Virgin , LLC / Version 2.1 / August 2020 Cleared for Release: 18-S-1862 – As Amended

1 LAUNCHERONE SERVICE GUIDE [email protected] •+1 562 384 4400 •virginorbit.com President and CEO Virgin of Orbit Hart Dan space to change the world for good! We invite you to contact us and share your mission needs. Together we open customer service that distinguishes Virgin companies. free, and we are enabling this with streamlined processes and the superior pre-launch paperwork. We believe launching your small should hassle- be provides freedom from the constraints of fixed ground infrastructure and onerous from scratch with these guiding principles, the LauncherOne air-launch system movement—to get small to orbit quickly, reliably, and affordably. Designed at lower cost. We developed LauncherOne to complement this transformational that benefit our . Small satellites are doing more on shorter timelines, and global connectivity, remote sensing, security, and other new, visionary capabilities Virgin Orbit is excited about the tremendous potential of small satellites to provide REVOLUTION LAUNCHING THE 2 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 7 6 5 4 3 2 1 CONTENTS A 1.5 1.4 1.3 1.2 1.1 A.4 A.3 A.2 A.1 7.3 7.2 7.1 6.2 6.1 5.12 5.11 5.10 5.9 5.8 5.7 5.6 5.5 5.4 5.3 5.2 5.1 4.6 4.5 4.4 4.3 4.2 4.1 3.6 3.5 3.4 3.3 3.2 3.1 2.9 2.8 2.7 2.6 2.5 2.4 2.3 2.2 2.1 APPENDIX DOCUMENT REFERENCE LOCATIONS ORBIT VIRGIN ENVIRONMENTS OPERATIONS LAUNCH AND PROCESSING PAYLOAD PROCESS SERVICE LAUNCH ORBIT VIRGIN THE MISSION YOUR DESIGN EXPERIENCE ORBIT VIRGIN THE

Capabilities at aGlance System Our to Know Get ExtraordinaryThe of Air Powers Launch Corporate Overview VirginAbout Orbit Customer Testing Requirements Spacecraft Customer Description of Deliverables Customer Deliverables Orbit Virgin of Description ofOverview Virgin Orbit Deliverables &Customer by Milestone List of Figures List of Tables Acronyms of List FacilitiesSpaceport VehicleLaunch Test and Production Facilities Spacecraft Qualification Compliance and Environment Fairing Pressure Humidity Environment and Thermal VehicleLaunch Carrier and to not exceed RF Electric Field Limit Spacecraft Intentional Emitters Receivers and Payload Radio Frequency (RF) Constraints Acoustics Vibration Random Environment Shock Quasi-Static from Acceleration Loads Constraints Payload System Coordinate Vehicle Mechanical Electrical and Access Flow Operations Launch Locations Launch Transport Payload Payload Processing Facilities Payload Processing Flow U.S. Compliance Export and Import Policy Photography Safety Mission and Assurance Responsibilities Customer Schedule Service Launch ServiceLaunch Elements Systems Separation Supported for CubesatsGeneral Rules of Thumb Electrical Access Electrical Interfaces Mechanical Interfaces Accommodations Payload Accuracy Insertion Orbit Profile Mission Payload Delivery Capability 51 50 50 49 47 47 47 43 42 40 40 39 38 38 37 36 35 34 34 33 33 31 31 31 30 28 26 23 23 23 22 22 21 19 18 17 16 15 14 13 11 10 8 7 6 4 4 THE VIRGIN ORBIT EXPERIENCE 4 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 1.2 1.1 1 launch service. launch of our investment in the team, technologies, and facilities required to build acustomer-focused affordable as the spacecraft themselves. Virgin Orbit’s , LauncherOne, is the resultThe rapidly growing small satellite industry requires alaunch service that is as agile, flexible, and intends to serve as the flexible European . for small satellites from Cornwall. With operations based in the UK, VO-UK Virgin Orbit UK Limited (VO-UK) is the new UK branch of Virgin Orbit LLC. VO-UK aims to enable demonstrations. separate launches to deliver dozens of small satellites to LEO for experiments and technology 2020, VOX Space secured the U.S. Space ’s STP-S28 launch contract, amission for three community with responsive, dedicated, and affordable launch services for small satellites.incorporated In entity headquartered in Manhattan Beach, CA, that provides the national security Virgin Orbit has two subsidiaries of as part its corporate structure. VOX Space, LLC, is aU.S.- 600 dedicated employees led by President and CEO Dan Hart. companies and (TSC). Virgin Orbit is comprised of nearly the ’s Galactic Ventures family of innovative space companies, along withthe our disruptive sister customer-focused DNA that the Virgin Group is known for. Virgin Orbit isEstablished of part in 2017, Virgin Orbit’s exclusive is serving the small satellite launch market with United Kingdom and Oita Spaceport in Japan. worldwide, such as Launch and Landing Facility in , Cornwall Spaceport in the inclination missions. Furthermore, LauncherOne is capable of operating from avariety of Virgin Orbit can also conduct LauncherOne missions from to support low- and mid- In addition to launching from the Mojave Air &Space Port to support high-inclination missions, production of the LauncherOne vehicle. and the close proximity of engineering, manufacturing, and operations functions enable high-rate facilities in nearby Mojave, . Avertically integrated approach, well-capitalizedprocessing factory, activities in Long Beach, California, and propulsion, test and launch operations Virgin Orbit is aUnited States company with its corporate headquarters, factory, and payload space industry. accessibility and is proud to bring the Virgin standard of unparalleled customer service to the has invested in the team, technologies, and facilities required to usher in anew era of launch the agility, flexibility, and affordability necessary to transform the space landscape.LauncherOne Virgin is the launchOrbit service that will accelerate the small satellite revolution by offering schedule of choice. Utilizing an air-launch approach from a747-400 carrier aircraft, Virginworld’s Orbit’s premier small satellite launch service providing dedicated launches to the orbit and dedicated rides to orbit for small satellites starting in 2020. Virgin Orbit is strivingVirgin to the be Orbit is developing the LauncherOne small launch platform, which will provide affordable, CORPORATE OVERVIEW CORPORATE ORBIT VIRGIN ABOUT EXPERIENCE ORBIT VIRGIN THE 5 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE (current President&CEO) From lefttoright:GeorgeWhitesides(formerCEO), SirRichardBranson,DanHart A teamphotooftheVirginOrbitstaffinOctober2018 THE VIRGIN ORBIT FAMILY ORBIT VIRGIN THE 1 FIGURE

6 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 1.3 ground launch locations. launch ground from fixed maneuvers dogleg drop eliminating points, optimal costly from most the launches enables aircraft acarrier Having suited customer’s to needs. individual operations each mission tailored offer can missions LauncherOne beginning fromBy this asset, mobile and well-characterized performance. chain supply with is design aglobal aproven Girl Cosmic excellence, of operational decades With pad. launch flying 747-400 afully-reusable as Our serves Girl, Cosmic aircraft, carrier architecture. The key tenets of our launch services are as follows: combining areliable and proven 747-400 carrier aircraft with asimple, low-cost Virgin Orbit’s LauncherOne system is the most flexible small launch system on the market, TAILORED MISSION OPERATIONS MISSION TAILORED THE EXTRAORDINARY POWERS OF AIR LAUNCH OF AIR POWERS EXTRAORDINARY THE reach their end of life or run into anomalies. orbit spares knowing that LauncherOne can fill gapsin when satellites constellations are planned; constellation operators can plan fewer on- widespread fallout. In addition, responsive launch will change the way constellations or individual satellites in the event of an anomaly or (primarily as adeterrent) and enable quick reconstitution of smallsat with providing resilient space capability for national security purposes shorter than with conventional ground launch solutions. This will help call-up service where asatellite is placed into orbit on timeframes much launch brings to the table. Responsiveness specifically refers to a quick Responsive launch is the culmination of the four flexible capabilities air access to launch will help spur new space economies around the world. framework and approvals are in place. Mobile launch and regional launches where aspaceport license is granted and the regulatory This includes regional access through spaceport hubs or in-country Virgin Orbit, for the first time in history, can bring a“launch you.”to world. Mobile launch is atrue game changer for the launch industry as a few days. They can transported be to any spaceport around the These trailers are fully mobile and can positioned be and readied within We utilize six main mobile trailers to support our launch campaigns. filling in coveragegaps. and populating constellations to enable rapid operational capability or a matter of days. This enables aresponsive capability for critical assets timeframe. As aresult, we are capable of getting prepared for launch in trailerized equipment can ready to be support launches in ashort Our aircraft-like operations, small launch support footprint, and flexibility for our customers. on schedule requirements. This white-tail approach provides ultimate operations, it is possible to move up or back in the manifest depending launch services. In addition, due to our small footprint and aircraft-like regular development of launch vehicles to provide on-time delivery of We are building continuously, not just mission. per This ensures . inclination in Mojave for high-inclination orbits and Guam for low- and mid- and runway access around the globe. This includes our main spaceport Any Low Orbit and inclination is obtainable via our spaceports RESPONSIVE LAUNCH RESPONSIVE SYSTEM LAUNCH MOBILE HIGH CADENCE SCHEDULE YOUR ON ORBIT ANY 7 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 1.4 aircraft, , as depicted in ground, LauncherOne is carried to an altitude of approximately 35,000 feet by the 747-400 carrier 500 kg/1,100 lbm into awide range of Low Earth Orbits (LEO). Rather than launching from the LauncherOne is asimple, expendable launch vehicle designed to place small satellites of up to LauncherOne is Your Ride to Space LAUNCHERONE SYSTEM EXPANDED VIEW EXPANDED SYSTEM LAUNCHERONE 2 FIGURE GET TO KNOW OUR SYSTEM KNOW TO GET LOX/RP-1 Pump-Fed Engine 73,500 lbf /327 kNvacuum thrust 3 min run time • • • • • • • • • • • • • • • NEWTONTHREE FIRST STAGE LAUNCHERONE COSMICGIRL of the launch vehicle enginestage burn to ensure safe operation provides thrust termination during the first An Autonomous Safety System (AFSS) Composite Structure 72 in. /1.8m Outer Diameter ignition of NewtonThree time5 sec release between of LauncherOne and has cleared the at point of release 75% —the amount of atmosphere LauncherOne 99+% is manufactured in the USA LauncherOne’s  17,500 mph is the typical maximum of LauncherOne’s  8,000 mph is the typical maximum of speed LauncherOne rocket, including the satellites 57,000 lbm is the typical takeoff weight of a 70 in ft length moment LauncherOne is released flightconditions of Cosmic Girlat the 35,000 mach 0.67, ft,  ground the leaves that everything 550,000 lbm is the typical of wingspan 211 ft 225 in ft length 747-400 aircraft

(N3) second stage first stage 27˚ FPA are the typical FIGURE 2 ADAPTER INTERSTAGE . • • • • • de-orbit. used forbe disposal orbit modification controlledor burns to optimize performance. Athird burn also may For many orbits, the second performs stage two second engine stage burn. two clamshell halves, which separate early in the optimized profile. The fairingconsists of volumepayload with capped an aerodynamically adapter and aclamshell fairing with acylindrical The module payload consists of aconical payload NEWTONFOUR (N4) SECOND STAGE 5,000 lbf of thrust orbit desired circularization of the 2 burns to allow Completed in 6 min run time Composite Structure 59 in. /1.5m Outer Diameter • • PAYLOAD 500-1000 km Typical altitude: 500 kg Maximum mass: payload 8 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 1.5 Key components of Virgin Orbit’s LauncherOne service are summarized in Guide, and may customized be as needed to suit each customer’s mission-specific requirements. capabilities listed here are discussed in greater detail in the following sections of this Service LAUNCH SERVICES QUICK SERVICES REFERENCE LAUNCH 1 TABLE CAPABILITIES AT AGLANCE CAPABILITIES Regulatory Approach Payload Integration Payload Processing Launch Schedule Inclinations Launch Altitudes/ PayloadDynamic Volume Payload Capability SERVICE

• • • • • • • • • • • • • • • • • CAPABILITY SUMMARY Compliance with international orbital debrisdisposalguidelines regulation 14CFR431,Launch andReentry of aReusable Launch Vehicle (RLV). Virgin Orbit’s LauncherOne launchislicensedundertheFederal Aviation Administration brokers oraggregators Secondary manifested andmanageddirectly by Virgin Orbit orviapayload Support for commercially available separation systems andCubeSat dispensers Compatible with ESPA andESPA Grande class configurations various diameters andboltpatterns available Payload Attach Fitting with baselineinterface diameter of 609.6 mm/24.0 inches; other Encapsulation of payload at thecustomer site Storage of loadedcubesat Receipt of loadedindispenser Additional Payload options include: room inLong Beach,CA Virgin Orbit’s customer payload processing facility with ISO Level 8(100kclass) clean Flexible launchwindows to accommodate schedulechanges/variation Emphasis onreducing time-to-launch; to accomodate <12month launchtimeline Flexibility to conduct launchesfrom any licensedspaceportfacility overflight constraints Capable of accessingany ; subject to any launchsite-specific population 3543 mm/139.5 inchoverall envelope length 2123 mm/83.6 inchconstant cylindrical length 1262 mm/49.7 inchconstant cylindrical diameter (LEO) Up to 500kg /1,100 lbmto 230km/124 nmicircular 0degree inclination Up to 300kg /661lbmto 500km/270 nmiSun- (SSO) TABLE 1 . The The .

DESIGN YOUR MISSION 10 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.1 2 to customize your mission. LauncherOne’s air-launch architecture enables unparalleled flexibility. This section will helpyou information separation on systems. small satellite separation systems and CubeSat dispensers. Please refer to Section 2.8for more along with the payload in accounting for total mass. LauncherOne is compatible with avariety of interface. Thus, the mass of any required separation system or dispenser must included be The performance curves in a circularization burn is not required. performance curves. The increased performance below 230 km is for direct-inject orbits where portion of total . This is represented as the dip in the performance at 600 km in the necessitates adisposal burn for orbital altitudes above 600 km, consequently consuming a than 25 for an upper stage left above approximately 600 km. Meeting this requirement LauncherOne is designed to meet regulations that require amaximum orbit lifetime of less capabilities, please contact Virgin Orbit. calculated for each customer based on their specific requirements. For more detailed payload in Performance curves for LauncherOne payload delivery to several reference orbits are provided FIGURE 3 FIGURE ORBITAL PAYLOAD DELIVERY PERFORMANCE CURVES PAYLOAD DELIVERY CAPABILITY MISSION YOUR DESIGN FIGURE 3

PAYLOAD MASS (KG) 400 600 500 300 200 450 550 350 250 100 150

200 . Due to LauncherOne’s high degree of customization, payload capabilities are best (Single 2Burn) Stage Injection Direct (Two 2Burns) Stage Injection Initial 400 FIGURE 3 provide the total spacecraft mass above the payload 600 CIRCULAR ORBITALCIRCULAR ALTITUDE[KM] Orbit-Lowering Maneuver 800 1,000 1,2001,400 Low IncSite: 0deg Low IncSite: 12deg High IncSite: 45deg High IncSite: 70 deg High IncSite: 80deg High IncSite: 90deg High IncSite: SSO 11 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.2 the orbit and ensure that the second stage lifetime is less than 25 years. payload separation. For missions above 625 km, the second stage performs athird burn to lower the final burn. Final verification of correct then occurs within 90 minutes of final deliver the payload into its target orbit. Payload separation is mission specific and willoccur after rate of 0.1 RPM. Once at target apogee, acircularization burn is performed to accurately During acoast of approximately half an orbit, passive thermal control is performed with anominal are not direct-inject), shedding the payload fairing along the way early during second stage burn. then ignited following ashort coast and carries the payload to alow parking orbit (for missions that Main Engine Cutoff (MECO) occurs at approximately 3minutes after drop. The second stage is vehicle ignition occurs and the vehicle ascends several hundred thousand feet before first stage LauncherOne after Cosmic Girl has entered into aclimb maneuver. Approximately 5seconds later, over an unpopulated flight corridor above oceanthe to an altitude of 35,000 feet, and releases Girl takes off from the launch site with the fueled LauncherOne and payload. The plane flies out For most LauncherOne missions, the mission profile is as follows. The carrier aircraft Cosmic MISSION PROFILE MISSION 5 FIGURE MISSION PROFILE PROFILE MISSION

HEIGHT ABOVE EARTH (KFT) 2,000 1,500 400 600 500 300 200 100

0 Rocket Ignition Start (MES) Main Engine 100 Cutoff (MECO) Main Engine Stage SeparationStage Second Engine Start 1(SES-1) 200 Fairing Separation TIME SINCEROCKETRELEASE(SECONDS) 300 400


Cutoff (SECO-1) Cutoff Second Engine Engine Second 600 3,000 Payload SeparationPayload Start 2(SES-2) Second Engine Cutoff 2(SECO-2) Second Engine 4,000 12 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE Payload separation LauncherOne ignition Cosmic GirlatLauncherOnerelease Payload deployment Second EngineStart 13 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.3 3-Axis Eccentricity Right Ascension of Ascending Node(RAAN) Inclination Altitude ALTITUDE TYPE ORBITAL PARAMETER TYPICAL ORBITAL INJECTION ACCURACY (3 SIGMA) ACCURACY INJECTION ORBITAL TYPICAL 2 TABLE TYPICAL PRE-SEPARATION ATTITUDE AND SPIN-RATE ACCURACIES (3 SIGMA) ACCURACIES SPIN-RATE AND ATTITUDE PRE-SEPARATION TYPICAL 3 TABLE LauncherOne are provided in mass, orbit altitude, and other mission-specific factors. Typical errors in injectionaccuracy inclinations for can also accommodated. be Orbit injection accuracy is dependent on payload of multiple payloads into orbits of different altitudes, eccentricities and slightlyimproved differentiated orbital insertion control compared to solid propellant upper stages. Deployment deployed. LauncherOne employs aliquid propulsion system for its final stage, which allows for Virgin Orbit takes our commitments seriously and that includes ensuring your payload is accurately the desired attitude. Typical accuracies for pointing and angular are shown in Prior to payload separation, the LauncherOne second stage can orient itself and the payload to specified mission parameters. standard mission analysis includes refinement of theseaccuracy predictions based on customer- Missions with multiple payload deployments may select different separation attitudes. ORBIT INSERTION ACCURACY ACCURACY INSERTION ORBIT

Yaw Pitch Roll PARAMETER TABLE 2 for a500-km circular -synchronous orbit. Virgin Orbit’s 0.0022 ± 0.2° ± 0.15° ± 15km ACCURACY ± 6.0° ± 6.0° ± ± 7.0° ANGULAR ERROR ± 0.5°/sec ± 0.5°/sec ± 2.0°/sec RATE ERROR TABLE 3 . 14 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.4 more information on the mechanical interface to LauncherOne, see section 2.5. evaluate your needs and discuss possible payload accommodations for unique requirements. Forseparation system. Virgin Orbit can perform mission-specific payload dynamic envelope analysis to envelope is the net volume available for the payload after accounting for the axial height of apayload a 3.63 m/139.5 in overall payload dynamic envelope length. The LauncherOne payload dynamic consists of a1.22 m/49.7 in diameter cylindrical section that is 2.12 m/83.6 in long resulting in shown in managed directly by Virgin Orbit, or via payload aggregators. Sample Payload Configurations are accommodate asingle ESPA Grande class payload. Secondary payloads can manifested be and ESPA class payloads is also possible as acustom configuration. TheLauncherOne fairing can also fitting interface with the primary payload mounted on top. Side-by-sideaccommodation of two payloads, typically asecondary payload adapter is attached to the standard payload attach to best meet customer requirements. For multi-satellite missions with primary and secondary has the ability to multi-manifest satellites, employing the large fairing volumeLauncherOne in avariety offers of ways one of the largest payload envelopes in the industry for its class. LauncherOne LauncherOne are illustrated in The available payload fairing dynamic envelope and launch vehicle to spacecraft interface for (3) Customadapterforyourspacecraftavailableuponrequests (2) Multiplefutureoptions–currentlyinwork (1) Readytolaunch(2or3standards) *Custom adapteravailableuponrequest. LAUNCHERONE SAMPLE PAYLOAD CONFIGURATIONS PAYLOAD SAMPLE LAUNCHERONE 6 FIGURE PAYLOAD ACCOMMODATIONS PAYLOAD

3543.3mm Envelope DynamicPayload FIGURE 6 2123.4mm

. 1262.4mm 441.96mm FIGURE 7 Payload Primary Single and and FIGURE 8 Payloads CubeSat Multiple and Primary Small , respectively. The dynamic envelope Release) (Axial Payloads Primary Similar Multiple, Release) (Lateral Payloads Primary Similar Multiple, Payloads Test 15 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.5 inch interface. Custom are PLAs available upon request. standard-sized Payload Adapters reducing (PLA), the payload interface from 24 inches to an 8or 13 dimensions of the standard interface are provided in compatible with the ESPA and ESPA Grande class configurations, are available upon request. The with 36 x¼”-28 bolts evenly spaced out. Mission-specific interfacebolt patterns, including those the payload stack. The baseline PAF interface is astandard 609.6 mm /24.00 inch bolt pattern a composite conical section, providing the mechanical interface between the launch vehicle and LauncherOne’s standard Payload Attach Fitting (PAF) consists of metallic forward and aft rings with section 2.7. spacecraft missions. For more information on the electrical interface to LauncherOne, see separation system. The payload controller is capable of providing multiple signals enablingpayload multi- controller provides aprimary and redundant separation signal directly to the payload For the standard launch vehicle-to-payload electrical interface scheme, the LauncherOne PAYLOAD FAIRING DYNAMIC ENVELOPE 7 FIGURE MECHANICAL INTERFACE

3543.3 mm 139.5 in 2123.4 mm 83.6 in FIGURE 8 . Additionally, Virgin Orbit offers two Ø Ø Fairing Fairing Dynamic Envelope 609.6 mm|24 in Fitting Attach Payload SeparationPayload System ReservedSpace for 63.5 mm|2.5 in 1262.4 mm 441.96 mm 111.76 mm 4.4 in 17.4 in 49.7 in 16 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.6 connection to the payload during storage and vehicle-level integration. Support Equipment (EGSE). This extra harness can used be to supply power and provide adata umbilical connector to provide aconnection from the spacecraft to customer Electrical Ground At the customer’s request, the Payload Attach Fitting (PAF) wire harness can include aspacecraft Modification foradditional Bridgewire or Motorized separation commands are available. • • • • • by astandard configuration of: The standard interface from the launch vehicle to the payload, including separation, is supported LAUNCH VEHICLE TO SPACECRAFT INTERFACE SPACECRAFT TO VEHICLE LAUNCH 8 FIGURE ELECTRICAL INTERFACES » » signals. band light motorized Twenty-four (24) Separation Commands that can tailored be to support bridgewire or One (1) RS-422 Communication line for payload use. One (1) Ethernet Communication line for payload use. Ten (10) breakwires from the payload to the launch vehicle for separation indication. Ten (10) breakwires from the launch vehicle to the payload for separation indication.

Four (4) Motorized Type Separation Commands. Twenty (20) Bridgewire Type Separation Commands.

Equally Spaced Equally 36 X¼-28 UNF Ø PAYLOAD INTERFACE 24.000 [609.60] -in [mm] 17 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.7 Electrical Bonding Voltage 19 of DO-160G should solicit guidance from Virgin Orbit. then the equipment must comply with Section 19 of DO-160G. Users who are unfamiliar with Section The Payload Electrical Interface is shown in payload communications is over 8twisted shielded pairs (TSP) of wires through the Cosmic Girl. When the satellite is mated to the rocket and the rocket is mated to the Cosmic Girl, EGSE to electrical access in the various phases of payload operations. between the satellite and the customer EGSE. The table below and section 4.6describe the The payload integration and launch operations process is designed to maximize electrical access Information about these payload accommodations are defined in DESCRIPTION ELECTRICAL ACCESS 5 TABLE PAYLOAD ELECTRICAL ACCOMMODATIONS 4 TABLE ELECTRICAL ACCESS ELECTRICAL Fairing Mated to theRocket, Rocket ismated to CosmicGirl Fairing Mated to theRocket, Rocket isontheRocket Trailer Encapsulated inthePayload Trailer Encapsulated intheCleanroom Mated to thePayload Attach Fitting CONFIGURATION

shall benegotiated by electromechanical ICDfor L/V-P/L interfaces. structures for typical L1 missiondesigns. Alternative electrical bondingrequirements bleed path to prevent on-orbit charging of thePayload Attach Fitting (PAF) andS/V The carbonfibercomposite layup hasbeen evaluated andprovides adequate charge- milliohms, combinedacross multiplemetal-to-metal andmetal-to-composite joints. The payload chassisiselectrically bondedto L/V structure with nomore than200 available uponrequest. ground operations andcaptive carry. Additional amperage capacity canbemade Harnessing capableof supporting28 Vdc power +/4 Vdc upto 3A isprovided during PROVISION FIGURE 9 Cosmic Girl None Test Connector Test Connector Test Connector INTERFACE CONNECTION . If the customer’s EGSE will fly on Cosmic Girl TABLE 4 . D3899/26FC35SN N/A D3899/26FC35PA D3899/26FC35PA D3899/26FC35PA LV CONNECTOR 18 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.8 contact with the deployed payload. Maneuver (C/CAM), if necessary, in order to minimize contamination and limit the potentialevent, the for second stage re- of LauncherOne will perform aCollision/Contamination Avoidance sequence allows for adequate separation between all deployed payloads. Following the separation mission requirements. For multi-payload missions, LauncherOne ensures that the deploymentnecessary to ensure safe separation from the launch vehicle and that it meets the customer Virgin Orbit will conduct an analysis of tip off rates and other payload separation dynamics as integration work. specification. Virgin Orbit can procure the separation system for the customer performand the separation system. CubeSat payloads typically use dispensers designed to the CubeSat design Primary spacecraft typically interface with the LauncherOne PAF via an annular or discrete point in selecting an appropriate separation mechanism or dispenser for their mission uniquein needs. order to offer maximum mission flexibility to our customers. Virgin Orbit can assistLauncherOne customers is compatible with many spacecraft separation systems and CubeSat dispensers PAYLOAD ELECTRICAL INTERFACE DIAGRAM 9 FIGURE SUPPORTED SEPARATION SYSTEMS SUPPORTED LEGEND COSMIC GIRL Quick Disconnect Harness Connector Mission Harness Specific 747 Harness (provided by Virgin Orbit) Confirmation Harness (by Virgin Orbit) Separation Harness (by Virgin Orbit)

Customer Separation Plane EGSE

Payload SeparationPayload Commands CONF CMDS

Sep System SEIP Payload ElectricalPayload Interface Controller Payload Separation System Second Stage Payload First Stage PAF Computer Flight

Mission Specific Payload SEIP Payload 8 TSP to 747 19 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 2.9 • • • Virgin Orbit requires the following items: • • • The following are best practices for to follow: MECHANICAL COMPATIBILITY MECHANICAL mass constraints of the dispenser or separation system. Spacecraft providers are responsible for ensuring that their spacecraft do not exceed the the spacecraft to either the dispenser or separation system. A fit check is required prior to payload integration to ensure mechanical andelectrical fit of integration. the spacecraft arrives late or does not fit within the allowable envelope during payload Spacecraft providers are responsible for supplying amass simulator in the event that that some dispensers allow for greater protrusions. specified in the CDS to ensure compatibilityacross multiple dispensers, despite the fact Railed CubeSat providers are strongly encouraged to conform to the allowable protrusions specified in the CDS. Railed CubeSat providers are strongly encouraged to conform to the volume envelope planetarysystemscorp.com/product/canisterized-satellite-dispenser/). to Planetary Science Corporation's (PSC) Payload for Spec 3U6U12U (https://www. encouraged to follow the CDS where appropriate while also ensuring conformance Obispo CubeSat Design Specification (CDS). Tabbed CubeSat providers are also strongly Railed CubeSat providers are strongly encouraged to design to the Cal Poly San Luis THE VIRGIN ORBIT LAUNCH SERVICE PROCESS 21 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 3.1 3 A.2 and A.3. A.3. and A.2 found in Appendixes the be can deliverables customer information and Virgin Orbit on detailed More in following the sections. described are considerations safety and documentation, schedule, manner. reliable in Typical asafe, and mission the expeditious, is and conducted exceeded or met are requirements customer ensure activitiesMissionthat analysis. integration flight post to and orbit, of spacecraft the integration, delivery vehicle payload-to-launch processing, for spacecraft accommodation mission planning, includes offering service Virgin launch Orbit’s • • • • • • • Optional Services: • • • • • • • • are asfollows:Standard Services experience and/or accommodate your unique needs. brand. To better serve our customers, we offer optional services to further enhance your launch All launches are given the high level of service and attention to detail that distinguishes the Virgin LAUNCH SERVICE ELEMENTS SERVICE LAUNCH PROCESS SERVICE LAUNCH VIRGIN THE Orbit corporate partners. corporate Orbit Insurance: LocalizedSecurity: and tailorable security is available, if desired. storage and handling is available for spacecraft propellant. Propellant Loading Planning: Assistance with logistics, processes, and procedures for on-site systems. craft engineering is available from who experts have formerly worked on the relevant space- Peer Review: reviewSpacecraft for , test, integration, and systems customers unfamiliar with spacecraft regulatory compliance. Licensing: AssistanceSpacecraft with various standard licensing processes is available for of your payload and the launch environment. Thermal Analysis: Ensure thermal compatibility with sensitive areas delivery, and processing of the separation system to ensure readiness for integration. System: Separation Payload Focus on your payload and let us handle the acquisition, State Department. Virgin Orbit will obtain and manage aTechnical Assistance Agreement (TAA) from the U.S. Compliance: InExport the case of anon-U.S. Customer and/or Spacecraft Manufacturer, containing details of launch , events, and environments. Post-Launch Evaluation Afull Report: will report delivered be within 60days after launch, hours after separation. of post-launch status from the launch vehicle data will occur no later than 3 Post-Launch Status Quick-Look: The spacecraft state vector and aquick-look assessment Analysis:Separation Verifiesaccurate and low risk payload deployment. environment. Analysis: Loads Coupled Confirms thatyour spacecraft is compatible with the launch and PerformanceTrajectory Analysis: Ensures your payload is delivered to your mission orbit. are documented and the launch service complies with your spacecraft needs. Virgin Document Control Orbit Interface (ICD): Ensures all of your mission requirements Agreement. You are assigned aMission Manager immediately after signing of the Launch Service Virgin Orbit Mission Manager: Your concierge for asmooth mission execution and launch. Various pre-launch and launch insurance options are available through Virgin

22 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 3.3 3.2 complete list and description of milestones and deliverables. vehicle, payload, and facilities to provide asafe and successful launch. the See appendices for a launch vehicle. Multiple reviews are held to coordinate the mission analysis and readinessand of the the customer to communicate requirements and ensure compatibility of the payload and the of the post-mission An report. Interface Control Document is jointly developed by Virgin Orbit with signing aLaunch Service Agreement (LSA),culminates in launch, and ends with the delivery customer varies according to the mission-specific requirements. Contractual launch servicebegins A top-level mission timeline is provided in Please contact Virgin Orbit for additional information. secondary rideshare payloads can launch in as little as 6months or less from contract execution. primary payload, payloads can launch in as little as 9months from contract execution. Small to launch your payload as quickly and reliably as possible. For astandard engagement of a time-to-launch. As such, Virgin Orbit has instituted the processes and supporting infrastructure Virgin Orbit’s dedication to streamlining launch for small satellites includes emphasis on reducing • • • • • • • documentation requirements are as follows: ensuring smooth launch operations, and is used to satisfy FAA reporting requirements. Typicalplans. This information facilitates coordination between the customer and Virgin Orbitcommunicate the payload system description, mission requirements, safety data, and processingAs the spacecraft owner, the customer is responsible for providing documents to formally MISSION TIMELINE MISSION FIGURE 10 FIGURE CUSTOMER RESPONSIBILITIES SCHEDULE SERVICE LAUNCH +0 Days StartContract LSA DATE OF EFFECTIVE identification of hazardous operations during payload processing. Documentation: IdentificationSafety of hazardous materials and quantity each;of and Processing Facilities.Payload ProcessingPayload Plan: Plan for payload processing and intended use of Virgin Orbit Finite Element Model: Model to enable payload-to-launch vehicle Coupled Loads Analysis. requirement was verified (e.g. inspection, analysis, test, demonstration). ICD VerificationDocumentation: Verification evidence indicating howeach customer ICD data for Virgin Orbit to evaluate launch vehicle integration and flight dynamics. and CAD model: mass Mass, properties Spacecraft CG, and moments &products of inertia the overall mission. operations needs, unique requirements, and other design considerations that encompass parameters, mechanical and electrical interface definition, RF characteristics, ground Inputs to the Launch Vehicle-to-Spacecraft ICD: Spacecraft configuration, mission orbital mission. Responses to Questionnaire: Payload Initial basic information about the payload and

+1 StartContract MEETING KICKOFF MISSION -9 Launch ICD INITIAL -8 Months Launch REVIEW ANALYSIS MISSION FIGURE 10 -6 Months Launch ICD SIGNED . The relative timing of milestones for each -45 Days Launch REVIEW READINESS MISSION -30 Days Launch AT PPF ARRIVAL SATELLITE -0 Days Launch LAUNCH 23 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 3.6 3.5 3.4 to the FAA and providing information to the U.S. Government for . provide assistance with regulatory needs, such as facilitating the submission of payload informationAdministration) prior to commencement of any launch integration activities. Virgin OrbitCommission, can International Telecommunications Union, National Oceanic and Atmosphericnational authority and any other necessary regulatory (e.g. body Federal Communications The customer is ultimately responsible for obtaining licenses, permits, and approval from their of the foregoing laws. Administration Foreign Act, Corrupt Practices and/or Act any regulation promulgated under any ITAR, Office of Foreign Assets Control regulations, anti-boycott laws under the U.S. Export or approvals, including without limitation the Commercial “CSLA”, Act EAR, Orders, rules and regulations, and conditions of all government licenses, permitsEach must party comply with all applicable United States federal, state and local laws, Executive 774), administered by the U.S. Department of Commerce. by the U.S. Department of State, and the Administration Export Regulations (15 (EAR), CFR §§730- including the International Traffic Arms Regulations (ITAR), (22 CFR Parts 120-130),administered Virgin Orbit’s technology, hardware and launch services are subject to U.S. control export laws, policy as regulation permits –after all, "parent and baby" selfies are important, too! teammates on site with us, we’ll ensure we’ve got as streamlined and permissive aphotography as your precious cargo moves through the integration and launch process. And when you have you to capture beautiful and useful photos step at every along the way, keeping you informed your hardware arrives in our facilities until the moment we deploy it into orbit, we willAnd work we know that with like parent, every you can never have enough baby photos! From the time Whether it’s your first mission youror five hundredth, we know that your satellite is your baby. prior written approval of Virgin Orbit. notifications, or announcements related to the mishap and investigation without the review and other applicable regulatory agencies. The payload provider may not make any public statements, The investigation will monitored be by both FAA and National Transportation Safety Board and and state agencies, the Payload provider will furnish data generated by or related to the Payload. launch anomalies, or other mishaps. If reasonably requested by Virgin Orbit, insurers, or federalThe Payload provider will cooperate with Virgin Orbit in the investigation of launch accidents, assessed during all readiness review meetings. payload documentation for compliance with applicable safety standards, and safety status is contains all questions needed for an FAA Launch License submittal. Virgin Orbit will review the The entry point for communication of payload safety data is the payload questionnaire and it requirements. these processes and requirements. Virgin Orbit can provide guidance regarding specific safety mitigated. Customer payloads and payload operations are responsible for compliance with risks and resulting hazards are methodically identified, and eithereliminated or appropriatelyBoth aSafety Policy and formal Safety and Mission Assurance Process are in place to ensure and Health Administration (OSHA), and other applicable regulatory agencies. exceed the requirements of the Federal Aviation Administration (FAA), the Occupational Safety aspects of payload processing, vehicle integration, and launch operations. Virgin Orbit strives to Virgin Orbit has established measures to ensure safety of personnel and throughout property all U.S. IMPORT AND EXPORT COMPLIANCE EXPORT AND IMPORT U.S. PHOTOGRAPHY POLICY ASSURANCE MISSION AND SAFETY 24 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE the U.S. State Department. manufacturers, Virgin Orbit will obtain and manage aTechnical Assistance Agreement (TAA) fromIn support of its provision of launch services for non-U.S. customers and/or Spacecraft from U.S. Customs and Border Protection. to space, including, if applicable, clearance of the payload and customer-furnished hardware country of origin to Virgin Orbit’s Payload Processing Facility or any other Launch Facilitythe Spacecraft and and in any other items furnished by the manufacturer of the Spacecraft from their Spacecraft has obtained and maintained, all licenses, permits or approvals necessary to transfer Furthermore, the customer will obtain and maintain, or ensure that the manufacturer of the PAYLOAD PROCESSING AND LAUNCH OPERATIONS 26 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 4.1 4 procedures to the customer’s specific mission requirements. described in this section. Virgin Orbit is able to tailor standard payload processing and launch ensure safety of the payload, and increase mission reliability. Atypical processing flow Payloadis integration and launch operations procedures are designed to minimize complexity, 07. 06. 05. 04. 03. 02. 01. other contiguous United States (CONUS) locations are depicted procedural steps for payload processing for launches from Mojave Air and or Spaceport from any at customer facilities and storage in aflight-ready state for rapid “on-demand” launch. Typical timeline can reduced be upon request. Additionally, options exist for encapsulation of the payloadas possible. Delivery of the payload is nominally planned for 30 days prior to launch, but this our customers by simplifying the integration process and offering as many essential resourcesVirgin Orbit aims to make payload processing operations as smooth and efficient possibleas for Long Beach to the spaceport will vary): (for other spaceports, the payload processing facility remains the same but transportation from FIGURE 11 11 FIGURE PAYLOAD PROCESSING FLOW PAYLOAD PROCESSING FLOW PROCESSING PAYLOAD OPERATIONS LAUNCH AND PROCESSING PAYLOAD

to the PPF Delivery Spacecraft CUSTOMER PAF Processing Fairingand VIRGIN ORBIT late access to the payload for mission-critical needs. While Access: Payload Late not of part the nominal launch process, it is possible to allow payload assembly to the launch vehicle. Integration with the Launch Vehicle: Virgin Orbit horizontally encapsulated the mates positive pressure environment during transport. to the spaceport. The trailer is equipped with an ISO 8cleanroom with aclimate-controlled The encapsulatedTransport to the Spaceport: payload is transported in the Payload Trailer for transportation to the launch site. the payload fairing. This encapsulated assembly is then rotated into ahorizontal configuration spacecraft and separation system on the payload attach fitting is then encapsulated within Fairing California): (Long Beach, Encapsulation orientation) integrated The (vertical system and/or payload attach fitting. Mate: AjointSpacecraft operation to mate the customer spacecraft to the separation Virgin Orbit-supplied man lifts and other equipment in the PPF. preparations such as panel cleaning and removal of covers, supported as necessary by customer completes independent verification of the spacecraft and makes final flight Standalone ProcessingSpacecraft and Final Preparation California): (Long Beach, The areas, and provides unpacking/packing support as needed. crated hardware and associated ground checkout equipment into the designated work California): (Long Beach, to the PPF Delivery VirginSpacecraft Orbit places the customer-

and Encapsulation and Fairing for Mate Setup PAF and and Final Preparation Processing Spacecraft Mate Spacecraft TOGETHER Encapsulation Fairing

FIGURE 11 Spaceport to the Transport and described as follows Launch Vehicle with the Integration Access Payload Late 27 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 7 -LatePayload Access 5 -TransporttotheSpaceport 3 -SpacecraftMate 2 - PPF, the to Spacecraft Processing and Final Delivery Preparations Spacecraft - 1 6 -IntegrationwiththeLaunchVehicle 4 -FairingEncapsulation 28 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 4.2 • • • • • • • • • • • • the Nebula Lounge Office all under one roof. Baseline services andequipment available include: Processing Facility located in Long Beach, California. The facility includes the Nebula cleanroom and Customers can test and process their satellite at Virgin Orbit’s state of the Nebula art Payload PAYLOAD PROCESSING FACILITIES external, Virgin Orbit-procured processing facility. fueling requirements upon request. Fueling of hazardous will occur at an promote the most efficient integration process, but Virgin Orbit is able addressto customer cold , /krypton, and various “green” propellants. Fully-fueled payload delivery will Accommodation for “green” propellant storage and loading. Possible propellants include access IDs, 24-hour facility security guard, and closed circuit television. Security is tailored for customer needs. Available security measures include electronic hours aday, and optional 24/7 support Virgin Orbit integration support personnel available up to six (6) days aweek for twelve (12) machine. Lounge style offices and conference rooms are provided with Wi-Fi, printer, copier, and fax and gloves. Consumables including compressed air, helium, , isopropyl alcohol, lint-free wipes, tools Uninterrupted Power Supplies (UPS), forklift, scissor lifts, rolling ladders, and small handheld 230V AC, 50 Hz Power provided for customer electrical ground support equipment at 100V AC, 60Hz and The cleanroom is equipped with amulti-speed 2Tcrane, with two hooks on one bridge. Temperature: 63-77°For 17-25°C Relative Humidity: 40-60% Certified ISO 8cleanliness level (Class 100K) The cleanroom environment will be: lock air Removable Main ISO 8cleanroom area room Gowning The cleanroom consists of: Urban location provides simplified logistics forpersonnel and resource planning. direct . Close proximity airport, to LAX amajor hub serving worldwide destinations, many with


50 ft Path Crane Path Crane 30 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 4.3 capabilities of the Payload Trailer include: conveniently transported to the launch site in the Payload Trailer. The baseline After encapsulation and final closeouts, the payload fairing module is safely and Payload integration • • • • • • PAYLOAD TRAILER 13 FIGURE PAYLOAD TRANSPORT PAYLOAD Cleanroom access IDs, 24-hour facility security guard, and closed circuit television. Security is tailored for customer needs. Available security measures include electronic Data Recorders tracking the actual environments. The trailer comes equipped with air ride suspension for asmoother ride and will have Event Transportation loads will not exceed flight loads. The Payload Trailer has apassthrough for cables from the EGSE room into the cleanroom. The trailer has aControl Room with storage capability for server and test racks. Temperature: 63-77°F Relative Humidity: 40-60% Certified ISO 8cleanliness level (Class 100K) The cleanroom environment will be:

Payload mate Gowning Room Gowning Control Room Entrance

31 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 4.6 4.5 4.4 coming online. ones new the and supported currently spaceports the about more 6.2 out to Section find See • • • While the payload is in the Payload Trailer: were designed to provide direct access as late as possible. Virgin Orbit understands how valuable late access to the satellite is for our customers. Operations 08. 07. 06. 05. 04. 03. 02. 01. relative to takeoff are as follows: encapsulated payload to the spaceport. Key events in the launch schedule and typical timing For standard launch operations, launch occurs within three days after the delivery of the MECHANICAL AND ELECTRICAL ACCESS FLOW OPERATIONS LAUNCH LOCATIONS LAUNCH

» » » Prior to take-off, while the payload is mated to the rocket on Cosmic Girl: detailed electrical interface information is available in Section 2.7. Electrical access through the Text Connectors on the base of the PAF is available. More Mechanical access is available through all four of the Fairing access doors LauncherOne release and launch (L-0day) by the carrier aircraft (L-0day) Cosmic Girl take-off; LauncherOne purge provided to payload encapsulated environment Cosmic Girl engine start and LauncherOne GSE disconnect (L-0day) Propellant loading (L-0day) Rollout and mate of LauncherOne with payload to carrier aircraft (L-2days) Launch Readiness Review (L-2days) Payload mate to LauncherOne (L-3days) LauncherOne vehicle integration and checkout (L-4days and earlier)

guidance. of DO-160G. Users unfamiliar with the specification should contact Virgin Orbit for Any customer EGSE that flies on Cosmic Girl is required to comply with Section 19 information is available in Section 2.7. Electrical access from Cosmic Girl is available. More detailed electrical interface Mechanical access is available through all four of the Fairing access doors PAYLOAD ENVIRONMENTS 33 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.2 5.1 5 standard service, and documented in the ICD. only. Mission-specific analysis payloadof expected environments performedis by Virgin Orbit as a following subsections. This payload environment data is provided for initial planningThe predicted purposes environmental conditions experienced by atypical payload are detailed in the throughout the flight profile, including ground segments, captive carry, and launch vehicle ascent. LauncherOne’s payload environments are competitive with other similar launch vehicles launcher separation plane. support apayload up to +/-50mm laterally and 0.6m axially from the payload to LauncherOne accommodates awide range of payload up to 500 kg/1,100 lbm and can vehicle and carrier aircraft. vector and the Y-axis is parallel to the ground, pointing out of the left side of the launch the Z-axis. When in ahorizontal, captive-carry configuration, the Z-axis is oriented inverse to the longitudinal centerline. Roll is defined about the X-axis, pitch is about the Y-axis, and yaw is about In this right-handed , the positive X-axis is aligned with the launch vehicle The standard LauncherOne launch vehicle coordinate reference frame is provided in LAUNCH VEHICLE COORDINATE SYSTEM COORDINATE VEHICLE LAUNCH 14 FIGURE PAYLOAD CONSTRAINTS COORDINATEVEHICLE SYSTEM ENVIRONMENTS PAYLOAD +X +X

+Y +Z +X +Z FIGURE 14 +Y . 34 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.4 5.3 MAXIMUM PREDICTED SHOCK ENVIRONMENT AT THE STANDARD PAYLOAD INTERFACE PAYLOAD AT STANDARD THE ENVIRONMENT SHOCK PREDICTED MAXIMUM 15 FIGURE Acceleration (g) NOTE: POSITIVE AXIAL ACCELERATION INDICATES COMPRESSIVE LOADS TYPE ultimate safety factors FAR per 25.303 should applied be (F.S. =1.5). acceleration for all phases of flight. As driving load cases are derived during aircraft operations, mission-specific Coupled Loads analysis. The values provided in the tablebound the maximum spacecraft with mass greater than 60kg. Predictions are further defined and verified by at the payload center of gravity. These are general quasi-static loads predictions for asingle In many cases, due to the addition of payload adapter structure, this value is lower. unique adapters, this shock value will recomputed be at the specific interface yourof spacecraft. interface from all launch vehicle events is shown below in The maximum predicted shock response spectrum at the standard payload-to-launch vehicle 10000 5000 700 100 FREQUENCY (HZ) LAUNCHERONE PRIMARY PAYLOAD DESIGN LOAD FACTORS LOAD DESIGN PAYLOAD PRIMARY LAUNCHERONE 6 TABLE TABLE 6 provides representative maximum predicted quasi-static limit loads for LauncherOne MAXIMUM PREDICTED SHOCK ENVIRONMENT AT THE STANDARD PAYLOAD INTERFACE PAYLOAD AT STANDARD THE ENVIRONMENT SHOCK PREDICTED MAXIMUM 7 TABLE SHOCK ENVIRONMENT QUASI-STATIC LOADS FROM ACCELERATION

SRS, Q = 10 (G-PEAK) SRS, Q = 10 -(GPeak)

10,000 10000 1000 1,000

100 100 10 10 100

100 -3g /+7g AXIAL (X)

FREQUENCY (HZ) 3000 3000 430 10 LAUNCHERONE MAX PREDICTED SHOCK ENVIRONMENT (G-PEAK) rqec [Hz] Frequency 1,000 1,000 TABLE 7 +/- 5g LATERAL (Y,Z)

and and FIGURE 15

10,000 . For mission 10,000 35 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.5 will recomputed be at the particular interface of your spacecraft. measured at the standard 24” diameter interface. For mission unique adapters, this environmentboth primary payloads and CubeSats. For primary payloads, the random vibration environment is The LauncherOne maximum predicted environment for random vibration is shown below for RANDOM VIBRATIONS MPE VIBRATIONS RANDOM 16 FIGURE RANDOM VIBRATION RANDOM grms 2000 800 50 20 grms 2000 800 100 20 FREQUENCY (HZ) FREQUENCY (HZ) RANDOM VIBRATION MPE FOR CUBESAT, 22.7 KG OR LESS (BASED ON NASA GSFC-STD-7000A) NASA ON (BASED LESS OR CUBESAT, KG 22.7 FOR MPE VIBRATION RANDOM 9 TABLE GREATER OR KG 60 SATELLITE, PRIMARY FOR MPE VIBRATION RANDOM 8 TABLE

PSDPSD (G^2/HZ) (g^2/Hz) 0.0001

0.0001 0.001 0.001 0.01

0.1 0.01 0.1 10

100 CubeSat (Based on NASA GSFC-STD-7000A for 22.7 kg or Less Payload) Less or kg for 22.7 NASA GSFC-STD-7000A on (Based CubeSat PrimarySatellite (60or kg Greater)

FOR 22.7 KG OR LESS PAYLOAD) CUBESAT (BASED ON NASA GSFC-STD-7000A 100 10.0 0.013 0.08 0.08 0.013 2.8 0.0010 0.0063 0.0063 0.0013 POWERSPECTRAL (PSD) (G^2/HZ) POWERSPECTRAL DENSITY (PSD) (G^2/HZ) FREQUENCY (HZ) 100 rqec [Hz] Frequency (60 KG OR GREATER) PRIMARY SATELLITE

1,000 1,000 36 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.6 400 315 250 200 160 125 100 80 63 50 40 31.5 25 20 acoustic analysis is performed. The maximum predicted acoustic environment for atypical payload fill factor is defined in FREQUENCY (HZ) MAXIMUM PREDICTED ACOUSTIC ENVIRONMENT ACOUSTIC PREDICTED MAXIMUM 10 TABLE TABLE 10 and ACOUSTICS MAXIMUM PREDICTED ACOUSTIC ENVIRONMENT ACOUSTIC PREDICTED MAXIMUM 17 FIGURE


SPL (dB ref 20E-6 Pa)

100 110 120 130 140 150 100 140 90 150 130 120 110 90 10 10 FIGURE 17 129.5 129.7 130.0 130.0 129.7 129.5 128.7 128.0 0 7. 2 1 126.0 125.0 124.0 123.0 122.0 (DB, REFERENCE: 2E-5 PA) SOUND PRESSURE LEVEL (SPL) . For missions of large very or small fill factors, a mission-unique 100 100 FREQUENCY (HZ) rqec [Hz] Frequency (OASPL) =[dB RE:2e-5 PA] Overall SoundPressure Level 10,000 8,000 6,300 5,000 4,000 3,150 2,500 2,000 1,600 1,250 1,000 800 630 500 FREQUENCY (HZ) 1,000 1,000 (OASPL) =141.40 Overall SoundPressure Level 116.0 117.0 118.0 119.0 120.0 125.0 0 7. 2 1 128.0 0 7. 2 1 126.0 126.0 0 7. 2 1 128.0 128.7 (DB, REFERENCE: 2E-5 PA) SOUND PRESSURE LEVEL (SPL) 10,000 10,000

37 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.7 1,215 1,215 960 960 340 340 320 320 152 152 108 108 10 (RF SUSCEPTIBILITY, MHZ) by Virgin Orbit. Maximum permissible payload electric field emissions are defined in after separation but are subject to the results of an EMI/EMC compatibility analysis conducted the payload. Payload RF transmissions are permitted during captive carry, ascent, and shortly with launch vehicle avionics given the proximity of launch vehicle communications systems to As with most modern launch vehicles, there is potential for electromagnetic interference (EMI) to verify compatibility. verify to spurious general emission from the spacecraft bus. Aradiated emission may required report be and FREQUENCY MAXIMUM SPACECRAFT ELECTRIC FIELD EMISSIONS FIELD ELECTRIC SPACECRAFT MAXIMUM 11 TABLE SPACECRAFT RADIO FREQUENCY (RF) CONSTRAINTS (RF) FREQUENCY RADIO SPACECRAFT MAXIMUM ALLOWABLE SPACECRAFT ELECTRIC FIELD EMISSIONS FIELD ELECTRIC SPACECRAFT ALLOWABLE MAXIMUM FIGURE 18 18 FIGURE FIGURE 18 ElectricELECTRIC Field (dbuV/m)FIELD (DBUV/M) 0.00E+00 4.00E+01 6.00E+01 9.00E+01 8.00E+01 5.00E+01 2.00E+01 3.00E+01 7.00E+01 1.00E+01

0.00E+00 1.00E+01 2.00E+01 3.00E+01 4.00E+01 5.00E+01 6.00E+01 7.00E+01 8.00E+01 9.00E+01

10 , and provided here as guidance for the customer. Generally, this will also include 10 Maximum SpaceVehicle (dBuV/m) FieldEmissions Electric 8.00E+01 3.80E+01 3.80E+01 8.00E+01 8.00E+01 3.77E+01 3.77E+01 8.00E+01 8.00E+01 2.40E+01 2.40E+01 8.00E+01 8.00E+01 (DBUV/M) ELECTRIC FIELD 100 100

Electric Field (dBuV/m) FREQUENCY (MHZ) Frequency (MHz) 1,000 18,000 5,100 5,100 5,020 5,020 2,120 2,120 2,015 2,015 1,680 1,680 1,559 1,559 (MHZ) FREQUENCY 1000 10,000 10000 8.00E+01 8.00E+01 5.68E+01 5.68E+01 8.00E+01 8.00E+01 2.00E+01 2.00E+01 8.00E+01 8.00E+01 2.00E+01 2.00E+01 8.00E+01 (DBUV/M) ELECTRIC FIELD 100,000 TABLE 11 100000

38 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.9 5.8 1,647 1,647 1,642 1,637 1,637 1,215 1,215 960 960 137 137 118 118 10 (RF EMISSIONS, MHZ) FREQUENCY MAXIMUM LAUNCH/CARRIER VEHICLE ELECTRIC FIELD EMISSIONS FIELD ELECTRIC VEHICLE LAUNCH/CARRIER MAXIMUM 12 TABLE to Virginto Orbit. A spacecraft receiver list with known in-band and out-of-band susceptibilities must provided be • • • • • • • information includes: “GUIDANCE ON OBTAINING LICENSES FOR SMALL SATELLITES” and the EELV-SIS; the collected integration, captive carry flight, or free-flight. Following the guidance of FCC DA:13-445 must provided be if the user intends to transmit intentionally during any phase of processing/ For spacecraft with intentional emitters (transmitters) and receivers: additional information The maximum launch vehicle and carrier aircraft electric field emissions are listed in and and ELECTRIC FIELD LIMIT RF EXCEED TO NOT AIRCRAFT CARRIER AND VEHICLE LAUNCH RECEIVERS AND EMITTERS INTENTIONAL SPACECRAFT FIGURE 19 ConOps plan for ground test and activation after deployment characteristics gain Antenna Emitter/signal Identifier (traceable to FCC Emissions Designator) Modulation Occupied bandwidth &data rate Peak power Center frequency

. Customers are to ensure that their spacecraft is not susceptible to these levels. 1.20E+02 1.46E+02 1.46E+02 1.46E+02 1.20E+02 1.20E+02 1.46E+02 1.46E+02 1.20E+02 1.20E+02 1.46E+02 1.46E+02 1.20E+02 1.20E+02 (DBUV/M) ELECTRIC FIELD

18,000 16,200 16,200 15,700 15,700 9,350 9,350 9,310 9,310 2,290 2,290 2,200 2,200 (MHZ) FREQUENCY 1.20E+02 1.20E+02 1.60E+02 1.60E+02 1.20E+02 1.20E+02 1.46E+02 1.46E+02 1.20E+02 1.20E+02 1.60E+02 1.60E+02 1.20E+02 (DBUV/M) ELECTRIC FIELD TABLE 12

39 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.10 Captive Carry–Bleed Air Captive Carry–GN2 (Ground Conditioning System) Mated to thelaunchvehicle spaceport) Payload Trailer (for transport to Processing Facility Virgin Orbit’s Nebula Payload opened through captive untilopened carry drop. a temperature and humidity controlled environment from the time the shipping container is Once the customer payload arrives at the Nebula Payload Processing Facility, it will remain in CONFIGURATION THERMAL AND HUMIDITY ENVIRONMENT HUMIDITY AND THERMAL F surface with an emissivity of 0.9. fairing, the payload will exposed be to an equivalent radiative heat flux emanating from a 200 deg During powered flight and until fairing separation, with aluminized Kapton on the interior of the customer’s request. thermal control. This is an optional service and will only included be as acapability at the Electrical power can provided be to the payload during captive carry for internal spacecraft Short outages of conditioned air may required be when changing configurations. THERMAL AND HUMIDITY ENVIRONMENT HUMIDITY AND THERMAL 13 TABLE EMISSIONS FIELD ELECTRIC AIRCRAFT CARRIER VEHICLE/ LAUNCH ALLOWABLE MAXIMUM 19 FIGURE

ELECTRIC FIELD (DBUV/M) 1.00E+02 1.60E+02 1.80E+02 1.40E+02 1.50E+02 1.20E+02 1.30E+02 Electric Field (dBuV/meter) 1.70E+02 1.10E+02

1.80E+02 1.00E+02 1.10E+02 1.20E+02 1.30E+02 1.40E+02 1.50E+02 1.60E+02 1.70E+02

10 10 Maximum Vehicle Launch/Carrier FieldEmissions Electric 40-80°F (4-27°C) 40-80°F (4-27°C) 63-77°F (17-25 °C) 63-77°F (17-25 °C) 63-77°F (17-25 °C) TEMPERATURE 100 100 Electric Field (dBuV/meter) Field Electric FREQUENCY (MHZ) Frequency (MHz) 1,000 ≤60% ≤60% ≤60% 40-60% 40-60% RELATIVE HUMIDITY 1000 10,000 10000 Class 8(100K) Supplied airconsistent with ISO Class 8(100K) Supplied airconsistent with ISO Class 8(100K) Supplied airconsistent with ISO ISO Class8(100K) ISO Class8(100K) CLEAN ROOM STANDARD 100,000 100000 40 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 5.12 5.11 than 0.55 psi/sec for no more than 5seconds. period during the transonic spike, in which there is atime-averaged decay rate that is no higher (0.4 psi/second) from liftoff through immediately prior to fairing separation, except forDuring abrief ascent, the maximum depressurization rate for LauncherOne is less than 2758 Pa/second for a detailed list of Customer Spacecraft Testing Requirements. Spacecraft list of Customer for adetailed A.4 Appendix the See required. be may tests system integrated and for interfaces acceptance qualification/ and handling, & safety logic, Additionally, information verification regarding • • • • • notare limited (but to):include verifications requirement design Required mission success. overall and launch on survivability to spacecraft ensure mandatory are levels analysis and detailing the test documents verification toenvironments, flight the spacecraft of the qualification and compliance to requirement design In order validate the SPACECRAFT QUALIFICATION AND COMPLIANCE AND QUALIFICATION SPACECRAFT ENVIRONMENT PRESSURE FAIRING Dynamic Loads and Environments Structural Fundamental Frequency Volume Mass Properties Safety Factors VIRGIN ORBIT LOCATIONS 42 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 6.1 6 Nebula PayloadProcessing Facility-LongBeach,CA unpacking and testing is complete. For details on payload processing, see Section 4.1. headquarters in Long Beach. The facility is where payloads are encapsulated after spacecraft Nebula, our Payload Processing Facility (PPF), is located just down the road from our main Long BeachHeadquarters which features state-of-the-art manufacturing equipment and custom-built test rigs. engineering team works directly adjacent to the LauncherOne production and assembly line, manufacturing, integration, assembly, and test activities occur in this facility.housing The Virgin office Orbitspace and a large manufacturing floor. The vast majority of our design, engineering, The Virgin Orbit headquarters is an 180,000 sq /16,700 ft sq mfacility in Long Beach, California, HEADQUARTERS IN LONG BEACH, CALIFORNIA FOR MANUFACTURING AND INTEGRATION AND MANUFACTURING FOR CALIFORNIA BEACH, IN LONG HEADQUARTERS 20 FIGURE LAUNCH VEHICLE PRODUCTION AND TEST FACILITIES TEST AND PRODUCTION VEHICLE LAUNCH LOCATIONS ORBIT VIRGIN

Manufacturing andIntegration 43 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 6.2 LauncherOne TGOSsetup- Mojave,CA relatively low-cost sovereign launch capability. LauncherOne Demo in May 2020. Customers can leverage LauncherOne’s modularity to unlock a in amobile, cleanroom environment. Virgin Orbit successfully proved out the TGOS during the to the carrier aircraft, fuel and pressurize the rocket, and service the LauncherOne payload of trailers capable of traversing public roads used to transport LauncherOne, mate LauncherOne extensive infrastructure traditionally associated with ground launch. The TGOS consists of aset leverages afully Transportable Ground Operating System (TGOS) to eliminate the for need licensed horizontal spaceport with along enough runway for a747-400 aircraft. Virgin Orbit The unique modularity of the LauncherOne system enables launches from any government Stage Test stands. test vertical Newton family of engines occur at our horizontal test stands, and stage tests are performed on composite tank, component, and overall stage testing. Acceptance testing for LauncherOne's Mojave, California, where there are multiple custom-built test stands for liquidThe Virgin propulsion, Orbit team conducts high- testing near the Mojave Air and Space Port in PROPULSION TEST SITE AND NEWTONTHREE HOT FIRE TEST ON TEST STAND TWO STAND TEST ON TEST FIRE HOT NEWTONTHREE AND SITE TEST PROPULSION LIQUID FIGURE 21 SPACEPORT FACILITIES

NewtonThree HotFireTest 44 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE the drop point is optimally located based on the inclination desired for the mission. coastline, after aflight of approximately one hour. For low-inclination launches from Guam, LauncherOne launch vehicle over the Pacific Ocean, tens of kilometers from the California The baseline flight profile LauncherOne ofa mission from Mojave involvesrelease of the Eastern and Western ranges. vehicles in the launch padkeep-out zone, and manifest jams on the increasingly crowded factors that can delay ground-based launches such as , offline radar tracking assets, Because we are not reliant on afederal launch range, we are unaffected by many of the external aircraft. Girl ground systems aboard the ground support trailers as needed prior to separation from Cosmic controllers in the control room receives telemetry and commands the launch vehicle, as well as and teams on console at the headquarters facility in Long Beach. Software operated by vehicle Launch operations are additionally supported by alaunch engineer on console in Cosmic Girl Launch operations for all spaceports are managed from Virgin Orbit’s Long Beach control room. LauncherOne-ready spaceports. discussions with many other countries on the prospects of expanding the number of international Newquay (NQY) in the UK and at Oita Airport (OIT) in Japan in the coming years. Virgin Orbit is in of commencing LauncherOne operations from both Cornwall Spaceport at Cornwall Airport network of spaceports and countries across the world. Currently, Virgin Orbit is in the process Virgin Orbit is also in the process of bringing flexible launch for small satellites to aglobal for commercial horizontal launch operations of reusable vehicles, such as our 747-400 aircraft. mid-inclination launch services take place out of Guam. Both sites are FAA licensed spaceports High-inclination launches take place out of Mojave Air and Space Port (MHV), California. Low- and MAP OF LAUNCH LOCATIONS LAUNCH OF MAP 22 FIGURE

Mojave Air and Port, Space CA Launch and Landing Facility, FL Spaceport Cornwall, UK , Guam Oita Spaceport, Japan Spaceport, Oita


DOCUMENT REFERENCE 47 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE .3 7. 2 7. 7.1 SSO SLF RP RF RAAN PSD PSC PPF PAF OSHA OIT N4 N3 NQY MHV LSA LOX LEO ICD GSE FAA EMI EMC ESPA EGSE CLA C/CAM CCAFS CAD Table 13 Table 12 Table 11 Table 10 Table Table 9 8 Table 7 Table Table 6 Table 5 Table 4 Table 3 2 Table Table 1 LIST OF TABLES LIST OF ACRONYMS LIST Figure 23 Figure 22 Figure 21 Figure 20 Figure 19 Figure 18 Figure 17 Figure 16 Figure 15 Figure 14 Figure 13 Figure 12 Figure 11 Figure 10 Figure 9 Figure 8 Figure Figure 7 Figure 6 Figure 5 Figure 4 Figure 3 Figure 2 Figure 1 LIST OF FIGURES LIST

Sun-Synchronous Orbit Facility Landing Shuttle Radio Frequency AscensionRight of Ascending Node SpectralPower Density Corporation Systems Planetary Facility Processing Payload Payload Attach Fitting Health SafetyOccupational and Administration Airport Oita [2ndNewtonFour stage engine] [1stNewtonThree stage engine] Cornwall Newquay at CornwallSpaceport Airport Mojave Port Space Air and Agreement Services Launch Liquid EarthLow Orbit Interface Document Control Equipment Support Ground Federal Aviation Administration Interference Electromagnetic Compatibility Electromagnetic EELV Payload Secondary Adapter Equipment Electrical Support Ground Analysis Loads Coupled Collision/Contamination Avoidance Maneuver CanaveralCape Air Force Station Computer-Aided Design Fully-integrated LauncherOne vehicle Fully-integrated LauncherOne ofMap Locations Launch Liquid Propulsion Test Site Fire Hot NewtonThree and Test Test on Stand Two in Beach, Long Headquarters California for Manufacturing Integration and Allowable Vehicle/Carrier Launch Maximum Aircraft Electric Field Emissions Allowable Spacecraft ElectricMaximum Field Emissions Predicted AcousticMaximum Environment Vibration Predicted Environment Random Maximum at the Standard Payload Predicted Environment Interface Shock Maximum VehicleLaunch System Coordinate Trailer Payload Layout of Payload Processing Facility in Beach, Long CA Payload Processing Flow Mission Timeline Payload Electrical Interface Diagram Interface Separation Payload Envelope Dynamic Fairing Payload Payload Configurations Sample LauncherOne Profile Mission Orbital Payload Delivery Curves -Guam Performance Orbital Payload Delivery Curves -Mojave Performance System View Expanded LauncherOne VirginThe Orbit Family Thermal and Humidity Environment and Thermal Launcher/CarrierMaximum Vehicle Electric Field Emissions Spacecraft Electric FieldMaximum Emissions Predicted AcousticMaximum Environment GSFC-STD-7000A) Vibration MPERandom for CubeSat, 22.7 Less or Kg (Based NASA on Vibration MPERandom for Satellite, Primary 60 Greater or kg Design Factors Load LauncherOne at the Standard Interface Payload Primary Design Factors Load LauncherOne Electrical Access Payload Electrical Accommodations Typical Pre-Separation Attitude Spin-Rate and Accuracies (3 sigma) Typical Orbital Injection Accuracy (3 sigma) ServicesLaunch Quick Reference APPENDIX 49 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE A.1 Post-Launch Launch +60Days Spacecraft Separation Launch +3Hours Launch -3 Days Launch -30 Days Review Mission Readiness Launch -45days Launch -2 Months Launch -3 Months Launch -6Months Review Mission Analysis Launch -8 Months Launch -9 Months Launch -10 Months Kick-off Meeting LSA+4 Weeks MILESTONE DATE DELIVERABLES BY MILESTONE & CUSTOMER ORBIT OF VIRGIN OVERVIEW • • • • • • • • • • • • • • • • • • • • • • VIRGIN ORBIT DELIVERABLES Post-Launch Evaluation Report Status Quick-Look separation vector; Post-Launch Separation confirmation and Day of launchschedule Launch CampaignOverview confirmation Launch vehicle readiness applicable) (if Updated engineeringanalyses Updated integration schedule ICD verifications Spacecraft processing plan re-contact analysis results Updated dispersed trajectory and Updated engineeringanalyses Updated missionschedule Updated verification matrix Signed ICD Payload stack configuration Preliminary engineeringanalyses Updated missionschedule Draft verification matrix Initial ICDrelease Mission schedule and thermalmodels Requirements for CAD, dynamics, Draft ICD • • • • • • • • • • • • • • • • • • • • • • • • CUSTOMER DELIVERABLES Spacecraft delivery Spacecraft pre-ship readiness verification Confirmation of alllicenses for transport Final massproperties Security andlogistics forms Environmental test reports ICD verifications Spacecraft processing schedule Spacecraft FCC licenseconfirmation Definition of fit checkgoalsand requirements FAA Launch License Completed template that supports document for the Updated spacecraft program/production schedules Signed ICD Spacecraft processing inputs Spacecraft safety inputs analysis isperformed) payloadSpacecraft specific thermal thermal model (if Spacecraft qualification plan Spacecraft program/production schedules Spacecraft Con-Ops Updated CAD &FEMmodels Craig-Bampton model-dependsontype/size) Spacecraft dynamicsmodel(can beeither aFEMor Mission-specific ICDinputs Spacecraft CAD modelandinitial massproperties Completed Payload Questionnaire 50 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE A.3 A.2 and Requirements Definition of Fit CheckGoals for FAA Launch License Supports SMA-28 Document Completed Template That Spacecraft Qualification Plan Production Schedules Spacecraft Program/ Spacecraft ConOps Spacecraft Dynamics Model and CAD Model Spacecraft MassProperties Payload Questionnaire Post-Launch Evaluation Report Post-Launch Status Quick-Look Engineering Analyses Interface Control Document DELIVERABLE DELIVERABLE DESCRIPTION OF CUSTOMER DELIVERABLES CUSTOMER OF DESCRIPTION DELIVERABLES ORBIT VIRGIN OF DESCRIPTION etc.) Overview of what isexpected for theFit Check(e.g. location of fit check, procedures, parameters, etc. This questionnaire requires inputs onlaunchdate, objects to achieve orbit, orbital Questionnaire that supports documentation required for FAA Launch License. qualification unit oristhere onlyaflight unit tobeused for testing)? Summary of approach taken towards(i.e. qualification willtheretesting be adedicated interdependencies. Integration, and Test (AI&T) andspacecraft delivery to inform Virgin Orbit of schedule Summary andtimingof key program milestones suchasPDR, CDR, Assembly, requirements. to better understand ifany spacecraft requirements may impact launchvehicle A basicdescription of thespacecraft Concept of Operations to enable Virgin Orbit provide detailed guidanceonthemodel requirements. Model to enablepayload-to-launch vehicle Coupled Loads Analysis. Virgin Orbit will flight dynamics. Mass, CG, andInertiaMatrix for Virgin Orbit to evaluate launchvehicle integration and Initial basicinformation aboutthepayload andthemission. trajectory, events, andenvironments. A fullreport willbedelivered within 60days after launch,containing details of launch the launchvehicle telemetry data willoccurnolater than3hours after separation. The spacecraft state vector andaquicklookassessment of post launchstatus from • • • Includes (butisnot limited to) thefollowing: complies with spacecraft requirements. Document that summarizes allmissionrequirements to ensure launchservice DESCRIPTION DESCRIPTION Separation Analysis: thisanalysis verifies accurate andlow riskpayload deployment. environment. Acoustics) confirm that spacecraft iscompatible with thelaunch vehicle Environments Analyses: theseanalyses (CLA, Random Vibration, Shock, and delivered to therequired missionorbit. Trajectory andPerformance Analysis: thisanalysis ensures that thepayload is 51 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 4 4 5 Frequency Natural Minimum Quasi-Static Loads Thermal (TVAC) RequirementStrength FatigueMechanical Vibration Random A.4 Mechanical Shock Mechanical Sine Vibration Acoustics 5. 4. 3. 2. 1. CUSTOMER SPACECRAFT TESTING REQUIREMENTS TESTING SPACECRAFT CUSTOMER Shock LowerTolerance:-3dB exceptions: Tolerances perSMC-S-016(version5September2014) Table4.7.1applywithfollowing Mechanical shocktestingisoptional. loads areenvelopedbyrandomvibrationtesting. Acoustic andsinevibrationtestingmaybewaived ifthepredictedspacevehicle An acceptancetestverifiestheworkmanshipofflightspacevehicles. positive minimummarginofsafetytoqualificationloads. protoqualification loadsanddurationsamechanicalstrengthanalysisshows fatigue analysisshowsacumulativedamageindex(CDI)oflessthan0.5for The protoqualificationtestarticlemaybeusedforflightifamechanical single spacevehicleatreduceddurationthatverifiesthedesignisqualified. A protoqualificationtestisamodifiedqualificationperformedon qualification testarticlemaynotbeusedforflight. life-cycle fatigueandaresubjecttochangeduepayloadspecificanalysis.The variability. Qualificationtestdurationsarecalculatedtoprovideanequivalent4x and fatiguerequirementswithmarginnecessarytoaccountforbuild-to-build A qualificationtestverifiesthatthedesignofspacevehiclemeetsstrength Test N/A N/A Test Test Test Test Analysis or Test Analysis or Test METHOD QUALIFICATION 8 Cycles Beyond ATP ±10°C N/A N/A 2 oct/min unmanned Limit x1.25 manned Limit x1.5 MPE +3dB 180 sec. at MPE +3dB 120 sec. at at MPE +3dB 3 exposures N/A unmanned Limit x1.25 manned Limit x1.5 MARGIN Performance Functional Post N/A N/A Failure No Performance Functional Post No Failure + Failure No Failure No Hz 35 > Failure No CRITERIA Test Analysis Analysis Test Test Test Test Analysis or Test Analysis or Test METHOD PROTOQUALIFICATION 4 Cycles ATP ±5°C Beyond Test Levels Qualification Test Levels qualification Proto- 4 oct/min unmanned Limit x1.25 manned Limit x1.5 MPE +3dB 120 sec. at MPE +3dB 60 sec. at MPE +3dB 1 exposure at N/A unmanned Limit x1.25 manned Limit x1.5 MARGIN Performance Functional Post MS >0 CDI <0.5 Yield No Performance Functional Post No Yield + Yield No Failure No Hz 35 > Yield No CRITERIA Test N/A N/A N/A Test N/A N/A N/A Test METHOD ACCEPTANCE 4 Cycles MPT N/A N/A N/A MPE +0dB 60 sec. at N/A N/A N/A Limit x1.1 MARGIN Performance Functional Post N/A N/A N/A Performance Functional Post No Yield + N/A N/A N/A Yield No CRITERIA 52 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE 53 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE Virgin Orbit, LLC / Version 2.1 / August 2020

For questions about bookings, capabilities, or this User’s Guide itself, please do not hesitate to contact Virgin Orbit at [email protected] Please note that this service guide is a working document, and as such is revised and updated periodically. Virgin Orbit encourages readers to visit virginorbit.com frequently to ensure they have the latest version.