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Vehicle Technical Specification - Part 6

16      PROPULSION JET

[Issue 8; Configuration 10; 10th May 2010]

16.1      Rolls Royce EJ200 Specification

Item Unit Condition Comment
Max. Thrust (wet) kN 90  
Max. Thrust (dry) kN 60  
Fuel Type - Jet A or JP8  
Power Supply Requirement V 28V  
Power Take Off -    
Fuel Usage at Max Thrust (wet) kg/s 4.23 – 4.41 Specific feio.23 – 4. Specific Fuel Consumption 47-49g/kNs with reheat
      Fuel usage = (47*90)/1000 - (49*90)/1000
Fuel Usage at Max Thrust (dry) kg/s 1.26 – 1.38 Specific feio.23 – 4. Specific Fuel Consumption 21-23g/kNs without reheat
      Fuel usage = (21*60)/1000 - (23*60)/1000
Fuel Usage at Idle kg/s 0.25  
Fuel Pressure Bar    
System Mass (dry) kg 1000  
Fuel Mass Required kg 353.43 I 5min idle, 10sec max thrust dry, 43sec max thrust wet, 5min cool down. DOES NOT INCLUDE ULLAGE
Diameter mm 740  
Length mm 4000  

 

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16.2      EJ200 Intake Duct Specifications

Item Unit Target Status
10th May 2010		 Status
Package Freeze		 Status
Drawing Release		 Comment
Intake Area m2 0.28 – 0.38 0.35      
Aspect Ratio - 1.5 – 2.6 2      
Offset Ratio - 0.23 0.23      
Area Ratio -   0.8      
Length mm   3.75      

 

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17      PROPULSION ROCKET

[Issue 8; Configuration 10; 10th May 2010]

17.1      Falcon Hybrid Rocket

Definition Unit Target Status
10th May 2010		 Status
Package Freeze		 Status
Drawing Release		 Comment
Hybrid Rocket Motor
Average Thrust kN 111 111      
Max Thrust kN 133 122      
Total Impulse kN.sec 2230 2230      
Specific Impulse sec 200 200     Hope to increase
Total Propellant Mass kg 1130 1130      
Mixture Ratio (Oxidant:Fuel)   5.25:1 5.25:1      
Initial System Mass kg TBC TBC      
Oxidant Feed Mechanism   Pump Pump Pump    
Oxidant
Oxidant Type - HTP (H2O2) HTP (H2O2) HTP (H2O2)    
Mass kg 963 963     (includes 10-15% ullage to prevent pump running dry)
Volume m3 0.696 0.696      
Tank Mass Fraction   0.85        
Tank Pressure MPa 0.165 0.165      
Density kg/m3 1370 1370      
Flow rate kg/sec 47.6 47.6      
Delivery Pressure MPa 7.58 7.58      
Fuel            
Fuel Type   HTPB HTPB HTPB    
Mass kg 181 181      
Combustion Chamber
Diameter mm 457 457      
Length mm 3.78 3780      
Mass Fraction   TBC TBC      
Catalyst Pack Type           Silver-Plated Nickel Gauze Mk 2

 

17.2      Falcon Monopropellant Rocket

Definition Unit Target Status
1st Mar 2010		 Status
Package Freeze		 Status
Drawing Release		 Comment
Monoprop. Rocket Motor
Average Thrust kN   44.5      
Max Thrust kN          
Total Impulse kN.sec   890      
Specific Impulse sec   117      
Run Duration sec   20      
Initial System Mass kg   TBC      
Propellant
Fuel Type - HTP (H2O2) HTP (H2O2) HTP (H2O2)    
Mass kg   776      
Density Kg/m3   1630      
Volume m3   0.566      
Delivery System -          
Tank Pressure MPa   0.165      
Flow Rate Kg/sec   38.8      
Delivery Pressure MPa   5.52      
Combustion Chamber
Diameter mm   457      
Length mm   707      
Mass kg   155      
Mass Fraction     TBC      
Catalyst Pack Type           Silver-Plated Nickel Gauze Mk 2

 

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18      OPERATING PROCEDURES

[Issue 8; Configuration 10; 10th May 2010]

Item Specification Comments
Transport to site 40ft Container with side loader  
Tow Point Rigid bar mounting point behind front nose section (front section of nose removed during towing)  
Front Jacking Point ? Will also be used as bolt down points (for transportation & tie-down tests) and axle stand points
Rear Jacking Point ? Will also be used as bolt down points (for transportation & tie-down tests) and axle stand points

 

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Part 1 ¦ Part 2 ¦ Part 3 ¦ Part 4 ¦ Part 5 ¦ Part 6

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