Diamant A

 

 Architecture
 
 First Stage
 
 Designation:
 Manufacturer:
 Length:
 Diameter:
 Gross Mass:
 Structure:
 Propellant Mass:
 Propellant:
 Primary Propulsion:
  Stage Thrust:
 Pitch/Yaw Control:
 Roll Control:
 Nominal Burn Time:
 Stage Shutdown:
 Stage Separation:

Emeraude
Nord Aviation
9.9925 m
1.4 m
14,230 kg
Vascojet 90 steel
12,770 kg
Nitric Acid/Turpentine
1 x Vexin
274 kN (SL), 310 kN (vac)
Gimbal nozzle
Four aerodynamic fins
93 sec.
On pressure decrease detection
Pyrotechnic actuators (12)
    Propulsion System

 Engine Designation:
 Manufacturer:
 Type:


 Thrust:
 Throttlability:
 Chamber Pressure:
 Specific Impulse:
 Mixture Ratio:
 Restartability:
 Expansion Ratio:

Vexin
LRBA
Pressure-fed
(solid gas generator for propellant tanks pressurization)
274 kN (SL), 310 kN (vac)
No
n.a.
n.a.
n.a.
No
n.a.
 
 Second Stage
 
 Designation:
 Manufacturer:
 Length:
 Diameter:
 Gross Mass:
 Structure:
 Propellant Mass:
 Propellant:
 Stage Thrust:
 Pitch/Yaw Control:
 Roll Control:
 Nominal Burn Time:
 Stage Shutdown:
 Stage Separation:

Topaze
Nord Aviation
4.7075 m
0.8 m
2,910 kg
Vascojet 1000 steel
2,260 kg
Isolane 28/7
150 kN (vac)
TVC
TVC
44 sec.
Burn to depletion
Fire in the hole?
    Propulsion System
 Engine Designation:
 Manufacturer:
 Type:
 Thrust:
 Specific Impulse:
 Expansion Ratio:

P2
SEPR
Solid, 4 nozzles
150 kN (vac)
n.a.
n.a.
 
 Third Stage
 
 Designation:
 Manufacturer:
 Length:
 Diameter:
 Gross Mass:
 Structure:
 Propellant Mass:
 Propellant:
 Stage Thrust:
 Pitch/Yaw Control:
 Roll Control:
 Nominal Burn Time:
 Stage Shutdown:
 Stage Separation:

P0.6 or P1
Sud Aviation
1.851 m
0.65 m
730 kg
Fiberglass
641 kg
Solid
27 to 53 kN (vac)
Spin by solid (300 rpm)
None
44.5 sec.
Burn to depletion
Spring ejection
    Propulsion System
 Engine Designation:
 Manufacturer:
 Type:
 Thrust:
 Specific Impulse:
 Expansion Ratio:

P064
Sud Aviation
Solid, 1 nozzle
27 to 53 kN (vac)
n.a.
n.a.
           
   Avionics
   Inertial guidance system inherited from Saphir test vehicle with new central unit.
 The avionics is located on top of the second stage. Final guidance is provided by the payload.

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