Shailesh Kumar/ National Defence Bureau,
New Delhi, 01 November 2019
MMRCA 2.0 Ep-2 Technical Specifications
So, If India is to procure 110 fighter aircraft under MMRCA 2.0, then what are the technical parameters of the aircraft for procurement. We will discuss the technical parameters in 5 parts over the next 5 days. But what is up in this second part of the MMRCA 2.0 series and first part of the technical parameters?
Well, in this episode of the MMRCA 2.0 news web series, we will discuss Parameter specifications as Physical Parameters and Features, Conditions of Use (Environmental Conditions), Aircraft Mass, Slinging and General Characteristics.
When we talk of technical specifications, physical parameters and features come first. Indian Air Force asked vendors in RFI-
What are the external dimensions of the aircraft, height, weight, span, wheel track, wheel base, overall length etc.?
Twin seat variant should retain all operational attributes of the single seat variant (Radar, Air to Air Refuelling (AAR) probe, Internal Gun, weapons and Infra Red Search and Track (IRST) etc).
In case of twin seat aircraft, workload should be manageable by a single pilot and it should be possible to undertake single seat operation in all roles.
IAF wants to confirm from OEM about the environmental conditions. OEM is to answer-
Is the aircraft and its systems tropicalised?
Are associated testers, tools and equipment tropicalised and ruggedized? Vendor to provide the cleared operating temperature range and relative humidity.
Is the aircraft adequately protected against effects of lightning strike as per MIL-STD or equivalent standards?
Electro-Magnetic Pulse (EMP) hardening should exist for flight safety related systems. Specify the details.
Are the aircraft and the pilot adequately protected whilst operating in Nuclear Biological and Chemical (NBC) environment? If so, details thereof.
Aircraft should meet its performance and maintenance conditions under Indian Reference Atmosphere (IRA) conditions unless specified otherwise. IRA conditions are placed at Annexure I.
OEMs are to provide details of aircraft mass-
Operational Empty Mass (weight of the complete aircraft with all systems and permanent fluids, mandatory launchers/pylons and the equipped pilots).
Certified Maximum Take-off Weight (MToW)
Certified Maximum Landing Weight. Specify permissible sink rate for landing.
Maximum weapon load carrying capability. Specify configuration.
What is the maximum external load, consisting of air to air and air to ground weapons and other external stores, (includes pylons and launchers) capacity of the aircraft?
Specify total jettisonable load carrying capability of the aircraft.
Slinging for portability parameters-
Is the aircraft capable of being under slung from a crane?
Will the vendor provide slings? If yes, what is the lifting load capacity of the slings? Vendor to provide required specifications of the salvage crane? If no, then what is the means of aircraft removal device (inflatable devices etc)?
IAF asks OEMs about the General Characteristics of the aircraft-
What is the Total Technical Life (TTL) and total calendar life of the aircraft?
Aircraft should be capable of sustaining ‘g’< 0 with full afterburner engaged for more than 10 sec. If not then, what is the time with ‘g’ < 0 in this condition?
Do all mission and safety critical systems have adequate redundancy and are they adequately separated and protected? Specify redundancy of each system.
Vendors are to define aspect and relevant radar frequency bands for calculation of Radar Cross Section (RCS) for the aircraft in the following configurations:-
(i) Clean configuration with landing gear retracted
(ii) Air to surface strike (2 PGMs + 1 Designator Pod + 2 BVRs + 2 x A4Ms + Ext Fuel)
(iii) Air to Air configurations (4 BVRs + 2 A4Ms + Ext Fuel ).
(e) What is the static Thrust-to-Weight (TWR) ratio of the aircraft at sea level, in ISA conditions and (with 50% internal fuel and BVR missiles with full complement of gun ammunition) with maximum afterburner? What is the static TWR ratio of the aircraft at sea level under ISA conditions at Max All-Up Weight? (Thrust for calculation should be un- installed thrust)
Are Operational Turn Round Servicing (Op TRS) timings inclusive of rearming, refueling and replenishment in cleared Air to surface strike and Air Defence role with one team, of not more than five technicians per aircraft, with any combination of weapon / reconnaissance load?
What is the Op TRS time for the following configurations (amount of fuel carried should be same as used for calculation of RoA/ loiter in Annexure V).
(i) Air to air configuration (4 BVRs + 2 A4Ms + Ext Fuel)
(ii) Air to surface configuration (2 PGMs + 1 Designator Pod + 2 BVRs + 2 x A4Ms + Ext Fuel)
Depending on the external loading, the aircraft configuration should be sensed automatically or else it should be possible to select it through a selection panel located inside the cockpit.
Are there any restriction/ limitation to fly in icing conditions? Specify.
That is it in this part of technical parameters. We will deal with rest of technical specifications in other parts of this news web series.
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