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Adey Rocket Fluid TEC

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Adey Rocket Fluid TEC: A Collaborative Design

Concept: A small, reusable micro-launcher with in-situ propellant production for frequent, low-cost launches of small payloads.

Key Features:

  • Sustainability: Onboard electrolyzer and water recovery system for producing LH2 and LOX from recovered water.
  • Reusability: Retractable landing legs, advanced thermal protection, and precise landing systems for rapid turnaround.
  • Efficiency: High-efficiency staged combustion cycle engine with deep throttling and variable geometry nozzles.
  • Versatility: Modular payload interface for accommodating various micro-satellites and small payloads.

Design Refinements (Incorporating Feedback):

  • Hybrid Propulsion: Integrate a hybrid propulsion system (e.g., solid fuel with liquid oxidizer) as a backup or for specific mission profiles. This enhances reliability and potentially reduces development costs.
  • Modular Design: Design the rocket with modular components (e.g., payload bay, engine section, propellant tanks) to allow for scalability and easier maintenance.
  • Enhanced Electrolyzer: Utilize advanced, high-efficiency solid oxide electrolyzer technology for improved energy conversion and reduced mass.
  • Water Recovery Optimization: Incorporate advanced water vapor capture techniques, such as cryogenic traps or membrane separators, to maximize water recovery efficiency.
  • Thermal Management: Integrate advanced thermal management systems, such as passive and active cooling techniques, to minimize heat losses and maintain optimal temperatures for cryogenic propellants and electronics.
  • Power Generation: Explore alternative power sources, such as fuel cells or radioisotope thermoelectric generators (RTGs), as supplements to solar power, especially for extended missions or low-light conditions.
  • Safety Enhancements: Implement robust safety systems, including redundant components for critical systems (e.g., ignition, power, propulsion), and incorporate advanced leak detection and mitigation measures.

Next Steps:

  1. Detailed Trade Studies: Conduct in-depth trade studies to evaluate the performance and cost-effectiveness of different design options, such as engine types, propellant combinations, and structural materials.
  2. Prototype Development: Develop and test critical subsystems, such as the electrolyzer, water recovery system, and thermal management system, in a ground-based environment.
  3. Simulation and Modeling: Utilize advanced simulation and modeling tools to analyze the rocket’s performance, assess risks, and optimize the design.
  4. Partnerships: Collaborate with universities, research institutions, and industry partners to leverage expertise in specific areas, such as materials science, propulsion technology, and cryogenic engineering.

Conclusion:

By combining the initial conceptual analysis with a detailed design approach, we have developed a more robust and refined concept for the „Adey Rocket Fluid TEC.“ This collaborative effort has resulted in a design that addresses the initial challenges, incorporates valuable feedback, and has the potential to revolutionize small-scale space launches.

Further Research:

  • Investigate the feasibility of using advanced materials, such as carbon nanotubes or graphene, for lightweight and high-strength structures.
  • Explore the potential of using laser propulsion systems as an alternative or supplementary propulsion method.
  • Conduct environmental impact assessments to ensure the sustainability of the rocket’s operations.

This collaborative design process demonstrates the importance of iterative refinement and continuous improvement in developing innovative and impactful space technologies. By addressing the challenges and incorporating feedback, we can move closer to realizing the vision of a sustainable and accessible space future.

Concept: Adey Rocket Fluid TEC – Self-Sustaining Micro-Launcher

Core Idea: A small, reusable launcher designed for frequent, low-cost launches of micro-satellites or other small payloads. It emphasizes sustainability through in-situ resource utilization (ISRU) and a closed-loop propellant system.

1. Propulsion System (Enhanced for Sustainability):

  • Rocket Engine:
    • A high-efficiency, deep-throttling rocket engine capable of operating on liquid hydrogen (LH2) and liquid oxygen (LOX).
    • Utilizes a staged combustion cycle for optimal performance and reusability.
  • Combustion Chamber & Nozzle:
    • Advanced materials and cooling techniques for extended burn times and reusability.
    • Variable geometry nozzle for optimized thrust at different altitudes.
  • Turbopumps:
    • High-performance turbopumps optimized for cryogenic propellants, driven by a closed-cycle turbine.
    • Utilizes the 1″ Swagelok U series for Hydrogen and Oxygen.
  • Propellant Tanks:
    • Cryogenic tanks with advanced insulation to minimize boil-off.
    • Integrated sensors for precise propellant level and temperature monitoring.
  • Ignition System:
    • Redundant spark igniters for reliable ignition.
    • Hypergolic backup system for added reliability.
  • Electrolyzer and Water Recovery:
    • Onboard electrolyzer system powered by high efficiency solar panels.
    • Water recovery system that captures water vapor from the combustion exhaust and recycles it.
    • This system will allow for the production of LOX and LH2 in flight, and on the ground, without the need for refilling.
    • Water will be stored in a tank, and pumped to the electrolyser.
  • Adey Rocket Fluid TEC:
    • This will be a system of heat exchangers, and cooling systems, that will manage the extreme temperatures within the rocket.
    • This system will also aid in the water recovery process, by condensing water vapor.

2. Structural System:

  • Airframe:
    • Lightweight, high-strength composite materials for optimal performance.
    • Aerodynamic design for efficient ascent and descent.
  • Stages:
    • Single-stage-to-orbit (SSTO) or a minimal two-stage design for simplicity and reusability.
  • Landing Legs:
    • Retractable landing legs for precise vertical landing.

3. Guidance, Navigation, and Control (GNC) System:

  • Advanced GNC:
    • High-precision inertial navigation system (INS) combined with GPS and star trackers for accurate trajectory control.
    • Real-time trajectory optimization and adaptive control algorithms.
  • Thrust Vectoring:
    • Gimbaled engine or reaction control system (RCS) for precise attitude control and trajectory adjustments.

4. Payload System:

  • Modular Payload Bay:
    • Standardized payload interface for easy integration of various micro-satellites and payloads.
    • Payload adapter with shock and vibration isolation.

5. Electrical and Power System:

  • High-Efficiency Solar Panels:
    • Integrated solar panels on the rocket’s body to generate power for onboard systems and the electrolyzer.
  • Advanced Batteries:
    • High-capacity, lightweight batteries for peak power demands.
    • Redundant power distribution system.

6. Recovery System:

  • Precise Landing System:
    • Combination of GPS, radar, and lidar for accurate landing site selection.
    • Automated landing control system for vertical landing.

7. Thermal Protection System:

  • Advanced Heat Shield:
    • Reusable thermal protection system (TPS) for atmospheric re-entry.
    • Cryogenic Insulation.
  • Adey Rocket Fluid TEC:
    • This system will also regulate the temperature of the cryogenic propellants, and the electronics.

8. Telemetry and Communication System:

  • High-Bandwidth Communication:
    • S-band and X-band communication systems for real-time data transmission.
    • Onboard data logging and analysis.
  • Sensor Network:
    • Comprehensive sensor network for monitoring engine performance, structural integrity, and environmental conditions.

Swagelok 1″ U Series Integration:

  • The 1″ Swagelok U series fittings and valves will be utilized in the high-pressure LH2 and LOX feed lines, providing reliable and leak-free connections.
  • This series is chosen for its high-pressure rating, cryogenic compatibility, and proven performance in demanding applications.

Operational Concept:

  1. Launch: The rocket launches vertically, powered by the LH2/LOX engine.
  2. Ascent: The GNC system guides the rocket to the desired orbit.
  3. Payload Deployment: The payload is deployed into orbit.
  4. Descent: The rocket performs a controlled descent and vertical landing.
  5. Refueling/Recharging: The onboard electrolyzer system begins to produce LOX and LH2 from the recovered water, and the solar panels recharge the batteries.
  6. Reuse: The rocket is prepared for its next launch.

Advantages:

  • Reduced launch costs through reusability and in-situ propellant production.
  • Increased launch frequency due to rapid turnaround.
  • Environmentally friendly due to the use of clean propellants and a closed-loop system.
  • Enhanced accessibility to space for micro-satellites and small payloads.

This concept provides a robust framework for the Adey Rocket Fluid TEC micro-launcher. Further detailed design and engineering analysis will be required to refine the system and validate its performance.