Sciences is developing a hybrid sounding rocket platform that carries scientific payloads for increased access to a microgravity environment and to kick-start an educational rocket program at the university. This paper gives an introduction and overview of the program, including the program goals and flight-weight prototype system design. An overview is given on the manufacture of the 1400 lbf (at altitude) prototype motor, and system testing. In addition, the results of recent vertical static test fire attempts are discussed, along with the preliminary goals of subsequent semesters of the project. NomenclatureCO 2 = Carbon Dioxide CFT = Cold Flow Test = Pressure = Temperature COPV = Composite-Overwrapped Pressure Vessel EPR = Electronics and Payload Recovery GSE = Ground Support Equipment HTPB = Hydroxyl-terminated Polybutediene = Mach number = Ratio of specific heats = Universal gas constant = Thrust HySoR = the Hybrid Sounding Rocket project N 2 O = Nitrous Oxide STF = Static Test Fire TPS = Thermal Protection System ̇ = Mass flow rate = Area = Velocity = Specific impulse
Historically, spacecraft reaction control systems have primarily utilized cold gas thrusters because of their inherent simplicity and reliability. However, cold gas thrusters typically have a low specific impulse. It has been determined that a higher specific impulse can be achieved by passing a monopropellant fluid mixture through a catalyst bed prior to expulsion through the thruster nozzle. This research analyzes the potential efficiency improvements from using tri-gas, a mixture of hydrogen, oxygen, and an inert gas, which in this case is helium. Passing tri-gas through a catalyst causes the hydrogen and oxygen to react and form water vapor, ultimately heating the exiting fluid and generating a higher specific impulse. The goal of this project was to optimize the thruster performance by characterizing the effects of varying several system components including catalyst types, catalyst lengths, and initial catalyst temperatures. Nomenclature a o = sonic velocity A e = exit area A t = throat area c * = characteristic velocity d = chamber diameter D = particle diameter g o = acceleration due to gravity γ = ratio of specific heats I sp = specific impulse k = conversion factor k m = MACOR thermal conductivity k s = stainless steel thermal conductivity l = catalyst bed length ̇ = fluid mass flow rate M e = exit Mach number µ f = fluid viscosity P c = chamber pressure P e = exit pressure Q = heat energy Re = Reynolds number ρ f = fluid density T o = stagnation temperature T ∞ = ambient temperature
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