News and press releases from Wendernes Technology
Preliminary engine testing of green-flame propellant revealed critical thermal management and nozzle erosion challenges. Chamber wall temperatures exceeded design limits. Nozzle throat experienced severe erosion from combustion products. Engine test terminated early due to structural concerns. Redesign of cooling and nozzle materials required before further testing.
Laboratory synthesis of green-flame metal oxides encountered significant purity challenges. Batch analysis revealed contamination from precursor materials and synthesis byproducts. Impurities altered combustion behavior and introduced variability. Purification procedures are under development to achieve specification requirements.
Bench-scale combustion analysis of green-flame propellant revealed incomplete reaction and unidentified exhaust products. Spectroscopic analysis showed unexpected absorption lines inconsistent with theoretical combustion model. Lab work identified potential toxic intermediate species requiring further investigation and hazard assessment.
Particle suspension formulation for green-flame propellant development encountered critical stability failures. Long-term storage tests revealed particle agglomeration and settling. Laboratory analysis showed surfactant incompatibility with green-flame metal compounds. Reformulation work underway to resolve precipitation issues.
Laboratory synthesis of green-flame propellant initiated to develop environmentally-favorable hypergolic fuel. Initial trials revealed critical issues with particle suspension and combustion stability. Lab work focused on addressing synthesis challenges and optimizing formulation chemistry.
Comprehensive ground testing of IWFNA and morpholine-TEA propulsion system successfully completed. Specific impulse achieved 225 seconds with stable combustion and excellent performance. Test validates entire development program and demonstrates safe, reliable hypergolic system.
IWFNA (inhibited white fuming nitric acid) combines WFNA with morpholine-TEA inhibitor to provide superior corrosion protection while maintaining high oxidizer performance. Achieves 220-230 seconds specific impulse with excellent material compatibility.
Research evaluated alternative corrosion inhibitors including iodine pentoxide and organic compounds. After comprehensive testing, morpholine-TEA was selected as the optimal inhibitor for IWFNA due to superior performance, stability, and safety characteristics.
Development of morpholine-TEA as corrosion inhibitor for WFNA systems. Reduces corrosion rates 85-90% while maintaining high performance. Formulation optimized at 0.3-0.5% by weight. Ground testing validates excellent compatibility and reliability.
Transition from HTP to white fuming nitric acid (WFNA) as primary oxidizer. WFNA offers higher density and better performance. Initial compatibility testing with morpholine-TEA fuel blend underway. Specific impulse improvements to 220-230 seconds observed.
Refocused development on proven morpholine-TEA injection system. Hypergolic catalyst approach abandoned. Optimizing morpholine-TEA blend for improved performance and reliability through injector design and blend ratio testing.
Catastrophic test stand failure during hypergolic catalyst testing. Combustion chamber ruptured due to uncontrolled pressure rise and detonation. One technician sustained minor injuries. Hypergolic catalyst program suspended pending investigation.
Catalyst mixed directly into morpholine-TEA fuel blend to create self-igniting propellant system. Goal: eliminate HTP decomposition stage. Initial tests show ignition but unstable combustion with pressure oscillations.
Morpholine and triethylamine (TEA) blend tested as fuel component. TEA addition improves combustion efficiency and reduces pressure oscillations. Performance improvement now 25-30% over monopropellant baseline.
Morpholine injection testing downstream of HTP catalyst bed. With the goal to convert monopropellant thruster to bipropellant system with improved specific impulse. Initial tests show 15-20% performance improvement.
Extended duration ground testing with improved thruster design. 12-second burn achieved with stable chamber pressure and consistent thrust output. Reinforced catalyst bed support performs without anomalies.
Catalyst bed support redesigned: nickel-based superalloy with reinforcement ribs. FEA verified safety factor ≥3 at 50 bar, 900°C. 30-second burn test successful, flawless performance. Support showed no damage or stress. Multiple tests successful. Enables aggressive testing: higher pressures, longer burns, new catalysts.
Catalyst bed support structure failure ruptured thruster chamber at 15 seconds into burn test. No injuries; safety procedures effective. Root cause: stainless steel support inadequate for high pressure/temperature. Undecomposed HTP accumulated, building pressure. Redesigned support: high-temperature alloy with reinforcement ribs. Enhanced test procedures and instrumentation.
45-second continuous operation achieved with stable chamber pressure and consistent thrust. Catalyst bed maintained activity, no degradation. Thruster design proven sound for extended operation. Program transitioning to systematic performance optimization. Next: test different configurations, propellant loads, nozzle designs, catalyst formulations.
Ground test stand operational: load cell (0.1 N accuracy), pressure transducers, thermocouples, 1 kHz data acquisition. Thrust, pressure, and temperature measurement systems verified. Test fires confirm high-quality data capture. Dedicated test area with safety systems. Enables systematic catalyst and geometry optimization testing.
Vacuum-distilled HTP (85% pure, stabilizers removed) confirmed solution to catalyst degradation. Extended operation (120 seconds) maintained 85-88% decomposition efficiency. Manganese oxide on stabilized alumina catalyst performed flawlessly. Stabilizer poisoning was root cause. Catalyst particles remained discrete, surface area preserved. Program path forward established.
Vacuum distillation facility operational. First production run: 2 liters of 85% pure HTP from 5 liters of 49.5% commercial HTP. Rotary vane pump reduces pressure to 10 millibars. Compact lab-scale facility produces several liters per week. Provides supplier independence and quality control.
HTP supplier quality control issues: purity variance 85-92% H2O2. Few suppliers available, switching costly. Decision made to build in-house vacuum distillation facility for high-purity HTP production. Facility design: several liters per week capacity. Strategic investment for testing reliability and supply independence.
Catalyst bed degradation during extended HTP operation traced to stabilizer poisoning from commercial-grade propellant. Decomposition efficiency declined from 80% to 60% over 50+ seconds. Ultra-pure HTP testing confirmed stabilizer contamination as root cause. Vacuum distillation facility required to produce clean, high-concentration HTP.
HTP monopropellant thruster program initiated. Catalyst screening evaluated manganese dioxide and nickel-based compounds. Early testing achieved 70-80% decomposition efficiency. Catalyst bed geometry critical to prevent channeling. Stainless steel selected for initial designs. Systematic testing underway to optimize decomposition efficiency and thruster performance.