摘要 :
This is a report of COMOPTEVFOR's first phase of follow-on operational test and evaluation (OT-IIIC), as defined in references (a) and (b), of the Global Positioning System (GPS) as installed in the ES-3A, performed under CNO Proj...
展开
This is a report of COMOPTEVFOR's first phase of follow-on operational test and evaluation (OT-IIIC), as defined in references (a) and (b), of the Global Positioning System (GPS) as installed in the ES-3A, performed under CNO Project 190-4. The purpose of the evaluation was to determine the reliability, maintainability, and availability of the AN/ARN-151 GPS User Equipment, as installed in the ES-3A, in an aircraft carrier environment. The GPS user equipment (UE) is determined to be operationally suitable. Approval for extension of application to platforms which require catapult launches and arrested landings is recommended.
收起
摘要 :
This report presents the results of field test measurements to define the noise produced on the ground by military, fixed wing aircraft during controlled level flyovers and ground runups. For flight conditions, data are presented ...
展开
This report presents the results of field test measurements to define the noise produced on the ground by military, fixed wing aircraft during controlled level flyovers and ground runups. For flight conditions, data are presented in terms of various acoustic measures over the range 200-25,000 feet minimum slant distance to the aircraft. For ground runups, data are presented as a function of angle and distance to the aircraft. All of the data are normalized to standard acoustic reference conditions of 59 deg. F temperature and 70% relative humidity. Noise data are presented in this Volume 3 for the following aircraft: A-7D, E; A-10A; A-37B; F-4C, D, E, F; F-5A, B; F-5E, F; F-15A; F-16A; F-104C, D, G; F-111A, E; F-111D, and F-111F.
收起
摘要 :
This series of reports presents the results of field test measurements to define the noise produced on the ground by military, fixed wing aircraft during controlled level flyovers and ground runups. For flight conditions, data are...
展开
This series of reports presents the results of field test measurements to define the noise produced on the ground by military, fixed wing aircraft during controlled level flyovers and ground runups. For flight conditions, data are presented in terms of various acoustic measures over the range 200-25,000 feet minimum slant distance to the aircraft. For ground runups, data are presented as a function of angle and distance to the aircraft. All of the data are normalized to standard acoustic reference conditions of 59 F temperature and 70% relative humidity. Noise data are presented in this volume for the following aircraft: A-3, TA-4J; RA-56; A-6A; AV-8A; F-8; F-14A; P-3A; S-3A; and T-2C.
收起
摘要 :
In the 1980s the Navy began a program that would replace its aging fleet of A-6 medium attack aircraft with a new aircraft-the A-12-that would incorporate stealth technology and could be deployed from an aircraft carrier. In Janua...
展开
In the 1980s the Navy began a program that would replace its aging fleet of A-6 medium attack aircraft with a new aircraft-the A-12-that would incorporate stealth technology and could be deployed from an aircraft carrier. In January 1988 the Navy awarded a fixed-price incentive contract for full-scale development of the A-12 to the team of General Dynamics and McDonnell Douglas Corporations. The contract had a target price of $4.4 billion and a ceiling price of $4.8 billion. On January 7, 1991, the Navy terminated the A-12 contract for default due to difficulties the contractors had in executing the contract. As we reported in March 1991, expenditures on the contract, which amounted to $2.7 billion, had not exceeded the contract's $4.4 billion target price. However, we also reported in July 1991 that, at the time of termination, the Navy was projecting the contractors would overrun the contract's ceiling price of $4.8 billion and that the A-12's first flight would be delayed by over 2 years. When the contract was terminated, the Secretary of Defense acknowledged that the Navy still needed to develop a next-generation replacement for its A-6 strike aircraft.
收起
摘要 :
This report consists of a table and accompanying illustrations which describe aircraft and weapons system functions displayed on the head-up displays in the A-7E, F-5, F-14, F-15, F-111A, CL-84, and AV-8A aircraft. Corresponding d...
展开
This report consists of a table and accompanying illustrations which describe aircraft and weapons system functions displayed on the head-up displays in the A-7E, F-5, F-14, F-15, F-111A, CL-84, and AV-8A aircraft. Corresponding display formats as given in MIL-D-81641(AS) and MIL-STD-884B are included for comparison.
收起
摘要 :
Flight data collected during scheduled Airbus A-310 flights by a Digital AIDS Recorder (DAR) were analyzed. The characteristics of the standard A-310 AIDS are compared to those of the A-300 AIDS. The A-310 reconstruction of the mo...
展开
Flight data collected during scheduled Airbus A-310 flights by a Digital AIDS Recorder (DAR) were analyzed. The characteristics of the standard A-310 AIDS are compared to those of the A-300 AIDS. The A-310 reconstruction of the motion state of the aircraft is more complete than with the older equipment. The DAR A-310 permits a detailed and extensive check of the basic AIDS measuring channels through independently measured quantities. This check, however, is restricted to the measuring ranges encountered in normal flight conditions. It cannot be extrapolated to extreme flight conditions expected in accidents or incidents. In the flight conditions of the scheduled flights, the correspondence between basic AIDS measurements and quantities from the extended AIDS is very good.
收起
摘要 :
Combat experience in Vietnam suggested that a correlation might exist between aircraft losses to gunfire and the amount (density) of smoke emitted by the aircraft. In connection with Joint Task Force Two (JTF-2) testing of aircraf...
展开
Combat experience in Vietnam suggested that a correlation might exist between aircraft losses to gunfire and the amount (density) of smoke emitted by the aircraft. In connection with Joint Task Force Two (JTF-2) testing of aircraft vulnerability to air defense weapons, preliminary tests on the smoke factor were conducted using manual data collection. Comparisons were made on the detection times--using different courses, altitudes, and test sites--for two types of aircraft that differ significantly in the amount of smoke emitted.
收起
摘要 :
Statistical analyses methodologies, such as analysis of variance, non-parametric tests and hypothesis tests were applied to uncover trends and dependencies of ejection-related injuries. Ejection-related fatality patterns for the A...
展开
Statistical analyses methodologies, such as analysis of variance, non-parametric tests and hypothesis tests were applied to uncover trends and dependencies of ejection-related injuries. Ejection-related fatality patterns for the A-6 aircraft were developed deterministically. The A-4, A-5, A-6, A-7, F-4, F-8 and F-9 ejection-related injuries were investigated, and parent probability density functions derived. The A-4, A-6, A-7, F-4 and F-8 contain an underlying injury trend. Fatalities occur randomly upon ejection from the A-4, A-7, F-4 and F-8 aircraft. Fatalities do not occur randomly from the A-6 aircraft. Differences were revealed among various ejection fatality scenarios: hardware hazards, aircrew judgment, environmental conditions, aircraft associated with ejections, and ejection seats used in ejection. (Author)
收起
摘要 :
The Tactical Air Command (TAC) and Aerospace Defense Command (ADC) have requested USAF Instrument Flight Center (USAFIFC) include Head-Up Display (HUD) information in Air Force Manual 51-37. The TAC and ADC requests are of extreme...
展开
The Tactical Air Command (TAC) and Aerospace Defense Command (ADC) have requested USAF Instrument Flight Center (USAFIFC) include Head-Up Display (HUD) information in Air Force Manual 51-37. The TAC and ADC requests are of extreme importance since HUD systems are presently installed in the A-7D, A-10, F-15, and F-111D aircraft and there is an expanding emphasis toward installing HUD systems in future aircraft. The role of HUD in an instrument environment must be defined to ensure its optimum operational utilization during various instrument flight regimes. A pilot factors survey was conducted to determine: (1) The present use of HUDs during instrument flight by USAF pilots; and (2) Problems encountered by USAF pilots while using HUDs during instrument flight.
收起
摘要 :
This report presents the results of field test measurements to define the noise produced on the ground by military, fixed wing aircraft during controlled level flyovers and ground runups. For flight conditions, data are presented ...
展开
This report presents the results of field test measurements to define the noise produced on the ground by military, fixed wing aircraft during controlled level flyovers and ground runups. For flight conditions, data are presented in terms of various acoustic measures over the range 200-25,000 feet minimum slant distance to the aircraft. For ground runups, data are presented as a function of angle and distance to the aircraft. All of the data are normalized to standard acoustic reference conditions of 59 deg. F temperature and 70% relative humidity. Noise data are presented in this Volume 4 for the following aircraft: F-100C, D, F; F-101B, C, F; F-102A; F-105B, D, F, G; F-106A, B; T-33A; T-37B; T-38A; T-39A, B, F; T-43A; and U-2.
收起
