Armstrong Siddeley Stentor
The Armstrong Siddeley Stentor, latterly Bristol Siddeley BSSt.1 Stentor, was a two-chamber rocket engine used to power the Blue Steel stand-off missile carried by Britain's V bomber force. One chamber was used for initial boost, then, 29 seconds after release the boost chamber was shut down and a smaller cruise chamber was used for most of the flight.[1][2][3]
Design and development
It was fuelled by hydrogen peroxide / kerosene propellant chemistry.
The engine incorporated an integral tubular mounting frame which was attached by six lugs to the rear bulkhead of the missile airframe, the complete engine being enclosed in a tube-shaped fairing with the nozzles at the rear.
Applications
Engines on display
Preserved Stentor engines are on display at the following museums:
Specifications
General characteristics
- Type: Liquid-propellant rocket engine
- Length: 58 in (147 cm)
- Diameter: 38 in wide, 44.5 in high (96 x 113 cm)
- Dry weight: 747 lb (339 kg) including oil and nitrogen
- Fuel: Kerosene
- Oxidiser: Hydrogen peroxide
Components
Performance
- Thrust: Large boost chamber rated at 24,000lbf (106.8kN)
smaller cruise chamber rated at 6,000lbf (26.7kN)
- Burn time:
See also
- Related development
- Related lists
References
|
|---|
| | Piston engines | |
|---|
| | Turbojets | |
|---|
| | Turboprops | |
|---|
| | Rocket engines | |
|---|
|
|
|---|
| | Liquid fuel | | US | |
|---|
| EU | |
|---|
| Russia | |
|---|
| Japan | |
|---|
| China | |
|---|
| India | |
|---|
|
|---|
| | |
|---|
| Semi-cryogenic
(Other) | |
|---|
| | |
|---|
| |
|---|
| | Solid fuel | US | |
|---|
| Japan | |
|---|
| EU | |
|---|
| India | |
|---|
| China | |
|---|
| Israel | |
|---|
|
|---|
| |
|
