Design Thermosphere-Entry Research Rocket
Budget: $10 – $1,000 USD
The task is to conceive, size, and validate a fully-automated sounding rocket able to cross the Kármán line and cruise into the lower thermosphere (around 90-120 km) on a single stage or staged configuration, strictly for scientific research.
Payload profile
– Primary function: real-time data relay through compact communication devices.
– Secondary systems: integrated ion thrusters for minor attitude correction, deployable solar panels for on-orbit power, and 4K cameras for visual documentation.
Total mass envelope for all payload hardware should remain under 15 kg; propose fairing dimensions accordingly.
Flight & automation
The vehicle must launch, navigate, and downlink telemetry autonomously—from pad-abort logic and ascent guidance to apogee-pointed payload deployment and recovery sequencing. Expect a ground station link budget and fully scripted flight software (e.g., PX4, custom RTOS, or comparable stack).
Deliverables (all files in open formats)
• Preliminary mission analysis: trajectory, Δv, and thermodynamic constraints
• Detailed CAD assembly with material specs and mass breakdown
• Propulsion design sheet (solid, hybrid, or liquid—justify choice), including thrust curve and chamber analysis
• Avionics architecture: sensor suite, flight computer layout, antenna gain study
• Control algorithms and simulation results (MATLAB/Simulink or Python) proving closed-loop stability through max-Q and vacuum phases
• Manufacturing plan with tolerances, suggested suppliers, and costed BOM
• Ground operations checklist and safety documentation
• Recovery concept (parachute, propulsive, or hybrid) with impact energy calculation
Acceptance criteria
The final design must show, through simulation, a minimum apogee of 100 km with ≤5 % margin on predicted total mass, meet ECSS thermal limits for avionics, and maintain uninterrupted downlink at ≥2 Mbps throughout ascent and descent.
All intellectual property produced transfers on full payment.
Payload profile
– Primary function: real-time data relay through compact communication devices.
– Secondary systems: integrated ion thrusters for minor attitude correction, deployable solar panels for on-orbit power, and 4K cameras for visual documentation.
Total mass envelope for all payload hardware should remain under 15 kg; propose fairing dimensions accordingly.
Flight & automation
The vehicle must launch, navigate, and downlink telemetry autonomously—from pad-abort logic and ascent guidance to apogee-pointed payload deployment and recovery sequencing. Expect a ground station link budget and fully scripted flight software (e.g., PX4, custom RTOS, or comparable stack).
Deliverables (all files in open formats)
• Preliminary mission analysis: trajectory, Δv, and thermodynamic constraints
• Detailed CAD assembly with material specs and mass breakdown
• Propulsion design sheet (solid, hybrid, or liquid—justify choice), including thrust curve and chamber analysis
• Avionics architecture: sensor suite, flight computer layout, antenna gain study
• Control algorithms and simulation results (MATLAB/Simulink or Python) proving closed-loop stability through max-Q and vacuum phases
• Manufacturing plan with tolerances, suggested suppliers, and costed BOM
• Ground operations checklist and safety documentation
• Recovery concept (parachute, propulsive, or hybrid) with impact energy calculation
Acceptance criteria
The final design must show, through simulation, a minimum apogee of 100 km with ≤5 % margin on predicted total mass, meet ECSS thermal limits for avionics, and maintain uninterrupted downlink at ≥2 Mbps throughout ascent and descent.
All intellectual property produced transfers on full payment.