APPENDIX 2 - PROJECT MERCURY TEST OBJECTIVES

MERCURY-LITTLE JOE MISSION AND TEST OBJECTIVES
Mission Launch Date Objectives
LJ-6 October 4, 1959
  1. To qualify the aerodynamics and structural integrity of the booster and the mechanical performance of the launcher.
  2. To check the performance of the system for transmitting a command signal from the ground station, receiving it in the booster during flight, and setting of an explosive system at the head end of each main rocket motor in the booster.
LJ-1A November 4, 1959
  1. To carry out a planned abort of the spacecraft from the booster at the maximum dynamic pressure anticipated during Mercury-Atlas exit flight.
  2. To obtain added reliability data on the Mercury drogue and main parachute operation.
  3. To study spacecraft impact behavior.
  4. To gain further operational experience in recovery of a floating spacecraft, utilizing a surface vessel.
  5. To obtain further experience and confidence in the operation of the booster command thrust termination system.
  6. To recover escape motor and tower.
LJ-2
Primate aboard		 December 4, 1959
  1. To carry out a planned escape of the spacecraft from the booster at high altitude (96,000 ft) just prior to main booster rocket motor burnout.
  2. To ascertain spacecraft entry dynamics for an uncontrolled entry.
  3. To check spacecraft dynamic stability on descent through the atmosphere without a drogue parachute.
  4. To determine the physiological and phychological effects of acceleration and weightlessness on a small primate (rhesus monkey).
  5. To obtain additional reliability data on the operation of the Mercury parachutes.
  6. To obtain more data on Mercury spacecraft flotation characteristics in sea areas typical of those planned for use as recovery areas.
  7. To obtain additional operational experience of spacecraft recovery by a surface vessel.
LJ-1B
Primate aboard		 January 21, 1960
  1. To check out the Mercury escape system concept and hardware at the maximum dynamic pressure anticipated during a Mercury-Atlas exit flight.
  2. To determine the effects of simulated Atlas abort accelerations on a small primate (female rhesus monkey).
  3. To obtain further reliability data on the Mercury spacecraft drogue and main chute operations.
  4. To check out the operational effectiveness of spacecraft recovery by helicopter.
  5. To recover the escape-system assembly (escape motor and tower) for a postflight examination in order to establish whether there had been any component malfunction or structure failure.
LJ-5A March 18, 1961
  1. Demonstrate the structural integrity of the Mercury spacecraft and escape system during an escape initiated at the highest dynamic pressure that can be anticipated during an Atlas launch for orbital flight.
  2. Demonstrate the performance of the spacecraft escape system, the sequential system, and the recovery system.
  3. Determine the flight dynamic characteristics of the Mercury spacecraft in an escape maneuver.
  4. Demonstrate the performance of a particular landing-bag configuration.
  5. Establish the adequacy of the spacecraft recovery procedures.
  6. Establish prelaunch checkout procedures for the functioning spacecraft systems.
  7. Determine the effects of the flight profile on the spacecraft equipment and systems not otherwise required for the first-order test objectives.
LJ-5B April 28, 1961
  1. Demonstrate the structural integrity of the Mercury spacecraft and escape system during an escape initiated at the highest dynamic pressure that can be anticipated during an Atlas launch for orbital flight.
  2. Demonstrate the performance of the spacecraft escape system, the sequential system, landing system, and the recovery system.
  3. Determine the flight dynamic characteristics of the Mercury spacecraft in an escape maneuver.
  4. Establish the adequacy of the spacecraft recovery procedures.
  5. Establish prelaunch checkout procedures for the functioning spacecraft systems.
  6. Determine the effects of the flight profile on the spacecraft equipment and systems not otherwise required for first-order test objectives.
MERCURY BEACH ABORT TEST OBJECTIVES
Mission Launch Date Objectives
Beach Abort
(Boilerplate spacecraft)		 May 9, 1960
  1. Demonstrate capability of escape system, landing system, and postlanding equipment during an off-the-pad abort.
  2. Demonstrate structural integrity of escape configuration during an off-the-pad abort.
  3. Provide time history data for the following parameters:
    1. altitude,
    2. range,
    3. velocity,
    4. pitch, roll and yaw angles,
    5. pitch, roll and yaw accelerations,
    6. impact accelerations, and
    7. sequence of events.
  4. Obtain operational experience for checkout, launch and recovery teams.
  5. Determine the effects of off-the-pad escape and landing conditions upon the spacecraft telemetry, instrumentation and communications systems.
  6. Provide time history data for the following parameters:
    1. indicated pressure altitude,
    2. outside skin temperature,
    3. inside skin temperature,
    4. cabin air temperature,
    5. noise level, and
    6. vibration.
MERCURY-REDSTONE MISSIONS AND TEST OBJECTIVES
Mission Launch Date Objectives
MR-1A
Unmanned		 December 19, 1960
  1. Qualify the spacecraft-booster combination for the Mercury-Redstone mission which includes attaining a Mach number of approximately 6.0 during powered flight, a period of weightlessness of about 5 minutes, and a deceleration of approximately 11g on reentry.
  2. Qualify the posigrade rockets.
  3. Qualify the recovery system.
  4. Qualify the launch, tracking, and recovery phases of operation.
  5. Qualify the Automatic Stabilization and Control System, including the Reaction Control System.
MR-2
Primate aboard		 January 31, 1961
  1. Obtain physiological and performance data on a primate in ballistic space flight.
  2. Qualify the Environmental Control System and aeromedical instrumentation.
  3. Qualify the landing bag system.
  4. Partially qualify the voice communication system.
  5. Qualify the mechanically-actuated side hatch.
  6. Obtain a closed-loop evaluation of the booster automatic abort system.
MR-BD
Booster Development Flight		 March 24, 1961
  1. Investigate corrections to booster problems as a result of the MR-2 flight. These problems were as follows:
    1. Structural feedback to control system producing vane "chatter".
    2. Instrument compartment vibration.
    3. Thrust control malfunction.
MR-3
Manned		 May 5, 1961
  1. Familiarize man with a brief but complete space flight experience including the lift-off, powered flight, weightless flight (for a period of approximately 5 minutes), reentry, and landing phases of the flight.
  2. Evaluate man's ability to perform as a functional unit during space flight by:
    1. Demonstrating manual control of spacecraft attitude before, during, and after retrofire.
    2. Use of voice communications during flight.
  3. Study man's physiological reactions during space flight.
  4. Recover the astronaut and spacecraft
MR-4
Manned		 June 21, 1961
  1. Familiarize man with a brief but complete space flight experience including the lift-off, powered flight, weightless (for a period of approximately 5 minutes), atmospheric reentry and landing phases of the flight.
  2. Evaluate man's ability to perform as a functional unit during space flight by:
    1. Demonstrating manual control of spacecraft during weightless periods.
    2. Using the spacecraft window and periscope for attitude reference and recognition of ground check points.
  3. Study man's physiological reactions during space flights.
  4. Qualify the explosively-actuated side egress hatch
MERCURY-ATLAS MISSIONS AND TEST OBJECTIVES
Mission Launch Date Objectives
Big Joe I September 9, 1959
  1. To recover the spacecraft.
  2. To determine the performance of the ablation shield and measure afterbody heating.
  3. To determine the flight dynamic characteristics of the spacecraft during reentry.
  4. To establish the adequacy of the spacecraft recovery system and procedures.
  5. To establish the adequacy of recovery aids in assisting the recovery of the spacecraft.
  6. To conduct familiarization of NASA operating personnel with Atlas launch procedures.
  7. To evaluate the loads on the spacecraft during the actual flight environment.
  8. To evaluate operation of the spacecraft control system
MA-2 February 21, 1961
  1. To determine the integrity of the spacecraft structure, ablation shield, and afterbody shingles for a reentry from a critical abort.
  2. To evaluate the performance of the operating spacecraft systems during the entire flight.
  3. To determine the spacecraft full-scale motions and afterbody heating rates during reentry from a critical abort.
  4. To evaluate the compatibility of the spacecraft escape systems with the Mercury-Atlas system.
  5. To establish the adequacy of the location and recovery procedures.
  6. To determine the closed-loop performance of the Abort Sensing and Implementation System.
  7. To determine the ability of the Atlas booster to release the Mercury spacecraft at the position, altitude, and velocity defined by the guidance equations.
  8. To evaluate the aerodynamic loading vibrational characteristics and structural integrity of the LO2 boiloff valve, tank dome, spacecraft adapter and associated structures
MA-4 September 13, 1961
  1. To demonstrate the integrity of the spacecraft structure, ablation shield, and afterbody shingles for a normal reentry from orbital conditions.
  2. To evaluate the performance of the Mercury spacecraft systems for the entire flight.
  3. To determine the spacecraft motions during a normal reentry from orbital conditions.
  4. To determine the Mercury spacecraft vibration environment during flight.
  5. To demonstrate the compatibility of the Mercury spacecraft escape system with the Mercury-Atlas system.
  6. To determine the ability of the Atlas booster to release the Mercury spacecraft at the prescribed orbital insertion conditions.
  7. To demonstrate the proper operation of the network ground command control equipment.
  8. To evaluate the performance of the network equipment and the operational procedures used in establishing the launch trajectory and booster cutoff conditions and in predicting landing points.
  9. To evaluate the applicable ground communications network and procedures.
  10. To evaluate the performance of the network aquisition aids, the radar tracking system, and the associated operational procedures.
  11. To evaluate the telemetry receiving system performance and the telemetry displays.
  12. To evaluate the spacecraft recovery operations, as to the equipment and procedures used for communications and for locating and recovering the spacecraft, for a landing in the Atlantic Ocean along the Mercury network.
  13. To obtain data on the repeatability of the booster performance of all Atlas missile and ground systems.
  14. To determine the magnitude of the booster sustainer/vernier residual thrust after cutoff.
  15. To evaluate the performance of the Abort Sensing and Implementation System.
  16. To evaluate and develop applicable Mercury Network countdown and operational procedures.
  17. To evaluate the Atlas booster with regard to engine start and potential causes for combustion instability
MA-5
Primate aboard		 November 29, 1961
  1. To demonstrate the performance of the Environmental Control System by utilizing a primate during an orbital mission.
  2. To demonstrate satisfactory performance of the spacecraft systems throughout a Mercury orbital mission.
  3. To determine by detail measurements, the heating rate and the thermal effects throughout the Mercury spacecraft for all phases of an orbital mission.
  4. To exercise the satellite clock.
  5. To determine the ability of the Atlas booster to release the Mercury spacecraft at the prescribed orbital insertion condition.
  6. To demonstrate satisfactory performance of the Mercury Network in support of an orbital mission.
  7. To demonstrate the ability of the Flight Controllers to satisfactorily monitor and control an orbital mission.
  8. To demonstrate the adequacy of the recovery plans for an orbital mission; particular emphasis is required for the spacecraft occupant.
  9. To evaluate the performance of the Abort Sensing and Implementation System.
  10. To determine the magnitude of the booster sustainer/vernier residual thrust or impulse after cutoff.
  11. To obtain data on the repeatability of the booster performance of all Atlas mission and ground systems.
  12. To evaluate the Mercury Network countdown and operational procedures.
  13. To evaluate the Atlas booster with regard to engine start and potential causes for combustion instability
MA-6
Manned		 February 20, 1962
  1. To evaluate the performance of man-spacecraft system in a three-orbit mission.
  2. To evaluate the effects of space flight on the astronaut.
  3. To obtain the astronaut's evaluation of the operational suitability of the spacecraft and supporting systems for manned space flight
MA-7
Manned		 May 24, 1962
  1. To evaluate the performance of man-spacecraft system in a three-pass orbital mission.
  2. To evaluate the effects of space flight on the astronaut.
  3. To obtain the astronaut's opinions on the operational suitability of the spacecraft systems.
  4. To evaluate the performance of spacecraft systems replaced or modified as a result of previous missions.
  5. To exercise and evaluate further the performance of the Mercury Worldwide Network
MA-8
Manned		 October 3, 1962
  1. To evaluate the performance of the man-spacecraft system in a six-pass orbital mission.
  2. To evaluate the effects of an extended orbital space flight on the astronaut and to compare this analysis with those of previous missions and astronaut-simulator programs.
  3. To obtain additional astronaut evaluation of the operational suitability of the spacecraft and support systems for manned orbital flights.
  4. To evaluate the performance of spacecraft systems replaced or modified as a result of previous three-pass orbital missions.
  5. To evaluate the performance of and exercise further the Mercury Worldwide Network and mission support forces and to establish their suitability for extended manned orbital flight
MA-9
Manned		 May 15, 1963
  1. To evaluate the effects on the astronaut of approximately one day in orbital flight.
  2. To verify that man can function for an extended period in space as a primary operating system fo the spacecraft.
  3. To evaluate in a manned one-day mission the combined performance of the astronaut and a Mercury spacecraft specifically modified for the mission