HAN‐Based Green Propellant, SHP163 – Its R&D and Test in Space

Abstract

HAN‐based green liquid propellant, SHP163 is tested in space at the Rapid Innovative Payload Demonstration Satellite (RAPIS) project. The first RAPIS satellite, RAPIS‐1, was successfully launched with six other small satellites on January 18th, 2019 by the Epsilon‐4 launcher. In addition, the thruster of the 1 N Green Propellant Reaction Control System (GPRCS) fueled with SHP163 was installed on RAPIS‐1, which has started its operation in space. The first injection was performed on February 18th, 2019 for 20 s, and the combustion was recognized with an increase in temperature of the catalyst bed and the increment of semi‐major axis of the satellite. The combustion efficiency evaluated using the semi‐major axis data was more than 80 %. The test in space will continue till the end of January 2020, setting the full success at 3,000 s of accumulated operation time and 10,000 times pulse mode burn.

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

“…This propellant has density of 1.4 g cm −3 yet achieves high volumetric specific impulse ρI sp = 396 g s cm −3 , which is higher than AF-315E (at 0.7 MPa chamber pressure and 50:1 nozzle expansion ratio at frozen conditions) [36]. The flame temperature is considered very high, as it records about 2400 K [36,37]. As SHP163 shows to be one of the most energetic propellants for use in a thruster, it demonstrates operational stability and shows enough safety levels to be accepted as a green and safe liquid propellant [38].…”

“…SHP163 is another very interesting HAN-based green propellant, which was being developed since the year 2000 at the Institute of Space and Astronautical Science (ISAS)/(JAXA). SHP163 is composed of 73.6 wt% HAN, 3.9 wt% AN, 16.3 wt% methanol, and 6.2 wt% water [36]. This propellant has density of 1.4 g cm −3 yet achieves high volumetric specific impulse ρI sp = 396 g s cm −3 , which is higher than AF-315E (at 0.7 MPa chamber pressure and 50:1 nozzle expansion ratio at frozen conditions) [36].…”

“…SHP163 is composed of 73.6 wt% HAN, 3.9 wt% AN, 16.3 wt% methanol, and 6.2 wt% water [36]. This propellant has density of 1.4 g cm −3 yet achieves high volumetric specific impulse ρI sp = 396 g s cm −3 , which is higher than AF-315E (at 0.7 MPa chamber pressure and 50:1 nozzle expansion ratio at frozen conditions) [36]. The flame temperature is considered very high, as it records about 2400 K [36,37].…”

“…Table 3. Physical properties and performance (@ 1 MPa chamber pressure, 100:1 expansion ratio, and vacuum conditions, using NASA Chemical Equilibrium Analysis (CEA) [32] and verified from [4,30,33,36,37,[44][45][46]). HNP225 is the one among the family with the least adiabatic flame temperature around 1000 K (even less than hydrazine ∼1200 K), while HNP221 is approximately 1400 K [33,43].…”

Structural Properties of HEHN- and HAN-Based Ionic Liquid Mixtures: A Polarizable Molecular Dynamics Study

“…Extensive research has led to success in formulating HAN-based and ADN-based monopropellant mixtures. For example, the most common ADN-based mixtures, FLP-106 and LMP-103S, offered enhanced energy densities, low adiabatic flame temperatures, and compatibility with stabilizing agents, like methanol, to better control burning rates. , Early HAN-based liquid gun propellants (LGPs) were found to be easily stored, characterized by hypergolic ignition behavior, and less toxic than hydrazine. ,,− Subsequent improvements to HAN-based formulas led to AF-M315E and SHP163 that have been used successfully for in-space technology demonstrations. , Other formulations, including HNPxxx and GEM, have become increasingly relevant due to their lower adiabatic flame temperatures and success when electrically or thermally ignited (as opposed to catalytically). , …”