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Rocket E ngine:
Lander ISP = (ISP − 3) s
= 460 − 3
= 457 s
Landing vEXH = Landing ISP · g0
= (457)(9.806650
= 4, 482 mps
Landing Δv Budget = P DI + P AI
= 2181 + 1890
= 4, 071 mps
Landing Reserve Δv = 0.75% · Landing Δv Budget
= 0.0075(4071)
= 31 mps
Landing Δv = Landing Δv Budget + Landing Reserve Δv
= 4071 + 31
= 4, 102 mps
Lunar M aterial:
Lunar M aterial = Science P ayload − P ayload T ray
= 4761 − 680
= 4, 081 kg
Propellant:
m1 = 2, 545 + CM + Lunar M aterial + P ayload T ray + Lander Kit
= 2545 + 4327 + 4081 + 680 + 406
= 12, 057 kg
Landing Δv
LanderP ROP ELLANT = m ( e1 Landing vEXH − 1)
= (12057)(e 4102 − 1)
4482
= 18, 052 kg
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Excess Landing P ropellant = P ropellant − LanderP ROP ELLANT
= 18053 − 18052
= 1 kg
Gross Mass:
m0 = m1 + Landing P ropellant
= 12057 + 18052
= 30, 108 kg
Financial:
Gross Income = Lunar M aterial · Selling P rice
= 4081 · 7500000
= $30, 604, 579, 769 U SD
T axable Income = Gross Income − Lunar Investment
= 30604579796 − 27140000000
= $3, 464, 579, 796 U SD
R.O.I . = ( T axable I ncome x 100)%
Lunar I nvestment
= 3464579796 x 100
27140000000
= 12.77%
::
So, in c onclusion,
● Propellant Needed: 18,052 k g
● Lunar M aterial: 4,081 kg
● Lunar Lander G ross W eight: 3 0,108 k g
● Gross Income: $30,604,579,976 USD
● Taxable I ncome: $ 3,464,579,976 U SD
● R.O.I: 12.77%
::
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8.04 Guided P ractice
You are a n spacecraft C aptain r esponsible to t ransport p assengers t o a nother space s tation. Use
the Boeing L unar L ander E quation t o d etermine t he parameters of y our s paceflight.
Mission Scenario #1
TEI O rbital A ltitude: 284 km
EOI O rbital A ltitude: 284 k m
Average Selling P rice: 3 00/carat USD
Output
Lander Gross Mass = _ _________ lbs
Propellant Mass = __________ l bs
Excess Propellant = _ _________ l bs
LH 2 Mass = __________ l bs
LO2 M ass = _ _________ lbs
Lunar Material Mass = _ _________ l bs
Gross Income = __________ lbs
Net Income = _ _________ lbs
Return On I nvestment = _ _________ %
::
Mission S cenario #2
TEI Orbital Altitude: 5 00 k m
EOI Orbital A ltitude: 500 km
Average Selling P rice: 1 50/carat USD
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Output
Lander G ross M ass = __________ l bs
Propellant Mass = __________ l bs
Excess P ropellant = __________ lbs
LH2 Mass = __________ lbs
LO 2 Mass = _ _________ l bs
Lunar M aterial Mass = _ _________ lbs
Gross I ncome = _ _________ lbs
Net I ncome = __________ lbs
Return On I nvestment = __________ %
::
8.05 C ross Curricular Exercises
ARTWORK
Find images of a crew capsule such as the Boeing CST–100 or the SpaceX Dragon on the
Internet. Use the images that you have researched to draw a picture of the spaceplane rocketing
into orbit.
R.A.F.T. WRITING
● Ro le: T eacher
● Au dience: M iddle School s tudents
● Fo rmat: F ive p aragraph e ssay
● T opic: The Apollo Lunar Module (LM). Who were the astronauts that flew the missions?
Where on the Moon did they land? What was unique about their missions? What was in
common with all the missions? How does an Apollo space mission differ from the space
mission presented in this textbook? How are they the same? Why even bother to explore
the M oon a nyway?
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DISCUSSION TOPICS
● Was the mathematics in this c hapter difficult t o understand?
● The a uthors conclude that the S pace T ug w ould make a n excellent Lunar L ander. D o y ou
agree with the a uthors? W hy or W hy n ot?
● What w ould i t b e l ike t o fly aboard a r ocket t hat h as landed on the M oon? W ould you fly
on the Boeing Lunar Lander? Why o r w hy n ot?
8.06 Engine Module Space Mission D esign Website
We n ow p roceed to c reate the s uborbital w ebsite t hat i ncludes t he e ngineering logs and the app
embedded i n a webpage.
INSERT T EXT HERE
INSERT TEXT HERE
::
8.07 Engine Module Space M ission Design S preadsheet App
Given the above information, we can use a spreadsheet to enter equations and data to create a
Space Mission Design A pp (SMDA).
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The S .T.E.M. for the Classroom/Google A pp is b roken down i nto four ( 4) p arts:
1. Input/Output I nterface
2. Graph
3. Constants
4. Calculations
The App can n ow be d eveloped.
Sample Open S ource Code
Once t he cells h ave b een named referencing cells i s e asy.
● CALCULATIONS
○ TotBA
I NSERT C ODE HERE
I NSERT C ODE HERE
::
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Sample A pp Interface
Image 46: L unar L ander D esign Spreadsheet A pp
8.08 L unar Lander Design M obile App Page 1 49 o f 176
Sample A ppSheet Mobile A pp D esign O pen Source Code
S.T.E.M. F or the Classroom
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Once t he G oogle S preadsheet has b een completed, i t c an b e used to h elp create t he mobile a pp.
I NSERT CODE HERE
I NSERT C ODE HERE
Sample AppSheet M obile A pp D esign
Image 47: Lunar Lander D esign M obile A pp
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8.09 L unar L ander Design Presentation D evelopment
INSERT T EXT H ERE
INSERT TEXT HERE
INSERT TEXT HERE
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8.10 C hapter T est
I. VOCABULARY
Match the a stronautics term w ith i ts d efinition.
1. Lunar I nvestment A. The amount of money needed to fully fund a mission
to the M oon.
2 . Lunar Lander K it B. Includes the lunar landing legs, infrastructure,
landing r adar, etc.
3 . L unar P ayload T ray C. The tray that transports payload to and from the lunar
surface.
4. P owered A scent I nitiation D. T he l ift o ff burn from the lunar s urface t o l unar orbit.
5 . Powered Descent I nitiation E. The landing burn from lunar orbit to the lunar
surface.
II. M ULTIPLE CHOICE
Circle the correct answer.
6 . T he p ropellant n eeded to l and o n t he M oon is equal to the p ropellant n eeded to take o ff
A. T RUE B. F ALSE
7. The ΔV Budget for a landing on the moon is just as much as going from the Earth to the
Moon.
A. T RUE B. FALSE
8. Collectors can purchase Lunar Material in the form of ________________ that has fallen to
Earth.
A. M eteors B. M eteorites C. Regolith D. C annot be d etermined
9. Lunar Material that has been brought back to Earth and sold for $1,000/carat has the
equivalent price of ___________ /gram.
A. $1,000 B. $5,000 C. 10,000 D. C annot b e d etermined
10. By retracting the nozzle of the RL10 rocket engine, the Specific Impulse (IS P) of the engine
decreases b y approximately _ ________ s econds.
A. T wo (2) B. T hree ( 3) C. Z ero ( 0) D. C annot be determined
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III. CALCULATIONS
You have invested $22.35B (USD) in a trip to the Moon. A Boeing Lunar Lander is to be used to
deposit geologic sensors on its surface, and to load the equivalent mass in Lunar Material to be
sold to pay for the trip. The payload for this mission is a standard 10Crew CM, and a standard
Lunar S ensor P ackage, which h as a mass o f 9,500 lbs. A ssume a s elling price o f $1,500/carat.
11. W hat i s t he n ew Specific Impulse of t he r ocket e ngine with t he r ocket nozzle r etracted?
12. W hat i s t he E xhaust V elocity (VE XH) of t he rocket engine?
13. W hat i s the w eight of t he P ropellant R eserve i n S.I. units?
14 . W hat i s t he mission payload in S .I. u nits?
15. What is t he E mpty Weight ( m1 ) o f t he l unar l ander?
16. W hat i s the Gross W eight ( m0 ) o f the lunar l ander?
17. What i s t he amount o f propellant n eeded f or t his Moon landing m ission?
18. W hat i s the a mount of Lunar M aterial in c arats?
19. What i s t he Gross Income from t he Lunar I nvestment?
20. W hat is the T axable Income f rom the L unar Investment?
IV. WRITING
Write a one p aragraph essay on the t opics b elow.
21. Explain why i t i s as d ifficult t o g et into and out o f t he Moon’s g ravity well as i t is t o fly t o the
Moon from L ow Earth O rbit.
22. Explain w hy creating a L unar l ander Kit to be a ttached to a B oeing Space T ug i s e asier a nd
more c ost effective t han d esigning and building a s eparate l anding vehicle.
23. E xplain w hy L unar Material would be a r are commodity if mined and t ransported back t o
Earth and sold o n t he o pen m arket.
24. E xplain how t o c alculate how m uch a n o bject would w eigh o n the lunar surface.
25. Write a short story about what it would feel like to land on the Moon and walk on its surface,
experiencing t he onesixth gravity of t he l unar environment.
END O F C HAPTER 8 E XAM
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END SPRING S EMESTER
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APPENDIX
COMING SOON . ..
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COMING S OON...
::
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ANSWERS TO P ROBLEM S ETS
COMING S OON...
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COMING SOON...
::
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GLOSSARY
Above G round L evel (AGL): The d istance a s pacecraft is a bove t he g round.
Adjacent Side o f a Right T riangle: The side next t o the g iven angle (not t he Hypotenuse).
Altitude: The distance a s pacecraft is a bove a g iven p oint.
Apoapsis: T he highest point i n an elliptical o rbit.
Apoapsis ΔV Burn : T he r ocket firing a t the h ighest p oint of a Transfer Orbit.
BA330 Module: A B igelow h abitat module t hat has a p ressurized v olume of 330 c ubic meters,
weighs 25 tonnes, and can h old 6 c rew.
BA330 S tack: Two BA300s a ttached t o a F alcon H eavy t hat i s o n the L aunch Pad.
BA2100 M odule : A B igelow h abitat m odule t hat has a p ressurized volume of 2,100 c ubic
meters, weighs 1 00 t onnes, a nd can h old 1 6 c rew.
BA2100 Stack: A B A2100 attached to a SLSI that is on the Launch Pad.
Begin Spaceflight : The m oment a spacecraft c rosses into space. U ntil this moment the spacecraft
has been t ravelling in t he atmosphere.
Begin Weightlessness : The moment after R ocket Burnout, when f orces due to a cceleration cease.
Boost P hase: The second o f s ix p hases i n a p arabolic s paceflight, where the r ocket e ngine is
turned o n f or maximum velocity.
Carrier Phase: The f irst of six phases in a p arabolic spaceflight, w here t he parabolic spacecraft
is carried to l aunch altitude.
Circular Orbit: A n o rbit t hat takes the s hape of a c ircle.
CM C ommunications: T he CM T V, a udio, a ntenna, e tc.
CM Contingency: T he C M emergency supplies.
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CM Controls: The C M R CS, E xpendables, c ontrols, lines, e tc.
CM C rew S ystems : T he C M B unks, seats, f ood, medical, etc.
CM D ynamic Mass : The weight o f the CM c omponents that v aries with the Mission D uration.
CM EC/LSS: T he C M Environmental C ontrol/Life S upport Systems. Cabin p ressure,
atmosphere, w ater, e tc.
CM E lectrical P ower: T he C M batteries, r egulators, j unction boxes, w ires, c ables, e tc.
CM Expendables: The CM Reaction Control S ystems p ropellant.
CM Instrumentation: T he C M d isplays, c ontrols, wiring, l ighting, etc.
CM M iscellaneous E quipment : T he CM m anipulator arms, displays and controls, m aintenance
equipment, etc.
CM S tatic Mass: The w eight of the CM components t hat d oes not vary with t he Mission
Duration.
CM S tructure : The CM s hell, m icrometeoroid shielding, insulation, r adiators, etc.
CM Crew/Volume R atio: T he volume t hat one astronaut occupies d uring a s pace m ission.
CM W eight : The sum o f t he C M Static and C M D ynamic W eights.
Crew Capsule : A s pacecraft, s uch a s the Boeing CST100, t hat i s u sed t o ferry c rew to a nd from
a space station.
Crew M odule (CM): The p art o f the spacecraft where the astronauts live and work.
Crew S ize: T he n umber o f astronauts a board a spacecraft or s pace station.
Crew V olume: The total p ressurized volume f or e ach c rew m ember.
Delta V ( Δv): T he change in v elocity required t o g o from one orbital a ltitude t o another.
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Δv B udget: T he t otal a mount of D elta V (ΔV) n eeded t o a ccomplish a space mission.
Descent Rate: T he d istance a s pacecraft descends o ver a c ertain period o f t ime.
Distance F rom S paceport : The ground distance from the edge o f t he r unway t o t he s pacecraft.
Docking N ode (DN) : A module t hat a llows C rew C apsules and Bigelow m odules t o b e a ttached
together.
Drop : R eleasing S paceShipTwo from t he m other ship. SpaceShipTwo t hen f alls a way to a safe
distance b efore igniting its r ocket e ngine.
Elliptical Orbit: A n orbit t hat takes t he s hape o f a n e llipse.
EM Empty W eight (M 1) : The w eight of t he s pacecraft f ully l oad e xcluding p ropellant.
EM Gross W eight ( M0 ) : T he weight of the spacecraft fully loaded i ncluding propellant.
EM I nert Weight: T he weight of the Engine Module without p ropellant a nd payload.
End S paceflight : T he moment a s pacecraft e xits from space. The s pacecraft returns to t he
atmospheric environment.
End Weightlessness : The moment a t R eentry Interface, w here t he s pacecraft b egins to slow
down a nd g ravity r eturns.
Engine Module ( EM): T he p art o f a s pacecraft t hat holds t he propellant t anks a nd t he rocket
engine.
Exhaust V elocity (v exh ): T he v elocity o f t he e scaping gas e xiting a rocket.
Expendable Launch Vehicle ( ELV): A vehicle that c arries i ts p ayload into space and is then
thrown a way, never t o be used a gain.
Falcon Heavy: An ELV f rom S paceX that c an l ift 53 mT i nto L ow E arth Orbit.
Glide Angle: T he angle f rom t he vertical that a L anding Laser points.
Glide D istance: The d istance t he L anding Laser m easures.
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Glide P hase : T he f ifth o f six p hases in a parabolic spaceflight, w here the s pacecraft r eturns t o
the launch site i n an u npowered l anding.
Glide Slope: T he angle a spacecraft m akes to t he horizontal.
Glide Speed: The s peed of the spacecraft during t he unpowered g lide landing.
Ground S peed: The s peed of t he s pacecraft as r elated to t he g round.
Higher Orbital Altitude : The h ighest a ltitude above M ean Sea L evel of an o rbiting b ody.
Hohmann T ransfer O rbit: T he path taken to either r aise o r l ower a n orbital a ltitude.
Hypotenuse of a Right T riangle: T he longest s ide of a right t riangle.
International S pace Station (I.S.S): The space s tation currently orbiting the earth; it is at a n
average orbital a ltitude o f 3 82 km (237 m i) with a n Orbital I nclination o f 52 d egrees.
Landing Laser: The l aser used t o determine the G lide D istance to a spacecraft.
Landing Profile: T he g raph of a landing spacecraft.
Latitude: The n umber o f d egrees above (or b elow) t he e quator.
Launch Pad: W here a rocket t akes off.
Launch S ite: The spaceport where the S kylon spaceplane launches a nd r ecovers.
Launch S ite Latitude: The l atitude ( measured i n degrees) of t he launch site.
LineOfSight D istance: The G lide Distance c onverted t o S.I. units.
Liquid H ydrogen ( LH2 ) : W hat a rocket engine u ses as fuel.
Liquid O xygen ( LO2 ) : What a r ocket e ngine u ses as an oxidizer.
Low E arth O rbit (LEO) : A b ody c ircling the Earth a t a minimum orbital altitude o f 1 85 k m (115
mi).
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Lower O rbital A ltitude: The lowest altitude above M ean S ea Level of an o rbiting b ody.
Lunar Investment : The a mount of m oney n eeded t o f ully fund a mission to the M oon.
Lunar Lander K it : Includes the l unar landing legs, infrastructure, landing radar, e tc.
Lunar Material: The rocks and d irt t hat is b rought b ack from the M oon and sold.
Lunar Payload T ray: T he t ray t hat transports payload t o a nd from the l unar s urface.
Maximum Altitude: The highest point that a spacecraft reaches during a parabolic spaceflight.
Mean S ea Level ( MSL): The distance a bove the average of E arth's oceans.
Mission Duration: T he t otal t ime n ecessary to a ccomplish a s pace mission.
Mission Elapsed Time ( MET): Time s ince the b eginning o f t he spaceflight.
Nozzle: The bellshaped p rotrusion at the tail e nd of a rocket w here t he exhaust of a r ocket
comes o ut.
NozzleExtended: T he rocket engine n ozzle which i s elongated to p rovide a pproximately 3
seconds m ore o f S pecific I mpulse.
NozzleRetracted: T he rocket e ngine n ozzle which i s p ulled back t o its o riginal shape.
OnStation Time: T he duration of time s pent a t t he m ission d estination.
Opposite S ide o f a Right T riangle: T he side opposite the given a ngle.
Orbital A ltitude: The h eight above Mean S ea L evel ( MSL) o f a s pacecraft.
Orbital I nclination : The n umber of degrees that an o rbit subtends relative t o t he e quator.
Payload: T he u seful l oad carried i nto space or t o t he surface of a n astronomical body.
Payload S hroud: T he c overing t hat p rotects the c argo f rom t he atmosphere o n i ts way into space.
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Payload M ass: The weight of a payload that i s effected by Earth’s g ravity.
PB/DN: Combination o f a Propulsion B us attached to a D ocking N ode a nd weighs 17 t onnes.
PB/DN Stack: T hree PB/DNs a ttached t o a F alcon Heavy that is on the L aunch P ad.
Periapsis: The lowest p oint in a n elliptical orbit.
Periapsis Δ V B urn: The rocket firing a t the l owest point o f a T ransfer O rbit.
Polar Orbit: A n orbit that flies a bove the N orth a nd S outh poles; it has an Orbital Inclination of
98 degrees.
Powered Ascent I nitiation ( PAI): The l ift o ff r ocket burn f rom the l unar surface t o lunar o rbit.
Powered Descent I nitiation (PDI) : The landing r ocket b urn from l unar o rbit t o the l unar surface.
Pressurized V olume: The v olume o f sealevel p ressure a ir t hat i s i n a Bigelow module.
Propellant: Total weight of LO2 a nd LH2
Propellant Ratio: The ratio o f L O2 to LH2 i n a rocket e ngine.
Propellant Weight : T he weight of both t he f uel (LH2 ) a nd the oxidizer (LO2 ).
Propellant Reserve: The p ercent o f the t otal propellant t hat i s s et a side i n c ase of e mergency.
Propulsion B us (PB) : T he u nit u sed t o r eboost t he s pace s tation due to orbital decay.
Radius o f H igher O rbit : T he h igher circular orbital altitude o f a s pacecraft as m easured f rom t he
center of an o rbiting b ody.
Radius of L ower O rbit : T he lower circular o rbital a ltitude of a spacecraft as measured from the
center of an orbiting b ody.
Reentry Interface: The m oment a s pacecraft encounters E arth's a tmosphere, w hich is used t o
slow t he s pacecraft d own for a safe l anding.
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Reentry P hase : The fourth o f six phases in a p arabolic s paceflight, where t he spacecraft c omes
back down into the a tmosphere.
Reserve P ropellant: The w eight o f the propellant u sed in c ase of an e mergency.
Right T riangle: A t riangle w ith one of t he angles equal t o exactly 9 0 degrees.
RL10 Engine: T he r ocket e ngine used in t he EM.
Rocket B urnout : The m oment a rocket engine s huts i tself o ff, where t he spacecraft continues
upward o n its o wn m omentum.
Round T rip Δv B udget: T he total Δv a space m ission needs to go to a destination and c ome b ack
home. I t is found b y d oubling the Δv Budget.
RoundTrip Time: The t ime i t takes for a spacecraft to reach its d estination and t o r eturn. It i s
found by d oubling the T ransfer T ime.
Space I nterface: T he h eight where space "officially" begins, which i s s et a t the internationally
agreed upon a ltitude o f 100,000 m (62 mi) MSL.
Space Launch S ystem Block IA ( SLSIA): An expendable vertical l aunch v ehicle t hat c an l ift
105 m T into o rbit.
SpaceShipTwo: The s pacecraft t hat is dropped from W hite K night 2 . A fter rocket b urnout, the
spacecraft c oasts up to s pace and b ack.
Space S tation : A place where s cientists, e ngineers, a nd tourists c an gather to explore t he many
wonders o f s pace.
Specific I mpulse (Is p ) : The force w ith r espect t o t he amount o f propellant used per unit of time.
Standard G ravitational P arameter ( mu) : The product of t he G ravitational Constant ( G) a nd the
mass o f a b ody ( M).
Standard Gravity ( g 0 ): T he a cceleration due to free f all.
Suborbital S paceflight: A s pacecraft t hat c oasts into s pace a fter rocket burnout that h as a f light
profile in t he shape o f a parabola.
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Time T o Touchdown: T he time t he spacecraft w ill t ake t o g lide t o a l anding.
Touchdown: T he m oment t he s pacecraft makes c ontact with t he runway during a landing.
Transfer O rbit # 1 : T he elliptical orbit a spacecraft f lies f rom periapsis to a poapsis.
Transfer O rbit # 2 : The elliptical orbit a s pacecraft f lies f rom apoapsis t o p eriapsis.
Transfer T ime : T he time b etween apoapsis and p eriapsis D elta V rocket firings.
Weightless P hase: The third of six phases in a p arabolic s paceflight, w here t he spacecraft and its
occupants experience w eightlessness.
White K night 2 : T he m other ship t hat c arries S paceShipTwo to l aunch a ltitude.
::
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EQUATIONS AND CONSTANTS
Altitude ( AGL)
Altitude (AGL) = Line − Of − Sight Distance · sin(Glide Slope)
CM Communications
CM COMM = 327
CM C ontingency
CM CONTINGENCY = 0.71M D + 852
CM Control
CM CONTROL = 60
CM Crew S ize
CM CREW = − 0.25M D + 15.5
CM C rew S ystems
CM SY STEMS = − 41.33M D + 3772
CM Crew V olume Ratio
CMV OLUME = 1260
CM CRE W
CM Dynamic W eight
W eightDynamic = CM SY STEMS + CM EC/LSS + CM EXP + CM CONTROL
CM EC/LSS
CM EC/LSS = 27.81M D + 1211
CM E lectrical
CM ELECTRIC = 130
CM Expendables
CM EXP = 20.50M D + 254
CM Instrumentation
CM INSTR = 188
CM M iscellaneous
CM MISC = 80
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CM S tatic W eight
CM STATIC = CM ELECTRIC + CM COMM + CM INSTR + CM CONTROL + CM MISC
CM S tructure
CM STRUCTURE = 2497
CM Weight ( lbs)
W eightCM = W eightStatic + W eightDynamic
CM Weight ( kg)
W eightCM
W eightCM = 2.2
Cosine o f a n A ngle
Adj acent S ide
cos(θ) = H y potenuse
Δv Apoapsis
√ √ΔvAP OAP SIS = μ (1 − 2R1 )
R2 R1 + R2
Δv Budget
ΔvBUDGET = ΔV P ERIAP SIS + ΔV AP OAP SIS
Δv P eriapsis
√ √ΔvP ERIAP SIS = μ ( 2R2 − 1)
R1 R1 + R2
Descent R ate
Descent Rate = Glide Speed · sin(Glide Slope)
Distance t o Spaceport
Distance T o Spaceport = Line − Of − Sight Distance · cos(Glide Slope)
Glide S lope
Glide Slope = Complement(Glide Angle) = 90o − Glide Angle
Glide S peed
Glide Speed = Line − Of − Sight Distance 2 − Line − Of − Sight Distance 1
Ground Speed
Ground Speed = Glide Speed · cos(Glide Slope)
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S.T.E.M. For t he Classroom
Adventures i n Outer S pace
Height S.I. C onversio n
h0 = Initial Height/3.28
Maximum Height
vertexh = − 1 go (vertext)2 + v0 (vertext ) + h0
2
Mission D uration
M D = On − StationDAY S + Round − T ripDAY S
OnStation T ime
On − StationDAY S = M ission Duration − Round − T ripDAY S
Radius o f L ower O rbit
R1 = AltitudeLOWER + RadiusEARTH
Radius o f Higher O rbit
R2 = AltitudeHIGHER + RadiusEARTH
RoundTrip Transfer T ime
Round − T ripDAY S = 2(T ransf er T imeDAY S )
Sine of a n A ngle
Adj acent S ide
cos(θ) = H y potenuse
Space H eight
h1 = h0 − 100, 000
Space Interface
100, 000 km
Spaceport America At Latitude P ayload
Spaceport − to − AtLatitude ALT = − 8.18ALT + 16, 335
Spaceport A merica I.S.S. Payload
Spaceport − to − ISS ALT = − 7.73ALT + 13, 982
Spaceport A merica P olar P ayload
Spaceport − to − P olar ALT = − 7.27ALT + 8, 118
Page 169 of 176
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Adventures in Outer S pace
Standard G ravity
g0 = 9.8 m/s2
Standard Gravitational Parameter
μ = 398, 600.4419 km3/s2
Time a t M aximum H eight
v0
vertext = g0
Time a t S pace I nterface
√spacet = v0 − vo2 + 2 g 0 h1
g0
Time Spent in S pace
T imespace = 2(vertext − spacet)
Time S pent Weightless
T imeweightless = 2(vertext)
Time To T ouchdown
T ime T o T ouchdown = Line−Of −S ig ht Distance
Glide S peed
Transfer Time
√T ransf er T imeDAY S = π (R1 + R2)3
8μ
Velocity S.I. C onversion
v0 = Initial V elocity(1609)/3600
Page 170 of 176
S.T.E.M. F or the Classroom
Adventures i n O uter S pace
IMAGE ATTRIBUTIONS
Cover. Adventures in Outer Space
Space S tation Bravo:
https://en.wikipedia.org/wiki/File:Complex_Bravo_Model.jpg
R.E.L. S kylon:
https://www.reactionengines.co.uk
Virgin Galactic SpaceShipTwo:
https://www.flickr.com/photos/rodeime/11904534745
Planet E arth:
http://maxpixel.freegreatpicture.com/WorldEarthRiseSunriseSpaceOut
erSunGlobe1765027
Composite I mage: h ttp://www.renewspace.media
01. Space I nvaders
http://www.renewspace.media
02. VG Pulp
http://www.renewspace.media
03. SS2 and V MS Eve
https://commons.wikimedia.org/wiki/File:SS2_and_VMS_Eve.jpg
04. VG G raph
http://www.renewspace.media
05. VG S preadsheet A pp
http://www.renewspace.media
06. VG M obile A pp
http://www.renewspace.media
07. Skylon P ulp
http://www.renewspace.media
08. SABRE D esigned F or S kylon S paceplane, 1 990s
https://commons.wikimedia.org/wiki/File:SABRE_engine_designed_for_Skylon_spacepl
ane,_1990s._(9660572897).jpg
Page 1 71 o f 176
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Adventures in O uter Space
09. Skylon Graph 0
http://www.renewspace.media
10. Skylon G raph 1 5
http://www.renewspace.media
11. Skylon Graph 3 0
http://www.renewspace.media
12. Skylon G raph 45
http://www.renewspace.media
13. Skylon G raph 6 0
http://www.renewspace.media
14. Skylon Spreadsheet App
http://www.renewspace.media
15. Skylon Mobile A pp, Part I
http://www.renewspace.media
16. Skylon Mobile A pp, Part I I
http://www.renewspace.media
17. Bigelow Pulp
http://www.renewspace.media
18. Inside Space S tation Alpha
https://commons.wikimedia.org/wiki/File:Inside_Space_Station_Alpha.jpg
19. Bigelow Space S tation
http://www.renewspace.media
20. Bigelow Spreadsheet App
http://www.renewspace.media
21. Bigelow M obile App
http://www.renewspace.media
Page 172 o f 176
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Adventures in Outer Space
22. Spaceport A merica P ulp
http://www.renewspace.media
23. Spaceport A merica terminal The G ateway
https://commons.wikimedia.org/wiki/File:Spaceport_America_terminal__The_Gateway
_(15094090585).jpg
24. Spaceport America Graph
http://www.renewspace.media
25. Spaceport A merica L anding D iagram
http://www.renewspace.media
26. Spaceport America T riangle
http://www.renewspace.media
27. Spaceport America S preadsheet App
http://www.renewspace.media
28. Spaceport A merica Mobile A pp
http://www.renewspace.media
29. Boeing D elta V Pulp
http://www.renewspace.media
30. Orbital Diagram ( Orbit1)
https://commons.wikimedia.org/wiki/File:Orbit1.svg
31. Hohmann Transfer Orbit
https://commons.wikimedia.org/wiki/File:Hohmann_transfer_orbit.svg
32. Boeing Delta V Spreadsheet App
http://www.renewspace.media
33. Boeing D elta V Mobile App
http://www.renewspace.media
34. Boeing Crew M odule P ulp
http://www.renewspace.media
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35. Boeing’s C ST100 Starliner S pacecraft D ocking t o t he I SS
https://commons.wikimedia.org/wiki/File:Boeing's_CST100_Starliner_spacecraft_docki
ng_to_the_ISS.jpg
36. Boeing S pace Tug S tudy C rew Module circa 1971 ( image credit: N ASA)
http://www.astronautix.com/s/spacetug.html
37. Boeing C rew M odule Spreadsheet App
http://www.renewspace.media
38. Boeing Crew Module M obile A pp
http://www.renewspace.media
39. Boeing E ngine M odule P ulp
http://www.renewspace.media
40. CST–100
https://commons.wikimedia.org/wiki/File:CST100.jpg
41. Boeing Space Tug Study Engine Module circa 1971 (image credit: N ASA)
http://www.astronautix.com/s/spacetug.html
42. Boeing Engine M odule S preadsheet A pp
http://www.renewspace.media
43. Boeing E ngine M odule M obile App
http://www.renewspace.media
44. Boeing L unar L ander P ulp
http://www.renewspace.media
45. Apollo 1 6 L M
https://commons.wikimedia.org/wiki/File:Apollo16LM.jpg
46. Boeing L unar Lander Spreadsheet A pp
http://www.renewspace.media
47. Boeing Lunar L ander M obile App
http://www.renewspace.media
Page 174 of 176
S.T.E.M. F or t he C lassroom
Adventures i n O uter S pace
INDEX
This book is provided in t he form of a PDF download. P lease use your PDF r eader to f ind any
words or p hrases t hat you w ish to look up.
::
Page 1 75 o f 176
S.T.E.M. F or the C lassroom
Adventures in Outer S pace
S.T.E.M. For the C lassroom
presents
ADVENTURES IN O UTER S PACE
A H igh S chool S .T.E.M. Laboratory Textbook
Copyright © 2017 b y Joe M aness and Richard K erry H oltzin, P h.D. Albuquerque, NM.
All rights reserved. No part of this t extbook may b e r eproduced, i n any form or b y any means,
without p ermission in w riting from the a uthor.
ISBN 9999999999
Page 1 76 o f 176
S.T.E.M. For the Classroom
Presents
ADVENTURES IN OUTER SPACE
A High School S.T.E.M. Laboratory Textbook
by
Joe Maness and Richard Kerry Holtzin, Ph.D.
This textbook is the lab for high school Junior mathematics. Students that have passed
Algebra 1 and Geometry should take this class. The textbook is based on a technical paper
that Joe and RK had written earlier about a commercial space program.
ABOUT THE AUTHORS
JOE MANESS Shortly after High School graduation, Joe enlisted in the U.S. Navy. He flew
backseat in S-3A Viking jet aircraft, accumulating over one hundred carrier landing or “traps.”
Joe rose to the rank of Petty Officer, 2nd Class. Joe then went to college after being Honorably
Discharged from the Navy, earning his Bachelor of Science degree in Applied Mathematics from
the University of New Mexico. Joe was a member of Kappa Mu Epsilon National Mathematics
Honor Society. Joe eventually became a Microsoft Certified Trainer, which in turn lead to a job
as a High School Math Teacher. During this time, Joe put together the website version of this
textbook. Joe is currently a Level 2 Secondary Education Teacher endorsed in Mathematics
with over 14 years of experience in the classroom. He resides in Albuquerque, NM, USA.
RICHARD KERRY HOLTZIN, PH.D. With three academic degrees in Eastern and Western
Philosophy, RK studied photography, anthropology, foreign languages, and sciences. Since the
mid-1980s, he has earned a living as an outdoors educator teaching geosciences, human
history, flora and fauna, ecology, archaeology, map and compass orienteering, and wilderness
survival. Previously, RK served two enlistments for a total of six years in the Navy, most of
which was with the Anti-Submarine Warfare Force (ASW). During this time, RK (his signature
'chop') was a radio operator, cryptologist, and courier for classified documents. After his
Honorable Discharge, including receiving a Letter of Meritorious Accommodation, he spent
more than forty years in the West and Southwest. To mention some of his many bailiwicks of
varying employment opportunities, he was a professional studio and stage musician, including
teaching guitar and music theory for some 25 years. He resides in Albuquerque, NM, USA.
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