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
Special Projects
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.
Stratolaunch is a mobile launch system with three primary components.
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.
Objectives:
Twenty-ninth full scale hot-fire. Test of flight-design RM2. Continued evaluation of all systems and components: - Extended burn duration in flight configuration - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
SNC successfully fired the flight motor for SpaceShipTwo at its test facility in Poway, testing an extended burn and further advancing the program towards full spaceflight later this year. This test built upon excellent results achieved in SpaceShipTwo's first supersonic, rocket-powered flight with motor of the same design. All objectives completed.
Objectives:
Perform hot-fire of off-nominal, non-flight configuration motor at Scaled's test facility. - Safety systems evaluation - Test stand evaluation - Data Acquisition system evaluation - Rocket Motor Controller performance - Pressurization System Controller performance - Rocket system performance - Valve / Injector / Igniter evaluation - Fuel formulation evaluation - CTN structural evaluation
Results:
Firing at Mojave test site by Scaled Composites of a non-flight experimental rocket motor in which flaws had been intentionally introduced to improve knowledge of different design components. Tested experimental grain to destruction. This unique test, which was necessary to perform during the test program, successfully collected data for several key safety systems.
Objectives:
Twenty-seventh full scale flight design RM2 hot-fire. Continued evaluation of all systems and components:
- Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Twenty-sixth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Twenty-fifth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Twenty-fourth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Twenty-third full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Twenty-second full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives complete.
Objectives:
Twenty-first full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Perform third full scale rocket motor hot-fire at Scaled's test facility: - Test stand evaluation - Data Acquisition system evaluation - Rocket Motor Controller performance - Pressurization System Controller performance - Rocket system performance - Valve / Injector / Igniter evaluation - Fuel formulation evaluation - CTN structural evaluation
Results:
Third full scale firing of a rocket motor at Scaled’s test site under full control of the spaceship’s Rocket Motor Controller (RMC). All objectives achieved.
Objectives:
Nineteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Eighteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
Objectives:
Seventeenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 45 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
Objectives:
Perform second full scale rocket motor hot-fire at Scaled's test facility Test stand evaluation Data Acquisition system evaluation Rocket Motor Controller performance Pressurization System Controller performance Rocket system performance Valve / Injector / Igniter evaluation Fuel formulation evaluation CTN structural evaluation
Results:
Second full scale firing of a rocket motor at Scaled’s test site under full control of the spaceship’s Rocket Motor Controller (RMC). All objectives achieved.
Objectives:
Fifteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 45 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
Objectives:
Fourteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 55 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
Objectives:
Thirteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 55 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
Objectives:
Perform first full scale rocket motor hot-fire at Scaled's test facility Test stand evaluation Data Acquisition system evaluation Rocket Motor Controller performance Pressurization System Controller performance Rocket system performance Valve / Injector / Igniter evaluation Fuel formulation evaluation CTN structural evaluation
Results:
First full scale firing of a rocket motor at Scaled’s test site under full control of the spaceship’s Rocket Motor Controller (RMC). All objectives achieved. The difference between Scaled’s site and SNC’s site at Lakeside is the focus on using SS2 flight vehicle hardware. These tests provide an end to end test of all the vehicle’s rocket motor systems and additional confidence before committing the vehicle to powered flight test.
Objectives:
Eleventh full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 50 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
Objectives:
Tenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 40 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
Objectives:
Ninth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed full 45 second hot fire as planned. Duration of burn chosen to allow examination of internal core geometry.
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.
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.
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.
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.
Objectives:
Perform fourth full scale flight design RM2 hot-fire - planned flight fuel Perform 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.
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.
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.
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.
| Fire: | 29 | ||
| Date: | 17 May 13 | ||
Objectives:
Twenty-ninth full scale hot-fire. Test of flight-design RM2. Continued evaluation of all systems and components: - Extended burn duration in flight configuration - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
SNC successfully fired the flight motor for SpaceShipTwo at its test facility in Poway, testing an extended burn and further advancing the program towards full spaceflight later this year. This test built upon excellent results achieved in SpaceShipTwo's first supersonic, rocket-powered flight with motor of the same design. All objectives completed.
| Fire: | 28 | ||
| Date: | 17 May 13 | ||
Objectives:
Perform hot-fire of off-nominal, non-flight configuration motor at Scaled's test facility. - Safety systems evaluation - Test stand evaluation - Data Acquisition system evaluation - Rocket Motor Controller performance - Pressurization System Controller performance - Rocket system performance - Valve / Injector / Igniter evaluation - Fuel formulation evaluation - CTN structural evaluation
Results:
Firing at Mojave test site by Scaled Composites of a non-flight experimental rocket motor in which flaws had been intentionally introduced to improve knowledge of different design components. Tested experimental grain to destruction. This unique test, which was necessary to perform during the test program, successfully collected data for several key safety systems.
| Fire: | 27 | ||
| Date: | 30 Mar 13 | ||
Objectives:
Twenty-seventh full scale flight design RM2 hot-fire. Continued evaluation of all systems and components:
- Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 26 | ||
| Date: | 08 Mar 13 | ||
Objectives:
Twenty-sixth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 25 | ||
| Date: | 28 Feb 13 | ||
Objectives:
Twenty-fifth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 24 | ||
| Date: | 24 Jan 13 | ||
Objectives:
Twenty-fourth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 23 | ||
| Date: | 08 Jan 13 | ||
Objectives:
Twenty-third full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 22 | ||
| Date: | 20 Dec 12 | ||
Objectives:
Twenty-second full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives complete.
| Fire: | 21 | ||
| Date: | 14 Dec 12 | ||
Objectives:
Twenty-first full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 20 | ||
| Date: | 06 Dec 12 | ||
Objectives:
Perform third full scale rocket motor hot-fire at Scaled's test facility: - Test stand evaluation - Data Acquisition system evaluation - Rocket Motor Controller performance - Pressurization System Controller performance - Rocket system performance - Valve / Injector / Igniter evaluation - Fuel formulation evaluation - CTN structural evaluation
Results:
Third full scale firing of a rocket motor at Scaled’s test site under full control of the spaceship’s Rocket Motor Controller (RMC). All objectives achieved.
| Fire: | 19 | ||
| Date: | 27 Nov 12 | ||
Objectives:
Nineteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 18 | ||
| Date: | 02 Nov 12 | ||
Objectives:
Eighteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed.
| Fire: | 17 | ||
| Date: | 20 Sep 12 | ||
Objectives:
Seventeenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 45 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
| Fire: | 16 | ||
| Date: | 10 Sep 12 | ||
Objectives:
Perform second full scale rocket motor hot-fire at Scaled's test facility Test stand evaluation Data Acquisition system evaluation Rocket Motor Controller performance Pressurization System Controller performance Rocket system performance Valve / Injector / Igniter evaluation Fuel formulation evaluation CTN structural evaluation
Results:
Second full scale firing of a rocket motor at Scaled’s test site under full control of the spaceship’s Rocket Motor Controller (RMC). All objectives achieved.
| Fire: | 15 | ||
| Date: | 09 Aug 12 | ||
Objectives:
Fifteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 45 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
| Fire: | 14 | ||
| Date: | 12 Jul 12 | ||
Objectives:
Fourteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 55 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
| Fire: | 13 | ||
| Date: | 26 Jun 12 | ||
Objectives:
Thirteenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 55 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
| Fire: | 12 | ||
| Date: | 20 Jun 12 | ||
Objectives:
Perform first full scale rocket motor hot-fire at Scaled's test facility Test stand evaluation Data Acquisition system evaluation Rocket Motor Controller performance Pressurization System Controller performance Rocket system performance Valve / Injector / Igniter evaluation Fuel formulation evaluation CTN structural evaluation
Results:
First full scale firing of a rocket motor at Scaled’s test site under full control of the spaceship’s Rocket Motor Controller (RMC). All objectives achieved. The difference between Scaled’s site and SNC’s site at Lakeside is the focus on using SS2 flight vehicle hardware. These tests provide an end to end test of all the vehicle’s rocket motor systems and additional confidence before committing the vehicle to powered flight test.
| Fire: | 11 | ||
| Date: | 06 Jun 12 | ||
Objectives:
Eleventh full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 50 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
| Fire: | 10 | ||
| Date: | 17 Apr 12 | ||
Objectives:
Tenth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed targeted 40 second hot fire as planned. Duration of burn chosen to allow examination of internal geometry.
| Fire: | 09 | ||
| Date: | 13 Mar 12 | ||
Objectives:
Ninth full scale flight design RM2 hot-fire. Continued evaluation of all systems and components: - Pressurization - Valve/Injector - Fuel formulation and geometry - Nozzle - Structure - Performance
Results:
All objectives completed. Performed full 45 second hot fire as planned. Duration of burn chosen to allow examination of internal core geometry.
| Fire: | 08 | ||
| Date: | 29 Nov 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 Aug 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 Mar 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 Aug 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 Mar 10 | ||
Objectives:
Perform fourth full scale flight design RM2 hot-fire - planned flight fuel Perform 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 Apr 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.
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