WhiteKnightTwo

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

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

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

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.

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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: 15
Date: 9 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: 6 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
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 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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