I-A Lunar Mission.

1. Guideline. The vehicle should be capable ultimately of manned lunar reconnaissance.

2. Justification. The mission is a step toward landing man on the moon and other planets.

3. Discussion.

(a) The trajectory of the vehicle must be such that reconnaissance of the moon can be effected in sufficient detail to acquire or verify information for selection of lunar landing sites and design of lunar landing vehicles.

(b) Close lunar orbit may be required for satisfactory reconnaissance.

(c) Instrumentation capabilities will dictate what required in the way of "closeness" to the moon and "time" near the moon.

I-B Orbital Mission.

1. Guideline. The lunar vehicle should be capable of earth orbital missions for initial evaluation and training. The reentry component of this vehicle should be capable of earth orbital missions in conjunction with space laboratories or space stations.

2. Justification. The reentry vehicle should be designed for use with both the lunar vehicle and the orbiting laboratory to avoid unnecessary duplication of vehicle development.

3. Discussion. It is assumed that the vehicle will consist of a "reentry component" and a "mission component" without reentry capability. The mission component for the basic vehicle should be designed for the circumlunar mission and the total vehicle should not weigh more than 15,000 pounds. However, the vehicle should be adaptable to an alternative mission component which will allow it to function as an earth orbiting laboratory. For this corollary earth orbiting mission, the total weight of the reentry vehicle plus mission component can be increased to the order of 25,000 pounds.

[55] I-C Propulsion and Weight.

1. Guideline. The multiman advanced space vehicle should be designed to be compatible with the Saturn and for the lunar mission it should weigh not more than 15,000 pounds including auxiliary propulsion and attaching structure.

2. Justification.

(a) Saturn will be the only propulsion system with sufficient payload capability available in the near future.

(b) The 3 stage Saturn C 2 payload capability for the lunar mission is estimated to be not more than 15,000 pounds.

3. Discussion.

None.

I-D Flight Time Capability.

1. Guideline. The vehicle should be designed for a flight time capability without resupply of 14 days.

2. Justification.

(a) Minimum time for lunar circumnavigation is on the order of 6 days.

(b) Total flight time may be appreciably affected by lunar perturbations, ensuing midcourse corrective actions, loiter time, or choice of nonminimum trajectories.

3. Discussion.

None.

I-E Maneuvering in Space.

1. Guideline. Adequate auxiliary propulsion should be provided for guidance maneuvers required to carry out the assigned missions and for safe return in event of launch emergencies.

2. Justification. Self evident from mission requirements.

[56] 3. Discussion.

(a) Guidance accuracies and capabilities should be studied in order to determine auxiliary propulsion requirements.

(b) Sufficient reserve propulsion should be included to accommodate corrections for maximum guidance errors.

(c) A single system may suffice for both midcourse escape propulsion requirements.

II-A Mission Abort Capability.

1. Guideline. The vehicle should have the capability of safe crew recovery from aborted missions at any speed up to maximum velocity, independent of use of the launch propulsion system.

2. Justification. The above requirement is basic to manned operations.

3. Discussion.

(a) The vehicle should be provided with some manner of abort capability throughout the launch phase.

(b) Safe control of the vehicle subsequent to aborting the mission is required, i.e.: auxiliary rocket power (maneuvering rockets) and the aerodynamic L/D capabilities of the configuration must be adequate for this condition as well as the normal mission.

II-B Ground and Water Landing Capability.

1. Guideline. The vehicle should be capable of a satisfactory landing on both land and water and should have the capability of avoiding local hazards.

2. Justification.

(a) Emergency abort conditions may force landing on either land or water.

(b) Reliability of guidance, control and propulsion systems on lengthy missions is unknown and may cause unexpected error in earth reentry coordinates.

[57] (c) Accessibility for recovery is an important consideration. Relative superiority of land versus water landing will vary with locale.

3. Discussion.

(a) Vehicle structure should be capable of adequate attenuation of ground and water landing loads in a 30-knot wind.

(b) Vehicle should be watertight and have adequate sea keeping qualities under sea state four conditions (10-12-foot waves).

II-C Point Return.

1. Guideline. The vehicle should have the normal capability of landing at one of several previously designated ground surface locations on the earth approximately 10 square miles in area.

2. Justification. This capability is needed to provide for convenient return of vehicle and crew.

3. Discussion.

(a) Studies are needed to assess the value of impulse maneuvers, guidance quality, and aerodynamic L/D for the return from lunar mission.

(b) This requirement is far less severe for the orbital mission.

II-D Postlanding Survival Period.

1. Guideline. The vehicle should be designed for crew survival for at least 72 hours after landing.

2. Justification. Due to the random nature of possible emergency maneuvers, it will be impossible to provide sufficient recovery forces to cover all possible landing locations. The above requirement would permit mobilization of normally existing facilities in adequate time for a safe recovery.

3. Discussion. The vehicle should be equipped with adequate location devices.

[58] III-A Crew Environmental Factors.

1. Guideline. The crew accommodations must provide for a safe and comfortable "shirt sleeve" crew environment for the entire mission.

2. Justification. The mission is predicated upon the efficient operation and safe return of the crew.

3. Discussion.

(a) A sealed cabin with decompression protection should be provided.

(b) The long duration of the flight precludes the continuous use of a pressure suit.

(c) An environmental control system capable of meeting the crew's load and flight duration must be developed.

(d) Accelerations imposed on the crew should not exceed the physiological limits in keeping with the support and restraint systems provided.

(e) Noise and vibration levels should be maintained within the tolerable limits.

(f) Provision for recreation and exercise required to maintain crew efficiency.

(g) The long confinement period may require provisions for individual privacy.

(h) Provisions for nutrition, personal hygiene, and waste disposal, should be provided.

III-B Crew Size.

1. Guideline. The minimum crew should consist of at least three men.

2. Justification.

(a) Continuous duties and communication make it desirable that at least one man be on duty at all times.

[59] (b) On duty off duty cycle tests indicate that three men may be the necessary minimum.

(c) Redundancy in capabilities for backup purposes is essential to insure a degree of success in the event of disablement of personnel.

3. Discussion.

None.

III-C Adequate Protection from Radiation.

1. Guideline. The mission should be accomplished without subjecting the crew to more than a permissably safe radiation dose.

2. Justification.

(a) The possible hazards to the health and well being of the crew must be commensurate with or less than the other risks inherent in an adventure of this nature.

(b) High dosage could incapacitate the crew for the proper performance of their duties.

3. Discussion.

(a) Present knowledge indicates that 25 REM is probably an upper limit.

(b) Studies of minimum radiation trajectories are needed.

(c) Maximum utilization of structural materials and onboard equipment should be studied for minimization of radiation dosage to crew.

(d) Detailed information regarding the radiation environment around the earth and in cislunar space is needed.

(e) Present knowledge of solar radiation, coupled with the payload capability of chemical propulsion systems currently under development, indicates that sufficient shielding cannot be provided for the crew in the advent of a solar flare.

(f) A solar flare prediction method is needed.

[60] IV-A Onboard Command.

1. Guideline. The primary command of the mission should be onboard.

2. Justification. System simplicity and mission reliability will result from the maximum utilization of the command decision capabilities of the crewman.

3. Discussion.

(a) Automatic control will be employed to obtain precision or speed of response otherwise unattainable, but monitoring by the crew of each control function with provision for override will be required.

(b) The navigation computer must not only solve the problems of insertion, midcourse, and terminal guidance, but also be capable of performing calculations to provide the crew the information that is required to assess or respond to emergency situations.

(c) Systems and simulation studies will be required to evolve computer requirements, navigation and guidance techniques, attitude control requirements, and display requirements.

IV-B Communication and Tracking Facilities.

1. Guideline. Communication and ground tracking should be provided throughout the lunar mission except when the vehicle is blanketed by the moon.

2. Justification.

(a) Communications and tracking are the means of keeping the ground crew informed of the mission status.

(b) Information for trajectory control will be obtained by ground tracking and relayed to the vehicle.

3. Discussion.

(a) Detailed studies are required to determine the most efficient and reliable means of maintaining communications and tracking.

(b) Contact at least once during each orbit will probably be adequate for the orbital mission.