table1.31

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

Table 1-31. Thor-Delta 3914 Characteristics

.

1st Stage Thor
Strap-on Solid Rocket Motors
2d Stage Delta
3d Stage
Total with Spacecraft

.

Height (m):

21.3

11.3

6.4

1.4

35.4

Diameter (m):

2.4

1.02

1.5

1.0

-

Launch weight (kg):

93 200

-

6 180

1 160

190 630

Propulsion system:

Powerplant:

RS-27

(9) TX-526 Castor IV

TR 201

TE 364-4

-

Thrust (newtons):

920 736

3 633 000 (total)

42 923

61 858

4 688 517

Burn time (sec.):

209

58.2

335

44

-

Propellant:

RP-1/LOX

solid

Aerozene 50/N₂0₄

solid

-

Payload capacity:

907 kg to synchronous transfer orbit

Origin:

Air Force IRBM

-

NASA-McDonnell Douglas design

-

-

Program manager:

Isaac Gillam, IV, Peter T. Eaton, NASA Hq.

Project manager:

William Schindler, Goddard Space Flight Center

Contractors:

McDonnell Douglas: prime Rocketdyne Div., Rockwell Corp.: propulsion

Thiokol Corp.

McDonnell Douglas: prime TRW: propulsion

Thiokol Corp.

-

How utilized:

medium-weight payloads, primarily commercial communications satellites

Remarks:

From a continuing effort to increase the launch capacity of the Thor-Delta configuration, the 3914 model emerged as the most powerful Thor-Delta of the 1970s. As shown in fig. 1-4, the only major alteration to the 2000 Series that was made to produce the 3914 was the substitution of the larger Castor IV strap-one for the long-used Castor Ills. NASA was using the Delta 1000, 2000, and 3000 models simultaneously during the late 1970s.

The RS-27 booster propulsion system was made of one main engine and two vernier engines. Five of the nine strap-one ignited at liftoff, the remaining four at 64 seconds after liftoff.

See also:

Volume 2.

- Back -

.	1st Stage Thor	Strap-on Solid Rocket Motors	2d Stage Delta	3d Stage	Total with Spacecraft
.
Height (m):	21.3	11.3	6.4	1.4	35.4
Diameter (m):	2.4	1.02	1.5	1.0	-
Launch weight (kg):	93 200	-	6 180	1 160	190 630
Propulsion system:
Powerplant:	RS-27	(9) TX-526 Castor IV	TR 201	TE 364-4	-
Thrust (newtons):	920 736	3 633 000 (total)	42 923	61 858	4 688 517
Burn time (sec.):	209	58.2	335	44	-
Propellant:	RP-1/LOX	solid	Aerozene 50/N₂0₄	solid	-
Payload capacity:	907 kg to synchronous transfer orbit
Origin:	Air Force IRBM	-	NASA-McDonnell Douglas design	-	-
Program manager:	Isaac Gillam, IV, Peter T. Eaton, NASA Hq.
Project manager:	William Schindler, Goddard Space Flight Center
Contractors:	McDonnell Douglas: prime Rocketdyne Div., Rockwell Corp.: propulsion	Thiokol Corp.	McDonnell Douglas: prime TRW: propulsion	Thiokol Corp.	-
How utilized:	medium-weight payloads, primarily commercial communications satellites
Remarks:	From a continuing effort to increase the launch capacity of the Thor-Delta configuration, the 3914 model emerged as the most powerful Thor-Delta of the 1970s. As shown in fig. 1-4, the only major alteration to the 2000 Series that was made to produce the 3914 was the substitution of the larger Castor IV strap-one for the long-used Castor Ills. NASA was using the Delta 1000, 2000, and 3000 models simultaneously during the late 1970s. The RS-27 booster propulsion system was made of one main engine and two vernier engines. Five of the nine strap-one ignited at liftoff, the remaining four at 64 seconds after liftoff.
See also:	Volume 2.