space launch and flight without rockets (v.3)

8/12/2019 Space Launch and Flight without Rockets (v.3)

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Non-Rocket Space Launch and Flight, Version 32 All Chapters1


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Non-Rocket Space Launch and Flight, Version 32 All Chapters2


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Non-Rocket Space Launch and Flight, Version 32 All Chapters

Non-Rocket Space Launch and FlightBy Alexander A. Bolonkin

Dr.Sci., proe!!or o Ru!!ian and A"erican #ni$er!itie!

For"er Senior Re!earcher o NASA

#SA Air Force and Ru!!ian Space %ndu!try

&drat, $.'()

To m !i"e #lga Lu$a%ina

*u+li!hing ou!e l!e$ier, London, 2/

'


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To m !i"e #lga Lu$a%ina

0ontent!A$stract&re"ace

'( Space ele%ator, transport sstem "or space ele%ator and tether sstem )'2( Ca$le space accelerators 3*+33( Circle launcher and space keeper 3)+( #ptimal in"lata$le space to!ers *2.3( /inetic space to!ers .'02*)( 1as tu$e hpersonic launchers '0+3)*( arth4oon ca$le transport sstem '22+*( arth4ars ca$le transport sstem '2.

.( /inetic anti-gra%itator 5Repulsator6 '30'0( Centri"ugal space launcher '220''( Asteroids as propulsion sstems o" space ships '*022)'2( 4ulti-re"le7 propulsion sstems "or space and air %ehicles and energ

trans"er "or long distance ''22'3( lectrostatic Solar !ind propulsion 2'

'.'+( lectrostatic utili8ation o" asteroids "or space "light 22'.3'( lectrostatic le%itation on arth and arti"icial gra%it "or space ships and asteroids 22.3'')( 1uided solar sail and energ generator 2+32'*( Radioisotope space sail and electro-generator 2033)

'( lectrostatic solar sail 2)3+)'.( 9tili8ation o" space 23)32

Attachments:Non-con%entional and non-rocket "light on arth

Air ca$le transport and $ridges 3'( Air ca$le transport and $ridges 2*+2( ;igh speed catapult a%iation 2.3.3( Light multi-re"le7 engine 2..+'2

+( #ptimal tra


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A+!tract

At present, rockets are used "or launches and "lights into space( The ha%e $een intensi%el de%elopedsince =orld =ar >> !hen the 1erman engineer F( Von ?raun designed the "irst long distance rocketFA9-2( >n the su$se@uent )0 ears li@uid and solid rockets reached the peak o" their de%elopment(Their main shortcomings are 5'6 %er high cost o" space launching 20,000 0,000Bkg 526 large "uelconsumption 536 "uel storage pro$lems $ecause the o7idi8er and "uel 5"or e7ample o7gen and

hdrogen6 re@uire crogenic temperatures, or the are poisonous su$stances 5"or e7ample nitric acid,N2#36(

>n the past ears the author and other scientists ha%e pu$lished a series o" ne! methods !hichpromise to re%olutioni8e space launching and "light( These include the ca$le accelerator, circlelauncher and space keeper, space ele%ator transport sstem, space to!ers, kinetic to!ers, the gas-tu$emethod, sling rotar method, asteroid emploment, electromagnetic accelerator, tether sstem, Sun andmagnetic sails, solar !ind sail, radioisotope sail, electrostatic space sail, laser $eam, kinetic anti-gra%itator 5repulsitor6, arth4oon or arth4ars non-rocket transport sstem, multi-re"lecti%e $eampropulsion sstem, electrostatic le%itation, etc(

iii

There are ne! ideas in a%iation !hich can $e use"ul "or "lights in planet atmosphere( Some o" theseha%e the potential to decrease launch costs thousands o" times, other allo! the speed and direction o"space apparatus to $e changed !ithout the spending o" "uel(The author summari8es some re%olutionar methods "or scientists, engineers, students, and the pu$lic(

;e seeks attention "rom the pu$lic, engineers, in%entors, scientists "or these inno%ations and he hopesthe media, go%ernment and the large aerospace companies !ill increase research and de%elopmentacti%it in these areas(

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*reace

The ne! methods are onl proposals( There are a lot o" pro$lems that must $e researched, modeled,and tested $e"ore these ideas can $e de%eloped, designed, $uilt, and e7plored( 4ost o" ideas aredescri$ed in the "ollo!ing !a: there is a $rie" e7planation o" the idea including its ad%antages and

short comings, then methods estimation and computations o" the main sstem parameters, and a $rie"description o" pro


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0hapter 1

Space le$ator, 4ran!port Sy!te" or Space le$ator, and

4ether Sy!te"

Su""ary

The chapter $rings together research on the space ele%ator and a ne! transportation sstem "or it(This transportation sstem uses mechanical energ trans"er and re@uires onl minimal energ so that itpro%ides a EFree Trip into space( >t uses the rotar energ o" planets( The chapter contains the theorand results o" computations "or the "ollo!ing pro


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>n '.*$ Arthur C( Clarkeintroduced the concept o" a space ele%ator to a $roader audience in his'.*no%el, The Fountains of Paradise(

Ga%id Smitherman o"NASAB4arshallHs Ad%anced &ro


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The e%ator !ould ha%e to $e $uilt o" a "aterialthat could endure tremendous !tre!!!hile also $einglight-!eight, cost-e""ecti%e, and manu"actura$le( A considera$le num$er o" other no%el engineeringpro$lems !ould also ha%e to $e sol%ed to make a space ele%ator practical( TodaHs technologydoes notmeet these re@uirements(There are a %ariet o" space ele%ator designs( Almost e%er design includes a $ase station, a ca$le,

clim$ers, and a counter!eight( The $ase station designs tpicall "all into t!o categories: mo$ile and

stationar( 4o$ile stations are tpicall large oceangoing %essels 5"ig( '(26( Stationar plat"orms aregenerall positiored in high-altitude locations(

Fig. 1.2( Sea space ele%ator(

The $uilding o" a space ele%ator has t!o main pro$lems: tire need "or material !ith a %er high tensilestressBspeci"ic densit ratio, and the %er large cost o" installation( ?ut a space ele%ator could $e maderelati%el economicall i" a ca$le !ith a densit similar to graphite, !ith a tensile strength o" around)'20 6*acould $e produced in $ulk at a reasona$le price( ? comparison, the strongest steels are no more than 1&a 5' 1&a '00 kgBmm2 0(' tonBmm26, $ut

steel is hea%( The much lighter materialke$larhas a tensile strength o" 2() +(' 1&a, !hile 7uart8"i$er can reach up!ards o" 20 1&a the tensile strength o"dia"ond"ilaments !ould theoreticall $eminimall higher( 0ar+on nanotu+e!ha%e a theoretical tensile strength and densit that lie !ell !ithin the desiredrange "or space ele%ator structures, $ut the technolog to manu"acture $ulk @uantities and "a$ricatethem into a ca$le has not et $een de%eloped( Theoreticall car$on nanotu$es can ha%etensilestrengths $eond '20 1&a( %en the strongest "i$er made o" nanotu$es is likel to ha%e nota$l lessstrength than its components 530)0 1&a6( Further research on purit and di""erent tpes o" nanotu$es!ill hope"ull impro%e this %alue(Note that at present 54arch 200+6, car$on nanotu$es ha%e an appro7imate cost o" '00Bgram, and 20million grams !ould $e necessar to "orm e%en a seed ele%ator( This price is decreasing rapidl, and

large-scale production !ould reduce it "urther( Clim$ers co%er a !ide range o" designs( #n ele%ator designs !hose ca$les are planar ri$$ons, someha%e proposed to use pairs o" rollers to hold the ca$le !ith "riction( #ther clim$er designs in%ol%emagnetic le%itation 5unlikel due to the $ulk track re@uired on the ca$le6(

&o!er is a signi"icant o$stacle "or clim$ers( Some solutions ha%e in%ol%ed nucler po!er, la!eror"icro9a$epo9er +ea"ing. The are %er comple7, or e7pensi%e, or ha%e %er lo! e""icienc( Theprimar po!er methods 5laser and micro!a%e po!er $eaming6 ha%e signi"icant pro$lems !ith $othe""icienc and heat dissipation on $oth sides( ?elo! the author o""eres a ca$le transport sstem !hichis more realistic at the present time(

:
http://en.wikipedia.org/wiki/Materialhttp://en.wikipedia.org/wiki/Stress_(physics)http://en.wikipedia.org/wiki/Stress_(physics)http://en.wikipedia.org/wiki/Technologyhttp://en.wikipedia.org/wiki/Pascalhttp://en.wikipedia.org/wiki/Kevlarhttp://en.wikipedia.org/wiki/Kevlarhttp://en.wikipedia.org/wiki/Kevlarhttp://en.wikipedia.org/wiki/Quartzhttp://en.wikipedia.org/wiki/Diamondhttp://en.wikipedia.org/wiki/Diamondhttp://en.wikipedia.org/wiki/Carbon_nanotubehttp://en.wikipedia.org/wiki/Laserhttp://en.wikipedia.org/wiki/Microwavehttp://en.wikipedia.org/wiki/Power_beaminghttp://en.wikipedia.org/wiki/Image:SpaceElevatorClimbing.jpghttp://en.wikipedia.org/wiki/Materialhttp://en.wikipedia.org/wiki/Stress_(physics)http://en.wikipedia.org/wiki/Technologyhttp://en.wikipedia.org/wiki/Pascalhttp://en.wikipedia.org/wiki/Kevlarhttp://en.wikipedia.org/wiki/Quartzhttp://en.wikipedia.org/wiki/Diamondhttp://en.wikipedia.org/wiki/Carbon_nanotubehttp://en.wikipedia.org/wiki/Laserhttp://en.wikipedia.org/wiki/Microwavehttp://en.wikipedia.org/wiki/Power_beaming


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There ha%e $een t!o methods proposed "or dealing !ith the counter!eight needed: a hea% o$


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m- gra%itation on 4oon sur"ace QmBs2F "orce Qn" altitude Qm" - ca$le tensile stress QnBm2"# perigee altitude Qm

k ! $ ratio o" ca$le tensile stress to densit QnmBkg

K ! k$'0*

coe""icient Qmillion meters% annual load Qkgn o%erloadn num$er o" !orking das&eSe annual emploee salar Qm m2Bm' relati%e apparatus mass( ;ere are m2is mass o" apparatus, m'is mass o" asteroid Qkg' e@uali8er mass Qkg'a annual maintenance o" installation Q'e "inal mass o" an >nstallation Qkg'o load mass deli%ered in one dar %aria$le

( - radius Qm(o- radius o" planet Qm(- radius o" geosnchronous or$it Qm(m- radius o" 4oon QmT- or$it period Qhours(v- %olume o" a ca$le Qm3)- speed o" space ship around asteroid QmBs)a- initial speed o" asteroid around space ship QmBs)d deli%er speed QkmBs)r ma7imum admitted ca$le speed QmBs)'- circulate speed QmBs

)2- escape speed QmBs)- ship additional speed recei%ed "rom asteroid QmBs*- mass o" a ca$le Qkg*r- relati%e mass o" ca$le 5ratio o" ca$le mass to ship mass *s6T- or$it period Qhours+ li%e time Qears

- tensile strength QNBm2

- angle speed o" a planet QradBs

m - angle speed o" the 4oon QradBs(

- densit o" ca$le QkgBm3

%ntroduction

At present, rockets are used to deli%er paloads into space and to change the tra


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"or this space mechanical energ trans"er or similar "acilities "or transporting a paload into space inthe literature and patents(

The present method does not re@uire geosnchronous or$it 5!hich is a$sent "rom most planets,moons, and asteroids !hich ha%e !eak gra%itation6 and instead, uses the kinetic and rotational energo" the space $od to modi" the tran the tether method t!oarti"icial $odies are connected $ ca$le( The main pro$lem !ith this method, !hich re@uires energ "orincreasing the rotation o" the tether sstem 5motori8ed tether26 is ho! to rotate it !ith a "le7i$le ca$leand !hat to do !ith momentum a"ter launch i" the tether sstem is used again, etc( >" this sstem isused onl one time, it is !orse than a con%entional rocket $ecause it loses the second $od andre@uires a large source o" energ(>n the suggested method, the space %ehicle is connected to a natural $od 5planet, asteroid, moon,

meteorite6( The ship gets energ "rom the natural $od and does not ha%e to deal !ith the natural $odin the "uture(>n the older idea, a space ele%ator is connected $et!een a geosnchronous space station and the arth

$ a ca$le+( This ca$le is used to deli%er a paload to the station( The main pro$lems are the %er largeca$le !eight and deli%er o" the energ "or mo%ement o" the load container(>n this suggested transport sstem the load engine is located on the arth and trans"ers energ to the

load container and the space station using a %er simple method 5see &ro


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A proposed centri"ugal space launcher !ith a ca$le transport sstem is sho!n in Fig( '(3( The sstemincludes an e@uali8er 5$alance mass6 located in geosnchronous or$it, an engine located on arth, andthe ca$le transport sstem ha%ing three ca$les: a main 5central6 ca$le o" e@ual stress, and t!o transportca$les, !hich include a set o" mo$ile ca$le chains connected se@uentiall one to an other $ the rollers(#ne end o" this set is connected to the e@uali8er, the other end is connected to the planet( Such a

separation is necessar to decrease the !eight o" the transport ca$les, since the stress is %aria$le alongthe ca$le( This transport sstem design re@uires a minimum !eight $ecause at e%er local distance there@uired amount o" ca$le is onl that o" the diameter "or the local "orce( The load containers are alsoconnected to the chain( =hen containers come up to the rollers, the mo%e past the rollers and continuetheir motion up the ca$le( The entire transport sstem is dri%en $ an con%entional motor located onthe planet( =hen paloads are not $eing deli%ered into space, the sstem ma $e used to trans"ermechanical energ to the e@uali8er 5load ca$in, the space station6( This mechanical energ ma also $econ%erted to an other sort energ(

Fig. 1.'a,+( The suggested Space Transport Sstem( Notations: ' Rotar planet 5"or e7ample, thearth6 2 - suggested Space Transport Sstem 3 - e@uali8er 5counter!eight6 + - roller o"Transport Sstem - launch space ship ) - a return ship a"ter "light * engine o" TransportSstem elliptic or$it o" tourist %ehicles . - 1eosnchronous or$it( a Sstem "or lo!coe""icient k, - Sstem "or high coe""icient k 5!ithout rollers +6(

The space satellites released $elo! geosnchronous or$it !ill ha%e elliptic or$its and ma $econnected $ack to the transport sstem a"ter some re%olutions !hen the space ship and ca$le are in thesame position 5Fig( '(36( >" lo! earth or$it satellites use a $rake parachute, the can ha%e their or$itclosed to a circle(

The space pro$es released higher than geosnchronous or$it !ill ha%e a hper$olic or$it, "l to otherplanets, and then can connect $ack to the transport sstem !hen the ship returns( 4ost space paloads, like tourists, must $e returned to arth( =hen one container is mo%ed up, thenanother container is mo%ed do!n( The !ork o" li"ting e@uals the !ork o" descent, e7cept "or a small

1'


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loss in the upper and lo!er rollers( The suggested transport sstem lets us "l into space !ithoute7pending enormous energ( This is the reason !h the method and sstem are named a EFree Trip( Ge%ices sho!n on "ig( '(+ are used to change the ca$le length 5or chain length6( The middle roller issho!n in "ig( '((

Fig. 1.. T!o mechanisms "or changing the rope length in the Transport Sstem 5The are same "or

the space station6( Notations: '' - the rope !hich is connected a7isA,B( This rope can change itslength 5the distanceAB6 '2 - additional rollers(

Fig. 1./.Roller o" Space Transport Sstem( Notations: ' roller, ') control '* transport sstemca$le ' main ca$le(

>" the ca$le material has a %er high ratio o" sa"e 5admissi$le6 stressBdensit there ma $e one chain5Fig( '(3$6( The transport sstem then has onl one main ca$le( #ld design 5"ig( '('6 has manpro$lems, "or e7ample, in the trans"er o" large amounts o" energ to the load ca$in(

4heory and 0o"putation

&in "etric !y!te"(

'( The ca$le o" e@ual stress "or the planet( The "orce acti%e in the ca$le is:

+=+==(

(

(

(

Ad(Fd*FAF

00

00 5'('6

!here

1


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=

0

22

000

(

(

(

. 5'(26

>" !e su$stitute 5'(26 in 5'('6 and "ind the di""erence to the %aria$le upper integral limit, !e o$tain thedi""erential e@uations

d(

(

(

(dA

A

=0

22

000'

( 5'(36

Solution to e@uation 5'(36 is

=

65e7p65 00

0

(B

A

A(a 5'(+6

'

2

''65

2

00

2

0

2

0(

(

(((rB

,

!here ais the relati%e ca$le area,B5r6 is the !ork o" li"ting ' kg mass(

The computation "or di""erentK!$o$'0* is presented in Figs( '(), '(*(

1/


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As ou see "orK! 2 the ca$le area changes $ '' times, $ut "or %er highK 30 onl $ '('.times(

2( The mass o" the ca$le *and a %olume v can $e calculated $ e@uations

====

(

(

(

(

(

(

d(B

k

F(*ad(

k

Fad(A

000

0

0

00

0

00 e7p65,

( 5'(6

The results o" the computation o" the ca$le mass "or the load mass o" 3000 kg 5"orce 3000 N6 andca$le densit o" '00 kgBm3is presented in Figs( '(, '(.(

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3( The li"t "orce o" a mass o" ' kg, !hich is located o%er geosnchronous or$it and has speed ) / )'is

2

0

0

2 ((

(F

Qkg"Bkgm( 5'()6

15


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The result o" this computation is presented in Fig( '('0( %er '00 kg o" a mass o" the e@uali8ergi%es kg" o" li"t "orce at the altitude '00,000 km(

+( The e@uali8er mass 5counter!eight6'"or di""erent radius 5altitudes6(andKma $e computed"rom the e@uili$rium e@uation and 5'()6:

2

0

0

2

00 65

(

(

('F(aF

,

[ ]2

0

0

2

0 '65

=

((

(

(aF'

( 5'(*6

Results o" this computation are presented on Fig( '('''('+( For a li"t "orce o" '0 tons at arth 5paload o"3000 kg6, the e@uali8er mass is *0 tons "orK! + and a$out +3 tons "orK!'0 at the altitude '00,000 km(

1


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Non-Rocket Space Launch and Flight, Version 32 All Chapters1:


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( >" the $alance ca$in 5load6 to $e mo%ed do!n is a$sent, then the deli%er !ork o" ' kg mass ma $ecomputed $ the e@uation

'

2

''65

2

00

2

0

2

0(

(

((((E

. 5'(6

The result o" this computation presented in Fig( '('(

2


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)( =hen a space %ehicle 5satellite6 is disconnected "rom the transport sstem $e"ore reaching geosnchronousor$it then an or$it perigee r 5perigee altitude"6 and period time Tcan $e computed $ the e@uations

0

(rT

u

u(r(r"

23)00

65,

2,

2B3

0

+=

==

, 5'(.6

!here u ! 2(3$0, 0 ! 3(.)'0'+(The result o" this computation is presented in Fig( '('), '('*( =hen this space %ehicle is in a suita$le

position 5a"ter the return "light6, it can $e connected $ack to the transport sstem(

Fig. 1.13( &erigee altitude 5in thousand km6 %ia disconnected 5apogee6 altitude o" a space ship(

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Fig. 1.15( #r$it period 5in hours6 %ia apogee altitude 5in thousand km6(

*( =hen the space %ehicle is disconnected "rom the transport sstem higher than the geosnchronousor$it, then the %ehicle speed ), the "irst space speed )', and the second 5escape6 space speed )2can$e computed $ "ormulas

'2

)

' +'+(','0.*)('.

, ))(

)() == ( 5'('06 Then the result o" computation are gi%en in Fig( '('( A$o%e an altitude o" 0,000 km the space%ehicle can go into interplanetar or$it( The necessar speed and direction can $e set $ a choice o"the disconnect point and position sstem in space( Additional speed o%er the escape %elocit mareach ) kmBsec( This is more then enough "or a "light to the "ar planets( =hen the space %ehiclereturns it can also choose a point in the transport sstem "or connection(

( Let us take a small part o" a rotar circle and !rite it e@uili$rium

22


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sin22 2

A(

)A( = (The ma7imum sa"e ca$le speed o" chains is

K)r*'0

QmBs ( 5'(''6

Results o" this computation are presented in Fig( '('.(

.( The deli%er cost o" ' kg load is 5Fig( '(206

d

aeei

)'S&

+

CC

3

' ( 5'('26'0( The increase o" the space installation mass is a geometric progression]

00

0

Bln

Bln'

'''

''n

e , 5'('36 !here n num$er o" !orking das 5Fig( '(2'6(

''( The planetar parameters used "or computations in all pro


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'2( The increase o" the space installation mass is a geometric progression]00

0

Bln

Bln'

'''

''n

e , 5'('36 !here n num$er o" !orking das 5Fig( '(2'6(

2


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'3( The planetar parameters used "or computations in all pro


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The transport sstem has three ca$les: one main and t!o in the transport sstem( ach ca$le cansupport a "orce 5load6 o" 3000 kg"( The main ca$le has a cross-sectional area o" e@ual stress( Then theca$le cross-section area is 5see Fig( '()6A 0(+2 mm25diameterD 0(*3 mm6 at the arthDs sur"ace,ma7imum '(+ mm2in the middle section 5D '(33 mm, altitude 3*,000 km6, andA 0(2 mm25D 'mm6 at the e@uali8er( The mass o" main ca$le is 20 tons 5see Fig( '(6( The chains o" the t!o transportca$le loops ha%e gross section areas to e@ual the tensile stress o" the main ca$le at gi%en altitude, and

the capa$ilities are the same as the main ca$le( ach o" them can carr 3 tons "orce( The total mass o"the ca$le is a$out )20 tons( The three ca$les increase the sa"et o" the passengers( >" an one o" theca$les $reaks do!n, then the other t!o !ill allo! a sa"e return o" the space %ehicle to arth and therepair o" the transport sstem( >" the container ca$le is $roken, the pilot uses the main ca$le "or deli%ering people $ack to arth( >"the main ca$le is $roken, then the load container ca$le !ill $e used "or deli%ering a ne! main ca$le tothe e@uali8er( For li"ting non-$alance loads 5"or e7ample, satellites or parts o" ne! space stations,transport installations, interplanetar ships6, the energ must $e spent in an deli%er method( Thisenerg can $e calculated "rom e@uation 5'(65Fig( '('6( =hen the transport sstem in Fig( '(3 is used,the engine is located on the arth and does not ha%e an energ limitation''( 4oreo%er, the transportsstem in Fig( '(3 can trans"er a po!er o" up to .0,000 k= to the space station "or a ca$le speed o" 3

kmBs( At the present time, the >nternational Space Station has onl )0 k= o" po!er(Deli$ery capa+ilitie!( For tourist transportation the suggested sstem !orks in the "ollo!ing manner(

The passenger space %ehicle has the "ull mass o" 3 tons 5)))* pounds6 to carr 2 passengers and t!opilots( #ne ship mo%es up, the other ship, !hich is returning, mo%es do!n then the li"t and descentenergies are appro7imatel e@ual( >" the a%erage speed is 3 kmBs then the "irst ship reaches the altitudeo" 2'( 23 thousands km in 2 hours 5acceleration '(. mBs26( At this altitude the ship is separated "romthe ca$le to "l in an elliptical or$it !ith minimum altitude 200 km and period appro7imatel ) hours5Figs( '('), '('*6( A"ter one da the ship makes "our re%olutions around the arth !hile the ca$lesstem makes one re%olution, and the ship and ca$le !ill $e in the same place !ith the same speed(The ship is connected $ack to the transport sstem, mo%es do!n the ca$le and li"ts the ne7t ship( Theor$it ma $e also 3 re%olutions 5period hours6 or 2 re%olutions 5period '2 hours6( >n one da the

transport sstem can accommodate '2 space ships 5300 tourists6 in $oth directions( This means morethen '00,000 tourists annuall into space( The sstem can launch paloads into space, and i" the altitude o" disconnection is changed then theor$it is changed 5see Fig( '('*6( >" a satellite needs a lo! or$it, then it can use the $rike parachute !henit "lies through the top o" the atmosphere and it !ill achie%e a near circular or$it( The annual paloadcapa$ilit o" the suggested space transport sstem is a$out '2,)00 tons into a geosnchronous or$it( >" instead o" the e@uali8er the sstem has a space station o" the same mass at an altitude o" '00,000km and the sstem can has space stations along ca$le and a$o%e geosnchronous or$it then thesestations decrease the mass o" the e@uali8er and ma ser%e as tourist hotels, scienti"ic la$oratories, orindustrial "actories(>" the space station is located at an altitude o" '00,000 km, then the time o" deli%er !ill $e .(3)

hours "or an a%erage deli%er speed o" 3 kmBs( This means )0 passengers per da or 2',000 peopleannuall in space(Let us assume that e%er person needs +00 kg o" "ood "or a oneear round trip to 4ars, and 4ars

has the same transport installation 5see ne7t pronternational Space Station has costman $illions o" dollars, $ut the suggested space transport sstem can cost a lot less( 4oreo%er, the

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suggested transport sstem allo!s us to create other transport sstems in a geometric progression Qseee@uation 5'('36( Let us e7amine an e7ample o" the transport sstem( >nitiall !e create the transport sstem to li"t onl 0 kg o" load mass to an altitude o" '00,000 km(9sing the Figs( '() to '('+ !e ha%e "ound that the e@uali8er mass is ( tons, the ca$le mass is '0(2tons and the total mass is a$out '. tons( Let us assume that the deli%er cost o" ' kg mass is '0,000(The construction o" the sstem !ill then ha%e a cost o" '.0 million( Let us assume that ' ton o" ca$le

!ithK + "rom !hiskers or nanotu$es costs 0(' million then the sstem costs '(2 million( Let usput the research and de%elopment 5RG6 cost o" installation at 2. million( Then the total cost o"initial installation !ill $e 220 million( A$out .0U o" this sum is the cost o" initial rocket deli%er(A"ter construction, this initial installation $egins to deli%er the ca$le and e@uali8er or parts o" the

space station into space( The ca$le and e@uali8er capa$ilit increase in a geometric progression( Theinstallation can use part o" the time "or deli%er o" paload 5satellites6 and sel"-"inancing o" thispro" the reader does not agree !ith this estimation, then e@uations 5'('6 to 5'('36 and Figs( '() to '(2'are a$le calculation o" the deli%er cost "or other parameters( >n an case the deli%er cost !ill $ehundreds o" times less than the current rocket po!ered method(

Deli$ery Sy!te" or Free Round 4rip to >ar! &*ro=ect 2(

A method and similar installation 5Figs('(3 to '(6 can $e used "or ine7pensi%e tra%el to other planets,"or e7ample, "rom the arth to 4ars or the 4oon and $ack 5Fig( '(226( A 4ars space station !ould $e

25


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similar to an arth space station, $ut the 4ars station !ould !eigh less due to the decreasedgra%itation on 4ars( This method uses the rotar energ o" the planets( For this method, t!o "acilitiesare re@uired, one on arth and the other on another planet 5e(g( 4ars6( The arth accelerates the spaceship to the re@uired speed and direction and then disconnects the ship( The space ship "lies in spacealong the de"ined tra


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2:


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Non-Rocket Space Launch and Flight, Version 32 All Chapters'


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Non-Rocket Space Launch and Flight, Version 32 All Chapters'1


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Free 4rip to >oon &*ro=ect '(

This method ma $e used "or an ine7pensi%e trip to a planetDs moon, i" the moonDs angular speed ise@ual to the planetDs angular speed, "or e7ample, "rom the arth to the 4oon and $ack 5Fig( '(30 to'(326( The upper end o" the ca$le is connected to the planetDs moon( The lo!er end o" the ca$le isconnected to an aircra"t 5or $uo6, !hich "lies 5i(e( glides or slides6 along the planetDs sur"ace( Thelo!er end ma $e also connected to an arth pole( The aircra"t 5or arth polar station, or 4oon6 has a

'2


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de%ice !hich allo!s the length o" ca$le to $e changed( This de%ice !ould consist o" a spool, motor,$rake, transmission, and controller( The "acilit could ha%e de%ices "or deli%ering people and paloadsto the 4oon and $ack using the suggested transport sstem( The deli%er de%ices include: containers,ca$les, motors, $rakes, and controllers( >" the aircra"t is small and the ca$le is strong then the motiono" the 4oon can $e used to mo%e the airplane( For e7ample, i" the airplane !eighs ' tons and has anaerodnamic ratio 5the li"t "orce to the drag "orce6 e@ual to , a thrust o" 3000 kg !ould $e enough "or

the aircra"t to "l "or in"init !ithout re@uiring an "uel( The aircra"t could use a small engine "ormaneu%era$ilit and temporar landing( >" the planet has an atmosphere 5as the arth6 the enginecould $e a tur$ine engine( >" the planet does not ha%e an atmosphere, a rocket engine ma $e used( >" the suggested transport sstem is used onl "or "ree thrust 5. tons6, the sstem can thrust the threenamed supersonic aircra"t or produce up to +0 millions !atts o" energ(

A di""erent "acilit could use a transitional space station located at the 8ero gra%it point $et!een theplanet and the planetDs moon( Fig( '(3' sho!s a sketch o" the temporar landing o" an airplane on theplanet sur"ace( The aircra"t increases the length o" the ca$le, "lies ahead o" the ca$le, and lands on aplanet sur"ace( =hile the planet makes an angle turn 51 30, see Fig( '(3'6 the aircra"t can $e on

a planet sur"ace( This time e@uals a$out 2 hours "or the arth, !hich !ould $e long enough to loadpaload on the aircra"t

(

Fig. 1.'. The suggested transport sstem "or the 4oon( Notations: ' arth, 2 - 4oon, 2) suggested 4oon transport sstem, 2*, 2 load ca$ins, 2. aircra"t, 30 ca$le control, 32 engine(

The 4oonDs tra


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Fig. 1.'1. Temporar landing o" the 4oon aircra"t on the arthDs sur"ace "or loading( a landing, +

take-o""(

The 4oonDs tra


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The other more simple design 5!ithout aircra"t6 is sho!n in Fig( *(', chapter *( The ca$le isconnected to on arth pole, to a special polar station !hich allo!s to change a length o" ca$le( Nearthe pole the ca$le is supported in the atmosphere $ air $alloons and !ings(

4echnical para"eter!

The "ollo!ing are some data "or estimating the main transport sstem parameters "or connecting to the4oon to pro%ide ine7pensi%e paload trans"er $et!een the arth and the 4oon( The sstem has threeca$les, each o" !hich can keep the "orce at 3 tons( 4aterial o" the ca$le hasK+( All ca$les !ouldha%e cross-sectional areas o" e@ual stress( The ca$le has a minimal cross-sectional areaA0o" 0(+2 mm2

5diameter d 0(*3 mm6 and ma7imum cross-sectional areaAmo" '(. mm25d '() mm6( The mass o"the main ca$le !ould $e '300 tons 5Fig( '(3)6( The total mass o" the main ca$le plus the t!o containerca$les 5"or deli%ering a mass o" 3000 kg6 e@uals 3.00 tons "or the deli%er transport sstem in Figs('(30 to '(33( An ine7pensi%e means o" paload deli%er $et!een the arth and the 4oon could thus$e de%eloped( The elapsed time "or the 4oon trip at a speed o" ) kmBs !ould $e a$out '( hours andthe annual deli%er capa$ilit !ould $e '320 tons in $oth directions(

Di!cu!!ion0a+le *ro+le"!

4ost engineers and scientists think it is impossi$le to de%elop an ine7pensi%e means to or$it to anotherplanet( T!ent ears ago, the mass o" the re@uired ca$le !ould not allo! this proposal to $e possi$le"or an additional speed o" more 2,000 mBs "rom one asteroid( ;o!e%er, todaDs industr !idelproduces arti"icial "i$ers that ha%e a tensile strength 3 times more than steel and a densit + timesless than steel( There are also e7perimental "i$ers !hich ha%e a tensile strength 30)0 times more thansteel and a densit 2 to + times less than steel( For e7ample, in the $ookAdvan0ed Fi-ers andCom#osites is p( ', there is a "i$er CD !ith a tensile strength o" 2 000 kgBmm2 and densit5speci"ic gra%it6 3 3( gBcm3( >" !e take an admitted strength o" *000 kgBmm252 *'0'0NBm2, 3

300 kgBm36 then the ratio, / 0(0'0-)or 2$3 20'0)5K 26( Although 5in '.*)6 the graphite"i$ers are strong 52$3'0'0)6, the are at $est still ten times !eaker than theor predicts(

Steel "i$er has tensile strengths o" ,000 4&A 500 kgBmm26, $ut the theoretic %alue is 22,000 4&a5'.*6( &olethlene "i$er has a tensile strength o" 20,000 4&a and the theoretical %alue is 3,0004&a 5'.*6( The mechanical $eha%ior o" nanotu$es also has pro%ided e7citement $ecause nanotu$es are seen asthe ultimate car$on "i$er, !hich can $e used as rein"orcements in ad%anced composite technolog(arl theoretical !ork and recent e7periments on indi%idual nanotu$es 5mostl 4=NTs6 ha%econ"irmed that nanotu$es are one o" the sti""est materials e%er made( =hereas car$oncar$on co%alent$onds are one o" the strongest in nature, a structure $ased on a per"ect arrangement o" these $ondsoriented along the a7is o" nanotu$es !ould produce an e7ceedingl strong material( Traditional car$on

"i$ers sho! high strength and sti""ness, $ut "all "ar short o" the theoretical in-plane strength o" graphitelaers 5an order o" magnitude lo!er6( Nanotu$es come close to $eing the $est "i$er that can $e made"rom graphite structure(

For e7ample, !hiskers made "rom car$on nanotu$es 5CNT6 ha%e a tensile strength o" 200 1iga-&ascals and IoungDs modulus o" o%er ' Tera &ascal 5'...6( The theor predicts ' Tera &ascal andIoung modulus ' Tera &ascals( The hollo! structure o" nanotu$es makes them %er light 5speci"icdensit %aries "rom 0( gBcc "or S=NTs up to '( gBcc "or 4=NTs, compared to 2(2) gBcc "or graphiteor *( gBcc "or steel6(

'/


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Speci"ic strength 5strengthBdensit6 is important in the design o" our transportation sstem and spaceele%ator nanotu$es ha%e this %alue at least 2 orders o" magnitude greater than steel( Traditional car$on"i$ers ha%e a speci"ic strength +0 times greater than steel( =here nanotu$es are made o" graphitecar$on, the ha%e good resistance to chemical attack and ha%e high terminal sta$ilit( #7idationstudies ha%e sho!n that the onset o" o7idation shi"ts $ a$out '00 C higher temperatures in nanotu$escompared to high modulus graphite "i$ers( >n %acuums or reducing atmospheres, nanotu$es structures

!ill $e sta$le at an practical ser%ice temperature( Nanotu$es ha%e e7cellent conducti%it like copper(The price "or the SiC !hiskers produced $ Car$orundun Co( !ith 20,).0 4&a, 3(22 gBcc!as ++0Bkg in '..( 4edicine, the en%ironment, space, a%iation, machine-$uilding, and the computerindustr need cheap nanotu$es( Some American companies plan to produce nanotu$es in 23 ears(

?elo! the author pro%ides a $rie" o%er%ie! o" the annual research in"ormation 520006 regarding theproposed e7perimental test "i$ers(

Data that can +e u!ed or co"putation

Let us consider the "ollo!ing e7perimental and industrial "i$ers, !hiskers, and nanotu$es:'( 7perimental nanotu$es CNT 5car$on nanotu$es6 ha%e a tensile strength o" 200 1iga-&ascals

520,000 kgBmm26, IoungDs modulus is o%er ' Tera &ascal, speci"ic densit '00 kgBm35'( gBcc65ear 20006(

For sa"et "actor n 2(+, 300 kgBmm2 (3'0'0NBm2,'00 kgBm3, 5$6+)'0),K +()( The S=NTs nanotu$es ha%e a densit o" 0( gBcc, and 4=NTs ha%e a densit o" '( gBcc(9n"ortunatel, the nanotu$es are %er e7pensi%e at the present time 5'..+6(

2( For !hiskers CD 000 kgBmm2, 300 kgBm35'..6 Qp('*(

3( For industrial "i$ers 00 )00 kgBmm2, '00 kgBm3, 2,*'0),K 0(2* 0(333, Figures "or some other e7perimental !hiskers and industrial "i$ers are gi%e in Ta$le '(2(

4a+le 1.2

----------------------------------------------------------------------------------------------------------------------------4aterial Tensile GensitFi$ers 4&a Gensit

strength gBcc gBcc=hiskers kgBmm2

Al?'2 2)0 2() WC-0 )200 '(.? 200 2(3 T4. )000 '(*.?+C 200 2( Thorael )0 '('Ti?2 33*0 +( Allien ' 00 '()SiC '30+'+0 3(22 Allien 2 3000 0(.*

See Re"erences *, , ., '0(

0onclu!ion!The ne! materials make the suggested transport sstem and pro


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prepared to discuss the pron a tether sstem t!o arti"icial $odies are connected $ a ca$le( The sstem rotates around its commona7is and the arth( This section contains a $rie" description o" the idea o" a tether sstem( The readercan "ind details in the Tethers in Space ;and$ook'and special researches made in this area( Short de!cription. A space tether is a long ca$le used to couple masses to each other or to otherspacecra"t, such as a spent $ooster rocket o" a space station 5Fig( '(336( Space tethers are usuall madeo" strong ca$le( The tether can pro%ide a mechanical connection $et!een t!o space o$ts longdimension is al!as oriented to!ards the planet( Some o" the earliest satellites !ere sta$ili8ed this!a, or used mass distri$ution to achie%e tidal sta$ili8ation( This is a simple "orm o" sta$ili8ation that

'5
http://fixedreference.org/en/20040424/wikipedia/Spacecrafthttp://fixedreference.org/en/20040424/wikipedia/Spacecrafthttp://www.tethers.com/EDTethers.htmlhttp://www.tethers.com/EDTethers.htmlhttp://fixedreference.org/en/20040424/wikipedia/Carbon_nanotubehttp://fixedreference.org/en/20040424/wikipedia/Satellitehttp://fixedreference.org/en/20040424/wikipedia/Tidal_forceshttp://fixedreference.org/en/20040424/wikipedia/Spacecrafthttp://www.tethers.com/EDTethers.htmlhttp://fixedreference.org/en/20040424/wikipedia/Carbon_nanotubehttp://fixedreference.org/en/20040424/wikipedia/Satellitehttp://fixedreference.org/en/20040424/wikipedia/Tidal_forces


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uses no electronics, rockets or "uel( A small $ottle o" "luid must $e mounted in the spacecra"t to damp%i$rations(

2. lectrodyna"ic tether!.An electrodnamic tether conducts current in order to act against aplanetar magnetic "ield( >tHs a simpli"ied, %er lo!-$udget magnetic sail(The tether inducts the arthHsmagnetic "ield electric "orce to use as po!er and produce su$stantial !ork( =hen a conducti%e tether is

trailed in a planetar or solar magnetosphere5magnetic "ield6, it generates a current, and there$ slo!sthe spacecra"t into a lo!er or$it( The tetherHs end can $e le"t $are( This is su""icient to make contact!ith the ionosphereand allo! a current to "lo!( A circuit in electrodnamic tethers can $e used as aphantom loop, !ith a cathode tu$es placed at the ends o" the tethers( A dou$le-ended cathode tu$etether !ill allo! alternating currents(

A similar concept !as used in the9irele!! tran!"i!!ion o energy(

lectrodnamic tethers $uild up %i$rations "rom %ariations in magnetic and electric "ields( #ne planto control these is to %ar the tether current to oppose the %i$rations( >n simulations, this keeps thetether together( ? channelling direct current through a tether, the spaceship can $e mo%ed into ahigher or$it(

'
http://fixedreference.org/en/20040424/wikipedia/Magnetic_fieldhttp://fixedreference.org/en/20040424/wikipedia/Magnetic_sailhttp://fixedreference.org/en/20040424/wikipedia/Magnetospherehttp://fixedreference.org/en/20040424/wikipedia/Ionospherehttp://fixedreference.org/en/20040424/wikipedia/Phantom_loophttp://fixedreference.org/en/20040424/wikipedia/Cathodehttp://fixedreference.org/en/20040424/wikipedia/Vacuum_tubehttp://fixedreference.org/en/20040424/wikipedia/Tesla_coilhttp://fixedreference.org/en/20040424/wikipedia/Tesla_coilhttp://fixedreference.org/en/20040424/wikipedia/Direct_currenthttp://fixedreference.org/en/20040424/wikipedia/Magnetic_fieldhttp://fixedreference.org/en/20040424/wikipedia/Magnetic_sailhttp://fixedreference.org/en/20040424/wikipedia/Magnetospherehttp://fixedreference.org/en/20040424/wikipedia/Ionospherehttp://fixedreference.org/en/20040424/wikipedia/Phantom_loophttp://fixedreference.org/en/20040424/wikipedia/Cathodehttp://fixedreference.org/en/20040424/wikipedia/Vacuum_tubehttp://fixedreference.org/en/20040424/wikipedia/Tesla_coilhttp://fixedreference.org/en/20040424/wikipedia/Direct_current


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'. Roto$ator!. A roto%ator is a rotating tether( A spacecra"t in one or$it ats angular momentum can$e charged electricall "rom solar or nuclear po!er, $ running current through a !ire that goesthe length o" the tether( =hen the tether turns o%er, the direction o" current must re%erse to actagainst the magnetic "ield( 9ltimatel, such a tether pushes agains the angular momentum o" theplanet(

Roto%ators can also $e charged $ momentume7change( 4omentum charging uses the rota%ator tomo%e mass "rom a place thatHs higher in the gra%it !ell to a place that is lo!er in the gra%it!ell( The energ "rom the "alling !eight speeds up the rotation o" the rota%ator( For e7ample, itis possi$le to use a sstem o" t!o or three roto%ators to implement trade $et!een the 4oonand

arth( The roto%ators are charged $ lunar mass 5dirt, i" imports are not a%aila$le6 dumped onarth, and use the momentum so gained to $oost arth goods $ack to the 4oon(

A rota%ator can pick up a mo%ing %ehicle and sling it into or$it( For e7ample, a rota%ator could pickup a 4ach-'2aircra"t "rom the upper atmosphere o" the arth, and mo%e it into or$it !ithoutusing rockets( >t could like!ise catch such aircra"t, and lo!er them into atmospheric "light( Animportant practical modi"ication o" a roto%ator !ould $e to add se%eral latch points, to achie%edi""erent momentum trans"ers( This is a %er %alua$le option, gi%en that such per"ormanceother!ise re@uires e7tremel e7otic spacecra"t propulsionsstems(

. Space ele$ator!5$eanstalks6 ma $e considered as a special case !hen the tether sstem is aroto%ator po!ered $ the spin o" a planet( For e7ample, on arth, a $eanstalk !ould go "rom thee@uator to geosnchronous or$it(

/. *ro+le"!. Simple tethers are @uickl cut $ micrometeoroids( The li"etime o" a one-strand tetherin space is on the order o" hours "or a length o" '0 km( Se%eral sstems ha%e $een proposed tocorrect this( The 9(S( Na%al Research La$ has success"ull "lo!n a longterm tether that used %er"lu"" arn( This is reported to remain uncut se%eral ears a"ter deploment( Another proposal is to usetape or cloth(

Roto%ators are currentl limited $ the strengths o" a%aila$le materials( The ultra-high strength plastic"i$ers 5/e%larand Spectra6 permit roto%ators to pluck masses "rom the sur"ace o" the 4oon and4ars(Roto%ators made "rom these materials cannot li"t masses "rom the sur"ace o" the arth( Tethers ha%eman modes o" %i$ration, and these can $uild to cause stresses so high that the tether $reaks(4echanical tether-handling e@uipment is o"ten surprisingl hea%, !ith comple7 controls to damp%i$rations( lectrodnamic tethers can $e sta$ili8ed $ reducing their current !hen it !ould "eed theoscillations, and increasing it !hen it opposes oscillations(

':
http://fixedreference.org/en/20040424/wikipedia/Angular_momentumhttp://fixedreference.org/en/20040424/wikipedia/Angular_momentumhttp://fixedreference.org/en/20040424/wikipedia/Solar_systemhttp://fixedreference.org/en/20040424/wikipedia/Solar_systemhttp://fixedreference.org/en/20040424/wikipedia/Sunhttp://fixedreference.org/en/20040424/wikipedia/Momentumhttp://fixedreference.org/en/20040424/wikipedia/Moonhttp://fixedreference.org/en/20040424/wikipedia/Earthhttp://fixedreference.org/en/20040424/wikipedia/Mach_numberhttp://fixedreference.org/en/20040424/wikipedia/Spacecraft_propulsionhttp://fixedreference.org/en/20040424/wikipedia/Meteoritehttp://fixedreference.org/en/20040424/wikipedia/Kevlarhttp://fixedreference.org/en/20040424/wikipedia/Mars_(planet)http://fixedreference.org/en/20040424/wikipedia/Vibrationhttp://fixedreference.org/en/20040424/wikipedia/Angular_momentumhttp://fixedreference.org/en/20040424/wikipedia/Angular_momentumhttp://fixedreference.org/en/20040424/wikipedia/Solar_systemhttp://fixedreference.org/en/20040424/wikipedia/Solar_systemhttp://fixedreference.org/en/20040424/wikipedia/Sunhttp://fixedreference.org/en/20040424/wikipedia/Momentumhttp://fixedreference.org/en/20040424/wikipedia/Moonhttp://fixedreference.org/en/20040424/wikipedia/Earthhttp://fixedreference.org/en/20040424/wikipedia/Mach_numberhttp://fixedreference.org/en/20040424/wikipedia/Spacecraft_propulsionhttp://fixedreference.org/en/20040424/wikipedia/Meteoritehttp://fixedreference.org/en/20040424/wikipedia/Kevlarhttp://fixedreference.org/en/20040424/wikipedia/Mars_(planet)http://fixedreference.org/en/20040424/wikipedia/Vibration


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9ne7pected electrostatic discharges ha%e cut tethers, damaged electronics, and !elded tetherhandling machiner(

(eferen0es for Cha#ter 45

'( dited $ Cosmo 4(L( and Loren8ini (C((Tethers in S#a0e "and-ook( 3rd dition( SmithsonianAstrophsical #$ser%ator( Gecem$er, '..*(

2( Xiegler S(=(and Cartmell 4(&(, E9sing 4otori8ed Tethers "or &aload #r$ital Trans"er,Journal ofS#a0e0raft and (o0kets, Vol(3, No ), 200'(

3( d!ards, ?radle C(, EGesign and Geploment o" Space le%ator(A0ta Astronauti0a, Vol( +*, No('0, pp( *3*++, 2000(

+( Smitherman G(V( Kr(, ESpace le%ators, NASABC&-2000-2'0+2.(( &almer 4(R(, EA re%olution in Access to Space Through Spino""s o" SG> Technolog,IEEE

Transa0tions on 'aneti0s, Vol( 2*, No( ', Kanuar '..', pp(''20()( &almer 4(R(, Economics and Technolog >ssues "or 1un Launch to Space, S#a0e Te0hnoloy,

'..), part 3, pp( ).**02(*( 1alasso F(S(,Advan0ed Fi-ers and Com#osite, 1ordon and ?ranch Science &u$lisher, '..(( Car-on and "ih Performan0e Fi-ers, Dire0tory,'..(.( Con0ise En0y0lo#edia of Polymer S0ien0e and Enineerin, d( K(>( /rosch!it8, '..0('0( Gresselhous 4(S(, Car-on &anotu-es, Springer, 2000(''( Anderson, K(G(,"y#ersoni0 and "ih Tem#erature 6as Dynami0s, 4cCro!-;ill ?ook Co(, '..('2( ?olonkin, A(A(, ;personic 1as-Rocket Launch Sstem(, A>AA-2002-3.2*, 3th

A>AABAS4BSABAS Koint &ropulsion Con"erence and 7hi$it, *-'0 Kul 2002( >ndianapolis,>N, 9SA(

'3( ?olonkin, A(A( >ne7pensi%e Ca$le Space Launcher o" ;igh Capa$ilit, >AC-02-V(&(0*,3rd >nternational Astronautical Congress, The =orld Space Congress 2002, '0'. #ct

2002( ;ouston, Te7as, 9SA('+( ?olonkin, A(A, ENon-Rocket 4issile Rope Launcher, >AC-02->AA(S(&('+, 3rd >nternationalAstronautical Congress, The =orld Space Congress 2002, '0'. #ct 2002( ;ouston, Te7as(

'( ?olonkin, A(A(, E;personic Launch Sstem o" Capa$ilit up 00 tons per da and Geli%er Cost' per l$( >AC-02-S(&(', 3rd >nternational Astronautical Congress, The =orld Space Congress 2002, '0'. #ct 2002( ;ouston, Te7as(

')( ?olonkin, A(A(, Emploment Asteroids "or 4o%ement o" Space Ship and &ro$es( >AC-02-S()(0+,3rd >nternational Astronautical Congress, The =orld Space Congress 2002, '0'. #ct 2002(;ouston, Te7as(

'*( ?olonkin, A(A(, ENon-Rocket Space Rope Launcher "or &eople, >AC-02-V(&(0), 3rd>nternational Astronautical Congress, The =orld Space Congress 2002, '0'. #ct 2002, ;ouston,

Te7as('( ?olonkin, A(A(, E#ptimal >n"lata$le Space To!ers o" ;igh ;eight( C#S&AR 02-A-0222,3+th Scienti"ic Assem$l o" the Committee on Space Research 5C#S&AR6, The =orld SpaceCongress 2002, '0'. #ct 2002( ;ouston, Te7as(

'.( ?olonkin, A(A(, ENon-Rocket arth-4oon Transport Sstem, C#S&AR-02 ?0(3-F3(3-0032-02,02-A-0222), 3+th Scienti"ic Assem$l o" the Committee on Space Research 5C#S&AR6( The =orldSpace Congress 2002, '0'. #ct 2002( ;ouston, Te7as(

20, ?olonkin, A(A(, ENon-Rocket arth-4ars Transport Sstem, C#S&AR 02-A-0222+, 3+thScienti"ic Assem$l o" the Committee on Space Research 5C#S&AR6( The =orld Space Congress 2002, '0'. #ct 2002( ;ouston, Te7as(


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2'( ?olonkin, A(A(, ETransport Sstem "or deli%er Tourists at Altitude '+0 km( >AC-02->AA('(3(03,3rd >nternational Astronautical Congress( The =orld Space Congress 2002, '0'. #ct 2002(;ouston, Te7as(

22( ?olonkin, A(A(, Non-Rocket Transport Sstem "or Space Tra%el,JBIS, Vol( ), No( *B, 2003, pp(23'2+.(

See Re"erences*, ( ., '0

(

0hapter 2

0a+le Space Accelerator;

Su""ary

A method and "acilities "or deli%ering paload and people into outer space are presented( This methoduses, in general, engines and a ca$le located on a planetar sur"ace( The installation consists o" a spaceapparatus, po!er dri%e stations located along the tratre@uires a %acuum underground tunnel '30 kilometers long located at a depth o" +0 kilometers( The

1


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pro


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The ca$le includes three parts 5Fig( 2(26: directi%e part, inlet part, and main 5pull6 part( The lengths o"the inlet and main parts e@ual the distance $et!een dri%e stations, the directi%e part controls onl itsel"(>t directs the inlet part to the dri%e stations( >ts length e@uals the "ull acceleration distance minus theinlet and pull parts( This design allo!s the use the current "i$ers and minimi8es the ca$le mass andenerg(

Fig. 2.2.#ptimal ca$le cross-sectional area along the launch distance(

The ca$les are made "rom light strong material such as arti"icial "i$ers, "ilaments, !hiskers, andnanotu$es( The $etter the ca$le properties the less the installation re@uires in terms o" the dri%estations, ca$le mass and energ(The rollers are made "rom strong matter such as a composite material(

Ad$antage!(The suggested launch ca$le sstem has $ig ad%ances in comparison !ith current rocketsstems:'( The ca$le launcher is cheaper $ se%eral times than the modern rocket launch sstem( No

e7pensi%e rockets are needed(2( The ca$le launcher decreases the deli%er cost $ some thousand times 5up to '2 per pound6(3( The ca$le launcher can $e made in one ear( 4odern rocket launch sstems re@uires some ears "or

de%elopment, design, and $uilding(+( The ca$le launcher does not re@uire high technolog and can $e made $ an non-industrial

countr(( Rocket "uel is e7pensi%e( The ca$le launcher can use the cheapest sources o" energ such as !ind,

!ater, or nuclear po!er, or the cheapest "uels such as gas, coal, peat, etc(, $ecause the engine islocated on the arthDs sur"ace( The "l!heels ma $e used as an accumulator o" energ(

)( >t is not necessar to ha%e highl @uali"ied personnel such as rocket specialists !ith high salaries(*( The "are "or the space tourists is small(( There is no pollution o" the atmosphere "rom to7ic rocket gas(.( Thousands o" tons o" use"ul loads can $e launched annuall('( 0a+le di!cu!!ing. The reader can "ind the ca$le discussing in Chapter ' and ca$le characteristics

in Re"erences.( >n our pro


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,'0,'e7p,,e7p

,,ln,,

*

0

0

''

0

'0'

'

'''''

'

0

=

====

======

K%n

m*nm

S%n

S

SSor

d%S*n

Sd%n

S

dSdSd%SnndmdF

%

%S

S

52('6

!here S'is the cross-section ca$le area o" main part Qm2 Sois the cross-section area o" ca$le near

the ship Qm2

nis the o%erload .(' mBs2

is gra%it is the tensile stress QNBm2

is thespeci"ic densit QkgBm3%is the distance $et!een po!er stations Qm mis the mass o" apparatusQkg m'is the mass o" the main ca$le part Qkg *is the ca$le !eight QkgKis the stresscoe""icient( The result o" the computation is sho!n in Figs( 2(3 to 2(*(

Fig. 2.'( Relati%e ca$le cross-sectional area %ersus the distance $et!een dri%e stations "or stress

coe""icientK 0('0( 5K '0*B6 and o%erload 3g(


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Fig. 2.( Ca$le mass %ersus distance $et!een dri%e stations "orK 0('0(, o%erload 3g, space shipmass ' tons(

Fig. 2./( Relati%e ca$le cross-sectional area %ersus distance $et!een dri%e station "orK ',o%erload 3g( A high stress coe""icient allo!s a decrease in the dri%e station distance 5compare!ith Fig( 2(36(

Fig. 2.3( Relati%e ca$le cross-sectional area %ersus the distance $et!een dri%e stations "or stress

coe""icientK 0('0( 5K '0*B6 and o%erload 2)*g, pro


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Fig. 2. 5( Ca$le mass %ersus distance $et!een dri%e stations "orK 0('0(3, o%erload 2)*g, andapparatus mass '00 kg(

$6 For the inlet part o" the ca$le the noted %alues are

( )

+=

==

===

=

==

'e7pe7p,e7p'e7p

,,,

,e7p'e7p,e7p

'

'

'

0

'

0

2

2

0

22

20

'2'022

'

%n

n%

%n

S*

n%n

S

S

S

ord%S*F

Snm

S

%n

%n

nmFd%%%n

SnndmdF

%

52('a6!here%'is the distance $et!een dri%e stations Qm(F2 is the "orce in the inlet ca$le part QN, and m2is the mass o" the inlet ca$le part( The inlet part introduces the main part to an inlet o" the dri%estation(c6 The directi%e part directs the inlet part to an inlet o" the dri%e station and supports onl itsel"( Thispart can $e thin and has a constant cross-section( The optimal ca$le cross section area is sho!n in "ig(2(2(

2. Saety ca+le !peed( Let us take a small part o" the rotar circle and !rite the $alance

,sin22 2

S

(

)S(=

!here )is the rotar ca$le speed QmBs, (is the circle radius Qm, and is the angle $et!een the

ends o" the circle part Qrad( >" 0 the relationship $et!een ma7imum rotational speed )and tensilestress o" the closed loop 5cur%e6 ca$le is

=) . 52(26

'. nergy,E, storage $ the rotar "l!heel per ' kg ca$le Q


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2

'

2

2

==)

E ( 52(36

. 4he "axi"u" di!tance%Qkm $et!een supports o" the suspension sstem 5!ithout !ings6 "or h

" x 0, then - ! "2( >"y 0, thenx ! 8 %B2( =e also

ha%e the $alance e@uation * ! 2Tsinor sin *$2T( =e su$stitute these e@uations and put tg

sin( The ca$le sag,"2, under its !eight is the as

T

%S

T

%S%

T

*%%%

%"

---+2

tan 22

2

====

=

The sag "rom the arthDs cur%ature is"'! %2$("rom e@uation 52(+6,and the total sag is

Y

+=

++=

(

%

(T

S%"""

'

-

'

-

22

2'

, 52(6

!here "is the sag o" the ca$le Qm%is the distance $et!een supports Qm Tis the tension o" theca$le Qkg, Sis the cross-section ca$le area Qm2,(is the arthDs radius Qm, *is the ca$le !eightQkg(

3. The estimation o" ma7imum hori8on light range, r,o" the !inged pro==

==

===

'

''fore

9

h0

9"Aa')'

0CA

)CDdA

)"CdD

-"

DDD

52(*6

!hereDis the air drag QN,'is the 4ach num$er, a const the speed o" sound QmBs, CDis thedrag coe""icient,Ais the speci"ic area Qm2, )is the ca$le speed QmBs, 0 ! h'$9 is the ratio a

thickness, h', to !idth, 9, o" an edge tpe ca$le, QkgBm3 is the air densit at altitude"Qm,

const theangle o" the ca$le to the hori8on,- '(3''('0+ the coe""icient o" change o" air

densit !ith altitude,o '(22 the air densit at" 0(

Let us su$stitute e@uations 52(*6 in the "irst e@uation "orDgi%en a$o%e and integrate this "or theinter%al o" altitude "rom"0to"5

( ) 65sin2

65sin2

sin2 00

0

(0('

0

2

02 -"-"-"-"

"

"

ee-

Sa)0ee

-

9a)0d"")9a0D ===

, 52(6

!here S ! 9h'Qm2 is the ca$le cross-section area(

( Lo!!) QmBso !peed, !hen a pro


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===="

"

-"-"-"

"

"

D ee-

a)AF0d"e

a)AF0EF

)CDd"

DE

0

0

0

6(5sin

2

sin

2,

2,

sin

0

2

'0

2

'2

For other cases the amount o" energ lost,E, is

)))

m

E))))

mE === '

2

'

2

'

2 ,2

6,5

2

,

or

65sin

2,

200

22 -"-"

ee-

a)F0E

m

E))) ==

, 52(.6

!here )is the initial speed o" the proCf.l;)?S @ DT! =.>Cf.t;)?S , S!d.=here T;,(e;,;,;are re"erence 5e%aluated6 temperature, Renolds num$er, air densit, and air

%iscosit respecti%el('is 4ach num$er, ) is speed,xis length o" plate 5distance "rom the$eginning o" the ca$le6, Tis "lo! temperature, T9is $od temperature, Cf.lis a local skin "rictioncoe""icient "or laminar "lo!, Cf,tis a local skin "riction coe""icient "or tur$ulent "lo!( Sis area o"


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skin Qm2 o" $oth plate sides 5this means "or the ca$le !e must take 0(S6 andDis air drag 5"riction6QN( >t ma $e sho!n that the general air drag "or the ca$le e@ualsD 0(DT 10(D%, !hereDTistur$ulent drag andD%is laminar drag(

From e@uation 52('06 !e can deri%e the "ollo!ing e@uations "or tur$ulent and laminar "lo!s o" ahori8ontal ca$le

DT ! 0(0+);0(;0(2)'.%0.d , 52(''6

D% ! 0(2';0(

;0(

)'.

%0.

d . 52('26

=here dis the diameter o" the ca$le Qm( The laminar drag is less than the tur$ulent drag $ 200300 times and can $e neglected(Let us note: i"%ois the "ull acceleration distance 5initial length o" ca$le6 Qm,%'is the distance$et!een dri%e stations Qm, and% is the %aria$le length o" ca$le Qm, !e can !rite the "ollo!inge@uations "or tur$ulent drag o" the di""erent ca$le parts:'6 4ain ca$le part a6 >" = % :%0%'" 5%0%'6 % %0, then D' ! B. 5%0%60(d'.

26 >nlet ca$le part a6 >" 0 % \ 5%0 2%'6 , then D2! B

.%'0(d2.

$6 >" 5%0 2%'6 % \ 5%0%'6 , then D2 ! B.5%0%60(d2. c6 >" 0 % 5%0 2%'6 , then D2 0 (36 Girecti%e part a6 >" 0 % \ 5%0-2%'6 , then D3 ! B.5%0%60(d3. $6 >" 5%0 2%'6 % %0, then D3! = . ;ere d', d2, d3are a%erage ca$le diameters o" the main, inlet, and directi%e parts respecti%el Qm(Full ca$le drag is thus

D ! D' 1 D21 D3( 52('36'0( >a!! o ca+leis

6R25Q+

'023'

22'

2'32' %%d%d%d'''' ++=++= ( 52('+6

The accelerated ca$le mass is

32' '2(0 ''''a ++ , 52('6!here the coe""icient 0('2 is the product o" an a%erage length 50(6 and an a%erage speed 50(26 o" thedirecti%e ca$le part(''( The energyre@uired $ the ca$le air drag is

=0

0

%

Dd%E ( 52(')6

The results o" computations o" e@uations 52('36 to 52('6 are presented in Fig( 2(. to 2('+ "or t!o

pro


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Fig. 2.( stimation o" %elocit lost $ a pro


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Fig. 2.1( Ca$le mass %ersus the initial ca$le diameter at ship '02 mm, "or distance $et!een dri%e

stations%' '0 km, o%erload n 3g, d3 ' mm, a%erage altitude" 2 km

Fig. 2.11( Ca$le air drag energ %ersus the initial ca$le diameter at ship '02 mm, "or distance$et!een dri%e stations%' '0 km, o%erload n 3g, d3 ' mm, a%erage altitude" 2 km, )max *(.3) kmBs(

/1


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Fig. 2.12( Ca$le drag along the acceleration distance "or initial ca$le diameter at ship do '02 mm,ca$le diameter o" part 3 d3 ' mm, o%erload n 2)*g, at altitude 2 km(

Fig. 2.1'( Ca$le mass %ersus the initial ca$le diameter at ship '02 mm, "or distance $et!een dri%estations%' 0(' km, o%erload n 2)*g, d3 ' mm, altitude" 2 km(

/2


53/396


Fig. 2.1( Ca$le air drag energ %ersus the initial ca$le diameter at ship '02 mm, "or distance$et!een dri%e stations%' 0(' km, o%erload n 2)*g, d3 ' mm, altitude" 2 km, )max kmBsec(

12.For su$sonic speed the "ormulas 52(''6 to 52('26 are the same, $ut con%entional andmust $einserted( 1'.The last dri%e station can $e located on a mountain top( The "inal ship tra


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Fig!. 2.1/. Final tra


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*ro=ect 14he Launch o 4ouri!t! into Space &Fig. 2.1a, Single 0a+le ?er!ion(

Assume the mass o" the space %ehicle is m ' tons 5'00 tourists and + mem$ers o" cre!6 o%erload is

n 3 Eg, the acceleration is a ! 30 mBs 5 .(' '0 mBs265this acceleration is sa"e "orcon%entional purposes6 the "inal speed is kmBs(

The re@uired distance o" acceleration is% ! )2$2a'0*0 km( The time o" hori8ontal acceleration is t! )$a + min 2* sec( 5>" trained cosmonauts are launched the sa"e acceleration can $e taken as andthe re@uired launch distance !ill $e +00 km and the time ' min +0 sec(6( The time o"%ertical acceleration 536 in the atmosphere 5a"ter disconnection6 is a$out 0 seconds( The "inal angle

is a$out '2( Assume !e use the arti"icial cheap "i$er !idel produced $ current industr( Sa"e tensile strength o"

the %ehicle ca$le is '0 kgBmm25sa"et "actor is n' )00B'0 3(336, densit '00 kgBm35K '0B'00 0('6( Then the cross-section area o" the %ehicle ca$le a$out the %ehicle !ill $e S0!

nm$ 20 mm2, diameter do 25SB60( '*( mm, a%erage diameter is a$out do,a '. mm(Let us assume that the dri%e stations are located e%er%' '0 km( =e need '0* dri%e stations( The

"inal dri%e station is located at altitude"0 + km( 4ass o" the ca$le is' * tons, accelerated ca$lemass is'a () tons 5Fig( 2('06( A %aria$le cross-section areas o" main and inlet ca$les are included inthe a%erage diameter( The energ re@uired "or accelerating the ship and ca$le isE ! 5m1'a6)2B2 ! ).'0. K 5).1iga" the sa"e tensile strength is '0 kgBmm2

, then the total masso" the "l!heels 5as energ o" storage6 !ill $e a$out'9 ! 2E$k 2+'0.B'0) '*) tons or'*)B'0* ')( tons "or each dri%e station(

cono"ic eiciency

Assume a cost o" 00 millions dollars "or the installation'', a li"e time o" '0 ears, and an annualmaintenance cost o" million dollars( >" '00 tourists are launched on e%er "light, and there is one"light e%er hour "or 30 das a ear, then +0,000 passengers !ill $e launched per ear( The launchcost "or one passenger is ,000,000B+0,000 )( plus "uel cost( >" *00 liters o" "uel are used "or 'passenger and the "uel price is 0(2 per liter, then the "uel cost is '* dollars per passenger( The total

production cost !ill then $e 2+' per person( >" the ticket is sold "or 3+., then the pro"it !ill $e a$out.0 million dollars per ear(

An reader !ho does not agree !ith this estimation can recalculate "or other data( >n an case, thecost o" deli%er !ill $e hundreds o" times less than deli%er $ rockets( Critics must remem$er that themain content o" this chapter is not economical estimations, $ut the ne! idea "or the launch o" spaceapparatus(

*ro=ect 2

4he Launcher or *ayload &*ro=ectile( 9ith igh Acceleration &235g(&Fig. 2.1+(

//


56/396


=e can use the e@uations "rom &ro" the "re@uenc o" launching is 0( hours then the re@uired

total po!er is 200 k= or 200B'20 23(3 k= "or e%er dri%e station( The total mass o" "l!heels isa$out '0 tons or +(3 kg in e%er station( The loss o" %elocit is 2* mBs !hen the pro


57/396


0hapter '

0ircle Launcher and Space @eeper;

Su""ary

>n this chapter proposes a ne! method and installation "or "light in space( This method uses thecentri"ugal "orce o" a rotating circular ca$le that pro%ides a means to launch a load into outer space andto keep the stations "i7ed in space at altitudes at up to 200 km( The proposed installation ma $e usedas a propulsion sstem "or space ships andBor pro$es( This sstem uses the material o" an space $od"or acceleration and changes to the space %ehicle traAA('(3(03 at the =ould Space Congress-2002,'0-'. #cto$er, ;ouston, TM, 9SA( The material is pu$lished inJBIS, %ol( ), No .B'0, 2003, pp( 3'+-32*(

/5


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No"enclature

a acceleration, mBs,

Cf,l local skin "riction coe""icient o" a t!o-sided plate "or laminar "lo!,Cf,t local skin "riction coe""icient o" a t!o-sided plate "or tur$ulent "lo!,C0,l!0(Cf,l local skin "riction coe""icient o" ca$le "or laminar "lo!,

C0,t 0(Cf,t local skin "riction coe""icient o" ca$le "or tur$ulent "lo!,Dair drag 5"riction6 QN(

DTtur$ulent drag QN,D%laminar drag QN,dca$le diameter Qm,

E IoungDs modulus,

Esenerg stored $ rotar circle per ' kg o" the ca$le QKBkg,F air "riction QN,

speci"ic gra%it o" the planet, mBs2 5"or the arth .(' mBs2at an altitude" 06,6 local load Qkg,"altitude Qm or Qkm(

"maxma7imam altitude o" a circle top Qm or Qkm" decrement o" an altitude Qm or Qkm,

k ! $ ratio o" tensile stress to ca$le densit,K ! kB'0*strength coe""icient,%length o" a ca$le Qm,'4ach num$er,

mthro!ing mass Qkg,mssmass o" a space ship Qkg,nsa"et "actor,&po!er QKBs(#internal pressure on the ca$le circle QNBm2,

Pma7imum %ertical li"t "orceo" the %ertical ca$le circle in the constant gra%it "ield o" a planet QN,P'speci"ic li"t "orce o" ' kg o" ca$le mass in a planetDs gra%it "ield QN,P%speci"ic li"t "orce o" ' m o" ca$le in a planetDs gra%it "ield QN,Pa"ull li"t "orce o" a closed-loop ca$le circle rotated around a planet QN,Pa,'speci"ic li"t "orce o" a ' kg closed-loop ca$le circle rotated around a planet QN,Pa,%speci"ic li"t "orce o" a ' m closed-loop ca$le circle rotated around a planet, !hen 0 QN,Pmax ma7imum li"t "orce o" the rotar closed-loop ca$le circle !hen gra%it 0 QN,r radius o" ca$le cross-section area or hal" o" ca$le !idth Qm,(ca$le 5circular6 radius Qm,(max ma7imum ca$le radius Qm,(oradius o" planet Qm,

(v radius o" o$ser%ation Qm,(e;re"erence Renolds num$er,

Scross-section area o" ca$le Qm2,S0ca$le sur"ace Qm2,Ssarea o" skin Qm2 o" $oth plate sides, !hich means "or ca$le !e must take S0 0(Ss,T air temperature QoC,T;re"erence 5e%aluated6 air temperature QoC,T9 temperature o" !all 5ca$le6 QoC,Tetemperature o" "lo! QoC,Tmaxma7imum ca$le thrust Qkg,

/


59/396


t time Qseconds,)rotar ca$le speed QmBs,)a ma7imum speed o" a closed-loop circle around a planet QmBs,)min minimum speed o" a closed-loop circle QmBs,)0mass speed QmBs,)f speed o" "alling "rom an altitude"QmBs,

*!eight 5mass6 o" ca$le Qkg or Qton,9 thickness o" a $oundar laer Qm, "or ca$le9 r,x length o" plate 5distance "rom the $eginning o" the ca$le6 Qm,

hca$le de"ormation a$out a local load Qm,

hoca$le de"ormation a$out a local load "or the ca$le circle around a planet Qm,

(increase in ca$le radius "rom internal pressure Qm,

)additional speed !hich a space ship o$tains "rom a ca$le propulsion sstem QmBs(

angle o" ca$le section Qrad,

h ca$le angle to the hori8on a$out a local load Qrad,ca$le densit QkgBm3,

air %iscosit "or standard conditions '(*2(

'0

,; re"erence air %iscosit QkgBm(s,

air densit "or standard condition '(22 kgBm3

;re"erence air densit QkgBm3,

ca$le tensile stress QNBm2,

planet angle speed QradBseconds(

%ntroduction

The author proposes a re%olutionar ne! method and launch de%ice "or: 5'6 deli%ering paloads andpeople into space, 526 accelerating space ships and pro$es "or space "light, 536 changing the tra


60/396


is connected to the ca$le circle $ a sliding connection the lo!er end is connected to a load motor( Theload is connected to the load ca$le $ a sliding control connection(

Fig. '.1. Circle launcher 5space station keeper6 and space transport sstem( Notations are: 'ca$le circle, 2main engine, 3 transport sstem, +top roller, additional ca$le, )the load 5space station6, *mo$ile ca$in, lo!er roller, .engine o" the transport sstem(

The installation can ha%e an additional ca$les to increase the sta$ilit o" the main circle, and thetransport sstem can ha%e an additional ca$le in case the load ca$le is damaged(

The installation !orks in the "ollo!ing !a( The main engine rotates the ca$le circle in the %erticalplane at a su""icientl high speed so the centri"ugal "orce $ecomes large enough to it li"ts the ca$le andtransport sstem( A"ter this, the transport sstem li"ts the space station into space(

The "irst modi"ication o" the installation is sho!n in Fig( 3(2( There are t!o main rollers 20, 2'( These

rollers change the direction o" the ca$le $ .0 degrees so that the ca$le tra%els along the diameter o"the circle, thus creating the "orm o" a semi-circle( >t can also ha%e t!o engines( The other parts aresame(

Fig. '.2. Semi-circle launcher 5space station keeper6 and transport sstem( Notation is the same!ith Fig( 3(' !ith the edditional 20 and 2'rollers( The semi-circle is the same 5see right sideo" Fig( 3(+6(

3


61/396


The installation can $e used "or the launch o" a paload to outer space 5Fig( 3(36( The load isconnected to the ca$le circle $ a sliding $earing through a $rake( The load is accelerated $ the ca$lecircle, li"ted to a high altitude, and disconnected at the top o" the circle 5semi-circle6(

The installation ma also $e used as transport sstem "or deli%er o" people and paloads "rom oneplace to another through space 5Fig( 3(+6(

Fig. '.'.Launching the space ship 5pro$e6 into space using ca$le semi-circle( 2*load, 2 %acuum tu$e5option6(

Fig. '.. Gou$le semi-circle !ith opposed speeds "or deli%er o" load to another semi-circle end( 2. -Roller(

The dou$le ca$le can $e used as an e7cellent launch sstem, !hich generates a ma7imum speed threetimes the speed o" the ca$le( The launch sstem has a space pro$e 5Fig( 3(6 connected to the semi-circular ca$le and to a launch ca$le( The launch ca$le is connected through a roller 5$lock6 to the mainca$le( A tackle $lock is used in !hich the ma7imum speed is three times more then the ca$le speed(

The ma7imum ca$le speed depends on the tensile strengths o" the ca$le material( Speeds o" +) kmBscan $e achie%ed using modern "i$ers, !hiskers, and nanotu$es 5see attached pro


62/396


Fig. './. Launching a load into space !ith a triple circle rope speed using the dou$le semi-circle(

Notations are: 3'space pro$e, 32engine, 33launch ca$le, 3+roller, 3connection point o" thelaunch ca$le, '), '*semicircle(

Fig. '.3.Supporting the semi-circle in %ertical position 5"or sta$ilit6( 3guide ca$le(

The ship installation ma $e used as a sstem "or %ertical landing on or taking-o"" 5launch6 "rom aplanet or asteroid $ecause the ca$le circle can !ork like a spring(

The ca$le circle o" the space ship can $e used as a propulsion sstem 5Fig( 3(*6( The propulsionsstem !orks in the "ollo!ing !a( 4aterial "rom asteroids or meteorites, or gar$age "rom the ship, ispacked in small packets( A packet is connected to the ca$le circle( then circle engine turns on androtates at high speed( At the desired point the pack is disconnected "rom the circle and, as the e


63/396


Fig. '.5. 9sing the rope circle as a propulsion sstem( Notations are: +0gar$age, +'space ship(

Fig. '..Ca$le circle around the arth "or '0 space o$


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Fig. '.:. Sstem "or changing the radius o" the circle circle( Notations are: 230 sstem "or radiuscontrol, 23+ engine, 23) mo$ile tackle $lock, 2++ transport sstem, 2+) engine, 2+ circle, 20 guide ca$le(

=ith the radius sstem the pro$lem o" creating the ca$le circle is sol%ed %er easil( 7pensi%erockets are not necessar( The operator starts !ith a small radius near the planet sur"ace and increasesit until the desired radius is achie%ed( This method ma $e used "or making a semi-circle or dou$lesemi-circle sstem(

The small installation ma $e used as a crane "or construction engineering, de%eloping $uilding,

$ridges, in the logging industr, and so on( The main ad%antage o" the proposed launch sstem is its %er lo! cost "or the amount o" paloaddeli%ered into space and o%er long distances( 7pensi%e "uels, comple7 control sstems, e7pensi%erockets, computers, and comple7 de%ices are not re@uired( The cost o" paload deli%er into space!ould drop $ a "actor o" a thousand( >n addition, large amounts o" paloads could $e launched intospace 5in the order o" a thousand tons a ear6 using a single launch sstem( This launch sstem issimple and does not re@uire high-technolog e@uipment( The paloads could $e deli%ered into space atproduction costs o" 2'0 dollars per kg 5see computations in the attached pro


65/396


) ! 5/6'B2! k'B2. 53('6 Results o" this computation are presented in Fig( 3('0( 4a7imum li"t "orcePmax o" the rotar closed-loop circle ca$le !hen the gra%it 0 e@uals the ca$letensile "orce is:

Pmax! 2)2S ! 2S . 53(26 The ma7imum %ertical li"t "orcePo" the %ertical ca$le circle in the constant gra%it "ield o" a planet

e@uals the li"t "orce in e@uation 53(26 minus the ca$le !eight

P ! 2S5 (6. 53(36 The ma7imum li"t "orcePo" the dou$le semi-circle ca$le in the gra%it "ield o" a planet is

P ! +S5 0((6 ( 53(3a6

Appro7imatel one @uarter o" this "orce can $e used( The results o" computation are presented in Fig(3(''(

3/


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The minimum speed o" the ca$le circle can $e "ound "rom e@uations 53(36 and 53('6 "orP 0

() min ( 53(+6

7ample: For( 0(' m, the minimum speed is 2(' mBs "or ( 0 km, the minimum speed is '2+'mBs( The minimum speed o" the dou$le semi-circle can $e "ound "rom e@uations 53(3a6 and 53('6 "orP 0

() (0min ( 53(+a6 The speci"ic li"t "orce o" one kg o" ca$le mass &' in a planetDs gra%it "ield e@uals the li"t "orce in

e@uation 53(36 di%ided $ the ca$le !eight 2(S( For a con%entional circle

P'! 5/(6 53(6!hile "or a dou$le semi-circle

P'! 5?/(6 . 53(a6 The speci"ic li"t "orceP%o" one meter o" ca$le in a planetDs gra%it "ield e@uals the li"t "orce in 53(36and 53(3a6 di%ided $ the ca$le length, respecti%el

P% ! SQ5$(6 , P% ! 2SQ5$(6 0( . 53()6,53()a6 The length o" a ca$le%, !hich supports the gi%en local load 6 is

% ! 6$P% . 53(*6

The ca$le angle, h, to the hori8on a$out a local load e@uals 5"rom a local e@uili$rium6

h! argsin56$2S6. 53(6 Ca$le de"ormation a$out a local load 5decrease in altitude6 "or a ca$le semi-circle in a planet gra%itDs"ield can $e "ound appro7imatel:

h 6%$'2S . 53(.6 Ca$le de"ormation a$out a local load "or the dou$le ca$le circle around a planet in space is

20

02+

S6"(

h

. 53('06

The internal pressure on the ca$le circle can $e deri%ed "rom the e@uili$rium condition( The result is

# ! r$2( . 53(''6

33


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The increase in ca$le radius under an internal pressure is

( ! )2($E . 53('26 The ma7imum ca$le radius 5ma7imal ca$le top6 in a constant gra%it "ield can deri%ed "rom thee@uili$rium o" the li"t "orce and a ca$le !eight:

a6 Full circle 5"rom 53(366

(max! $ , "max ! 2(max ( 53('36$6 Semi-circle 5"rom 53(3a66(max! 2$ , "max ! (max ( 53('3a6

The results o" this computation are presented in Fig( 3('2(

Fig. '.12. >axi"u" radio! o the arth !e"i-circle $er!u! !peciic ca+le !tre!!

The ma7imum ca$le radius in a %aria$le gra%it "ield o" a rotating planet can $e "ound "rom the

e@uation o" a circle located on a "lat e@uator

( ) ( )

((

((

(((

=

+

++

02

2B3

0

0

B3'

B'. 53('+6

The ma7imum speed o" a closed-loop circle rotated around a planet 5Fig( 3(6 can $e "ound "rom thee@uili$rium $et!een centri"ugal and gra%it "orces

)a! Q5/61 ('B2 . 53('6 The results o" computation are presented in Fig( 3('3( The minimum %alue )a! 5(6'B2occurs !hen

k ! /! 0.

35


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The li"t "orcePao" a dou$le closed-loop ca$le circle rotated around a planet can $e "ound "rome@uili$rium o" a small circle element

Pa ! +S5)s2k(6. 53(')6

The "ull li"t "orce o" a dou$le closed-loop ca$le circle rotated around a planet is "ound $ multipling#

"rom e@uation 53(''6 $ a ca$le area +(r, or

Pa! 2S . 53(')a6

The results o" computation are presented in Fig( 3('+(

3


69/396


The speci"ic li"t "orce o" a one kgclosed-loop ca$le circle rotated around a planet can $e "ound "rome@uation 53(')6, $ di%iding $ ca$le !eight

Pa,'! /( . 53('*6 The speci"ic li"t "orce o" a one meter closed-loop circle around a planet in space, !hen 0, canalso $e "ound "rom e@uation 53(')6, i" it is di%ided $ the ca$le length

Pa,%! S$( . 53('6 =e can deri%e "rom momentum theor an additional speed, ), !hich a space ship 5Fig(3(*6 gets"rom a ca$le propulsion sstem

) ! )0mB5mss m6 . 53('.6 The results o" computation are presented in Fig( 3('(

The speed o" "alling "rom an altitude" is gi%en $ )f! 52"60( ( 53(206

The energ,Es, stored $ a rotar circle per ' kg o" the ca$le mass can $e deri%ed "rom the kno!ne@uation o" kinetic energ( The e@uation is

Es! /2 . 53(2'6

The results o" computation are presented in Fig( 3(')( The radius o" o$ser%ation %ersus altitude" Qkm o%er the arth is appro7imatel

(r! 52(o" 1 "260( Qkm , 53(226!here arth radius(o )3* km( >"" '0 km, then(r '3.' km(

!ti"ation o 0a+le Friction Due to the Air

This estimation is %er di""icult $ecause there are no e7perimental data "or air "riction o" an in"initel%er thin ca$le 5especiall at hpersonic speeds6( A computational method "or plates at hpersonicspeed !as used, see re"erence+ p(2*( The computation is made "or t!o cases: a laminar and a tur$ulent$oundar laer(

The results are %er di""erent( The ma7imum "riction is "or tur$ulent "lo!( A$out 0U o" the"riction drag occurs in the troposphere 5"rom 0 to '2 km6( >" !e locate the ca$le end on a mountain atan altitude o" + km the ma7imum air "riction decreases $ 30U( So the drag is calculated "or threecases: !hen the ca$le end is located on the ground " 0(' km a$o%e sea le%el," ' km and !hen itis located on the mountain at" + km 52200 "t6(

The ma" hal" the ca$le sur"ace has a laminar

laer it means that !e must decrease the air drag calculated "or the "ull tur$ulent laer $ a minimumo" t!o times(?elo! the e@uations "rom Anderson+ "or computation o" local air "riction "or a t!o-sided plate are

gi%en(

( ) ,(0,(0,

0.2(0,

65

))+(0,,

,+(''0

'0+-(',,'-(0032(0'

,,,,2(0P,(0,

(')2

tft0lfl0

e

Tf

e

%fe

9

CCCC(

C(

CT

)x(

T

T

T

T

a

)'

T

T'

T

T

======

+==

++=

D%! 0(Cf.l;)2S , DT! 0(Cf.t;)2S . D ! 0(5DT1 D%6. 53(236

3:


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To appl the a$o%e theor to the dou$le semi-circle case !e can appro7imate the atmosphere densit$ the e7ponential e@uation

-he0= , 53(2+6!hereo '(22 kgBm3, - 0(000'+, his the altitude Qm( Then the air "riction drag is

,sinarg,cosB65650

0''

P

,,

2

,

0""

"hdhhhCd)D

m

"

"

lt0%T = 53(26

5


71/396


!hereDT,%and C0,l,tare the tur$ulent and laminar drag and drag coe""icient respecti%el, 'is the angleo" the ca$le element to the hori8on( The "ull drag isD ! 0(5DT1D%6. The results o" computation arepresented in Fig( 3('*(

The radius o" o$ser%ation %ersus altitude" Qkm o%er the arth is appro7imatel(r! 52(o" 1 "

260( Qkm , 53(226

!here arth radius(o )3* km( >"" '0 km, then(r '3.' km(

!ti"ation o 0a+le Friction Due to the Air

This estimation is %er di""icult $ecause there are no e7perimental data "or air "riction o" an in"initel%er thin ca$le 5especiall at hpersonic speeds6( A computational method "or plates at hpersonicspeed !as used, see re"erence+p(2*( The computation is made "or t!o cases: a laminar and a tur$ulent$oundar laer(

The results are %er di""erent( The ma7imum "riction is "or tur$ulent "lo!( A$out 0U o" the"riction drag occurs in the troposphere 5"rom 0 to '2 km6( >" !e locate the ca$le end on a mountain atan altitude o" + km the ma7imum air "riction decreases $ 30U( So the drag is calculated "or three

cases: !hen the ca$le end is located on the ground " 0(' km a$o%e sea le%el," ' km and !hen itis located on the mountain at" + km 52200 "t6(The ma" hal" the ca$le sur"ace has a laminarlaer it means that !e must decrease the air drag calculated "or the "ull tur$ulent laer $ a minimumo" t!o times(

?elo! the e@uations "rom Anderson+"or computation o" local air "riction "or a t!o-sided plate aregi%en(

( ) ,(0,(0,

0.2(0,

65

))+(0,,

,

+(''0

'0+-(',,'-(0032(0'

,,,,2(0P,(0,

(')2

tft0lfl0

e

Tf

e

%fe

9

CCCC(

C(

CT

)x(

T

TT

T

a

)'

T

T'

T

T

======+

==

++=

D%! 0(Cf.l;)2S , DT! 0(Cf.t;)2S . D ! 0(5DT1 D%6. 53(236 To appl the a$o%e theor to the dou$le semi-circle case !e can appro7imate the atmosphere densit$ the e7ponential e@uation

-he0= , 53(2+6

!hereo '(22 kgBm3, - 0(000'+, his the altitude Qm( Then the air "riction drag is

,sinarg,cosB6565

0

0''

space launch and flight without rockets (v.3)

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