Author
Klusman Steven Arlen
Bio: Klusman Steven Arlen is an academic researcher. The author has contributed to research in topics: Ground resonance & Landing gear. The author has an hindex of 1, co-authored 3 publications receiving 7 citations.
Topics: Ground resonance, Landing gear
Papers
More filters
Patent•
03 Dec 1976
TL;DR: In this paper, a passive aircraft landing gear system in which the spring rate and damping for aircraft rolling motions about a longitudinal axis are independent of the aircraft vertical motions is presented.
Abstract: A passive aircraft landing gear system in which the spring rate and damping for aircraft rolling motions about a longitudinal axis are independent of the spring rate and damping for aircraft vertical motions, thereby permitting the landing gear system to optimally accomplish both landing impact attenuation and ground resonance instability abatement.
7 citations
Patent•
31 Mar 1978
TL;DR: In this article, the authors present a passif and passif dispositif d'atterrissage for aeronefs, en particulier pour helicopteres, which permet, grâce a cette independance, d'affaiblir au mieux le choc a l'atter rissage and l'instabilite par resonance du soL
Abstract: L'invention concerne un dispositif d'atterrissage pour aeronefs, en particulier pour helicopteres. Le dispositif de l'invention est passif et se caracterise essentiellement en ce que son elasticite et son amortissement en roulis sont independants de son elasticite et de son amortissement pour des mouvements verticaux. Le dispositif de l'invention permet, grâce a cette independance, d'affaiblir au mieux le choc a l'atterrissage et l'instabilite par resonance du soL
Cited by
More filters
Patent•
29 Jan 1979TL;DR: In this paper, a helicopter landing gear assembly includes a pair of crosstubes (20, 22) having struts (28, 30) connected at the outboard ends thereof.
Abstract: A helicopter landing gear assembly includes a pair of crosstubes (20, 22) having a pair of struts (28, 30) connected at the outboard ends thereof. A first of the crosstubes (22) is connected to the helicopter fuselage (16) at a pair of laterally spaced points (24, 26). The second of the crosstubes (20) is joined by a pivot connection (32) to a structural bridge (10) positioned above the second crosstube. The structural bridge (10) is connected at its outer ends to the fuselage main beams (12, 14). The structural bridge (10) connected to the second crosstube (20) permits the helicopter fuselage (16) to pivot about a fore-aft axis thereof to lower the natural roll frequency of the helicopter airframe and therefore increase the margin of stability to prevent ground resonance.
39 citations
Patent•
26 Jul 2005TL;DR: In this article, a method of controlling the hardness of a damper in an aircraft landing gear was proposed, where the aircraft having a structure that is deformable at a natural frequency is adjusted during a contraction of the damper as a function of the natural frequency.
Abstract: In a method of controlling the hardness of a damper in an aircraft landing gear, the aircraft having a structure that is deformable at a natural frequency, the hardness of the damper is adjusted during a contraction of the damper as a function of the natural frequency.
13 citations
Patent•
26 Oct 2012TL;DR: A landing gear vibration absorber of a helicopter with a landing gear comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids to a helicopter's fuselage is described in this paper.
Abstract: The invention is related to a landing gear vibration absorber (1) of a helicopter (2) with a landing gear (3) comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids (4, 5) to a helicopter's fuselage (8). At least one spring-mass system (10, 20, 24) is mounted to the landing gear (3). Said at least one spring-mass system (10, 20, 24) is tuned to the helicopter's main excitation frequency and said at least one spring--mass system (10, 20, 24) being located at or near at least one antinode of the landing gear (3). The invention is related as well to a method of operating a landing gear vibration absorber (1) of a helicopter (2).
9 citations
Patent•
16 May 2016TL;DR: In this paper, an external cargo damping system includes lifting gear and a damping assembly, which is connected in series with the lifting gear, and disposed along the load path to damp vibratory force transmitted between the lifting body attachment and lifting gear ends.
Abstract: An external cargo damping system includes lifting gear and a damping assembly. The lifting gear has a lifting body attachment end and an opposed external cargo end, and defines a load path that extends between the lifting body attachment and external cargo ends of the lifting gear. The damping assembly is connected in series with the lifting gear and is disposed along the load path to damp vibratory force transmitted between the lifting gear lifting body attachment and lifting gear ends.
6 citations
Patent•
17 Nov 2016
TL;DR: In this article, a belly bar is used to attach, carry and release external cargo from a hovering aircraft using an articulated tubing tool connected to an airframe of the hovering aircraft at a first mounting end and at a second mounting end.
Abstract: A belly bar method and apparatus use to attach, carry and release external cargo from a hovering aircraft. The belly bar apparatus has articulated tubing tool connected to an airframe of the hovering aircraft at a first mounting end and at a second mounting end. The articulated tubing tool has a first external catch and a second external catch mounted on the articulated tubing tool. The first external catch is manually configured for optional attach, carry and release of the external cargo via the cyclic. The second external catch is electronically configured for optional attach, carry and release of the external cargo proximate the collective.
5 citations