ARCA
ARCA
text/css

 

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.

 

text/css

Haas 2B technical data

 

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

 

text/css

 

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:

 

Length
11.3 ft
3.43 m
Diameter
7.92 ft
2.4 m
Launch mass
5,500 lb
2,500 kg

 

text/css

 

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.

 

text/css

 

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

 

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

 

text/css

 

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:


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

 

Technology

HAAS 2CA
DEMONSTRATOR 3
HAAS 2B
ARCABOARD


Programs

IAR-111 EXCELSIOR
HELEN
STABILO
DEMONSTRATOR 2B
EXOMARS

Support

ARCABOARD FAQ
ARCABOARD WARRANTY

Info

ABOUT US

LATEST NEWS
NEWS ARCHIVE
NEWSLETTER
CONTACT

 


© 2017 ARCA SPACE CORPORATION. All rights reserved.