Haas 2B Haas 2B is a single stage suborbital manned rocket. It has the capability to transport a crew of five into suborbital flight, inside a manned capsule. Haas 2B is designed to compete on the suborbital space tourism market. The rocket is built primarily of composite materials and the liquid oxygen tank is made of 304L stainless steel. At the rear end is the Executor 2 rocket engine with a sea level thrust of 50,660 lbf (23,000 kgf). The engine is fueled with liquid oxygen and kerosene. On top of the rocket engine is the composite kerosene tank. The composite pressurization sphere is placed in the middle of the rocket airframe. The liquid oxygen tank is at the top of the booster. The service module is located just beneath the manned capsule containing five Venator engines. Four lateral engines can be used as an escape system, while the central engine can be utilized as a second stage motor to increase the maximum altitude for the capsule, after the booster separation.
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Haas 2B technical data
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Length |
53.8 ft |
16.3 m |
Diameter |
7.92 ft |
2.4 m |
Empty mass |
8,855 lb |
4,020 kg |
Launch mass |
31,100 lb |
14,120 kg |
Sea level thrust |
50,660 lb |
23,000 kgf |
Max. payload |
5,730 lb |
2,600 kg |
Time to burnout | 82 s |
82 s |
Burnout altitude | 125,400 ft |
38,000 m |
Time to max. altitude | 244 s |
244 s |
Max. altitude |
528,000 ft |
160,000 m |
Crew |
1+4 |
1+4 |
Crew capsule The five person capsule is made entirely of composite materials. The access of the crew is made through the top hatch. The capsule is equipped with two deployable parachutes, one as a reserve. The outside view is ensured by eleven portholes. The capsule attitude after booster separation is made with the use of the nitrogen feed RCS system. Crew capsule technical data:
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Length |
11.3 ft |
3.43 m |
Diameter |
7.92 ft |
2.4 m |
Launch mass |
5,500 lb |
2,500 kg |
Executor 2 rocket engine The pressure fed Executor 2 rocket engine is specially designed for the Haas 2B suborbital rocket. It was designed as a moderate performance, highly reliable engine for manned suborbital applications. The combustion chamber and the nozzle are built from composite materials comprising of two layers. The internal layer is made of silica fiber and phenolic resin, and the external one is made of carbon fiber and epoxy resin. The phenolic resin reinforced with silica fiber pyrolyzes endothermally in the combustion chamber walls, releasing gases like oxygen and hydrogen, leaving a local carbon matrix. The gases spread through the carbon matrix and reach the internal surface of the wall where they meet the hot combustion gases and act as a cooling agent. Furthermore, the engine is equipped with a cooling system that injects on the internal wall 10 percent of the total kerosene mass.
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The main engine valves are made of 304L type stainless steel and are pneumatically driven, allowing engine throttling. The engine injector and the liquid oxygen intake pipes are made of 304 L type steel and the kerosene intake pipe is made of composite materials. The engine is not gimballed, but the rocket attitude and trajectory are controlled via four composite vanes. Executor 2 rocket engine, technical data and performances
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Max. diameter | 3.23 ft |
0.98 m |
Length | 7.2 ft |
2.2 m |
Weight | 550 lb |
250 kg |
Fuel | LOX + kerosene |
LOX + kerosene |
Flow rate | 264 lb/sec |
120 kg/sec |
Sea level thrust | 50,660 lb |
23,000 kgf |
Vacuum thrust | 57,300 lb |
26,000 kgf |
Impulse (vacuum) | 312 sec |
312 sec |
Service Module Venator rocket engine The Service Module (SM) is powered by the Venator, pressure-fed rocket engine, that has a vacuum thrust of 5,500 lbf (2,500 kgf). The Venator rocket engine has no vanes on the main pipes. It uses instead burst disks, between the tanks and the engine. The SM tanks are pressurized to 2 bars at lift-off and after the booster burn-out, the tanks will be pressurized to 16 bars. At that pressure the disks will burst and the fuel will flow through the engine. The same procedure is applied when using the Venator engine for the abort procedure. Using burst disks, the mass of the SM will decrease while the reliability will increase. The engine injector and the liquid oxygen intake pipes are made of 304 L type steel and the kerosene intake pipe is made of composite materials. Venator rocket engine, technical data:
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Max. diameter | 2.64 ft |
0.8 m |
Length | 4.62 ft |
1.4 m |
Weight | 145 lb |
66 kg |
Fuel | LOX + kerosene |
LOX + kerosene |
Flow rate | 17.8 lb/sec |
8.1 kg/sec |
Chamber pressure | 145 psi |
10 bars |
Vacuum thrust | 5,500 lb |
2,500 kgf |
Impulse (vacuum) | 317 sec |
317 sec |
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