1. SpaceShipOne Lance Erickson MSA 603

2. SpaceShipOne Suborbital Project Introduction Mission & Objectives Flight Operations Flight Vehicle & Characteristics Launch Vehicle Spacecraft Costs Summary References

3. SpaceShipOne and White Knight

4. Introduction

5. SpaceShipOne was the first successful suborbital civil space flight vehicle launched into space Unique, low-cost, multi-flight, ballistic reentry, composite vehicle Unique, low cost launcher – White Knight Inaugural flight into space was made in in 2004 SpaceShipOne was a proof-of-concept project and no commercial operations were planned by Scaled Composites

6. SpaceShipOne suborbital vehicle

7. Basic Operations Air launched from 50,000’ (White Knight) 1 pilot, 1 passenger Hybrid rocket engine Composite construction 285 KEAS maximum speed for ballistic flight Flight trajectory to 100 km altitude Manual control until reentry Conventional (runway) landing

8. Objectives

9. SpaceShipOne was designed as a multiple-launch suborbital manned vehicle to conform to the X-Prize requirements $10M award to the first to fly to 100 km & return Had to be repeated within 3 weeks Civilian passenger required Air launch for lowest cost

10. SpaceShipOne attached under White Knight Note similar cockpit size & shape Useful for simplified pilot training, and aerodynamic & operational tests

11. Flight Operations

12. SpaceShipOne (SSO) is launched from the White Knight carrier The White Knight is a two-engine turbojet high-lift, high altitude carrier and launch aircraft Separation (launch) at 50,000’ SSO then goes through an automated pitch up maneuver and rocket ignition Pitch up further to ~80 o Reentry after burnout and coast ~ 3.5 min in zero-g Attitude controlled with pressurized air thrusters until reentry

13. Flight Profile

14. Flight Operations (cont.) Reentry temperature maximum ~ 1,200 o F Reentry temperature maximum ~ 1,200 o F Maximum loading 5 g during reentry (4 g for more than 20 sec) Maximum loading 5 g during reentry (4 g for more than 20 sec) Stability provided during critical reentry interface by “shuttlecock” rear aerofoil Stability provided during critical reentry interface by “shuttlecock” rear aerofoil Increased drag from deployed shuttlecock (Feather) reduces reentry loads: Increased drag from deployed shuttlecock (Feather) reduces reentry loads: Reduces maximum speed to Mach 3.3 (Space Shuttle ~ Mach 25) Reduces maximum speed to Mach 3.3 (Space Shuttle ~ Mach 25) Maximum g loading ~ 4g Maximum g loading ~ 4g Reduced thermal loading and maximum temperature Reduced thermal loading and maximum temperature

15. Flight Operations (cont.) Electrically-operated aerodynamic controls employed after initial entry Automated reentry & approach Feather structure includes rudders, elevons and trim stab controls Feather structure extension & retraction by pneumatic controls Terminal velocity ~ 60 KEAS (knots, equivalent airspeed) 1 knot = 1.6 mph

16. Shuttlecock Feather Extended

17. Flight Operations (cont.) Feather empenage retracted after reentry to reduce stress Normal glider control and characteristics from Feather retraction to landing Approach ~ 110 Knots Touchdown ~ 70 Knots Landing made on rear main gear wheels and skid front gear

18. Launch Vehicle – White Knight

19. The White Knight is a twin turtbojet powered carrier aircraft used to lift spacecraft to 50,000’ to reduce the space vehicle’s propulsion, size & cost J85-GE-5 with afterburner, rated at 3,850 lb f Unique design for unique mission Used also for aerodynamic testing of supersonic SpaceShipOne Wind tunnel testing expensive 82’ wingspan Vne = 160 KEAS (Vne = never exceed velocity)

20. White Knight and SpaceShipOne

21. White Knight in flight

22. SSO Spacecraft

23. Spacecraft Composite structure with Nomex core Designed to withstand supersonic reentry and Feather deployment High temperatures reduced by high-drag, reduced reentry velocity configuration Stability during reentry provided by shuttlecock Feather Entry attitude can be almost any angle Retracted Feather also provides lift for unpowered glide to landing

24. Diagram of SpaceShipOne

26. Spacecraft (cont.) Primary systems Structure Propulsion Thermal control Attitude & aerodynamic control Life support Guidance, navigation & control Landing gear

27. Spacecraft (cont.) Structure Monocoque structure made of composite Carbon-fiber/epoxy honeycomb Nomex core Nomex is a fire-resistant meta-aramid polymer material related to nylon Ablation material on 25% of highest temp surface Fiberglass is used in the rear hinge region for antenna transmission transparency Escape provided by nose drop & parachute

28. Spacecraft (cont.) Structure Empty weight: 2,640 lb (1,200 kg) Loaded weight: 7,920 lb (3,600 kg)

29. Spacecraft (cont.) Propulsion Hybrid rocket engine Solid fuel core Nitrous oxide oxidizer stored in forward tank as liquid 65-second burn to reach Mach 3.6 (240 KEAS, 2,170 mph, 3,518 km/h) Throttleable, and can be shut down and restarted Low cost rocket engine was developed & tested by a separate company - SpaceDev

30. Hybrid rocket engine Solid fuel - butylated rubber Oxidizer – liquid nitrous oxide

31. SSO hybrid rocket engine test (Mojave site)

32. Spacecraft (cont.) Thermal control Maximum temperature ~1,200 o F Maximum temp regions covered with 0.035” proprietary ablative material Can be recoated easily for subsequent flights Phenolic resin covers other intermediate- heat areas

33. Spacecraft (cont.) Attitude control Compressed gas thrusters for use above the atmosphere Pitch & yaw thrusters forward Roll thrusters outboard on Feather structure Aerodynamic control surfaces for boost, reentry and glide phases Elevons (outboard) for pitch & roll control Twin, split rudders (outboard) for yaw control Upper rudder section used for subsonic flight Lower rudder section used for supersonic flight Trim stabilizers

34. Spacecraft (cont.) Life support Atmosphere provided from compressed gas tanks on the SSO after launch Atmosphere provided by White Knight bleed air while attached Humidity removal by fan and stored dessicant CO 2 removal by “Sodiabsorb” Emergency escape provided by cabin drop section and/or left cabin door (used for vent during taxi) and crew parachutes Parachutes used only for emergency bailout

35. Spacecraft (cont.) Guidance, Navigation & Control Hand flown during ascent and weightlessness Onboard computer control (autopilot) during reentry Avionics included GPS navigation Dual pitot tube air data provided

36. Spacecraft (cont.) Landing gear Deployable dual main gear Deployable front nose skid Touchdown ~ 60 Knots

37. Cost Estimate

38. Costs Development & production ~$20 M Individual flight (projected) ~ $80,000 Certification (FAA/NASA) ~ $80-$100 M Funded by Paul Allen (Microsoft)

39. Summary

40. The SpaceShipOne program proved the ability to fly civilians on suborbital space flights safely, simply and inexpensively The SpaceShipOne program proved the ability to fly civilians on suborbital space flights safely, simply and inexpensively Designed to also satisfy X-Prize requirements Designed to also satisfy X-Prize requirements White Knight test flights included 30 by April, 2003 White Knight test flights included 30 by April, 2003 First SSO flight dropped from 48,000’ First SSO flight dropped from 48,000’ First space flight 2004 First space flight 2004 2nd X-Prize flight Oct 4, 2004 2nd X-Prize flight Oct 4, 2004

41. Summary (cont.) Civil flights being developed by Virgin Atlantic director (Richard Branson) Space operation certification required to fly public passengers Both vehicles developed by Scaled Composites (Burt Rutan)

42. Post-flight celebration (left to right) Peter Diamandis (X-Prize), Paul Allen (primary sponsor), Burt Rutan (designer), Brian Binnie (pilot)

43. Postscript - SpaceShipTwo

44. Diagram of SpaceShipOne

45. SpaceShipTwo SpaceShipTwo (SS2) is under development as a suborbital spaceplane for carrying space tourists Development and operation by Sir Richard Branson's Virgin Galactic enterprise Virgin Galactic spaceline plans to operate a fleet of five of these craft in passenger-carrying private spaceflight service starting no earlier than 2011 Ticket costs are expected to be $200,000-$250,000 Capacity: 2 crew Six passengers

46. References: Aviation Week & Space Technology, April 21, 2003 Scaled Composites-Virgin Atlantic http://www.scaled.com/projects/tierone/092704_scaled_http://www.scaled.com/projects/tierone/092704_scaled_paul_alle n_virgin_galactic.htm