NASA Sounding Rocket Program Handbook. - NASA Visitor Center ...
NASA Sounding Rocket Program Handbook. - NASA Visitor Center ...
NASA Sounding Rocket Program Handbook. - NASA Visitor Center ...
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810-HB-SRP<br />
canards are mounted in pairs on two orthogonal shafts. Each pair of canards is deflected<br />
by a pneumatic servo that is supplied with nitrogen or air from a pressure vessel.<br />
Guidance Scheme<br />
Table 3.3.1 NSROC Boost Guidance Systems<br />
S-19/D/G Family<br />
Rail Attitude Hold<br />
Guides to a specific attitude<br />
specified by the launch rail QE and<br />
AZ<br />
DS-19/GS-19 Family<br />
Integrated Impact Point<br />
Guides to a preprogrammed IIP<br />
and continually updates throughout<br />
the burn phase<br />
Dispersion Specifics<br />
Onboard Sensor(s)<br />
Canards decouple at t + 18 seconds.<br />
Impact dispersion (3s theoretical)<br />
Down Range = 7.5% of apogee<br />
Cross Range = 7.5% of apogee<br />
S-19: MIDAS roll stabilized gyro<br />
platform (position gyros)<br />
S-19D: DMARS Inertial<br />
Measurement Unit (rate gyros,<br />
accels)<br />
S-19G: GLN-MAC-200<br />
incorporating roll gimbal mounted<br />
LN-200 Fiber Optic Gyro<br />
Canards decouple at t + 45 seconds<br />
Impact dispersion (3S theoretical)<br />
Down Range = 2% of apogee<br />
Cross Range = 1.2% of apogee<br />
DS-19: DMARS Inertial<br />
Measurement Unit (rate gyros,<br />
accels)<br />
GS-19: GLN-MAC-200 (software<br />
not yet available for IIP<br />
computation).<br />
A guidance system operates during the first 18 seconds of flight. Figures 3.3.1-1a and 3.3.1-1b<br />
are photos of the S-l9 Boost Guidance System. Figure 3.3.1-2 is a photo of the DS-19 Boost<br />
Guidance System.<br />
Figure 3.3.1-1a: S-19 Boost Guidance System<br />
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