Title:
【発明の名称】航空機慣性基準装置の囲い
Document Type and Number:
Japanese Patent JPS61501944
Kind Code:
A
Abstract:
An enclosure for an aircraft inertial unit (IRU) includes a dip-brazed chassis (10) having an inertial sensor assembly (ISA) compartment (40) and an electronics module compartment (36). The ISA compartment (40) is rigid with the ISA (42) being mounted therein via diagonally opposed shock isolation mounts (330, 332). The centers of elasticity of the shock isolation mounts (330, 332) are aligned with the center of gravity of the ISA. A caging system (340, 342) prevents excessive movement of the ISA (42) with respect to the ISA compartment (40). The electronics module compartment (36) includes a thermal mass (62, 64) for heat sinking the electronics module (60) by conduction. The surfaces of the walls in the electronics module (60) are heat reflective to prevent heat in the enclosure from being radiated to the electronics module (60). The remaining surfaces of the enclosure are black to promote heat radiation. The IRU enclosure is mounted to the aircraft by means of a mounting tray (12). The tray (12) has diagonally positioned alignment pins (150, 152) that mate with alignment holes in the IRU enclosure (10) to assure proper IRU alignment. Pliant, heat conductive fingers (136) affixed to the tray (12) contact the thermal mass (62, 64) to promote heatflow from the enclosure (10) to the tray. Thermally conductive feet (140, 142) on the tray provide a path for heat flow to the aircraft.
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Inventors:
Nye, William S
Application Number:
JP50209185A
Publication Date:
September 04, 1986
Filing Date:
April 18, 1985
Export Citation:
Assignee:
Sandstrand Data Control-Le Inco-Polled
International Classes:
B64D43/00; G01D11/24; G01C21/16; (IPC1-7): B64D43/00; G01C21/16; G01D11/24
Attorney, Agent or Firm:
Soga Doteru