4-1

Statistical Distribution of Spacecraft Acceleration Spectra During
Liftoff Based on Five Ranger Flight Measurements

.......

4-3

4-2

4-3

RA-6 Vibration Levels Corrected to RA-1 Through RA-5 During Liftoff.
Statistical Distribution of Spacecraft Acceleration Spectra During
Transonic Flight Based on Five Ranger Flight Measurements . . . . . .

4-4

4-5

4-4

4-5

RA-6 Vibration Levels Corrected to RA-1 Through RA-4 During Transonic
RA-6 Flight, IRIG Channel 18

4-6

4-9

4-9

5-1

RA-6 Measured Flight Vibration Corrected to the Spacecraft Flight.
Analog Record of Channel 8 During Cruise Mode

4-15

5-2

Reduced Channel 8 Telemetry Voltages at Prelaunch and During
Inadvertent Turn-On

5-10

5-3

5-4

5-5

Reduced Channel 8 Telemetry Voltages Following Separation
Reduced Channel 8 Telemetry Voltages During Terminal Phase
RA-6, Full Mission Telemetry Plot, Channel 8, Point 3, F-Battery
Internal Temperature

5-11

5-12

5-13

5-6

RA-6, Full Mission Telemetry Plot, Channel 8, Point 4, P-Battery

Number

ILLUSTRATIONS (cont)

Title

Page

5-7

RA-6, Mission Telemetry Plot, Channel 8, Point 7, Top Hat,
Temperature, (-Y Axis)

5-15

5-8

RA-6, Mission Plot, Channel 8, Point 8, Shroud Temperature
(-Y Axis)

5-16

7-3

A-1

A-2

RA-6 Agena Separate and Spacecraft Umbilical Connectors.
RA-6, Channel 8, Point 1, Calibration Curve, Unregulated Voltage
RA-6, Channel 8, Point 2 Calibration Curve, Low Current Regulator
Output

7-6

A-6

A-7

..........

A-3

RA-6, Channel 8, Point 3 Telemetry, Calibration Curve, F Battery
Internal Temperature.

A-8

A-4

RA-6. Channel 8, Point 4, Telemetry Calibration Curve, P Battery
Internal Temperature.

RA-6, Channel 8, Point 7, Telemetry Calibration Curve, Top Hat
Temperature (-Y Axis).

Critical Area of Electrostatic Potential Versus Atmosphere (In Terms
of Altitude and Spark-gap)

E-3

F-1

Channel 17 Power Spectral Density (PSD), 2.5 to 4. 5 Seconds

F-2

F-2

F-3

Channel 17 Power Spectral Density (PSD), 41. 75 to 43. 75 Seconds.
Channel 17 Power Spectral Density (PSD), 49. 2 to 51. 2 Seconds.

F-3

F-4

ILLUSTRATIONS (cont)

Number

Title

Page

F-4

F-5

Channel 17 Power Spectral Density (PSD), 113.5 to 115. 5 Seconds.
Channel 18 Acoustic Energy -8 to 6 Seconds

F-5

F-6

F-11

F-12

High Frequency Acceleration Pickup, RA-6 Accelerometer Location.
Ratio of Acoustic Susceptances of Flight Accelerometers Configurations,
Block II Mounting, Foot A, No Diaphragm to Block III Mounting, Foot A,
No Diaphragm.

F-11

F-12

F-15

F-13

Ratio of Acoustic Susceptances of Flight Accelerometer Configurations,
Block III, Foot A, With Diaphragm to Block III Mounting, Foot A,
No Diaphragm.

F-16

F-14

Ratio of Acoustic Susceptances of Flight Accelerometer Configurations,
Block II Mounting, Foot A, With Diaphragm to Block III Mounting,
Foot A, No Diaphragm

F-17

F-15

RA-6 Measured Flight Vibration Corrected to the RA 1-4 Flight
Accelerometer Installation, Liftoff

F-18

F-16

RA-6 Measured Flight Vibration Corrected to the RA 1-4 Flight
Accelerometer Installation, Transonic

Command Decoder Mounted on C-210 Shaker for X Axis Vibration
Command RTC-7, TV Command Switch Interface.

G-10

G-14

Command and CC&S Subsystems Interface for Real Time Commands.
Frequency Analysis of Shaped Noise Vibration, Run No. 22, Plane X,
Reference Level 60 G rms, Accelerometer No. 2, Z Direction
Frequency Analysis of Shaped Noise Vibration, Run No. 22, Plane X,
Reference Level 60 G rms, Accelerometer No. 3, Z Direction
Frequency Analysis of Shaped Noise Vibration, Run No. 22, Plane X,
Reference Level 60 G rms, Accelerometer, No. 1, X Direction .
Frequency Analysis of Shaped Noise Vibration, Run No. 23, Plane X,
Reference Level 64. 5 G rms, Accelerometer No. 2, Z Direction

G-16

G-17

G-18

G-19

G-20

Number

ILLUSTRATIONS (cont)

Title

Page

G-15

G-16

G-17

G-18

H-1

Frequency Analysis of Shaped Noise Vibration, Run No. 23, Plane X,
Reference Level 64. 5 G rms, Accelerometer No. 3, Z Direction
Frequency Analysis of Shaped Noise Vibration, Run No. 23, Plane X,
Reference Level 64. 5 G rms, Accelerometer No. 1, X Direction
Frequency Analysis of Shaped Noise Vibration, Run No. 25, Plane Z,
Reference Level 64. 5 G rms, Accelerometer No. 3, Z Direction
Frequency Analysis of Shaped Noise Vibration, Run No. 25, Plane Z,
Reference Level 64. 5 G rms, Accelerometer No. 1, Z Direction
Command Switch

G-21

G-22

G-23

G-24

H-2

5-3

Woomera Channel 8 Telemetry Data During Telemetry Turn-On of
Channel 8 at S+ 17M 030:16:36:34 (Tape Playback)

5-4

5-4

Woomera Channel 8 Telemetry Data Time 030:16:49:00 to 030:16:52:00
(Tape Playback)

5-4

5-5

Goldstone Channel 8 Telemetry Data (Impact -22 Minutes to Impact
Tape Playback).

5-5

A-3

Woomera Channel 8 Telemetry Data During Telemetry Turn-On at
S+ 17M (Tape Playback)

A-3

A-4

Woomera Channel 8 Telemetry Data Time 030:16:49:00 to 030:16:52:00
(Tape Playback)

A-4

A-5

Goldstone Channel 8 Telemetry Data (Impact -22 Minutes to Impact
Tape Playback).

A-5

G-2

Detailed Summary of Tests Performed in Conjunction with the RCA
TV Command Switch.......

G-11