Energetic green propulsion for small spacecraft

Gibbon, D.; Paul, Malcolm; Jolley, Patrick; Zakirov, Vadim; Haag, Gary S.; Coxhill, Ian; Sweeting, Martin; EIoirdi, England R.

doi:10.2514/6.2001-3247

Cited by 11 publications

(8 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…VFP may be considered more complex due to adding the second fuel grain from the nozzle side, which has a cylindrical fuel port. EBH seems to be more studied in the literature than VFP, which was first proposed by Gibbon et al [17]. The most extensive published VFP research has been performed by the team at the Space Propulsion Laboratory (SPLab) of Politecnico di Milano [18][19][20][21][22][23].…”

Section: Vortex Flow Pancake and End-burning Hybrid Rocket Enginesmentioning

confidence: 99%

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Palacz,

Cieślik

2023

Aerospace

View full text Add to dashboard Cite

The paper is part of the research aimed at determining if the vortex flow pancake (VFP) hybrid rocket engine is feasible as green in-space chemical propulsion. The objective of this study is to test an N2O/HDPE VFP hybrid ignited with N2O/C3H8 torch igniter. The N2O is used in self-pressurizing mode, which results in two-phase flow and varying inlet conditions, thus better simulating real in-space behavior. The study begins with characterizing the torch igniter, followed by hot-fire ignition tests of the VFP. The results allow for the improved design of the torch igniter and VFP hybrid. The axial regression rate ballistic coefficients are reported for the N2O/HDPE propellants in the VFP configuration.

show abstract

Section: Vortex Flow Pancake and End-burning Hybrid Rocket Enginesmentioning

confidence: 99%

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Palacz,

Cieślik

2023

Aerospace

View full text Add to dashboard Cite

show abstract

“…This means that the I ssp of an FMMR system can be higher than that of a cold gas system. It should, however, be noted that there are cold gas and resistojet systems with liquid and solid propellant storage [18,19]. Those systems still, however, operate at high pressures with viscous losses.…”

Section: Background and Theorymentioning

confidence: 99%

Fabrication and evaluation of a free molecule micro-resistojet with thick silicon dioxide insulation and suspension

Palmer

Nguyen

Thornell

2013

J. Micromech. Microeng.

View full text Add to dashboard Cite

A silicon free molecule micro-resistojet (FMMR) with a thermally insulating suspension frame composed of silicon dioxide has been designed, fabricated and tested. The concept was developed to increase the efficiency of FMMRs, especially in silicon-based integrated systems. Fabrication of the thick insulating frame was performed through oxidation of high-aspect ratio silicon trenches. The thermal properties of the 1 cm2 thruster were evaluated using an IR camera, and it was found that when the volume inside the frame is heated more than 200 °C using integrated nickel heaters, the temperature increase in the volume outside the frame is less than 50 °C. During operation in vacuum, the thrust range was calculated to be about 13–1070 µN and the maximum specific impulse 54 s. At maximum thrust, and a power consumption of 1.6 W, the total efficiency of the thruster was 17%. Designs of more efficient and versatile systems are discussed.

show abstract

“…Surrey Space Center and the University of Surrey have been conducting extended investigations into thruster reactors for small satellites using N 2 O catalytic decomposition [324][325][326][327]. More than 50 catalysts were tested by Zakirov [324], with the most active being nickel oxides deposited on zircon and iridium oxides, or rhodium oxides deposited on γ -Al 2 O 3 .…”

Section: Effect Of Stabilizers On Catalytic Decompositionmentioning

confidence: 99%

Catalytic Decomposition of Energetic Compounds: Gas Generators and Propulsion1A list of abbreviations/acronyms used in the text is provided at the end of the chpater

Batonneau

Kappenstein

Keim

2008

Handbook of Heterogeneous Catalysis

View full text Add to dashboard Cite

The sections in this article are Introduction Energetic Compounds Propellants Gas generators Explosive Materials Ignition systems Scope of the Chapter, and Literature Data Units Some Propulsion Elements A Short Introduction to Propulsion Theory Comparison of Propulsion Types and Propellants Propulsion System Types Propellants Advantages of Catalytic Propulsion A Brief History of Rocketry and Catalytic Propulsion The Current Supremacy of Hydrazine Introduction Catalysts Heterogeneous Catalysis: General Studies Mechanistic Considerations A Literature Overview B Thermodynamic Data C Isotope‐Related Studies D Single‐Crystal Studies E Catalytic Cycle Proposals Iridium‐Based Industrial Catalysts A Shell 405 Catalyst ( USA ) B K ali C hemie KC 12 GA Catalyst ( G ermany) C C nesro Catalyst ( F rance) D GIPKh Catalysts (former USSR ) New Hydrazine Decomposition Catalysts Homogeneous Catalysis and Coordination Chemistry of Hydrazine Applications of Hydrazine Catalytic Decomposition Gas Generators Use in Fuel Cells Corrosion Protection Drawbacks of Hydrazine “Green” Propellants as Hydrazine Replacements Introduction Energetic Aqueous Ionic Liquids Thermal Decomposition Catalytic Decomposition of HAN , ADN , and HNF A Hydroxyl Ammonium Nitrate ( HAN ) B Hydrazinium NitroFormate ( HNF ) C Ammonium DiNitramide ( ADN ) Development of Tools for Catalyst Evaluation The Comeback of Hydrogen Peroxide Introduction Thermal and Catalytic Decomposition Catalysts for Monopropellant Engines Kinetic Rate of Decomposition Hybrid Engine Hypergolic Bipropellant Engine Effect of Stabilizers on Catalytic Decomposition Nitrous Oxide (N 2 O) for Monopropellant Engines or Hybrid Engines Introduction Catalysts Use of N 2 O as a Monopropellant Use of N 2 O for Hybrid Engine Future Prospective Applications of Catalytic Propulsion New Energetic Liquids Catalysts for Air‐Breathing Supersonic or Hypersonic Jets Catalysts for Pulse Detonating Engine Ignition of Gaseous Hydrogen–Oxygen Mixtures Gas Generator to Power Micropumps through Small Turbines Conclusion: A Biological System using H 2 O 2 Decomposition for Tactical Defense Acknowledgement

show abstract

Energetic green propulsion for small spacecraft

Cited by 11 publications

References 1 publication

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Fabrication and evaluation of a free molecule micro-resistojet with thick silicon dioxide insulation and suspension

Catalytic Decomposition of Energetic Compounds: Gas Generators and Propulsion1A list of abbreviations/acronyms used in the text is provided at the end of the chpater

Contact Info

Product

Resources

About