Atlas V Launches the Orbital Test Vehicle-1 Mission Overview. Atlas V 501 Cape Canaveral Air Force Station, FL Space Launch Complex 41

Transcription

1 Atlas V Launches the Orbital Test Vehicle-1 Mission Overview Atlas V 501 Cape Canaveral Air Force Station, FL Space Launch Complex 41

2 Atlas V/OTV-1 United Launch (ULA) Alliance is proud to support the Air Force Rapid Capabilities Office (RCO) with the first launch of the Orbital Test Vehicle (OTV). The OTV, also known as the X-37B, supports space experimentation, risk reduction, and concept of operations (CONOPS) development for long duration and reusable space vehicle technologies. My thanks to the entire Atlas team for its dedication in bringing the OTV to launch, and to the RCO for selecting Atlas for this ground breaking mission. Go Atlas, Go Centaur, Go OTV! Mark Wilkins Vice President, Atlas Product Line 1

3 Atlas V 501 Vehicle Configuration Overview The Atlas V 501 configuration consists of a single Atlas V booster stage and the Centaur upper stage. The Atlas V booster is 12.5 ft in diameter and ft long. The booster s tanks are structurally stable and constructed of isogrid aluminum barrels, spun-formed aluminum domes, and intertank skirts. Atlas booster propulsion is provided by the RD-180 engine system (a single engine with two thrust chambers). The RD-180 burns RP-1 (Rocket Propellant-1 or highly purified kerosene) and liquid oxygen, and delivers 860,200 lb of thrust at sea level. The Atlas V booster is controlled by the Centaur avionics system that provides guidance, flight control, and vehicle sequencing functions during the booster and Centaur phases of flight. The Centaur upper stage is 10 ft in diameter and 41.5 ft long. Its propellant tanks are constructed of pressure-stabilized, corrosion resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen- (cryogenic-) fueled vehicle. It uses a single RL10A-4-2 engine producing 22,300 lb of thrust. The cryogenic tanks are insulated with a combination of helium-purged insulation blankets, radiation shields, and closed-cell foam insulation. The Centaur forward adapter (CFA) provides the structural mountings for vehicle electronics and the structural and electronic interfaces with the spacecraft. The OTV mission is encapsulated within the Atlas V 5-meter-diameter short payload fairing (PLF). The 5-meter PLF is a bisector PLF with a composite structure made from sandwich panels with carbon fiber face sheets and a vented aluminum honeycomb core. The 5-meter PLF is comprised of two major components: the lower section, or base module, that encapsulates the Centaur, and the upper section, or common payload module (CPM), that encapsulates the spacecraft. The Atlas V booster, Centaur, and the 5-meter payload fairing boattail are attached by the 3.8-meter diameter Centaur interstage adapter (C-ISA). The C-ISA is a composite structure with graphite epoxy facesheets over an aluminum honeycomb core. 2

4 Atlas V 501 Vehicle Forward Load Reactor (FLR) Orbital Test Vehicle Centaur RD-180 Engine Atlas V Booster Cylindrical Interstage Adapter Centaur Interstage Adapter RL 10A Centaur Engine Centaur Conical Interstage Adapter Payload Fairing 3

5 Atlas V Processing Overview Denver, CO Booster Fabrication & Final Assembly Centaur Final Assembly Cape Canaveral Air Force Station, FL Payload Processing & Encapsulation Launch Vehicle Processing Encapsulated Payload Mating Launch San Diego, CA Centaur Tank Fabrication Harlingen, TX Booster Adapter Fabrication Centaur Adapter Fabrication Zurich, Switzerland 5-meter Payload Fairing Manufactured at RUAG Space 4

6 Launch Site Processing Overview Atlas Spaceflight Operations Center (ASOC) Receiving & Inspection VIP Viewing Launch Control Center ULA Offices Communication Center Mission Director s Center Battery Lab ITAR Facility Administrative Offices Conference Center Material Stores Centaur Antonov AN-124 Interstage Adapters Antonov AN-124 Booster 5-m Payload Fairing Halves Vertical Integration Facility Integration Spacecraft Mate Testing SLC-41 Testing & Launch Payload Transporter Mobile Launch Platform Spacecraft Processing Facility Processing Testing Encapsulation Spacecraft 5

7 Launch Site Overview Space Launch Complex 41 Vertical Integration Facility (VIF) Ordnance Annex Atlas Spaceflight Operations Center (ASOC) Customer Support Center (CSC) Launch Control Center (LCC) 6

8 Launch Site Overview (concl d) Entry Control Bldg. (ECB) VIF Launch Vehicle MLP Bridge Crane Hammerhead Bridge Crane Centaur LO 2 LH 2 Storage Area Pad ECS Shelter RP-1 Storage Area Launch Vehicle MLP Gaseous Helium Conversion Plant Booster LO 2 Pad Equipment Bldg. (PEB) Pad Support Area Payload Van High Pressure Gas Storage Ready Room Southwest View of Space Launch Complex 41 (SLC-41) South View of the Vertical Integration Facility (VIF) 7

9 OTV Flight Profile Atlas/Centaur Separation Centaur MES-1 Centaur MECO-1 PLF & FLR Jettison Atlas Boost Phase Mission Overview: Developed by the United States Air Force, the X-37B OTV is the United States newest and most advanced re-entry spacecraft. Objectives of the autonomous, unmanned space test platform include space experimentation, risk reduction, and CONOPS development for long duration and reusable space vehicle technologies. The Boeing Company is the prime contractor for the OTV program and the Air Force Rapid Capabilities Office is leading the initiative with continued participation by NASA. Key objectives of the first flight include demonstration and validation of guidance, navigation and control systems to include fault tolerant, autonomous re-entry and landing as well as lightweight high-temperature structures and landing gear. On-orbit tests of the thermal management, power control and distribution, and attitude control subsystems are also planned objectives. Vandenberg Air Force Base (AFB) will be the primary landing site, with Edwards AFB as a backup. Liftoff 8

10 Sequence of Events Event RD-180 engine ignition Liftoff Start pitchover, turn to zero alpha Begin zero angle of attack flight Start alpha bias steering Enable guidance steering Payload fairing jettison Forward load reactor jettison Booster engine cutoff (BECO) Atlas/Centaur separation Centaur first burn, main engine start (MES-1) Centaur first burn, main engine cutoff (MECO-1) Time (seconds) Values Approximate 9

11 Atlas V Countdown (F-1 Day) F-1 Day - MLP TRANSPORT TO PAD T-11:30 T-11:00 T-10:00 T-9:00 T-8:00 T-7:00 T-6:00 T-5:00 T-4:00 T-3:00 Start Count Weather Brief Status Check Weather Brief Status Check MLP Hard Down MLP MLP Transport Preps MLP Roll MLP Connect GC3 & RF / FTS Transport Preps Pad Connections Flight Control Flight Control Preps Atlas RP-1 RP-1 Tanking (If Required) Atlas/ Centaur Pneu, Prop Transport Preps Pneumatic System Preps 10

12 Atlas V Countdown (F-0 Day) F-0 Day - LAUNCH T-6:20 T-6:00 T-5:00 T-4:00 T-3:00 T-2:00 T-1:00 T-:45 T-:30 T-:15 T-:04H Start Count Weather Brief Status Check Weather Brief Status Check Flight Control GC3 & RF / FTS Power Application, System Preps, Flight Control/Guidance Tests & Countdown Preps Open Loop Test & Monitor Preps Flight Control Final Preps Open/Closed Loop Tests T-0:04 (T-4) & Holding ECS ECS GN2 Preps All Systems on GN2 LAUNCH Atlas/ Centaur Pneu, Prop Centaur LH 2 /LO 2 Preps Atlas Propulsion/Hydraulic Preps Storage Area Chilldown Pressurize Chilldown & Tanking 11

13 12 Notes

14 Copyright 2010 United Launch Alliance, LLC. All Rights Reserved. Atlas is a Registered Trademark of Lockheed Martin Corporation. Used with Permission. United Launch Alliance P.O. Box Littleton, CO (720)