vehicle for launching small payloads to orbit and possibly a Saturn V class vehicle for very large payloads which might exceed the capacity of the shuttle. The shuttle obviously will permit major reductions in launch costs over present day expendable vehicles because of its extensive reusability. In addition, and we don't think we really know the full impact of this, there will be very significant benefits in payload design, development and operations that will occur because of its large cargo bay and weight to orbit capability; its in-orbit satellite servicing capability; and its ability to return satellites from space for refurbishment and

reuse.

Current status

During 1970 NASA continued to implement the President's stated objective to substantially reduce the cost of space operations and to provide a future capability to support a large variety of space applications.

Two sets of one year definition study contracts were awarded in June 1970, one for the Shuttle vehicle and the other set for the engine. Basic objectives are to define the Shuttle system and the engine requirements, accomplish preliminary design, and predict the scope, schedule and cost of a fully reusable two stage shuttle. Meanwhile other contractual studies of alternate vehicle concepts are also being conducted to insure that all approaches are fully explored.

Concurrent with the vehicle and engine study efforts, we initiated other studies and analyses in the areas of payloads, and mission traffic requirements. These will yield a better understanding of what the shuttle will mean to payload designers, and how the projected missions will fit into a national space traffic pattern.

Definition contractors have passed the midway point in their definition studies and significant progress has been made in thermal protection materials, structural fabrication studies, avionics, aerodynamic effects, and main rocket engine preliminary design and testing. Each of the vehicle studies has focused on specific design and on the supporting technology for one basic configuration. These designs are basically delta wing configurations and provide high cross range capability.

Performance

SHUTTLE APPLICATIONS

My next chart MH-71-5390 shows the general characteristics of the Space Shuttle. It will be designed for airplane type reusability. A payload bay, 60 feet long and 15 feet in diameter will be able to carry satellites, logistic support payloads and passengers. An inboard profile MH-71-5015, shows the major parts of an Orbiter with a candidate payload, in this case a communication satellite Intelsat IV, installed.

Flight accelerations will not exceed 3 Gs so that non-astronaut personnel can be transported.

The main propulsion system will use throttleable high performance hydrogen/ oxygen engines.

The significant impact of the shuttle on payload launch costs is clearly demonstrated when launch cost as low as $75 per pound of payload for the shuttle is compared to $800/lb. for the Saturn V and $900/lb. for the Titan-3c.

One of the basic capabilities of the space shuttle orbiter is the ability to maneuver during reentry into the earth's atmosphere resulting in a lateral displacement to the landing point. This is cross range. Cross range capability is desirable because it reduces the number of landing sites required to provide for a once per day return to the Continental United States from orbit and the capability to return to the launch site at the end of the first revolution. The capability to return to the launch site is especially important since any problem that might occur during the launch phase could quickly be taken care of by returning the orbiter to the launch site after one orbit. The orbiter will be designed for 1100 miles cross range MH 71-5164 to cover a wide range of contingencies and specific mission requirements.

The shuttle will operate in low earth orbits under 600 nautical miles altitude. Payloads destined for high energy orbits will be transported to low earth orbit by the shuttle along with a propulsion stage. The propulsion stage will then transfer the payload to its destination. In this manner the shuttle can support geosynchronous missions as well as deep space missions.

• 1100 N.M. ORBITER NOMINAL CROSSRANGE

• MISSION DURATION 7 DAYS SELF SUSTAINING FROM LIFT-OFF TO LANDING

- 30 DAYS EXPENDABLES CHARGED AGAINST PAYLOADS

• MAIN ENGINE BASELINED AT 550,000 POUNDS SEA LEVEL THRUST (BOOSTER

59-311 0-71-No. 2, pt. 2-5

LH 2

ON ORBIT
TANKS

MAIN ENGINES

LO 2 TANKS

NASA HQ MH71-5015

The two stage vehicles shown here in MH 70-5065 is representative of the Delta-wing configurations included in our definition studies. We believe that this approach will best satisfy our needs for driving down the operational costs of space transportation.

On a typical mission, MH 70-7241A, the Shuttle will take off under rocket power with the booster accelerating the orbital stage to the outer fringe of the earth's atmosphere where separation will occur. At this point, about 40 miles high, the shuttle will have a speed of almost 8,000 miles per hour. After separation the booster will reenter the Earth's atmosphere and cruise to a horizontal landing in a flight pattern quite similar to a large commercial transport.

The orbiter, powered by its own rocket engines, will proceed to an orbital speed of approximately 18,000 miles per hour to deliver its payload and perform its assigned mission. After spending up to seven days in orbit, the orbiter will reenter, MH 71-5064, and return to a conventional jet airport runway and land. Avoided will be the expensive costs of recovery at sea by eliminating the need for ships, airplanes, helicopters, and the water recovery team. After a short period of approximately two weeks, during which minimum maintenance will be performed, both shuttle stages will be ready for another mission. Utilization

A fully operational shuttle system will provide transportation for operational and development payloads for the Department of Defense, National Aeronautics and Space Administration, the National Oceanographic and Atmospheric Administration, and other users such as the Departments of Interior and Agriculture for earth resources observations. Many other countries can utilize the shuttle. In cooperation with the United States they are already making plans to participate.

Many earth orbital transportation requirements can be satisfied. It will be used for MH 71-5179, placement and retrieval of satellites, satellite servicing and maintenance, short duration orbital missions, delivery of propulsive stages and payloads for high energy missions, Space Station logistics support and replacement of scientific personnel, and delivery of propellants. Initially the shuttle will be used to orbit and retrieve automated satellites, MH 71-5233. The Space Sciences and Applications Office of NASA has many missions for future shuttle flights already identified. These payloads cover six major categories: Space Physics, Astronomy, Space Applications, Life Sciences, Planetary, and Earth Resources.