Final Proposal: Advanced Tactical Missile II (ATM) IPT 2006 Team H
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Final Proposal: Advanced Tactical Missile II (ATM) IPT 2006 Team H Submitted By: May 2, 2006 Submitted To: Dr. Robert A. Frederick, Jr. Associate Professor Technology Hall N231 Department of Mechanical and Aerospace Engineering University of Alabama in Huntsville Huntsville, AL 35899 [email protected] Class Web Page: http://www.eb.uah.edu/ipt/ Contributors Project Office Jerry Dickson System Engineering Marie Vogan Aerodynamics Stephen Strand Propulsion Stephen Strand Weight/ Structures Ricardo Naranjo Trajectory Jason Williams, Mutasem Shannag Avionics Jason Martin Review Team C. Stephen Cornelius, Chairman AMRDEC Christina Davis, Customer AMRDEC Kader Frendi UAH Joe Hudock GDATP Richard Kretzschmar AMRDEC George Sanders AMRDEC Dean Slocum GDATP James Snider UAH Department of Mechanical and Aerospace Engineering The University of Alabama in Huntsville May 2, 2006 Executive Summary [J. Dickson] The Viper Company of America is proud to submit the Puff Adder Advanced Tactical Missile II concept in response to the U.S. Army's Concept Description Document dated 2 February 2006. The Puff Adder concept completely fulfills the Army's requirement to upgrade the existing 2.75 tactical missile at an affordable cost. The Puff Adder's technical design approach employs a combination of mature proven technologies (propulsion, warhead, structural materials) coupled with the most innovative technologies in guidance and control (controllable diverter thrusters and radar). Particular emphasis has been placed on using commercial off the shelf technology where appropriate. The Puff Adder has no outside movable aerodynamic control surfaces, which is a unique advantage over other conventional missile systems. Aerodynamic control is provided by 4 rings of thrusters, each containing twelve thrusters that are software controllable. The use of diverter thruster technology increases overall missile reliability, reduces system cost and eases assembly and integration operations. Another unique technological advancement found in the Puff Adder is the simplistic W-band frequency modulated continuous wave radar. The radar is used for ground track, roll rate determination and warhead deployment. The propulsion system uses a double base, minimum smoke propellant which is cartridge loaded. The existing M261 warhead has been maintained. The Puff Adder's performance is extraordinary since we meet the threshold range of 8000 meters (26,246 ft) at below the threshold weight 15.39 < 15.63 Kg (33.85 < 34.38 lbs). The Puff Adder payload of 38 rockets (two pods) reduces the payload weight allowance by 9.12 kg (20.064 lbs). At the average cost of $1 million dollars per pound weight reduction cost for a helicopter development program such as the Comanche, the Army can immediately realize a cost avoidance of $20.064 million dollars with the Puff Adder. The Puff Adder Advanced Tactical Missile II meets the Army's critical threshold production cost of less than $15k per round at $11,450. The Puff Adder's length is 181.43 cm (71.43 in) which is below the objective length of 182.1 cm (71.7 in) : iii ATM Compliance List [J. Dickson] The following list details the location of all specification compliances for the ATM. The list shows the location in the CDD provided by the Army of every specification and the number of the page where that specification is dealt with in this proposal. CDD Proposal Specification Location Location Operational between 61.0 m (200 ft) below MSL and 6,096.0 m 2.2.1.1.1 1.3.3, 2.7.3 (20,000 ft) above MSL Range of 1 km (0.62 mi) to 8 km (4.97 mi) when fired from 2.2.1.2.1 2.7.3 Helicopter Range of 1 km (0.62 mi) to 4 km (2.5 mi) when fired from Ground 2.2.1.2.1 2.7.3 Maximum Platform Error of 19 milliradians 2.2.1.2.2 2.6.4.2 Operational under Maximum Crosswind of 7.7 m/s (15 knots) 2.2.1.2.3 2.6.6 Minimum Smoke Signature 2.2.1.2.5 2.4.4 Motor Cannot Produce Damaging Ejecta 2.2.1.2.6 2.4.4 Capable of being loaded in military issued clothing 2.2.2.1 1.3.3 Compatible with the M261 Launcher 2.2.2.2 2.5.4,2.8 Compatible with the M261 Launcher Interfaces 2.2.2.2.1 2.8 Minimal Longitudinal Force Greater than 13.5 times the Maximum 2.2.2.2.2 2.2,2.4.4 System Weight Modified Fusing System for M261 MPSM Warhead 2.2.2.3 2.6.4 Submunition Deployment to occur at ± 10 m of Wall in Space 2.2.2.3.1 2.6.4 Safe and Arm device 2.2.2.3.2 2.6.4 Maximum lateral acceleration of 79 g 2.2.2.3.3 2.4.4 Submunition Deployment Velocity 603 m/s (1978 fps) 2.2.2.3.4 2.7 Maximum System Weight of 297 kg (654.6 lbs), Objective Weight 2.2.3 2.5.1,G.2 of 267.9 kg (590.0 lbs) Maximum System Length of 202.4 cm (79.7 in), Objective Length 2.2.3.1 2.5.1,G.1 of 182.1 cm (71.7 in) Maximum Outer Diameter of 70 mm (2.794 in) 2.2.3.2 2.5.1,G.1 Minimum Service Life of 10 years, Objective of 25 years 2.2.4.1 3.5 Maximum Unit Production Cost of $15,000/unit on 10,000 units w/ 2.2.4.2 3.1 Objective Cost of $10,000/unit Storage Temperature Range from -53.8oC (-65oF) to 73.9oC (165oF) 2.2.5.1 2.4.4,2.6.3 Operational Temperature Range from –31.7oC (-25oF) to 65.5oC 2.2.5.1 2.2,2.4.4,2.6.3 (150oF) Operational During or After Constant 100% Humidity 2.2.5.2 2.4.4,2.6.3 Minimum Hazard Classification of 1.1 with Objective of 1.3 2.2.6.1 2.4.4 Satisfying IM Compliance Requirements 2.2.6.2 2.4.4 Flight Fail Safe 2.2.6.3 2.7.3, I Minimum Ballistic Trajectory of 3.5 km (2.17 mi) 2.7.3, I Objective Ballistic Trajectory of 5 km(3.11 mi) 2.7.3, I All Components of System shall be Unclassified 2.2.7 complies Documentation 2.2.8 included iv ATM II Project Ground Rules and Assumptions [M. Vogan] All teams in the project adopted a set of common ground rules and assumptions to focus their efforts. This focused their efforts to fit the resources of time and tools available for the project. Each team could also make Team-specific ground rules and assumptions for their study. This page shows the Global and Team Specific ground rules and assumptions. Global Ground Rules and Assumptions [R. Frederick] 1. Ground Rules a. The GPS location of the launch platform and the target are available in electronic form outside of the launcher 10 seconds before launch. 2. Assumptions a. The control system has precise position coordinates available to at one second intervals during flight. b. Cross winds are constant throughout predicted flight. Team Specific Ground Rules and Assumptions [M. Vogan] 3. Ground Rules a. The position and target data can be transmitted through the launcher to the missile b. This data allows the missile to know both where it is located, and where its target is located prior to launch. c. The operational requirement of launch at 20,000 ft above MSL as quoted in the CDD refers not to an altitude of 20,000 ft. above the ground, but rather to the capability for the missile to launch and fly in the atmosphere found at 20,000 ft above MSL. d. All technologies shall be unclassified. 4. Assumptions a. The warhead used is of a constant design with no significant modifications, as it was taken from the baseline missile. v Table of Contents 1.0 ATM-Advanced Tactical Missile....................................................................................14 1.1 The Need [J. Dickson]..................................................................................................14 1.2 The Requirements [J. Dickson] ..................................................................................14 1.3 The Solution [J. Dickson, M. Vogan] .........................................................................15 1.4 The Performance [J. Dickson, M. Vogan] .................................................................17 1.5 The Implementation [J. Dickson, M. Vogan] ............................................................18 2.0 Technical Description of Methods Used ........................................................................19 2.1 Project Office [J. Dickson] ..........................................................................................19 2.2 Systems Engineering [M. Vogan] ...............................................................................20 2.3 Aerodynamics [S. Strand] ...........................................................................................25 2.4 Propulsion [S. Strand] .................................................................................................31 2.5 Structures [R. Naranjo]...............................................................................................36 2.6 Avionics [J. Martin].....................................................................................................38 2.7 Trajectory [J. Williams, M. Shannag, S. Strand, J. Martin] ...................................50 2.9 Trade Studies and Interactions of Subsystems [S. Strand]......................................56 3.0 Implementation Issues.....................................................................................................56 3.1 Production Cost [M. Vogan].......................................................................................56 3.2 Manufacturability [R. Naranjo] .................................................................................57 3.3 Test Schedule [M. Vogan] ...........................................................................................59 3.5 Discussion of Application and Feasibility [M. Vogan] .............................................60 4.0 Company Capabilities [J. Dickson]................................................................................61 4.1 Viper Company of America Overview