table1.35

SP-4012 NASA HISTORICAL DATA BOOK: VOLUME III
PROGRAMS AND PROJECTS 1969-1978

Table 1-35. Titan HIE-Centaur Characteristics.

.

Stage O Solid Rocket Motors (2)
Ist Stage Titan
2d Stage Titan
3d Stage Centaur D-IT
Centaur Standard Shroud
Total

.

Height (m):

25.9

22.2

7.1

9.7

(17.7)

48.8

Diameter (m):

3.05

3.05

3.05

3.05

4.3

-

Launch weight (kg):

226 800 each

123 830

33 112

17 700

3092

631 334

Propulsion system

Powerplant:

United Technology 1205

Aerojet YLR87-AJ-11

Aerojet YLR91-AJ-11

Pratt & Whitney (2) RL-1OA-3-

-

-

Thrust (newtons):

10.68 mill (combined)

2.31 mill

449 248

133 440

-

13.55 mill

Burn time (sec.):

110

150

208

450

-

918

Propellant:

powdered aluminum/ ammonium perchlorate

N₂H₄-UDHM/ N₂0₄

N₂H₄-UDHM/ N₂0₄

LH₂/LOX

-

-

Payload capacity:

15 000 kg to earth orbit

3000 kg to synchronous orbit

3402 kg to Mars

Origin:

Air Force Titan IIID modified to NASA's requirements

-

-

NASA design

-

-

Contractors:

Chemical Systems Div., United Technologies

Martin Marietta Corp.

General Dynamics/Convair

-

-

-

Program manager:

R.A. Mattson, NASA Hq.

Project manager:

Andrew J. Stofan, Lewis Research Center

How utilized:

Viking, Voyager

Remarks:

In this configuration, the Centaur upper stage replaced the standard Titan third stage, called the transtage; Centaur was capable of restarting its two engines, a desirable characteristic for planetary missions. During Centaur's coast phase, attitude control was accomplished by 14 small hydrogen peroxide thrusters.

When the two five-segment solid rocket motors, together known as "stage O," were jettisoned, the Titan first stage ignited. These strap-on motors provided more than four times the thrust of the Atlas booster at liftoff. For two missions (Hellos I and Helios 2), a fourth-stage solid-propellant motor (Thiokol TE-M-364-4) added to the spacecraft package.

- Back -

.	Stage O Solid Rocket Motors (2)	Ist Stage Titan	2d Stage Titan	3d Stage Centaur D-IT	Centaur Standard Shroud	Total
.
Height (m):	25.9	22.2	7.1	9.7	(17.7)	48.8
Diameter (m):	3.05	3.05	3.05	3.05	4.3	-
Launch weight (kg):	226 800 each	123 830	33 112	17 700	3092	631 334
Propulsion system
Powerplant:	United Technology 1205	Aerojet YLR87-AJ-11	Aerojet YLR91-AJ-11	Pratt & Whitney (2) RL-1OA-3-	-	-
Thrust (newtons):	10.68 mill (combined)	2.31 mill	449 248	133 440	-	13.55 mill
Burn time (sec.):	110	150	208	450	-	918
Propellant:	powdered aluminum/ ammonium perchlorate	N₂H₄-UDHM/ N₂0₄	N₂H₄-UDHM/ N₂0₄	LH₂/LOX	-	-
Payload capacity:	15 000 kg to earth orbit
	3000 kg to synchronous orbit
	3402 kg to Mars
Origin:	Air Force Titan IIID modified to NASA's requirements	-	-	NASA design	-	-
Contractors:	Chemical Systems Div., United Technologies	Martin Marietta Corp.	General Dynamics/Convair	-	-	-
Program manager:	R.A. Mattson, NASA Hq.
Project manager:	Andrew J. Stofan, Lewis Research Center
How utilized:	Viking, Voyager
Remarks:	In this configuration, the Centaur upper stage replaced the standard Titan third stage, called the transtage; Centaur was capable of restarting its two engines, a desirable characteristic for planetary missions. During Centaur's coast phase, attitude control was accomplished by 14 small hydrogen peroxide thrusters. When the two five-segment solid rocket motors, together known as "stage O," were jettisoned, the Titan first stage ignited. These strap-on motors provided more than four times the thrust of the Atlas booster at liftoff. For two missions (Hellos I and Helios 2), a fourth-stage solid-propellant motor (Thiokol TE-M-364-4) added to the spacecraft package.