech Sparrow
Reusable SSO and LEO launcher

RRDD - First development phase, Proof of concept and competence

Project goals

Low cost development of critical components and subsystems
Proof of concept
Proof of competence of the team and of collaboration efficiency

Capabilities -perform all the critical maneuvers during launch, reentry and landing, including:

Take off and climb to a specified altitude
In flight engines restart
Hover
Precise landing

Specifications

Concept: A drone powered by four fixed off axis PEPEk 1 engines
Total nominal thrust: 4.4kN
Hover time: 90 120s
Empty mass: 120kg
Take off mass: 300kg
Max diameter: ~800mm (w/o fixed landing legs)
Height: ~1.7m (w/o fixed landing legs)
Pitch, yaw, roll by means of thrust variation of the PEPEk 1 engines