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Listed below are the locations of the various modifications made to the HIAPER platform. More detailed information regarding the engineering specifications for the modifications made and the research systems incorporated into the GV can be found in the GV Investigator's Handbook.
Aperture Pads and Plates
(8 Total, 6 Upper Fuselage and 2 Lower)
Description: Each pad/plate is 10 in. long and 7 in. wide. Investigators are advised that the volume available behind (i.e., inside the fuselage) is not the same for each aperture plate. Please contact the HPO for additional information.
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Upper fuselage (6 total) locations:
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Pad #1:
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GVFS 255.5, LBL 13.91
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Pad #2:
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GVFS 255.5, RBL 13.91
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Pad #3:
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GVFS 328.5, BL 0.0
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Pad #4:
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GVFS 434.0, LBL 14.84
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Pad #5:
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GVFS 498.0, RBL 14.84
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Pad #6:
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GVFS 532.0, LBL 21.7
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Lower fuselage (2 total) locations:
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Plate #1:
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GVFS 250.0, LBL 9.0
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Plate #2:
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GVFS 250.0, RBL 9.0
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Fuselage Mounts [top]
(8 Total, 4 Upper Fuselage and 4 Lower)
Description: Each mount is 4.25 in. long and 3.0 in. wide and has a 1.75-in. diameter hole in the center of the mount to which a second plate can be mounted externally to attach inlets, bulkhead feed-through connectors, or lugs for securing fairings.
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Upper fuselage mount (4 total) locations:
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Upper mount #1:
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GVFS 271.0, BL 0.0
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Upper mount #2:
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GVFS 310.0, BL 0.0
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Upper mount #3:
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GVFS 346.0, BL 0.0
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Upper mount #4:
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GVFS 421.8, LBL 14.8
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Upper fuselage mount (4 total) locations:
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Lower mount #1:
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GVFS 235.0, BL 0.0
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Lower mount #2:
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GVFS 235.0, LBL 19.97
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Lower mount #3:
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GVFS 270.91, BL 0.0
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Lower mount #4:
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GVFS 310.23, BL 0.0
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Forward Fuselage Pads [top]
(6 Total, 3 Left Side and 3 Right Side)
Description: Each forward fuselage pad is a mounting plate 4.75 inches by 4.5 inches that has a 2.0-inch diameter hole in the center of the pad to allow for the mounting/internal clearance of a cylinder 2.0 inches in diameter and 4.0 inches in length. It should be noted that at present, NCAR intends to use five to six of the forward fuselage pads for the mounting of state parameter (e.g., temperature, dew point, and pitot) sensors on the aircraft.
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Left side forward fuselage pad (3 total) locations:
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Left side pad #1:
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GVFS 54.0, WL 105.54, LBL 19.0
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Left side pad #2:
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GVFS 82.0, WL 65.8, LBL 27.95
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Left side pad #3:
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GVFS 82.0, WL 60.4, LBL 21.93
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Right side forward fuselage pad (3 total) locations:
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Right side pad #1:
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GVFS 54.0, WL 105.54, RBL 19.0
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Right side pad #2:
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GVFS 82.0, WL 65.8, RBL 27.95
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Right side pad #3:
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GVFS 82.0, WL 60.4, RBL 21.93
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Optical View Ports [top]
(3 Total)
Description: Three (3) 20.5-inch diameter optical view ports are installed on the aircraft centerline in the forward section of the GV fuselage. Two of the view ports are down-looking and one is upward-looking. The forward down-looking and up-looking ports are co-aligned vertically. Additionally, this pair of view ports overlaps with the forward-most window on each side of the aircraft, thereby providing users with the opportunity to perform remote sensing measurements in the up-, down-, and side-looking directions from one instrument mount location. The view ports are designed to provide an unobstructed view from within the GV cabin to the exterior of the aircraft and to accommodate flat user-supplied optical glass windows.
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Optical view port (3 total) locations:
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Up-looking view port:
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GVFS 290.5, BL 0.0, WL 142.5 for
internal mounting surface
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Forward down-looking
view port:
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GVFS 290.5, BL 0.0, WL 58.25 for
internal mounting surface
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Aft down-looking
view port:
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GVFS 339.5, BL 0.0, WL 58.25 for
internal mounting surface
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Wing Hard Points [top]
(6 Total, 3 Underneath Each Wing)
Description: Each hard point can carry a maximum static load of 1,450 lbs. This load includes the weight of the wing pod, fairing, and rack mount hardware. Installed hard points are compatible with USAF/NATO rack mount specifications, and each hard point can accommodate either 14-inch or 30-inch rack mount hardware. Power and signal wiring is provided to each wing hard point; see Section 2.3.2 of the GV Investigator's Handbook for additional information. Investigators wishing to deploy instrumentation in wing pods on the aircraft should also note that a pod of similar size and configuration needs to be deployed on the opposite wing of the aircraft from the primary instrumentation pod. However, it is not necessarily the investigator’s responsibility to provide this second wing pod.
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Wing hard point (6 Total, 3 Underneath Each Wing) locations:
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Inboard, each wing:
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BL 123.017, canted 0.22 degrees
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Middle, each wing:
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BL 192.787, canted 1.25 degrees
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Outboard, each wing:
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BL 264.133, canted 2.08 degrees
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Modification Views [top]
View of GV upper fuselage, showing inlet aperture pads (green and red), optical view port (light blue), fuselage mounts (dark blue), and two forward fuselage pads below windscreen (grey circles). Drawing courtesy of Lockheed Martin.:
View of GV lower fuselage, showing instrument aperture plates (green), optical view ports (light blue), fuselage mounts (dark blue), and four forward fuselage pads (grey circles). Drawing courtesy of Lockheed Martin.:
View of GV from above showing locations of six (6) under wing hard points with notional wing stores mounted at each hard point:
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