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SERVICE GUIDE

Virgin , LLC / Version 1.2 / July 2019 Cleared for Release: 18-S-1862 1 LAUNCHERONE SERVICE GUIDE V1.2 +1 5623844400 virginorbit.com [email protected] Contact Us President and CEO Virgin of Orbit Hart Dan open space to change the world for good! We invite you to contact us and share your mission needs. Together we companies. Virgin distinguishes this with streamlined processes and the superior customer service that launching your small should hassle-free, be and we are enabling fixed ground infrastructure and onerous pre-launch paperwork. believeWe LauncherOne air-launch system provides freedom from the constraints of and affordably. Designed from scratch with these guiding principles, the transformational movement; to get small to orbit quickly, reliably,timelines, and at lower cost. We developed LauncherOne to complement this capabilities that benefit our planet. Small satellites are doing more on shorter to provide global connectivity, remote sensing, security, and visionary new Virgin Orbit is excited about the tremendous potential of small satellites 2 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 7.3 7.2 7.1 7/DOCUMENT 39REFERENCE 6.3 6.2 6.1 35 ORBIT VIRGIN 6/ ABOUT 5.13 5.12 5.11 5.10 5.9 5.8 5.7 5.6 5.5 5.4 5.3 5.2 5.1 23 ENVIRONMENTS 5/ 4.5 4.4 4.3 4.2 4.1 17 OPERATIONS LAUNCH AND PROCESSING 4/ PAYLOAD 3.4 3.3 3.2 3.1 13 PROCESS SERVICE LAUNCH ORBIT VIRGIN 3/ THE 2.5 2.4 2.3 2.2 2.1 7 MISSION YOUR DESIGN 2/ 1.1 3 EXPERIENCE ORBIT VIRGIN 1/ THE CONTENTS

List of Figures 41 Figures of List Tables 40 of List 40 Acronyms of List 38 Facilities 37 Test Facilities and Production Vehicle Launch 36 Overview Corporate 32 Interface Electrical 32 Signal System Separation 31 Compliance and Qualification Spacecraft 31 Environment Pressure Fairing 30 Environment Humidity and Thermal 29 Receivers and Emitters Intentional Spacecraft 28 Environment and Constraints (RF) Frequency Radio Payload 27 Acoustics 26 Random Vibration 25 Environment Shock 25 Loads Quasi-Static from Acceleration 24 Constraints Payload 24 System Coordinate Vehicle 21 Flow Operations Launch 21 Locations Launch 20 Flow Processing Payload 19 Transport Payload 18 Facilities Processing Payload 16 Assurance Mission and Safety 15 Responsibilities Customer 15 Schedule Service Launch 14 Elements Service Launch 12 Systems Separation Supported Payload Accommodations 10 9 Accuracy Insertion Orbit 9 Pofile Mission 8 Capability Delivery Payload 6 aGlance at Capabilities

3 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 4 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 EXPANDED VIEW SYSTEM LAUNCHERONE 1/ FIGURE

performance. trap of incurring significant cost increases for only a marginal increase in favoring astraightforward and reliable design. This avoids the common LauncherOne’s design, the Virgin Orbit team actively rejected complexity, (different numbers of stages, various propulsion types, etc.). Throughout which all potential vehicle configurations were traded againsteach other LauncherOne was designed through a“clean-sheet” design process, in low. In order to balance performance with commercially-competitive pricing, The simple design of LauncherOne increases reliability while keeping costs 747-400 carrier aircraft, , as depicted in LauncherOne is carried to an altitude of approximately 35,000 feet by the (LEO) at an affordable price. Rather than launching from the ground, small satellites of up to 500 kg/1100 lbm into awide range of Low Earth LauncherOne is asimple, expendable, designed to place LauncherOne is Your Ride to Space facilities required to build acustomer-focused launch service. LauncherOne, is the result of our investment in the team, technologies, and that is equally agile, flexible, and affordable. Virgin Orbit’s launchThe rapidlyvehicle, growing industry requires alaunch service THE VIRGIN ORBIT EXPERIENCE ORBIT VIRGIN THE FIGURE 1 . 5 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 PAYLOAD CONFIGURATIONS PAYLOAD SAMPLE LAUNCHERONE 2/ FIGURE 3543.3mm Envelope Dynamic Payload

2123.4mm 1262.4mm 441.96mm of accommodating avariety of standards for one or multiple spacecraft. LauncherOne offers alarge fairing for its class with apayload adapter capable centers, making work shifting comfortable and convenient. also close to local amenities such as hotels, restaurants, shopping, and fitness clearances to work, featuring modern facilities and equipment. The facility is to many other launch systems. The site is secure but does not require The staffing and launch campaign logistics are simplified in comparison connectivity to all of parts the world. proximity to these international travel and shipping hubs enables seamless Airport (LGB), and both the of ports Long Beach and Los Angeles. The major airports such as Los Angeles International and (LAX) Long Beach The payload processing facility is located at an optimal location, close to Class Leading Flexibility Payload of origin, orbital destination, and launch date. available to small satellites, including tremendous flexibility in the spaceport a mobile launch platform, offering custom launch solutions not traditionally and vehicles in the launch padstay-out zone. The carrier aircraft serves as congestion in the launch queue, weather, unavailable radar tracking assets, LauncherOne avoids common causes of launch delays such as manifest operations. Byoperating independently from national launch ranges, ground launched systems, and provides unprecedented flexibility in launch lead time. Air-launch eliminates much of the compulsory overhead of Launches are available to any orbit inclination with as little as 6months Your Orbit on Your Schedule Payload Primary Single CubeSat Multiple and Primary Small Release) (Axial Payloads Primary Similar Multiple, Release) (Lateral Payloads Primary Similar Multiple, Payloads Test 6 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 Regulatory Approach Payload Integration Payload Processing Launch Schedule Launch Altitudes/Inclinations PayloadDynamic Volume Payload Capability Service QUICK REFERENCE SERVICES LAUNCH 1/ TABLE

• • • • • • • • • • • • • • • • • Capability Summary to suit each customer’s mission-specific requirements. following sections of this Service Guide, and may customized be as needed Key components of Virgin Orbit’s LauncherOne service are summarized in to contact us with questions or special accommodation requests. each customer to assist in all aspects of the mission. Please do not hesitate Launch Services Agreement is executed, aMission Manager is assigned to detailed, mission specific information is available upon request. After a This document is intended as alaunch planning resource, and more processes leading up to launch and emphasizing customer satisfaction. improving the overall experience of getting to orbit, by streamlining the engineers can add to your launch experience. To accomplish this we are particular emphasis on the value that our dedicated and spirited team of renowned Virgin customer service to the industry, placing As amember of the Virgin family, Virgin Orbit aims to extend the world Bringing Launch to Space the Virgin Experience of the lounge style office space our facility is wellequipped to hostyour team. tailored to the small satellite customer and all the comforts and convenience integration and testing in our state of the cleanrooms, art with features located in Long Beach, . Payload teams can perform all final Customers are welcomed at Virgin Orbit’s premier payload processing facility TABLE 1 CAPABILITIES AT AGLANCE CAPABILITIES Compliance with international orbital debris disposalguidelines Launch andReentry of aReusable Launch Vehicle (RLV). VO’s LauncherOne launchislicensed undertheFederal Aviation Administration regulation 14CFR431, aggregators Secondary payloads manifested andmanageddirectly by Virgin Orbit orviapayload brokers or Support for commercially-available separation systems andCubeSat dispensers Compatible with ESPA andESPA-Grande classconfigurations diameters andboltpatterns available Conical payload adapter with baselineinterface diameter of 609.6 mm/24.0 inches; other various Encapsulation of payload at thecustomer site Storage of loadedcubesat Receipt of loadedindispenser Additional Payload options include: in Long Beach,CA Independently-operated customer payload processing facility with ISOLevel 8(100kclass) cleanroom Flexible launchwindows to accommodate schedulechanges/variation Emphasis onreducing time-to-launch; 9months for atypical primarypayload Flexibility to conduct launchfrom any licensedspaceport facility overflight constraints Orbital inclinations from 0to 180degrees; subject to any launch-site specificpopulation 3543 mm/139.5 inchoverall envelope length 2123 mm/83.6 inch constant cylindrical length 1262 mm/49.7 inchconstant cylindrical diameter Up to 500kg /1100lbmto 230km/124 nmicircular 0degree inclination (LEO) Up to 300kg /661lbmto 500km/270 nmiSun-Synchronous Orbit (SSO) . The capabilities listed here are discussed in greater detail in the

7 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 8 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 PERFORMANCE CURVES PERFORMANCE ORBITAL PAYLOAD DELIVERY 3/ FIGURE

Stage 2Burn) (Single Stage 2Burns) Parking Orbit Ascent (Two contact aLauncherOne Mission Manager for more information. separation systems and CubeSat dispensers. Please see Section 2.3or for total mass. LauncherOne is compatible with avariety of small satellite system or dispenser must included be along with the payload in accounting above the payload interface. Thus, the mass of any required separation The performance curves in circularization is burn not required. 230 below increased performance is km for direct-inject orbits where a represented the as dip 625 at in the performance 3 in km FIGURE 625 km, consequently consuming of total aportion This . is this requirement necessitates adisposal for burn orbital altitudes above orbit lifetime above 625 left for stage upper an km. Therefore, meeting is designed to regulations meet LauncherOne that require amaximum capabilities, please contact Virgin Orbit. customer based on their specific requirements. For more detailed payload degree of customization, payload capabilities are best calculated for each orbits are provided in the figurebelow. Due LauncherOne’sto high Performance curves for LauncherOne payload delivery to several reference orbital destination to inclinations as low as 0-degree equatorial orbit. LauncherOne’s air-launch architecture enables unparalleled flexibility in PAYLOAD DELIVERY CAPABILITY MISSION YOUR DESIGN Orbit-Lowering Maneuver FIGURE 3 provide the total spacecraft mass Low IncSite:20deg Low IncSite:0deg High IncSite:SSO High IncSite:90deg High IncSite:80deg High IncSite:70deg . The The . 9 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 MISSION PROFILE MISSION 4/ FIGURE

specified mission parameters. includes refinement of theseaccuracy predictions based on customer- km circular sun-synchronous orbit. Virgin Orbit’s standard mission analysisinjection accuracy for LauncherOne are provided in mass, orbit altitude, and other mission-specific factors. Typical errors in also accommodated. be Orbit injection accuracy is dependent on payload different altitudes, eccentricities and slightly differentiated inclinationssolid propellant can upper stages. Deployment of multiple payloads into orbits of its final stage, which allows for improved orbital insertion control, to compared is accurately deployed. LauncherOne employs aliquid propulsion system for We take our commitments seriously and that includes ensuring your payload 90 minutes of final payload separation. lowering burn, and final verification of correct occurs within target orbit. For missions above 625 km, the second stage performs an orbit circularization burn is performed to accurately deliver the payload into its performed with anominal spin rate of 0.1 RPM. Once at target apogee, a During acoast of approximately half an orbit, passive thermal control is inject), shedding the payload fairing along the way early during Stage 2’s burn. and carries the payload to alow parking orbit (for missions that are not direct- 3 minutes after drop. The second stage is then ignited following ashort coast thousand feet before Stage 1Main Engine Cutoff (MECO) occurs at approximately later, vehicle ignition occurs and the vehicle ascends several hundred LauncherOne with an pitch angle of 27.5 degrees. Approximately 5seconds corridor above oceanthe to an altitude of 35,000ft, and releases fueled LauncherOne and payload. The plane flies out over an unpopulated The carrier aircraft, Cosmic Girl, takes off from the launch site with the ORBIT INSERTION ACCURACY ACCURACY INSERTION ORBIT PROFILE MISSION TABLE 2 for a500

10 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 3-Axis Altitude Type Eccentricity Right Ascension of Ascending Node(RAAN) Inclination Altitude Orbital Parameter ACCURACIES (3SIGMA) ACCURACIES SPIN-RATE AND ATTITUDE TYPICAL PRE-SEPARATION 3/ TABLE (3SIGMA) ACCURACY TYPICAL ORBITAL INJECTION 2/ TABLE

pointing and angular velocity are shown in itself and the payload to the desired attitude. Typical accuracies for Prior to payload separation, the LauncherOne second stage can orient payload deployments may select different separation attitudes. Yaw Pitch Roll Parameter result of this removal. Virgin Orbit can perform mission specific analysis to are compatible with the changes to acoustic and thermal environments as a the available volume for spacecraft that exceed this dynamic envelope and fairing inner wall. These blankets may reduced be or removed to increase thickness of acoustic blankets lining the conical and ogive sections of the accounting for the axial height of apayload separation system and the payload dynamic envelope is the net volume available for the payload after m /139.5 in overall payload dynamic envelope length. The LauncherOne diameter cylindrical section that is 2.12 m/83.6 in long resulting in a3.63 interface schematic for LauncherOne are illustrated in The available payload fairing dynamic envelope and spacecraft separation customer spacecraft prior to launch vehicle propellant loading. situation, the fairing access doors allow for late access to key portions of a the base of the fairing composite structure. In the event of a contingency The LauncherOne fairing incorporates standard payload access doors near directly by Virgin Orbit, or via payload aggregators. Grande class payload. Secondary payloads can manifested be and managed configuration. TheLauncherOne fairing can alsoaccommodate a single ESPA- by-side accommodation of two ESPA class payloads is possible as acustom payload adapter interface with the primary payload mounted on top. Side- payloads, typically asecondary payload adapter is attached to the standard requirements. For multi-satellite missions with primary and secondary employing the large fairing volume in avariety of ways to best meet customer for its class. LauncherOne has the ability to multi-manifest satellites, LauncherOne offers one of the largest payload envelopes in the industry FIGURE 6 PAYLOAD ACCOMMODATIONS PAYLOAD

, respectively. The dynamic envelope consists of a1.22 m/49.7 in ± 6.0° ± 6.0° ± ± 7.0° Angular Error 0.0022 ± 0.2° ± 0.15° ± 15km Accuracy TABLE 3 . Missions with multiple ± 0.5°/sec ± 0.5°/sec ± 2.0°/sec Rate Error FIGURE 5 and and 11 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 PAYLOAD SEPARATION INTERFACE 6/ FIGURE DYNAMIC ENVELOPE PAYLOAD FAIRING 5/ FIGURE

standard interface are provided in the ESPA and ESPA-Grande class configurations. The dimensions of the interface bolt patterns are available, including those compatible with interface is astandard 609.6 mm /24.00 inch bolt pattern. Various the launch vehicle and the payload stack. The baseline payload adapter composite conical section, providing the mechanical interface between payload adapter consists of composite forward and aft rings with a accommodations for specific requirements.LauncherOne’s standard evaluate your specific mission needs and discusspossible payload FIGURE 6 . 12 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 deployed payload. minimize contamination limit and the potential for with re-contact the Contamination Avoidance (C/CAM), Maneuver in if order to necessary, will aCollision/ perform ofevent, LauncherOne stage the second Following payloads. deployed all separation between the separation ensures allows that sequence the for deployment adequateLauncherOne your meets missionand requirements. For multi-payload missions, to ensure safe separation necessary as dynamics from the vehicle launch Virgin Orbit will analysis conduct of tip separation other off and payload Astrofein Picosatellite GmbH Launcher, D-Orbit’s and DPOD. Deployer,Spacecraft Xtenti Separation System, FANTM XPOD RAiL, Containerized PSC Solutions QuadPack, (ISIS) and in DuoPack Space Tyvak Rail-POD, Nanosatellite Adapter System Launch Innovative (NLAS), include, are not but limited by LauncherOne supported to: Cal-Poly P-POD, or independent deployment of multiple . Cubesat dispensers configurations. These of dispenserscapable aresimultaneous usually accommodate the common 1U, 2U, 3U, 6U, 12U, 16U, 27U and CubeSat dispensersCubeSat are commercially in available various sizes to System. Separation separation systems, Low Sierra Corporation QwkSep and Nevada Profile to: Systems Corporation (PSC) Motorized Planetary Lightband, RUAG PAS separation systems payload annular include, are not but limiedSupported dispensers designed to design the specification. CubeSat or discrete use point separation typically system. payloads CubeSat adapter, payload with the LauncherOne above, described via annular an mission typically flexibilityinterface to our customers.spacecraft Primary separation dispensers systems CubeSat and in order to offer maximum is compatible system.deployer with LauncherOne multiple spacecraft Virgin Orbit will assist the customer in appropriate selecting an separation/ SEPARATION SYSTEMS SUPPORTED

13 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 14 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 • • • Optional Services: • • • • • • • • Standard Services: accommodate your unique needs. optional services to further enhance your launch experience and/or distinguishes the Virgin brand. To better serve our customers, we offer All launches are given the high level of service and attention to detail that documentation, and safety considerations are described in the following sections. is conducted in a safe, expeditious, and reliable manner. Typical schedule,ensure that customer requirements are met or exceeded and the mission the spacecraft to orbit, and post flight analysis.Mission integrationactivities spacecraft processing, payload-to-launch vehicle integration, delivery of Virgin Orbit’s launch service includes mission planning, accommodation for LAUNCH SERVICE ELEMENTS SERVICE LAUNCH PROCESS SERVICE LAUNCH VIRGIN THE compliance. is available for customers unfamiliar with spacecraft regulatory Licensing: of your payload and the launch environment. Thermal Analysis: Ensure thermal compatibility with sensitive areas ensure readiness for integration. the acquisition, delivery, and processing of the separation system to System: Separation Payload Focus on your payload and let us handle Technical Assistance Agreement (TAA) from the U.S. State Department. or Spacecraft Manufacturer, Virgin Orbit will obtain and manage a Compliance: InExport the case of anon-U.S. Customer and/ and environments. 60 days after launch, containing details of launch trajectory, events, Post-Launch Evaluation Afull Report: will report delivered be within minutes after separation. preliminary evaluation of mission success, will occur no later than 180 post-launch status from launch vehicle telemetry data, as well as a L1 navigation solution at separation. AQuick-Look assessment of made available within 90 minutes after separation based on the Post-Launch Status Quick-Look: Spacecraft state vector will be deployment. Analysis:Separation Verifiesaccurate and low risk payload with the launch environment. Analysis: Loads Coupled Confirms thatyour spacecraft is compatible delivered to your mission orbit. and PerformanceTrajectory Analysis: Ensures your payload is your spacecraft needs. requirements are documented and the launch service complies with Virgin Document: Control Orbit Interface Ensures all of your mission integration and launch. Virgin Orbit Mission Manager: Your concierge for asmooth spacecraft Assistance with various standard licensing processes

15 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 FOR LAUNCH SERVICE LAUNCH FOR SCHEDULE NOMINAL 7/ FIGURE of LSA Date Effective +0 Days Contract Start

+90 Days Contract Start Meeting Kickoff Mission

requirements. Typical documentation requirements are as follows: ensuring smooth launch operations, and is used to satisfy FAA reporting facilitates coordination between the customer and Virgin Orbit mission requirements, safety data, and processing plans. This informationdocuments to formally communicate the payload system description, As the spacecraft owner, the customer is responsible for providing completion of the launch service. detailed schedule of all key technical milestones necessary for successful launch. The outline schedule shown in the vehicle, payload, and facilities to provide asafe and successful Reviews (LRR) are held to coordinate and assess overall readiness of compatibility of the payload and the launch vehicle. Launch Readiness Virgin Orbit and the customer to communicate requirements and ensure leading to launch. An Interface Control Document is jointly developed by Manager as the primary point of contact and facilitator for all activities and delivery of apost-mission Each report. customer receives aMission begins with signing aLaunch Service Agreement and culminates in launch according to mission-specific requirements. Contractual launch service in A top-level schedule for acomplete launch service engagement is provided less from contract execution. execution. Small secondary rideshare payloads can launch in 6months or primary payload, payloads can launch in as little as 9months from contract payload as quickly and reliably as possible. For astandard engagement of a corporate culture, processes, and supporting infrastructure to launch your emphasis on reducing time-to-launch. Virgin Orbit has instituted the Virgin Orbit’s dedication to streamlining launch for small satellites includes • • • • CUSTOMER RESPONSIBILITIES SCHEDULE SERVICE LAUNCH FIGURE 7 +180 Days Contract Start Draft ICD available through Virgin Orbit corporate partners. Insurance: LocalizedSecurity: and tailorable security is available, if desired. for on-site storage and handling is available for spacecraft propellant. Propellant Loading: Assistance with logistics, processes, and procedures have formerly worked on the relevant spacecraft systems. integration, and systems engineering is available from who experts Peer Review: reviewSpacecraft for , test, . The relative timing of milestones for each customer varies -180 Days Launch Report Design Service Launch Various pre-launch and launch insurance options are -45 Days Launch LRR1 FIGURE 7 serves as the basis for a at PPF Arrival Satellite -30 Days Launch Site at Launch Arrival Satellite

-2 Days Launch (Final ICD) LRR2 -0 Days Launch Launch

16 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 status is assessed during all readiness review meetings. documentation for compliance with applicable safety standards, and safety for an FAA Launch License submittal. Virgin Orbit will review the payload data is the payload questionnaire and it contains all questions needed safety requirements. The entry point for communication of payload safety and requirements. Virgin Orbit can provide guidance regarding specific payload operations are responsible for compliance with these processes and either eliminated or appropriately mitigated. Customer payloads and in place to ensure risks and resulting hazards are methodically identified, Both aSafety Policy and formal Safety and Mission Assurance Process are Health Administration (OSHA), and other applicable regulatory agencies. the Federal Aviation Administration (FAA), the Occupational Safety and launch operations. Virgin Orbit strives to exceed the requirements of throughout all aspects of payload processing, vehicle integration, and Measures are in place to ensure safety of personnel and property information to the U.S. Government for . facilitating the submission of payload information to the FAA and providingVirgin Orbit can provide assistance with regulatory needs, such as Administration) prior to commencement of any launch integration activities. Telecommunications Union, National Oceanic and Atmospheric body approval from their national authority and any other necessary regulatory The customer is ultimately responsible for obtaining licenses, permits, and • • • • • • • SAFETY AND MISSION ASSURANCE MISSION AND SAFETY payload processing. quantity of each; and identification of hazardous operations during Documentation: IdentificationSafety of hazardous materials and use of Virgin Orbit Payload Processing Facilities. ProcessingPayload Plan: Plan for payload processing and intended Coupled Analysis. Loads Finite Element Model: Model to enable payload-to-launch vehicle test, demonstration). each customer ICD requirement was verified (e.g. inspection, analysis, ICD VerificationDocumentation: Verification evidence indicating how integration and flight dynamics. & products of inertia data, for Virgin Orbit to evaluate launch vehicle and CAD model: mass Mass, properties Spacecraft CG, and moments the overall mission. unique requirements, and other design considerations that encompass interface definition, RF characteristics, ground operations needs, configuration, mission orbital parameters, mechanical andelectrical Inputs to the Launch Vehicle-to-Spacecraft ICD: Spacecraft the payload and mission. Responses to Questionnaire: Payload Initial basic information about (e.g. Federal Communications Commission, International

17 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 18 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 • • • • • • • • • • • roof. Baseline services and equipment available at the PPF include: control rooms, and conveniently located lounge style offices all under one California. The facility includes an ISO 8cleanroom, dedicated electrical state of the payload art processing facility located in Long Beach, Customers are welcome to test and process their satellite at Virgin Orbit’s customer’s specific mission requirements. to tailor standard payload processing and launch procedures to the A typical processing flow is described in this section. Virgin Orbit is minimize complexity, ensure system safety, and increase mission reliability.Payload integration and launch operations procedures are designed to PAYLOAD PROCESSING FACILITIES OPERATIONS LAUNCH AND PROCESSING PAYLOAD Virgin Orbit procured processing facility. upon request. Fueling of hazardous will occur at an external, process, but Virgin Orbit is able to address customer fueling requirements Fully-fueled payload delivery will promote the efficient integration propellant include cold , /krypton, and various “green” propellants. Accommodation for “green” propellant storage and loading. Possible closed circuit television. include electronic access IDs, 24-hour facility security guard, and Security is tailored for customer needs. Available security measures week for twelve (12) hours aday, and optional 24/7 support Virgin Orbit integration support personnel available up to six (6) days a isopropyl alcohol, lint free wipes, gloves. Consumables including compressed air, helium, and , and small handheld tools Uninterupted Power Supplies (UPS), forklift, scissor lifts, rolling ladders, 100V AC, 60Hz and 230V AC, 50 Hz Power provided for customer electrical ground support equipment at printer, copier, and machine. fax Lounge style offices and conference rooms are provided with wi-fi, cables. through between the control room and the cleanroom for electrical electrical equipment for spacecraft testing or charging. There is apass Electrical Control Room adjacent to the cleanroom for placing all encapsulation and will be: The cleanroom is for customer spacecraft processing and fairing planning. Urban location provides simplified logistics forpersonnel and resource with direct . airport,Near LAX amajor hub serving worldwide destinations many Temperature: 63-77°F Relative Humidity: 40-60% Certified ISO 8cleanliness level (Class 100K)

19 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 PAYLOAD TRANSPORT AND INTEGRATION TRAILER 9/ FIGURE CA BEACH, IN LONG FACILITY PROCESSING PAYLOAD OF LAYOUT 8/ FIGURE

launch vehicle. launch the journey from Long Beach to the spaceport site and integration to the and humidity is controlled between 40% -60%RH for the duration of vehicle. The internal environment is maintained at 21 ±3.5 °C(63-77°F) encapsulated payload to the spaceport site and integrate it to the launch Class 8clean room is equipped to safely and efficiently transport the Payload Transport and Integration Trailer. This purpose built mobile ISO After encapsulation the payload fairing module is secured within the PAYLOAD TRANSPORT PAYLOAD Airlock Cleanroom Control Room

Anteroom Entrance 20 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 07. 06. 05. 04. 03. 02. 01. Beach to the spaceport will vary): payload processing facility remains the same but transportation from Long (Contiguous ) locations are as follows (for other , the for launches from Mojave Air and or Spaceport from any other CONUS “on-demand” launch. Typical procedural steps for payload processing payload at customer facilities and storage in aflight-ready state for rapid reduced upon request. Additionally, options exist for encapsulation of the is nominally planned for 30 days prior to launch, but this timeline can be and offering as many essential resources as possible. Delivery of the payload efficient possibleas for our customers by simplifying the integration process Virgin Orbit aims to make payload processing operations as smooth and PAYLOAD PROCESSING FLOW PROCESSING PAYLOAD

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

21 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 PAYLOAD PROCESSING FLOW 10/ FIGURE

03. 02. 01. launch schedule and typical timing relative to takeoff are as follows: delivery of the encapsulated payload to the spaceport. Key events in the For standard launch operations, launch occurs within three days after the from km over the port. 1000 launch theaircraft the flexible and droplocationspoint be can for spaceports, inclination desired for the mission. to Due of range the the large carrier inclination the drop launches, point is on the optimally based located coastline, after aflight approximatelyof 30 minutes fromMojave. lowFor vehicle over the PacificOcean, tens of kilometers fromCalifornia the baselineThe flightlaunch profile LauncherOne involvesrelease of the the Pacific Islands. The mid-inclination site is in , and the low-inclination site is located inWestern ranges. The high-inclination launch site is the Mojave, California.keep-out zone, and manifest jams on the increasingly crowded Eastern and such as weather, offline radar tracking assets, vehicles in the external factors that can delay ground based launches from federal ranges a government maintained launch range, we are unaffected by many of the LauncherOne operates independently, and because we are not reliant on LAUNCH OPERATIONS FLOW OPERATIONS LAUNCH LOCATIONS LAUNCH Launch Readiness Review (L-2days) Payload mate to LauncherOne (L-3days) LauncherOne vehicle integration and checkout (L-4days and earlier) 22 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 10. 09. 08. 07. 06. 05. 04.

Payload injection (Mission dependent, but approximately T+60min) Second stage ignition (T+3minutes) LauncherOne release and launch (T+0minutes) encapsulated environment by the carrier aircraft (T-30 minutes) 747 aircraft take-off; LauncherOne purge provided to payload 747 aircraft engine start and L1GSE disconnect (T-30 minutes) Propellant loading (T-6hours to T-60minutes) (L-2 days) Rollout and mate of LauncherOne with payload to carrier aircraft

23 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 24 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 COORDINATE SYSTEM VEHICLE LAUNCH 11/ FIGURE +X +X

+Y +Z laterally and 0.6m axially from the payload to launcher separation plane. kg /1100 lbm and can support apayload center of mass up to +/50mm LauncherOne accommodates awide range of payload masses up to 500 side of the launch vehicle and carrier aircraft. gravity vector and the Y-axis is parallel to the ground pointing out of the left horizontal, captive-carry configuration, the Z-axis is oriented inverse to the the X-axis, pitch is about the Y-axis, and yaw is about the Z-axis. When in a aligned with the launch vehicle longitudinal centerline. Roll is defined about LauncherOne launch vehicle coordinate reference frame is provided in environments relative to the LauncherOne payload orientation, the standard For interpretation of the quasi-static acceleration and random vibration performed by Virgin Orbit as astandard service, and documented in the ICD. purposes only. Mission-specific analysis payloadof expected environments is subsections. This payload environment data is provided for initial planning conditions experienced by atypical payload are detailed in the following captive carry, and launch vehicle ascent. The predicted environmental launch vehicles throughout the flight profile, including ground segments, LauncherOne’s payload environments are competitive with other similar FIGURE 11 PAYLOAD CONSTRAINTS COORDINATEVEHICLE SYSTEM ENVIRONMENTS PAYLOAD . In this right-handed coordinate system, the positive X-axis is +X +Z +Y 25 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 Note: Positive axial acceleration indicates compressive loads Acceleration (g) Type DESIGN LOAD FACTORS LOAD DESIGN PAYLOAD PRIMARY LAUNCHERONE 4/ TABLE 10000 5000 700 100 Frequency (Hz) AT THE STANDARD INTERFACE AT STANDARD THE FACTORS LOAD DESIGN LAUNCHERONE 5/ TABLE

3000 3000 430 10 (G-Peak) Predicted ShockEnvironment LauncherOne Max should applied be (F.S. =1.5). derived during aircraft operations, ultimate safety factors FAR per 25.303 maximum acceleration for all phases of flight. As driving load cases are Coupled Loads analysis. The values provided in the table bound the than 65kg. Predictions are further defined and verified by mission-specific quasi-static loads predictions for asingle spacecraft with mass greater loads for LauncherOne at the payload center of gravity. These are general due to the addition of payload adapter structure, this value is lower. recomputedbe at the specific interface yourof spacecraft. In many cases, to-launch vehicle interface from all launch vehicle events is shown below in The maximum predicted shock response spectrum at the standard payload- -3g /+7g Axial (x) TABLE 4 provides representative maximum predicted quasi-static limit TABLE 5 SHOCK ENVIRONMENT QUASI-STATIC LOADS FROM ACCELERATION and and

FIGURE 12

PSD (g^2/Hz) 10,000

SRS,SRS, Q Q= = 10 10 [G(G-Peak)-Peak]1,000 0.0001 10,000 0.001 1,000 100 0.01 100 0.1 10 10 100 100 10 . For mission unique adapters, this shock value will +/- 5g Lateral (y, z) AT THE STANDARD PAYLOAD INTERFACE PAYLOAD AT STANDARD THE ENVIRONMENT SHOCK PREDICTED MAXIMUM 12/ FIGURE 1,000

100 Frequency (Hz) Frequency [Hz] Frequency [Hz] 1,000 10,000 1,000 10,000 26 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 grms 2000 800 100 20 Frequency (Hz) THE STANDARD PAYLOAD RANDOM VIBRATION ENVIRONMENT AT PREDICTED MAXIMUM LAUNCHERONE 6/ TABLE

5.5 0.004 0.025 0.025 0.005 (PSD) (g^2/Hz) Power Spectral spacecraft. this environment will recomputed be at the particular interface of your 24” diameter interface, is shown below. For mission unique adapters, environment in the axial and lateral direction, as measured at the standard The LauncherOne primary payload predicted maximum random vibration RANDOM VIBRATION RANDOM

PSD (g^2/Hz) 0.001 0.01 0.1 10 INTERFACE ENVIRONMENT AT THE STANDARD PAYLOAD VIBRATION RANDOM PREDICTED MAXIMUM 13/ FIGURE 100

Frequency (Hz) 1000 27 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 400 315 250 200 160 125 100 80 63 50 40 31.5 25 20 Frequency (Hz) ACOUSTIC ENVIRONMENTACOUSTIC PREDICTED MAXIMUM 14/ FIGURE ACOUSTIC ENVIRONMENTACOUSTIC PREDICTED MAXIMUM 7/ TABLE SPL (dB ref 20E-6Pa) 100 120 130 140 150 SPL110 [dB ref 20E-6 Pa] 100 110 120 130 140 150 90 90 10 10

LauncherOne Max Predicted Acoustic Environment

100 100 129.5 129.7 130.0 130.0 129.7 129.5 128.7 128.0 0 7. 2 1 126.0 125.0 124.0 123.0 122.0 (dB, Reference: 2e-5 Pa) Sound Pressure Level (SPL) small fill factors, a mission uniqueacoustic analysis performed.is factor is defined in The maximum predicted acoustic environment for atypical payload fill ACOUSTICS Frequency (Hz) Frequency [Hz] 1,000 1000 TABLE 7 and 10,000 10000 (OASPL) =[dB RE:20e-6Pa] 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) FIGURE 14 . For missions of large very or (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) 28 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 1,215 1,215 960 960 340 340 320 320 152 152 108 108 10 (RF susceptibility, MHz) Frequency ELECTRIC FIELD EMISSIONSELECTRIC SPACECRAFT ALLOWABLE MAXIMUM 15/ FIGURE FIELD EMISSIONSELECTRIC SPACECRAFT MAXIMUM 8/ TABLE

Electric Field (dBuV/m) Electric Field (dbuV/m) 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 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 10

Maximum SpaceVehicle (dBuV/m) FieldEmissions Electric 100 100 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 and provided here as guidance for the customer. payload electric field emissions are defined in compatibility analysis conducted by Virgin Orbit. Maximum permissible and shortly after separation but are subject to the results of an EMI/EMC Payload RF transmissions are permitted during captive carry, ascent, proximity of launch vehicle communications systems to the payload. magnetic interference (EMI) with launch vehicle avionics given the As with most modern launch vehicles, there is potential for electro- PAYLOAD RADIO FREQUENCY (RF) CONSTRAINTS (RF) FREQUENCY RADIO PAYLOAD Frequency (MHz) Electric Field (dBuV/m) 1,000 Frequency (MHz) 1000 10,000 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 10000 100,000 100000 TABLE 8 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 and and FIGURE 15

,

29 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 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 ELECTRIC FIELD EMISSIONSELECTRIC VEHICLE LAUNCH/CARRIER MAXIMUM 9/ TABLE

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 damage components. of S/V by the P/L User, however they assume full responsibility for malfunctionsusceptible or to damage by RF or DC/AC magnetic fields. This canbe waived must provided, be if the User determines the equipment may be ReceiverS/V list, including known in-band and out-of-band susceptibilities • • • • • • • collected information includes: ON OBTAINING LICENSES FOR SMALL SATELLITES” and the EELV-SIS; the Flight, or Free-Flight. Following the guidance of FCC DA:13-445 “GUIDANCE intentionally during any phase of processing/integration, Captive-Carry additional information must provided be if the user intends to transmit For spacecraft with intentional emitters (transmitters) and receivers: SPACECRAFT INTENTIONAL EMITTERS AND RECEIVERS AND EMITTERS INTENTIONAL SPACECRAFT ConOps Plan for Ground Test and Activation after Deployment characteristics gain Antenna Emitter/signal Identifier (traceable to FCC Emissions Designator) Modulation Occupied bandwidth &datarate Power Peak Center frequency 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 30 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 CARRIER AIRCRAFT ELECTRIC FIELD EMISSIONS ELECTRIC CARRIER AIRCRAFT VEHICLE/ LAUNCH ALLOWABLE MAXIMUM 16/ FIGURE

ElectricElectric Field Field (dBuV/meter) (dBuV/m) 1.00E+02 1.10E+02 1.20E+02 1.30E+02 1.40E+02 1.50E+02 1.60E+02 1.70E+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 1.80E+02 10 10

Maximum Vehicle Launch/Carrier FieldEmissions Electric 100 100 bulk fairing environment: an altitude of 10,000 The ft. nitrogen gas system will maintain the following filtered dry nitrogengas from the aircraft. gasThe willbe suppliedbelow When the aircraft is ready for take-off the purge air will transition to • • • will provided be to maintain the following bulk fairing environment: Once the payload fairing is mated to the launch vehicle filtered purge air • • • cleanroom designed to maintain the following environment: in the Payload Transportation and Integration Trailer. Equipped with a Post-encapsulation the Payload Fairing is transported to the spaceport • • • process in acleanroom designed to maintain the following environment: captive carry until drop. Upon arrival in Long Beach the payload will environment from the time the shipping container is opened through Facility, it will remain in atemperature and humidity controlled Once the customer payload arrives at the Virgin Orbit Payload Processing THERMAL AND HUMIDITY ENVIRONMENT HUMIDITY AND THERMAL Supplied air consistent with ISO Class 8(100K) Relative Humidity: ≤60% Temperature: 63-77°F (17.22-25 °C) ISO Class 8(100k) Relative Humidity: 40-60% Temperature: 63-77°F(17.22-25 °C) ISO Class 8(100k) Relative Humidity: 40-60% Temperature: 63-77°F(17.22-25 °C)

Electric Field (dBuV/meter) Field Electric Frequency (MHz) Frequency (MHz) 1,000 1000

10,000 10000 100,000 100000 31 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 required. qualification/acceptance and for integratedinterfaces system be may tests Additionally, information regarding verificationlogic, and safetyhandling, & • • • • • verifications include are not(but limited to): overall mission and on launch Required success. design requirement tothe test survivability analysis and ensure levels are mandatory spacecraft to thethe flight spacecraft environments, verificationdocuments detailing In order to validate the design requirement qualification compliance and of 0.55 psi/sec for no more than 5seconds. spike, in which there is atime-averaged decay rate that is no higher than prior to fairing separation, except for abrief period during the transonic than 2758 Pa/second (0.4 psi/second) from liftoff through immediately During ascent, the maximum depressurization rate for LauncherOne is less surface with an emissivity of 0.9. exposed to an equivalent radiative heat flux emanating from a 200 deg F During powered flight and until fairing separation, the payload willbe the payload during captive carry for internal spacecraft thermal control. configurations. At the customer’s request,electrical power is provided to Short outages of conditioned air may required be when changing • • • following bulk fairing environment: with filtered engine bleed air. The engine bleed air system will maintain the Above 10,000 the ft. nitrogen is turned off and the payload is supplied • • • SPACECRAFT QUALIFICATION AND COMPLIANCE AND QUALIFICATION SPACECRAFT ENVIRONMENT PRESSURE FAIRING Dynamic Loads and Environments Structural Fundamental Frequency Volume Mass Properties Safety Factors Supplied air consistent with ISO Class 8(100K) Relative Humidity: ≤60% Temperature: 60±20 °F(15.5 ±11.1 °C) Supplied gas consistent with ISO Class 8(100K) Relative Humidity: ≤60% Temperature: 60±20 °F(15.5 ±11.1 °C) 32 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 ground processing at the customer’s request. wires to GSE can supported be to provide Command and Telemetry during is shown below in accommodations are defined in to the payload during storage and vehicle-level integration. These payload extra harness can used be to supply power and provide adata connection spacecraft to customer electrical ground support equipment (EGSE). This a spacecraft umbilical connector to provide aconnection from the At the customer’s request, the payload adapter wire harness can include missions. spacecraft ofcontroller providing is capable multiple signals enabling multi- separation signal directly to separation system. the payload payload The redundant controller and provides payload aprimary the LauncherOne For vehicle-to-payload launch the standard interface scheme, electrical SPACECRAFT ELECTRICAL INTERFACE ELECTRICAL SPACECRAFT SIGNAL SYSTEM SEPARATION FIGURE 17 . Payload communication over 8twisted pair TABLE 10 . The Payload Electrical Interface 33 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 Electrical Bonding Voltage Description PAYLOAD ELECTRICAL ACCOMMODATIONS 10/ TABLE INTERFACE DIAGRAM PAYLOAD ELECTRICAL 17/ FIGURE

requirements shallbenegotiated by electromechanical ICDfor L/V-P/L interfaces.” Adapter (PLA)sand S/V structures for typical L1 missiondesigns. Alternative electrical bonding been evaluated andprovides adequate charge-bleed path to prevent on-orbit charging of thePayload across multiplemetal-to-metal andmetal-to-composite joints. The carbonfibercomposite layup has The payload chassisiselectrically bondedto L/V structure with nomore than200milliohms, combined and Electrical SupportEquipment electronics. unfamiliar with Section 19of DO-160G shouldseekfurtherguidanceto ensure compatibility with Payload and captive carry. Additional amperage capacity canbemadeavailable uponrequest. Users whoare Harnessing capableof supporting28 Vdc power +/4 Vdc upto 3A isprovided duringground operations Provision 34 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 separation commands is available. Modification foradditional separation commands for standard ordnance • • • • • • a standard configuration of: The standard interface to the payload, including separation is supported by SPACECRAFT SEPARATION SIGNALS One (1) RS-422 Communication line for payload use. One (1) Ethernet Communication line for payload use. separation indication to the launch vehicle. Two (2) Breakwires from the payload to the launch vehicle for separation indication to the payload. Eight (8)Breakwires from the launch vehicle to the payload for Eight (8)pairs of Double Twisted Shielded Separation Commands Rack through the umbilical to the SEIP Eight (8)Twisted Shielded Pairs 22awg from the 747 Payload Interface 35 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 36 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 THE VIRGIN ORBIT FAMILY ORBIT VIRGIN THE 18/ FIGURE

test facilities from and TSC. satellite launch market. Virgin Orbit maintains separate manufacturing and 500 dedicated employees, Virgin Orbit’s exclusive focus is on the small companies Virgin Galactic and (TSC). With almost Virgin Orbit is of part the Galactic Ventures family, along with our sister worldwide. LauncherOne is capable of operating from avariety of spaceports cost launch vehicles. In addition to launches originating from Mojave, operations functions are our keys to the production of reliable, low- approach and the close proximity of engineering, manufacturing, and operations facilities in Mojave, nearby California. vertically A integrated production in Long Beach, California, and propulsion, test and launch Virgin Orbit is aUnited States company with corporate headquarters and CORPORATE OVERVIEW CORPORATE ORBIT VIRGIN ABOUT 37 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 STAND TWO STAND TEST ON TEST FIRE 3 HOT NEWTON AND SITE TEST PROPULSION 20/ FIGURE AND INTEGRATION MANUFACTURING FOR CALIFORNIA BEACH, IN LONG HEADQUARTERS 19/ FIGURE

stands, and completed stage tests are performed on the vertical tests stands. LauncherOne engine acceptance testing is supported by horizontal test and overall stage testing is performed here at one of eight test stands. Air and Space Port in Mojave, California. Liquid propulsion, composite tank, High-energy structure, and propulsion testing is performed near the Mojave manufacturing equipment and custom-built test rigs. LauncherOne production and assembly line featuring state-of-the-art facility. The Virgin Orbit engineering team works directly adjacent to the manufacturing, integration, assembly, and test activities occur in this large manufacturing floor. The vast majority of our design, engineering, meter facility in Long Beach, California, housing office space and a The Virgin Orbit headquarters is an 180,000 square foot /16,700 square LAUNCH VEHICLE PRODUCTION AND TEST FACILITIES TEST AND PRODUCTION VEHICLE LAUNCH 38 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 VEHICLE FULLY-INTEGRATED LAUNCHERONE FIGURE21/

trailers as needed prior to separation from the 747 aircraft. launch vehicle, as well as ground systems aboard the ground support controllers in the control room receives telemetry and commands the headquarters facility in Long Beach. Software operated by vehicle launch engineer on console in the 747-400 and teams on console at the Beach control room. Launch operations are additionally supported by a Launch operations for all spaceports are managed from Virgin Orbit’s Long and ground support trailers. only the Cosmic Girl carrier aircraft, with LauncherOne mated underwing, with ground launch. “Clean pad”operations are entirely mobile and involve LauncherOne eliminates the for need extensive infrastructure associated sites employ similar architecture. The mobile launch capability provided to operations of reusable vehicles, such as our 747 aircraft. Additional launch (MHV), aspaceport licensed by the FAA for commercial horizontal launch The high-inclination launch service location is the Mojave Air &Space Port SPACEPORT FACILITIES 39 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 40 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 Table 11. Table 10. Table 9. Table 8. Table 6. Table 5. Table 4. Table 3. Table 2. Table 1. SSO SLF RP RF RAAN PSD PSC PPF OSHA N4 N3 MHV LSA LOX LEO ICD GSE FAA EMI EMC ESPA EGSE CLA C/CAM CCAFS CAD LIST OF TABLES LIST OF ACRONYMS LIST

Sun-Synchronous Orbit Sun-Synchronous Facility Landing Shuttle Propellant Radio Frequency Node Ascending of Ascension Right Density Spectral Power Corporation Systems Planetary Facility Processing Payload Administration Health and Safety Occupational engine] stage 4[2nd Newton engine] stage 3[1st Newton Port Space and Air Mojave Agreement Services Launch Liquid Orbit Earth Low Document Control Interface Equipment Support Ground Administration Aviation Federal Interference Electromagnetic Electromagnetic Compatibility Adapter Payload EELV Secondary Equipment Support Ground Electrical Analysis Coupled Loads Maneuver Avoidance Collision/Contamination Station Force Air Canaveral Cape Design Computer-Aided Payload Power Services 33 Services Power Payload 29 Emissions Field Electric Vehicle Launcher/Carrier Maximum 28 Emissions Field Electric Spacecraft Maximum 27 Environment Acoustic Predicted Maximum 26 Interface Payload Standard the at Environment Vibration Random Predicted Maximum LauncherOne 25 Interface Standard the at Factors Load Design LauncherOne Factors Load Design Payload Primary LauncherOne sigma) (3 Accuracies Spin-Rate and Attitude Pre-Separation Typical 10 (3 sigma) Accuracy Injection Typical Orbital Reference Quick Services Launch 6

25 10 41 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 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 7. Figure 6. Figure 5. Figure 4. Figure 3. Figure 2. Figure 1. Figure LIST OF FIGURES LIST

Fully-integrated LauncherOne vehicle LauncherOne 38 Fully-integrated Two 37 Test Stand Test on Fire 3Hot Newton and Test Site Propulsion Liquid Necker 37 Integration and Manufacturing for California Beach, Long in Headquarters 36 Family Orbit Virgin The 33 Diagram Interface Electrical Payload 30 Emissions Field Electric Aircraft Vehicle/Carrier Launch Allowable Maximum 28 Emissions Field Electric Spacecraft Allowable Maximum 27 Environment Acoustic Predicted Maximum 26 Interface Payload Standard the at Environment Vibration Random Predicted Maximum 25 Interface Payload Standard the at Environment Shock Predicted Maximum 24 System Coordinate Vehicle Launch 21 Flow Processing Payload Trailer 19 Integration and Transport Payload Layout of Payload Processing 15 Service Launch for Schedule Nominal 11 Interface Separation Payload 11 Envelope Dynamic Fairing Payload 9 Profile Mission 8 Curves Performance Delivery Payload Orbital 5 Configurations Payload Sample LauncherOne 4 View Expanded System LauncherOne Facility in Long Beach, CA 19 CA Beach, Long in Facility

42 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2 43 VIRGIN ORBIT LAUNCHERONE SERVICE GUIDE V1.2

Virgin Orbit, LLC / Version 1.2 / July 2019

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 customer brochure is a working document, and as such is revised and updated periodically. Virgin Orbit encourage readers to visit virginorbit.com frequently to ensure they have the latest revision.