SPACE SHUTTLE

Slide 21 of 125

Notes:

By mid-1969, the ambitious new NASA Administrator, Tom Paine, had proposed an extensive manned space exploration program as the logical follow-on to Apollo. A new modular, reusable space transportation system consisting of the space shuttle as well as interplanetary nuclear and chemical “space tugs” and space stations would be required to set up bases on the Moon and Mars during the 1970s and 1980s. The first major goal was now a 12-man space station by 1975 and NASA awarded $2.9-million study contracts to North American Rockwell and McDonnell-Douglas in July 1969. The space station would later evolve into a 50-man "space base" by 1980 and additional " way-stations" would be deployed in geostationary, lunar and Mars orbit during the 1980s.

The U.S. aerospace industry naturally was very interested in NASA future manned spaceflight plans since it could result in production contracts worth billions further down the read. These modular concepts were proposed by General Electric who sought join a shuttle contractor team in late 1969. The “siamese” design at left has two identical vehicles with additional engines mounted on the structure between them. Four vehicles operating in tandem could boost a heavy space station into orbit (center). The more traditional concept at right consists of a 90.5 meter long double-delta booster with a wingspan of 54.9 meters. The orbiter is derived from the HL-10 lifting body shape.

George Mueller's “space shuttle” effort also appeared to be picking up speed as the Apollo project grew to a close. NASA awarded four $0.3-million space shuttle / integral launch & reentry vehicle “phase-A” study contracts to North American Rockwell, McDonnell-Douglas, Lockheed and General Dynamics in January 1969. Martin Marietta's bid was rejected, but the company nonetheless decided to participate using its own funds. The range of possible concepts was very large and some 120 different permutations were investigated by the contractors. The requirements called for “Integral Launch & Reentry Vehicles” having a 12-crew capability, 720km reentry crossrange, and a 2.268-22.68t payload capability by 1974. The most important mission was expected to be space station resupply payloads weighing about 11,340kg.

1975 1976 1977 1978 1979 1980 1981 1982 1983 1984 1985 TOTAL

UNMANNED SATELLITES 2 2 2 2 2 2 2 2 2 2 2 22

UNMANNED PLANETARY PROBES 7 1 8 3 4 6 5 2 7 5 3 51

SPACE STATION (ROTATE 12-CREW EVERY 3 MTHS.) 7 7 7 7 7 35

SPACE BASE (5 FLIGHTS/QUARTER TO ROTATE ENTIRE 50-CREW) 23 23 23 23 23 23 138

LUNAR PROGRAM (6-MAN LUNAR ORBITAL STATION + 6-MAN MOONBASE) 48 48 34 34 34 34 34 34 300

=TOTAL UNMANNED FLIGHTS 9 2 2 2 2 2 2 2 2 2 2 29

=TOTAL MANNED FLIGHTS 7 7 7 55 55 57 57 57 57 57 57 473

TOTAL SHUTTLE FLIGHTS: 16 10 17 60 61 65 64 61 66 64 62 546

Space Shuttle Mission Model (mid-1969)

In April 1969, Mueller set up a NASA space shuttle task group headed by LeRoy Day to evaluate potential uses of the vehicle. The shuttle requirements had changed considerably as a result of the new post-Apollo program which required a total of 546 shuttle launches in 1975-85. In May, Mueller instructed the task group to increase the payload capability to 22,680kg to comply with US Air Force requirements, but also because there would be a need to launch vast quantities of low-density rocket propellants into Earth orbit for future space stations in geostationary and lunar orbit. The mission requirements also grew significantly more complex and diverse (see table) as the Shuttle had to be capable of launching unmanned satellites and spaceprobes as well.

ORBITAL CHARACTERISTICS SPACE STATION / BASE LOGISTICS SUPPORT PLACEMENT AND RETRIEVAL OF SATELLITES DELIVERY OF PROPULSION STAGES & PAYLOAD DELIVERY OF PROPELLANTS SATELLITE SERVICING & MAINTENANCE SHORT DURATION ORBITAL MISSIONS

ALTITUDE (KM) 370 TO 555KM 185 TO 1480KM 185 TO 230KM 370 TO 555KM 185 TO 1480KM 185 TO 555KM

INCLINATION (DEG.) 28.5 - 90 28.5 - 98 28.5 - 55 28.5 - 55 28.5 - 98 28.5 - 90

DURATION (DAYS) 7 7 7 7 7 TO 15 7 TO 30

PAYLOAD CHARACTERISTICS SPACE STATION / BASE LOGISTICS SUPPORT PLACEMENT AND RETRIEVAL OF SATELLITES DELIVERY OF PROPULSION STAGES & PAYLOAD DELIVERY OF PROPELLANTS SATELLITE SERVICING & MAINTENANCE SHORT DURATION ORBITAL MISSIONS

CREW 2 2 2 2 2 2

PASSENGERS (MIN.) 50 MEN / QTR 2 2 2 4 10

PAYLOAD DIAMETER (M) 4.57 4.57 4.57 4.57 4.57 4.57

ASCENT PAYLOAD WT. 31750KG / QTR 4536-22680KG 11340-22680KG 22680KG 2268-6804KG 11340-22680KG

ASCENT PAYLOAD VOL. 142-283 M³ 283 M³ 283 M³ 142-283 M³ 113-170 M³

RETURN PAYLOAD WT. 20412KG / QTR 4536-22680KG -- -- 6804KG 22680KG

RETURN PAYLOAD VOL. -- 142-283 M³ -- -- 142-283 M³ 113-170 M³

Space Shuttle Mission Requirements (mid-1969)

An important result of Tom Paine's “bold thinking” and cost-is-no-object approach was that only fully reusable VTHL TSTO concepts were considered because they offered the lowest cost per flight and better operability, high payload capability and flexibility. NASA directed its Phase A contractors to concentrate on fully reusable shuttle concepts from August 1969 onwards after the Shuttle task group had investigated the potential life-cycle costs of three classes of 22,680-kilogram payload RLVs. An advanced low-cost expendable rocket plus reusable spacecraft would have cost an estimated $2.5 billion (=$11.35B in 1999 dollars) to develop and $43.1 million (=$195.7M, or $8600/kg in FY'99 $) per launch. The ILRV/Starclipper-type partially reusable SSTO would have had a development cost of $3.9B (=$17.7B in FY'99 $) and the cost per launch was $5.3-12.6M (=$24.1-57.2M / $1000-2500/kg) depending on the production cost of the expendable propellant tanks. Finally, NASA estimated that a simple fully reusable TSTO configuration such as the GD Triamese would have a development cost $4.5B (=$20.5B at 1999 economic conditions) but the cost per launch would only be $3.2 million (=$14.5M in FY'99 $s, or $640/kg).

“NASA Space Shuttle Summary Report”-- Revision 1, July 31, 1969

“Reusable Shuttle Configurations Emerging” -- AW&ST, 1969/November 10/p.73

“Characteristics of the Space Shuttle” -- Jean & Scott, AAS 1970/vol.28/p.141

	1975	1976	1977	1978	1979	1980	1981	1982	1983	1984	1985	TOTAL
UNMANNED SATELLITES	2	2	2	2	2	2	2	2	2	2	2	22
UNMANNED PLANETARY PROBES	7	1	8	3	4	6	5	2	7	5	3	51
SPACE STATION (ROTATE 12-CREW EVERY 3 MTHS.)	7	7	7	7	7							35
SPACE BASE (5 FLIGHTS/QUARTER TO ROTATE ENTIRE 50-CREW)						23	23	23	23	23	23	138
LUNAR PROGRAM (6-MAN LUNAR ORBITAL STATION + 6-MAN MOONBASE)				48	48	34	34	34	34	34	34	300
=TOTAL UNMANNED FLIGHTS	9	2	2	2	2	2	2	2	2	2	2	29
=TOTAL MANNED FLIGHTS	7	7	7	55	55	57	57	57	57	57	57	473
TOTAL SHUTTLE FLIGHTS:	16	10	17	60	61	65	64	61	66	64	62	546

ORBITAL CHARACTERISTICS	SPACE STATION / BASE LOGISTICS SUPPORT	PLACEMENT AND RETRIEVAL OF SATELLITES	DELIVERY OF PROPULSION STAGES & PAYLOAD	DELIVERY OF PROPELLANTS	SATELLITE SERVICING & MAINTENANCE	SHORT DURATION ORBITAL MISSIONS
ALTITUDE (KM)	370 TO 555KM	185 TO 1480KM	185 TO 230KM	370 TO 555KM	185 TO 1480KM	185 TO 555KM
INCLINATION (DEG.)	28.5 - 90	28.5 - 98	28.5 - 55	28.5 - 55	28.5 - 98	28.5 - 90
DURATION (DAYS)	7	7	7	7	7 TO 15	7 TO 30

PAYLOAD CHARACTERISTICS	SPACE STATION / BASE LOGISTICS SUPPORT	PLACEMENT AND RETRIEVAL OF SATELLITES	DELIVERY OF PROPULSION STAGES & PAYLOAD	DELIVERY OF PROPELLANTS	SATELLITE SERVICING & MAINTENANCE	SHORT DURATION ORBITAL MISSIONS
CREW	2	2	2	2	2	2
PASSENGERS (MIN.)	50 MEN / QTR	2	2	2	4	10
PAYLOAD DIAMETER (M)	4.57	4.57	4.57	4.57	4.57	4.57
ASCENT PAYLOAD WT.	31750KG / QTR	4536-22680KG	11340-22680KG	22680KG	2268-6804KG	11340-22680KG
ASCENT PAYLOAD VOL.		142-283 M³	283 M³	283 M³	142-283 M³	113-170 M³
RETURN PAYLOAD WT.	20412KG / QTR	4536-22680KG	--	--	6804KG	22680KG
RETURN PAYLOAD VOL.	--	142-283 M³	--	--	142-283 M³	113-170 M³