l1_lDavid Miller

l1_lDavid Miller - LAUNCH SYSTEMS Col. John Keesee 5...

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LAUNCH SYSTEMS Col. John Keesee 5 September 2003
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Outline • Launch systems characteristics • Launch systems selection process • Spacecraft design envelope & environments.
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Lesson Objectives • Each student will • Understand launch system characteristics, sizing and trade-offs. • Estimate launch system sizes, staging requirements. • Be able to select appropriate launch system for a given mission from available systems. • Be able to estimate spacecraft requirements driven by launch vehicle induced environments. • Determine costs of launch systems.
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Rocket Basics Thrust Specific impulse where K depends on J and the engine pressure ratio ) ( f 0 . p e p e A e V e m F M c T K Isp g m F Isp { m e V e P e A e f p Fuel in Oxidizer in Thrust p c Throat
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Rocket Equation Where is the mass ratio (Assumes zero losses due to drag and gravity) t m o M veh M g veh M Isp m veh M F a & 0 ' V adt Isp g ³ dm dt dt M o 0 dm d t t t o t f ³ ¸ ¸ ¹ · ¨ ¨ © § ¸ ¸ ¸ ¸ ¸ ¸ ¸ ¹ · ¨ ¨ ¨ ¨ ¨ ¨ ¨ © § ¸ ¸ ¸ ¸ ¸ ¸ ¸ ¹ · ¨ ¨ ¨ ¨ ¨ ¨ ¨ © § 0 ' R n Isp g f M o M n Isp g propellant M o M o M n Isp g V # # # R M o M f
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Rocket Equation (Cont.) M p M f e ' V Isp g §# ©# ¨# ¨# ¨# ¨# ¨# ¨# ¨# ¨# ¨# ·# ¹# ¸# ¸# ¸# ¸# ¸# ¸# ¸# ¸# ¸# 0 1 ª# ¬# «# «# «# «# «# «# «# º# ¼# »# »# »# »# »# »# »# M o 1 0 e 0' V / Isp g §# ©# ¨# ¨# ¨# ¨# ¨# ¨# ·# ¹# ¸# ¸# ¸# ¸# ¸# ¸# ª# ¬# «# «# «# «# «# º# ¼# »# »# »# »# »# M p = mass of propellant M o = initial mass M f = final mass ' V = vehicle velocity change M veh = vehicle mass
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Staging • Near burnout, rocket acceleration is diminished because payload mass includes entire launch systems structure. • Staging removes lower stage structural weight M oi = initial mass of rocket including all upper stages and payload. M
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This note was uploaded on 11/08/2011 for the course AERO 16.851 taught by Professor Ldavidmiller during the Fall '03 term at MIT.

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l1_lDavid Miller - LAUNCH SYSTEMS Col. John Keesee 5...

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