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Aviation History
1973
1973 - 0156.PDF
98 FLIGHT International, IS January 1973 BOEING'S SUB-HUNTER The information presented on the pilot's tactical display developed by IBM for the Boeing maritime- reconnaissance 707 includes: Aircraft present position Aircraft track angle Ninety second predicted track (curved) across the ground or ocean Minimum descent range prediction Current descent range prediction Four long-range navigation waypoints Three course line vectors between long-range navigation waypoints Fifteen sonobuoys Five MAD marks Ten hook points Four range circles Two bearing lines Ten fly-to points One range and bearing cursor with range and bearing between the aircraft and any display point or between any two display points Display scale annotation Self test patterns and cues Flight artist Michael Badrockehas used details of the equipment installed in the test aircraft and the proposed layout of the definitive aircraft to draw this illustration of 707-ASW occur. Excellent handling characteristics have been demonstrated during exten sive low-altitude flight tests with the control-wheel steering and the altitude- hold engaged. The system has allowed accurate altitude control during rapid manoeuvres and changes to power or flap settings. The flight-control system includes a turn coordinator, which reduces side-slip and is effective up to the maxi mum roll rate together with a yaw damper. An auto-throttle assists air speed control throughout the flight envelope During low-speed, low-alti tude anti-submarine manoeuvres the autopilot provides flightpath angle and track angle control and may be coupled to the tactical computer for automatic calibration of the Magnetic Anomoly Detection (MAD) system. A low-altitude monitor and warning system has also been developed and installed to increase safety during let down and during flight at low-altitude. Dual flight-path angle and radar alti meter inputs are used by this warning system. The 720 test aircraft has been used to determine the feasibility of dual wingtip-mounted MAD booms. The boom tips were designed to accept the AN/ASQ 10 or AN/ASQ 501 detector heads. Three different boom lengths, allowing the detector to be located between 5ft and 10ft (l-5m to 3m) behind the wing trailing edge, have been flown to determine the optimum boom length for production aircraft. According to Boeing, tests have shown that the wingtip is an excellent loca tion for the boom and a dual system results in improved submarine detec tion and location. Two Boeing designed and fabricated sonobuoy launch tubes are installed in the test aircraft, one is mounted ver tically and the other 30° to the ver tical. Storage racks are provided for up to 100 sonobuoys. Separation of sono buoys from the aircraft has been in vestigated using both cartridge assisted and free-fall release. Cart ridge-assisted launches have been made at altitudes between 1,000ft and 40,000ft and at airspeeds up to 400kt, 700km/hr TAS. Free-fall drops have been made at low altitude (below 3,000ft) at airspeeds from 180kt to 240kt, 315km/hr to 420km/hr. Thirty in-flight launches have been carried out with complete success, excellent separation being obtained under all conditions. A comprehensive navigation system is planned for production aircraft and the development 720 has been used to evaluate each piece of equipment to assess the best method of integration
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