Briggs FXG Vancoollins
Length: 52 metres (provisional due to variations in nose-cone length)
Wingspan: 31 metres (provisional due to variations in wingspan)
Height: 12 metres (provisional due to tail height and number of tailplanes)
Initial; 5 Perm engine company (ex-Solovyev) D-30F6 afterburning turbo-fans with 34,000 lbs thrust per engine total 77.2 tonnes of thrust
Alternate power-plants: Lyulka AL-31F afterburning turbo-fans rated at 12,500 kgs (27,562 lbs.) thrust each with afterburning total 62.5 tonnes of thrust if the Perm engines are not available. If the Lyulka engines are also not available, 6 engines of aftermarket military types such as Pratt & Whitney F-100 will be sort.
Hypersonic development program
A single hypersonic prototype engine is anticipated to produce greater than fifty tonnes of thrust. Two engines will be lifted by the FXG during later test flights and comparitive trials.
Early test flights will use one or two rocket motor(s) to accelerate the aircraft from Mach 2 to a sustained Mach 7.4 for 1-2 minutes. These first flights will form primarily envelop, airframe and power plant dynamic testing
Hypersonic engine prototype testing
Later tests: 2 hypersonic engines with coupled inlets and 1 or 2 hypersonic engine + one rocket engine for low orbital flights and HYT test parameters
Empty equipped weight (with 5 Perm engine company engines: excluding the hypersonic engine(s)) 33 tonnes
Thrust to weight ratio (earlier test flights): 0.96:1
MTOW thrust to weight ratio (equipped with two 30 tonne hypersonic engine prototypes at zero thrust***): 0.48:1
***from hypersonic engines
Normal take-off weight: 80 tonnes
Maximum take-off weight: 160 tonnes
Payload allows for additional weight of fuel and hypersonic development engines of up to 30 tonnes each: engines will be developed individually though two different types may be flown simultaneously.
Maximum fuel: up to 75 tonnes
Normal fuel: 46 tonnes - 26 tonnes for hypersonic flight (including cryo-fuels, such as LOX and H), 20 tonnes for ascent, descent and reserves
Number to be built: 4
Crew: 1 -2
Expected range at 150,000 ft and Mach 7.4: normal fuel 9,000 km
Expected ceiling 200,000 feet (normal)
Up to 600 km orbit (with rocket engine – J2000 HYT test programme).
Maximum speed limited to Mach 8.0 during Neecenow development
Hypersonic engine V-max will be established after engine certification for the J2000 programme
MOMN configuration dependent; up to Mach 25
Take-off distance 1600 metres (variation depending on wing and fuselage design)
Landing distance 1900 metres at MTOW without reverse thrust (variation depending on wing and fuselage design)
G-limits +8.0 -5.0G
Hypersonic engine program: Briggs
Briggs will be building up to 8 different hypersonic engine prototypes for testing and evaluation: this may include two of more examples of the same power plant. The Aceson budget gives $800 million to the FXG Vancoollins program for engine prototyping and development.