Founded in 1982 by Burt Rutan, Scaled has broad experience in air vehicle design, tooling and manufacturing, specialty composite structure design, analysis and fabrication, and developmental flight tests of air and space vehicles.
Founder/Chairman Emeritus
Model 97 is a two-place, side-by-side airplane of the 300 lb empty weight class. It has a slightly swept-back canard forward and swept back wings with winglets at the tips.
A subscale version of an eleven-place, twin turboprop, high-performance business aircraft developed for Beech Aircraft Corporation.
The Model 133-4.62 ATTT proof-of-concept demonstrator is a 62% scaled version of an airplane designed to challenging STOL and long range requirements.
The all-composite Triumph, an 8,500 lb, pressurized 8-place business aircraft, was designed around the brand-new, never flown, Williams FJ-44 turbofan engine.
Scaled did the structural design, tooling, fabrication, and static testing of an 85 ft span and a 108 ft span rigid sail/airfoil for the America’s Cup Challenge Race.
The ARES, Scaled Model 151, was designed initially in response to a U.S. Army request for a Low Cost Battlefield Attack Aircraft (LCBAA).
The Advanced Engineering Staff of General Motors designed a technology demonstration vehicle called the Ultralite, an automobile with interior room capable of seating four full size adults, and with excellent visibility, handling, performance, emissions and fuel consumption.
The Raptor Demonstrator high-altitude, long endurance, unmanned aerial vehicle (UAV) program was conducted under a contract from Lawrence Livermore National Laboratory to Scaled Composites, LLC.
In early 1993, Jim Rice and Tom Stark of the fledgling VisionAire Corporation visited Scaled with conceptual designs for a new single-engine business jet.
Walled Lake, Michigan, June 23, 1997 -- Williams International today announced that its all-composite, turbofan- powered "V-JET II" light aircraft is on schedule for its July 31 fly-in and follow-on demonstration flights and exhibition at the Experimental Aircraft Association (EAA) convention at Oshkosh, July 30 to August 5, 1997.
Proteus is a twin-turbofan, high-altitude, multi-mission aircraft powered by Williams International FJ44-2E engines.
The Model 309 is a proof-of-concept aircraft built for Adam Aircraft Industries.
The GlobalFlyer is a single seat, turbofan powered airplane designed to fly around the world nonstop, unrefueled, with a solo pilot.
SpaceShipOne, the first private manned spacecraft, is a three-place, high-altitude research rocket.
White Knight is a three-place, high-altitude, flexible and capable research aircraft.
The Model 326 aircraft (or Pegasus X-47A) is an unmanned aerial vehicle built for Northrop Grumman.
SpaceShipTwo will be powered by a unique hybrid rocket motor, which is currently under development.
WhiteKnightTwo, or Eve, is the mothership and launch platform for SpaceShipTwo.
Firebird is an optionally-piloted intelligence-gathering aircraft system.
BiPod is a hybrid gasoline-electric roadable aircraft.
BiPod
Conceived as a rapid, low-cost electric test-bed using as many commercial off-the-shelf components as possible, BiPod can operate as either a high-performance airplane or as a road commuter vehicle.
SpaceShipTwo
SpaceShipTwo is the prototype for the world's first commercial manned spaceship, destined to take private astronauts into space and paving the way for space transportation.
WhiteKnightTwo
Utilizing an open-architecture design and powered by four Pratt & Whitney turbofans, WhiteKnightTwo provides the high-altitude launch platform for SpaceShipTwo to achieve sub-orbital flight.
Virgin Atlantic GlobalFlyer
This record-breaking, single-place, aviation marvel features two external booms flanking a center pod where the pilot sits, on top of which is the aircraft's powerhouse, a Williams turbofan jet engine.
SpaceShipOne
SpaceShipOne, the first private manned spacecraft, is a three-place, high-altitude research rocket, designed for sub-orbital flights at an altitude of 100 km and powered by a unique hybrid rocket motor.
White Knight
Initially developed to provide a launch platform at 50,000 ft for SpaceShipOne, White Knight is a three-place, high-altitude, flexible and capable research aircraft.
RocketMotorTwo Hot-Fire Test Summaries
Many subscale hot-firings were performed at Scaled Composites, LLC between Jun 05 and April 09 to evaluate several different fuels, igniters, injectors, insulators and nozzle configurations, as well as other components and parameters.
Based on the results of those subscale firings, the Scaled/SNC team chose a full-scale rocket motor system design and began testing in April 2009.
The following list includes summaries of the hot-fire activity of the RocketMotorTwo rockets.
Fire: 08
Date: 29 November 11
Objectives:
Perform eighth full scale flight design RM2 hot-fire
All systems evaluation
Modified pressurization schedule
Fuel formulation evaluation
Nozzle evaluation
Motor structural evaluation
Valve/injector performance evaluation
Results:
All objectives completed. Performed 10 second and then 58 second hot fires.
Fire: 07
Date: 25 August 11
Objectives:
Perform seventh full scale flight design RM2 hot-fire
Continue all systems evaluation
Continue fuel formulation evaluation
Continue nozzle evaluation
Continue motor structural evaluation
Continue valve/injector performance evaluation
Results:
All objectives completed. Performed 55 second, full duration hot-fire, including igniter performance, oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection.
Fire: 06
Date: 24 March 11
Objectives:
Perform sixth full scale flight design RM2 hot-fire
Continue all systems evaluation
Continue fuel formulation evaluation
Continue nozzle evaluation
Continue motor structural evaluation
Continue valve/injector performance evaluation
Results:
All objectives completed. Performed increased duration hot-fire, including igniter performance, oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 05
Date: 11 August 10
Objectives:
Perform fifth full scale flight design RM2 hot-fire
Continue all systems evaluation
Continue fuel formulation evaluation
Continue nozzle evaluation
Continue motor structural evaluation
Continue valve/injector performance evaluation
Results:
All objectives completed. Performed successful increased duration hot-fire, including igniter performance, oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 04
Date: 30 March 10
Objectives:
Perform fourth full scale flight design RM2 hot-fire – planned flight fuel
Performed flight design Rocket System evaluation
Pressurization system evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Valve/injector evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 03
Date: 20 May 09
Objectives:
Perform third full scale RM2 hot-fire with first generation design - same fuel as HF02
Continued Rocket system evaluation
Igniter evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system, igniter performance measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 02
Date: 06 May 09
Objectives:
Perform second full scale RM2 hot-fire with first generation design - different fuel
Continued Rocket system evaluation
Igniter evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system, igniter performance measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels. Preliminary fuel performance in line with predictions.
Fire: 01
Date: 20 April 09
Objectives:
Perform first full scale RM2 hot-fire with first generation design
Test stand evaluation
Rocket system evaluation
Igniter evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system, igniter performance measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection.
Back to SpaceShipTwo Information
Based on the results of those subscale firings, the Scaled/SNC team chose a full-scale rocket motor system design and began testing in April 2009.
The following list includes summaries of the hot-fire activity of the RocketMotorTwo rockets.
Fire: 08
Date: 29 November 11
Objectives:
Perform eighth full scale flight design RM2 hot-fire
All systems evaluation
Modified pressurization schedule
Fuel formulation evaluation
Nozzle evaluation
Motor structural evaluation
Valve/injector performance evaluation
Results:
All objectives completed. Performed 10 second and then 58 second hot fires.
Fire: 07
Date: 25 August 11
Objectives:
Perform seventh full scale flight design RM2 hot-fire
Continue all systems evaluation
Continue fuel formulation evaluation
Continue nozzle evaluation
Continue motor structural evaluation
Continue valve/injector performance evaluation
Results:
All objectives completed. Performed 55 second, full duration hot-fire, including igniter performance, oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection.
Fire: 06
Date: 24 March 11
Objectives:
Perform sixth full scale flight design RM2 hot-fire
Continue all systems evaluation
Continue fuel formulation evaluation
Continue nozzle evaluation
Continue motor structural evaluation
Continue valve/injector performance evaluation
Results:
All objectives completed. Performed increased duration hot-fire, including igniter performance, oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 05
Date: 11 August 10
Objectives:
Perform fifth full scale flight design RM2 hot-fire
Continue all systems evaluation
Continue fuel formulation evaluation
Continue nozzle evaluation
Continue motor structural evaluation
Continue valve/injector performance evaluation
Results:
All objectives completed. Performed successful increased duration hot-fire, including igniter performance, oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 04
Date: 30 March 10
Objectives:
Perform fourth full scale flight design RM2 hot-fire – planned flight fuel
Performed flight design Rocket System evaluation
Pressurization system evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Valve/injector evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 03
Date: 20 May 09
Objectives:
Perform third full scale RM2 hot-fire with first generation design - same fuel as HF02
Continued Rocket system evaluation
Igniter evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system, igniter performance measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels.
Fire: 02
Date: 06 May 09
Objectives:
Perform second full scale RM2 hot-fire with first generation design - different fuel
Continued Rocket system evaluation
Igniter evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system, igniter performance measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection. Determined stability levels. Preliminary fuel performance in line with predictions.
Fire: 01
Date: 20 April 09
Objectives:
Perform first full scale RM2 hot-fire with first generation design
Test stand evaluation
Rocket system evaluation
Igniter evaluation
Data Acquisition system evaluation
Fuel formulation evaluation
Nozzle evaluation
CTN structural evaluation
Results:
All objectives completed. Performed successful hot-fire, including oxidizer flow and pressurization systems, data acquisition system, igniter performance measurements, structural evaluation, nozzle ablation, and fuel regression rate data collection.
Back to SpaceShipTwo Information
