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This paper aims to evaluate the factors that dictate the design of a mini unmanned aircraft system (UAS).

This paper analyses various dimensions that dictate the design criteria for a mini UAS.

Compared to civil applications, design of mini UAS for military application is much more challenging owing to combat restrictions. Topics related to civil applications dominate research in the field of mini UAS, with over 60% of the papers accounting for civil applications. Limited published articles related to military applications are available. While 86% of the in-production mini UAS is primarily meant for military applications, only 9% of the research is devoted to military applications of mini UAS. Most mini UAS, although designed primarily for military applications, are also extensively used for various civil applications. Critical aspects that influence the employment of mini UAS in the tactical battlespace are area of interest, type of operation, type of operational tasks, terrain and network-centric operations. All these factors collectively impact the design of a mini UAS.

According to various studies, mini UAS is the fastest growing segment amongst all classes of UAS. This paper will provide vital inputs to the designers and manufacturers of mini UAS for both military and civil applications.

Mini UAS are in the list of “must-have” for modern militaries across the world and is also growing exponentially in the civil domain. Therefore, it is important to understand the critical factors that dictate the design of mini UAS.

To the best of the authors’ knowledge, such an analysis is not available in the open domain.

This research is associated with the real-time parameters of wide- and narrow-body aircraft to recognize the quantitative relationship framework. This paper aims to find the superiority of aircraft design technology which triggers the reduction in specific fuel consumption (SFC) and economic competitiveness.

The real case study is performed with 22 middle-of-the-market (MoM) aircraft. This paper develops a fuel burn mathematical model for mid-size transport aircraft by a multi-linear regression approach. In addition, sensitivity analysis is performed to establish the authentication of the fuel burn model.

The study reveals that the MoM aircraft would be the future aircraft design in terms of better fuel economy and carbon footprint. From the multi-regression analysis, it is observed that the logarithmic regression model is the best fit for estimating the SFC. Moreover, fineness ratio, aspect ratio, gross weight, payload weight fraction, empty weight fraction), fuel weight fraction, payload, wing loading, thrust loading, range, take-off distance, cruise speed and rate of climb are observed as the suitable parameters which provide the best fitness value as 0.9804.

Several existing literature reveals that a few research has been performed on the MoM aircraft with wide-body configuration. Moreover, mathematical modelling on the fuel consumption was insignificantly found. This study examines several parameters which affect the fuel consumption of a wide-body aircraft. A real-case study for design configurations, propulsive systems, performance characteristics and structural integrity parameters of 22 different MoM aircraft are performed. Moreover, multi-regression modelling is developed to establish the relation between SFC and other critical parameters.

Amongst all classes of unmanned aircraft system (UAS), the rise of the Mini UAS class is the most dominant. Mini UASs are field-deployable systems and hence are not expected to operate from a runway. Therefore, the operating terrain plays an important role in the deployment and employment of the Mini UAS. However, there is limited published work in this area. The impact of terrain is more critical for military applications than civilian applications. The purpose of this paper is to explore the implications of various types of terrain on the employment and deployment of Mini UAS.

This paper explores the implications of various types of terrain on the employment and deployment of Mini UAS.

Mini UAS with field deployable requirements is often launched within the tactical battle area in case of military applications or in close proximity to the intended target area for civilian applications. Due to the size and weight of the Mini UAS, launch and recovery becomes an important factor to be considered. Rotary wing or fixed-wing vertical take-off and landing configuration UAS overcomes the limitations of Mini UAS and hence it is the preferred option. Impact of the terrain is significantly higher for military applications as compared to civil applications. Mountain terrain is the most challenging for Mini UAS operations.

This paper will help the designers configure the UAS as per the operating terrain.

Terrain affects the deployment and employment of Mini UAS and the capabilities of the system with respect to terrain in which it is expected to operate must be considered during the design of a Mini UAS. The paper will help the designers configure the UAS as per the operating terrain.