Downloaded 21 times
Uploaded byDHA Suffa University, AeroX
"It isn't exactly Rocket Science" The artsy science of rocket propulsion
The document discusses the evolution and mechanics of rocket propulsion, emphasizing the stagnation of scientific innovation in Pakistani universities and the need for more practical applications in technology. It explores the historical advancements in rocketry, from early Chinese rockets to modern propulsion systems, detailing different propulsion methods and propellant compositions. Key concepts include Tsiolkovsky's rocket equation, classifications of rockets, and the importance of specific impulse in evaluating rocket performance.
More Related Content
Similar to "It isn't exactly Rocket Science" The artsy science of rocket propulsion
"It isn't exactly Rocket Science" The artsy science of rocket propulsion
- 1. It isn't exactlyRocket Science The artsy science of rocket propulsion Bilal A. Siddiqui October 07, 2016 Invited Lecture Session
- 2. Introduction ▫ Publishing andProducing Science is necessarily innovative. It cannot stagnate. Research in many Pakistani universities has stagnated to Publishing. It’s publish of perish, for individuals. But publishing for the sake of publishing is perishing the society. We need to selfish collectively, not individually. Zalimaa Science Pila day! 2 ICEE’16
- 3. Distributed NMPC Formation Controlwith Limited Bandwidth 3
- 4. Science Sells ▫ Weare consumers of technology, not producers. ▫ We spend money ON technology, not FROM it. ▫ Universities have huge resources which can make commercializable products. ▫ But Pakistani universities are more interested in teaching standard curricula with little out of the box thinking. ▫ To change this, we need to change the way we think. ▫ Education needs to be student centered, soft wired. 4 ICEE’16
- 5. Distributed NMPC Formation Controlwith Limited Bandwidth 5
- 6. www.hearlihy.com Briefly about propulsion •It is a simple reaction engine, much like any other aviation engine. ▫ A mass of fluid is accelerated somehow ▫ This ‘propelled mass’ exerts an equal and opposite force on the engine 6
- 7. Jet Propulsion Classifications •Air-Breathing Systems ▫ Also called duct propulsion. ▫ Vehicle carries own fuel; surrounding air (an oxidizer) is used for combustion and thrust generation ▫ Gas turbine engines on aircraft… • Rocket Propulsion ▫ Vehicle carries own fuel and oxidizer, or other expelled propellant to generate thrust: ▫ Can operate outside of the Earth’s atmosphere ▫ Launch vehicles, upper stages, Earth orbiting satellites and interplanetary spacecraft … or www.gadgets-reviews.com …or go karts! www.the-rocketman.co … a rocket powered scooter!
- 8. Early History • China,1232 • Chinese history in the use of primitive rockets spans centuries • Armies fired flaming rockets at enemies • Battle of Kai-fung-fu, rockets launched could be heard for 15 miles when launched and upon impact devastated everything in all directions for 2,000 feet • Carried incendiary materials and iron shrapnel • Essntially bamboo filled with gunpowder • Armies started preferring cannons to Chinese rockets 8
- 9. Early History –Tipu Sultan • Next breakthrough came in India • Mysorean rockets were the first iron- cased rockets successfully deployed for military use. Hyder Ali and son Tipu Sultan used them against the British during the 1780s. • This exposed the British to this technology, which was then used to advance European rocketry with the development of the Congreve rocket in 1804. • Rocket became in vogue again! Distributed NMPC Formation Control with Limited Bandwidth 9
- 10. History – Britishand the US • British developed a rocket program. Used this program on United States • Bombed Baltimore for 25 hours • Francis Scott Key wrote poem “...and the rockets red glare...gave proof through the night that our flag was still there...” • Confederate States of America, 1864 • 12 foot long rocket, 10 pounds of gunpowder • Launched from Richmond, Virginia • Intended to be first ballistic missile • Target was Washington, D.C. • Brass case marked C.S.A. • Roar out of sight • Never found Distributed NMPC Formation Control with Limited Bandwidth 10
- 11. So what wasthe point? • Rockets = weapons • No real thought on how they worked or functioned • No control, just light it and hope it doesn’t return • Someone changed all that… 11
- 12.
- 13. Jules Verne • 1866,published, “From the Earth to the Moon” • He changed the thinking of rockets • He saw them as method of travel • He presented the world with a glimpse of the future • Deeply affected the course of rockets • Also published Time travel • Makes you wonder why beards were fashionable back in the day? 13
- 14. Russia 1883 • SchoolTeacher, Konstantin Tsiolkovsky, published famous “Rocket Equation” in 1903 • Considered mad at time now a monument stands in Moscow • Influenced by Verne • Very poor and nearly deaf • Was self educated • Published over 500 papers • Talked about multistage rockets, liquid rockets 14
- 15. Distributed NMPC Formation Controlwith Limited Bandwidth 15
- 16. Tsiolkovsky’s Rocket Equation •Newton’s F=ma holds, but actually represents only constant mass systems in this form • For variable masses, it is ∫ 𝐹𝑑𝑡 = ∫ 𝑚𝑑𝑣 • Integrating this, Tsiolkovsky found 𝑣 𝑏 = 𝑣𝑒 ln 𝑀 𝑜 𝑀𝑓 where vb is rocket velocity at burnout, M0 is the mass of the rocket at take-off and Mf is the final mass • Let this equation talk to you. 16
- 17. Mission Delta-V Requirements Mission(duration) Delta-V (km/sec) Earth surface to LEO 7.6 LEO to Earth Escape 3.2 LEO to Mars (0.7 yrs) 5.7 LEO to Neptune (29.9 yrs) 13.4 LEO to Neptune (5.0 yrs) 70 LEO to alpha-Centauri (50 yrs) 30,000 LEO = Low Earth orbit (approx. 274 km)
- 18. Anatomy of theChemical Rocket • Tsiolkovsky got depressed since it was impossible to him how could one produce so much thrust as required by Verne (moon guy) • Until he met Mendeleyev (periodic table guy) • They decided the best way is to burn things. • All chemical rockets require ▫ Oxidizer ▫ Fuel • All of these guys wore beards 18
- 19. Modern Rocketry • China(300 B.C.) ▫ Earliest recorded use of rockets ▫ Black powder • Russia (early 1900’s) ▫ Konstantin Tsiolkovsky ▫ Orbital mechanics, rocket equation • United States (1920’s) ▫ Robert Goddard ▫ First liquid fueled rocket (1926) • Germany (1940’s) ▫ Wernher von Braun ▫ V-2 ▫ Hermann Oberth Wan-Hu who tried to launch himself to the moon by attaching 47 black powder rockets to a large wicker chair! onenew.wordpress.com Prof. Tsiolkovsky Dr. Goddard goddard.lit tletonpubli cschools.n et Dr. von Braun www.britannica.com www.geocities.com
- 20. Space Propulsion System Classifications StoredGas Chemical Electric Advanced • Electrothermal • Electrostatic • Electrodynamic • Nuclear • Solar thermal • Laser • Antimatter LiquidSolid Hybrid Pump FedPressure Fed Monopropellan t Bipropellant Space propulsion systems are classified by the type of energy source used.
- 21. Stored Gas Propulsion •Primary or auxiliary propulsion. • High pressure gas (propellant) is fed to low pressure nozzles through pressure regulator. • Release of gas through nozzles (thrusters) generates thrust. • Currently used for momentum management of the Spitzer Space telescope. • Propellants include nitrogen, helium, nitrous oxide, butane. • Very simple in concept. P Gas Fill Valve Pressure Gage High Pressure Isolation Valve Pressure Regulator Filter Thruster Propellant Tank Low Pressure Isolation Valve
- 22. Chemical Propulsion Classifications •Liquid Propellant ▫ Pump Fed Launch vehicles, large upper stages ▫ Pressure Fed Smaller upper stages, spacecraft ▫ Monopropellant Fuel only ▫ Bipropellant Fuel & oxidizer • Solid Propellant ▫ Launch vehicles, Space Shuttle, spacecraft ▫ Fuel/ox in solid binder • Hybrid ▫ Solid fuel/liquid ox ▫ Sounding rockets, X Prize www.aerospaceweb.org en.wikivisual.com news.bbc.co.uk
- 23. Monopropellant Systems • Hydrazinefuel is most common monopropellant. ▫ N2H4 • Decomposed in thruster using catalyst to produce hot gas for thrust. • Older systems used hydrogen peroxide before the development of hydrazine catalysts. • Typically operate in blowdown mode (pressurant and fuel in common tank). PFuel Fill Valve Pressure Gage Isolation Valve Filter Thrusters Propellant Tank Nitrogen or helium Hydrazine
- 24.
- 25. Bipropellant Systems • Afuel and an oxidizer are fed to the engine through an injector and combust in the thrust chamber. • Hypergolic: no igniter needed -- propellants react on contact in engine. • Cryogenic propellants include LOX (-423 ºF) and LH2 (-297 ºF). ▫ Igniter required • Storable propellants include kerosene (RP-1), hydrazine, nitrogen tetroxide (N2O4), monomethylhydrazine (MMH) FUEL OX P P Isolation Valves Engine Chamber Nozzle
- 26. Liquid Propellant Systems •Pump fed systems ▫ Propellant delivered to engine using turbopump Gas turbine drives centrifugal or axial flow pumps ▫ Large, high thrust, long burn systems: launch vehicles, space shuttle ▫ Different cycles developed. Photos history.nasa.goF-1 Engine Turbopump H-1 Engine Turbopump F-1 engine turbopump: • 55,000 bhp turbine drive • 15,471 gpm (RP-1) • 24,811 gpm (LOX) A 35’x15’x4.5’ (ave. depth) backyard pool holds about 18,000 gallons of water. How quickly could the F-1 pump empty it? Ans: In 27 seconds!
- 27. Rocket Engine PowerCycles • Gas Generator Cycle ▫ Simplest ▫ Most common ▫ Small amount of fuel and oxidizer fed to gas generator ▫ Gas generator combustion products drive turbine ▫ Turbine powers fuel and oxidizer pumps ▫ Turbine exhaust can be vented through pipe/nozzle, or dumped into nozzle ▫ Saturn V F-1 engine used gas generator cycle www.aero.org/public ations/ crosslink/winter200 4/03_sidebar3.html www.answers.com
- 28. Rocket Engine PowerCycles - cont • Expander ▫ Fuel is heated by nozzle and thrust chamber to increase energy content ▫ Sufficient energy provided to drive turbine ▫ Turbine exhaust is fed to injector and burned in thrust chamber ▫ Higher performance than gas generator cycle ▫ Pratt-Whitney RL-10 www.aero.org/publicati ons/ crosslink/winter2004/0 3_sidebar3.html science.nasa.gov
- 29. Rocket Engine PowerCycles - cont • Staged Combustion ▫ Fuel and oxidizer burned in preburners (fuel/ox rich) ▫ Combustion products drive turbine ▫ Turbine exhaust fed to injector at high pressure ▫ Used for high pressure engines ▫ Most complex, requires sophisticated turbomachinery ▫ Not very common SSME (2700 psia) www.aero.org/public ations/ crosslink/winter200 4/03_sidebar3.html www.rocketrelics.com shuttle.msfc.nasa.gov
- 30. The Big Engines… F-1Engine Saturn V 1.5 million lbs thrust (SL) LOX/Kerosene www.flickr.com Main Engine Space Shuttle 374,000 lbs thrust (SL) LOX/H2 spaceflight.nasa.gov RD-170 1.78 million lbs thrust (SL) LOX/Kerosene www.aerospaceguide.net
- 31. www.nationalmuseum.af.mil Solid Propellant Motors •Fuel and oxidizer are in solid binder. • Single use -- no restart capability. • Lower performance than liquid systems, but much simpler. • Applications include launch vehicles, upper stages, and space vehicles. www.aerospaceweb.org www.propaneperformance.com
- 32. Ignition System • Largesolid motors typically use a three-stage ignition system ▫ Initiator: Pyrotechnic element that converts electrical impulse into a chemical reaction (primer) ▫ Booster charge ▫ Main charge: A charge (usually a small solid motor) that ignites the propellant grain. Burns for tenths of a second with a mass flow about 1/10 of the initial propellant grain mass flow.
- 33. Propellant Grain • Twomain catagories ▫ Double Base: A homogeneous propellant grain, usually nitrocellulose dissolved in nitroglycerin. Both ingredients are explosive and act as a combined fuel, oxidizer and binder ▫ Composite: A heterogeneous propellant grain with oxidizer crystals and powdered fuel held together in a matrix of synthetic rubber binder. Less hazardous to manufacture and handle
- 34. Conventional Composite • Fuel ▫5-22% Powdered Aluminum • Oxidizer ▫ 65-70% Ammonium Perchlorate (NH4ClO4 or AP) • Binder ▫ 8-14% Hydroxyl- Terminated Polybutadiene (HTPB)
- 35. Fuels • Aluminum (Al) ▫Molecular Weight: 26.98 kg/kmol ▫ Density: 2700 kg/m3 ▫ Most commonly used • Magnesium (Mg) ▫ Molecular Weight: 24.32 kg/kmol ▫ Density: 1750 kg/m3 ▫ Clean burning (green) • Beryllium (Be) ▫ Molecular Weight: 9.01 kg/kmol ▫ Density: 2300 kg/m3 ▫ Most energetic, but extremely toxic exhaust products
- 36. Oxidizers • Ammonium Perchlorate(AP) ▫ Most commonly used ▫ Cl combining with H can form HCl Toxic Depletion of ozone • Ammonium Nitrate (AN) ▫ Next most commonly used ▫ Less expensive than AP ▫ Less energetic ▫ No hazardous exhaust products
- 37. Binders • Hydroxyl TerminatedPolybutadiene (HTPB) ▫ Most commonly used ▫ Consistency of tire rubber • Polybutadiene Acrylonitrile (PBAN) • Nitrocellulose (PNC) ▫ Double base agent
- 38. Additives • Used topromote ▫ Curing ▫ Enhanced burn rate (HMX) ▫ Bonding ▫ Reduced radiation through the grain (darkening) ▫ Satisfactory aging ▫ Reduced cracking
- 39. Some More Maths •Rocket Ignition ▫ Energy Harnessing Solution ▫ Newton’s 3rd Law • Performance calculated through quantities of temperature and pressure ▫ Combustion Thermodynamics Tsiolkovsky’s Rocket Equation 𝑣 𝑏 = 𝑣𝑒 ln 𝑀 𝑜 𝑀𝑓
- 40. Rocket Performance Calculations •Thrust & Specific Impulse ▫ Thrust is the amount of force generated by the rocket. ▫ Specific impulse is a measure or engine performance (analogous to miles per gallon) Units are seconds • Rocket Equation V gIsp ln mi mf Isp F w F rocket thrust w weight flowrate of propellant g 9.8 m/s2 mi mass of vehicle before burn mf mass of vehicle after burn mp mass of propellant for V mi mf mp mi 1 e V gIsp Rocket equation assumes no losses (gravity effects, aerodynamic drag). Actually very accurate for short burns in Earth orbit or in deep space! 𝑣 𝑏 = 𝑣𝑒 ln 𝑀 𝑜 𝑀𝑓
- 41. Specific Impulse Comparison •Stored gas • Monopropellant hydrazine • Solid rocket motors • Hybrid rockets • Storable bipropellants • LOX/LH2 • 60-179 sec • 185-235 sec • 280-300 sec • 290-340 sec • 300-330 sec • 450 sec Specific impulse depends on many factors: altitude, nozzle expansion ratio, mixture ratio (bipropellants), combustion temperature. This thruster was used on the Viking Lander. It has a specific impulse of about 225 seconds.www.rocketrelics.com
- 42. COMMON LIQUID ROCKETFUELS• Most Common Liquid Oxidizers ▫ LOX ▫ Hydrogen Peroxide ▫ Nitric Acid ▫ Nitrogen Tetroxide ▫ Liquid Florine • Most Common Liquid Fuels ▫ Hydrocarbon fuels (RP1, kerosense, methane) ▫ Liquid hydrogen ▫ Hydrazine (also mono) ▫ Unsymmetrical Dimethylhydrazine 42
- 43. Propellant Calculation Exercise •Determine the mass of propellant to send a 2500 kg spacecraft from LEO to Mars (0.7 yr mission). ▫ Assume the 2500 kg includes the propellant on- board at the start of the burn. ▫ Assume our engine has a specific impulse of 310 sec (typical of a small bipropellant engine). ▫ Use the rocket equation: mp 2500 1 e 5700 9.8 310 2117 kg Most of our spacecraft is propellant! Only 383 kg is left for structure, etc! How could we improve this?
- 44. SUMMARY OF KEYEXIT VELOCITY EQUATIONS For high Ue (for all thermal rockets), desire: ▫ Propellants with low molecular weight, M ▫ Propellant mixtures with large QR/M ▫ High combustion chamber pressure, P02 1 02 1 02 2 1 02 2 12 1 1 2 12 p p M Q U p p T M R p p TCU eR e e o e ope 44
- 45. Rocket Science –Govt or Pvt? • Rocket science is well….rocket science • Modern Rockets actually started from universities • Since then, governments have monopolized the field…..until recently • In 1999, Stanford professors started a startup SPG based on an old rocket technology they made commercially viable…..Hybrid Rocket Technology. • NASA is now fighting for its “space” • Space flight is now a venture capitalist away 45
- 46. Types of Rockets •3 types of rockets based on fuels • Solid Rocket Motor (SRM) • Liquid Rocket Engine 46
- 47. Hybrid Rocket Engines •Oxidizer is liquid and fuel is solid…mostly • So what’s so innovative? • Well, you can use anything as fuel: ▫ Rubber, wax, plastic and even your old Bata shoes 47
- 48. Advantages • Mechanically simpler,less plumbing, less parts • They are very safe (solid rockets tend to ) • They are throttlable, restart-able • They are very cost effective • Almost military application, therefore open to universities and private sector. • Still not fully saturated in terms of innovation • A hot ;) area of research, easily publishable. • A lot of customers (more on this later) 48
- 49. Hybrid Rockets atDSU 49 • Inspired by my background in Aerospace and SUPARCO, I convinced a group of junior students to design and manufacture Pakistan’s first hybrid rocket engine. • It is now their FYP. • It is reusable. Three test fires so far. • It is among about 20 rocketry programs in top world universities (MIT, Stanford, TU-M etc) • The 2nd Program in Asia!
- 50.
- 51. Business Oppurtunities 51 • Wehave in advanced negotiations with three venture capitalists for commercializing this technology • The current state of TR is at the technology demonstrator stage • Rocket Assisted Takeoff (RATO) is one application investors have taken keen interest in. • Another application is small satellite launch. Hybrids offer a very cheap and affordable way of reaching space and securing orbits (SUPARCO?)
- 52. Questions and CommentsWelcome 52 • Making science make money is rocket science, but we can do it through FYPs. • Entire project cost PKR 25K. We hacked a lot of university equipment to make ends meet. • Thank you for your patience. • We look forward to your questions.