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IoA Technical Presentation-2
- 1. INSTITUTE OF AVIATION 10 N GREEN MONOPROPELLANT THRUSTER Samantha Booth Jordan Kenton Patrick Nienhaus Erich Zahn
- 2. • The number and frequency of past and future space missions • Variation in satellite sizes and the availability of rocket engines for them • Green fuels and current market fuels MARKET ANALYSIS
- 3. HYDROGEN PEROXIDE • Decomposes into steam and oxygen gas • spontaneous decomposition at high temperatures or with catalyst • high exhaust temperatures, low molecular weights • safe • Dpecific impulse increases with concentration • High density, non-toxic, non-corrosive, non-reactive • Easy to handle, inexpensive • Release response for HTP is to rinse with water • Lower specific impulse, higher density specific impulse • Storable? • lowest storage hazard class
- 4. MONOPROPELLANT COMPARISON • HTP has one of the largest densities. • Exemplifies the ideal green monopropellant • only questionable area is the storability • HTP is the recommended monopropellant.
- 5. CEA RESULTS
- 6. • Using tables from various websites, a list of materials and their compatibility with HTP was made. • Eliminating all materials that did not meet an excellent rating left these materials. • This is list was used to start finding materials that could be used in constructing the engine. POTENTIAL MATERIALS
- 7. CLOSER LOOK AT MATERIALS Steel 316 Inconel 625 Strength Strong Very Strong Thermal Average High Machining Easily formed Tough Cost ~$4/Kg ~$15/Kg
- 10. VALVES • Many different applications: • Submarines • Oil Piping • Missiles • Robots • There are many different kinds of valves: • Poppet • Spool • Proportional • Ball https://encrypted- tbn0.gstatic.com/images?q=tbn:ANd9GcQ0wHbVVYn4I0Qrp6L8wtmkGoff CFyWKWeGlhwuMTzTU-JlQs5T
- 11. VALVE CHARACTERISTICS • Thruster Valves • Before the Decomposition Chamber • Dual Redundant • Continuous Duty • Doesn’t Overheat • Current Drain • Amount Used • Cv Factor • Units of Gal/Min • Given Temperature and Pressure • Correction Factor • Multiple Flows • Manual Shutoff?
- 12. SOLENOID VALVE • Controlled by a Solenoid • Normally Closed/Open • AC vs. DC • Different types of solenoid valves • Proportional • Poppet • Spool
- 13. POPPET VALVE • Component covers internal passage blocking flow. • They are self cleaning, simple, and can be normally closed. www.europeanoilandgas.co.uk
- 14. VALVE
- 15. VENTURI NOZZLE • Venturi nozzle was required to control the mass flow. • Research showed that an inlet angle of 30⁰ and an outlet angle of 20⁰ was appropriate. • Length was dependent on an inlet diameter of 3.9688 mm and an outlet diameter of 9 mm and the specified angles. • Will be connected to the valve at the inlet section and the decomposition chamber at the outlet section.
- 16. FACEPLATE DESIGN • Distribute propellant evenly across the catalyst bed • Since it’s a monopropellant no atomization is required • Combustion chambers need atomization • Shower head design http://www.rnrassociates.com/word press/wp- content/uploads/2012/11/kohler- moxie-showerhead-and-wireless- speaker4-400x320.jpg
- 17. SHOWER HEAD
- 18. SHOWER HEAD ANALYSIS (DISPLACEMENT)
- 19. SHOWER HEAD ANALYSIS (STRESS)
- 20. DESIGN PARAMETERS OF CATALYST BED • Required diameter and length to obtain optimal decomposition of HTP (~95%) • Obtained diameter of approximately 9 mm
- 21. DESIGN PARAMETERS OF CATALYST BED • Length of approximately 30 mm was obtained through interpolation of the best fit line.
- 22. THERMAL AND STRUCTURAL ANALYSIS
- 23. • Using Bartz equation, an approximate heat load was found. • The convection constraint is based on the properties of air. • The temperature constraint is based on the properties of the decomposition of HTP. • This was then applied to the test section to analyze the result. THERMAL AND STRUCTURAL ANALYSIS
- 25. NOZZLE PARAMETERS • The two most important nozzle parameters: Throat Area, Area Ratio (Exit to Throat) • These can be found using the following relationships:
- 26. NOZZLE PARAMETERS • CF is a property of the geometry. • C* is a property of the propellant, H2O2. Pc 8 Bar Gamma 1.28 (constant) c* 1015 m/s c* efficiency 0.9 5 P∞ 1 Bar Isp 130 s ṁ 0.0078 kg/s (for 10N Thrust) At 9.46 µm2 (1.74 mm radius)
- 27. 0 10 20 30 40 50 60 70 80 0 2 4 6 8 10 12 14 16 18 20 Pressure Ratio Pc/Pe Thrust(N) Thrust vs Pressure Ratio for Different AR at Ambient 1 Bar AR:1.5 AR:2 AR:3 AR:4 AR:10
- 28. NOZZLE PARAMETERS • Choosing the Area Ratio • For example, if ideal expansion is desired: Chamber Pressure (bar) Pressure Ratio Area Ratio for Ideal Expansion 6 6 1.563 8 8 1.843 10 10 2.108
- 29. NOZZLE CONTOUR • Simple, 15o divergent half angle • Easier to design/manufacture • On large thruster, is inefficient, energy losses, non uniform exit flow • For our purposes, for such a small thruster, this method is appropriate to save time, effort, and cost. • Uses MoC to minimize length, therefore minimizing weight • High initial divergent angle, levels off to a small exit divergent angle • More efficient, less energy loss, uniform exit flow • Harder to design/manufacture Converging Section Due to the low mach, low energy flow, the convergent section is simple. A convergent half angle of anywhere from 20o to 60o will work. Conical Diverging Section Optimum Bell Diverging Section
- 30. NOZZLE CONTOUR A 60% bell nozzle has a length that is 60% of a 15o conical nozzle.
- 31. CURRENT NOZZLE DESIGN Covergent Half-Angle 50o Divergent Half-Angle 12o Throat Area 7.57 µm2 (1.55 mm Radius) Exit Area 15.9 µm2 (2.25 mm Radius) Area Ratio 2.11
- 33. FULL DESIGN