SAWE Technical Papers

@inproceedings{3664,

title = {3664. Advanced Lightweight 3D Structures (AL3DS) Manufacturing Design Concept},

author = {Max Feldman and Jonathan Sobol and Dr. Donna Gerren},

url = {https://www.sawe.org/product/paper-3664},

year  = {2016},

date = {2016-05-01},

booktitle = {75th Annual Conference, Denver, Colorado},

pages = {14},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {Weight is one of the factors with the greatest influence on aircraft performance. The Advanced Lightweight 3D Structures design concept proposes to reduce structural frame we ight through the use of novel manufacturing techniques. The primary objective of this paper is to analytically demonstrate the feasibility of using a 'node and rod' design for an aircraft wing box section. Preliminary analysis shows that weight reduction is possible by employing carbon-fiber rods connected with aluminum 3D printed 'nodes' in place of traditionally manufactured ribs and spars. The 'nodes' can be specifically designed in complex shapes while still allowing for mass - production by using CAD and 3D printing technology. This flexibility in rapid-prototyping allows the engineer to vary the geometry of connectivity in order to optimize for a specific design. The 'node and rod' technique would enable the design and development of increased complexity structural designs in a simple and repeatable way. Analytical software is developed to model the aerodynamic loads acting on a wing box, as well as to analyze the structural properties of a 3D wing box structure. The computational tools are validated using commercial finite element modeling programs such as ANSYS and SOLIDWORKS. These models are compared for different flight loading conditions imposed by varying angle of attack and flight Mach number. Furthermore, the models are compared for different materials,such as aluminum vs carbon-fiber rods.If successful, the node and rod concept can be implemented across multiple engineering disciplines to reduce weight in a wide range of structural design paradigms. The concept would fit well within existing engineering infrastructure as well: the structures team may design the nodes based on the desired geometry and loading cases, while the manufacturing team is able to rapidly prototype and iterate to a final node design, and of course the rods may be sub contracted out. The applications for lightweight, strong structures are endless - cars, robots, architecture, and so on. However, any possible weight reduction would drastically improve aircraft performance in fuel efficiency, range, cruise speed, and available payload. The Advanced Lightweight 3D Structures design concept would allow for a new and improved method for designing and building aircraft.},

keywords = {27. Weight Reduction - Materials, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3672,

title = {3672. Weight's Importance in Machine Design},

author = {Jacob Hundl},

url = {https://www.sawe.org/product/paper-3672},

year  = {2016},

date = {2016-05-01},

booktitle = {75th Annual Conference, Denver, Colorado},

pages = {9},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {This report will describe the prototyping, design, fabrication and testing of a device that was designed to propel golf and ping-pong balls a distance of at least three feet into separate containers. After a five second delay, the device was required to deposit the first ball into its container. At least five of each type of ball had to be deposited within twenty seconds of the release time. The device had to begin operation with a release or a flick of a switch. The device also had to cost less than $100 dollars and weigh less than ten pounds at testing. Finally, the device was required to be constructed out of raw materials. Any type of pre-fab system in the device would lead to the device's elimination. The device was graded more favorably if it was powered by gravity as opposed to electricity or a spring force. The simplicity of our device's design and its reliance on gravity as the driving force for the motion of the balls led us to believe that our design was very reliable. However, the observed difference in final and initial testing produced unexpected results.},

keywords = {24. Weight Engineering - System Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3359,

title = {3359. Weight and Balance Considerations for Unmanned Combat Aerial Vehicles},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3359},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {23},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {Sentinel Aerospace presents Cavalier, a ship-based morphing unmanned combat aerial vehicle (UCAV), in response to the 2004 ? 2005 American Institute of Aeronautics and Astronautics (AIAA) Graduate Team Aircraft Design Competition. Cavalier uses a combination of speed, stealth, and maneuverability to perform the suppression of enemy air defenses (SEAD) mission. The profile includes a 200 nautical mile cruise segment and a four hour loiter followed by a 0.757 Mach dash to the target area where four AGM-88 HARM missiles are to be expended, and a 5 g maneuver to egress the threat area. The alternate mission, which is also required, involves the same mission profile, but without engaging the enemy target. Cavalier effectively uses several forms of morphing on the wing. As the plane is to takeoff and land on LHA ships, a span limitation of 48 feet exists. Therefore, Cavalier uses shape memory alloy-actuated folding wingtips that extend after takeoff, and provide an additional 8.2 feet of span on each wing. Pivoting leading edge strakes are used to adjust planform area, mean sweep and thickness-to-chord for the different flight conditions. Hinge-less ailerons, based on the Smart Wing Program, will be employed to provide roll control while improving the radar cross-section. During the course of this investigation, it was realized that substantial savings could be achieved if morphing was applied to the propulsion system as well. The use of technology derived from the Smart Aircraft and Marine ProjectS demonstratiON (SAMPSON) was found to reduce the installation losses, in turn improving specific fuel consumption and net thrust. Additional morphing system concepts will be discussed that could yield a significant increase in performance. However, research and technology projects are still being conducted to determine a reasonable figure for benefits and penalties from these systems. As such, credit for these concepts has not been applied to the current configuration.},

keywords = {22. Weight Engineering - Structural Design, 33. Unmanned Vehicles, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3365,

title = {3365. Firefox: Gunship Structural and Material Considerations},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3365},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {17},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {In response to the 2005 American Institute of Aeronautics and Astronautics (AIAA) Team Undergraduate Design Competition, Paladin Aerospace presents Firefox, a new generation gunship to replace the AC-130. Modern demands have outgrown the aging cargo-based airframe of the AC-130H/U Spooky gunship. First introduced during the Vietnam War in 1968, the AC-130 has been modified and improved to meet the continuously evolving demands of modern warfare. In recent years, the proliferation of Anti-Aircraft Artillery (AAA) and low-cost Man Portable Air Defense Systems (MANPADS) has created a gap in defensive technology. Nearly 80% of all fixed-wing aircraft lost during Operation Desert Storm were to MANPAD systems. Spooky, with its low-altitude, predictable, circular attack patterns was particularly vulnerable to these radar and IR seeking devices. The request for proposal (RFP) requires an affordable, highly survivable aircraft to provide lethal firepower during a 4 hour loiter. Firefox moves away from the cargo-based configuration of the AC-130 to a conventional fuselage sized around a single 105mm Rheinmetall tank gun and three 40mm autocannons. This paper focuses on the methods used to reinforce the aircraft for survivability with advanced materials and provide adequate structural support to endure the gun forces. The blast overpressure, recoil force, and heat generated by each of the four guns create material and structural issues unique to a gunship aircraft. Maintaining a low weight is desired to minimize acquisition cost to meet the affordability requirement of the RFP. Only essential areas are reinforced with high strength, resilient, but heavier or more costly materials.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3376,

title = {3376. Paragon: Structure and Weight Considerations for an Advanced Gunship},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3376},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {31},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {Tip of the Sword Aerospace, of California Polytechnic State University, was presented with the challenge to conceptually design an advanced military gunship. Tip of the Sword Aerospace has responded with Paragon, a highly survivable gunship that has the capability to provide precise and persistent firepower in high threat combat environments. Paragon is in response to the 2004-2005 AIAA Undergraduate Team Design RFP, which calls for an advanced military gunship that can destroy personnel, light armored vehicles, and buildings at low cost. Paragon is an unmanned combat aerial vehicle (UCAV) that employs a conventional configuration with a high wing, H-tail, and tricycle style landing gear. It is equipped with 15,526 pounds of weapons, including two M230 30mm chain guns, 16 HELLFIRE II?s, and 8 GBU-12 Paveway II bombs. Since the Paragon is a UCAV, it can persist in extremely high risk daytime and night-time environments, without risking the lives of a pilot or crew members. This report presents the conceptual approach used to design the Paragon, focusing on the preliminary sizing, weight estimation, and structural layout processes. Initial sizing was primarily driven by the weapons payload requirement of at least 15,000 lbs, a minimum mission radius of 500 n.m., and a four hour time-on-station without refueling. The structural layout was designed to maximize survivability by implementing robust and redundant design features.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3377,

title = {3377. GRYPHON: Considerations of Weight and Structure in the Design of an Advanced Gunship},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3377},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {23},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {In response to the 2004/2005 AIAA Undergraduate Team Aircraft Design Competition?s request for proposal (RFP) for an Advanced Gunship, Fallen Angel Aerospace is pleased to present Gryphon. Gryphon is both highly survivable against MANPADS and AAA and capable of affordable, precise, and persistent firepower. Dorsal mounted engines shield Gryphon?s exhaust plume effectively reducing IR signature and increasing survivability against MANPAD threats. Gryphon features an H-tail for redundant flight controls as well as redundant systems for increased survivability. The primary weapons featured on Gryphon are the GAU-13 for rapid area suppression and the Bushmaster II for pinpoint attacks. These primary weapons are turret mounted to provide flexible and unpredictable attack patterns. Gryphon?s arsenal includes a side mounted howitzer for persistent and flexible heavy firepower. To provide greater standoff and destructive potentiality, Gryphon also features Hellfire missiles and JDAM bombs. The combat mission profile for Gryphon consists of a 500 n.mi. ingress, followed by a four hour loiter and attack period, and a 500 n.mi. egress. Gryphon is a versatile aircraft that effectively fulfills the close air support, airinterdiction and armed reconnaissance roles. Preliminary capability analyses show that three Gryphon aircraft in the close air support role are capable of responding to a situation anywhere in Iraq within 15 minutes. This same task currently requires approximately eight AC-130?s.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3378,

title = {3378. LEBOWSKI: Considerations of Weight and Structure in the Design of an Advanced Gunship},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3378},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {23},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {In response to the AIAA Undergraduate Team Aircraft Design Competition?s request for proposal (RFP) for an Advanced Gunship, Mad Hatter Aerospace proudly presents Lebowski. This Unmanned Combat Aerial Vehicle (UCAV) is a remotely?piloted aircraft designed to maximize mission effectiveness while simultaneously minimizing not only mission cost, but also the overall price of the aircraft. It is armed with a complement of guns and droppable ordnance that optimize the precision, persistence, and affordability of the aircraft. The weapons onboard are: two M230 30mm guns, a Bofors L70 40mm Cannon, two GBU-29 Joint Direct Attack Munitions, and four GBU-39 Small Diameter Bombs. Lebowski is equipped with survivability features that have been optimized to meet specific RFP requirements while minimizing weight and maximizing performance. It can cruise at over 400 knots at 30,000 feet and loiter over the target area for four hours at 20,000 feet. The airfoil selection and wing layout are optimized for the RFP mission and feature a modified 6-series airfoil and a slightly blended wing body. Given the RFP requirements for minimum cost and a 400 knot initial cruise at 30,000 feet, a PW 6124 engine is featured on the Lebowski and is sized by taking conservative estimations of future engine technology advances. The structure of the gunship was designed with versatility, survivability, and cost in mind. Lebowski effectively and efficiently fills the niche between the aging AC-130 airframe and the A-10 attack aircraft.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3344,

title = {3344. Stormcrow: Considerations of Weight and Structure in the Design of an Advanced Tactical Tanker/Transport},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3344},

year  = {2004},

date = {2004-05-01},

booktitle = {63rd Annual Conference, Newport, California},

pages = {20},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Newport, California},

abstract = {In response to Boeing?s request for proposal (RFP) for a tactical tanker/transport aircraft, Ninja Aerospace presents Stormcrow. This aircraft is capable of fulfilling the dual mission requirements set forth in the RFP and takes into account the call for increased survivability. The cargo bay of Stormcrow can accommodate all interim combat brigade vehicles as well as other oversized cargo loadings, with a 70,000 lb cargo capacity. A dual probe/drogue refueling boom, and the ability to fly from 100 knots to above 0.8 Mach allows Stormcrow to refuel any aircraft in the U.S. inventory. Through use of externally blown flaps and robust landing gear, Stormcrow can land at austere airfields with less than 2,000 feet of runway. By employing cascade style thrust reversers, Stormcrow boasts ground maneuverability exceeding that of the C-17 Globemaster III. With a wingspan comparable to that of a C-130, Stormcrow can deliver more payload to smaller airfields for greatly increased throughput. The cargo bay is can be configured for vehicles, personnel or aero-medical uses, to make this a truly versatile aircraft. Through creative shaping and configuration choices, the Stormcrow tactical transport has an average radar return of currently operational non low-observable fighters, greatly reducing the amount of electronic countermeasures needed to mask its presence when in harm?s way. Use of a saw-edged wing, canted H-tail, and fuselage chine, contribute to lower radar cross-section (RCS). Radar absorbing materials (RAM) have been used sparingly to reduce cost, weight, and avoid the high maintenance of such material. Cost and maintenance were foremost throughout the design process. The end result is Stormcrow, a highly versatile aircraft that can be developed and deployed at a reasonable cost to fulfill the military needs for advanced tanker/transports.},

keywords = {22. Weight Engineering - Structural Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3345,

title = {3345. Weight Tracking for Controlled Growth of a Backpackable UAV},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3345},

year  = {2004},

date = {2004-05-01},

booktitle = {63rd Annual Conference, Newport, California},

pages = {95},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Newport, California},

abstract = {Vindication Aerospace proudly presents the Phoenix UAV system, a backpack portable UAV designed to provide day and night over-the-hill reconnaissance in response to the 2003/2004 AIAA Graduate Team Aircraft RFP. The Phoenix will work along side existing man portable UAV systems such as Dragon Eye and Desert Hawk, but it will have greater capability. The Phoenix can operate in 30 knot winds and be launched out of a 20 meter clearing with 10 meter obstacles on all sides. The Phoenix can provide troops with at least one hour on station up to 20 kilometers away. It also packs up into package 0.18 ft3 larger than its competitor, Dragon Eye. This paper is a design report which highlights some of the unconventional ways in which preliminary sizing, weight estimation, and performance analysis can be applied to arrive at a workable solution. The Phoenix is not born out of textbook equations, it is derived from system sizing, derived equations, and real world testing. Because weight is such an integral component of aircraft design, the entire report was deemed relevant to the study of weight tracking and how it influences an evolving design.},

keywords = {22. Weight Engineering - Structural Design, 33. Unmanned Vehicles, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3346,

title = {3346. The Weight and Structural Design of Daedalus, an Airport Adaptive STOL Transport},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3346},

year  = {2004},

date = {2004-05-01},

booktitle = {63rd Annual Conference, Newport, California},

pages = {27},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Newport, California},

abstract = {Poultry in Motion Aerospace presents the Daedalus, an airport adaptive Super Short Take-off and Landing (STOL) transport. The 2003/2004 AIAA undergraduate design competition Request for Proposal (RFP) calls for an airport adaptive STOL transport with a secondary role in the Civil Reserve Air Fleet (CRAF). Poultry in Motion?s answer to the AIAA RFP, Daedalus, consists of a high wing, T-tail configuration, which employs upper surface blowing and a circulation control wing. Features tailored for the airport adaptive transport (AAT) requirement include a stair door, an enlarged rear cargo door with loading ramp, and robust landing gear. A special avionics package facilitates the simultaneous non-interfering (SNI) approach. This report documents progress thus far.},

keywords = {22. Weight Engineering - Structural Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3347,

title = {3347. Weight Study of the HALO: An Advanced Tactical Transport/Tanker},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3347},

year  = {2004},

date = {2004-05-01},

booktitle = {63rd Annual Conference, Newport, California},

pages = {22},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Newport, California},

abstract = {Deus Ex Machina Aeronautics is proud to present the Halo, an advanced Tactical Transport and Tanker (T3) designed in concert with Boeing PhantomWorks to address the current deficiency in strategic and intra-theater transport. The Halo is a high wing, subsonic aircraft powered by two reliable General Electric CF6-80C2 turbofans mounted atop of the fuselage and fed by a dorsal inlet. This arrangement, together with planform edge alignment, endows the Halo with a lower radar cross-section than any current transport and enhances its survivability on the battlefield. The double-wide cargo bay was chosen for its versatility and speedy loading/unloading, a decisive factor in increasing the aircraft?s throughput. The Halo is capable of refueling all aircraft in the U.S. inventory, and is able to get nearer to the threat area thanks to the incorporation of a high level of survivability in the design. In its transport role, the Halo will increase the mobility of ground forces by delivering 70,000 pounds of payload to austere locations close to the front. These locations are currently accessible by C-130s only, which do not possess the internal payload capacity, the survivability, and the range required to fulfill the current mission. Deus Ex Machina Aeronautics designed a cost effective system, a necessity at a time of shrinking defense budgets. A multidisciplinary approach was used between propulsion, aerodynamics, structures, and materials members of the team in order to achieve synergies leading to a highly optimized system under stringent signature constraints, and possessing the lowest takeoff gross weight compatible with impressive mission effectiveness. The cavernous cargo bay, the high wing configuration, and the high lift systems confer the Halo an unparalleled degree of versatility, which enables the undertaking of alternative missions. Affordability is to some extent a function of the number of aircraft produced; the increased procurement numbers stemming from the procurement of the specialized versions guarantees a lower unit acquisition cost across the entire fleet.},

keywords = {22. Weight Engineering - Structural Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3348,

title = {3348. Determination of Weight and Structures for an ESTOL Regional Airliner},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3348},

year  = {2004},

date = {2004-05-01},

booktitle = {63rd Annual Conference, Newport, California},

pages = {21},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Newport, California},

abstract = {A growing problem in the commercial airline industry is a rise in delays due to crowded airport traffic patterns and weather. To address such concerns, the American Institute of Aeronautics and Astronautics (AIAA) has called for an Adaptive Regional Transport aircraft in its 2003-2004 Undergraduate Team Aircraft Design Competition. The requirements driving the design of this aircraft are that it must carry 49 passengers, be essentially capable of flying in all weather conditions, and complete a Simultaneous Non-Interfering (SNI) Approach. The advanced weather systems will theoretically mitigate weather delays. The SNI approach is a spiraling approach above the airport runway, which minimizes delays by utilizing smaller, under-used runways and allowing larger transports the luxury of using the normal larger runways in a conventional matter. Lastly, the aircraft must be converted to complete a wildfire support mission. Flexibility and the capability to complete other missions are desired, but must not be design drivers. Initial sizing was a driving factor in the determination of the configuration. In addition, the desire to convert the aircraft from a regional passenger transport to a wildfire support aircraft was a determining factor in the cabin layout and of structural members. Also related to the weight of the aircraft is the difference in the required payload between the primary mission and the secondary mission. The loading scenarios for this wildfire support scenario were an influential factor in the structural determination of the aircraft as well. This report also covers the effect of growth versions and how the weight of these different growth versions impacted the design process for Vega.},

keywords = {22. Weight Engineering - Structural Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3317,

title = {3317. Weights and Materials Considerations in the Design of an Ultra Heavy Lift Aircraft},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3317},

year  = {2003},

date = {2003-05-01},

booktitle = {62nd Annual Conference, New Haven, Connecticut},

pages = {15},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New Haven, Connecticut},

abstract = {Abrams Haulers Incorporated (AHI) presents the AHI-10, an Ultra Heavy Lift Aircraft (UHLA) designed in response to the 2002-2003 AIAA Undergraduate Team Aircraft Design Competition. The AHI-10 fulfills the military?s need to transport massive amounts of equipment in a short period of time, allowing them to deploy entire army battalions within days, satisfying the Rapid Global Mobility Requirements of Joint Vision 2020. The 2002-2003 AIAA request for proposal (RFP) requires designing an aircraft capable of transporting a payload of 1.2 million pounds. Other payload requirements include ten M1A2 Abram tanks, 60 463L pallets, 300 medical litters, as well as 1000 paratroops. The performance requirements include an unrefueled range of 5000 nautical miles at 500 knots at a cruise altitude of 25,000 feet. The aircraft is also required to take off and land in a distance less than 9,000 feet. The vast amount of cargo requirements along with the strict performance requirements set by the RFP requires in-depth analysis of structures and mass properties. The mass properties analysis plays an important role in the aircraft?s design, due to the necessity of reducing aircraft weight in order to achieve the maximum performance necessary to satisfy the RFP requirements. After thorough design analysis, the aircraft has a length of 311 feet and a wingspan of 300 feet, incorporating an all-surface lifting configuration. The AHI-10 uses eight GE 90-115B power plants producing a takeoff thrust of 128,000 pounds force per engine.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3318,

title = {3318. Weight Study of the Gemini : An Ultra-Heavy Lift Aircraft},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3318},

year  = {2003},

date = {2003-05-01},

booktitle = {62nd Annual Conference, New Haven, Connecticut},

pages = {26},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New Haven, Connecticut},

abstract = {Vesper Design Concepts presents Gemini, an Ultra-Heavy Lift Aircraft in response to the 2002-2003 AIAA Team Undergraduate Aircraft Design Competition. This aircraft is required to carry ten M1A2 Abrams tanks over an unrefueled range of 5,000 n. mi. at 500 kts at an altitude of 25,000 ft. or more. As a conventional aircraft would require a wingspan in excess of 400 ft., Gemini utilizes an unconventional c?wing configuration to limit its span to 300 ft. Weight analysis of an aircraft of such unconventional size and configuration has required/resulted in some interesting weight optimization studies. Empirical methods were the main form of analysis used in creating an optimized weight buildup. Analytical methods were only used to contrast with the empirical ones. Initially, very simple methods based on historical trends and basic parameters were used. These led into more complicated empirical relationships focusing on specific aircraft weight groups. Three different methodologies taken from aircraft design texts, were used to define and optimize the Gemini. These methods, along with known aerodynamic quantities, allowed the wing and canard to be optimized for cruise. The placement of different weight groups on the aircraft allowed construction of its pitching moment equation. This in turn allowed the canard to be optimized for trimming the aircraft during takeoff. The landing gear weight was examined in more detail, as it had to be built to take some unusual conditions, like the 15-feet-per-second vertical descent rate. The structural weight was also examined in more detail, as the empirical estimations most likely did not account for a floor loading as high as Gemini?s.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3231,

title = {3231. The Assailant: An Advanced Deep Interdiction Aircraft On CD-R},

author = {California Polytechnic State University},

url = {https://www.sawe.org/product/paper-3231},

year  = {2002},

date = {2002-05-01},

booktitle = {61st Annual Conference, Virginia Beach, Virginia, May 18-22},

pages = {84},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Virginia Beach, Virginia},

abstract = {Freedom Aerospace, at California Polytechnic State University, San Luis Obispo, is proud to present The Assailant as a contender in the Society of Allied Weight Engineers? 2002 Student Paper Competition. The Assailant is a supersonic, stealth bomber capable of performing, deep interdicting missions of up to a 3,500 nautical mile range at Mach 1.6 supercruise. Using modern statistical weight estimation methods from a variety of reliable sources, aircraft takeoff gross weight is currently estimated 112,500 pounds with a fuel weight fraction of 0.45. Since the aircraft is not expected to enter service for several years from the present, the design benefits from progressive development of new materials and technology to gain positive results in terms of weight control and structural strength. Cost engineering is performed by examining the correlations and carrying out trade studies between the cost of these new advancements and the overall benefits that are gained through their utilization. The Assailant deep interdicting aircraft is designed not only to meet all mission requirements, but also to do so in the most affordable and efficient way possible.},

keywords = {10. Weight Engineering - Aircraft Design, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}