Scaled Composites Conducts First SpaceShipTwo Engine Test Firing in 10 Months

SS2 and VMS Eve in hangar 2

Scaled Composites conducted a fourth test of the engine for its SpaceShipTwo vehicle on March 30, according to a log on the company’s website. The “full scale flight design RM2 hot-fire” was the first test done since May 20 of last year – a 10-month gap.

The test log says the firing was a success:

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.

The first three hot fires had been done between April 20 and May 20 of last year. Scaled Composites is working with Sierra Nevada Corporation, which is overseeing the engine tests at a facility in Southern California.

Virgin Galactic released a video of the tests at the end of last May. They have been largely silent since that time. The long gap in testing has spurred rumors that engineers are dealing with serious performance problems with the engine.

Virgin Galactic officials insist that the program is going smoothly, and that SpaceShipTwo tests flights with the engine are set to begin in early 2011.

“We do not share data on the rocket motor for a variety of reasons, including ITAR [U.S export law], but suffice to say we have done several tests and the latest at full power, the program is progressing smoothly,” said Virgin Galactic President Will Whitehorn. “And we expect to start engine tests with the actual vehicle in the air next year leading to experimental flights in the upper atmosphere and then into space.”

Scaled Composites Engine Test Log

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.