Haas_Orbital_Rocket_Launcher

8/7/2019 Haas_Orbital_Rocket_Launcher

1/20Orbita l Roc ket Launcher


2/20

P

reface Preface

In 2007, X Prize Foundation together with Google Corporation announcedGo og le Luna r X Prize, a $30 million c om pet ition for astronautics.The Europ ean Luna r Explorer (ELE) is ARCA s p rojec t for this c ompetition. ELE will

be launc hed to the Moo n with Haas Orbita l Roc ket Launc her. The first flight issc hed uled for 2011.Haas is a three-stage, balloon-launched vehicle, based on the technologydeve lop ed a t ARCA for the Demonstra tor and Sta b ilo Prog rams.The m a in source of fund ing for this vehicle w ill be throug h p ub lic d ona tions andsponsorships. ARCA has sponsors that already considered continuing theirfinanc ial e ffort fo r the Haas-ELE system.The short-term o b jec tive for Haas launc her is to suc c essfully deliver the ELEspac ec ra ft to the M oon. The long-term ob jec tive is to c rea te a reliable, co st-effec tive sma ll orbital roc ket launc her.

Dumitru Pop esc uARCA President


3/20

Overview Conrad Haa s

Conrad Haas (1509-1579) was anAustrian-Romanian medieval rocketpioneer, the first creator of multiplesta ges roc kets. In 1529, Conrad Haas

suc ceeded to launc h in SibiuCounty, Romania, rockets with twoand three stages that used blackpowder. He understood the role ofrocket propulsion for civilapplication. Haas even suggestedan experiment with an animal onboa rd o f a roc ket.Haa s launc her, named a fter ConradHaas, is a three-stage balloon-launc hed orbital vehic le, ab le to p ut

a 400 kg payload into Low EarthOrb it. The Europ ea n Luna r Explorer(ELE) designed for Google Lunar XPrize space will be launchers firstpayload.

Ove

rview


4/20

The air launchedsolution allowedthe rocket to flyat low dynamicpressure.

There is no external aerodynamic structure on theroc ket. The oxid izer tanks and roc ket eng ines a reforming the o ute r shell in order to save we ight. Theae rod ynamic forc es on the roc ket are red uced . Thehighest drag on the launcher is about 10% from the

thrust o f the first sta ge. This loss is less then twice the ga inobtained from the reduced weight obtained by usingspherical shapes for the oxidizer tanks.

The first sta ge is working a t low atm ospheric p ressureexpanding the burned gasses into a huge nozzle ,

increa sing the spec ific impulse. The nozzle is expandedto a much higher value compared with ground-launched vehicles and it has an advantageousimpulse/weight penalty ratio.

The struc ture itself for one stage is rep lica ted a t d ifferentsc a les for the o ther two sta ges. This solution red uc es thedesign and test c osts. This design for the struc ture is a lsoused fo r ELE.

Innovative Design

Haas is an innova tive air-launched , 3 sta ge s orbital roc ket. The go a l was to c rea te asimp le, reliab le a nd low c ost o rb ita l roc ket launc her. The high p erforma nc e w as neve ran objective. Even so, the Haas launcher has a good launch weight/payload ratiowithin the c lass of sma ll orbita l launc hers.


5/20

Struc ture & Propulsion

MaterialsThe roc ket s is ent irely ma de o f va rious c om posite materials.Oxidizer tanks internal structure is made o f ep oxy S type g lass fibe r and theexternal structure is reinforced with epoxy carbon fiber.Rocket engines internal structure is made of phenol resin silica fiber and theouter structure is reinforced with epoxy carbon fiber.

Working pa ram eters

The oxid izer tanks a re p ressurized a t va lues rang ing from 20 to 30 ba rs. First Sta geH1 is pressurized at 30 bars.Bec ause of p ressure fe d system, the ta nk struc ture is strong. This a llows theremova l of seve ra l reinforc ed eleme nts on the roc ket structure.The roc ket engines a re working a t initial p ressures rang ing from 14 to 24 bars. Firststage engine is working at an initial pressure of 24 bars. Nozzle expansion ratio is38 for the first sta ge a nd 43 for the third sta ge.Haas is using the hybrid rocket propulsion. All stages are using CommercialGrade (CG) Hydrogen Peroxide and bitumen-based, high regression rate solidfuel. The spec ific impulse of the first sta ge is 245 sec ond s a t launc h a ltitude.Bitum en-based fuel wa s c hosen b ec ause o f its goo d reg ression ra te . The high

carbon percentage is not substantially affecting the combustion gasses molarmass (respectively the specific impulse) because of high percent of waterpresent in the oxidizer.

Structure&

Propulsion


6/20

Usually, a hybrid rocket engine burning chamber is long, because of the fuel regression rate

de pe ndence. In the c ase o f Haa s, the roc ket engines burning c ham be rs are p lac ed inside ofthe oxid izer tanks allowing a short ove ra ll length of the launc her.Despite the p ressure feed system solution, the roc ket structure is lighter com pared with mo stof the sma ll launc hers on the ma rket.The Haas launc her will sta rt engines tests in the spring of 2009. The team estima tes a firstlaunch at the beginning of 2011. On this launch, the rocket will carry the complete ELEpa yloa d for the GLXP Com pe tition.

The no zzles for the sec ond and third sta ge s a re extendab le, in orde r to save leng th andincrease structure strength.


7/20

Stage H1Type: Roc ket p ow ered , pressure feedUsed for: Rocket accelerationGross weight: 14 800kgBurn time: 100sFuel: Hydrog en p eroxide CG + bitumenbasedThrust: 48 000kgf

Stage H2Type: Roc ket p ow ered , pressure feed

Used for: Roc ket a c c elera tionGross weight: 7 350 kgBurn time: 110 sFuel: Hydrogen p eroxide CG + b itume nbasedThrust: 25 000 kg f

Haa s technic al da taType: Air launc hed orbita l roc ketStages: 3 (H1+H2+H3)Roc ket ve hicle leng th (w ith ELE payloa d):17mRocket vehicle diameter: 3.6mRoc ket vehic le gross weight: 23 300kgLEO mass: 400kg

Stage H3Type: Roc ket p ow ered , pressure feed

Used for: LEO injec tionGross weight: 2 100 kgBurn time: 168 sFuel: Hydrogen p eroxide CG + b itumenbasedThrust: 5 900 kg f


8/20


9/20

System Capabilities

HAAS is ab le to p ut 400kg into Low Earth Orbit (LEO) a t a n apog ee of 200 km a nd100kg on a Mo on trajec tory.

SystemCapab

ilities


10/20


11/20

The

Balloon

ARCAs Stab ilo System launc hed on Mission2 fromMidia C ap e Air Force Base, Sep temb er 2007


12/20

Preliminary Ba lloon-Haas

initia l choice of launchosition and d a te

Launc h w indow de termina tio

long te rm meteo rologica lrediction

Launch window p rec isedetermination/ short-termmeteorolo ic al redic tion

Balloon-Haas flightmo nitoriza tion/ a ltitude/ time

ELE Moon interc e tion

ELE Trajec to ry correc tion

Ba lloon-Haas launc h

Haas launch

Final decision on Balloon-Haaslaunch osition and moment

ARCA s Sola r Balloo n d uring infla tion a tMidia Ca pe Air Force Base, Sep temb er 2007

ARCA c rea ted it s ow n pow erful simulation softwa re tha t a llow ed to p rec isely de te rmine the 3D flight softwa re is working with high qua lity w indg rams and it will be used for the Haas-ELE GLXP launc h.Because it will be able to be launched from sea/ocean surface, close to the Earths Equator Haas has to have a muc h higher numb er of launc h windo ws compa red with ground launched vehic les.ARCA p rod uc ed and op erated the largest sola r ba lloo ns in the wo rld for the Sta b ilo System. Haas-ELE wila ba lloon.


13/20

European Lunar Explorer

ARCA Tea m a nd Pete r Diam and is in front of ELEmo c k-up a t ISU, Strasbourg, M ay 2007


14/20

Google Lunar X Prize Flight

In order to win the Google Lunar X Prize (GLXP), a private team must build andsend to the Moon a spa c ec raft ab le to trave l at lea st 500 m on the Moo n surfac eand send defined da ta set to Earth. The p rize is ava ilab le until 2012 and ma y beextended until 2014.

The Europ ean Luna r Explorer - ELE is a 400 kg, three sta ges spac ec raft designe d

for the GLXP Co mp et ition. It is ab le to fly from LEO to the M oo n, to t rave l 500m o nthe Moon surfac e a nd to send da ta b ac k to Earth.

There a re multip le flight trajec to ry ap proa c hes for an Earth-Moon t rave l. The m ostused and m ost efficient, from the energetica lly po int of view, is tha t of p lac ing thespacecraft into LEO and from there to a Moon trajectory. Another method is aballistic vertica l launc h from the Earth to the Moo n. This flight t ra jec to ry wa s neverused befo re for inte rp lane ta ry flights bec ause o f effic ienc y loss resulting in a muc hsmaller mass to be placed on a Moon trajectory. However, this method is to beconsidered for GLXP Competition because it can save costs and developingtime.

Google

LunarXPr

izeFlight


15/20


16/20

Stage E3 European Lunar Land er (ELL)

ELL is the ob ject that will soft land on the Moo n surfac e, c ollec t d ata and transmit them ba ck to Earth.Type : Roc ket pow ered, pressure fee d , resta rta ble c old roc ket eng ineUsed for: Moon land ing + Lunar surface moveme ntMa x. DV: 300 m/ sGross weight: 42 kgBurn time: 120 sFuel: Hydrogen peroxide 85%Max. Thrust: 14 kgf

Restartab le hybrid en gine tec hnolog y tested at A RCA,October 2008

Stage E2

Type: Roc ket p owered,pressure feed, restartableroc ket engineUsed for: Earth-Moo ntrajec tory co rrec tion + Nea rMoon spee d brakeMa x. DV: 2400 m/ sGross weight: 65 kgBurn t ime: 185 sFuel: Hydrog en peroxideCG + bitumen b asedMax. Thrust: 100 kgf

Stage E1

Type : Roc ket p owered,pressure feed, restartableroc ket engineUsed for: Earth orbitcircularization + LunarinjectionMa x. DV: 3300 m/ sGross weight: 316 kgBurn t ime: 170 s

Fuel: Hydrog en pe roxide C G+ bitumen basedMax. Thrust: 500 kgf


17/20

Flight Sequenc e

1. The launc h will be m ad e from the sea with the help o f a large ma rine platform de signedby A RCA.The roc ket will be lifted from the sea using the wo rld heav iest 0 pressure b alloon e ver

build.Once the platform into position, the rocket will be placed on the sea surface and thehydrog en pe roxide oxidizer will be transferred into the fuel ta nks. After the fuel ta nks will befilled, the te am will start the ba lloon inflation proce d ure. When the ba lloon will rea c h thenec essary lifting c ap ab ility, the rocket will be lifted from the sea surfac e a nd plac ed intonea r vertic al position benea th the ba lloon, atta c hed w ith a ca ble. The distanc e be twee nthe b alloon and the roc ket will be 200 m. The b alloon and roc ket will fly to an a ltitude of18.000 m for 1 h, 45 min.

2. At 18.000 m the roc ket w ill sta rt it s first stage roc ket e ngine. A fter eng ine c ut-off, the firststag e w ill be de tac hed . Soon afte r, roc kets sec ond stag e w ill be ignited .

3. The roc ket s third a nd last sta ge will be ignited and it will burn for another 168 sec,putting the ELE to an elliptical LEO to an altitude of 140 km. At this altitude the rockets

third sta ge will sep arate from the ELE p rob e.

6. After Stag e E2 fuel de pletion, it will be e jected at an altitude of a bo ut10 km from the lunar surfac e, the ELE Luna r Land er (ELL) w ill soft land onthe M oon using the Stag e E3 main eng ine and inertial guida nc e launc hpla tform. The Sta ge E3 ma in eng ine is thrust a d justa ble, g imbaled ,

hydrogen pe roxide mono prope llant 14 kgf, roc ket mo tor. The time fromthe Earth launch to the Moon surface will last for 116 hours (4 days, 2hours).

7. The d esired Mo on land ing po int is the North reg ion of the Ca rpa thianMo unta ins. This spo t wa s c hosen b ec ause, the Ca rpa thian Mountainsare a lso p assing Rom ania from the North to the West.

4. After the Haas 3rd stage burnout, the ELEspa c ec raft will be pla c ed into o rb it. ELE will sta rt theStage E1 ma in engine a t first orbit s ap og ee for aDV=260m/s in order to circularize the orbit to analtitude of 250 km. After a short time spent in Earthorbit, ELE will ignite once again the E1 main enginethat will increase vehicles speed to 11,2 km/s. AfterStag e H1 fuel de pletion it will be ejecte d onvehicles wa y to the Moon.

5. As the ELE will head to the Moon, the trajectorywill be p eriod ica lly co rrec ted using the Stage E2main brake engine. During the trip from the Earth tothe Mo on , ELE will dep loy tw o 100 W sola r pa nels.Nea r the Mo on , ELE will sta rt Sta ge E2 in an op positedirec tion face d to the spe ed vec tor. The tea m willtry to reduce as much as possible the number ofbrake eng ine sta rts.

FlightSequ

ence


18/20


19/20

About ARCA

Aeronautics and Cosmonautics Romanian Association (ARCA) is a non-governmentalorganization that promotes innovative aerospace projects. ARCA joined the Ansari XPrize Competition in 2002. ARCA developed two main projects: the Demonstratorroc kets and Sta bilo. Dem onstrato r 2B roc ket, eq uipped with world first c om po sitema teria ls reusable m ono prop ellant eng ine ever to fly, wa s launc hed in 2004. Sta b ilo, atwo sta ge s ma nned suborbita l vehicle c ompleted three flights until now . The first stageis world largest solar balloon and the second stage is a rocket powered mannedspaceship.

ARCA

Op1, Cp13,Rm. Va lceaRomania

www.arcaspace.rowww .arca spa ce.comoffice@arca spa ce.roTel: +4 0350 413 486; +4 0743 420 073; +4 0350 803 161Fax: 0250 732 466

AboutARCA


20/20

Haas_Orbital_Rocket_Launcher

Documents

Transcript of Haas_Orbital_Rocket_Launcher