2012/2013 AIAA Foundation Graduate Team Aircraft Design Competition

Transcription

1 2012/2013 AIAA Foundation Graduate Team Aircraft Design Competition High Altitude Long Endurance (HALE)Unmanned Aerial System (UAS) for Missile Defense with Directed Energy (DE) Laser Weapon I. Rules-General 1. All graduate AIAA Student Members are eligible and encouraged to participate. 2. An electronic copy of the report in MS Word or Adobe PDF format must be submitted on a CD or DVD to AIAA Student Programs. Total size of the file(s) cannot exceed 20 MB. Students may submit their final report via to the AIAA Student Programs Coordinator (Rachel Andino, rachela@aiaa.org). A Signature page must be included in the report and indicate all participants, including faculty and project advisors, along with students AIAA member numbers and signatures. Designs that are submitted must be the work of the students, but guidance may come from the Faculty/Project Advisor and should be accurately acknowledged. Each proposal should be no more than 100 double-spaced pages (including graphs, drawings, photographs, and appendices) if it were to be printed on 8.5 x 11.0 paper, and the font should be no smaller than 10 pt. Times New Roman. Up to five of the 100 pages may be foldouts (11 x 17 max). 3. Design projects that are used as part of an organized classroom requirement are eligible and encouraged for competition. 4. The prizes shall be: First place-$500; Second place-$300; Third place-$200 (US dollars). Certificates will be presented to the winning design teams for display at their university and a certificate will also be presented to each team member and the faculty/project advisor. One representative from the first place design team may be expected to present a summary paper at the 2013 Aviation Conference. Reasonable airfare and lodging will be defrayed by the AIAA Foundation for the team representative. 5. More than one design may be submitted from students at any one school. 6. If a design group withdraws their project from the competition, the team leader must notify AIAA Headquarters immediately! 7. Team competitions will be groups of not more than ten AIAA Student Members per entry. Individual competitions will consist of only 1 or 2 AIAA Student Member per entry. II. Copyright All submissions to the competition shall be the original work of the team members. Any submission that does not contain a copyright notice shall become the property of AIAA. A team desiring to maintain copyright ownership may so indicate on the signature page but nevertheless, by submitting a proposal, grants an irrevocable license to AIAA to copy, display, publish, and distribute the work and to use it for all of AIAA s current and future print and electronic uses

2 (e.g. Copyright 20 by. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.). Any submission purporting to limit or deny AIAA licensure (or copyright) will not be eligible for prizes. III. Conflict of Interest It should be noted that it shall be considered a conflict of interest for a design professor to write or assist in writing RFPs and/or judging proposals submitted if (s)he will have students participating in, or that can be expected to participate in those competitions. A design professor with such a conflict must refrain from participating in the development of such competition RFPs and/ or judging any proposals submitted in such competitions. III. Schedule and Activities Significant activities, dates, and addresses for submission of proposal and related materials are as follows: A. Letter of Intent 22 March 2013 B. Receipt of Proposal 14 June 2013 C. Announcement of Winners August 2013 Groups intending to submit a proposal must submit a Letter of Intent (Item A), with a maximum length of one page to be received with the attached form on or before the date specified above. LOI may be ed to Rachel Andino (rachela@aiaa.org). If you chose to mail your forms, they must be typed or clearly printed and mailed to: AIAA Student Programs Attn: Student Programs Coordinator 1801 Alexander Bell Drive, Suite 500 Reston, VA The CD containing the finished proposal must be received at the same address on or before the date specified above for the Receipt of Proposal (Item B). IV. Proposal Requirements The technical proposal is the most important factor in the award of a contract. It should be specific and complete. While it is realized that all of the technical factors cannot be included in advance, the following should be included and keyed accordingly: 1. Demonstrate a thorough understanding of the Request for Proposal (RFP) requirements. 2. Describe the proposed technical approaches to comply with each of the requirements specified in the RFP, including phasing of tasks. Legibility, clarity, and completeness of the technical approach are primary factors in evaluation of the proposals. 3. Particular emphasis should be directed at identification of critical, technical problem areas. Descriptions, sketches, drawings, systems analysis, method of attack, and discussions of new techniques should be presented in sufficient detail to permit engineering evaluation of the proposal. Exceptions to proposed technical requirements should be identified and explained. 4. Include tradeoff studies performed to arrive at the final design. 5. Provide a description of automated design tools used to develop the design.

3 V. Basis for Judging 1. Technical Content (35 points) This concerns the correctness of theory, validity of reasoning used, apparent understanding and grasp of the subject, etc. Are all major factors considered and a reasonably accurate evaluation of these factors presented? 2. Organization and Presentation (20 points) The description of the design as an instrument of communication is a strong factor on judging. Organization of written design, clarity, and inclusion of pertinent information are major factors. 3. Originality (20 points) The design proposal should avoid standard textbook information, and should show independence of thinking or a fresh approach to the project. Does the method and treatment of the problem show imagination? Does the method show an adaptation or creation of automated design tools. 4. Practical Application and Feasibility (25 points) The proposal should present conclusions or recommendations that are feasible and practical, and not merely lead the evaluators into further difficult or insolvable problems. VI. Request for Proposal (RFP) High Altitude Long Endurance (HALE) Unmanned Aerial System (UAS) for Missile Defense with Directed Energy (DE) Laser Weapon 1. Opportunity Background In February 2010, the Airborne Laser Program (ABL) demonstrated the capability to destroy ballistic missiles in their boost phase. For that demonstration, the ABL used a chemical laser, which has a limited number of operations before it consumes the chemical reactants and pressurants used to fuel the laser. An advanced, electric powered laser could provide an infinite magazine, given appropriate power supply and storage with allowance for acceptable cooling. Further, a manned aircraft platform to provide missile defense capability would have endurance limitations based on the crew and would require accommodations for the crew, while an unmanned aircraft would not have these restrictions. To provide a more robust solution for airborne missile defense, a future platform has been envisioned: an air vehicle with an electric pumped laser that would provide persistent directed energy presence to deter or defend against a ballistic missile attack. This vehicle would support a broader capability of continuous, multi-day presence on theater. Because adverse weather conditions can significantly degrade the performance of directed energy weapons, operating at highaltitudes (above most weather) is essential to mission feasibility. Additionally, the desired mission endurance on station suggests extended mission times not amenable to a manned aircraft. Further, there are inherent risks due to proximity to the missile launch site enabling boost phase interception. Coupling of these mission conditions have

4 indicate a HALE UAS as a preferred concept, and this request for proposal seeks definition of such a UAS to enable technical and economic feasibility assessment. The proposed aircraft will be a forward deployed, land-based system. Given the high value of this weapon system, the aircraft will operate at standoff range in situations where a potential missile launch site has limited anti-aircraft capability or, if advanced antiaircraft capabilities are present, the aircraft will operate in an airspace protected by other assets. Mission and Payload Takeoff and landing: The aircraft shall be deployed from and recovered from any airport or military base near the theater of operations that can be used by the US Navy s P-8A Poseidon; therefore, the air vehicle must be compatible with available paved runways that are at least 7,000 feet long. Mission Range: The aircraft shall fly from its point of departure to the theater, which may be as far as 2,000 miles from the point of departure. A long-endurance loiter phase shall follow in the theater, and the aircraft shall then fly back to the point of departure. Vertical profile and speed for climb, cruise, and descent are not specified and must be identified in the design proposal. Loiter: The aircraft shall loiter on theater for no less than 24 hours at an altitude of at least 40,000 ft. A maximum loiter time is not specified, but values greater than the minimum (24 hr.) may be desired. This air vehicle requirement relates to but is not the same as multi-day presence on theater. As with the deployment segment, loiter speed(s), vertical profile, and flight pattern(s) are not specified and must be identified in the design proposal. Payload: The DE weapon-related payload description appears in the section Procured Data. Proposers should include additional payload (for example, power storage equipment, heat transport and dissipation equipment) deemed necessary to support the aircraft mission, including firing of the antimissile laser. Additionally, proposers should account for communications and flight control equipment to facilitate operation of the aircraft. Other Design Requirements Entry into Service and Lifetime: The aircraft shall enter into service in It shall be designed to have a service life no less than 20 years. DE Power Supply and Thermal Management: A key design consideration for this concept pertains to subsystem integration of the DE laser weapon into the platform, particularly with regards to weapon power requirements, thermal management, and onboard power generation and storage. Novel concepts for heat dissipation are encouraged, but volume, weight and power requirements for these concepts must be presented as part of the proposal. Proposals must demonstrate that the aircraft has sufficient propulsive power throughout the mission, that sufficient power is available to the DE laser weapon throughout the loiter phase given directed energy delivery requirements, and that heating experienced by components do not degrade mission effectiveness or expected service life. Directed Energy Delivery: The aircraft shall support no less than five consecutive firings of the DE laser weapon, with each lasting no less than 10 seconds. The time between each sequence of five consecutive discharges should be minimized. Theater Presence: For a boost phase intercept mission, the ability to have a presence on-station continuously for several days is critical; depending on aircraft capabilities, it is possible that more than one vehicle may be needed. Presence on theater by one or more aircraft shall be no less than three days.

5 Cost: The total costs of the fleet required to satisfy the above requirements shall be minimized. This includes research, development, test and evaluation (RDT&E), acquisition and operations and maintenance (O&M). Recognizing that the costs of a future directed energy weapon are highly uncertain, the proposers should estimate costs of the air vehicle(s) less costs associated with the directed energy system. The total production number of airframes will vary with the proposer s selected combination of loiter time and number of aircraft to provide three-day continuous coverage; however, proposers should assume that 20 systems capable of three-day coverage will be acquired. In other words, if a single aircraft provides three-day coverage, 20 airframes are needed; if three aircraft provide the three-day coverage, 60 airframes are needed. Tradeoffs of Interest In addition to typical sizing tradeoffs investigating wing geometry and area, installed thrust or power, tail configuration and sizing, there are two types of tradeoffs of specific interest for this study. Tradeoffs between the aircraft design and the fleet size to meet theater persistence requirements are of interest to try to minimize the total cost of providing three-day continuous on station coverage. A propulsion system trade study that considers the number and type of power plant should be undertaken to maximize the final aircraft design s persistence (range & endurance) and power generation while still maintaining the affordability and feasibility of the concept. The team can utilize any propulsion modeling tools they deem appropriate (i.e. engine design programs, guidelines from aerospace design textbooks, open source information, etc.). Provide rationale justifying the propulsion system selection as appropriate for meeting RFP requirements. Design Data Requirements The technical proposal must clearly and concisely present the design of the aircraft covering all relevant aspects, features, and disciplines. Pertinent analyses and studies supporting design choices must be presented with sufficient detail. A full description of the aircraft is expected along with performance capabilities and operational limits. These include, at a minimum: 1. Aircraft weight statement; aircraft center-of-gravity envelope reflecting relevant payloads and fuel allocation. 2. Materials selection for main structural groups and general structural design, including layout of primary airframe structure. 3. Complete geometric description, including clearances, control surfaces, and internal arrangement of relevant payload with particular emphasis on the DE laser weapon. 3-views and 3-D model imagery of appropriate quality are expected. 4. A description of the design mission(s) selected for the proposed concept 5. Important aerodynamic characteristics and aircraft performance descriptions for key mission segments during the design mission (this includes, but is not limited to: L/D, velocity, rate-of-climb, duration, fuel consumption, etc.) 6. Power plant description and characterization of propulsion performance 7. Discussion of power generation and / or storage for the DE laser, supporting sen-

6 sors and other flight equipment including weight and volume 8. Discussion of thermal management to reject heat from the aircraft to the atmosphere, with consideration of maintaining function of the on-board infrared sensors 9. Summary of basic stability and control characteristics; this should include, but is not limited to static margin, pitch, roll and yaw derivatives 10. Performance flight envelope, takeoff and landing performance 11. Data that describes aircraft capability for missions other than the design mission that trade deployment range and onstation loiter time; this must include a self-deployment mission (i.e., maximum range with no on-station loiter). 12. Summary of cost estimate analysis, main cost groups and drivers Procured Data Directed Energy Laser: The following description attempts to provide a reasonable representation for this student design project, and it is not meant to represent any specific laser, or to predict the specific size and performance of any lasers in existence or in development. The description draws upon the stated goals of DARPA s High Energy Liquid Laser Area Defense System (HELLADS) program and assumes that those goals are scalable to the power requirements for defeating ballistic missiles. The weight of the 1-megawatt laser system, including the cooling system for the diodes, is assumed to be 11,025 lb (5000 kg), matching the HELLADS program goal of 5 kg/kw. The volume of the laser system is assumed to be ft 3 (20 m 3 ), also matching the HELLADS goal of 3 m 3 for a 150 kw laser. For this competition, the laser system has a minimum dimension of 8.2 ft (2.5 m); in other words, the laser system may be reconfigured in shape as long as the ft 3 volume is maintained and no dimension is shorter than 8.2 ft. Also for the purposes of this competition, the laser system is assumed to have an electrical-to-optical efficiency of 25%, which is at the high range of solid-state lasers, with the lost power being converted to heat (i.e., to provide a 1-megawatt laser beam, the system requires 4-megawatts of input and generates 3-megawatts of heat). This study may assume that the effective range of the laser for disabling a missile is 250 miles (400 km). Laser Turret: The power of the laser for this system is comparable to that used in the ABL, the turret must house a 1.5 meter telescope similar to that used in the ABL to focus the beam on the target and to collect return images and signals. Assuming advances in materials and actuation systems for beam control for this project, the assumed weight of this turret is 5,500 lb (roughly half of the approximate weight of the turret on the ABL). The turret must be mounted to have a field of regard of ±120 degrees in azimuth and±90 degrees in elevation. Sensors: The aircraft will have infrared sensors for target detection. For this project, the infrared sensor package may be assumed to require 40 kw of power for operation and to be mounted in an external pod 80 inches long, 12 inches in diameter with a weight of 220 lb. The aircraft will also have two 1-kilowatt solid-state lasers; the first will track the target, while the second will measure atmospheric disturbances in the atmosphere to enable proper focus for the main high-energy

7 laser. For this project, these supporting laser sensors may be assumed to have 30% electrical-to-optical efficiency, assuming efficiency of these smaller lasers will exceed that of the high-powered laser. These supporting lasers may also be assumed to have the laser generator and turrets mounted in a separate pod from the infrared sensors; this pod has dimensions of 90 inches in length and 15 inches in diameter. Powerplant: No specific powerplant or propulsion data is provided. Depending upon the proposing team s determination of operating speeds, either propeller or jet propulsion mechanisms are acceptable. Proposing teams should use any level of propulsion modeling they deem appropriate, along with a justification of why the selected modeling is appropriate for their proposal.

8 Intent Form AIAA Graduate Team Aircraft Design Competition Request for Proposal: High Altitude Long Endurance (HALE) Unmanned Aerial System (UAS) for Missile Defense with Directed Energy (DE) Laser Weapon Title of Design Proposal: Name of School: Designer s Name AIAA Member # Graduation Date Degree Team Leader Team Leader In order to be eligible for the AIAA Graduate Team Aircraft Design Competition, you must complete this form and return it to AIAA Student Programs (rachela@aiaa.org) before 22 March 2013, at AIAA Headquarters to satisfy Section IV, Schedule and Activity Sequences of the competition. For any nonmember listed above, a student member application and member dues payment should also be included with this form. Signature of Faculty Advisor Signature of Project Advisor Date Faculty Advisor Printed Project Advisor Printed Date