Potential DOD applications of nuclear thermal propulsion are listed and the performance goals and cost benefits of these propulsion systems are outlined

Bleeker, Gary A.

English

NASA Technical Reports Server

N 9 3 - 2 6 9 1 1  
* DOD REQUIREMENTS 
FOR 
SPACE NUCLEAR THERMAL PROPULSION 
PRESENTATION TO 
NUCLEAR PROPULSION TECHNICAL 
INTERCHANGE MEETING 
BY 
LT COL GARY A. BLEEKER 
SNTP PROGRAM MANAGER 
PHILLIPS LABORATORY 
20 OCTOBER 1992 
POTENTIAL DOD APPLICATIONS 
OF NUCLEAR THERMAL 
PROPULSION 
o UPPER STAGES ON EXISTING AND/OR 
NEW LAUNCH SYSTEMS 
o ORBIT TRANSFER VEHICLES (OTVs) 
o REUSABLE ONs 
o ORBIT MANEUVERING VEHICLES 
Intruduction: Requirements 16 N P-TIM-02 
https://ntrs.nasa.gov/search.jsp?R=19930017722 2020-03-17T05:26:55+00:00Z
Typical Upper Stage P 
PBR Second Stage Typically Offers 
Exo-Atmospheric Operation 
2x - 4x Payload Improvement 
(> 50 n.m.) 
7)esign Basetllm 
83 klbf Engine 
I. I P 
)plications 
75 klbf' 500 klM PBR Stage Thtusl 40 klbf 40 klbf 45 klbf 170 klbf' 
300 
sa 
Y70 
060 
Y, 
340 
-30 
120 
P 10 
MX MX SI + MX Sl/ll+ Atlas Atlas IlAS Atlas Deriv Tim:: Titan + Titan 
SVll/lll PBR PBR IlAS + P E R  + P B R  IV PER SRMS+ 
I*I PER Core 
- -  
Complement National 
System 
~~~ ' +SNTP N L S  3 
NLS Requirements 
USAFlNASA Requirements: 
20 Klbs to LEO - NLS 3 
50 Klbs to LEO - NLS 2 
15 Klbs to GSO - NLS2 
Add'l NASA Requirements: 
SEI Heavy Lift - TBD 
SSF: 80 Klbs - NLS 1 
LEO 
GSO 
N 
NP-TIM-92 
NLS 3 
. -. 
20 41 
3.5 12 
17 
Launch 
N L S  3 NLS 3 
+ S N T P  + S N T P  
+GEMS +GEMS 
Introduction: Rcauircments 
DOD APPLICATIONS NO LONGER 
UNDER CONSIDERATION 
o BALLISTIC MISSILE INTERCEPTOR SECOND 
STAGE 
o ICBM SECOND STAGE 
DODIAIR FORCE NTP f$&IJ ,.a& 
7 REQUIREMENTS 
o DOD AND AIR FORCE DO NOT 
SPECIFICALLY CALL OUT NEED FOR NTP 
-- CALL OUT MISSION REQUIREMENTS, 
NOT TECHNOLOGY 
ACCOMPLISHMENT (LAUNCH UPPER 
STAGE) AT LESS EXPENSE AND WITH 
GREATER RELIABILITY 
-- NTP COULD ENABLE MISSION 
Introduction: Requhmentr 18 NP-TIM-92 
SNTP PERFORMANCE 
GOALS 
_. 
Potential Cost Benefits 
SNTP HAS THE FOLLOWING PERFORMANCE GOALS IN DEVELOPING 
AN ENGINE TECHNOLOGY WITH TWICE THE SPECIFIC IMPULSE OF 
HdOz ENGINES WITH COMPARABLE THRUST TO WEIGHT 
THRUST: 20,000 to 80,000 LBF 
THRUST TO WEIGHT RATIO: 
SPECIFIC IMPULSE, ISP: 1,000 SEC 
GAS CHAMBER TEMPERATURE: 3,000K 
RUN TIME DURATION: 1,000 SEC 
ENGINE CYCLES: 3 TO 10 
ENGINE STARTUP TIME: 
UP TO 35 TO 1 
UNDER 10 SEC 
Assumed $loOO/Lb Launch Cost to LEO (Past Year 2OOO) 
Mission 
National 
Launch 
Systtm 
Atlas 
Upgrade 
Orbital 
Maneuvering 
Vehicle 
Impact of sm 
Eliminate 
W o e  
Core 
Titan IV 
Payload 
Capability 
Retrieve/Repair 
High Value 
Satellites 
$/Mission 
'N~a-R~~urrin 
$25 M 
+ $2 B+ 
$130 M 
$500 M 
- 
-
20 Year 
Total 
$4.0 B 
- 
$10.4 B 
$5.0 B 
USAF 
$19.4 B 
NP-TIM-92 19 Introduction: Requirements 


DOD requirements for space nuclear thermal propulsion

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