Co-design of aircraft vertical tail and control laws using distributed electric propulsion

Van, Eric Nguyen; Alazard, Daniel; Döll, Carsten; Pastor, Philippe

doi:10.1016/j.ifacol.2019.11.295

Cited by 19 publications

(7 citation statements)

References 8 publications

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“…The idea of the distributed propulsion has been aroused based on the need for a system compatible with advanced aircraft designed to be environmentally friendly, which is commonly a hybrid or fully electric system considered for different sizes of aircraft 4 and it influences the design process and control system of them. 23 In both configurations, such systems have to use propellers or fans to generate propulsion with special design and control 23 considering aerodynamic effects of the propeller and the engine position on the wings, 24 which also requires a new design for the fan and duct. 25 However, the propulsion set introduced by the current study is a system based on jet propulsion, and its working envelope is considerably wider than usual concepts in this category.…”

Section: Analyzing the Resultsmentioning

confidence: 99%

“…DEA compressor creates a higher pressure ratio in comparison with fans and propellers that are usually being used to design full-electric propulsions. 25,23 This specification is a result of its low energy consumption to work. Required energy to operate compressors is a big obstacle for using them in the full-electric aircraft propulsions that make propulsion designers use fans or propellers to configure such aircraft propulsions 26 that make full-electric aircraft's performance limited.…”

Section: Analyzing the Resultsmentioning

confidence: 99%

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A novel hybrid aircraft propulsion based on the DEA compressor—part B: Performance

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This two-parts article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part B of this article explains the performance sizing of the propulsion set designed in part A. Evaluating the performance of the propulsion, computer programs are written for all major components of the both master engine and ancillary thruster. The intake, compressor, detonation process, diffusers, axial turbine, and exit nozzle are modeled under certain flight conditions, and their performances are revealed and analyzed. The flight conditions are considered from the static condition at the sea level up to flight Mach number 5 at an altitude of 20,000 m. The performance of the propulsion set is also compared with some aircraft propulsions modeled by similar studies in all important aspects.

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Section: Analyzing the Resultsmentioning

confidence: 99%

Section: Analyzing the Resultsmentioning

confidence: 99%

A novel hybrid aircraft propulsion based on the DEA compressor—part B: Performance

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In [4], a trim analysis is performed for a conventional aircraft enhanced with DEP over wingspan, showing that the size of the vertical tail can be reduced by 45% by exploiting differential thrust without adversely affecting directional stability. The idea is further explored in [5] together with a H ∞ control methodology in a sequential optimization process, which reduces the area of vertical tail by 60% and lowers the actuator bandwidth, while maintaining the overall control loop bandwidth. In [6], a propeller optimization is applied to a DEP enhanced airplane configuration to decide for the optimal propeller diameter, which shows up to 80% of take-off distance reduction compared to the two-propeller conventional counterpart.…”

Section: Introductionmentioning

confidence: 99%

Attainable Moment Set Optimization to Support Configuration Design: A Required Moment Set Based Approach

2021

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In this paper, we discuss an attainable moment set (AMS) optimization methodology considering a system’s required moment set (RMS). The AMS describes the achievable moments from a system, given its input limits. An RMS, like an AMS, is a convex set in the moment space, describing the required moments for a system to meet the designed mission profile and disturbance rejection requirements. Given the configuration of a system, its mission requirements, and the derived RMS, the proposed optimization maximizes coverage of the AMS onto the RMS, thus ensuring the system possesses the guaranteed controllability to fulfill its required missions from a design level. To achieve this goal, the variables to optimize are chosen as effector settings, such as the installation position and angle of propellers and control surfaces, which effectively change the AMS without a vast impact on major design parameters, such as mass and moment of inertia. Since the optimization includes massive geometry operations of rays intersecting polyhedron, an efficient intersection solver is proposed to speed up the optimization process. The described method is applied to an electric-vertical-take-of-landing vehicle (eVTOL) with eight hover propellers, which delivers a highly improved coverage of the RMS compared to its initial design.

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“…Co-design, therefore, requires a set of aircraft models featuring various control surface configurations. Reference [9,10] obtained linear fractional representation (LFR) of the set of models, where the control surface sizing is parameterized by µ, see Figure 1. The control law and control surface size optimization is then carried out based on this representation.…”

Section: Introductionmentioning

confidence: 99%

“…Recent research on co-design [9,10] focuses on rigid body aircraft design. These are either concerned with the baseline control or distributed propulsion control.…”

Section: Introductionmentioning

confidence: 99%

Grid-Based and Polytopic Linear Parameter-Varying Modeling of Aeroelastic Aircraft with Parametric Control Surface Design

Mocsányi

Takarics

Kotikalpudi

et al. 2020

Fluids

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The main direction of aircraft design today and in the future is to achieve more lightweight and higher aspect ratio airframes with the aim to improve performance and to reduce operating costs and harmful emissions. This promotes the development of flexible aircraft structures with enhanced aeroelastic behaviour. Increased aeroservoelastic (ASE) effects such as flutter can be addressed by active control technologies. Control design for flutter suppression heavily depends on the control surface sizing. Control surface sizing is traditionally done in an iterative process, in which the sizing is determined considering solely engineering rules and the control laws are designed afterwards. However, in the case of flexible vehicles, flexible dynamics and rigid body control surface sizing may become coupled. This coupling can make the iterative process lengthy and challenging. As a solution, a parametric control surface design approach can be applied, which includes limitations of control laws in the design process. For this a set of parametric models is derived in the early stage of the aircraft design. Therefore, the control surfaces can be optimized in a single step with the control design. The purpose of this paper is to describe as well as assess the developed control surface parameterized ASE models of the mini Multi Utility Technology Testbed (MUTT) flexible aircraft, designed at the University of Minnesota. The ASE model is constructed by integrating aerodynamics, structural dynamics and rigid body dynamics. In order to be utilized for control design, control oriented, low order linear parameter-varying (LPV) models are developed using the bottom-up modeling approach. Both grid- and polytopic parametric LPV models are obtained and assessed.

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Co-design of aircraft vertical tail and control laws using distributed electric propulsion

Cited by 19 publications

References 8 publications

A novel hybrid aircraft propulsion based on the DEA compressor—part B: Performance

A novel hybrid aircraft propulsion based on the DEA compressor—part B: Performance

Attainable Moment Set Optimization to Support Configuration Design: A Required Moment Set Based Approach

Grid-Based and Polytopic Linear Parameter-Varying Modeling of Aeroelastic Aircraft with Parametric Control Surface Design

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