Amphibious airplane for underwater observation: Conceptual design

This paper aims at presenting the conceptual design of an amphibious airplane for underwater observation in the territory of Japan. Taking into account the specificity of this type of vehicles, particular attention should be paid to the analysis of aerodynamic and dynamic characteristics of aircraft. In order to cope up with this topic, commercial tools have been exploited (such as ANSYS Fluent for wing aerodynamics analysis) as well as the home-built software PANUKL package for aerodynamic analysis of the entire airplane and simulation and dynamic stability analysis for dynamic analysis. Special attention was given to the priorities resulting from understanding the characteristics of the Japanese client.

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Conceptual design of an aircraft for Mars mission

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-08-2018-0231 ◽

2019 ◽

Vol 91 (6) ◽

pp. 886-892

Author(s):

Agnieszka Kwiek

Keyword(s):

Stability Analysis ◽

Dynamic Stability ◽

Conceptual Design ◽

Design Stage ◽

Content Type ◽

Mars Mission ◽

Longitudinal Dynamic ◽

Short Period ◽

The Impact ◽

Tailless Aircraft

Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic stability was computed by MATLAB code, and the derivatives computed by the SDSA software were used as the input data. Different aircraft configurations have been studied, including different wing’s aerofoils and configurations of the side plate. Findings This paper presents results of aerodynamic characteristics computations and longitudinal dynamic stability analysis. This paper shows that tailless aircraft configuration has potential to be used as Martian aircraft. Moreover, the study of the impact of side plates’ configurations on the longitudinal dynamic stability is presented. This investigation reveals that the most effective method to improve the short period damping ratio is to change the height of the bottom plate. Practical implications The presented result might be useful in case of further design of the aircrafts for the Mars mission and designing the aircrafts in a tailless configuration. Social implications It is considered by the human expedition that Mars is the most probable planet to explore. This paper presents the conceptual study of aircraft which can be used to take the high-resolution pictures of the surface of Mars, which can be crucial to find the right place to establish a potential Martian base. Originality/value Most of aircrafts proposed for the Mars mission are designed in a configuration with a classic tail; this paper shows a preliminary calculation of the tailless Martian aircraft. Moreover, this paper shows the results of a dynamic stability analysis, where similar papers about aircrafts for the Mars mission do not show such outcomes, especially in the case of the tailless configuration. Moreover, this paper presents the results of the dynamic stability analysis of tailless aircraft with different configurations of the side plates.

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Conceptual Design of a 200 Passenger Blended Wing Body Aircraft

Volume 1: Advances in Aerospace Technology ◽

10.1115/imece2014-36676 ◽

2014 ◽

Cited By ~ 1

Author(s):

Sami Ammar ◽

Jean-Yves Trépanier

Keyword(s):

Dynamic Stability ◽

Conceptual Design ◽

Aircraft Design ◽

Optimization Methods ◽

Integrated Optimization ◽

Aerodynamic Analysis ◽

Performance Improvements ◽

Static And Dynamic Stability ◽

Blended Wing Body ◽

Large Aircraft

The Blended Wing Body (BWB) aircraft is based on the flying wing concept. For this aircraft the literature has reported performance improvements compared to conventional aircraft. However, most BWB studies have focused on large aircraft and it is not sure whether the gains are the same for smaller aircraft. The main objective of this work is to perform the conceptual design of a 200 passengers BWB and compare its performance against an equivalent conventional A320 aircraft in terms of payload and range. Moreover, an emphasis will be placed on obtaining a stable aircraft, with the analysis of static and dynamic stability. The design of BWB was carried out under the platform called Computerized Environment for Aircraft Synthesis and Integrated Optimization Methods (CEASIOM). This design platform, suitable for conventional aircraft design, has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the BWB aircraft.

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Tip-Over Stability Analysis of Mobile Boom Cranes With Swinging Payloads

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.4023276 ◽

2013 ◽

Vol 135 (3) ◽

Cited By ~ 7

Author(s):

Andreas Rauch ◽

William Singhose ◽

Daichi Fujioka ◽

Taft Jones

Keyword(s):

Stability Analysis ◽

Dynamic Analysis ◽

Dynamic Stability ◽

Dynamic Method ◽

Static Stability ◽

Multibody Simulation ◽

The World ◽

The Stability ◽

Boom Crane ◽

Mobile Base

Mobile boom cranes are used throughout the world to perform important and dangerous manipulation tasks. The usefulness of these cranes is greatly improved if they can utilize their mobile base when they lift and transfer a payload. However, crane motion induces payload swing. The tip-over stability is degraded by the payload oscillations. This paper presents a process for conducting a stability analysis of such cranes. As a first step, a static stability analysis is conducted to provide basic insights into the effects of the payload weight and crane configuration. Then, a semi-dynamic method is used to account for payload swing. The results of a full-dynamic stability analysis using a multibody simulation of a boom crane are then compared to the outcomes of the simpler approaches. The comparison reveals that the simple semi-dynamic analysis provides good approximations for the tip-over stability properties. The results of the stability analyses are verified by experiments. The analysis in this paper provides useful guidance for the practical tip-over stability analysis of mobile boom cranes and motivates the need to control payload oscillation.

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