Appendix 5

Apollo Program Flight Objectives

Apollo Mission A-002 (December 8, 1964)

First Order Objectives:

1. Demonstrate satisfactorily launch escape vehicle performance utilizing the canard subsystem and boost protective cover and to verify the abort capability in the maximum-dynamic pressure region with conditions approximating emergency detection system limits.
2. Deliver the Apollo boilerplate spacecraft to the desired conditions for demonstration of the launch escape vehicle.

Second Order Objectives:

1. Determine the performance of the launch escape vehicle in the maximum-dynamic pressure region.
2. Demonstrate satisfactorily launch escape vehicle power-on stability for abort in the maximum-dynamic pressure region with conditions approximating emergency detection subsystem limits.
3. Demonstrates satisfactory canard deployment, launch escape vehicle turnaround dynamics, and main heatshield forward flight stability prior to launch escape subsystem jettison.
4. Demonstrate satisfactory separation of the launch escape system plus boost protective cover from the command module.
5. Demonstrate satisfactory operation and performance of the emergency landing system using reefed dual drogues.
6. Determine the command pressure loads, including possible plume impingement, in the maximum dynamic pressure system.

Apollo Mission A-003 (May 19, 1965)

First Order Objectives:

1. Demonstrate satisfactory launch escape vehicle performance at an altitude approximating the upper limit for the canard subsystem.
2. Demonstrate orientation of the launch escape vehicle to a main heatshield forward attitude.
3. Deliver the Apollo boilerplate spacecraft to the desired conditions for demonstration of the launch escape vehicle.

Second Order Objectives:

1. Determine the damping of the launch escape vehicle oscillations with the canard subsystem deployed.
2. Demonstrate jettison of the launch escape system plus boost protective cover after high-altitude entry.

Pad Abort Test 2 (June 29, 1965)

First Order Objective:

1. Demonstrate the capability of the launch escape vehicle, equipped with a canard subsystem and a boost protective cover, to abort from the launch pad and recover.

Second Order Objectives:

1. Determine the performance and stability characteristics of the launch escape vehicle with boost protective cover and control weight command module.
2. Determine the turnaround dynamics of the launch escape vehicle following canard deployment.
3. Demonstrate satisfactory separation of the launch escape subsystem and boost protective cover from the command module.
4. Demonstrate proper event sequencing during abort from the launch pad and recovery.

Apollo Mission A-004 (January 20, 1966)

First Order Objectives:

1. Demonstrate satisfactory launch escape vehicle performance for an abort in the power-on tumbling boundary region.
2. Demonstrate the structural integrity of the launch escape vehicle airframe structure for an abort in the power-on tumbling boundary region.
3. Deliver the Apollo spacecraft to the desired conditions for demonstration of the launch escape vehicle.

Second Order Objectives:

1. Demonstrate the capability of the canard subsystem to satisfactorily reorient and stabilize the launch escape vehicle heatshield forward after a power-on tumbling abort.
2. Demonstrate the structural capability of the production boost protective cover to withstand the launch environment.
3. Demonstrate the capability of the command module forward heatshield thrusters to satisfactorily separate the forward heatshield after the tower has been jettisoned by the tower jettison motor.
4. Determine the static loads on the command module during launching and abort sequence.
5. Determine the dynamic loading on the command module inner structure.
6. Determine the dynamic loads and the structural response of the service module during launch.
7. Determine the static pressures imposed on the command module by free stream conditions and launch escape motor plumes during a power-on tumbling abort.