The HAD S34 'Venom' is a highly maneuverable, supersonic Light Strike Fighter (LSF) derived from the SM-27J/L Turbofan Kradin originally. The most significant evolution of the Kradin series, the Venom marries a Turbofan Kradin derivative fuselage to a Forward Swept Wing (FSW) augmented by custom canard foreplanes and a distinctive empennage and an engine bay which accommodates a 22,000 to 25,000 static thrust class turbofan. Presenting greater capabilities than the standard turbofan Kradin, the HAD S34 is oriented toward fulfilling both Fighter, Attack and Advanced Pilot Trainer roles.
Power for the HAD S34 is provided by a single 22,000 lb st to 25,000 lb st class turbofan powerplant including a single Afterburning GEAE F414-GE-400 derivative engine mounted within a custom engineered, modular engine bay. Powerplant airflow is supplied by laterally mounted, bifurcated fuselage normal shock pitot inlets. An aft fuselage/exhaust duct mounted axisymmetric, lower observability variable geometry thrust vectoring exhaust nozzle may be fitted for improved engine performance.
A single piece bubble canopy and pressurized cockpit with zero-zero crew-member escape capability is provided. Flight controls are of four-channel, Fly-By-Wire, artificial force-feedback type with yaw dampening. Tricycle landing gear consisting of a forward retracting oleo-pneumatic nose strut and inboard wing/fuselage retracting oleopneumatic main gear is employed.
HAD S34 primary structure is an amalgamation of composite and advanced alloy materials designed to reduce detectability and offer a slight stealth ability, though this is not in the same catagory of say the F-35 area of stealth, it does have such. By weight, 33% of the aircraft structure is composite material, 55% is advanced alloy and 12% is polycarbonate and other non-metallic materials. Approximately 31% 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 2% 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.
HAD S34 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 6% 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.
Nearly 49% of the HAD S34 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, ribs and fuel tanks, canard spars and ribs, empennage spars and ribs, fuselage 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 SM-47 include 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 6% of the HAD S34 structural weight. Nearly 7% of the remaining SM-47 structural composition consists of the transparent polycarbonate material used in the thicker and sturdier HAD S34 clamshell bubble canopy.
The HAD S34 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 +7.8g and -3.9g at Maximum Gross Takeoff Weight (MTOW) with maximum external stores. The SM-47 will regularly "pull" up to +13.0gs as an unmanned autonomous aircraft armed with 2 x AIM-9 and 4 x AIM-120 in the air intercept configuration.
The HAD S34 fuselage is a compact unit consisting of the fuselage core, radome and engine cowling. The fuselage is largely similar to that of the HAD S32/LSF thru Fuselage Station F.S. 172. The fuselage core is a unitized 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 as well as efficiencies pioneered in the F-16, B-1, F/A-22 and F/A-35. 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 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 HAD S34 fuselage features the Cockpit Armor Module (CAM) for integrated cockpit protection. The HAD S34 fuselage features an integrated armored ammunition cell and rigid internal 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.
Of supersonic design, the HAD S34 Forward Swept Wings have a leading edge sweep of -30º. With a 4% to 6% thick supersonic airfoil, HAD S34 wings benefit from computer selected variable camber, including wing slats and trailing edge flaperons. Wing span is 36 ft 0 in. Reference wing area is 280 sq ft. Wing aspect ratio is 4.63. Of thin section, the SM-47 wing is of multi-spar construction with titanium ribs and spars. To provide the stiffness necessary to counter aeroelastic effects, the HAD S34 wing is skinned in hi-tensile strength IM-9 carbonfiber suspended in a matrix of high temperature Polyimide resin to permit sustained supersonic flight. HAD S34 wings feature four underwing hardpoints for external stores and provisions for optional wing-tip launch rails for the carriage of AAMs including the AIM-9 and AIM-120.
The HAD S34 wing is a modular, three-piece, fail-safe structure consisting of an integrated center section. The center section consists of four 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, friction stir welding and rivets.
A comprehensive integrated avionics suite, including Electronic Warfare/Electronic Counter Measures (EW/ECM) is featured. Stores and ordinance is carried on eight wing hardpoints. Typical fixed internal armament includes an under nose mounted GSH 30 mm cannon with up to 1,000 rounds of ammunition for the Fighter role and 500 rounds in the Advanced Pilot Trainer role. A ventrally mounted conformal fuel tank may be fitted to the aircraft fuselage, incorporating a total of four weapons hardpoints, increasing the total number of available external stores hardpoints to twelve. Standard HAD S34/T external armament include wing-tip rail mounted AIM--9 X Sidewinders augmented by a host of wing mounted AIM-120s or precision guided ordinance.
General characteristics
Model Types: HAD S34S & HAD S34T Venom LSF
HAD S34S: Single Seat Light Strike Fighter (LSF)
HAD S34T: Two Seat Tandem Light Strike Fighter/Supersonic Trainer
Dimensions
Length: 47 ft 4¾ in (14.45 m)
Wingspan: 26 ft 8 in (8.13 m)
Height: 13 ft 4½ in (4.08 m)
Wing area: 186 ft² (17.28 m²)
Performance
Maximum speed: Mach 2 (2,204 km/h, 1,372 mph) at altitude
Combat radius: 800 km (500 mi, 432 nmi)
Ferry range: 3,200 km (2,000 mi) with drop tanks
Service ceiling: 15,240 m (50,000 ft)
Wing loading: 283 kg/m² (58 lb/ft²)
Thrust/weight: 0.97
Powerplant
Number and Type: HAD-SAT12 (Single Afterburning Turbofan 12 Series Production)
Model: GEAE F414-GE-400 Afterburning Turbofan
Maximum Afterburning Thrust (lbs-sl): 22,000 lbs
Maximum Military Thrust (lbs-sl): 14,756 lbs
*Zero-lift drag coefficient: 0.0200
Drag area: 3.4 ft² (0.32 m²)
Aspect ratio: 3.86
Internal fuel: 677 US gal (2,563 L)
External fuel: 275 US gal (1,040 L) per tank in up to 3 tanks
Targeting Systems
Targeting Pod/FLIR Option # 1: BSM LITENING III FLIR (External Hardpoint)
Targeting Pod/FLIR Option # 2: BSM RECON Advanced Targeting Pod (External Hardpoint)
Radar
VCI AN/APG-67(V4) Multi-Mod
Helmet Mounted Display
VCI Electronics Night Star Repeater
Head Up Display
Forward Station Option # 1: VCI Electronics Night Star
Aft Station Option # 1: VCI Electronics Night Star Repeater
Multi-Functional Displays
(5) x L3 Actiview 104P 6 x 8 in LCDs
Mission Computer
VCI MDP/MMRC Multi-Role Computer
Stores Management
SMS/WDNS: VCI SMS-86 Stores Management System
Navigation System
GPS/INS: VCI H-764G Embedded GPS/INS
TACAN: AN/ARN-153(V) DME/TACAN
ADF: VCI ADF-462/4000
VOR/ILS: VCI AN/ARN-147V
Radar Altimeter: VCI APN-194
Communication Systems
UHF/VHF COMM: VCI AN/ARC-232(V) Starbright
IFF Transponder: VCI AN/APX-113(V) CIT
Secure Voice: BSM KY-58 SVS
Datalink: AN/URC-138 Link 16 Low Volume Terminal
Intercom: VCI Electronics A301-412 Intercom
Emergency Power: HAD PS-855/B Emergency Power Supply
Cockpit VADR: HAD SA2100 Cockpit Voice/Data Recorder
Electronic Warfare Suite
Self-Protection Suite: ASPIS
RF ECM: AN/ALQ-187 Internal Countermeasures
MAWS: VCI AN/AAR-58 Advanced
RWR: AN/ALR-93V Radar Warning Receiver
SPJ: AN/ALQ-165 ASPJ
LWR: HAD-20V-2 Laser Warning System
Chaff/Flare Dispenser: HAD AN/ALE-47; 10-12 Dispensers
Fixed Internal Armament
HAD S34S: (1) x GSH 30 mm Cannon with 1,000 rds or (1) x M242 20 mm Cannon with 1,500 rds
HAD S34T: (1) x GSH 30 mm Cannon with 500 rds or (1) x M242 20 mm Cannon with 1,000 rds
External Armament
Eight (8) Wing Mounted External Hardpoints for 11,000 lbs Stores/Ordinance Using WA Standard Lug Suspension.
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