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Brian Katz March 2014.  Space/Rocket Curriculum Goals ◦ Provide Information About Space, Science, Rocketry and Transportation Machines ◦ Stimulate Interest.

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Presentation on theme: "Brian Katz March 2014.  Space/Rocket Curriculum Goals ◦ Provide Information About Space, Science, Rocketry and Transportation Machines ◦ Stimulate Interest."— Presentation transcript:

1 Brian Katz March 2014

2  Space/Rocket Curriculum Goals ◦ Provide Information About Space, Science, Rocketry and Transportation Machines ◦ Stimulate Interest in School/Learning/Goals/Better One’s-Self ◦ Promote Open Discussions, Allow Students To Think, Express and Brainstorm ◦ Teach Students How To Follow Instructions and Complete a Project - working together as a team (Build and Possibly Launch a Rocket)  Sessions ◦ #1: History of Space Travel ◦ #2: Orbits and Gravity ◦ #3: General Rocketry ◦ #4: Rocket Design ◦ #5: Build Rocket(s) ◦ #6: Launch  Session Formats ◦ Imagery (online videos): “Fire and Smoke” ◦ Rocket building project and launch (rocket derby)

3  Goal ◦ Familiarize Students with the Fascinating History of Rocketry ◦ Talk about how to accomplish a “big” project – break it down into sub sections and accomplish piece by piece (Mercury/Gemini/Apollo)  See attachment 1: History of Space Travel Presentation – walk through this  Videos: ◦ ◦ ◦ ◦ ◦  Side topics/discussions: ◦ Balloons, Airplanes, Helicopters, Rockets – Why/How Do They Fly ◦ Emphasize Ingenuity/Motivation to Create  Digress – Find Their Interests, Search For Ideas, What Have they ever built, want to build, etc… ◦ Watch October Sky and Apollo 13

4  Goal: ◦ Instruct Students on where we are going – to space, what is space?  Discuss Orbit, Gravity and Atmosphere ◦ Orbit: What is an Orbit: Show Video With Canyon Ball: ◦ Gravity: a. Talk about how ideally, all masses fall to ground at same acceleration; discuss big rock/little rock when dropped will hit ground at the same time b. Talk about gravity around all planets/moons c. Discuss table of relative body weights on other planets ready d. Show video of Astronauts In Space Shuttle and explain that they are floating because they are FALLING!! Use dropping elevator scenario or the dropping airplane scenario ◦ Atmosphere: ◦ Talk about friction, rub hands together for younger kids Relative weights of objects on planets Mercury0.38 Venus0.91 Earth1 Mars0.38 Jupiter2.54 Saturn1.08 Uranus0.91 Neptune1.19 Pluto0.06 Moon0.6

5  Goal ◦ Instruct Students on General Rocketry – what are rockets, their uses, their operation principles  Basic Operation ◦ How/Why Rockets Fly – fire/smoke out the backend – equal and opposite reaction, payload upfront, separation of stages – why? ◦ Temperatures/Speeds/Materials ◦ Newton’s Laws (see next slide)  Digress – Talk about science, science laws and our world


7  1st Law (Inertia): ◦ “In the absence of contrary forces, the speed and direction of an object’s movement will remain constant.”  Explanation: The force generated by the escaping gasses from the rocket motor must be great enough to lift the rocket’s total mass from the launch pad, or it will not fly.  2nd Law (Acceleration): ◦ “A body that is subject to forces moves at a speed which is proportional to the amount of force applied.”  Explanation: The greater the force supplied by the rocket motor, in relation to the total mass of the rocket vehicle, the faster it will go.  3rd Law (Action/Reaction): ◦ “For every force action there is an equal and opposite reaction.”  Explanation: Release of gases through the nozzle (action) produces a force on the rocket (reaction) in the opposite direction, causing the rocket to accelerate.

8  From Newton’s 2nd Law (motion of the Rocket)-  Where:  F = force  m = mass  a = acceleration  The rocket motor’s total energy is called its total “Impulse” and is a measure of rocket motor’s overall performance-  Impulse is the sum (or integral) of total force imparted over the time it acts upon the rocket: or  Where:  F = force history profile  T = Total time

9  Goal: ◦ Dig in deep to rocket design - learn the major components and systems ◦ Discuss Design, Analysis, Test, Build  Discussion: ◦ Propulsion (Solid, Liquid) ◦ Fins – why do we need them ◦ Nose Cone – Aerodynamics and payload protection ◦ Nozzle – essence of the propulsion system ◦ Igniter – gets it all started  Operation ◦ How do we Maneuver Rockets ◦ Flight Termination ◦ Countdown/procedures  Show Rockets That Didn’t Make It Video ◦ ◦ What can we learn from this video?

10 By 1926, Goddard had constructed and tested successfully first rocket using liquid fuel on March 16,1926, at Auburn, Massachusetts. Rocket used cylindrical combustion chamber with impinging jets to mix and atomize liquid oxygen and gasoline The rocket, which was dubbed "Nell", rose just 41 feet during a 2.5-second flight that ended 184 feet away in a cabbage field US and German engineers quickly ran with this idea and greatly expanded on the technology

11 Liquid vs Solid Propulsion Systems

12  Turbo Machinery  Boost Pumps  Main Pumps  Injector  Igniter  Combustion Chamber  Nozzle  Heat Exchanger  Mixture and throttle Valves  Pneumatic actuation, pressurant, and purge systems

13  Rocket Equation Variables:  q = ejected mass flow rate  V e = exhaust gas ejection speed  P e = pressure of the exhaust gases at the nozzle exit  P a = pressure of the ambient atmosphere  A e = area of the nozzle exit  A t = throat area of the nozzle  m 0 = initial total mass, including propellant  m 1 = final total mass  v e = effective exhaust velocity  g o = Gravitational Constant  P c = Chamber Pressure  F (Thrust Vac ) = Force produced by the engine at 100% throttle in a vacuum environment  Δv = maximum change of velocity  Isp = Ratio of the thrust to the ejected mass flow rate used as the primary efficiency measure  C* (C-Star) = characteristic exhaust velocity term used as a primary engine development value

14 ◦ Major Components ◦ Injector ◦ Structural Jacket ◦ Coolant Liner ◦ Coolant Inlet Manifold ◦ Nozzle extension attachment  Design Considerations ◦ Oxidizer / Fuel Mixing ◦ Ignition ◦ Flame Holding ◦ Cooling ◦ Weight ◦ Manufacturability ◦ Engine Integration Combustion Chamber

15  Nozzle is Tightly Integrated with Combustion Chamber  Nozzle can be an awkward part of engine that makes packaging difficult ◦ Extendable Nozzles are complicated and expensive, (Delta 4 and Arianne upper stages are examples) ◦ Fixed nozzles are bulky and extend vehicle length, and increase re-contact risks  Nozzle Cooling is commonly Achieved by ◦ Ablative materials ◦ Regenerative cooling ◦ Film Cooling Nozzle

16  Hypergolic: fuels and oxidizers that ignite spontaneously on contact with each other and require no ignition source  Nitrogen Tetroxide (NTO, N2O4). red- fuming nitric acid  N2H4 - Hydrazine  UDMH – Unsymmetrical dimethyl hydrazine (Lunar lander RCS UDMH/N2O4)  Aerozine 50 (or "50-50"), which is a mixture of 50% UDMH and 50% hydrazine  MMH (CH3(NH)NH2) - Monomethylhydrazine  NTO/Aerozine 50 for Delta II second stage  NTO/MMH is used in the Shuttle OMS  opellants Propellants

17  Simplest of the Power Cycles  No turbo-machinery making it one step up in complexity over solid motors  Requires high pressure tank structure to provide sufficient inlet pressures  Common for hypergolic engines which also eliminates the need for an ignition source  Chamber pressures ~100 to 200 psi  AJ-10 uses NTO/A50 ◦ ISP Vac 271 Sec ◦ 7.5k lbs thrust  Space X Kestrel uses LOX/RP-1 ◦ ISP Vac 317 Sec ◦ 6.9k lbs of thrust Pressure Fed System

18 Engines are commonly tested at ground level, usually in vertical configuration or horizontal configuration with slight slant Upper stage engines are commonly testing in altitude chambers Exhaust gas flow detachment will occur in a grossly over-expanded nozzle. Thrust Vac : 750,000 lbf (3.3 MN) Burn Time: 470 s Design: Gas Generator cycle Specific impulse: 410 s Engine weight – dry: 14,762 lb (6696 kg) Height: 204 in (5.2 m) Diameter: 96 in (2.43 m) Overexpanded Optimum Underexpanded

19 Ground systems for liquid rockets are commonly more complex than the rocket itself Atlas V pad has accommodations for LOX, RP, H2, N2, and He Extensive plumbing, tanking and de- tanking capabilities Electrical control to ensure proper filling and top-off Significant leak, thermal, flammability, oxygen deficiency and explosive concerns Day of launch operations are extensive and very dynamic during preparation, fueling, monitoring, top-off, startup verification, liftoff disconnects, and possible shutdown and de-tanking operations vs Liquid Propulsion Solid Propulsion

20 Atlas VDelta IV HeavyDelta IIFalcon 9Antares o Discuss: - Vastness of these engineering marvels – as tall as a 10 – 20 story building - Attention to detail, ask questions, learn, communicate with each other

21 Convert chemical energy to heat ==>> Movement of heated gases ==> Energy of motion (Burning Propellant) (through Nozzle exit) (Imparted Force) Cut-away view of a typical Rocket Motor Propellant Ignitor Exhaust Nozzle Motor Case o Discuss: - Solid Propellant details - Concept of ground testing – why?

22  Flight Computer  Guidance/Navigation and Control  Electrical Power  Thrust Vector Control  RF o Discuss: - There are lots of different types of engineers who work with rockets – we work as a team

23 Flight Termination Payload Separation Stage Separation o Discuss: - Why Do we need Flight Termination? - Why Do we need separation mechanisms?

24  Goal: ◦ Build Rockets/team work/follow instructions – team work  Build Ideas: ◦ Students Read Out loud Instructions ◦ Students Initial Steps Complete ◦ Students Perform Quality Inspections  Launch Ideas: ◦ Create Launch Countdown Checklist and Have various students perform duties  Test Conductor  Pad Chief  Range Safety Officer  Counter

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