SPACE LAUNCH REPORT
      Gilmour Space Eris Launch Vehicle Flight History 
                 by Variant/Year (2024-)
         by Ed Kyle, Last Update March 23, 2024
  
        L(F) = Number of Launches(Number of Failures)  

         Eris                                       Grand
                                                    Total
Year     L(F)       L(F)       L(F)       L(F)      L(F) 
------------------------------------------------------------------
2020      -          -          -          -          -    
2021      -          -          -          -          -      
2022      -          -          -          -          -     
2023      -          -          -          -          -  
------------------------------------------------------------------
         Eris                                        Grand
                                                     Total
         L(F)       L(F)       L(F)        L(F)      L(F)    
------------------------------------------------------------------
Suborb    -          -          -          -          -    
Orbit     -          -          -          -          -  
Total     -          -          -          -          -  
------------------------------------------------------------------


                    Eris Vehicle Configurations

==================================================================
              Payload        Config.            Height     Mass  
              (tonnes)                         (meters)  (tonnes)   
          [1] 500 km SSO
          [2] LEO     
==================================================================
Eris      0.215 t [1]      3-stg Eris            25 m      >30 t   
          0.305 t [2]      
==================================================================
 


                     Eris  Vehicle Components

------------------------------------------------------------------
  	
                  Stg 1       Stg 2      Stg 3      PLF   
==================================================================
Diameter (m)      2 m         1.5 m      1.5 m      1.5 m       
Length (m)       
Mp (tonnes) 	     	  	 
GLOW (tonnes) 	  	  	 
Propellant 	  Hybrid      Hybrid     RP/LOX
                  HTP/        HTP/
                  Polyethl.   Polyethl.
                                               
T (SL tonnes) 	  ~40 t   	  	      
T (VAC tonnes) 	              11.22 t    >1 t   
ISP (SL/Vac sec)  
                              
Burn Time (sec)   100 s       100 s      190 s    	  	 
Engines/Motors    4           1          1  
                                               
Engine 	          4xSirius    1xSirius   1xPhoenix
==================================================================

  	 

                     ERIS LAUNCH HISTORY

------------------------------------------------------------------

DATE    VEHICLE ID  PAYLOAD               MASS(t)  SITE*    ORBIT*
==================================================================
mm/dd/yy aaaa   nn  aaaaa                  n.nn    aa nnnnn  aaa
================================================================== 

      NOTES by Vehicle ID

*ABBREVIATIONS

SITE

BO:  Bowen Orbital Spaceport, Abbot Point State Development Area, 
     Queensland, Australia

ORBIT

LEO:  LOW EARTH ORBIT
LEO/S:  SUN SYNCHRONOUS LOW EARTH ORBIT
SUB:  SUB-ORBITAL MISSION
[FTO]:  FAILED TO ORBIT
[LEO]:  UNPLANNED LEO
------------------------------------------------------------------


                 SPACE LAUNCH REPORT
                 Gilmour Space Eris 
           Planned Australian Launch Vehicle
                    by:  Ed Kyle             

Australia's Gilmour Space plans to launch its three-stage Eris 
orbital launch vehicle from a new pad at Bowen, Queensland, 
possibly during 2024.  The company was founded by brothers Adam 
and James Gilmour.

The small rocket uses hybrid motors to power its first two 
stages.  Four Sirius hybrids in the first stage use polyethlyene 
solid fuel cylinders that are injected with HTP liquid to produce 
up to 11.2 tonnes thrust each in vacuum. A single Sirius powers 
Stage 2.  Each stage burns for up to 100 seconds.  

The liquid third stage burns kerosene and LOX.  It fires for 
120 seconds after a 300 second coast.

The 25 meter tall rocket is expected to weigh more than 30 tonnes 
at launch.  It will rise on about 40 tonnes liftoff thrust.  
Payload capability is listed as 305 kg to LEO or 215 kg to a 
500 km sun synchronous orbit.

                         


References