[61] 1. A study of launch trajectories is needed to determine:

(a) Velocity changes necessary to safely abort the mission during launch.

(b) Design criteria for heating and air loads associated various emergency reentry situations.

2. A study of the reentry following return from the lunar mission is needed to:

(a) Establish navigation accuracy required during the terminal adjustment and reentry maneuvers.

(b) Determine auxiliary propulsion requirements during this phase.

(c) Establish L/D requirements for corridor maneuvers.

(d) Determine design criteria for heating and air loads associated with the corridor boundary conditions.

(e) Determine the desired amount of aerodynamic L/D needed during the postblackout period.

3. Additional research must be done to extend aerodynamic heating theory to escape velocity and to establish the magnitude of shock wave radiation.

4. Continue development of high temperature structures and materials. Establish ablation effectiveness of suitable materials for heating situations to be encountered.

5. Continue study of promising configurations until best reentry vehicle can be established. Study should include among other things:

(a) Parametric wind tunnel studies where practical.

(b) Single unit and caboose type vehicles.

(c) Practical method of escape during boost within atmosphere.

6. Extend evaluation of subsonic L/D and wing loading criteria for glider landing to include rough water conditions.

[62] 7. Investigate and establish design criteria for large parachutes and parachute clusters. Note that parachute systems with translation capability may be desired.

8. Continue investigation of impact bags and other impact attenuation devices.

9. Establish design criteria for auxiliary propulsion systems. Note this will probably be different for solid and liquid rocket systems. Institute the development of suitable rocket systems in accordance with established requirements.