June 15, 1997
June 15, 1997
June 18, 1997
2.59.1 - 2.59.8
Aircraft Landing Gear Simulation and Analysis1
Derek Morrison2, Gregory Neff 3 and Mohammad Zahraee4
Abstract A computer aided graphical synthesis was undertaken to understand the kinematics of a nose wheel landing gear mechanism such as that on the Lockheed F-16 using Working Model software. The mobility of the design was verified by computer animation.
To contrast the nose gear kinematic simulation, the main landing gear located under the wing of a light weight aircraft such as the Berkut (Ber-koot) was also studied. The Berkut is the product of Experimental Aviation, Inc. (E.A.I) located in Santa Monica, California. This plane was selected because it is representative of the growing market of kit and light weight general aviation aircraft in the 1,000 to 2,000 pound weight range. In this weight class, the Solid-Spring landing gear can be used instead of the oleoshock-strut type used in the F-16.
Computer modeling and finite element analysis are explored to analyze stresses developed while landing at normal sink rates.
The deflections of the main spring gear are calculated and the internal stresses evaluated utilizing the finite element program Stardyne (Research Engineers, Inc.). The results of the modeling and simulation are discussed in this paper.
+PVTQFWEVKQP Mechanism kinematics is a very important area in the design of aircraft landing gear. Gear design largely deals with links that make up the geometry of the landing gear and their spatial relationships. The geometry and kinematics of the gear are functions of the aircraft using the gear. Very seldom can any one kinematic design be used for several different aircraft since the design is a function of the individual aircraft’s need, i.e., weight, space, volume, aircraft’s mission, such as fighter, transport passenger, cargo, etc. Also of importance in the design of aircraft landing gear is the structure. The gear must be able to withstand the shocks of landing and taxiing. A collapse of a landing gear during the landing roll can have devastating effects on the aircraft. This paper seeks to investigate the methods used in the design of landing gear, with an introduction to the kinematics of landing gear design and a detailed structural analyses of a light weight 2000 lb aircraft’s main gear.
#PCN[UKU In this paper two analysis were performed. The first was the kinematic evaluation of a front nose gear such as the Lockheed F-16. The second analysis was a structural study of a main gear for a light weight aircraft such as the Berkut (see figure 3 and 4). The contrasting aircraft and their 1 Sponsored by the Allied Signal/ McNair Summer Undergraduate Research Internship, 1995. 2 McNair scholar, Mailing address: 9546 South Indiana, Chicago, IL 60628. 3 Mailing address: MET Program, Purdue University Calumet, Hammond, IN 46323-2094, e-mail: email@example.com, phone: (219) 989-2465. 4 Mailing address: Purdue University Calumet, Hammond, IN 46323-2094, e-mail: firstname.lastname@example.org, phone: (219) 989-2464.
Morrison, D., & Zahraee, M., & Neff, G. (1997, June), Aircraft Landing Gear Simulation And Analysis Paper presented at 1997 Annual Conference, Milwaukee, Wisconsin. https://peer.asee.org/6415
ASEE holds the copyright on this document. It may be read by the public free of charge. Authors may archive their work on personal websites or in institutional repositories with the following citation: © 1997 American Society for Engineering Education. Other scholars may excerpt or quote from these materials with the same citation. When excerpting or quoting from Conference Proceedings, authors should, in addition to noting the ASEE copyright, list all the original authors and their institutions and name the host city of the conference. - Last updated April 1, 2015