Pegasus® User’s Guide April 2010 Release 7.0 Approved for Public Release Distribution Unlimited Copyright© 1996-2010 by Orbital Sciences Corporation. All Rights Reserved.
Pegasus User’s Guide This Pegasus® User’s Guide is intended to familiarize potential space launch vehicle users with the Pegasus launch system, its capabilities and associated services. The launch services described herein are available for commercial procurement directly from Orbital Sciences Corporation. Readers desiring further information on Pegasus should contact us via: E-mail to: Telephone: baldwin.bryan@orbital.
Pegasus User’s Guide TABLE OF CONTENTS PAGE 1. INTRODUCTION .................................................................................................................................... 1 2. PEGASUS DESCRIPTION..................................................................................................................... 3 2.1. Pegasus XL Vehicle Description .................................................................................................... 3 2.1.1. Solid Rocket Motors ......
Pegasus User’s Guide TABLE OF CONTENTS (CONTINUED) PAGE 4.9.4. Powered Flight......................................................................................................................... 21 4.9.5. Nitrogen Purge ........................................................................................................................ 21 4.10. Payload Electromagnetic Environment ........................................................................................ 21 4.11.
Pegasus User’s Guide TABLE OF CONTENTS (CONTINUED) PAGE 6.2. 6.1.1.4. Pegasus Launch Site Operations ..................................................................................... 41 6.1.1.5. Pegasus Systems Safety .................................................................................................. 41 Mission Integration Process ......................................................................................................... 41 6.2.1. Mission Teams.......................
Pegasus User’s Guide TABLE OF CONTENTS (CONTINUED) PAGE 8.3.1. Trajectory Analysis .................................................................................................................. 54 8.3.2. Guidance, Navigation, and Control Analyses.......................................................................... 54 8.3.3. Coupled Loads Analysis .......................................................................................................... 55 8.3.4. Payload Separation Analysis...
Pegasus User’s Guide TABLE OF CONTENTS (CONTINUED) PAGE 10.19. Pegasus Separation System Test Unit......................................................................................... 64 10.20. Round-the-Clock Payload Support............................................................................................... 64 10.21. Stage 2 Onboard Camera ............................................................................................................ 64 10.22.
Pegasus User’s Guide LIST OF FIGURES PAGE Figure 1-1. Pegasus Rollout ........................................................................................................................ 1 Figure 1-2. Pegasus Launch Locations ....................................................................................................... 2 Figure 2-1. Pegasus XL on the Assembly and Integration Trailer (AIT) ...................................................... 3 Figure 2-2.
Pegasus User’s Guide LIST OF FIGURES (CONTINUED) PAGE Figure 5-8. 59 cm (23 in.) Separable Payload Interface ............................................................................ 32 Figure 5-9. Payload Separation Velocities Using the Standard Separation System ................................. 33 Figure 5-10. Standard Payload Electrical Interface ................................................................................... 34 Figure 5-11. Payload Mass vs. c.g. Location on X Axis................
Pegasus User’s Guide LIST OF ACRONYMS 3DOF 6DOF A, Amps AACS ac A/C AFB AIT ARAR ARO ASE ATP AWG C/CAM C CCB CDR CFR c.g. c.m.
Pegasus User’s Guide NASA National Aeronautics and Space Administration NRTSim Non-Real-Time Simulation nm Nautical Miles NTE Not To Exceed OASPL Overall Sound Pressure Level OCA Orbital Carrier Aircraft OD Operations Directive OR Operations Requirements Document Orbital Orbital Sciences Corporation P/L Payload PA Payload Adapter PDR Preliminary Design Review PDU Pyrotechnic Driver Unit PLF Payload Fairing POST Program to Optimize Simulated Trajectories PPWR P Power PRD Program Requirements Document psf Po
Pegasus User’s Guide 1. INTRODUCTION On August 10, 1989, Orbital Sciences Corporation (Orbital) rolled out the first commercially developed space launch vehicle for providing satellites to low earth orbit (see Figure 1-1). Over the past 21 years, the “winged rocket” known as Pegasus has proven to be the most successful in its class, placing over 78 satellites in orbit with 40 launches as of April 2010. Figure 1-1.
Pegasus User’s Guide Figure 1-2. Pegasus Launch Locations vehicle approach is an example of the Pegasus way of providing customer oriented launch service. In the interest of continued process improvement and customer satisfaction, the Pegasus Program successfully completed a 1-year effort of ISO 9001 certification. In July 1998, Orbital’s Launch Systems Group was awarded this internationally recognized industry benchmark for operating a quality management system producing a qualityproduct and service.
Pegasus User’s Guide range coordination, launch site processing, and operations. The mission team is responsible for ensuring all mission requirements have been satisfied. 2. PEGASUS DESCRIPTION The Pegasus User’s Guide is dedicated to the discussion of the Pegasus XL configuration, capabilities, and associated services. 2.1. Pegasus XL Vehicle Description Pegasus XL is a winged, three-stage, solid rocket booster that weighs approximately 23,130 kg (51,000 lbm), and measures 16.9 m (55.
Pegasus User’s Guide Figure 2-2. Expanded View of Pegasus XL Configuration Orbital’s low-contamination frangible separation joint. These ordnance events are sequenced for proper separation dynamics. A hot gas generator internal to the fairing is also activated at separation to pressurize two piston-driven pushoff thrusters. These units, in conjunction with cams, force the two fairing halves apart. The halves rotate about fall-away hinges, which guide them away from the satellite and launch vehicle.
Pegasus User’s Guide Figure 2-3. Principle Dimensions of Pegasus XL (Reference Only) 2.1.4. Flight Termination System The Pegasus Flight Termination System (FTS) supports ground-initiated command destruct as well as the capability to sense inadvertent stage separation and automatically destruct the rocket. The FTS is redundant, with two independent safe and arm devices, receivers, logic units, and batteries. Release 7.0 2.1.5.
Pegasus User’s Guide Figure 2-4. Typical Pegasus XL Motor Characteristics in Metric (English) Units developed for the Space Shuttle ascent guidance. Attitude control is closed-loop. The vehicle attitude is controlled by the Fin Actuator System (FAS) during Stage 1 flight. This consists of electrically actuated fins located at the aft end of Stage 1.
Pegasus User’s Guide Figure 2-5. Typical Attitude and Guidance Modes Sequence 2.1.7.2. Aft Skirt Assembly The aft skirt assembly is composed of the aft skirt, three fins, and the fin actuator subsystem. The aft skirt is an all-aluminum structure of conventional ring and stressed-skin design with machined bridge fittings for installation of the electromechanical fin actuators. The skirt is segmented to allow installation around the first stage nozzle.
Pegasus User’s Guide The OCA also has the capability to ferry Pegasus across the United States or across the ocean (depending on landing site) to support ferry and campaign missions. 3. GENERAL PERFORMANCE CAPABILITY This section describes the orbital performance capabilities of the Pegasus XL vehicle with and without the optional HAPS described in Section 10.
Pegasus User’s Guide Figure 3-1. Pegasus XL Mission Profile to 741 km (400nmi) Circular, Polar Orbit with a 227 kg (501 lbm) Payload 3.2. Performance Capability Performance capabilities to various orbits for the Pegasus XL are illustrated in Figure 3-3 and Figure 3-4 (HAPS configuration). These performance data were generated using the Program to Optimize Simulated Trajectories (POST), which is described below.
Pegasus User’s Guide Figure 3-2. Pegasus XL with HAPS Mission Profile to 741 km (400nmi) Circular, Polar Orbit with a 227 kg (501 lbm) Payload trajectory design, payload mass, and the guidance strategy requested by the payload. As a result, the specific Pegasus orbit accuracy capabilities for a particular mission are generally determined only after these mission-specific details are defined and detailed mission-specific analyses have been performed.
Pegasus User’s Guide Figure 3-3. Pegasus XL Without HAPS Performance Capability based on the actual vehicle performance while minimizing the eccentricity of the final orbit. guidance strategies that are designed and tailored to meet specific mission objectives. These strategies fall into several basic categories: (1) Minimize Insertion Errors.
Pegasus User’s Guide Figure 3-4. Pegasus XL With HAPS Performance Capability orbit energy, or specific altitude and velocity thresholds may be defined, which trigger energy-scrubbing only in the event that the thresholds are exceeded. The optimal strategy for a particular mission will therefore depend on the specific guidance objectives. ination Avoidance Maneuver (C/CAM).
Pegasus User’s Guide Figure 3-6. Typical and Recent Pegasus Orbital Accuracy the separation distance between the two bodies. (2) At payload separation +300 seconds, the launch vehicle begins a “crab-walk” maneuver. This maneuver, performed through a series of RCS thruster firings, is designed to impart a small amount of delta velocity in a direction designed to increase the separation distance between Pegasus and the payload. The maneuver is terminated approximately 600 seconds after separation.
Pegasus User’s Guide loads. It shall survive those conditions in a manner that ensures safety and that does not reduce the mission success probability. The primary support structure of the spacecraft shall be electrically conductive to establish a single point electrical ground. Spacecraft design loads are defined as follows: Design Limit Load — The maximum predicted ground-based, captive carry, or powered flight load, including all uncertainties.
Pegasus User’s Guide Figure 4-1. Factors of Safety for Payload Design and Test envelope that encompasses all phases of a Pegasus launch operation including OCA takeoff, captive carry, and powered flight. events is shown in Figure 4-8. The flight limit levels are derived from ground stage and payload separation test data assuming a 38” Orbitalsupplied separation system.
Pegasus User’s Guide was used to create this overall envelope that encompasses all phases of Pegasus launch operation including OCA takeoff, captive carry, and powered flight. A +6 dB factor should be added to this spectrum for 75 seconds for payload standard acoustic testing to account for fatigue duration effects to encompass at least two launch attempts and powered flight. 4.8.
Pegasus User’s Guide Figure 4-4. Pegasus XL Maximum Quasi Steady Acceleration as a Function of Payload Weight Figure 4-5. Pegasus Net CG Load Factor Predictions Release 7.
Pegasus User’s Guide Figure 4-6. Motor Ignition Transient Shock Response Spectrum Specification Figure 4-7. Payload Interface Random Vibration Specification Release 7.
Pegasus User’s Guide Figure 4-8. Shock Environment at Base of the Payload Figure 4-9. Payload Acoustic Environment Release 7.
Pegasus User’s Guide Figure 4-10. Representative Fairing Internal Pressure Profile During Captive Carry Figure 4-11. Representative Fairing Internal Pressure Profile During Powered Flight Release 7.
Pegasus User’s Guide fairing is maintained to < 60%. The flowrate of air through the fairing is maintained between 120 and 200 cfm. 4.9.3. Ground Operations at the Flightline and Launch Operations Following transportation of the Pegasus vehicle to the Hot Pad, the fairing is continuously purged with conditioned filtered air. During ground operations, the temperature of the conditioned air, as measured at the fairing inlet, is maintained between 13 to 29 ºC (55.4 to 84.2 ºF).
Pegasus User’s Guide Figure 4-12. Pegasus XL RF Emitters and Receivers strength values in the table occur during powered flight after the payload fairing has been jettisoned and the Pegasus Stage 3 S-band antenna is active. Figure 4-13 lists the frequencies and maximum field strength associated with RF emitters on the L1011 carrier aircraft.
Pegasus User’s Guide practices that are followed to ensure payload contamination requirements are met. The VAB is maintained at all times as a visibly clean, air-conditioned, humidity-controlled work area. As a standard service, the payload can be provided with a soft-walled cleanroom that is certified and operated at Class 8 (Class 100,000) level per ISO 14644-1. This vertical down flow cleanroom is 12’(W) x 24’(L) x 14’(H).
Pegasus User’s Guide aluminum attach joint allows each half of the fairing to then rotate on hinges mounted on the Stage 2 side of the interface. 5.1.1. Fairing Separation Sequence The fairing separation sequence consists of sequentially actuating pyrotechnic devices that release the right and left halves of the fairing from a closed position, and deploy the halves away from either side of the core vehicle. The nose bolt is a noncontaminating device.
Pegasus User’s Guide Figure 5-1. Payload Fairing Static Envelope with 97 cm (38 in.) Diameter Payload Release 7.
Pegasus User’s Guide Figure 5-2. Payload Fairing Dynamic Envelope with 97 cm (38 in.) Diameter Payload Release 7.
Pegasus User’s Guide Figure 5-3. Payload Fairing Static Envelope with 59 cm (23 in.) Diameter Payload Release 7.
Pegasus User’s Guide Figure 5-4. Payload Fairing Dynamic Envelope with 59 cm (23 in.) Diameter Payload Release 7.
Pegasus User’s Guide Figure 5-5. Payload Fairing Access Door Placement Zones (shown with optional second door shown) The separation ring to which the payload attaches is supplied with through holes. The weight of hardware separated with the payload is approximately 4.0 kg (8.7 lbm) for the 97 cm (38 in.) system and 2.7 kg (6.0 lbm) for the 59 cm (23 in.) system.
Pegasus User’s Guide Figure 5-6. Nonseparable Payload Mechanical Interface Release 7.
Pegasus User’s Guide Figure 5-7. 97 cm (38 in.) Separable Payload Interface Release 7.
Pegasus User’s Guide Figure 5-8. 59 cm (23 in.) Separable Payload Interface Release 7.
Pegasus User’s Guide Figure 5-9. Payload Separation Velocities Using the Standard Separation System 5.3.1. Standard Electrical Interface The standard electrical interface between the Pegasus launch vehicle and a payload using a nominal 38” separation system is shown in Figure 5-10. In this case standard electrical interface between the Pegasus launch vehicle and payload is two 42-pin MIL-C-38999 Series II electrical connectors located at the separation plane.
Pegasus User’s Guide Figure 5-10. Standard Payload Electrical Interface Orbital will provide limited space within the Launch Panel Operator (LPO) Station on the carrier aircraft for the payload’s electrical support equipment. As a standard service, Orbital will provide personnel to operate the payload electrical support equipment during launch operations.
Pegasus User’s Guide incorporated into launch vehicle telemetry using a serial telemetry interface. This interface is either a 4-wire RS-422, or a 2-wire RS-485 serial communication link between the Pegasus flight computer and the spacecraft. Up to 250 bytes/sec of payload data can be incorporated into Pegasus telemetry. The payload data is available in the launch control room during ground operations, captive carry and powered flight.
Pegasus User’s Guide 5.4. Payload Design Constraints 5.4.1. Payload Center of Mass Constraints To satisfy structural constraints on the standard Stage 3 avionics structure, the axial location of the payload center of gravity (c.g.) along the X axis is restricted as shown in Figure 5-11. Along the Y and Z axes, the payload c.g. must be within 3.8 cm (1.5 in.) of the vehicle centerline for the standard configuration and within 2.5 cm (1.0 in.
Pegasus User’s Guide Orbital to obtain proper range clearances and protection. Figure 5-12. Payload Mass Property Measurement Error Tolerances receivers on the Pegasus launch vehicle. Prior to launch, Orbital requires review of the payload radiated emission levels (MIL-STD-461, RE02) to verify launch vehicle EMI safety margins in accordance with MIL-E-6051. Payload RF transmissions are not permitted after fairing mate and prior to separation of the payload.
Pegasus User’s Guide 5.4.7. System Safety Constraints Orbital considers the safety of personnel and equipment to be of paramount importance. The payload organization is required to conduct at least one dedicated payload safety review in addition to submitting to Orbital an Accident Risk Assessment Report (ARAR) or equivalent as defined in AFSPCMAN 91-710. 110 VAC, 60 Hz at maximum current of 15 A.
Pegasus User’s Guide 5.5.2. Payload Support at Launch Panel Operator Station Since it is not possible to accommodate payload personnel on the carrier aircraft during flight, Orbital will provide a dedicated operator to monitor and control payload ASE during launch operations. The operator, know as the Payload LPO, will monitor critical payload data, send commands, and adjust ASE settings per payloadprovided procedures as required at the direction of the Launch Conductor (LC).
Pegasus User’s Guide Figure 6-1. Mission Integration Management Structure 6.1.1.1. Pegasus Program Management The Pegasus Program Manager has direct responsibility for Orbital’s Pegasus Program. The Pegasus Program Manager is responsible for all financial, technical, and programmatic aspects of the Pegasus Program. Supporting the Pegasus Program Manager are the Contract Manager and the Pegasus Chief Engineer. All contractual considerations are administered between the payload and Pegasus Contract Manager.
Pegasus User’s Guide the Pegasus Mission Manager to ensure that vehicle preparation is on schedule and satisfies all payload requirements for launch vehicle performance. The Pegasus Mission Mechanical Engineer is responsible for the mechanical interface between the satellite and the launch vehicle. This person works with the Pegasus Mission Engineer to verify that mission-specific envelopes are documented and environments, as specified in the ICD, are accurate and verified.
Pegasus User’s Guide They provide the necessary continuity throughout each phase of the integration process from initial mission planning through launch operations. The team is responsible for documenting and ensuring the implementation of all mission requirements via the payload to Pegasus ICD. 6.2.2. Integration Meetings Two major types of meetings are used to accommodate the free flow of information between the mission teams.
Pegasus User’s Guide conducting the launch operation. Due to the variability in complexity of different payloads and missions, the content, quantity, and schedule of readiness reviews are tailored to support the mission-unique considerations. 6.3. Mission Planning and Development Orbital will assist the customer with mission planning and development associated with Pegasus launch vehicle systems.
Pegasus User’s Guide Activity Mission Integration Interface Development InterfaceControl Document Mission Analysis Coupled Loads Analysis Payload Milestones (P/L Dependent) Drawings Mass Properties Finite Element Model Integrated Procedures Range Documentation (UDS) Launch Vehicle Range Documentation (UDS) Flight Plan/Trajectory Safety Process Payload Safety Reviews Safety Documentation Operations Planning Ground Operations Launch Operations Launch Checklist/Constraints Program Reviews Launch Vehicle Hardw
Pegasus User’s Guide It cannot be overstressed that the applicable safety requirements should be considered in the earliest stages of spacecraft design. Processing and launch site ranges discourage the use of waivers and variances. Furthermore, approval of such waivers cannot be guaranteed. 6.5.2. System Safety Documentation A Payload System Safety Program Plan (SSPP) shall be submitted to and approved by Orbital and the applicable Range Safety Organization.
Pegasus User’s Guide meeting the intent of individual requirements. This is especially critical for newly designed hazardous systems, or new applications of existing hardware. sessions are held periodically to clarify the intent of requirements and discuss approaches to hazard control. These working sessions are normally scheduled to coincide with existing MIWGs and GOWGs.
Pegasus User’s Guide Payload Processing: Receipt and checkout of the satellite payload, followed by integration with Pegasus and verification of interfaces; and Launch Operations: Mating of Pegasus with the carrier aircraft, take-off, and launch. Each of these phases is more fully described below. Orbital maintains launch site management and test scheduling responsibilities throughout the entire launch operations cycle. Figure 7-2 provides a typical schedule of the integration process through launch. 7.
Pegasus User’s Guide Figure 7-2. Typical Pegasus Integration and Test Schedule Figure 7-3. Orbital Carrier Aircraft Hot Pad Area at VAFB Release 7.
Pegasus User’s Guide 7.1.1.2. Vehicle Integration and Test Activities Figure 7-4 shows the Pegasus stages being integrated horizontally at the VAB prior to the arrival of the payload. Integration is performed at a convenient working height, which allows easy access for component installation, test, and inspection. The integration and test process ensures that all vehicle components and subsystems are thoroughly tested before and after final flight connections are made. are exercised.
Pegasus User’s Guide later than 120 days prior to first use (draft) and 30 days prior to first use (final). 7.1.2.1. Ground Support Services The payload processing area capabilities depend on which mission option is chosen based on launch site: integrate and launch; integrate, ferry, and launch; or Pegasus campaign to launch site. Payload-unique ground support services are defined and coordinated as part of the MIWG process.
Pegasus User’s Guide the propellant loading facilities in the VAB at VAFB. All launch integration facilities will be configured to handle these sealed systems in the integration process with the launch vehicle. The propellant loading area of the VAB is maintained visibly clean. 7.1.3. Launch Operations 7.1.3.1. Orbital Carrier Aircraft Mating The Pegasus is transported on the AIT to the OCA for mating. This activity typically takes place about 3 to 4 days prior to launch.
Pegasus User’s Guide Figure 7-5. Typical Pegasus Launch Checklist Flow countdown procedure. The Orbital Vehicle Engineer has the overall responsibility for the Pegasus launch vehicle. A team of engineers, which reviews the telemetry to verify that the system is ready for launch, support the Vehicle Engineer. The range status is coordinated by the Range Control Officer who provides a Go/No-Go status to the LC. The third group is the Airborne Operations Group, which includes the LPO and the aircraft crew.
Pegasus User’s Guide the LPO station is supplying external power to the spacecraft, the spacecraft will be transitioned to internal power no later than L-6 minutes. At L-45 seconds, the fin thermal batteries are activated and a sinusoidal fin sweep is commanded by the flight computer to all fins to verify functionality prior to drop. The fin sweep telemetry, fin position, and command current are monitored and verified. Once this is completed, Pegasus is “Go For Launch.
Pegasus User’s Guide 8.3.1. Trajectory Analysis Orbital performs Preliminary and Final Mission Analyses using POST and the NRTSIM 6DOF analysis tool. The primary objective of these analyses is to verify the compatibility of the payload with Pegasus and to provide succinct, detailed mission requirements, such as payload environments, performance capability, orbit insertion accuracy estimates, and preliminary mission sequencing.
Pegasus User’s Guide autopilot. For the exo-atmospheric portions of flight, the autopilot margins are similarly evaluated at discrete points to account for the changing mass properties of the vehicle. The control system gains are chosen to provide adequate stability margins at each operating point. Orbital validates these gains through perturbed flight simulations designed to stress the functionality of the autopilot and excite any possible instabilities.
Pegasus User’s Guide Prior to each flight, Orbital evaluates the interaction of the flight MDL with the missionindependent guidance and control software in the Guidance and Control Laboratory (GCL). Orbital personnel conduct a formalized series of perturbed trajectories, representing extreme disturbances, to ensure that both the flight MDL and the G&C software are functioning properly. MDL performance is judged by the ability of the simulation to satisfy final stage burnout requirements.
Pegasus User’s Guide shear, bending moment, axial and lateral loads, and stiffness. For preliminary design purposes, coupled effects with the forward payload can be considered as a rigid body design case with Orbital-provided mass and c.g parameters. Integrated CLA will be performed with test verified math models provided by the payload contractors. These analyses are required to verify the fundamental frequency and deflections of the stack for compliance with the Pegasus requirement of 20 Hz minimum.
Pegasus User’s Guide Figure 9-2. Dual Payload Attach Fitting Configuration transmitted around the lower spacecraft via the DPAF structure, thus avoiding any structural interface between the two payloads. ejected from within the cylinder that remains with the third stage. For the upper payload the DPAF uses either an Orbital standard 97 cm (38 in.) Marmon clamp band interface, or an Orbital 59 cm (23 in.) Marmon clamp band interface on a separable adapter cone.
Pegasus User’s Guide Pegasus will be integrated at Vandenberg and flown to the alternate integration site. The Pegasus will be demated from the OCA, transported to the integration facility, the fairing will be removed, payload integration activities will be conducted, the fairing will be reinstalled, and the Pegasus will be transported back to the OCA and prepared for launch.
Pegasus User’s Guide 10.5. Optional Payload/Vehicle Integration Environment 10.7. Enhanced Fairing Internal Surface Cleaning Authorize by: L-20 months Authorize by: L-20 months Orbital is capable of providing a payload/vehicle integration environment that is clean, certified, and maintained at ISO 14644-1 Class 7 (10,000), to support payload integration through fairing encapsulation. As a part of this service, Orbital will provide and certify a Class 7 softwall cleanroom.
Pegasus User’s Guide tube truck is disconnected. Ground nitrogen is continually supplemented by a tube truck, so capacity limitations are generally not a problem. The payload purge can be routed directly to the payload interior via a quick disconnect device as an additional mission-unique optional service. The quick disconnect exerts less than 50 lbf on the payload fitting. Back pressure must be limited to 10 psig when the purge gas is plumbed directly into a payload supplied device.
Pegasus User’s Guide Figure 10-1. Hydrazine Auxillary Propulsion System (HAPS) Release 7.
Pegasus User’s Guide and the avionics section also alters the maximum expected shock response spectrum at the base of the payload. Environmental levels for a vehicle configured with HAPS will be provided on a mission-specific basis. 10.12. Load Isolation System Authorize by: L-24 months Orbital can provide a Load Isolation System that will lower the fundamental frequencies of the payload to avoid dynamic coupling with the Pegasus fundamental frequencies at drop.
Pegasus User’s Guide 10.16. Payload Electrical Connector Covers Authorize by: L-20 months Orbital can provide flight-proven connector covers for the payload side of the separation system to cover the 42-pin interface connectors. The connector covers are spring loaded and attach to the standard umbilical support brackets. A bracket on the launch vehicle side of the separation system is used to hold the cover open until the two halves of the separation system are physically separated.
Pegasus User’s Guide coating or thermal blankets. All work procedures and added materials must be approved by Orbital in advance of ring shipment. 10.24. Multiple Payload Adapters Including Related Mission Integration Support Authorize by: L-24 months 10.23. 43 cm (17 in.) Payload Adapter Authorize by: L-24 months As a nonstandard service, Pegasus can accommodate a 43 cm (17 in.) PA. The 43 cm (17 in.) PA is comprised of a 43 cm (17 in). Marmon clamp band separation system on a 97 cm (38 in.
Pegasus User’s Guide The impact on Pegasus performance associated with the DPA will be based on the configuration chosen and must be determined on a missionspecific basis. 10.25.1. Dual Payload Adapter with 59 cm (23 in.) Primary PA Pegasus offers a DPA that supports primary and secondary payloads in a non-load bearing configuration. The DPA uses a structural cylinder of variable length to support the primary payload PA. The cylinder encapsulates the secondary payload.
Pegasus User’s Guide 10.26. Secondary Payload Adapters for Nonseparating Secondary Payloads Authorize by: L-24 months 10.26.1. 59 cm (23 in.) or 43 cm (17 in.) PA for Nonseparating Secondary Payloads The DPA described in Section 10.24 can be used to accommodate a nonseparating secondary payload. In this application, the DPA cylinder is separated from the Pegasus launch vehicle. Orbital will provide a nonseparating PA for use by a secondary payload in conjunction with the DPA described in Section 10.24.
Pegasus User’s Guide APPENDIX A PAYLOAD QUESTIONNAIRE A Payload Questionnaire (PQ) is required from the payload organization for use in preliminary mission analysis. The PQ is the initial documentation of the mission cycle and is needed 22 months before the desired launch date. It is not necessary to fill out this PQ in its entirety to begin mission analysis. Simply provide any available information and submit the document electronically via e-mail or fax. Release 7.
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Pegasus User’s Guide APPENDIX B VAFB VEHICLE ASSEMBLY BUILDING CAPABILITIES Release 7.
Pegasus User’s Guide B1.0 GROUND SUPPORT SERVICES The payload processing area within the VAB will be made available to the payload 30 calendar days prior to launch for independent payload checkout. This area is intended to allow payload preparations prior to mate. All work performed within the VAB is scheduled through the Orbital Site Manager. Orbital will support and schedule all payload hazardous or RF test operations conducted within the VAB that require Range notification or approval. B2.
Pegasus User’s Guide Figure B-1. The Vandenberg Vehicle Assembly Building General Layout Release 7.
Pegasus User’s Guide APPENDIX C LAUNCH RANGE INFORMATION Release 7.
Pegasus User’s Guide C1.0 LAUNCH RANGE INFORMATION INTRODUCTION Pegasus’ air-launched design vastly increases launch point flexibility. Some ground support is required to ensure the safety of the people and property, to communicate with the carrier aircraft, and to provide data collection and display.
Pegasus User’s Guide C5.0 CONTROL CENTER The launch team requires a control center to conduct the launch countdown. This center requires a minimum of 20 consoles with voice nets and network computer displays. The consoles must have the capability to remote key the radios for communications with the carrier and chase aircraft. C6.0 DATA REQUIREMENTS C6.1 Recording Recording of all the telemetry downlinks is required. C6.2 IRIG Timing IRIG timing is required. C6.
Pegasus User’s Guide APPENDIX D PEGASUS FLIGHT HISTORY Release 7.
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