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Phantom88 last won the day on November 17 2015

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About Phantom88

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  1. RECON mission looking for Scud MIssile pop ups with The Harrier. Thanks for viewing friends
  2. Few screenshots popped up on DCS forums
  3. P3DV4

    Great Detail,Thx for posting.
  4. Thought this would be interesting to share here,The differences between Lot # of Hornets.The DCS Hornet will be based on a Charlie Model Lot#20 Differences between LOTS (lot means production year of the airframe, each lot includes previous upgrades etc ) Lot 12. The Lot 12 series F/A-18, introduced in FY90, provided the F/A-18 with a night attack capability. This was accomplished by providing NVG compatible cockpit lighting and displays, a thermal imaging navigation set, digital map set, multipurpose color displays, and a raster HUD. In addition, an independent aft cockpit capability was included for the two-seat F/A-18D (USMC) version. Lot 13. The Lot 13 series F/A-18 was introduced in FY91. The enhancements provided by this Lot included the OBOGS, which replaced the lox converter. The NACES and SEWARS were added and armament capabilities were enhanced through the additional hardware provisions for AGM-86 Harpoon and AGM-84 Stand-off Land Attack Missile. The Inertial Navigation System (INS) was also upgraded to the AN/ASN-139 that uses ring laser gyro technology. Lot 14. The Lot 14 series F/A-18 was introduced in FY92. This update added full AN/ARC-210 HAVEQUICK/SINCGARS VHF FM Radio provisions to the aircraft and the AN/AAS-38A FLIR/LDT was also incorporated into the F/A-18. Additionally, the Deployable Flight Incident Recorder Set (DFIRS) provides non-volatile storage of the last 30 minutes of flight incident data in a deployable unit. Lot 15. Delivered in FY93, the Lot 15 series F/A-18 integrated an enhanced engine into the airframe. The F404-GE-400 Power Plant was replaced by the F404- GE-402 EPE. The new engine provided increased power, coupled with reduced fuel consumption. Additionally, the XN-8 Mission Computer and the 91 series Operational Flight Program (OFP) were introduced. Lot 16. The enhancements provided by the Lot 16 series F/A-18, which was introduced in FY94, included the integration of the AN/APG-73 Radar Upgrade (RUG) Phase I. The primary improvements provided by the AN/APG-73 RUG Phase I were increased Electronic Counter Countermeasures capabilities, increased memory and processing speed of the signal and data processing functions, and increased receiver bandwidth combining to provide growth capabilities for incorporation of advanced radar modes. The AN/ARC-210 HAVEQUICK/SINCGARS VHF FM Radio was also installed along with the LAU-115 Launcher improvements and incorporation of the 09 (formerly 93) series OFP.I-10 Lot 17. In FY95, the Cockpit Video Recording System (CVRS) and the AN/AAS-38B Advanced FLIR were introduced. Additionally, there were provisions added for the GPS. Lot 18. Lot 18 series F/A-18 were delivered in FY96 and included the GPS, the AN/ALE-47 Countermeasures Dispensing Set, and a sixth avionics multiplexer bus. Additionally, the 11 series OFP was introduced. Lot19. Introduced in FY97, Lot XIX series F/A-18C/D Aircraft received a Stores Management System upgrade and an AN/APX- 111(V) Combined Interrogator- Transponder (CIT). Lot 20. In FY98, Lot 20 series F/A-18C/D Aircraft were delivered, integrating the Phase II AN/APG-73 RUG, ATARS, Joint Direct Attack Munitions, Joint Stand Off Weapon, and EGI to meet the precision navigation capability that future weapon systems require. EGI provides an all-altitude, worldwide source of navigation and attitude information. Lot 21. One F/A-18E Aircraft was delivered in fourth quarter FY99 at NAS Lemoore and included a modified airframe, new engines, and an additional weapons station under each wing. The Lot XXI aircraft also incorporated a low drag pylon, AN/ALE-47 dispensers, AN/ALE-50 Chaff Dispenser, XN-8 Mission Computer, AN/ARC- 210(V) VHF FM Radio Set, GPS, AN/ALR-67(V3) Radar Warning Receiver, and a modified FCC. F/A-18E/F Low Rate Initial Production (LRIP) 1 are equipped with the AN/APX- 100(V) Identification Friend or Foe (IFF) vice the AN/APX-111(V) CIT. Lot 22. Lot 22 began LRIP 2 in third quarter FY00 for the F/A-18E/F, which included the AN/APX- 111(V) CIT and Advanced Tactical Forward Looking Infra Red. Lot 23. Lot 23 began delivery in first quarter FY01 with the Digital Communication System (DCS), Radio Frequency Defensive Electronic Countermeasures (RF DECM), Joint Helmet Mounted Cueing System, and Tactical Aircraft Moving Map Capability (TAMMAC
  5. ***Splendid*** What a wonderful variation in scenery,The Tripple 7 is at home anywhere in the skies!
  6. That sounds too good to pass on,Thanks Mike
  7. ***Classic*** Love The DC-3,Really itching to pick this one up.
  8. ***Little O.T.*** Thought some of you future DCS Hornet Drivers would be interested in this.... Retired Navy Hornet Driver has a podcast discussing everything Hornet/Naval aviation.
  9. ***V-Tail Classic***
  10. ***Mini Update*** "Over the past several months there has been a lot of work going on behind the scenes that has been confined to code… nothing visible to really show. More recently, more and more of this work is now being tied together and integrated into the larger simulation. The included screen shot shows some of this work: - Air Combat Maneuvering (ACM) modes. The Hornet has several ACM modes that include boresight acq, vertical acq, wide acq, and long range auto acq. In the image, you can see vertical acq selected, illustrated on the HUD and attack display. Much of the radar effort is currently focused on Single Track Target (STT) logic. - Not as obvious in this image, but target aging is also now implemented. Unlike our current implementation of air-to-air radar that is based on target IDs, the Hornet moves us to a much more realistic air-to-air radar model that faithfully simulates the radar beam. - On the Azimuth Display (aka RWR scope), we now have detection logic working that uses a much improved simulation of radar detection. In a related matter, the Control Indicator Panel is also now function that allows the Azimuth Display and DDI EW page to tailor the displays. This also includes the correct BIT. - On the left DDI you will note that waypoint data is now displayed on the HSI with the ability to select one of five sequences. You may also notice TACAN and ADF information is also displayed. In the second image, you can observe some improvements we are making to the reflective properties of the displays. Thanks, Matt “Wags” Wagner Senior Producer"
  11. ***Update*** "While we’ve already undertaken the development of an engine model with the Viggen, we decided last year to completely redesign this portion of our simulation framework, in order to create an much more in-depth and realistic simulation of a turbofan engine. This will also help us in recreating the P&W TF-30 engines for the F-14A, as well as other turbofan, turbojet, or turboshaft engines for our future product lineup. The F-14B is powered by two F110-GE-400 turbofan engines with variable exhaust nozzles and afterburner augmentation.They are dual-rotor engines consisting of a three-stage fan driven by a two stage, low-pressure turbine and a mechanically independent, aerodynamically balanced, nine-stage high-pressure compressor driven by a single-stage, air-cooled, high-pressure turbine. Engine operation is automatically regulated and maintained electrically by the augmenter fan temperature control unit and by throttle inputs to the main engine control. This new F110 model has been built entirely from scratch, incorporating many new features and improving the accuracy and fidelity of the engine simulation. The following components of the engine have been modeled based on actual F110 engine data gathered from various sources: Air Inlet Control System (AICS) The primary job of the AICS is to provide quality airflow to the engine in sufficient quantities to prevent engine operation issues. This involves a reduction of the speed of air entering the engine’s fan/compressor face. During this process, incoming freestream airflow is slowed and compressed. As a result, ram temperatures and pressures entering the engine are increased. On the F-14 this is achieved primarily by a system of 3 moving ramps per side that are scheduled based on flight conditions. During supersonic flight, these ramps are scheduled to move in a way that creates multiple shockwaves to more efficiently compress incoming air than a conventional duct would. The efficiency of the inlet’s pressure recovery throughout the flight envelope has been captured from real F-14 flight test data for use in the Heatblur F-14. Considerations for ramp actuator malfunctions have been made, which can include thrust loss and reduced stability margin (i.e. higher potential for compressor stall) if the ramps are out of their scheduled positions (i.e. high speed with the ramps in their stowed position...don’t do this!). Augmenter Fan Temperature Controller/Main Engine Control (AFTC/MEC) The AFTC/MEC on the F-14 is similar to a FADEC (Full Authority Digital Engine Control) in function. It schedules fuel to the engine and afterburner based on numerous inputs. It also provides limiting functions to prevent engine damage and reduce risk of compressor stalls. RPM, EGT, and acceleration/deceleration are all limited by the AFTC to ensure safe engine operation. Other AFTC functions include engine start control, asymmetric thrust limiting, automatic relight, and fault detection. Fault detection automatically switches the engine control to secondary mode in the event of core overspeed, fan speed signal loss and other abnormal conditions. The AFTC/MEC simulation on the Heatblur F-14 takes in probe temperatures and pressures from the AICS, Mach number, pilot throttle positions, fan and core rpms, and engine ignition status, and outputs demanded fuel valve positions. These valve positions correspond to fuel flows that will cause the engine’s core to accelerate or decelerate as demanded by the pilot. While the pilot can demand a certain core speed, the AFTC is also constantly monitoring other engine parameters, such as N2 RPM and EGT to ensure that engine design limits are not exceeded and engine damage does not occur. Essentially, the AFTC protects the engine from the pilot while trying its best to give the pilot what he/she demands. When AFTC failures occur, the AFTC/MEC model reverts to what is known as secondary mode, in which the MEC governs N2 speed based on throttle inputs, but protection features such as EGT limiting are no longer available. Be aware that engine stall margin is decreased slightly at low rpm in this mode. Fuel Metering Unit (FMU) The FMU consists of the system of valves and pumps responsible for carrying out AFTC fuel schedule demands. The AFTC outputs fuel valve position commands which in turn spray high pressure fuel into the combustor and afterburner when in use. The Heatblur F-14 model consists of a system of valves that open/close according to AFTC demands, as well as a shutoff valve for engine fires and automated shutdown commands coming from the AFTC. Failures such as stuck valves and clogged fuel filters may be implemented in the future. Gas Generator (N2) The gas generator is the heart of any turbomachinery. Its primary purpose is to provide hot, high pressure air to the combustor. This is done by reducing the speed and increasing the pressure/temperature of the incoming inlet air even further, which the F110 can do at a pressure ratio of in excess of 30:1. The gas generator on the F110 is driven by a single stage high pressure turbine. The gas generator simulation in the Heatblur F-14 is robust, with the speed and acceleration of the core determined by fuel flow from the FMU, the speed of air entering the engine, and the inertia of the core itself. The amount of fuel introduced into the flow by the FMU directly corresponds to changes in torque applied to the power turbine, which in-turn changes the compressor speed as it is connected to the same spool. Failures such as compressor stalls (core airflow disturbances) may affect core speed, as well as any failures of upstream components that affect the fuel flow, such as AFTC/MEC or FMU failures. Fan (N1) The fan on the F110 is driven by a two stage turbine, with a bypass duct that is mixed back in to the core flow in the afterburner section. The bypass ratio of the F110 is about 0.85. Low-bypass ratio turbofans such as the the F110 have the benefit of improved fuel economy at cruise speeds, while still maintaining very good high speed performance. This makes them excellent engines in fighter aircraft applications. The Heatblur F-14 fan simulation is driven as a function of core speed, with a given steady state core speed corresponding to a steady state fan speed. Any failures affecting the core will also affect fan speeds. Combustor/Exhaust Gas Temperature Model The combustor section of the F110 ensures that high pressure fuel flow is efficiently ignited, dramatically increasing the temperature and pressure of the gases before the flow is expanded through power turbine section. The Heatblur F-14 combustor/EGT simulation is dependent on the amount of fuel being introduced into the engine, which is determined by the AFTC/MEC and FMU models. Afterburner The afterburner on the F110 provides extra thrust by introducing additional fuel into the flow after the power turbine section. Fuel flow to the afterburner is controlled by the AFTC and AB Fuel Control (AFC), with its own set of high pressure fuel pumps that cycle fuel back to the engine boost pumps when afterburner is not in use. This ensures that high pressure AB fuel is available at all times to prevent thrust lags and surges when AB is initiated. The Heatblur F-14 afterburner simulation is purely dependent on available AB fuel flow and throttle position, with the extra thrust as a function of AB fuel flow and nozzle position. Failures to the AFTC/MEC, AB fuel pump failures, or exhaust nozzle failures will affect AB operation and performance. AB operation is inhibited when in AFTC/MEC secondary mode. Starting System The engine start system is a turbine powered either by a ground air/power cart or via a crossbleed start from the opposite engine. Ground power can achieve approximately 30% N2 before light-off. In our F-14 starter simulation, the ENG CRANK switches open pneumatic valves allowing the ground cart air to begin spool-up of the core. As the core spins up, the MEC primes the engine with fuel and provides ignition and fuel control up to 59% N2 RPM. Variable Exhaust Nozzle The variable exhaust nozzle is responsible for controlling the expansion of exhaust flow downstream of the afterburner section. Engine exhaust gases at higher thrust settings are discharged through the nozzle throat at sonic velocity and are accelerated to supersonic velocity by the controlled expansion of the gases. Varying nozzle throat area controls fan stall margin, which optimizes performance. The Heatblur F-14’s nozzle simulation is dependent on Mach number, altitude, throttle position, weight on wheels, engine oil pressure, and AB operation status. Failures in the nozzle will affect engine thrust and stability. We’re still working on completing our engine simulation. In particular some of the remaining items to be completed pre and post early access include the: Engine Oil System Bleed Air Draw Effects Generator Load Effects AICS Anti-Ice and Icing Effects AFTC/MEC Secondary Mode Effects Reduced Arrestment Thrust System (RATS) Asymmetric Thrust Limiting Afterburner Ignition System Throttle Control Modes (Approach Power Compensator already complete) Windmill and Cross-start failures and effects Battle Damage Effects FOD Effects This new engine modeling will serve as a robust and deep base for all of our future jet aircraft simulation. An accurate recreation of the aircraft’s powerplant and all of the follow on effects is important, as it allows us to more accurately depict common F-14 flight characteristics, failure states and especially dangerous situations arising from engine related issues. These effects will become even more apparent as we simulate the TF-30 engines as found in the F-14A. Be gentle with those throttles! Below are a couple of exports from our engine diagnostic interface. The descriptions above each column describe the conditions in which the snapshot of data was taken in.
  12. Love that Cardinal