000			14626cam a2200397 i 4500
005			20221102172110.0
008			110626s2012 gw a b 001 0 eng d
011			_aBIB MATCHES WORLDCAT
020			_a3642225365
020			_a9783642225369
035			_a(ATU)b12489621
035			_a(OCoLC)733249494
040			_aBTCTA _beng _erda _cBTCTA _dUKMGB _dYDXCP _dTJC _dATU
050		4	_aTL545 _b.A43 2012
082	0	4	_a629.1 _223
100	1		_aAlber, Irwin E., _eauthor. _91094531
245	1	0	_aAerospace engineering on the back of an envelope / _cIrwin E. Alber.
264		1	_aHeidelberg : _bSpringer ; _aChichester, UK : _bPublished in association with Praxis Publishing, _c2012.
300			_axix, 326 pages : _billustrations ; _c25 cm.
336			_atext _btxt _2rdacontent
337			_aunmediated _bn _2rdamedia
338			_avolume _bnc _2rdacarrier
490	1		_aSpringer-Praxis books in astronautical engineering
504			_aIncludes bibliographical references and index.
505	0		_a1. Introduction -- 2. Design of a high school science-fair electro-mechanical robot -- 3. Estimating Shuttle launch, orbit, and payload magnitudes -- 4. Columbia Shuttle accident analysis with Back-of-the-Envelope methods -- 5. Estimating the Orbiter reentry trajectory and the associated peak heating rates -- 6. Estimating the dimensions and performance of the Hubble Space Telescope -- --
505	0	0	_g1. _tIntroduction -- _g1.1. _tWhy Back-of-the-Envelope engineering? -- _g1.1.1. _tBack-of-the-Envelope engineering; an important adaptation and survival skill for students and practicing engineers -- _g1.1.2. _tDesign of a high school science fair electro-mechanical robot -- _g1.1.3. _tDesign of a new commercial rocket launch vehicle for a senior engineering student's design project -- _g1.1.4. _tPreliminary design of a new telescope system by an engineer transferred to a new optical project -- _g1.1.5. _tExamining the principles and ideas behind Back-of-the- Envelope estimation -- _g1.2. _tWhat is a Back-of-the-Envelope engineering estimate? -- _g1.2.1. _tTradeoffbetween complexity and accuracy -- _g1.2.2. _tBack-of-the-Envelope reasoning -- _g1.2.3. _tFermi problems -- _g1.2.4. _tAn engineering Fermi problem -- _g1.3. _tGeneral guidelines for building a good engineering model -- _g1.3.1. _tStep by step towards estimation -- _g1.3.2. _tQuick-Fire estimates -- _g1.4. _tQuick-Fire estimate of cargo mass delivered to orbit by the Space Shuttle -- _g1.4.1. _tCargo mass problem definition -- _g1.4.2. _tLevel-0 estimate: the empirical ''rule of thumb'' model -- _g1.4.3. _tLevel-1 estimate: cargo mass using a single stage mathematical model based on the ideal rocket velocity equation -- _g1.4.4. _tLevel-2 estimate: cargo mass using a two stage vehicle model based on the ideal rocket velocity equation -- _g1.4.5. _tLevel-3 estimate: cargo mass delivered by a two stage vehicle; based on a revised estimate for second stage structural mass fraction -- _g1.4.6. _tImpact of added knowledge and degree of model complexity -- _g1.4.7. _tMoving from the Shuttle to the Hubble Space Telescope -- _g1.5. _tEstimating the size of the optical system for the Hubble Space Telescope -- _g1.5.1. _tSystem requirements for the HST -- _g1.5.2. _tShuttle constraint on HST size -- _g1.5.3. _tEstimating the length of the HST optical package -- _g1.6. _tConcluding remarks -- _g1.7. _tOutline of this book -- _g1.8. _tReferences -- _g2. _tDesign of a high school science-fair electro-mechanical robot -- _g2.1. _tThe Robot-Kicker Science Fair Project -- _g2.2. _tBack-of-the-Envelope model and analysis for a solenoid kicking device -- _g2.2.1. _tDefining basic dimensions and required soccer ball velocity -- _g2.2.2. _tSetting up a Bot Emodel for the solenoid kicking soccer ball problem -- _g2.2.3. _tModel for solenoid kicker work and force -- _g2.2.4. _tFinal design requirements for linear-actuator solenoid and supporting electrical system -- _g2.3. _tAppendix: Modeling of the temperature rise produced by ohmic heating from single or multiple solenoid-actuator kicks -- _g2.3.1. _tQuick-Fire problem approach -- _g2.3.2. _tProblem definition and sketch -- _g2.3.3. _tThe baseline mathematical model -- _g2.3.4. _tPhysical parameters and data -- _g2.3.5. _tNumerical results -- _g2.3.6. _tInterpretation of results -- _g2.4. _tReferences -- _g3. _tEstimating Shuttle launch, orbit, and payload magnitudes -- _g3.1. _tIntroduction -- _g3.1.1. _tEarly Space Shuttle goals and the design phase -- _g3.1.2. _tThe Shuttle testing philosophy and the need for modeling -- _g3.1.3. _tBack-of-the-Envelope analysis of Shuttle launch, orbit, and payload magnitudes -- _g3.2. _tShuttle launch, orbit, and reentry basics -- _g3.2.1. _tThe liftoffto orbit sequence -- _g3.2.2. _tReentry -- _g3.3. _tInventory of the Shuttle's mass and thrust as input to the calculation of burnout velocity -- _g3.3.1. _tBurnout velocity -- _g3.3.2. _tThe velocity budget -- _g3.3.3. _tMass inventory -- _g3.3.4. _tThrust and specific impulse inventory -- _g3.4. _tMass fraction rules of thumb -- _g3.5. _tQuick-Fire modeling of the takeoffmass components and takeoffthrust using SMAD rules of thumb -- _g3.5.1. _tQuick-Fire problem approach -- _g3.5.2. _tProblem definition and sketch -- _g3.5.3. _tMathematical/''Rule of Thumb'' empirical models -- _g3.5.4. _tPhysical parameters and data -- _g3.5.5. _tNumerical calculation of total takeoffmass, cargo bay mass, and total takeoffthrust -- _g3.5.6. _tInterpretation of the Quick-Fire results -- _g3.5.7. _tFrom Quick-Fire estimates to Shuttle solutions using more accurate inputs -- _g3.6. _tIdeal velocity change Dv for each stage of an ideal rocket system -- _g3.6.1. _tPropellant mass versus time -- _g3.6.2. _tTime varying velocity change -- _g3.6.3. _tEffective burnout time and average flow rate -- _g3.6.4. _tIdeal altitude or height for each rocket stage -- _g3.7. _tDvideal estimate for Shuttle first stage, without gravity loss -- _g3.7.1. _tEstimate of SSME propellant mass burned during first stage -- _g3.7.2. _tFirst stage mass ratio and average effective exhaust velocity -- _g3.7.3. _tAverage specific impulse for the ''parallel'' (solidþliquid) first stage burn -- _g3.7.4. _tDvideal estimate for Shuttle first stage -- _g3.7.5. _tDvideal and altitude as functions of time, for the Shuttle first stage -- _g3.8. _tThe effect of gravity on velocity during first stage flight -- _g3.8.1. _tModeling the effects of gravity for a curved flight trajectory -- _g3.8.2. _tTime-varying pitch angle model -- _g3.8.3. _tEffect of gravity on rocket velocity during first stage flight -- _g3.8.4. _tEffect of gravity on rocket height during first stage flight -- _g3.8.5. _tComparing model velocity and altitude with Shuttle data -- _g3.8.6. _tGravity loss magnitudes for previously flown launch systems -- _g3.8.7. _tModel velocity, with gravity loss, compared with flight data -- _g3.8.8. _tCalculation of gravity-loss corrected velocity at first stage burnout -- _g3.9. _tThe effect of drag on Shuttle velocity at end of first stage flight -- _g3.9.1. _tModeling the effects of drag in the equation of motion -- _g3.9.2. _tEstimating first stage drag loss -- _g3.9.3. _tFinal drag and gravity-corrected velocity at first stage burnout; key elements of the overall ''velocity budget'' for the first stage -- _g3.10. _tCalculation of second stage velocities and gravity losses -- _g3.10.1. _tPitch and gravity loss modeling for the second stage flight period -- _g3.10.2. _tTime-varying gravity loss solution, region 2a -- _g3.10.3. _tTime-varying velocity solution, region 2b -- _g3.10.4. _tCombined velocity solution for regions1, 2a, and 2b and v(MECO) -- _g3.11. _tSummary of predicted Dv budget for the Shuttle -- _g3.12. _tComparison of Back-of-the-Envelope modeled Shuttle velocity and altitude as a function of time to NASA's numerical prediction for all stages -- _g3.12.1. _tComparison of model velocity with NASA's numerical prediction -- _g3.12.2. _tComparison of model altitude with NASA's numerical prediction -- _g3.12.3. _tModeled altitude sensitivity to pitch time scale -- _g3.13. _tEstimating mission orbital velocity requirements for the Shuttle -- _g3.13.1. _tPart1: circular orbital velocity -- _g3.13.2. _tPart2: elliptical orbits and the Hohmann transfer Dv's -- _g3.13.3. _tNumerical values for transfer orbit Dv's -- _g3.13.4. _tTime of flight for a Hohmann transfer -- _g3.13.5. _tDirect insertion to a final orbital altitude (without using a parking orbit) -- _g3.14. _tA Back-of-the-Envelope model to determine Shuttle payload as a function of orbit altitude -- _g3.14.1. _tAnalytic model for payload as a function of orbital altitude -- _g3.14.2. _tApproximate linearized solution for payload -- _g3.14.3. _tReduction in useful cargo mass due to increases in OMS propellant mass -- _g3.14.4. _tOMS models for correcting cargo or payload mass -- _g3.14.5. _tModel for rate of change of ''useful cargo'' with altitude -- _g3.14.6. _tApproximate analytic model for useful cargo -- _g3.14.7. _tModeling missions to the International Space Station -- _g3.15. _tTabulated summary of Back-of-the-Envelope equations and numerical results -- _g3.16. _tReferences --
505	0	0	_g4. _tColumbia Shuttle accident analysis with Back-of-the-Envelope methods -- _g4.1. _tThe Columbia accident and Back-of-the-Envelope analysis -- _g4.1.1. _tBot Emodeling goals for the Columbia accident -- _g4.1.2. _tQuick estimation vs accurate estimation -- _g4.2. _tQuick-Fire modeling of the impact velocity of a piece of foam striking the Orbiter wing -- _g4.2.1. _tInterpretation of Quick-Fire results -- _g4.2.2. _tThe bridge to more accurate Bot Eresults -- _g4.3. _tModeling the impact velocity of a piece of foam debris relative to the Orbiter wing; estimations beyond the Quick-Fire time results -- _g4.3.1. _tLooking at the collision from an earth-fixed or moving Shuttle coordinate system -- _g4.3.2. _tThe constant drag approximation -- _g4.3.3. _tAnalytically solving for the impact velocity and mass, given the time to impact -- _g4.3.4. _tSummary of results for constant acceleration model compared to data -- _g4.3.5. _tThe non-constant acceleration solution -- _g4.3.6. _tAn estimate of impact velocity and particle mass, taking the time to impact as given (the ''inverse'' problem) -- _g4.3.7. _tComparing Osheroff 's ''inverse'' calculations to our ''direct'' estimate results -- _g4.3.8. _tConcluding thoughts on the impact velocity estimate -- _g4.4. _tModeling the impact pressure and load caused by impact of foam debris with an RCC wing panel -- _g4.4.1. _tThe impact load -- _g4.4.2. _tImpact overview -- _g4.4.3. _tImpact load mathematical modeling -- _g4.4.4. _tElastic model for the impact stress -- _g4.4.5. _tElastic-plastic impact of a one-dimensional rod against a rigid-wall -- _g4.4.6. _tThe elastic-plastic model -- _g4.4.7. _tNumerical results and plotted trends -- _g4.4.8. _tImpact area estimate -- _g4.4.9. _tLoad estimate -- _g4.4.10. _tImpact loading time scale (Bot E) -- _g4.4.11. _tLoading time histories, numerical simulations -- _g4.5. _tDevelop a Back-of-the-Envelope engineering stress equation for the maximum stress in the RCC panel face for a given panel load -- _g4.5.1. _tBot Epanel stress model -- _g4.5.2. _tEstimates for the allowable maximum stress or critical load parameters for failure -- _g4.5.3. _tFinal comments on the prediction of possible wing damage or failure -- _g4.6. _tSummary of results for Sections 4.2, 4.3, and 4.4 -- _g4.7. _tReferences -- _g5. _tEstimating the Orbiter reentry trajectory and the associated peak heating rates -- _g5.1. _tIntroduction -- _g5.2. _tThe deorbit and reentry sequence -- _g5.3. _tUsing Quick-Fire methods to crudely estimate peak heating rate and total heat loads from the initial Orbiter kinetic energy -- _g5.3.1. _tQuick-Fire problem definition and sketch -- _g5.3.2. _tThe Quick-Fire baseline mathematical model, initial results, and interpretation -- _g5.4. _tAlook at heat flux prediction levels based on an analytical model for blunt-body heating -- _g5.4.1. _tNumerical estimates of Stanton number using the Sutton- Graves constant -- _g5.5. _tSimple flight trajectory model -- _g5.5.1. _tAsimple Bot Emodel for the initial entry period; the entry solution -- _g5.5.2. _tThe equilibrium glide model -- _g5.6. _tCalculating heat transfer rates in the peak heating region -- _g5.6.1. _tSelecting the nose radius -- _g5.6.2. _tComparing the model maximum rate of heat transfer, q_wmax , with data -- _g5.6.3. _tModel estimate for nose radiation equilibrium temperature, Tmax -- _g5.6.4. _tModel calculations of q_w as a function of time -- _g5.6.5. _tModel calculations for total heat load at the stagnation point -- _g5.7. _tAppendix: Bot Emodeling of non-Orbiter entry problems -- _g5.8. _tReferences -- _g6. _tEstimating the dimensions and performance of the Hubble Space Telescope -- _g6.1. _tThe Hubble Space Telescope -- _g6.1.1. _tHST system requirements -- _g6.1.2. _tHST engineering systems -- _g6.1.3. _tRequirements for fitting the HST into the Orbiter -- _g6.2. _tThe HST Optical Telescope design -- _g6.2.1. _tThe equivalent system focal length -- _g6.2.2. _tHow do designers determine the required system focal ratio, Feq? -- _g6.2.3. _tTelescope plate scale -- _g6.2.4. _tSelection of HST's primary mirror focal ratio, F 1 1/4 jf1j=D -- _g6.2.5. _tCalculating the magnification m and exact constructional length L -- _g6.2.6. _tEstimating the secondary mirror diameter -- _g6.2.7. _tEstimating the radius of curvature of the HST secondary mirror -- _g6.3. _tModeling the HST length -- _g6.3.1. _tThe light-shield baffle extension -- _g6.3.2. _tModeling the length of the light shield -- _g6.3.3. _tThe length of the instrument section -- _g6.3.4. _tCalculating the total HST telescope length -- _g6.4. _tSummary of calculated HST dimensions -- _g6.5. _tEstimating HST mass -- _g6.5.1. _tPrimary mirror design -- _g6.5.2. _tEstimating primary mirror mass -- _g6.5.3. _tThe estimated total HST system mass and areal density -- _g6.5.4. _tSome final words on the HST mass estimation exercise -- _g6.5.5. _tOnward to an estimate of HST's sensitivity -- _g6.6. _tBack-of-the-Envelope modeling of the HST's sensitivity or signal to noise ratio -- _g6.6.1. _tDefining signal to noise ratio -- _g6.6.2. _tModeling the mean signal, S -- _g6.6.3. _tModeling the noise -- _g6.6.4. _tFinal equation for signal to noise ratio -- _g6.6.5. _tFinal thoughts on Bot Eestimates for HST sensitivity -- _g6.7. _tReferences.
588			_aMachine converted from AACR2 source record.
650		0	_aAerospace engineering _9328467
650		0	_aEngineering design. _9317331
830		0	_aSpringer-Praxis books in astronautical engineering. _91082775
907			_a.b12489621 _b06-09-21 _c28-10-15
942			_cB
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