Space Launch Vehicle: Using Surplus ICBM Motors to Achieve
• SSC98-III-3
• The Orbital/Suborbital Program (OSP) "Minotaur" Space Launch Vehicle: • Using Surplus ICBM Motors To Achieve Low Cost Space Lift For Small Satellites Major Steven 1. Buckley, Captain Steven C. Weis, • Lieutenant Luis M. Marina, Jr., and Lieutenant Christopher Blair Morris Space and Missile Test and Evaluation Directorate 3550 Aberdeen Avenue SE • Kirtland AFB, NM 87117-5776 (505) 846-0185 • [email protected] • Scott Schoneman Orbital Sciences Corporation Launch Systems Group • 3380 South Price Road Chandler, AZ 85248 • (602) 814-6688 • [email protected] Abstract. The United States Air Force is developing a new family of launch vehicles using surplus Minuteman II • rocket motors to support both orbital launches of small satellites and suborbital ICBM-trajectory missions. Under the OSP contract awarded to Orbital Sciences Corporation in September 1997, four different vehicle configurations are being developed: I) single reentry vehicle ballistic launch, 2) multiple payload ballistic launch, 3) flight test • capability for developmental upper stages, and 4) space lift capability for small U.S. Government satellites. The space launch vehicle or "Minotaur" is composed of an M-55 (Minuteman II Stage 1), SR-19 (Minuteman II Stage • 2), Orion 50XL (Pegasus Stage 2), Orion 38 (Pegasus Stage 3), Pegasus avionics section, and Pegasus fairing. The initial launch of Minotaur will take place in September 1999 and will carry two military satellites: the FalconSat • payload for the U.S. Air Force Academy and the JA WSAT payload for the Space Test Program.
• Introduction pursued the use of surplus Intercontinental Ballistic Missile (ICBM) rocket motors to reduce the cost of • The desire for reliable, low-cost access to Low Earth small space lift in support of DoD and other U.S. Orbit (LEO) for small Research and Development Government small satellite projects. The concept is (R&D) satellites has increased in recent years. For simple. The largest components of hardware costs for • example, numerous small satellite initiatives have small space lift are the rocket motors that make up the emerged at colleges and universities. The Department various stages. This cost is typically 300/0-50% of the • of Defense (DoD) has a long history of using small cost of a ride to orbit. satellites to support the testing of new components prior • to incorporation into large-scale operational satellite The U.S. Air Force has developed and fielded several programs. There are significant small satellite programs generations of ICBMs in support of national defense within NASA, the Department of Energy, and other programs. These missiles served long and well on • United States government agencies. Finally, advances "alert" guarding the United States from attack. As in satellite manufacturing technology have allowed the these systems aged, they were retired and replaced with • size and mass of satellites to diminish without loss of newer systems. These ICBM components were stored capability. All of these factors have contributed to the for future use or disposal. Over the years, these assets • growing need for reliable, low-cost small spacelift. have been used to support a variety of DoD programs. Smaller rocket motors have been used to drive rocket There are currently several initiatives underway to meet sleds to test aircrew egress systems, missile guidance • this requirement. The techniques used to reduce launch systems, or conduct scientific research in human factors costs include new manufacturing techniques, reusable engineering or other areas of scientific investigation. • systems, streamlined operational procedures, and the Larger motors have been integrated with other motors • use of surplus components. The U.S. Air Force has to make small sub-orbital rockets used for R&D • Major Steven 1. Buckley 12th AIAA/USU Conference on Small Satellites • • activities or target systems. Some ICBM systems, such fairing from the Pegasus XL air-launched space • as the Atlas and Titan II missiles, have been converted vehicle. The Minotaur approach reduces development to stand-alone space launch vehicles. and recurring launch costs by the utilization of • commercially developed, flight proven components and Currently, the Air Force has retired all Minuteman I propulsion from the Pegasus vehicle. Moreover, launch and Minuteman II solid rocket ICBM systems. These support costs are further reduced by adapting much of • missiles were dismantled and transported to the austere site stool launch approach demonstrated by government depots for storage under controlled the Taurus launch vehicle. • conditions. There are several hundred motor sets available to support DoD launch vehicle initiatives. The overall vehicle configuration is shown in Figure I. • These components are controlled and maintained by the It consists of two major subassemblies: I) the Lower Rocket Systems Launch Program (RSLP) located at Stages Assembly (LSA) consisting of the Minuteman Kirtland Air Force Base, New Mexico. RSLP has used boosters and 2) the Upper Stages Assembly (USA) • these Minuteman assets over the last thirty years to incorporating the Pegasus-derived front section and support DoD research and testing, chiefly as target new interstage. The vehicle length is approximately • vehicles for interceptor and sensor testing. The Air 63 ft from Stage nozzle exit planes to the top of the Force has a goal to use these components to support fairing. The launch weight of the Minotaur is 79,800 orbital launches as welL • Ibm, not including the mass of the payload. A variety of launch vehicle configurations have been • proposed over the years but none met the minimum lift Propulsion requirements and none were developed until the RSLP • program initiated the OrbitaVSuborbital Program All four boosters are solid propellant motors with the (OSP). The goal of the OSP program is to develop and characteristics shown in Table 1. The M55 and SRI9 field suborbital and orbital Minuteman II derived utilized for Stages I and 2 were originally developed • launch vehicles in support of DoD activities. The and produced for the Minuteman II ICBM. Because of program consists of two suborbital configurations, the the reduction in ICBMs due to the START-l treaty, • capability to use Minuteman II stages to boost several hundred sets of Minuteman boosters are in developmental upper stages into space for flight test, storage and available for use. They are provided as and an orbital small launch vehicle nicknamed • Government Furnished Property (GFP) through RSLP. "Minotaur". All elements of the OSP program, with The Orion 50XL developed for Pegasus is used as the the exception of the experimental upperstage test third stage motor instead of the normal Minuteman II • capability, are designed to be a "launch service". M57. This provides additional throw-weight capability as well as allowing the existing Pegasus Orion 38 motor • The Air Force contracted with Orbital Sciences and fairing to be used without changes. A relatively Corporation to integrate the surplus rocket motors with simple metallic interstage structure is used to integrate other components (the Minotaur uses Pegasus XL the Pegasus and Minuteman motors. This approach • components), integrate the launch vehicle with the reduces design risk by keeping the top two stages of payload and launch facilities, and execute the launch Minotaur identical to the Pegasus XL's top two stages • mission. This gives the Air Force flexibility to support a variety of sub-orbital missions as well as an efficient system to support small space lift requirements. The Payload Fairing • major interest of the small satellite community is in the Minotaur Small Launch Vehicle (SL V) so this paper The baseline Payload Fairing utilized by Minotaur is • will concentrate on this configuration. the same fairing design used by Pegasus. It is 14.5 feet long with and principal diameter of 50 inches. The • nominal mass for the integrated fairing system is 374 Vehicle Description Ibm. It is constructed of 60 mil face sheets over 0.5 in aluminum honeycomb. Honeycomb venting is provided • The Minotaur is a four stage, ground launched, solid through small holes in the inner face sheet, while bulk propellant, and inertially guided spacelift vehicle. It venting is accommodated via two cutouts near the base • uses the fITst two stages from the Minuteman II ICBM of the fairing. The fairing completely encloses the combined with the upper two stages, structure, and payload, avionics subsystem and fourth stage motor. • • Major Steven J. Buckley 2 12''' AIAAlUSU Conference on Small Satellites • • • • • • • • •
r.~"'1.'.s1i:,1'.t'8.(.(j~;·I2~ ~1 'ie,," • ;\iZI,.ITVC • ';l~~IGvrol1d6.,.~ • • -'i.llif'l'lt(l"':'A • • • Figure 1. Minotaur Vehicle Configuration
• Table 1. Minotaur Booster Characteristics • Stage 1 Stage 2 Stage 3 Stage 4 MM55Al MM SR-19 Orion 50XL Orion 38 Dimensions • Length 294.87 in 162.32 in 141 in 52.7 in Diameter 65.69 in 52.17 in 50.2 in 38in Mass (each) • Propellant Mass 45830 Ibm 13753 Ibm 8633 Ibm 1699 Ibm Gross Mass 50885 Ibm 15506 Ibm 9551 Ibm 1977 Ibm Structure • Type Monocoque Monocoque Case Material D6AC Steel 6AI-4V titanium Graphite Epoxy Graphite Epoxy Propulsion • Propellant TP-HIOll Type II ANB-3066 HTPB HTPB Average Thrust 178000lbs 603l21bs 345151b 704351b Number of Motors 1 1 1 1 • Number of Segments 1 1 1 1 Isp 237 sec vac 287.5 sec vac 290.1 sec vac 290.2 sec vac Chamber Pressure 1019 psia 656 psia • Expansion Ratio 58.6:1 67.5:1 Control-Pitch, Y aw TVC (±8°) LlTVC EMA(±3°) EMA(±3°) Roll TVC (±8°) WarmgasRCS Nitrogen Cold Gas RCS Nitrogen Cold Gas RCS • Events: Nominal Bum Time 60.8 sec 65.54 sec 72.5 sec 69.6 sec Stage Shutdown bum to depletion bum to depletion bum to depletion bum to depletion • Stage Separation Spring Ejection Spring Ejection • • • • Major Steven J. Buckley 3 121h AIAAlUSU Conference on Small Satellites • •
Openings in the fairing are provided for two sets of executes a series of pre-specified commands contained • RCS thruster pods, a payload access door (second door in the mission data load to provide the desired initial available as an option) and pyrotechnic bolt cutters for payload attitude (prior to payload separation). The • separation of the forward fairing clamp ring. When on attitude can be inertially and spin stabilized. For the launch pad, the payload area may be cooled and inertial attitudes the payload and fourth stage can be maintained under positive pressure by the conditioned oriented to an accuracy of better than ±4 degrees in • air supply through a fly~away connection to the fairing. angular position in each axis. For spin stabilized, the It also supports a nitrogen purge option when required maximum spin rate attainable depends on the payload • by the payload. and spent fourth stage combined spin axis moment of inertia. • Avionics Airborne Range Safety System (ARSS) • Minotaur utilizes avionics similar to those on Pegasus and Taurus with modifications to increase the The Minotaur vehicle combines proven and qualified • capability and flexibility of the Minotaur system. As components from Pegasus, Taurus, and Minuteman. with Pegasus, the avionics mount onto the cylindrical The Stage I and 2 flight termination system (FTS) • avionics structure attached to the Orion 38 with the ordnance is the All Ordnance Destruct System (A ODS) upper end of the avionics structure providing the used on every Minuteman test flight. Similarly, the payload interface plane. The structure is fabricated FTS ordnance on the Orion 50XL and Orion 38 are the • from a composite material (0.5 inch aluminum identical components and configurations as Pegasus. A honeycomb core with graphite/epoxy face sheets) with new ordnance interface is being developed and will be • the avionics components primarily mounting onto the fully qualified for the Minotaur system. The command outer circumference of the structure. Some destruct receiver has been flown on Taurus. As a components are mounted to the inner diameter of result, the overall ARSS is expected to be certified to • structure to facilitate packaging within the fairing EWR 127-1 (95) requirements with primarily analytic volume. Components mounted to the interior of the verification requiring minimal re-qualification. • structure include the Litton LN~ 100LG inertial measurement unit. The other avionics components include the Oettle Reichler (or) flight computer, • Performance telemetry transmitter, telemetry multiplexer, ordnance and RCS thrusters, dual flight termination receivers, The Minotaur launch vehicle will be capable of placing • radar transponder, batteries and various other a 780 Ibm payload into a 400 om circular, sun components and harnesses. synchronous orbit, or 1482 Ibm into a 100 om circular, • 28.5 deg orbit. Figure 2 shows Minotaur performance into other orbits. The available payload envelope using Attitude Control Systems (ACS) the baseline Pegasus fairing (see Figure 3) is 46 inches • in diameter for the first 48 inches above the payload Minotaur utilizes the existing Minuteman II thrust interface plane tapering to 29.9 inches in diameter at • vector control (TVC) for stage 1 control which uses 4 the maximum length of 88 inches. nozzles to achieve 3 axis control. Control during the SR~ • 19 burn is provided by liquid injection TVC with warm gas utilized for roll control. Upper stage (both Standard Payload Accommodations Orion 50XL and Orion 38 stages) thrust vector control • is supplied by gimbaled actuation of the single flexseal The Minotaur uses the Pegasus fairing and interfaces to nozzle from independent pitch and yaw actuators. Roll provide an adaptable, flight proven system without • attitude is controlled by cold gas jets located on the additional development risk. Interface Control avionics structure. This cold gas system is identical to Documents (ICDs) will be used for each mission to that used on Pegasus. Openings in the payload fairing document all mission specific requirements and to • permit reaction control prior to payload fairing ensure efficient resolution of all integration issues. separation. The cold gas control is also employed • during every coast phase to maintain three axis control. The payload fairing is identical to the Pegasus fairing. Following orbital insertion, the Minotaur fourth stage Payload access is provided by a single 8 X 13 inch door • • Major Steven J. Buckley 4 12th AIAAlUSU Conference on Small Satellites • • •
• that can be positioned as required on a mISSIon by with the Taurus and Pegasus vehicles. A thermal mission basis. The payload interface is the forward protection system (TPS) will be used on the fairing to • flange of the avionics structure via a 38 inch diameter minimize the temperature of the fairing inner wall. bolt ring. Optional adapter cones and separation Temperatures inside the fairing will be maintained • systems are also available in various sizes. within 200 degrees Fahrenheit. A low emissivity fairing liner is available, if required, to reduce radiation Sixteen discrete outputs are provided to initiate payload exchange between the fairing and the payload. • functions and deployments. A telemetry interface is provided by a Loral Conic PCM600. Payload electrical Standard Pegasus contamination control, maintaining a • interface on the pad will be provided by a dedicated Class 100,000 environment, will be used on the • ground umbilical. Minotaur. • Axial and lateral loads are expected to be in-family
1~r--'--'---.ri --'!--'i--'I---ir-~ IORBIt A.S~NSYN~ • looo~~----t-·--~-+--+-~--~~ • 1000
• 800 700 • 800 400 0 50 100 150 ~ 250 300 350 400 • CIRCUU\R ORBIT ALTITUDE (nm) CIRCULAR ORBIT ALTITUOE (nm) • • Figure 2. Minotaur Performance
,.-- PAYLOAD ACCESS • OSP REQUIREMENT S.5"X 13" PAYLOAD AVAIlABLE INTERFACE PLANE • ENVELOpE • • • STANOARO PAYLOAD AVIONICS ACceSS DOOR SHELF • ZONE • • • • Figure 3. Minotaur Standard Fairing • Major Steven J. Buckley 5 Ii" AIAAlUSU Conference on Small Satellites • •
Non-Standard Options Nitrogen Purge • The following outlines the non-standard options A nitrogen purge system is available for payloads with • available to the customer to customize this launch more stringent contamination requirements. This vehicle. There are several available options ranging option provides continuous nitrogen purge from • from larger volume payload accommodation to a pay load encapsulation up until launch. custom soft ride system that tunes the environments to more benign levels. Any or all of these options can be • exercised on each mission. Second Payload Access Panel • The basic launch service includes' one payload access Increased Payload Volume door. For dual manifested missions or to provide additional payload access, an additional door can be • The payload customer may procure a larger fairing to purchased for access to both satellites. accommodate their space vehicle. The Air Force is • pursuing a joint large fairing developmental effort between Orbital, Air Force Research Lab (AFRL), and Navigation Data • Boeing that will use composite materials manufactured by a fiber placement system. While the fmal A Global Positioning System (GPS) Position Beacon dimensions are TBD, the estimated interior numbers are (GPB) is an option when C-band is not available or • 52.5 inches by 130 inches. desired. The GPB is a stand-alone unit that was flown on sub-orbital missions. • Payload Separation System Enhanced Telemetry • The standard launch service does not include a separation system. A contractor-provided separations An additional encoder can be purchased to increase the • system is available as an option. The baseline is a 38 amount of information gathered from the vehicle inch separation system. In addition, 23 inch and 17 during flight. This option is being exercised on the first • inch separation systems that have flown on Pegasus are mission to help defme the exact environments available. The system imparts a velocity of 3 feet per experienced during this flight. This will increase total second with tip off rates less than five degrees per bit rate available to 2 Mbps. • second. • Enhanced Contamination Control Enhanced Insertion Accuracy Enhanced contamination control similar to that used on • The customer can increase the accuracy of their Pegasus is available as an option on the Minotaur satellite's orbit by the procurement of a Pegasus vehicle. This option allows for a Class 10,000 • Hydrazine Auxiliary Propulsion System (HAPS) to environment to be maintained. All materials within the maximize the accuracy' of the insertion orbit. This fairing are cleaned, the payload is encapsulated in a • system provides a deviation of only +/- 10 nautical GFE clean room, and HEPA filters maintain the miles and +/- 0.1 degree inclination accuracy. environment following encapsulation. • Conditioned Air Soft Ride For Small SateUites (SRSS) • Space vehicle temperature and/or humidity The soft ride system helps satellite payloads to requirements that are more rigorous than the standard withstand the launch loads by tuning the acoustic • launch service parameters can be met with an option to vibrations that could damage the space vehicle away purchase conditioned air. The conditioned air will be from payload resonating frequencies to more • provided from payload encapsulation through launch acceptable frequencies. This system is currently being operations and is accomplished by using fly-away designed by AFRL through a Small Business • ducts. Innovative Research (SBIR) contract with CSA • Major Steven J. Buckley 6 12th AIAA/USU Conference on Small Satellites • • •
• Engineering of Palo Alto, California. A similar system Launch Operations Concept has flown on previous Taurus missions. It can be used • either above or below the separation system and should The launch operations concept for the Minotaur be available for use by either or both payloads in a dual program is very similar to the Taurus capability. The • manifest situation. The weight of each system will be system is completely self contained and is capable of no more than 25 pounds. supporting a launch from an austere location if necessary. The system is composed of a Launch • Support Van that contains the minimum control stations Multi-Payload Capabilities necessary to support a launch, the Launch Equipment • Van which contains the unique interface equipment for There are currently two options in work that will allow the Minotaur launch vehicle, a 20~foot pedestal launch multiple payloads to share the same ride to orbit. One platform nearly identical to the current Taurus • is for larger payloads and the other is for micro configuration, and a sacrificial umbilical tower. These satellites. systems are detailed in Figures 4.-6. If the launch is • made from an existing launch range, this system can smoothly integrate with existing range control facilities • Dual Payload Attach Fitting (DPAF) to provide an expanded launch support capability. The frrst stage of the Minotaur stack is a Minuteman II M- This option allows for two relatively large payloads to 55 which is a treaty-compliant booster. This limits the • share a ride to orbit. One satellite fits inside the DPAF available launch sites to those that have been declared a structure (a can like structure). The other payload space launch site or a test range. The United States is • mounts to the top of this can. The frrst satellite is limited to only five space launch sites under our current separated from the top of the can, the top of the can is treaty obligations. The plan is to use four commercial separated, and then the second payload is deployed. A spaceports and a Air Force-owned launch pad to • collision avoidance maneuver is performed between support Minotaur operations. The commercial each separation event. Similar systems have been spaceports that are available are located at Wallops • flown on Pegasus missions. Island, Virginia, Cape Canaveral, Florida, Vandenberg AFB, California, and Kodiak Island, Alaska. The Air Force pad is also located at Vandenberg AFB, • Multi-Payload Adapter (MPA) California. Launch site selection will be driven by the technical requirements of the mission. The most • The other option supports micro satellite missions. important criteria for launch site selection is the This developmental adapter will fly on the first planned orbital inclination of the mission. A site at • Minotaur mission. This concept uses a structural space Vandenberg AFB (the commercial spaceport or frame with four separate bays to carry at least four government pad) or the Kodiak Island spaceport will be micro satellites to orbit. The payloads integration used for high-inclination orbits. The Wallops Island or • scheme is simple, involving a flat plate mounting Cape Canaveral spaceports will be used to support system and a separation pulse sent to each microsat to lower-inclination orbits. Launch site selection will be • fire its separation system. The Minotaur can fly two of made at least one year from the launch date. these MPA's to allow a total capacity of eight micro satellites and one larger satellite carried on top of the • MPA. • • • • • • • Major Steven J. Buckley 7 12th AIAAlUSU Conference on Small Satellites • • • • • Range Operations Control Center (Optional) • Launch Support Van (LSV) • TlM Monitor Console • Data Reduction Console • • Background limit Checking Console • Data Display Consoles • Flight Computer Console • • Power Control Console • FTS Control Console • Payload Console • • Launch Equipment Van (LEV) • Serial Interface Rack • Power Supply Rack • FTS Interface Rack • • IGN/Ann Rack .. • PayloadlJoterface Ratck n u a r o lw, • Flyaway Power Umbis • Payload Cooling Duct • • \/laming lights • lightning Protect TM14340.003 • Figure 4. OSP Launch Operations Concept • • Proven Hinge Mechanism and Active Retraction System on Taurus • • • • • • • • • • Figure 5. Minotaur Stack with Umbilical Tower • • Major Steven J. Buckley 8 12th AIAAJUSU Conference on Small Satellites • • • • SILO RECEIVER • RING (GFE) • BOLTED INTERFACE SHIMMED TO MAKE LEVEL • 2 INCHES THICK (3 PLACES, 60 • APART) • A36STEEL~ • • ~ ADAPTER RING, MISSILE BASE SUPPORT • (NEW) • • • • • TM1409!H)01 Figure 6. OSP Launch Stand
• Customer Issues Stage 3 and Stage 4 motors are manufactured by Alliant Techsystems, the fairing is also manufactured by • The major issue with using surplus ICBM components Alliant Techsystems, and various sub-systems are is that many of these components are tracked by manufactured by a variety of aerospace contractors). • international agreements or treaties. For example, the Manufacturing of these components for Minotaur M-55 Minuteman II Stage 1 is tracked by the Strategic applications strengthens the commercial space business Anns Reduction Treaty (START) and all applications base. In addition, all OSP configurations are • using an M-55 rocket motor must be treaty compliant. compatible with new commercial spaceport facilities In addition, the United States wants to foster new and a contract is in place to utilize this new launch • commercial space lift initiatives and so space launch facility capability. activities using surplus ICBM components are tracked to ensure that they comply with the Commercial Space The primary method that the Air Force uses to ensure • Act and do not adversely affect commercial space Minotaur mission treaty compliance and avoid adverse activities. effects on the commercial space community is to limit • the satellites qualified to fly on the Minotaur SL V to Many elements of the Minotaur program foster U.S. Government payloads or those sponsored through • commercial space activities. For example, while the U.S. Government agencies such as the university Air Force controls all surplus Minuteman components payloads sponsored by the University Space Research and will not allow Orbital Sciences Corporation to offer Association (USRA). Currently, no commercial • the Minotaur configuration as a commercial vehicle, the satellites will be allowed to ride on a Minotaur SLV. vehicle is designed and integrated by Orbital and major • elements of the vehicle are commercial products (the Each launch of the Minotaur vehicle (as is the case with • • Major Steven J. Buckley 9 12th AlAAlUSU Conference on Small Satellites • • • all launches using treaty compliant boosters such as the Demonstration of Capability Air Force Taurus that uses a Peacekeeper Stage I) requires approval from the Secretary of Defense. In This first launch of the Minotaur SL V will occur in • addition, un-encrypted telemetry from lift-off through September 1999 and will carry two military payloads. payload separation must be collected and made The Air Force recognizes that some non-recurring • available to Russian treaty officials. For those payloads effort is required to fully integrate the Minotaur that do qualify for lift as a Minotaur payload, the vehicle. The mission of the first launch is to capture process is simple. those non-recurring tasks, to baseline the vehicle • characteristics, and to demonstrate the viability of the The first step is the mISSIon feasibility study that launch vehicle design. To support these mission • determines that the Minotaur system can meet mission requirements, the first vehicle will be heavily requirements. This phase also includes developing the instrumented and additional technical support has been • approval package for the Office of the Secretary of provided to adequately evaluate vehicle design and risk Defense, development of a Mission Requirements mitigation. All missions after the Demonstration Document (MRD), and transfer of sufficient funds to mission will be simple launch services. • the Air Force to cover mission costs. Once approval and funding for the mission are in place, the Air Force • will assign a Mission Manager to the project, manifest Summary the mission in an open launch slot (orbital missions must maintain 60-day centers), and let the task order to The OSP program, and in particular the Minotaur small • Orbital for vehicle procurement integration, and launch. launch vehicle, represents a cost-effective way to use surplus ICBM boosters to support U.S. Government • A master mission integration schedule will be spacelift requirements. The cost of safely disposing of developed by the Mission Manager. This individual the boosters on the ground greatly exceeds the cost of will chair a series of Technical Interchange Meetings using them to lift government payloads as well as • (TIMs) to discipline mission details and develop providing significant cost savings on the launch service Interface Control Documents (ICDs) for launch costs. The availability of surplus ICBM motors • vehicle/payload and launch vehicle/launch range integrated with various commercially developed integration. Mission management will use a team systems has allowed the Air Force and its commercial • approach composed of key members from the Air partner, Orbital Sciences Corporation, to develop a Force, launch vehicle and payload contractors, and small launch vehicle that can lift almost twice the range officials. Mission success (meeting all payload payload of a Pegasus XL for about 60% of the costs. • objectives) will be the driving criteria for programmatic This capability provides an extremely cost effective and technical decisions. Six months after letting the way to lift U.S. Government payloads without • task order for the launch service, the space launch adversely affecting the growing commercial launch facility will be selected. The Air Force has the option to capability. . • use government or commercial launch facilities in accordance with U.S. treaty obligations. • • • • • • • • Major Steven J. Buckley 10 12th AIAAlUSU Conference on Small Satellites • • •
• Mission Parameters Payload Mass: 400 Ibm ~------~~ ~ ,CD> I'j3\ Out-of.f'Ion. @s"",. 4 Su"""" B ~~_ Orbtt Altitude: 400 nm x 4DO nm @ ~ 4 \:7 Tum (Orliil Insertion) _roo,,""'" • Inclination: 98.36deg. t;1\s_ 3 Ignition • Sun Synchronous -..:.:.; Separation FALCONSAT MISSION SCENARIO
• EVENT TIME ALTITUDE RANGE VELOCITY 1 Stage 1 Ignition 0.0 sec 0.00 nm O.DOnm o tVsee • 2 Pitch Down 2.5 sec 0.02 nm O.DOnm 97 tVsBe 3 Load Relief 20.0 sec 1.S2nm 0.61 nm 1,115tVsec
4 Stage 1 Separation! 60.9 sec 16.43 nm 13.73 nm 4,841 tVsec • Stage 2 Ignition 5 Stage 2 Skirt Separation BO.9 sec 27.B2 nm 26.98 nm 5,950tVsec
5 Fairing Separation 11B.3 sec 53.60nm 54.86nm 9,109 tVsec • 7 Stage 2 Separation 125.B sec 59.45 nm 74.44 nm 9,522tVsec 8 Stage 3 Ignition 127.9 sec 51.10nm 77.27 nm 9,590tVsec • 9 Out-of-Plane Tum 132.9 sec 55.01 nm 84.13nm Stage 3 Burnout 199.8 sec • 0ee,in-- 11 Stage 3 Separation 604.1 sec 12 Stage 4 Ignition 515.1 sec 13 Out-of-Plane Tum 620.1 sec • 14 Stage 4 Burnout 684.5 sec 15 Payload Separation 744.6 sec • TM14l4O.005 • Figure 7. Minotaur Vehicle Launch Scenario • • • • • • • • • • • • • Major Steven 1. Buckley 11 12th AlAA/USU Conference on Small Satellites • • • BIOGRAPHY OF Major Steven J. Buckley •
Major Steven J. Buckley is the Chief of the Small Launch Vehicle Division, Space and Missile Systems Center Test • and Evaluation Directorate, Kirtland Air Force Base, New Mexico. He provides small spacelift services to the Department of Defense and other U.S. Government agencies. His unit holds contracts that provide launch services • using the Pegasus XL, Taurus, and Minotaur launch vehicles. Major Buckley served as a U.S. Army enlisted man from 1975 to 1978. He joined the Air Force Reserve Officer Training Program and received his commission as a • distinguished graduate in 1983. As a new lieutenant, he flight tested Inertial Navigation Systems (INSs) and was assigned as Lead Flight Test Engineer for the Advanced Medium Range Air-to-Air Missile (AMRAAM) Full Scale Development (FSD) effort, conducting over 500 flight test missions using captive pods and live missiles. This • effort included over 27 live missile test missions that he supported as Mission Director, chase aircraft aircrew, and launch aircraft aircrew. Major Buckley was assigned as a Flight Test Manager to the F-15 Systems Program Office • (SPO) at Wright-Patterson AFB where he managed the testing of the F-15E APG-70 radar, F-15E missile integration effort, and the F-15E engine test program. He was responsible for developing five radar operational software loads, firing 6 missiles during live missile software verification, and integrating the Improved Performance • Engines (IPE) into the F-15E fleet. He served as Program Manager for several advanced development programs for the tactical community. He was assigned as the F-16 Program Manager for engines and several F-16 avionics • programs. He managed three major motor anomalies that resulted in one third of all F-16s world-wide being grounded. He instituted actions to inspect these aircraft and fix anomalies that resulted in five F-16s "saved" when • components were replaced within several flight hours of catastrophic failure. Major Buckley transferred to his current assignment in April 1995 and immediately took charge of the Pegasus launch vehicle Return to Flight (RTF) after the Air Force mission failure in June 1995. This effort resulted in the successful Radiation Experiment II • (REX II) in March 1996 that recovered the Pegasus capability for the United States. He managed three Air Force Pegasus launches and supported several NASA and foreign missions as Air Force Observer. His unit is working on • two upcoming Taurus missions and took a leading role in the development of the new Minotaur vehicle that uses Minuteman II and Pegasus components to provide lower cost small spacelift. Major Buckley holds a Bachelor of Science degree in aerospace engineering from the University of Florida and a Master of Science degree in aerospace • engineering from the University of Dayton. He was the recipient of the 1987 Air Force Science and Technology Award (Test and Evaluation). His decorations include 2 Meritorious Service Medals, a Joint Service • Commendation Medal, an Air Force Commendation Medal, 2 Air Force Achievement Medals, an Army Good Conduct Medal, and a National Defense Service Medal. He is married to the former Jan Ferrara of West Palm • Beach, Florida and they have three children; Robert, Sarah, and Heather. In his spare time he likes to hunt, fish, backpack, climb mountains, and hike trails. He is actively involved in the Boy Scout program and local school planning activities. • • BIOGRAPHY OF Mr Scott Schoneman •
Scott Schoneman is Lead Systems EngineerlMission Manager for the Orbital Suborbital Program(OSP) at Orbital • Sciences Corporation (Orbital), Launch Systems Group (LS). He has fifteen years experience in missile and launch systems development. He has been with Orbital since 1992, including serving as Lead Systems Engineer - Target • Programs, leading the development of a Microsat Secondary Payload Carrier (MSPaC) for Pegasus, University-class satellite (ASUSat) interface coordination, as well as system requirements development and verification for TMD targets, Hyper-X Launch Vehicle, and other suborbital systems. Other technical experience includes conceptual • system design, trajectory analysis, GNC simulation, and aerodynamics analysis and testing. Prior to coming to Orbital, Mr Schoneman held a variety of positions in systems engineering, preliminary design, and aerodynamics at • General Dynamics, Air Defense Systems Division in Rancho Cucamonga, CA on projects including the Stinger surface-to-air missile system, anti-tank smart submunitions, laser-beam rider anti-tank missiles, and exoatmosperic • kinetic energy interceptor systems. He jointly holds patent for a telescoping missile airframe concept. He has also • Major Steven J. Buckley 12 12th AIAAlUSU Conference on Small Satellites • • • • taught gas dynamics and aerospace engineering course part-time at California State Polytechnic University, Pomona. His educational background includes MS coursework and a BS in Aerospace Engineering from the • California State Polytechnic University, Pomona in 1983. He is an Associate Fellow of the AlAA. Other AIAA activities include serving as the Chairman of the AIAA Young Members Committee, member of the Systems • Engineering Technical Committee, and Chairman of the Phoenix Section. • BIOGRAPHY OF • Captain Steven C. Weis Captain Steven C. Weis is the Chief, Small Launch Vehicle Engineering Division, Test and Evaluation Directorate, • Space and Missiles Systems Center, Kirtland Air Force Base, New Mexico. Capt Weis was born in Albuquerque, New Mexico on August 22, 1964 Capt Weis attended the University of Colorado, Boulder on a four-year Air Force • Reserve Officer Training Corps scholarship. He graduated in May 1986 with a Bachelor of Science degree in Aerospace Engineering, and received an educational delay allowing him to attend graduate school before being • called to active duty. He continued his studies at the University of Colorado and in May 1987 he completed a Master of Science degree in Aerospace Engineering. Upon entering active duty in October 1987, Capt Weis was assigned to the Integrated Engineering and Technical Management Directorate, Aeronautical Systems Center, • Wright-Patterson Air Force Base, Ohio as a Weapons Application Engineer. He was responsible for developing and verifying methodologies to analyze the capability of weapons systems in the operational environment, supporting • the Advanced Tactical Fighter, F-16 and AC-130U Gunship program offices. Capt Weis also developed and modified computer software used for data reduction and analysis, and served as computer systems manager for a network of engineering workstations supporting 30 engineers. Capt Weis was assigned to the F-22 System Program • Office in January 1992 where he served as the Lead F-22 Air Vehicle System Effectiveness Engineer. As the manager of the integrated government/contractor analysis team which predicted F -22 weapon system effectiveness • using digital models and simulations, he was responsible for providing F-22 lethality and susceptibility data for trade studies and design reviews, including the F-22 Critical Design Review. Capt Weis personally planned and • performed numerous effectiveness analyses providing critical data to the F-22 System Program Director and Chief Engineer to support program decisions impacting cost, weight and performance. Several of his studies were briefed to the Air Force Chief of Staff. Currently, Capt Weis is the Air Force's chief engineer for launches using Orbital • Sciences Corporation Pegasus XL, Minotaur and Taurus launch vehicles, and is responsible for managing all launch vehicle technical issues and risk mitigation activities supporting the launch of DoD Research & Development • satellites. He was the lead launch vehicle engineer on the successful launches of the Radiation Experiment II (REX II), Fast On-orbit Reporting of Transient Events (FORTE) and Space Test Experiments Platform Mission 4 (STEP • M4) payloads. BIOGRAPHY OF • FIRST LIEUTENANT LUIS MODESTO MARINA, JR • First Lieutenant Luis Modesto Marina, Jr. was born to Luis and Mercedes Marina on 08 February 1973 at the US • Air Force Academy in Colorado Springs, CO. As a son of Air Force parents, he was able to travel the country and the world and experience different cultures. Lt Marina's travels during his grade school years include stops in Ramstein, Germany, Warner-Robbins, Georgia, Zaragoza, Spain and upon his father's retirement in Rome, New • York. A member of the honors program, he was an active member of both the National and Junior National Honor Societies and graduated ninth in a class of 408 students. He also lettered in Varsity soccer and Varsity tennis. Lt • Marina's excellent academic record earned him several scholarships to attend the Pennsylvania State University. Among those scholarships were the Air Force Reserve Officer Training Corps (AFROTC) scholarship and the Penn State Honors Scholarship. While at Penn State, he earned a Bachelor of Science degree in Aerospace Engineering. • As part of the senior design curriculum, Lt Marina was part of the first Penn State team to design, build and wind test a model of an aircraft aimed at flying specifically in the ground effect regime. The one-tenth scale model was • also designed so that it can be altered to test flight conditions other than ground effect. His excellent record at Penn • • Major Steven J. Buckley 13 12th AIAAlUSU Conference on Small Satellites • • • State earned him membership to Sigma Tau Gamma National Aerospace Honor Society and Scabbard and Blade Tri-Service Honor society. While at Penn State, Lt Marina was an active member of the Penn State AFROTC, was a certified Calculus III tutor and played several intramural sports. Commissioned a 2nd Lt January 1996, Lt Marina • received orders to Kirtland AFB, NM. Currently, Lt Marina is a Small Launch Vehicle Mission Manager for the Air Force Small Launch Vehicle Division, Launch Test Programs, Test and Evaluation Directorate, Space and Missile • Systems. He is responsible for all mission aspects, including technical, funding, and schedule issues, of putting small satellites into low earth orbit. He enjoys spending his personal time playing soccer in the Albuquerque Men's Soccer League and fly-fishing. Lt Marina has one older sister, Mercedes Raquel, and an younger brother, David. •
BIOGRAPHY OF • SECOND LIEUTENANT CHRISTOPHER BLAIR MORRIS • Second Lieutenant Christopher Blair Morris was born to Wallace and Rebecca Morris on 07 March 1970 in Florence, AL. He spent his entire childhood in the same town. Lt Morris worked hard throughout his school years • and excelled in both middle and high schools. He was very active during his high school years participating in band, chorus, varsity soccer and serving as Vice President of the senior class. Despite this busy schedule he was a member of the National Honor Society and graduated seventh of 222 students. Lt Morris' academic achievements • earned him several scholarships to various schools, but he chose to attend the University of Alabama on an Entrepreneurial Scholarship and a Supe Store Book Scholarship. While at Alabama, Lt Morris earned a Bachelor of • Science degree in Accounting. Continuing his record of outstanding academic achievements Lt Morris earned membership in the Beta Alpha Psi Accounting Honor Society and the Phi Kappa Phi National Honor Society. He graduated Cum Laude in August 1992. After a month off, he began working toward his Masters of Business • Administration at the University of North Alabama. Lt Morris worked part time as a server in a local restaurant while a full time student and graduated in December 1994 with a 3.9 grade point average. In the summer of 1995, • Lt Morris moved to Knoxville TN and that fall began work with Oak Ridge National Laboratories (ORNL) as a fmance officer. On 28 September 1996, Lt Morris married the former Alyssa Marie Thorne of Clarksville, TN. In • November 1996, Lt Morris applied for the Air Force Officer Training School. He learned of his acceptance in February 1997 and started his training on 29 April 1997 at Maxwell AFB, AL. He fmished his training as a Distinguished Graduate and was commissioned a 2nd Lt on 08 August 1997. Lt Morris received orders to Kirtland • AFB, NM as an Acquisition Manager. Currently he is a Small Launch Vehicle Mission Manager for the Air Force Small Launch Vehicle Division, Launch Test Programs, Test and Evaluation Directorate, Space and Missile • Systems. Lt Morris is responsible for all mission aspects, including technical, funding, and schedule issues, of putting small satellites into low earth orbit. In his spare time, Lt Morris enjoys running, weight training and fishing. He is also very active in his Church. Lt Morris has one older sister, Stacey Rutland. • • • • • • • • • • Major Steven J. Buckley 14 12th AIAA/USU Conference on Small Satellites • •