Vendetta Final Proposal Part 2 - Cal Poly

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(4) Mk-84 LDGP + (2) AIM-120 (4) GBU-27 + (2) AIM-120 (4) 2000lb JDAM +(2) AIM-120 (4) AGM-154 JSOW + (2) AIM-120 (16) 250 lb Small Smart Bomb AIM-120 C AMRAAM Weapon Weight 1967 lb Weapon Weight 2165 lb Weapon Weight 2100 lb Weapon Weight 1064 lb Weapon Weight 250 lb Weapon Weight 327 lb Installed Configuration Weight 10222 lb Installed Configuration Weight 11014 lb Installed Configuration Weight 10754 lb Installed Configuration Weight 6610 lb Installed Configuration Weight 5500 lb Installed Configuration Weight 5500 lb Weapon Length Weapon Diameter Tail Span Max Drop Height Max Tested Drop Velocity Guidance Weapon Information: 12.6 ft 18 in 2 ft Unlimited M=1.3 Ballistic Development of the Mk 84 Low Drag General Purpose Bomb for use by the United States armed forces began in the 1950's. The Mk 84 bomb, which is fitted with 30 in (0.762m) spaced suspension lugs, is packed with 942 lb (426 kg) of Tritonal or H-6. The known inventory of Mk 81, 82, and 84 bombs is 1.13 million. Weapon Length Weapon Diameter Tail Span Max Drop Height Max Tested Drop Velocity Guidance Weapon Information: 13.9 ft 14.6 in 2 ft Unlimited Unknown Semi-Active Laser The GBU-27 is a modified GBU-24 Paveway III designed for internal carriage in the F-117A. This LGB carries the designation GBU-27 /B and uses a BLU-109 /B penetrator bomb for its warhead. The main modifications made to the GBU-24 were to have shorter adaptor rings and to use the GBU-10's rear wing unit to decrease the bomb's length, and to clip the canards in order to make the weapon fit into the small F-117A Bomb Bay. The other major difference was the use of radar absorbing materials in order to prevent the bombs from being picked up by enemy radar once the aircraft's bomb doors were opened. As a result of these modifications, the GBU-27 has a shorter range than the GBU-24, which can also be launched at lower altitudes. Guidance is by semi-active laser, the scanning detector assembly and laser energy receiver being mounted in the front of the canister behind the glass dome. After the bomb is released the laser error detector measures the angle between the bomb's velocity vector and the line between the bomb and target. Steering corrections are made by moving the nose mounted canard control fins to adjust the bomb's trajectory to line up with the target. The tail fins/wings are for stabilization purposes only. Target illumination for the system may be either by an aircraft-mounted laser marker (not necessarily the parent aircraft) or a ground-based laser transmitter. Weapon Length Weapon Diameter Tail Span Max Drop Height Max Drop Velocity Guidance Weapon Information: 13.2 ft 18 in 2 ft Unlimited M=1.3 tested GPS / INS A parallel program to the AGM-154 JSOW the GBU-31 JDAM program began in the late 1980's. The goal of the program was to produce a low cost guided munition. Interesting to note is the GBU-31 is soon to be replaced by the GBU-32/35. This new weapon, will utilize a I-1000 (1000lb)(452.5kg) penetrator warhead and is intended for future use in the F-22 raptor. This weapon, the GBU-32/35 is being used to size the raptor's bomb bay's. The GBU-31 utilizes both the Mk 84 and BLU-109 warheads. Due to the Mk 84's low cost, and commonality, it was chosen for the solid model seen above. The GBU-31 consists of three major subassemblies. The warhead (Mk 84), Saddleback stub wing assembly (attaches at hardpoints, three components), and a bolt on tail cone guidance kit. The guidance kit, contained within the replacement bolt-on tail cone consists of the following key elements: combined inertial measuring unit and GPS receiver; flight control computer; battery and power distribution unit; tail actuators and four movable clipped delta fins in a cruciform configuration. In keeping with other GPS guided weapons, the unit is believed to be fitted with two GPS antennas, one on top of the unit for initial flight and one in the tail for good reception during terminal maneuvering. Prior to bomb release the guidance unit will be fed with aircraft position, velocity and target coordinates through the aircraft to bomb interface. After release the bomb will guide itself to the target by means of rear fin deflection which are driven by commands from an onboard computer that is constantly being updated by the GPS. The combination of the INS/GPS is expected to allow the bombs to hit within 10m (32.8ft) to 15m (49.2ft) of their targets. Wind tunnel tests in 1996 are reported to have cleared JDAM for release at up to M 1.3. Weapon Length Weapon Diameter Tail Span Max Drop Height Max Drop Velocity Guidance Weapon Information: 14 ft 21 in 24 in Unlimited Subsonic GPS / INS In the late 1980's the US Navy began a review of conventional weapons with the intention of reducing the number of weapon types. New systems were selected for future development: JDAM, TSSAM, JASSM, and the advanced interdiction weapon system to be later named Joint Standoff Weapon (JSOW). The JSOW program is intended to replace six existing weapons: the AGM-65 Maverick, AGM-123 Skipper, AGM-62A Walleye, Rockeye and APAM (Anti-Personnel/Anti-Material) submunition dispensers, and laser- and TV- guided bombs. Of particular attention on the previous list is: 1) All weapons are air to ground. 2) This weapon is designed to replace the GBU-27, one of the weapons on the RFP attachment 3 list. The JSOW is an aerodynamically shaped, unpowered glide dispenser with a rectangular cross-section body shape. It is made up of three major sections: a streamlined nose fairing that houses the guidance and control system, a rectangular center section payload container for holding the bomblets (this is fitted with two folding high aspect ratio wings on its upper surface, and two standard 30 in (0.762 m) spaced suspension lugs); and the tail section which has six fixed, sweptback rectangular fins positioned radially on the boat tail and contains the flight control system. Weapon Length Weapon Diameter Max Drop Height Max Drop Velocity Guidance Weapon Information: 8.2 ft 6 in Unlimited Unknown GPS / INS The Small Smart Bomb is a 250 lb (113 kg) weapon that has the same penetration capabilities as a 2000lb (905 kg) BLU-109, but with only 50 lbs (22.6 kg) of explosive. With the INS/GPS guidance in conjunction with differential GPS (using all 12 channel receivers, instead of only 5) corrections provided by GPS SPO Accuracy Improvement Initiative (AII) and improved Target Location Error (TLE), it can achieve a 5-8m (16.4 to 26.3 ft) CEP. The submunition, with a smart fuze, has been extensively tested against multi-layered targets by Wright Laboratory under the Hard Target Ordnance Program and Miniature Munitions Technology Program. The length to diameter ratio and nose shape are designed to optimize penetration for a 50lb (22.6 kg) charge. This weapon is also a potential payload for standoff carrier vehicles such as Tomahawk, JSOW, JASSM, Conventional ICBM, etc. The Swing Wing Adapter Kit (SWAK) is added to give the SSB standoff of greater than 25 nm (48.6 km) from high altitude release. The wing kit is jettisoned at a midcourse way point if penetration is required so that velocity can be increased after wing release. For soft targets the wing kit continues to extend the glide range until small arms threat altitude is reached. At this point the wings are released. With INS/GPS guidance, coupled with AII, a 6-8 m (19.7 to 26.3 ft) CEP can be achieved. This wing kit allows the SSB to be directly attached to the aircraft at any 300 lb (135.75 kg) store station. The major advantage to the 250 lb (113.125 kg) small smart bomb is an improved number of targets per pass capability. Weapon Information: The Advanced Medium-Range Air to Air Missile (AMRAAM) AIM-120 development program was started in 1975. It was designed to follow on and better the performance of the Aim-7 Sparrow and be carried on the F-14, F-15, F-16 and F/A-18 aircraft. In the late 90's a modified(smaller) version of the missile, the AIM-120C was developed to be fitted to the F-22 Raptor. This newer version also incorporates a dual mode active and passive radar seeker. The AIM-120C is deigned to be rail, ejector or trapeze launched. On the F-22 the AIM-120C is launched using an EDO corp. LAU-142/A hydraulic / pneumatic ejector. In a typical engagement the missile is launched and first guided by on-missile inertial navigation, with command guidance updates from the launch aircraft. The missile then goes into the mid-course autonomous mode and continues to guide by by inertial navigation only. <strong>Final</strong>ly, the terminal mode is automatically initiated by the missile itself when the target is within rage of the missile's active monopulse radar seeker, which then guides the missile onto the target aircraft. <strong>Vendetta</strong> Chris Droney Nate Schnaible Rev. 3 Weapon Length Weapon Diameter Fin Span Max Drop Height Max Drop Velocity Guidance Kolby Keiser Chris Maglio 12 ft 7 in INS High Rollers 1 ft 6 in Unlimited Supersonic Command from Launch Aircraft Monopulse Radar Seeker Foldout 5 Weapon Systems Chris Atkinson Dan Salluce 5/23/02
13 Cockpit Cockpit design began with the RFP requirement for a crew of two. A comparison of tandem versus side-by-side seating arrangement, and its affect on cross sectional area, was conducted. A solid model was constructed with room provided for instrumentation, controls, circuit breakers and military aft pilot vision requirements (MIL-STD-850B) allowing the frontal cross-sectional area of each configuration to be determined. The results are shown in Figure 13.1. Figure 13.1 - Cockpit Width Trade Study The results show that the configuration has very little effect on frontal area of the cockpit. For this reason, other factors were taken into account before a final decision on pilot configuration was made. The use of the 180 in MPRL, favored the side-by-side seating arrangement because the width of the fuselage was already driven to be large. This arrangement allowed greater pilot communication as well as the elimination of many redundant circuit Figure 13.2 – Fuselage Comparison breakers and instruments; however, preliminary stability and control analysis revealed a need to narrow the forward fuselage due to the undesirable C mα characteristics of a wide nose section. Therefore the decision was made to utilize a tandem seating configuration. This configuration offered a better field of vision for the primary pilot and decreased the width of the forward fuselage as shown in Figure 13.2. Utilizing this information the detailed virtual cockpit model, shown in Figure 13.3, was generated. The solid model also took into account the use of an ejection seat, room for instrumentation, controls, switch placement as well as the military vision specifications outlined in Table 13.I. 71
Page 1 and 2: well as a tip back angle which did
Page 3 and 4: Table 9.II - Final Component Weight
Page 5 and 6: the center-of-gravity location clos
Page 7 and 8: 10 Stability and Control To initial
Page 9 and 10: management system could then be use
Page 11 and 12: 40 30 20 10 0 -10 -20 -30 -40 -50 2
Page 13 and 14: flight. This would require a large
Page 15 and 16: Table 10.IV - Longitudinal and Late
Page 17 and 18: Additional components were integrat
Page 19 and 20: 11 Performance 11.1 Specific Excess
Page 21 and 22: 70,000 60,000 50,000 Altitude (ft)
Page 23 and 24: 11.3 Mission Requirements The RFP d
Page 25 and 26: 11.4 Takeoff & Landing The RFP requ
Page 27 and 28: 12 Payload Weapon internal layout w
Page 29: ange occurs due to the additional w
Page 33 and 34: Due to RFP requirements the majorit
Page 35 and 36: fuelled systems offer high power to
Page 37 and 38: 14.4 Government Furnished Equipment
Page 39 and 40: The assembly line would allow for m
Page 41 and 42: is a learning curve associated with
Page 43 and 44: Table 17.I - RFP Compliance Checkli
Page 45 and 46: 20,000 0.9 581 2,164 3,231 4,407 5,
Page 47 and 48: Appendix B - Design Tools Company S
Page 49: 25. Roskam, J. Airplane Flight Dyna

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