Space Exploration Technologies; NEW PETITION
`Exhibit 1112
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`Page 1 of 25
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`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 1 of 25
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`

`
`Property of:
`h&arsha1II{.I{ap1an
`8029 Rising Ridge Road
`Bethesda, MD 20817
`
`INTERNATIONAL
`
`REFERENCE GUIDE TO
`
`SPACE LAUNCH SYSTEMS
`
`FOURTH EDITION
`
`STEVEN J. ISAKOWITZ 0 JOSHUA B. HOPKINS - JOSEPH P. HOPKINS JR.
`
`Corporate Sponsors
`
`Spzceworks Engineering, Inc.
`Lockheed Martin Corporation
`
`Published and disttibuteci by
`
`
`
`American Institute of Aeronautics and Astronautics
`1801 Alexander Bell Drive, Suite 500
`Reston, Virginia 20191-4544
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
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`Page 2 of 25
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`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 2 of 25
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`

`
`
`
`PHOTO CREDITS
`
`Front cover, from lefi‘:
`
`H-IIA, Dnepr, Athena, and Minotaur
`
`Back cover, from la 2‘:
`GSLV, Voina, Arias V, and Delta IV
`
`Bar/égmmzdr
`Athena launch from Kodiak Island, Alaska
`
`Cover design by Sara Bluestone
`
`Library of Congress Cataloging-in-Publication Data
`
`Isakowitz, Steven J.
`International reference‘ guide to space launch systems /’ Steven Isakowitz, joseph P. Hopkins ]r., Joshua
`B. Hopl<ins.«~ 4th ed.
`p. cm.
`
`Includes bibliographical references.
`ISBN 1-56347-591-X (pbk. : alk. paper)
`1. Launch vehicles (Astronautics}--Encyclopedias. 2. Reusable space vehicles-~Encyclopedias. 3. Space
`shuttles--Encyclopedias.
`I. Hopkins, Joseph P. II. Hopkins, joshua B. III. Title.
`
`TL783.8.I.3I83 2004
`
`629.47--dc22
`
`2004014007
`
`Copyright © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All other rights reserved.
`Printed in the United States of America. No part of this publication may be reproduced, distributed, or
`transmitted in any form or by any means, pr stored in a database or retrieval system, without the prior writ-
`ten permission of the Publisher.
`
`Data and information appearing in this book are for informational purposes only and are not intended for use
`:10: to be relied upon. AIAA, SpaceWorks Engineering, In-:., and Lockheed Martin Corporation are not
`responsible for injury or damage resulting from use or reliance, and do not warrant that use or reiiance will
`be free from privately owned rights.
`
`Space Exploration Technologies; NEW PETITION
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`Space Exploration Technologies; NEW PETITION
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`
`185
`K-1 6 UNiTED STATES
`
`Iii-1
`
`GENERAL DESCRIPTION
`
`Summary
`The K-1 is a new two—siago reusable launch vehicle being deveioped commercially by Kistler Aerospace Corporation. The
`K 1 can cairn} payloads up to 4600 kg. Fioth stages are recovered using parachutes .inci airbags. Launch operations will be
`conducted from new launch facilities in Australia and Nevada. Bot*i stages burn LO)(i-lkerosene propellants and are pow~
`erect by Aerojet engines modified lrorn the core Russian Nl(—33/43 engines. An optional expendable third stage, fueled by
`MMHINZO4, can be used for high—orbli missions. An optional cargo module can be used for international Space Station
`USS) resupply missions.
`Status
`in deveiopmont. First launch planned 13-18 months after completion of financing.
`
`Origin
`United States
`
`Key Organizations
`Nlarieetirig Ofgafliéfliitfli
`Launch Service Provider
`Prime Contractor
`
`Kisfler Aerospace Corporation
`Kisiler Aerospace Corporation
`Kistlez Aerospace Corporation
`
`Primary Missions
`ISS servicing: LEO sateilites, or small satellites to higi1—energy orfits with optional upper stage.
`Estimated Launch Price
`$17 million for LEO missions l_Kistlur 2002)
`$25 million with upper stage (Kistier 2002)
`
`
`
`Spaccports
`Launch Site
`Location
`Available inciinations
`Landing Site
`
`Launch Site
`Location
`Available inclinations
`Landing Site
`
`Woomera. Australia
`3' .1“ 5, 136.6‘ E
`45--6-D deg, 84-99 dag
`Woomera, Australia
`
`Nevada Test Site
`313° N, 116.5“ W
`45430 deg B4-99 deg
`Nevada Test Site
`
`Performance Summary
`The ioliowing periormanoo values are for a launch from the 'r'lloorr-era Spaceport using the standard payload module for
`LEO missions, the Active Dispenser Module for high orbits. and the ISS cargo module for ISS m:ssions. Payload adapter
`mass must be subtracted to determine available spacecraft mass.
`
`200 km (108 nmi), 45 deg
`200 km (103 nmi), 90 dog
`Space Station Orbit: 40; km (220 nmiji, 51.6 dog
`
`Sun-Synohroiious Orbit: 800 km (432 nmi), 98.6 deg
`GTO: 200x35.’/'86 i-cm [10Bx19,323i1mi), 45 deg
`Geostationary Orbit
`
`4500 kg €10,150 ibm)
`3000 kg 16500 ii:-I11)
`3750 kg (8250 ibm) upmass
`900 kg (2000 lbm) ciowrmase
`1250 kg (2Ih0 Ihrn)
`1570 kg (3460 itm)
`800 kg (1760 itrrri)
`
`Plight Record (through 31 December 2003)
`Total Orbital Flights:
`0
`
`Flight Rate
`To be determined
`
`Space Exploration Technologies; NEW PETITION
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`Space Exploration Technologies; NEW PETITION
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`

`
`NOMENCLATURE
`
`189
`K-1 9 UNITED STATES
`
`The K—1 designation refers to the lirst launch vehicle developed by Kisiler Aerospace Corporation. The lirst stage of the K-1 is referred to as the Launch
`Assist Platform (LAP). The name stems from an early design in which the first stage was to be a rocket-powered platiorm that carried the second stage,
`The second stage is called the Orbital Vehlcic (UV). Spacecraft are carried in a reusable payload module (PM) rather than a converrlicnel payload lair-
`ing, Three types are available
`the Standard Payload Module TSPM‘,-, Extended Payload Module (EPM), and Active Dispenser Payload Module (ADPM).
`The phrase Active Dispenser refers to an optional expendable upper stage. A cargo module (CM) is also availat:-‘re to support SSS resupply missions.
`
`COST
`
`The K-1 deveiopment program has been financed commercially. More than $600 million in financing was raised through the mid 1990s before invest-
`ment began to decline. The funding was provided by iiivestors in the United States. Saudi Arabia, Asia. and Europe. and from vendors and subcon-
`tractors. For example, lxlnrlhrup Grumman had:-1 COMBO! 10f $145 million to build structures for the vehicle, and advanced $30 million to Kisller in 1998
`to continue work when funding slowed.
`In 2001 Kistler received a contract worth up to $135 l'T-ll|iO|'I from NASA under the Space Launcr. Initiative,
`However, this consisted of a $10 million Iirni contract and options for up to $125 million for flight demonstrations of 13 leoliriolcgie.-5 if the K-1 vehicle
`was developed. ("l'hese options had not been exercised at the time or publication.)
`According to Kistler, LEO missions will be priced at $17 million per flight. Missions requiring the expendable upper stage will be priced at $25 million.
`These prices do not include m ssion Eiilegralion.
`
`The first launch date is contingent on completion of fundraising. Once Full financing is in piece, first l|ig'lt could occur within 18 months.
`
`AVAILABILITY
`
`PERFORMANCE
`
`The K-1 will be launched from Spaceport Woornerai in Australia, A second launch site is also planned at the Nevada Test Site in the United States. Both
`sites are landlocked, so iaiinnh azimuths are limited to those that do not endanger populated areas. The K-1 can roach inclinations in two sectors
`between 45-60 deg and 84-99 may from both sites. As operational experience is gathered additional inclinations can be cchsiclerec depending on cue-
`lorner needs. Parlormaace shown incl.ides a 3—sigma flight performance reserve (FPH). These performance values do not account for miaaion—epecii—
`ic spacecraft adapters or dispensers. Launches are assumed to be conducted from Spaceport Woomera. the location of initial llights. i-‘enorman-so is
`up to 400 kg (880 lhm) higher ior launches from the Nevada Test Site as a result ol the higher launch site olevotion.
`
`Woornera Azim uths
`55-33 deg
`5 ‘14 deg
`
`Nevada Azim-uths
`62 as deg
`5-14 deg
`
`Resulting Inclination
`45-so deg
`34 99 deg
`
`Space Exploration Technologies; NEW PETITION
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`Space Exploration Technologies; NEW PETITION
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`

`
`190
`K-1 6 UMTED STATES
`
`PERFORMANCE
`
`0
`
`1 00
`
`200
`
`300
`
`400
`
`Altitude (nmi)
`500
`500
`
`700
`
`800
`
`900
`
`1000
`
`5000 0’
`
`'
`
`.,
`
`-_
`45 d
`B9 1
`52 deg ’
`' 60 deg
`4000 I
`_
`
`66 deg §
`-
`--
`3
`-~ 3000 -
`E
`- 98 deg 1
`1:
`‘
`g
`-5.
`EL
`
`2000 '-
`
`.
`7
`.
`-
`Adapts; Mass Must be Sumracled to
`Determine Available Spacecraft Mass
`Launch from Woomera
`5
`1
`f
`
`.
`
`'
`
`1
`
`r11ooo
`
`10000
`
`_ 9000
`i 8000
`
`7000
`I 5000
`
`‘U
`‘E
`8
`Q.
`5000 E
`3,
`4000
`
`1°00
`
`O .
`0
`
`0
`
`5000
`
`'.
`200
`
`_‘
`400
`
`000
`
`.
`
`.
`
`4
`800
`
`'
`1000
`Altitude (km)
`K-1: circular Orbit Performance with Standard Payload Module
`
`100
`
`200
`
`300
`
`400
`
`Altitude (nmi}
`500
`800
`
`
`
`3000
`
`2000
`
`1000
`
`0
`
`11000
`
`,
`
`_ 10000
`' 9000
`
`_ B000
`
`- 7000
`
`E
`*5
`g
`' 6000
`D.
`5000 E
`3
`-r
`
`4000
`
`3000
`
`2000
`
`1000
`
`.
`
`1200
`
`1400
`
`1600
`
`1800
`
`2000
`
`700
`
`800
`
`900
`
`1000
`
`-
`
`-
`
`-1
`l
`.
`.
`Adapter Mass Must be Subtracted to
`Delermlns Available Spacecrafl Mass
`
`Lauochfrom Vltoulnera
`
`
`
`45 d.Qg___
`52 deg 1
`‘
`..
`4000 “soaég"
`
`3
`1 95 d
`meg-1
`‘*
`
`93 deg
`
`:
`
`——~ 3000
`E’
`:6’
`g
`"S.
`‘“
`0- 2000
`
`1000 J
`
`0
`
`0
`
`
`'
`'
`1200
`E00
`1000
`Altitude (krnl
`K-1: Circular Orbit Performance wlrfi Extended Payload Module
`
`I
`200
`
`.
`
`‘
`400
`
`.
`
`I
`600
`
`l
`
`1400
`
`'
`1600
`
`.
`
`1800
`
`I. O
`2000
`
`Space Exploration Technologies; NEW PETITION
`Exmbfl1112
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`Page 6 of 25
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`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 6 of 25
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`

`
`191
`K-1 9 UNITED STATES
`
`PERFORMANCE
`
`5000
`
`Apogee Attitude (nmi)
`10000
`
`15000
`
`20000
`
`200 km [108 nmi) Perigee. 45 deg lncliaéion
`
`N
`
`__
`
`9P"1§l|V039J
`
`6500
`
`- 0000
`
`5500
`
`5000
`
`0
`3000 '
`
`2
`
`‘-._
`
`2000 -
`
`
`
`Payload(kg) E8
`
`1000
`
`500
`
`0
`
`I
`
`10000
`
`20000
`Apogee Altitude (km)
`
`30000
`
`40000
`
`K-1: GTO Performance with Active Dispenser
`
`1500
`
`1250 ;
`
`1000
`
`750
`
`500
`
`250
`
`
`
`Payload(kg)
`
`-
`
`3003
`
`[ 2500
`
`2000
`
`oad(lbm)
`
`-1500-—
`Payl
`
`1000
`
`500
`
`20
`
`10
`
`0
`
`2
`10
`'
`Escape Energy (km2.’s2}
`
`0
`
`30
`
`'
`
`40
`
`50
`
`K4: Earth Escape Performance wifh Active Dispenser
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
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`Space Exploration Technologies; NEW PETITION
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`
`192
`K-1 v UNITED STATES
`
`Overall Vehicle
`
`VEHICLE DESIGN
`
`EXTENDED
`
`PAYLOAD
`
`MODULE
`
`-L ‘
`
`VEHICLE
`PLATFORM
`
`18 6 m
`€51 3 ft?
`
`0fiElTAL
`
`LAUNCH
`ASSIST
`
`caurtesy Krétlér Aerospace Corporafloi
`
`Helgr.-t
`Gross Liftoff Mass
`Thrust al LI'.‘fGf.'
`
`K-1
`36.9 m (121,211) wifh Extended Payload Module
`382 t (841 klbm}
`15540 RN (1020 kEhf)
`
`Space Exploration Technologies; NEW PETITION
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`Space Exploration Technologies; NEW PETITION
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`

`
`
`
`VEHICLE DESIGN
`
`193
`K-1 o uurrso STATES
`
`gmges
`}fi,:,—K-1 is a two-stage, reuszrblervehiole. Tie system design is strongly -:lr‘ver.- by requirements for reusability, system longevity (the vehicle is designed
`W mg iilgiiisi, low cost, and rapid maintenance. Both stages burn RP grade ke’oserte and LOX, avoiding the complexities of hydrogen-fueted systems.
`The K4 :5 powered hy liquid-propellant engines fr-:>n'iAeroi'e1 based on the NK—33 and NK-43 engines originally developed lor the Soviet manned lunar
`landing program, The NK--33 and NK-43 in turn were developed as upgrades to the NK- l5 and NK-25 engines that powered the test fiights of the Soviet
`N4 heavy taungh ve‘h;cle. Title engicnes were designed and produced by
`ND Kuznetsoil
`cien i to Tap nlcal
`omplex and underwent a very tnc-r=
`.
`Main pa,-achuges
`Ougi-i development and test process to demonstrate high reliability, extend»
`mummum Lox tank
`'
`99. mg, and rousability. A tuiai 0" 250 NK3:-ms engines were tested. accu-
`mulating over 108,000 s of test tiring Iirne. (this was in addition to the 581
`NK,t5 engines that had already accumulated 86,000 5 of test firing time.)
`up to 17 firings (18,000 5:
`total) were demonstrated on a single engine
`between overhau's. The Ni<—35 and NK43 are very similar, the primary dis
`lincflofl being that the NK-43 has a larger nozzle for improved performance
`in vacuum, wh¥e the MK 33 is designed for lirst-stage applications. The
`gngines use a staged combustion cycle to achieve high spcoilic impulse
`and a high tnrust to-weight ratio. ‘Ens turbopump is driven by an -3xidi7e.'r
`rich prebumer. rasutting in high pertormarcs. The engines tor the K-1 use
`the extensively tested NK-33r’43 orig-'ne core (turbornacninery, hot gas sys-
`tems, combustion chamber, and nozzle] combined with new systems
`developed by /‘torojet, s.rch as electronic oar-trollers,
`ignition systems,
`electromechanical valve actuators, and a now glmbal bearing. The center
`f,-,5g.5mgg engine has a new dualszart canridge and other modifications
`required to restart the engine for return to the launch site.
`the K-1 first-
`stage engines derived trom the NK 33 are designated the AJ26-58 (single
`
`Aluminum HP
`tank dome
`
`start) or AJ26r59 (restart). Tho second-stage engine derived from the NK—
`
`AJ26_59 mam
`engine
`
`Airbags
`
`43 is designated the AJ26~60, The engines are intended to be refurbished
`after to flights, then flown to more times before being retired.
`The K-1 includes a new Orbital Maneuvering System (OMS) that burns
`Loxiethanof propellants. it is based on development work done at Aeroiet
`in the 19803 intended to create a nontoxic propulsion system to replace the
`Space Shuttle ACS engines. Typical systems such as the Space Shutlte K" I-a""°"' A593’ P’am”"'”
`AC5 engines use UDMH,rN,.O4 propeliants, which are highly toxic and
`therefore the engines are expensive and time consuming to refLirbish and
`maintain between llights, l_O><«’ethanol was selected for the K11 because it is nontoxic and easier to maintain than UDMH/N20,; systems. The K-1 OM-S
`system consists of two spherical propellant tanks (one LOX, one ethanol} in ire aft compaitrrien‘. of the DV second stage, and one electromechanical
`ly gimbaled OVIS engine.
`I" he engine is tluid—lilm cooled, with a colurnbi-.im combustion chamber and nozzle. An eiectrical igriiler burning ethanol and
`gaseous oxygen is used to ignite the engines to avoid the maintenance requirements at pyrotechnic or hypergolic lgniters. The OMS angina is used for
`V9'°C”l' trim at the end ol the main-engine burn, for circularizatron/orbit iniection, and ‘-or maneuvering into the phasing orbit and reentry trajectory.
`P39“ 51399 include-‘3 8 lJi'DiDUiSiUfl S5"-W-‘mt 3 Cfimposlte airlrame. and propellant tanks. In addition to the two primary propellant tanks, the first stage
`includes a smaller LOX retention tar-k in the center of the toroidal kerosene tank. This tank retains the LOX needed to restart the main engine for the
`return of the first stage to the launch si:e. The retention tank is
`required ocoause any remaining LOX in the primary tank would
`slosh toward the warm top of the tank during the pitch maneuver
`that turns the vehicle back toward the launch site. The LOX
`would vaporize at the top of the tank and could not be led to the
`engines. The tanks are pressurized with helium stored at 400 bar
`(6000 psi) in composite overwrappecl titanium pressure bottles.
`Nitrogen is stored in bottles of the same design tor purging, valve
`actuation, and inflating the landing airbags. The stages are sep-
`arated using the air pressure retained in the intarstage area. At
`littofl,
`the interstege contains air at ambient pressure. During
`flight this air is vented slowly, so that when the stages separate
`at approximately 43 km (14t),0OO ftl altitude, the internal air pres-
`sure is stilt about 43 kPa (6.3 psi). When the 0V is released, this
`air pressure pushes the two stages apart, eliminating the need
`for springs or retr-.n-'oc|»ts-ts.
`
`c°mP0site HF‘ tank dame
`
`AJZB-60 main
`
`Mumifium LOX fafik
`Ii‘
`(9
`
`-“
`
`
`
`-
`
`'
`
`‘
`
`_
`'
`Orbital maneuvering system
`
`-
`_
`Airbags
`
`K-1 Orbital‘ Vehicle
`
`Courtesy KrstlerAerospacc Corporation.
`
`
`
`Feediifles
`
`COUWBSY W-‘rile? PWUSPECE Cotimtfltloftr
`
`Both siagss have recovery systems that consist of drcgue and
`man parachutes for deceleration and airbags to cushion the
`landing ‘he parachutes can be reused six times. The airbags
`are pressurized using nitrogen. The 0V is protected from reen«
`try heating by ceramic TPS on the forward surface of the pay-
`load module and thermal blankets on areas that experience less
`he tin .
`a
`g
`
`Space Exploration Technologies; NEW P|_E'|_'|T|ON
`Exhibit 1112
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`Space Exploration Technologies; NEW PETITION
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`Page 9 of 25
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`

`
`VEHICLE DESIGN
`
`0V (Stage 2)
`
`Active Dispenser
`
`194
`K-1 o uumso STATES
`
`Dimensions
`Length
`Diameter
`Mass
`Propetlant Mass
`Inert Mass
`Gross Mass
`
`Props-liant Mass Fraction
`5trueture
`Type
`
`Material
`
`Prep11lsiu11
`Engine Designation
`
`Number of Engines
`Propeffant
`
`Average Thrust (each)
`
`tap
`
`Chamber Pressure
`
`LAP (Stage 1)
`
`18.4 m (60.2 it)
`6.7 In (22 ft)
`
`2271 (499.7 kblm}
`22.7 1 (50 kibm)
`249 1 (550 klbmjr
`
`0.91
`
`tanks.‘ mnnnooque
`Thrust frame: truss
`A:r1rame: .=:kin—stringer
`Tarks. aluminum
`Thrust frame: composite
`Airframe. graphite composite
`
`AJ2S—58 and AJ26—ti9 (Aerojet, nased
`on ND Kuzneltsnv NK 33)
`
`3 (two AJ26-58, one AJ2669)
`LOXfFlP (kerosene)
`
`Sea level: 1512 kN (339.9 lclhf)
`VaCULlTIZ 1683 kit (3r8.3 klbt)
`Sea level: 297.2 s
`'1/acuum:331.3
`145.4 bar (2109 psi)
`
`1.5m(5 ft)
`
`7 V
`
`ariable
`
`7 4
`
`090 kg (9000 lbm)
`
`Struts. cylindrical tank.
`thrust cone
`
`Composites
`
`No designation (Aeroietl
`
`1 M
`
`MH/NED.»
`
`8960 M (2000 lbf)
`
`200:1
`
`Pressure led
`
`None
`
`Multiple
`
`Helium
`
`Electromechanical nozz='e Qimbi
`17 deg
`
`Monopropellant hydrazine A95
`
`23.6 m (77.3 it) including bell nozzle
`4.3 rn (14 ft)
`
`116 I (257 klbm)
`'12 V1 (28 klbrn)
`129 t(285 kltrm) (includes
`payload mudtiie)
`D90
`
`Tanks: monocoque
`Airframe. Si-:ln-stringer
`
`LOX tank: aluminum
`Airframe and RF‘ tank:
`graph re composite
`
`Main engine: AJ26-6-D (Ararojetj
`based on ND Kuznetsov NK-4:5)
`OMS: No designation (Aerujel)
`1 main engine + 1 OMS
`Main engine: LOX./FlP (kerosene)
`OMS: LOX/ethanol
`
`Main engine: 1769 W i_39?."/ klbt)
`OMS: 3870 N (870 ll:-l)
`Main engine: 348.3 s
`OMS: 305 9
`
`Main engine: 145.4 bar (2109 psi)
`OMS: 10.3 bar (150 psi)
`Main engine: 60.1
`OMS: 1U0:1
`Main engine: oxidizer-rlch
`staged co1'nbusr'on luruupump
`OMS: pressure led
`Main engine: 2:592:1
`OMS: 1 5 1
`Main engine: 55 104%
`OMS: Nona
`Main engine: none
`OMS: 5 firings per flight
`Main engine: helium
`OMS: helium
`
`Main engine: Pumped
`hydraulic gimbal 16 deg
`OMS electrorr-act-anical
`girnbal rat-3 deg
`GOX/utnarlol AC5
`
`Main engine: 233 s
`OMS: mission dependent
`
`variable
`
`Main engine: command shutdown
`OMS: command shutdown
`
`Command shutdown
`
`Nozzle Expansion Flatio
`
`2711
`
`Prape.'Iant Feed System
`
`Oxidizenrlch staged-combustion
`mmoptimp
`
`2,5861
`
`5041 04%
`
`AJ2Ei—5u: nowe
`[U26 59: ‘ restart
`Heliurr
`
`Pumped hydraulic gimba! :6 deg
`
`GOX.’ethanoi ACE: (main engines
`not used for roll control)
`
`139 .=: tor launch, plus 35 5
`using center engine
`only for recovery
`Command shutdown
`
`Stored air pressure in intefstago
`
`Mixture Flatto (O/F)
`
`Thrcttiing Oapab/'1'i'ty
`
`Flestart G'apabii.-'ty
`
`Tank Pressurization
`
`Altitude Control
`Pitch, ‘/aw
`
`Ftoii
`
`Staging
`Ivorninai fiurri Time
`
`Shutnlown Process
`
`Stage Separation
`Recovery
`Deceieration
`
`Landing
`
`Two clusters 013 main parachutes each,
`deployed by two ctrogue parachutes
`Near-vertical landing on airbags
`
`3 main parachutes deployed by drogue
`parachute and ctaollzation parachute
`Nearwertical landing on airbags
`
`V-band clamp
`
`Not recovered
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`
`Page 10 of 25
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 10 of 25
`
`

`
`VEHICLE DESIGN
`
`195
`K-1 0 UNITED STATES
`
`Attitude Control System
`The original NK«33 and NK-43 engines have been modified by Aeroiet to su
`pport engine gimballng for altitude control during first and 5econd—stage
`main engine bums, The primary changes include modifications to the thrust
`structure. addition of a new gimbal block. and new TVC actuators, The
`hydraulic actuators are powered by high-pressure fuel topped off the fuel turbopump oulfet. The total gimbal range is :6 deg. Tho second-stage OMS
`engine is aiso gimbaled using electromechanicai actuators with- a range of 1:8 deg Each stage has an Independent AC8 system (the tire: stage requires
`its own for recovery maneuvers). The thrusters are hot gas bipropeflant engines that burn GOX/ethanol,
`
`Avionics
`
`The K-1 ras two unique requirements that aflecl the design of the avionlcs systems First, since both stages must be capable of independent flight, they
`must each have their own controi systems. Second. the CV second stage must power down for approximately 18 h while in oroit to conserve power.
`Therefore, the system must be capabis nf powering up on crblt. Like other reusebfe Iaundt systems, the K-1 must also be highly reliable to ensure that
`it can be reused over a large number oi flights.
`
`Each stage of the K 1 has its own independent guidance and control system. Because high reliability is needed, the guidance and control systems are
`triple-redundant and lauit tolerant. Navigation data are provided by three integrated Embedded GPS/INS (Global Positioning Systemflnertial Navigation
`system) devices called EG|s ’rr each stage that combine both GPS receivem and Honeywell Inertial measurement units. For the first stage, only the
`inertial date are used in the navigation solution. On the second stage, the GPS measurements are blended with the inertial data for a combined navi-
`gatinn solution. While a few other space launch systems are beginning to use GPS lor tracking, the K=1 will be one oi the first to use GPS for naviga-
`tion ln the control system. To save power -during the long on-orbit phase before reentry, the avionics, with the exception of the inertial measurement unit,
`are turred 011 after payload depfoyment.
`
`The flight computing and CC-1TliTCif1Cl functions are divided between redundant vehicle management computers (VMCs), subsystem management unit
`rsrviu}, a power distribution unit (PDUL and a payload modnfe controller (PMC}. The VMCS perform the guidance, navigation, and control computations,
`provide for communications and redundancy management, and command the propulsion and landing subsystems. The VMCS are organired as a redun-
`dam system with three identical, synchronized ttight computers, each running the same software. Voting among the three channels detects computer
`faults, and only one functioning channel is required to perform the flight. The VMCS communicate with the engine controller units on the main engines
`to implement mrnmands. Controls and power switching for most other subsystems are implemented through ccrnmunicatlohs with the SMU, PDU, and
`PMC, whicl“ serve as the direct input/output irrteifaces with these subsystems. For example, the PMC performs low-level controi of the payload deploy-
`ment motors or airbag inflation systems. All flight software for tho Vlli-1Cs_ SMU, PDU, and PMC is iutly tested irra rlardware-in-the loop simulation at C6.
`Draper Laboratory before f. ight.
`
`During flight the various subsystems communicate using three redundant MiL-STD—1553B date buses. Each of the three VMC channels controls one
`bus and monitors the others. The K-1 can transmit telemetry to the ground using the Tracking Data Relay Satellite System (TDHSS). The vehicle also
`has an FAA standard transponder. On the ground. before launch or after landing, each stage communrcates with the ground-based mission control com-
`puter (MCC) through RS-422 serial data connections. The V?\llCs are capable of storing flight data in nc-nvolatilo memory for download to the MCC after
`landing.
`
`Power for the K-1 is provded by rechargeable batteries that remain inside the vehicle and a'e charged by ground-basec charge control systems before
`toms.
`launch. Exact; stage uses three iithiurn—ion batteries to power the primary electrical system and avionics, controt motors and valves, and pyrotechnic sys-
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`
`Page 11 of 25
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 11 of 25
`
`

`
`
`
`i
`F
`_[
`i
`l
`
`|
`E
`l
`]
`
`""
`
`-
`-" xasmriaaui‘-—“‘-“‘».
`3
`3
`i
`I
`l
`i
`I
`i
`l
`:
`
`vm_-mu
`l“"“‘l
`
`it
`
`196
`K-1 4 urvnso STATES
`
`VEHICLE DESIGN
`
`Payload Module
`Like a conventional payload iairing, the iunctiori of the K ‘l Payload Module (PM): is to enclose and protect the payload. However, its design -rlitlers sig-
`nificantly from typical fairlngs. The PM is a separate element of the launch vehicle, which completely encloses the payload. it is removed from the launch
`vehicle alter landing to support processing and encapsulation of the next payload offline from the rest of the launch vehicle preparations. The torward
`dome of the PM has a blunt shape and is covered with thermal
`protective materials because it serves as the lorward surface of
`tho second stage during reentry. Unlike a conventional fairing‘
`the PM does not split open and separate from the vehicle to
`expose the payload during llight.
`instead, the forward dome
`swings open on an articulated hinge to allow payload deploy-
`rnent, theft swings back "into place and latches shut for reentry.
`Single payloads can be deployed axially out of the fixed cylin-
`drical section oi the PM. single or multiple payloads that are
`designed to be deployed radially can be pushed forward on an
`elevator plate to clear the cylindrical section, then deploy radial"
`ly. When used, the payload elevator is driven by three electii-
`caily redundant electromechanical ballsscrew actuators. Four
`interchangeable payload modules are available. The standard
`PM (SPM'i can hold payloads approximately 3 m (10 ft) tall,
`while the extended PM lEPt\.l) is roughly twice as tall. To main-
`taln oontroliability during reentry,
`the upper half of tho EPM
`retracts over the Iuwer half after payload ctoplcryment. making it
`roughly the same heght as the SPM. Acoustic blankets and
`environmental uoniroi are standard ieatures of both PM designs.
`For missions with the expendable upper stage,
`the Active
`Dispenser Payload Module is used, which shares its mold like
`and retractable fairing with the EPM. A Cargo Module (Gt./iji,
`which has the same dimensions as the SP, is available to sup-
`port ISS resuppty missions. The CM is equipped with special
`sensor arrays for lss rendezvous. a colctgas ACS, and e grap-
`ple fixture and common berthlng mechanrsrn (CBM) lor berihing
`operations with the LES.
`it
`includes a 3OArn° pressurized con-
`tainer for transportation of cargo to anotrorrs the ISS.
`
`Nliculeting
`name E099“)
`
`Purgc G:s
`mtedacizs
`
`H
`
`1
`
`,
`
`
`
`aayioaa Dem“.
`'“"““°’ El"?
`
`Counosy Kistler Aerospace Corporation
`Standard Payload Module
`
` we Imam '
`
`
`
`Courtesy Kleilel Aerospace Corporation.
`
`csr? I ‘n:
`:“a'Nn
`(160.5133)
`2520 mm |
`291tvrIgn
`(1114 in 5
`(l1-1.6m)
`zmumm
`(125.2 "U
`
`{ll5U.Cini
`
`mom»
`l1iE.5ln)
`5245 mm
`25651»)
`E
`
`5
`
`I
`
`=
`
`_
`
`l
`‘
`l
`3
`3
`1
`J
`:
`
`i
`
`l
`
`Length
`Pdmary Diameter
`Ma-9-‘-"
`Sections
`Structure
`Material
`
`fitandard Payload Module
`3.5 m (11.5 ft]
`4.3 m ($4 ft)
`1383 kg (3043 tbrn)
`1
`Honeycomb
`Composite
`
`Extended Payload Module
`5.9 m (19.2 ft)
`4.3 m (14 it)
`1689 kg (3716 lbrn)
`1
`Honeycomb
`Composite
`
`Active Dispenser
`0.7 m (12.2 ft)
`3.4 m (11 ft)
`1471 kg (3237 lbm)
`1
`Honeycomb
`Composite
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`
`Page 12 of 25
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 12 of 25
`
`

`
`PAYLOAD ACCOMMODATIONS
`
`19?
`K-1 0 UNITED STATES
`
`3350 mm (132.0 in.)
`SPM: 246-5 mm (97.1 in.)
`EPM; 4590 mm (192.5 in.)
`ADPM: 3726 mm (11167 In.)
`445 mm (17.5 in.) total height above and below lull-width volume
`2300 mm (90.55 in.)
`
`Approximately 15 months from contract to launch for a lirst launch. depending on dispenser:
`as little as 3 clays for repeat launches.
`
`1-20 min
`Not app!laahle—not storod on pad
`T-24 h
`
`+6.6 9
`:2 g
`10 Hz lateral/25 Hz axial
`125.5 dB 511100 Hz
`13-8 dB
`Dependent on separation system
`
`? P
`
`ayload module opens in orbit. Heating is near zero, depending on orbit a;'titude_
`-3.7 i(F'a/s (0.54 psi)
`Class 100,000
`
`110 km (5.4 nmi), :().05 clog :1: D 01 eccentricity, 10.04 deg FIAAN
`
`yoically 0.510 1 mls i1.6—3.3 ills) depending on separation system:
`Dispenser dependent
`23 h
`Yes, including complete de-orbit
`
`? T
`
`The K-1 will be capable 01 carrying multiple spacecraft and can provide either axial or
`radial deployment.
`Kisller is interested in carrying small payloads cn missions with surplus capability. Dispensers
`for Srriall spacccrafi are under consideration. Flideshare opportunities are available on early
`Kdflights and in conjunction with NASA Space Launch Initiative missions. Contact Kisller
`for more information.
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`
`Page 13 of 25
`
`Payload Compartment
`Maximum Payload Diameter
`Maxirnum Cylinder Langlli
`
`Maximum Cane Length
`Payload Adapter interface Diamelcr
`Payload Integration
`Nominal Mission Schedule Begins
`
`Launch Window
`Lasl Countdown Hold Not Requiring Recycling
`On-Pad Storage Capability
`I asl/lccwess to Payload
`Environment
`Mzmimtim Axial Load
`Maximum Lateral Load
`Minimum l_alsral'/l_ongiludinal Payload Fruquurluy
`Marrimum Acoustic Level
`Overall Sound Pressure Level
`Maximum Flight Shook
`Maxirnum Dyna.rm'i:: Pressure on Fairing
`Maximum Aeronearing Flare at Fairing Separation
`Maximum Pressure Cnange in Fairing
`Cleanliness Level in Fairing
`Payluad Delivery
`standard Orbit in/action Accuracy (3 sigma)
`Altitude Accuracy (3 sigma)
`Nominal Payload Separation Hale
`Deployment Flotation Flare Available
`Laiter Duration in Orbit
`
`Maneuvers {Thermal/Collision Avoidance)
`Multipleiléuxilinry Payloads
`Multiple or Comanilesl
`
`Auxiliary Paylaaas
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 13 of 25
`
`

`
`198
`K-1 0 UNlTED STATES
`
`1
`
`Production
`
`PRODUCTION AND LAUNCH OPERATTONS
`
`Kistlemerospace Corporation performs overall design, systems engineering, add operation of the K-1 launch vehicle. Detailed design and manufact_u:
`ing are contracted to a number oi esiablishoo aerospace companies. each of which has relevant experience .n the subsystems for which they are
`responsible.
`
`Organization
`Kr'stIerAsrospacev Corporation
`Aerojet
`Lockheed Martin Michaud Spoor: Sysloms
`Norlhrop Grumman Cor,oorah'on
`Charles Stark Draper Laboratory
`Honeywell
`.'rw‘r‘rAa'Iospaz:e, inc,
`Oceaneerfrzg Space Systems
`
`Launch Facilities
`
`Responsibility
`Systems engineering, program managemerl, vehicle afiselilblyi and operations
`A-526158/59/60 main engines, OMS. and Subsystem:
`Aluminum tanks
`Composite FlP tank and vehicle structure
`GNC system and lllght soltware
`Venlcle management system and flight computer
`Parachutes and airbags
`Thermal protection system
`
`95'’
`inclination
`(Azimuth) M4")
`
`34::
`(5.)
`
`
`
`\ i
`
`'1,
`
`'\
`
`Spaceport
`
`(I
`n Woomera
`
`xl
`
`
`
`Latitude:
`Longitude:
`Elevation:
`
`31.08“ South
`136.66° East
`561 f‘:
`
`oounesy Kistier Aerospace Co poraiiu.-i.
`Australia Launch Site, Spaceport Woomera
`inclination
`99"
`34°
`{A2‘imuih)
`(-14°)
`(5°i
`.___E.
`. .°1‘/°.":".‘:f_,‘§§ (‘L
`mwtnrucz v
`
`
`
`
`Spaceport
`Nevada
`
`Latitude:
`Longitude:
`Elevation:
`
`37.1?“ North
`1 16.2?“ West
`5700 ft
`
`Sc-urtesy KistIe' Aerospace Corporation
`Nevada Launch Site, Spaceport Nevada
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`
`Page 14 of 25
`
`Space Exploration Technologies; NEW PETITION
`Exhibit 1112
`Page 14 of 25
`
`

`
`—
`
`199
`K-1 ¢ UNlTED STATES
`
`I’RoDUcs1oN AND LAUNCH OPERATIONS
`
`Larmch Operations
`The K-1 will be launched from Woomera. Australia. A second launch site is planned at the Nevada Test Site near Las Vegas, Nevada, in the United
`grates. Both sites offer large, flat areas for parachute recovery of the stages, and tow population density so that the vehicle can fly over land. Spaceport
`woorners will be activated first. Launch operations from Woomera are described below and operations in Nevada will be similar.
`The K-1 witl initially be launched from a new iauhch complex in the Woomera Prohibited Area,
`in South Australia, roughly 470 km (280 mi) north of
`Adelaide. Woomcira was originally developed in 1946 as a ioint British and Australian test site for long-range missiles, sounding rockets, and, eventual-
`|-y_ of space launch vehicles. in 1967, Australia launched its first satellite irorn Woomere using a SPARTA rocket, a modified U.S. Fledstona. Several ta lad
`39513 of the joint European Europa space launch vehicle took place at Woomra from 1968-1970. in 1971 a British Black Arrow launch vehicle placed
`the Prospero satellite In orbit. However, following the cancellation of the Black Arrow program, the United Kingdom abandoned Woomera in 1976. With
`the exception of sounding rocket launches and support crl Japanese reentry vehicle tests, there has been little space—relaled actiifly at Woornera since.
`{F19 Kistter facilities at Woomera are located along the Kooiymilka—Woomora road at Ashton Hill, about 19 km 1 12 mil northwest of the village of
`Woomera. l-(lstier has leased approximately 30 ion? (12 mi?) lrom the government of Australia. Within Spaceport Woomera are three primary areas: a
`1_s—km (1.1-mi) diam fiat, open area reserved for parachute landings of the returning stages, a