Fuel-Saving Climb Procedure by Reduced Thrust near Top of Climb

Mori, Ryota

doi:10.2514/1.c035200

Cited by 9 publications

(4 citation statements)

References 14 publications

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“…Although it is recognized that operational changes and trajectory optimizations can further reduce the fuel burn [25,26] and ATR [27], such improved operational schemes are outside the scope of the current study. Nevertheless, it is recommended to perform a simultaneous optimization of the aircraft design and operations to minimize the climate impact, including non-CO 2 effects, in the future by employing similar approaches as were taken in previous studies [23,28].…”

mentioning

confidence: 99%

Airplane Design Optimization for Minimal Global Warming Impact

Proesmans

Vos

2022

Journal of Aircraft

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This paper presents a method to assess the key performance indicators of aircraft designed for minimum direct operating costs and aircraft designed for minimum global warming impact. The method comprises a multidisciplinary aircraft optimization algorithm capable of changing wing, engine, and mission design variables while including constraints on flight and field performance. The presented methodology uses traditional class-I methods augmented with dedicated class-II models to increase the sensitivity of the performance indicators to relevant design variables. The global warming impact is measured through the average temperature response caused by several emission species (including carbon dioxide, nitrogen oxides, and contrail formation) over a prolonged period of 100 years. The analysis routines are verified against experimental data or higher-order methods. The design algorithm is subsequently applied to a single-aisle medium-range aircraft, demonstrating that a 57% reduction in average temperature response can be achieved as compared to an aircraft optimized for minimal operating costs. This reduction is realized by flying at 7.6 km and Mach 0.60, and by lowering the engine overall pressure ratio to approximately 37. However, to compensate for the lower productivity, it is estimated that 13% more climate-optimized aircraft have to be operated for the hypothetical fleet under consideration.

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confidence: 99%

Airplane Design Optimization for Minimal Global Warming Impact

Proesmans

Vos

2022

Journal of Aircraft

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“…On the other hand, the climb maneuver structure is also a relevant factor to resemble real operating conditions. This has been addressed by analyzing different flight profiles (Mori, 2020). Typically, the optimal flight profile follows an exponential ascend.…”

Section: Realistic Conditions Simulationmentioning

confidence: 99%

“…The simulations of this section are aimed to resemble the typical operating conditions of aircraft turbojet automatic control: smoother references with a certain degree of uncertainty in the set-point (caused by the unfiltered noise from the outer control loop). While it is true that the optimal reference depends on the aircraft mission and characteristics, and that the noise is partially limited by the outer control loop bandwidth, the simulation presented in Figure 12 aims at resembling the conditions faced by the thrust controller in articles that dealt with aircraft control (Sun et al, 2019;Kar asek et al, 2019;Mori, 2020). Nonetheless, a deeper analysis of the optimal climb path or the attitude control design stands out of the scope of this article.…”

Section: Realistic Conditions Simulationmentioning

confidence: 99%

Turbojet direct-thrust control scheme for full-envelope fuel consumption minimization

Villarreal-Valderrama

Delgado

Zambrano‐Robledo

et al. 2020

AEAT

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Purpose Reducing fuel consumption of unmanned aerial vehicles (UAVs) during transient operation is a cornerstone to achieve environment-friendly operations. The purpose of this paper is to develop a control scheme that improves the fuel economy of a turbojet in its full operating envelope. Design/methodology/approach A novel direct-thrust linear quadratic integral (LQI) approach, comprised by an optimal observer/controller satisfying specified performance parameters, is presented. The thrust estimator, based in a Wiener model, is validated with the experimental data of a micro-turbojet. Model uncertainty is characterized by analyzing variations between the identified model and measured data. The resulting uncertainty range is used to verify closed-loop stability with the circle criterion. The proposed controller provides stable responses with the specified performance in the whole operating range, even with after considering plant nonlinearities. Finally, the direct-thrust LQI is compared with a standard thrust controller to assess fuel economy and performance. Findings The direct-thrust LQI approach reduced the fuel consumption by 2.1090% in the most realistic scenario. The controllers were also evaluated using the environmental effect parameter (EEP) and transient-thrust-specific fuel consumption (T-TSFC). These novel metrics are proposed to evaluate the environmental impact during transient-thrust operations. The direct-thrust LQI approach has a more efficient fuel consumption according to these metrics. The results also show that isolating the thrust dynamics within the feedback loop has an important impact in fuel economy. Controllers were also evaluated using the EEP and T-TSFC. These novel metrics are proposed to evaluate the environmental impact during transient-thrust operations. The direct-thrust LQI approach has a more efficient fuel consumption according to these metrics. The results also show that isolating the thrust dynamics within the feedback loop has an important impact in fuel economy. Originality/value This study shows the design of an effective direct-thrust control approach that minimizes fuel consumption, ensures stable responses for the full operation range, allows isolating the thrust dynamics when designing the controller and is compatible with classical robustness and performance metrics. Finally, the study shows that a simple controller can reduce the fuel consumption of the turbojet during transient operation in scenarios that approximate realistic operating conditions.

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“…Some of them are based on energy models, some have a totally analytical approach, some research finds the numerical approaches better, and some do explicit simulations to find the solution. Not only the solution but the procedure has also been developed to execute the fuel-efficient climb, for example, the findings of the work 18 reveal that climb procedure can be executed which proposes a way to save the fuel by reducing thrust near the top of climb.…”

Section: Introductionmentioning

confidence: 99%

Aircraft trajectory generation and control for minimum fuel and time efficient climb

Salahudden

Joshi

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents a novel approach for generating the best possible climb trajectory that ensures minimum fuel and time efficient climb. The problem is first formulated using standard steady climb equations, which generate a unique combination of flight velocity and flight path angle at each altitude. A possible scenario, such as air density, mass, available power, and required powered variation with altitude, is taken into account when defining the problem. Thereafter, sliding-mode-based trajectory tracking control is formulated with its design procedures, system stability with applied control inputs, finite-time convergence analysis, and complete architecture. A Hansa-3 research aircraft is considered as an example model to demonstrate the work. The findings of generated trajectory are then produced and discussed. In order to follow the design trajectory and achieve the same, the sliding-mode-based control command is supplied. The novelty of the present work lies in proposed strategy of trajectory generation, wherein the aircraft path and velocity are found out to make the fuel and time efficient climb possible. Subsequently, robust control law is developed which shows the applicability of the proposed work on autopilot. The results show that the proposed controller not only controls the aircraft but is also able to follow the design trajectory with minimal errors. To further explore the impact of aircraft mass on climb performance, repeated set simulation is carried out. The outcome is compared with conventional climb, which promises its practical implementation since the proposed solution is simple and compatible to integrate with the existing aircraft autopilot.

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Fuel-Saving Climb Procedure by Reduced Thrust near Top of Climb

Cited by 9 publications

References 14 publications

Airplane Design Optimization for Minimal Global Warming Impact

Airplane Design Optimization for Minimal Global Warming Impact

Turbojet direct-thrust control scheme for full-envelope fuel consumption minimization

Aircraft trajectory generation and control for minimum fuel and time efficient climb

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