SPACE LAUNCH REPORT
              Terran-R  Launch Vehicle Flight History 
                   by Variant/Year (202x-Present)
               by: Ed Kyle, Last Update:  12/31/2023

           L(F) = Number of Launches(Number of Failures)  
        
      Terran-1                                               Grand
                                                             Total
Year     L(F)       L(F)       L(F)       L(F)      L(F)      L(F) 
------------------------------------------------------------------
2020      -          -          -          -         -         - 
2021      -          -          -          -         -         -
2022      -          -          -          -         -         -
2023     1(1)        -          -          -         -        1(1)
------------------------------------------------------------------
       Terran-1                                              Grand
                                                             Total
         L(F)       L(F)       L(F)       L(F)      L(F)      L(F)    
------------------------------------------------------------------
Suborb    -          -          -          -         -         - 
Orbit    1(1)        -          -          -         -        1(1) 
Total    1(1)        -          -          -         -        1(1)
------------------------------------------------------------------


                TERRAN R LAUNCH HISTORY

DATE     VEHICLE   ID  PAYLOAD               MASS(t) SITE*  ORBIT*
------------------------------------------------------------------
03/23/23 Terran 1  F1  GLHF Test Flight      0.002  CC 16    [FTO]
------------------------------------------------------------------

[F1] 0325 UTC.  Inaugural launch, named "Good Luck, Have Fun".  
First CH4/LOX orbital attempt by U.S.  Stage 2 failed to ignite.  
FTO.  No deployable payload or PLF.  Slow opening engine main 
valves impacted pressures in the system and timing of propellant 
reaching the thrust chamber assembly (TCA) and gas generator (GG) 
during the start sequence.  LOX pump did not generate pressure 
when spin start power was applied to the turbines.  Possible vapor 
bubble at the pump inlet.  Due to off nominal propellant pressure
and timing, the GG did not light, and the engine did not reach 
full power.

 
              Terran-R  Vehicle Configurations

==================================================================
            Payload          Config.          Height        GLOW     
           (tonnes)                         (meters)      (tonnes)  
          (1) LEO DRL                     
          (2) GTO DRL
          (3) LEO Expend
==================================================================
Terran R  23.5 t (1)        S1: 13xAeon-R     82.3171 m   ~1300 t   
          5.5 t (2)         S2: 1xAeon-R Vac
          33.5 t (3)                         
==================================================================
DRL = Down Range Landing


                Terran R Vehicle Components          
  	
                 Stg 1      Stg 2          
                 9xAeon     1xAeonVac   PLF       
===================================================================
Diameter (m)     5.4878 m   5.4878 m    5.5 m
Length (m)       58 m       7.5 m       16.8 m       
Mp (tonnes) 	       	  	 
GLOW (tonnes) 	  	  	 
Propellant       LNG/LOX    LNG/LOX   	  	 
T (SL tonnes)    1681 t    	  	 
T (VAC tonnes)              126.6 t 
ISP (Vac sec) 		  	 
Burn Time (sec)  163 s      320 s          	  	 
Engines/Motors 	 13         1  
Engine 	         Aeon-R     Aeon-R 
                            Vac 
==================================================================	  	 

*ABBREVIATIONS

SITE

CC:  CAPE CANAVERAL

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
   
                       TERRAN R 

                    by:  Ed Kyle
                   February 07, 2024

Relativity Space is developing Terran-R. It is designed for reuse.  
It is meant to lower costs. 

Terran R will launch from Launch Complex 16 at Cape Canaveral 
Space Force Base starting in 2026. 

Terran R Architecture

A two-stage, 270-foot-tall, 18-foot diameter rocket with a 
5-meter diameter payload fairing, Terran R is designed to launch 
commercial and government payloads to LEO, MEO, GEO, "and beyond".
It will lift 23.5 tonnes to LEO or 5.5 tonnes to GTO when the 
first stage is recovered downrange.  When the stage is expended, 
LEO payload rises to 33.5 tonnes.

The rocket will be processed horizontally and will launch 
from Space Launch Complex 16 at Cape Canaveral, possibly as soon 
as 2026.  

Terran R will feather "3D printed" parts.  It will use aluminum 
alloys and will be manufactured in Long Beach, California.

The first stage will use 13 gas generator cycle Aeon R 
LOX/Methane engines each producing 258,000 lb. sea level thrust.  
Stage 2 will use a single LOX/Methane Aeon Vac engine making 
279,000 lb. vacuum thrust. Electromechanical actuators will 
provide engine thrust vector control.  

The first stage will have four outer fixed engines aligned under 
four landing legs and nine center gimbaled engines.  The LOX 
tanks will be forward of the methane tanks on both stages, 
separated by a common dome.  The tanks will be pressurized by 
cryogenic helium.  Pneumatic pushers will separate the stages.   

The first stage will use two long aero strakes and four moving 
grid fins, alonng with four retractable landing legs and an 
aft-end reentry heat shield, to provide recovery.  

Engine development is being performed at NASA Stennis Space 
Center in Mississippi.  After production in Long Beach, Terran R 
vehicles will travel by sea through the Panama Canal to 
Mississippi for testing and then Florida for launch.