in the aft crew compartment. 2.3.6 Location in Aircraft Location of the sensing devices and instrumentation equipment installed in the two aircraft is described for each aircraft in the sub-paragraphs below. The instrumentation of the individual aircraft was not changed between Mike and King Shots. For Shot 9, additional instrumentation was added to the B~36 empennage. 2.3.6.1 Fig. 2.5 Pyions, Left Wing B=36 Aircraft B-36 Aircraft The location of sens~ ing elements and recording equip- ment utilized on the Be36 air craft for IVY is shown schematically in Fig. 2.7. The code numbers are used to cross-reference Fig. 2.7 and Table 2.1 which supply additional detail on the various installations. The aircraft was instrumented for 14 resronse and two inout measurements. The pressure transducers were mounted in the boom on the left wing, shown in Fig. 2.7, to minimize the influence cf the aircraft on the free air overpressure measurement. inctrumentation was located either in the fuselage or the left side of the aircraft, except for one bending gage installed in the right wing to check loading symmetry. The metnod of installing and electrically connecting the various gages has been discussed earlier in paragraph 2.3.2, which also includes sketches of typical installations. The oscillographs and associate equipment were located in the aft crew compartment shown in Fig. 2.8. The view shows the left side of the compartment looking forward. The table occupies the space normally used by the lower bunk. Two of the four oscillographs mounted on the table are shown. The oscillograph in the foreground was used to re~ cord blast data; the remaining three were used to record thermal data, To facilitate switching from main to spare gages an_ to permit recording any of the gage outputs on any of the 16 channels, a selector panel, shown in F ig. 2.9, was installed, The bridge balances employed The high frequency pressure recorder used in the measure~ re also shown. » A controlled manually by a switch oF f Ce oe ep eae # Operation of the cameras was ORT We Figure 2.6 shows the camera installation with the cover off and cover in place, ren, lage. wy we eee ve merge ot ont RT Pts +ee . ale ’ ate “1? Fb. .- respectively. The cameras were disposed as follows: one GSAP and one Camera-Flex camera viewing,the left wing, one GSAP and one Camera-Flex camera viewing the tail, and one GSAP camera sighting for~ ward along the top of the fuse-