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*No torsional test performed on RA-6; PTM levels were 11 G Zero to Peak (O-P) at spacecraft feet.

Noise

±6 G Noise

See B2

and Fig. 4-2 and 4-4

See B2 and

Fig. 4-2 and 4-4

See Fig. 4-9 for
noise portion of
test (same for all
Spacecraft axes)

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The duration

The test level was based on the expected 95 percentile level. (number of cycles of sine wave) was derived such that the shock spectrum of the flight was enveloped by the laboratory pulse shock spectrum. The sine sweep was selected such that the spacecraft, at its resonant frequency on the fixture, would respond to the approximate G level as experienced during the transient test. Figures 4-6 and 4-7 are reproductions of a section of the flight record covering BECO and booster jettison, respectively. Figure 4-8 is a reproduction of a section of the flight record at Channel 8 Off.

C.

RANGER 6 VIBRATION FLIGHT ACCEPTANCE TESTING

The RA-6 spacecraft was subjected to the following tests, as described in JPL Specification 50107, along each of three (x, y and z) spacecraft axes:

1)

A low frequency sinusoidal sweep test from 10-100-10 cps.

2)

A high frequency sinusoidal sweep test from 100-2000-100 cps.

3) A gaussian noise test bandlimited between 100 and 2000 cps.

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2.

1) Lateral Axes (x, y), 0.5 G rms 10-100-10 cps 149 sec.
2) Axial (z) 1.0 G rms 10-100-10 cps 149 sec.

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2

/cps

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1)

White gaussian noise, wideband power spectral density 0.012 g2/
(2.05 G rms), bandlimited between 100 and 450 cps.

2)

White gaussian noise, wideband power spectral density 0.040 g2/cps (7.90 G rms), bandlimited between 450 cps and 2000 cps.

Test duration 16 sec.

The RA-6 spacecraft performed normally during and after the vibration tests. A similar set of tests was performed to 3 db higher levels on the PTM spacecraft (JPL Specification 50071).

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