Mithridates
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an stunnishing airplane, the Rockwell HiMAT. lets check some facts about it:
thrust/weight: 0.88 (dry), 1.23 (afterburner). all this with only a GE J-85 engine which we can produce now and 1800 kg of maximum take off weight. while for F-22 T/w ratio is: 0.8 (dry) and 1.08 (afterburner)
sustained turn ratio: the manufacturer stated it's STR is twice of F-16, depending on falcon's version it can achieve 15-21 degrees per second that means HiMAT STR could be somewhere between 30-42 DPSs. the STR (sustained turn ratio) of EF typhoon is 25 DPSs (degrees per second), MIG-29's STR is 24 DPS, F-22 and SU-35 both have 28 DPSs as their STR, F-35's STR is 18 DPS, F/A-18 has the same number as F-35 and Swedish JAS-39 has only 20 DPS. closest rivals of Himat are F-22 and SU-35 which both utilize thrust vectoring control system. if HiMAT utilize similar systems it can increase the STR even further.
HiMAT design featured a modular structure where you can change the overall shape to a delta wing, forward swept wing, variable incident wing and original design.
the structure was build mainly of titanium and aluminum but it used extensive amount of synthetic fibers including glass fiber and carbon fibers, resulting in light overall weight.
so the point of all this is: what if we can make a twin engine variant of this?? it's performance is excellent with owj/J-85 and with future J-90 it's a dream comes true. technical aspect is, if an engine can support 1800 kg so it's obvious that second engine can maintain the above mentioned features for the same weight increase. this means you have 1800 kg room for fit your radar, avionics, cannon, ejection seat, pilot weight, extra fuel and extra weight of enlarged fuselage and second engine.
grifo-346 radar weights 110 kg, k-36 ejection seat weights 103 kg, owj/J-85 maximum weight is 240 kg, a simple IRST weights 20 kg itself and 45 with it's power supply unit and each MFD weights almost 80 kg (with related avionics). this far we spend the 800 kg of original 1800 kg. now we have 1 ton for fuel and weapons and it's completely disappointing. but what if we replace the 9 percent of steel skin with titanium and 30 percent aluminum with aluminum foam?? this way we can save 500 kg more weight. this way we will have a plane with 1800 kg empty weight and 1800 kg fuel capacity. comparing with F-5 i say it worth it to take a shot. and also consider the fact that this numbers are result of calculations based on general electric J-85 performance. with J-90 we can achieve better results and ranges.
thrust/weight: 0.88 (dry), 1.23 (afterburner). all this with only a GE J-85 engine which we can produce now and 1800 kg of maximum take off weight. while for F-22 T/w ratio is: 0.8 (dry) and 1.08 (afterburner)
sustained turn ratio: the manufacturer stated it's STR is twice of F-16, depending on falcon's version it can achieve 15-21 degrees per second that means HiMAT STR could be somewhere between 30-42 DPSs. the STR (sustained turn ratio) of EF typhoon is 25 DPSs (degrees per second), MIG-29's STR is 24 DPS, F-22 and SU-35 both have 28 DPSs as their STR, F-35's STR is 18 DPS, F/A-18 has the same number as F-35 and Swedish JAS-39 has only 20 DPS. closest rivals of Himat are F-22 and SU-35 which both utilize thrust vectoring control system. if HiMAT utilize similar systems it can increase the STR even further.
HiMAT design featured a modular structure where you can change the overall shape to a delta wing, forward swept wing, variable incident wing and original design.
the structure was build mainly of titanium and aluminum but it used extensive amount of synthetic fibers including glass fiber and carbon fibers, resulting in light overall weight.
so the point of all this is: what if we can make a twin engine variant of this?? it's performance is excellent with owj/J-85 and with future J-90 it's a dream comes true. technical aspect is, if an engine can support 1800 kg so it's obvious that second engine can maintain the above mentioned features for the same weight increase. this means you have 1800 kg room for fit your radar, avionics, cannon, ejection seat, pilot weight, extra fuel and extra weight of enlarged fuselage and second engine.
grifo-346 radar weights 110 kg, k-36 ejection seat weights 103 kg, owj/J-85 maximum weight is 240 kg, a simple IRST weights 20 kg itself and 45 with it's power supply unit and each MFD weights almost 80 kg (with related avionics). this far we spend the 800 kg of original 1800 kg. now we have 1 ton for fuel and weapons and it's completely disappointing. but what if we replace the 9 percent of steel skin with titanium and 30 percent aluminum with aluminum foam?? this way we can save 500 kg more weight. this way we will have a plane with 1800 kg empty weight and 1800 kg fuel capacity. comparing with F-5 i say it worth it to take a shot. and also consider the fact that this numbers are result of calculations based on general electric J-85 performance. with J-90 we can achieve better results and ranges.
