The HIA S30 Sylrada went through seven versions, starting with the S30-1, then S30-2 and S30-3 with various minor improvements, then the S30-4 with improved low-level bombing equipment with the Non-Afterburning GEAE F414 Turbofan engine.
The cockpit is available in two configurations: the single seat S30 Sylrada and the two seat tandem S30 Sylrada-B. Each configuration is designed for reduced workload operations with crewmembers seated on unreclined Martin Baker MK.16E ejection seats. Both S30 Sylrada models incorporate auto-eject and auto-eject sequencing. The cockpit is pressurized to 8,000 ft and air-conditioned. Standby crew oxygen is provided by a Carlton OC1132 Molecular Sieve Oxygen Generating System (MSOGS).
The cockpit for S30 Sylrada/B is a completely modular unit, produced as a unitized, self contained system external to the fuselage. Incorporating distinct, armored and EM hardened quick interconnects for flight controls, electrical junctions, avionics buses and environmental control, the Machete cockpit is installed and extracted vertically in the absence of the bubble canopy. Cockpits for either model attache to the CAM bath-tub structure through bolts in vibration damping fittings.
The CAM, featuring armor plate and Spectra® fiber significantly mitigates the penetrative effects of projectiles and spall. Cockpit modules are interchangeable, allowing a specific aircraft to be converted to either a single seat or two place tandem variant.
The aircraft bubble canopy is of large area, frame-less, single-piece clamshell type. The canopy is of advanced bullet resistant polycarbonate composition and can safely sustain the impact of a 4 lb bird at airspeeds exceeding 450 kts from any attitude. Visibility is 350° azimuthal with 13° over-the-nose and 25° over-the-side. The canopy is hydraulically lifted upward for cockpit access. The canopy is defrosted and purged of precipitation using a perimeter high pressure, powerplant bled, hot air system. An internally mounted, manual unlatch and hand-crank is provided.
All S30 Sylrada variants benefit from a HOTAS flight controls arrangement consisting of a right hand/starboard mounted Flight Control Grip (Mason Electric/F-16 derivative) right console mounted flight control column, full deflection rudder pedals, power control lever (Mason Electric/F-16 Grip Derivative), prop control level (turboprop model) and flap lever. Stick and throttle flight control grips are provided by Mason Electric and are based upon current production articles for the F-16 Block 50+ to reduce tooling complexity. HOTAS provides toggles for aircraft trim, sensors, weapons release, microphone, etc. Rudder pedals are fully adjustable.
The primary visual flight reference display is the CMC NIght Hawk wide field-of-view HUD and HUD repeater system. Secondary flight reference instruments include the customers choice of LCD MFD configurations including five L3 Communications Actiview 104P 6 x 8 in LCDs. A VSI Integrated HMDS may be used as an alternative to the HUD for the forward crew station.
The aft panel of the S30 Sylrada is largely identical to that of the forward panel, with exception of the HUD being replaced by a HUD repeater. IFR certified, the cockpit is designed for Generation III night vision compliance and Helmet Mounted Cuing Systems/Integrated Helmet and Display Sighting Systems (HMCS/IHDSS). Forward and rear panels are complemented by a comprehensive warning annunciator panel, two air conditioning/heater vents and standby instruments.
Conceived to address real counter-terrorism needs, the S30 Sylrada series enables air strikes directly at core insurgent forces in the field, in training, and in hiding. Particularly well-suited for low-level Close Air Support (CAS), COIN and Forward Air Control (FAC) above dense jungle, desert, maritime, and rugged mountain environments with limited forward and ground support, Machete aircraft will exhibit exemplary maneuverability, integrated sensors and electronic countermeasures, superior low-speed handling, short-field performance, high maximum level speed, significant external warload and reduced maintenance requirements.
The single-seat, turbofan-powered S30 Sylrada is a high-performance CAS aircraft suitable to succeed the the Su-25 Frogfoot, A-37B Dragonfly, L-159A and Hawk 200 single-seat light attack aircraft.The two-seat tandem turbofan powered S30 Sylrada is a Lead-In Fighter aircraft appropriate for fast jet advanced training and COIN/CAS/light attack. A successor to a variety of two-place light attack and trainer class aircraft, the S30 Sylrada is a suitable replacement for the T-37 Tweet, Alpha Jet C-20, AT-63 Pampa, M-346, MB-339, L-139, L-159B, Hawk 100 Series, T-45A Goshawk and Yak-130.
As wars of terror and insurgent aggression become more prevalent, the market for S30 Sylrada aircraft can only increase. Offering significantly greater speed, survivability, payload, armament and endurance than helicopter gunships and far greater endurance, efficiency, and economy in the COIN role than either the Su-25 or the A-37B Dragonfly, the S30 Sylrada satisfies the COIN mission without compromise.
Over 8,000 lbs of expendable, external stores and ordinance are carried on a total of eight external, wing-mounted hardpoints equipped with WA standard 14-inch and 28-inch lug suspension systems. Of the eight hardpoints, two are rated to 1,000 lbs, two are rated to 2,000 lbs and four are rated to 2,500 lbs maximum external carriage capacity at a +7.5 g load factor. Four of the external wing hardpoints are plumbed for external fuel tanks.
The S30 Sylrada/B is designed primarily for air-to-ground missions, employing ordinance such as the AGM-65, GBU-39/B, GBU-31, GBU-32, GBU-38, CBU-97, CBU-59, BLU-107 and additional stores. Optimized for precision strike, the S30 Sylrada/B employs GPS guided munitions, including the GBU-39/B Small Diameter Bomb (SBD) to dispatch ground threats with minimal collateral damage. The S30 Sylrada/B can carry up to 28 GBU-39/Bs, or 6 AGM-65s or 2 GBU-31 JDAMS externally in addition to 2 AIM-9s.
Air-to-Air capability is provided through the carriage of AIM-9 and similar passive homing/IR AAMs. The S30 Sylrada/B is capable of LANTIRN, LITENING and ECM pod carriage and employs a MIL-STD-1760 Weapon Interface Data Bus. Weapons release is conducted through a control column gun trigger switch and weapon release button for air-to-air/air-to-ground. An abridged S30 Sylrada/B stores loading chart is provided:
S30 Sylrada/B avionics are integrated about a MIL-STD-1553B Interface/Data Bus with Data Bus wiring used throughout the system architecture to reduce wiring bundles. The S30 Sylrada/B features a comprehensive navigation/communications suite. The philosophy driving the S30 Sylrada/B avionic configuration emphasizes mission completion, reliability, flexibility and ease of serviceability. Avionics may be of a variety of types including either COTS or MOTS. Wherever possible, avionics are of modular LRU type with BIT. Principal avionics and sensors are contained in two to three bays including the nose radome/sensor bay, forward fuselage avionics bay and aft cockpit avionics bay as available in the S30 Sylrada/B.
The avionics/sensor suite is designed and integrated by Stavatti based upon customer specifications. Stavatti has developed a Standard Avionics/Sensors/EW configuration which includes a variety of proven, reliable systems from which WA end-users may select a specific S30 Sylrada/B configuration. This Standard configuration is optimized to permit unrestricted export of the Machete via Direct Commercial Sales (DCS) to the majority of NATO members, although specific avionics, including GPS with PPS, as well as particular COMSEC/TEMPEST equipment, must be procured via FMS or on a government-government basis. Principal sensors and avionics included in the Standard Configuration are:
• VCI AN/APG-67(F) Multi-Mode Pulse Doppler Radar mounted in the forward Radome
• VCI AN/AAS-52 Multi-Spectral Targeting System.
The cockpit is equipped with a Cockpit Video Recording (CVR) system capable for recording at least 120 minutes of HUD symbology, the external HUD field of view, cockpit LCD MFD symbology and all aircraft communication system audio. The aircraft is also equipped with a crash survivable Flight Data Recorder (FDR) capable of storing the last 90 minutes of flight data for post-crash flight reconstruction. The aircraft is fitted with a Crash Position Indicator (CPI) and a survivable Underwater Locator Beacon (ULB). Halon 1301 is employed for avionic system fire suppression within sealed avionic bays.
The cockpit is available in two configurations: the single seat S30 Sylrada and the two seat tandem S30 Sylrada/B. Each configuration is designed for reduced workload operations with crewmembers seated on unreclined Martin Baker MK.16E ejection seats. Both models incorporate auto-eject and auto-eject sequencing. The cockpit is pressurized to 8,000 ft and air-conditioned. Standby crew oxygen is provided by a Carlton OC1132 Molecular Sieve Oxygen Generating System (MSOGS).
The cockpit for S30 Sylrada is a completely modular unit, produced as a unitized, self contained system external to the fuselage. Incorporating distinct, armored and EM hardened quick interconnects for flight controls, electrical junctions, avionics buses and environmental control, the Machete cockpit is installed and extracted vertically in the absence of the bubble canopy. Cockpits for either model attache to the CAM bath-tub structure through bolts in vibration damping fittings.
The CAM, featuring armor plate and Spectra® fiber significantly mitigates the penetrative effects of projectiles and spall. Cockpit modules are interchangeable, allowing a specific aircraft to be converted to either a single seat or two place tandem variant.
The aircraft bubble canopy is of large area, frame-less, single-piece clamshell type. The canopy is of advanced bullet resistant polycarbonate composition and can safely sustain the impact of a 4 lb bird at airspeeds exceeding 450 kts from any attitude. Visibility is 350° azimuthal with 13° over-the-nose and 25° over-the-side. The canopy is hydraulically lifted upward for cockpit access. The canopy is defrosted and purged of precipitation using a perimeter high pressure, powerplant bled, hot air system. An internally mounted, manual unlatch and hand-crank is provided.
All S30 Sylrada variants benefit from a HOTAS flight controls arrangement consisting of a right hand/starboard mounted Flight Control Grip (Mason Electric/F-16 derivative) right console mounted flight control column, full deflection rudder pedals, power control lever (Mason Electric/F-16 Grip Derivative), prop control level (turboprop model) and flap lever. Stick and throttle flight control grips are provided by Mason Electric and are based upon current production articles for the F-16 Block 50+ to reduce tooling complexity. HOTAS provides toggles for aircraft trim, sensors, weapons release, microphone, etc. Rudder pedals are fully adjustable.
The primary visual flight reference display is the CMC NIght Hawk wide field-of-view HUD and HUD repeater system. Secondary flight reference instruments include the customers choice of LCD MFD configurations including five L3 Communications Actiview 104P 6 x 8 in LCDs. A VSI Integrated HMDS may be used as an alternative to the HUD for the forward crew station.
The aft panel of the S30 Sylrada is largely identical to that of the forward panel, with exception of the HUD being replaced by a HUD repeater. IFR certified, the cockpit is designed for Generation III night vision compliance and Helmet Mounted Cuing Systems/Integrated Helmet and Display Sighting Systems (HMCS/IHDSS). Forward and rear panels are complemented by a comprehensive warning annunciator panel, two air conditioning/heater vents and standby instruments. The forward panel of the S30 Sylrada smoothly integrates the HUD, MFDs and traditional analog flight reference instruments.
The S30 Sylrada employs an internal Electronic Counter Measures (ECM) suite. The S30 Sylrada EW system accommodates a wide variety of external jamming pods and countermeasures dispensers and includes Radar Warning Receivers, Laser Warning Systems, Self Protection Jammers and Advanced Missile Warning Sensors. The ECM suite is designed and integrated by Stavatti based upon customer specifications. Stavatti has developed a Standard (NATO Export) ECM/EW Configuration which includes demonstrated as well as next generation electronic warfare systems which may equip Machete.
This Standard configuration is designed to satisfy the needs of the majority of potential WA customers without export restriction, however, particular ECM systems must be procured on an FMS or government to government basis. Typical S30 Sylrada ECM systems include:
• 14 AN/ALE-47 Countermeasures Dispensers
• The ATK AN/AAR-47 Missile Warning System
S30 Sylrada primary structure is an amalgamation of composite and advanced alloy materials. By weight, 22% of the aircraft structure is composite material, 64% is advanced alloy and 14% is polycarbonate and other non-metallic materials.
Approximately 14% of the aircraft structure is comprised of Hexcel IM9 graphite fiber suspended in a matrix of hi-temperature polyimide resin, also known as Graphite Reinforced Plastic (GRP). Graphite composite components include primary structural members such as fuselage skins, vertical stabilizer skins, horizontal stabilizer skins, flaps and flight control surfaces.
Nearly 4% of the aircraft structure consists of Dupont Kevlar® 149,129 or 29 aramid fiber suspended in a matrix of epoxy or polymer resin, refered to hereafter as Kevlar Reinforced Plastic (KRP). Approximately 4% of the aircraft structure is composed of Honeywell Spectra® 2000 fiber of 650 and 1,200 denier employed in a ballistic capacity or suspended in a matrix of epoxy or polymer resin, hereafter referred to as Spectra® Reinforced Plastic (SRP). KRP and SRP composites are used within the aircraft fuselage structure as a secondary structure and as a discrete ballistic armor. KRP and SRP are used as the primary structural material for radome, antenna fairings, support and access panels, engine cowling and in discrete armor throughout the aircraft.
S30 Sylrada alloy components include principal load-bearing elements and aero-structures such as wing and canard skins, spars, ribs, fuselage subframe, engine firewall and mounts, landing gear, electronic/subsystems mounting chassis, electronics Faraday cage and as a component of all discrete armor.
Approximately 7% of the aircraft structure consists of Alcoa produced aluminium alloys including 7150-T7751 Aluminum, 7075-T651 Aluminum, 7055-T7751 Aluminum and other high performance aircraft aluminum. Aluminum is used in the aircraft wing skins, canard skins, vertical stabilizer skins, fuselage and landing gear structure.
Over 58% of the S30 Sylrada/B structure is composed of Titanium alloys including the general purpose Ti-6Al-4V Titanium, SP 700 Titanium, Ti-15V-3Cr-3Sn-3Al, and Ti-6Al-2Zr-2Sn-2Mo-2Cr-0.25Si (Ti-6222) Titanium for airframe structural elements.
Titanium primary structures include wing spars, skins, ribs and fuel tanks, canard spars and ribs, empennage spars and ribs, fuselage geodetic subframe, empennage stabilizer booms, canopy frame, landing gear struts and hardware, aircraft firewall and engine bay and in discrete armor. Titanium components are produced using laser forming, laser machining and traditional aerospace Titanium part production methodologies. Titanium components are fastened to the aircraft structure via laser welding, Titanium Bolts and Huck Ti-Matic rivets as appropriate. Additional alloys used throughout the S30 Sylrada include molecularly pure Chromium, 2090-T83 Aluminum Lithium, and PH 15-7 Stainless Steel.
Additional composite materials used throughout the aircraft include Hexcel IM7/polyimide, Kevlar®-49/epoxy, Kevlar®-29/epoxy, Kevlar®-129/epoxy and Spectra® 1000/epoxy. These and other alloys and composite materials constitute over 5% of the S30 Sylrada/B structural weight. Over 8% of the remaining S30 Sylrada structural composition consists of the transparent polycarbonate material used in the Machete clamshell bubble canopy.
The S30 Sylrada is designed for an operational service life of 15,000 hours, accumulating an average of 750 hours per annum. Aircraft fatigue life will be based upon 30,000 takeoffs and landings (cycles). The aircraft maximum design load factor limit is +7.5g and -3.5g at Maximum Gross Takeoff Weight (MTOW) with maximum external stores.
The tubofan S30 Sylrada fuselage is a compact unit consisting of the fuselage core, radome and engine cowling. The fuselage core is a unitized frame structure consisting of a Titanium and Aluminum sub-frame. This subframe employs the structural principals pioneered in highly survivabile aircraft including the B-17 and A-10. The alloy subframe is a laser welded and built-up structure which serves as a rigid chassis for the integration of all alloy frames, primary bulkheads, mounts and the firewall. All fuselage contained systems, including avionics, electrical, armament hydraulic and the CAM, are secured to subframe integrated alloy mounts. The subframe is skinned in an alloy film to ensure all TEMPEST sensitive avionic and electrical systems are contained within a Faraday cage.
The fuselage core is skinned with a unitized sandwich structure consisting of a Hexcel IM9 graphite/polyimide external skin and and finely woven Kevlar® (KRP) and Spectra® (SRP) internal skin, separated by a proprietary thin core optimized for improved ballistic projectile threat protection.
The S30 Sylrada fuselage features the Cockpit Armor Module (CAM) for integrated cockpit protection. The Machete fuselage features an integrated armored ammunition cell and internal self-sealing fuel tanks. The fuselage incorporates discrete armor throughout. The fuselage features a starboard located downward hinged door with integral steps for crew ingress/egress.
The radome is composed of bandpass Spectra® (SRP) and hinges to the port for radar/avionics access. The engine cowling is of three-part clamshell type and is composed of a Kevlar® (KRP) composite sandwich.
The wings of the S30 Sylrada are largely similar to those of the S30 Sylrada/B in terms of configuration and construction, differing primarily with respect to airfoils. S30 Sylrada wings are of high aspect ratio, low-wing, cantilever type. Wing leading edge sweep is 5° and trailing edge sweep is -5°. Wing span, excluding wing-tip dispensers/winglets is 47 ft 0 in. Reference wing area is 243.4 sq ft. Wing aspect ratio is 9.08. Designed to operate at maximum airspeeds in excess of Mach 0.85, the wings of the S30 Sylrada feature a high-speed airfoil of 10% thickness to increase wing critical Mach number. To accommodate this airfoil change, aircraft wing spars feature thicker, albeit shorter, webs with increased spar cap thickness. Like the S30 Sylrada/B, turbofan Machete wing tips employ 2° washout to alleviate the negative affects of tip stall. Wing incidence is 0°. Wing dihedral, from root, is 2°. Wing Drag Divergent MACH Number is greater than 0.87 MACH.
The S30 Sylrada wing is a modular, three-piece, fail-safe structure consisting of an integrated center section spanning 149 in and port and starboard outer sections spanning 208.25 in each. The center section consists of two sine wave Ti-6222 spars which form the basis of a rigid, laser welded, Titanium carry-through box. This carry-through box serves as mount and armored housing for the main landing gear. The carry-through box is also the principal mount and interface for port and starboard Titanium monocoque empennage support booms which serve as the structural interface for the vertical and horizontal stabilizers. The center section has Titanium ribs, stringers and skins. All alloy components are fastened via laser welding and flush rivets (Ti-Matic).
The port and starboard wing sections feature two Titanium sine-wave spars and one Titanium false spar for aileron/flap attachment. Each wing section incorporates eighteen Titanium ribs and twelve Titanium stringers. Wing sections benefit from Titanium skins, with all alloy components fastened by computer directed laser welding. Each wing contains a rigid Titanium, self-sealing fuel tank located between the two spars. Each wing section is equipped with 0.301c ailerons for roll control and 46% span 0.301c double slotted, trailing edge Fowler flaps. The inboard wing center section is also equipped with a trailing edge elevon which may function as an elevator, aileron or plain flap to enhance pitch control. Each wing section is also equipped with leading edge slat and spoilers for additional roll control. Trailing and leading edge flaps/slats are hydraulically actuated while the ailerons are mechanically controlled with electric trim tabs. Ailerons, flaps, slats, spoilers and speed-brakes are of GRP construction. Each wing section is equipped with a streamlined tip fairing housing chaff/flare dispensers and inverted low aspect ratio winglet for induced drag reduction.
Wings are equipped with an Electro-Expulsive Separation System (EESS) for in-flight deicing. Wings are equipped with a total of eight external stores hardpoints, with three hardpoints located on each outer wing section and two canted hardpoints located on the wing center section tips fitted directly to the empennage support boom. Four wing hardpoints are rated to 2,500 lbs capacity at +7.5g, while the two canted hardpoints are rated to 2,000 lbs capacity at +7.5g. The two remaining outer wing hardpoints are rated to 1,000 lbs capacity at +7.5g. Two hardpoints per wing are plumbed for external fuel carriage. Standard external tanks include 100 through 230 USG types. Each wing may be fitted with an additional, wing tip mounted hardpoint for the carriage of stores, including the AIM-9 AAM, up to 200 lbs at +7.5g pending the removal of tip fairings and winglets.
The aircraft canard foreplanes are fixed, close-coupled cantilever type. Canards enhance aircraft low speed handling, maneuvering and short field performance through the generation of high energy vortices. The canards are of lifting type, adding to aircraft gross wing area. Leading edge canard sweep is 36° and trailing edge sweep is 19°. Canard dihedral is 3°. Canard unit span is 6 ft 0 in. Total canard area and aspect ratio is 36.37 sq ft and 4.03 respectively. Canard mean airfoil is a NACA 65-209 section.
Canard construction consists of two Ti-6222 spars, seven Titanium ribs and Titanium skins. Canards benefit from laser formed components which are laser welded to form a smooth, high tolerance finish. Canards incorporate flaperons of Aluminum construction which operate collectively with the all moving horizontal stabilizer to enhance pitch rate.
The S30 Sylrada empennage consists of an all-moving, mass balanced horizontal stabilizer for longitudinal stability and pitch control and twin vertical stabilizers. The empennage is close-coupled to the aircraft wing to improve instantaneous maneuverability and reduce aircraft physical dimensions. The empennage is mated to Machete via the wing mounted integrated empennage support boom structure and aerodynamically contoured fuselage braces which blend directly into the horizontal stabilizer. Both the horizontal and vertical stabilizers are equipped with EESS deicing.
The S30 Sylrada horizontal stabilizer has a leading edge sweep of 34° and trailing edge sweep of 10.3°. Horizontal tail unit span is 10 ft 3.5 in. Total horizontal tail area and aspect ratio is 88.52 sq ft and 2.39 respectively. Horizontal tail mean airfoil is a NACA 0009 section and anhedral is 8°. The horizontal stabilizer is composed of three Ti-6A1-4V Titanium sine-wave spars and ten IM9/polyimide ribs. Horizontal stabilizer skins are flush riveted IM9/polyimide. Maximum horizontal stabilizer deflection angle is +/- 40°.
S30 Sylrada vertical stabilizer consists of two independent units of trapezoidal configuration with dorsal fairings. Vertical stabilizer leading edge sweep is 40° and trailing edge sweep is 9°. Vertical stabilizer span is 155 in. Total vertical tail area and aspect ratio is 58.32 sq ft and 2.88 respectively. Vertical stabilizer mean airfoil is a NACA 0009 section with dihedral of 90°.
The vertical stabilizer is composed of three Ti-6A1-4V Titanium sine-wave spars, five IM9/polyimide false spars, six titanium ribs and flush riveted IM9/polyimide skins. Each vertical stabilizer features a IM9/polyimide rudder. Rudders incorporate trim tabs and are capable of deflection angles of +/- 35°. Each vertical tail incorporates a SRP tip antenna fairing for vertical tail mounted antennas, EW and RWR.
The aircraft fuel system is of OBIGGS pressurized type, composed of six rigid self-sealing fuel tanks and one feeder tank. The OBIGGS employed is the Carlton NC1029.
Five of the fuel tanks are located within the fuselage, while the remaining two tanks are located within the port and starboard wing respectively. The maximum useful internal fuel load for the S30 Sylrada is 6,000 lbs, equivalent to approximately 895 gallons of JP-8 (at 6.7 lbs/gal) or 923 gallons of JP-4 (at 6.5 lbs/gal). S30 Sylrada fuel tanks are sized for 925 usable gallons of JP-4, resulting in a total capacity of 930 gallons, including the volume necessary to accommodate self-sealing cells. Unusable internal fuel equates to approximately 46 lbs.
Fuel tanks are fitted with tear-resistant, self-sealing bladders lined with open cell reticulated foam as secondary survivability protection in addition to the OBIGGS. A single point refueling interface is located on the starboard fuselage, while gravity refueling may be accomplished through three filler locations including one on each wing and the single fuselage point.
A probe-and drogue in-flight refueling system may be installed within the fuselage nose section as a customer, cost plus option. The refueling probe for the in-flight refueling system is of retractable type based upon technologies developed by Sargent Fletcher in their ART/S Aerial Refueling Tank System. The retractable refueling probe system will likely be produced by Sargent Fletcher.
S30 Sylrada Airframe Systems include flight controls, hydraulics and electrical units. The S30 Sylrada flight control system is a full-authority, Digital Fly-By-Wire (FBW) flight control system.
Ailerons, flaperons, rudders and stabilators are internally mass balanced. Ailerons and rudders feature electric trim tabs controllable through a control column rheostat. Stabilators feature electric trim, actuators for which are located in the support boom. The S30 Sylrada is fully aerobatic and will perform standard maneuvers including the stall, slip and spin, without departure, with stall, slip and spin modes being permitted by the FBW system to enable full exercises throughout the advanced training syllabus.
The S30 Sylrada features two, independent, 4,000 psi hydraulic systems. Hydraulic functions include landing gear extension and retraction, trailing and leading edge flap extension and retraction, canopy extension and retraction, crew boarding ladder retraction, clamshell cowling actuation and ventral airbrake actuation.
Hydraulic pressure is maintained automatically. The hydraulic power package supplies hydraulic pressure and incorporates an electrically-powered variable displacement motor/pump, a reservoir and low pressure filter. A nitrogen-charged accumulator is used to minimize pressure loss while allowing for thermal expansion. The aircraft hydraulic system employs Spectra® filament wrapped titanium lines and non-flammable hydraulic fluid for survivability.
The S30 Sylrada electrical system supplies 115 volt, three-phase, 400 cycle AC power and 28 VDC per MIL-STD-704D. Three independent sources are used for power generation consisting of a primary starter/generator, a secondary generator and two batteries. AC power is supplied by two engine driven static invertors rated at 125 volt amps, providing outputs of 26 VAC at 400 Hz and 115 VAC at 400 Hz.
Power is normally supplied by one invertor with the second serving as a backup. DC power is supplied through one 24 VDC, 40 amp-hour, nickel-cadmium battery. The starter/generator is a combination engine starter and 28 VDC, 300 amp generator. The secondary generator is a 28 VDC, 130 amp generator. An external 28 VDC power connector is provided within the engine bay.
The S30 Sylrada features hydraulically actuated, retractable tricycle landing gear. The main landing gear consists of wing mounted, single-strut, oelo-pneumatic, single wheel units featuring carbon disk brakes. Main wheels use 24 x 8.0-13 size tires including Goodyear 18 ply rib tread with a maximum inflation pressure of 285 psi. The main gear retracts 90° inboard, with wheels stowed in the wing center section carry-through box upon retraction.
Landing lights are incorporated into the main gear struts. A hand-crank system is provided for emergency main gear extension.
Nose landing gear retracts forward and is an oelo-pneumatic, fork-braced single wheeled unit. The nose wheel uses 19 x 6.75-8 size tires including 10 TL ply, Goodyear Rib tread with a maximum inflation pressure of 110 psi. Nose wheel steering, and main gear braking, is provided via rudder pedal inputs. Nose gear may be gravity extended in the event of hydraulic failure.
The landing gear is capable of unprepared, forward operations and sink rates of 15 ft/s enabling a high tolerance to hard landings. Maximum landing gear deployment airspeed is 200 Kts. Machete wheelbase is 14 ft 11 in. S30 Sylrada wheel track is 10 ft 9 in. Nose gear/main gear weight distribution is 15/85 at MTOW.
Substantial emphasis has been placed upon ensuring S30 Sylrada survivability in the low-level, hostile environment. In so doing, significant quantities of both integral and discrete armor are incorporated throughout the airframe.
Integral Armor consists of primary aircraft structural elements that not only serve as load-bearing members, but also provide an element of armor protection by inherent design. Featuring fail-safe construction throughout, the S30 Sylrada wings and canards feature two sine-wave Titanium spars and numerous titanium sine-wave ribs. These spars and ribs in-turn assist in shielding discrete, self-sealing wing fuel tanks. S30 Sylrada horizontal and vertical stabilizers feature three sine-wave spars and multiple sine-wave ribs. This use of Titanium spars and ribs significantly improves aircraft survivability. Employing significant quantities of geodetically arranged Titanium mated to Spectra® ballistic materials, the S30 Sylrada fuselage is of inherently survivable and crash-worthy design.
All S30 Sylrada fuel is contained within discrete tanks located in the wings and fuselage. Each rigid tank consists of a Titanium fuel cell that provides both structural form and function as well as a degree of armor protection. Within each cell is a tear-resistant, self-sealing bladder. Whenever possible, fuel lines are contained within fuel tanks. All fuel lines, hydraulic lines and flight control lines are contained within Titanium or Spectra® filament jackets to ensure survivability. The aircraft flight control, electrical and hydraulic systems are duplicated and physically separated by more than 24 in to ensure redundancy.
Presenting a compact, close coupled arrangement, the Machete configuration is directed toward survivability. The empennage, for instance, is configured such that the GRP skinned vertical stabilizers provide the aircraft propulsion system with a degree of profile shielding.
Learning from the A-10, the S30 Sylrada empennage is slightly oversized to ensure continued control in the event of significant loss of stabilizer area during combat. Additional reductions in overall aircraft vulnerable area are derived from the use of a low-wing situated directly beneath the aircraft fuselage fuel tanks, ammo drum and to a degree, propulsion system, as shielding. The use of vertically sloped forward fuselage cross sections further improves survivability by ensuring that the majority of incoming ballistic projectiles will be received as deflection impacts met by Spectra® ballistic material.
S30 Sylrada Discrete Armor consists of materials which function wholly as armor, serving no secondary structural purpose. The S30 Sylrada employs no less than 500 lbs of Discrete Armor, strategically placed within critical vulnerable areas including around/about the aircraft powerplant (engine cowling case armor), electrical generation, environmental, hydraulic and control systems, as well as around the internal ammunition drum. To ensure crew survivability, the Machete cockpit is an integral unit contained within a unitized Cockpit Armor Module (CAM). The CAM is a laser welded, armored structure, conceptually identical to the A-10 crew protection structure. The Discrete Armor used throughout the Machete, including the CAM, is a Stavatti proprietary laminate of alloy and composite materials including an alloy face sheet backed by multiple layers of Spectra® 2000/Spectra®Shield. Thickness of the Discrete Armor laminate varies based upon specific application, ranging from 0.25 in to more than 1.25 in.
Composed of advanced bullet-resistant polycarbonate, the S30 Sylrada transparent bubble canopy is no less than 1.00 in thick throughout and provides impact protection against a 4 lb bird up to airspeeds in excess of 450 kts. Ensuring crew protection through 0.44 Magnum/7.62mm caliber small arms, the canopy benefits from technologies developed at HAD.
Ensuring crew survivability, the S30 Sylrada is equipped with the highly reliable and proven Martin Baker MK.16E zero-zero ejection seat. The ejection seat is provided with both sequential and auto-eject features. Incorporating a comprehensive internal electronic countermeasures suite, proven Radar Warning Receivers, Laser Warning Receivers, Missile Approach Warning Systems and Self Protection Jammers produced by Elisra, Elta and/or Raytheon are carried as customer selected, standard equipment.
A rugged flexible platform, the S30 Sylrada will deliver precision guided ordinance in significant quantities while surviving substantial small arms fire and direct hits from Man-Portable SAMs.
Specifications
Model Specified: HIA S30 Sylrada
Production Status: General
Mission: Ground Attack/Anti-Armor/Emplacement Destruction
Accomodation: Single (S) or Two Place Tandem (T)
Dimensions
Length: 41 ft 3 in (12.58 m)
Wingspan: 50 ft 0 in (15.24 m)
Height: 17 ft 1 in (3.68 m)
Wing area: 400 ft² (37 m²)
Empty weight: 12,900 lb (5,864 kg)
Loaded weight: 18,700 lb (8,500 kg)
Max takeoff weight: 22,960 lb (10,436 kg)
Performance
Powerplant: One (1) Non-Afterburning GEAE F414 Turbofan; 14,756 lbs st
Maximum Speed: 590 kts (MACH 0.90) at Sea Level
Range: 1,900 nmi (2,200 mi, 3,520 km)
Service ceiling: 48,100 ft (14,664 m)
Rate of climb: 7,290 ft/min (37 m/s)
Armament
[1] GSH 30mm Cannon
Ammunition: 675 Rounds
Other: 9,350kg on 10 external hardpoints
Listed Types:
150 USG External Tank
M134D Gun Pod
LAU-10C Rocket Pod
LAU-61C Rocket Pod
CBU-97/105 SFW
HIA Rb-05
HIA R7-SGFFM
HIA Taytmo Vmufan
HIA R2B Pylg cdyp
HIA Brimstone
GBU-12 PAVEWAY II
GBU-24 PAVEWAY III
GBU-39/B SDB
R-73
K-74
If interested in purchasing this vehicle, please make your orders here: HIA