Design & Manufacturing

Aero-Structures Analysis

• Rapid design iteration

• Physics, Analysis-oriented testing

• Efficient Cross-Specialty Collaboration

• Development for Reliability, Robustness

• Expand team technicality, individual learning capability

Flight Avionics: Stackable Sub-Module Array

Instrumentation Requirements:

Command/Communications Structure

Control State Structure

Development Steps:

1. High-Level Rocket Structure: Thrust Range, Vehicle Mass (+-50%)

2. Conservative(High-Thrust) Thruster / Feed System Design + Review

3. Fluid System Assembly, Testing, Calibration. Instrumentation and Control Development. Flight Structure Design Integration

4. Static Fire Testing. Mass Optimization, Simulation Refinement.

5. Flight Vehicle Integration

Thruster + Injector

Priorities: Stable, Conservative Performance and Efficient Manufacturing/Assembly

• Injector: Unlike-Doublet Impinging, LOX-centered

• Chamber: Ablative + Fuel Jetted Wall-Film. 6061 Aluminum Jacket.

• Nozzle: Graphite Throat, 316L Stainless Steel Expansion

Fluid System (Engine "Feed System")

Specifications

• Dual side dual deployment

• Redundant Altimeters, ejection charges

• Dual-Camera Onboard Monitoring

• GPS real-time telemetry

Requirements

• Drogue Deployment velocity < 50 ft/s

• Main chute deployment velocity < 100 ft/s

• Landing velocity: below 25 ft/s

• Downwind Drift < 1 km

Demonstration Launch 11/2023

MCMC Dispersion Analysis

• Target Apogee, Precision: 2500m, +-10%

• Approx. Vehicle Mass: 40kg dry

• Approx. Thrust Level, Burn Time: 1.80kN, 10sec