Lunar Capability Guide – SCM 2008‐005A Page | I

Lunar Capability Guide – SCM 2008‐005a Page | i

Table of Contents

1 Introduction ...... 1 2 Launch Overview ...... 1 3 Launch Vehicles ...... 2 3.1 Falcon 1 ...... 2 3.1.1 Capability ...... 2 3.1.2 Availability ...... 3 3.1.3 ATP to Launch ...... 3 3.1.4 Price ...... 3 3.1.5 Fairing ...... 3 3.2 Falcon 1e ...... 4 3.2.1 Capability ...... 4 3.2.2 Availability ...... 6 3.2.3 ATP to Launch ...... 6 3.2.4 Price ...... 6 3.2.5 Fairing ...... 6 3.3 Falcon 9 ...... 7 3.3.1 Capability ...... 7 3.3.2 Availability ...... 7 3.3.3 ATP to Launch ...... 7 3.3.4 Price ...... 8 3.3.5 Fairing ...... 8 4 Launch Facilities ...... 9 5 Services Overview ...... 10 5.1 Standard Services ...... 10 5.2 Non‐standard Services ...... 10

1 Introduction A new challenge beyond low Earth orbit has arisen – a return to the Moon. SpaceX is committed to revolutionizing access to space by providing low cost, reliable launch services in an effort to be the catalyst for future development and exploration of space. As innovative concepts driving space‐related commerce mature, this guide was developed to be a lunar planning handbook for SpaceX launch services to the Moon and is a supplement to the launch vehicle‐specific Users Guides available at SpaceX.com.

SpaceX currently offers three launch vehicles: Falcon 1, Falcon 1e, and Falcon 9, each having certain cost advantages and capabilities. Outlined in this guide are each vehicle’s performance, availability, and specifications for Trans Lunar flight. Please refer to the specific launch vehicle Users Guides for complete launch environments and system detail. 2 Launch Overview There are numerous ways to utilize SpaceX launch services for lunar missions. Depending on the program requirements, several variables such as time, mass, complexity, and cost can be traded to provide different options for a successful lunar mission. If time is a driving force, spacecraft can be placed directly into a lunar transfer orbit aboard the Falcon 9 launch vehicle, arriving at the lunar injection point within 2‐3 days. However, if budget is of primary concern, the Falcon 1/Falcon 1e can be employed for injection into a Highly Elliptical Orbit (HEO). A kick motor on the spacecraft can then provide the necessary delta‐v to complete the Trans Lunar trajectory. Other low‐energy transfers utilizing weak stability boundaries can also be employed if time is not a driving requirement.

3 Launch Vehicles 3.1 Falcon 1 The Falcon 1 launch vehicle offers the lowest price launch on the market, and it has been the pathfinder for all subsequent SpaceX launch vehicles. The Falcon 1 User’s Guide outlines the environments and structural characteristics of the launch vehicle in detail and is available for download on SpaceX.com.

3.1.1 Capability The Falcon 1 launch vehicle is capable of injecting up to 420 kg (924 lbm) into a 185 km circular orbit. Additional trajectories include a range of highly elliptical orbits for proportionally less payload up to 8000 km as shown in Figure 3‐1. By employing a Falcon 1, a lunar‐bound spacecraft equipped with a kick‐motor is capable of reaching sufficient velocities for Trans Lunar Injection (TLI). See Figure 3‐2 for performance to LEO at different altitudes.

(lb) (kg)

Mass Mass

Payload Payload

Figure 3‐1: Falcon 1 Highly Elliptical Orbit Performance, based on a 185km circular orbit launched due east (9.1 deg) from SpaceX's Kwajalein Launch Facility

(kg) (lb)

Mass Mass

Payload Payload

Figure 3‐2: Falcon 1 LEO Performance, two‐burn injection

3.1.2 Availability The standard Falcon 1 is currently available until mid 2010, when the upgraded Falcon 1e will become the vehicle for transporting small payloads.

3.1.3 ATP to Launch SpaceX requires authority‐to‐proceed (ATP) 9‐12 months prior to launch, although accelerated timelines may be possible for missions if no changes to the launch vehicle baseline design are required.

3.1.4 Price The base price for a Falcon 1 launch is $7.9M (in Jan 2008 US dollars), which includes standard payload processing and range fees. Standard and non‐ standard services are outlined in Section 5. Additional customer specific payload options and services will be priced as needed.

3.1.5 Fairing The dynamic envelope available for payloads inside the standard Falcon 1 fairing is illustrated in Figure 3‐3.

Figure 3‐3: Falcon 1 dynamic envelope with standard fairing, meters [inches]

3.2 Falcon 1e The enhanced Falcon 1, or Falcon 1e, is the next generation of the Falcon 1 launch vehicle and offers additional capability enabled by an upgraded Merlin engine, elongated first stage tank, and an expanded fairing. The following information is based upon the planned vehicle configuration and its anticipated performance.

3.2.1 Capability Falcon 1e is capable of putting just over 1000 kg (2200 lbs) into LEO at 185km circular orbit and proportionally smaller spacecraft into a highly elliptical orbit of altitudes up to 25,000 km. After LEO or HEO insertion, a kick motor on the spacecraft could then provide the necessary delta‐v to complete a Trans Lunar trajectory and ultimately put a payload onto the lunar surface.

(lb)

(kg)

Mass

Payload Payload

Figure 3‐4: Falcon 1e Highly Elliptical Orbit Performance, based on a 185km circular orbit launched due east (9.1 deg) from SpaceX's Kwajalein Launch Facility

Figure 3‐5: Falcon 1 and Falcon 1e Upgrade [Units: Feet]

(kg) (lb)

Mass Mass

Payload Payload

Figure 3‐6: Falcon 1e LEO Performance, two‐burn injection

(lb) (kg)

Mass Mass

Payload Payload

Figure 3‐7: Falcon 1e Escape Energy Performance, based on launch due east (9.1 deg) from SpaceX's Kwajalein Launch Facility

3.2.2 Availability Falcon 1e launch services are currently being contracted with capacity available beginning in mid‐2010.

3.2.3 ATP to Launch SpaceX requires authority‐to‐proceed (ATP) 9‐12 months prior to launch, although accelerated timelines may be possible for missions if no changes to the launch vehicle baseline design are required.

3.2.4 Price The base price for a Falcon 1e launch is $9.1M (in Jan 2008 US dollars), which includes standard payload processing and range fees. Standard and non‐standard services are outlined in Section 5. Additional customer specific payload options and services will be priced as needed.

3.2.5 Fairing The dynamic envelope available for payloads inside the standard SpaceX Falcon 1e fairing is illustrated in Figure 3‐8.

Figure 3‐8: Falcon 1e dynamic

envelope with standard fairing, meters [inches]

3.3 Falcon 9 The Falcon 9 launch vehicle design builds on the technologies and expertise acquired during development and commercial deployment of SpaceX’s Falcon 1 launch vehicle. It offers significantly greater lifting power and therefore provides the capability for a direct Trans Lunar Injection insertion eliminating the need for a kick motor.

3.3.1 Capability When launched from Cape Canaveral, Falcon 9 is capable of inserting roughly 1925 kg (4240lbm) into TLI based upon a 48‐hour direct transfer and the characteristic energies illustrated in Figure 3‐10.

Figure 3‐10: Falcon 9 Escape Energy Performance based on launch from SpaceX's Cape Canaveral Launch Facility (28.5 deg).

NOTE: Data reflects the Falcon 9 Block 1 design, applicable for flights prior to mid‐2010. Please inquire for later flights.

3.3.2 Availability SpaceX is currently contracting Falcon 9 for launches beginning in 2010, as the Falcon 9 manifest is currently booked to capacity through the end Figure 3‐9: The of 2009. Falcon 9 Launch Vehicle with 5.2 m 3.3.3 ATP to Launch fairing SpaceX requires authority‐to‐proceed (ATP) 12‐18 months prior to

launch, although accelerated timelines may be possible for missions if no changes to the launch vehicle baseline design are required.

3.3.4 Price The base price for a Falcon 9 launch to LEO is $36.75M (in Jan 2008 US dollars), which includes standard payload processing and range fees. Standard and non‐standard services are outlined in Section 5. Additional customer specific payload options and services will be priced as needed. Missions to Trans Lunar Injection will have an additional charge of $10M since the second stage is non‐recoverable. Further customer specific payload options will be priced as needed.

3.3.5 Fairing The dynamic envelope available for payloads inside the standard Falcon 9 ‐ 5.2 meter fairing is illustrated in Figure 3‐1.

Figure 3-1: Falcon 9 Dynamic Fairing Envelope, meters [inches]

4 Launch Facilities SpaceX currently supports lunar‐bound launches from both the facilities at the Kwajalein Atoll (9.1˚ inclination) and Cape Canaveral (28.5˚ inclination) for the Falcon 1/1e and Falcon 9, respectively. See Figure 4‐1 for approximate locations. The Falcon 1 launch facilities are situated on Omelek Island, part of the Ronald Reagan Ballistic Missile Defense Test Site (RTS) at United States Army Kwajalein Atoll (USAKA). Additional information regarding facility accommodations, payload processing and integration capabilities, and standard services are provided in the Users Guides available at SpaceX.com.

Cape Canaveral 28.5˚

Kwajalein Atoll 9.1˚

Equator

Figure 4-1: SpaceX Launch Facilities at Kwajalein Atoll and Cape Canaveral

5 Services Overview 5.1 Standard Services SpaceX provides the following services as part of its standard launch service: • Launching the spacecraft into the specified orbit within the specified environmental constraints • Personnel, services, hardware, equipment, documentation, reviews, analyses and facilities necessary to support mission planning, launcher production, mission and payload integration and launch • A single flight set of electrical connectors • Class 100K clean room integration space for the spacecraft prior to the scheduled launch date on the launch range with additional floor space for GSE and personnel • Processing, integration and encapsulation of the payload within the fairing, testing of electrical and signal interfaces with the spacecraft at the launch site • Conditioned air into the payload fairing • A simple, marmon clamp separation system • Up to two access doors in the payload fairing for Falcon 1/1e and up to three access doors for Falcon 9 • A Mission Simulation Test exercising operational readiness, vehicle equipment and ground systems • A Mission Dress Rehearsal similar to the mission simulation test for key launch team members • Provision of all range and safety interfaces including requirements document templates for the spacecraft provider to complete • Facilitate the range and range safety integration process • Perform a collision avoidance maneuver (as required) • Provision of post‐flight analysis to verify successful separation from the launch vehicle and identify the spacecraft orbit • Provision of post‐flight launch services, including delivery of the Post Flight Report, which shall include (but not be limited to) payload separation confirmation, ephemeris, payload environment, significant events and anomalies • Generation of all mission required licensing including FAA and State Department, with input from the payload customer 5.2 Non‐standard Services The following are non standard services that may be required for the lunar missions. Please note that it may be possible to provide these and others on a case by case basis. • Custom payload separation system • Hazardous fueling and residual fuel disposal • Solid rocket motor handling • Modifying the location of the fairing access door(s) • Additional fairing access door(s)

• GN2 purge • Class 10K clean room processing • Additional accommodations for spacecraft processing/fueling • Non‐standard electrical interface services • Spin balancing and enhanced spacecraft spin up prior to separation