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development the F136 produced by General Electric in conjunction with Rolls-Royce had its funding reinstated. Some of the requirements of the four sponsoring Services appear to be diametrically opposing in terms of achieving a nal solution and present severe challenges. Nevertheless, if a high degree of commonality can be maintained between the competing variants and/or requirements then the US military authorities will have achieved a degree of standardisation which will doubtless yield signi cant bene ts of scale: both to the operational Services and the taxpayer on both sides of the Atlantic
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10.9 Technology Developments/Demonstrators
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Supporting the F-35 ight demonstration programme is the JSF Integrated Subsystems Technology (J/IST) Demonstrator Program. Key among the aircraft systems related demonstrations are: Fault Tolerant 270VDC electrical power generation system Thermal and Energy Management Module (T/EMM) AFTI F-16 EHA Demonstration
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10.9.1 Fault Tolerant 270VDC Electrical Power Generation System
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The J/IST electrical power generation and distribution system as tted to the NASA Dryden Advanced Fighter Technology Integration (AFTI) F-16 is based upon an 270 VDC 80 KW switched reluctance starter/generator incorporating a dual channel converter/controller supplied by Sundstrand. The aircraft also has a 270 VDC 15 KW emergency generator. This system provides ight critical power by means of two independent 270 VDC aircraft buses as shown in Figure 10.21. Each 270 VDC bus feeds one half of a Power Drive Electronics unit (PDE) of which there is one per primary ight control surface. The PDE in turn controls one half of the Parker Aerospace dual tandem 270 VDC EHA. All of the ight control actuator EHAs are supplied by a consortium of Parker Aerospace and Moog. Five main ight control actuators so powered are: Left aperon Right aperon Left horizontal tail Right horizontal tail Rudder
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10.9.2 Thermal and Energy Management Module
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The Thermal and Energy Management Module (T/EMM) combines the function of a traditional APU, emergency power unit and environmental control
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Technology Developments/Demonstrators
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80 KW Starter Generator 15 KW Emergency Generator 270VDC Battery Converter Controller 1 Converter Controller 2
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PDE 2
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Left Flap
Left HT
Rudder
Right HT
Right Flap
AFTI F-16 simpli ed 270 VDC system
system. This allows the conventional AMAD to be removed as is the aircraft central hydraulics system. The engine fan duct air is used as the heat sink thereby removing the usual heat exchangers and associated ducting. Extensive operation of the Honeywell (Allied Signal) supplied T/EMM has been accomplished during subsystem rig testing prior to engine and T/EMM integration in early 2000.
10.9.3 AFTI F-16 Flight Demonstration
The AFTI F-16 is the ight test bed for the ying elements of the J/IST demonstration programme. The aircraft has been modi ed to accommodate the 270 VDC architecture shown in Figure 10.22. The ve PDEs each drive a dualtandem actuator supplied by Parker Aerospace; one for each ight control surface as already mentioned. PDE channels 1 and 2 each drive a brushless DC motor which in turn powers half of the actuator package; a PDE channel performs loop closure around its respective components. Each half of the actuator comprises a motor, pump, local uid reservoir and a valve assembly. As the name suggests, normally both channels operate in tandem. The valve assemblies ensure that each channel can drive the actuator ram if the other channel fails. In the event of both channels failing, aerodynamic pressure drives the control surface to central position where it becomes hydraulically locked. A simpli ed schematic of the dual-tandem actuator is at Figure 10.22.
PDE 1 PDE 2
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M Reservoir P Valve
Motor
M Reservoir
Pump
P Valve
Actuator Stroke
Simpli ed schematic of J/IST dual-tandem actuator
The control side of the implementation posed the problem of interfacing the existing quadruple-redundant Digital Flight Control Computer (DFCC), with the ve new PDE actuator drive packages. This was achieved by the introduction of a new triple-redundant control electronics unit which interfaces the old digital ight control system with the new PDEs and actuators. For a comprehensive overview of the AFTI F-16 system see Schley and Kotalik [15]. A three-dimensional diagram of the AFTI F-16 is at Figure 10.23 though the aircraft external appearance yields no clue as to the major systems modi cations which are contained therein.
NASA Dryden AFTI F-16 (Courtesy of NASA)