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Article
Publication date: 25 February 2021

Marcin Figat and Agnieszka Kwiek

The aim of the research is to conduct a study into a configuration of an aircraft system with a focus on aerodynamics. In addition, trim condition and static stability constraints…

Abstract

Purpose

The aim of the research is to conduct a study into a configuration of an aircraft system with a focus on aerodynamics. In addition, trim condition and static stability constraints were included. The main application of this system is suborbital space flights. The presented concept of a modular airplane system (MAS) consists of two vehicles: a Rocket Plane and a Carrier. Both are designed in tailless configurations but coupled formed a classic tail aircraft configuration, where the Rocket Plane works as the empennage. The most important challenge is to define the mutual position of those two tailless vehicles under the assumption that each vehicle will be operating alone in different flight conditions while joined in one object create a conventional aircraft. Each vehicle configuration (separated and coupled) must fulfil static stability and trim requirements.

Design/methodology/approach

Aircrafts’ aerodynamic characteristics were obtained using the MGAERO software which is a commercial computing fluid dynamics tool created by AMI Aero. This software uses the Euler flow model. Results from this software were used in the static stability and trim condition analysis.

Findings

The main outcome of this investigation is a mutual position of the Rocket Plane and the Carrier that fulfils project requirements. Also, the final configuration of both separated vehicles (Rocket Plane and Carrier) and the complete MAS were defined. In addition, it was observed that in the case of classic aircraft configuration which is created by connecting two tailless vehicles increasing horizontal tail arm reduces static stability. This is related to a significantly higher mass ratio of the horizontal tail (the Rocket Plane) with respect to the whole system. Moving backward, the Rocket Plane has a notable effect on a position of a centre of gravity of the whole system static stability. Moreover, the impact of the mutual vehicles’ position (horizontal tail arm) and inclination angle on the coupled vehicle lift to drag ratio was analysed.

Research limitations/implications

In terms of aerodynamic computation, MGAERO software using an inviscid flow model, therefore, both a friction drag and breakdown of vortex are not considered. But the presented research is for the computation stage of the design, and the MGAERO software guarantees satisfactory accuracy with respect to the relatively low time of computations. The second limitation is that the presented results are for the conceptual stage of the design and dynamic stability constraints were not taken into account.

Practical implications

The ultimate goal of the coupled aircraft project is to conduct flying tests and the presented result is one of the milestones to achieve this goal.

Originality/value

A design process for a conventional aircraft configuration is well known however, there are not many examples of vehicles that consist of two coupled aircrafts where both vehicles have similar mass. The unique part of this paper includes results of the investigation of the mutual position of the vehicles that can fly alone, as well as in coupled form. The impact of the position of the centre of gravity on trim conditions and static stability of the coupled configuration was investigated.

Details

Aircraft Engineering and Aerospace Technology, vol. 93 no. 2
Type: Research Article
ISSN: 1748-8842

Keywords

Article
Publication date: 5 April 2021

Agnieszka Kwiek, Cezary Galinski, Krzysztof Bogdański, Jaroslaw Hajduk and Andrzej Tarnowski

According to the study of the space flight market, there is a demand for space suborbital flights including commercial tourist flights. However, one of the challenges is to design…

Abstract

Purpose

According to the study of the space flight market, there is a demand for space suborbital flights including commercial tourist flights. However, one of the challenges is to design a mission and a vehicle that could offer flights with relatively low G-loads. The project of the rocket-plane in a strake-wing configuration was undertaken to check if such a design could meet the FAA recommendation for this kind of flight. The project concept assumes that the rocket plane is released from a slowly flying carrier plane, then climbs above 100 kilometers above sea level and returns in a glide flight using a vortex lift generated by the strake-wing configuration. Such a mission has to include a flight transition during the release and return phases which might not be comfortable for passengers. Verification if FAA recommendation is fulfilled during these transition maneuvers was the purpose of this study.

Design/methodology/approach

The project was focused on the numerical investigation of a possibility to perform transition maneuvers mentioned above in a passenger-friendly way. The numerical simulations of a full-scale rocket-plane were performed using the simulation and dynamic stability analyzer (SDSA) software package. The influence of an elevator deflection change on flight parameters was investigated in two cases: a transition from the steep descent at high angles of attack to the level glide just after rocket-plane release from the carrier and an analogous transition after re-entry to the atmosphere. In particular, G-loads and G-rates were analyzed.

Findings

As a result, it was found that the values of these parameters satisfied the specific requirements during the separation and transition from a steep descent to gliding. They would be acceptable for an average passenger.

Research limitations/implications

To verify the modeling approach, a flight test campaign was performed. During the experiment, a rocket-plane scaled model was released from the RC model helicopter. The rocket-plane model was geometrically similar only. Froude scales were not applied because they would cause excessive technical complications. Therefore, a separate simulation of the experiment with the application of the scaled model was performed in the SDSA software package. Results of this simulation appeared to be comparable to flight test results so it can be concluded that results for the full-scale rocket-plane simulation are also realistic.

Practical implications

It was proven that the rocket-plane in a strake-wing configuration could meet the FAA recommendation concerning G-loads and G rates during suborbital flight. Moreover, it was proven that the SDSA software package could be applied successfully to simulate flight characteristics of airplanes flying at angles of attack not only lower than stall angles but also greater than stall angles.

Social implications

The application of rocket-planes in a strake-wing configuration could make suborbital tourist flights more popular, thus facilitating the development of manned space flights and contributing to their cost reduction. That is why it was so important to prove that they could meet the FAA recommendation for this kind of service.

Originality/value

The original design of the rocket plane was analyzed. It is equipped with an optimized strake wing and is controlled with oblique, all moving, wingtip plates. Its post-stall flight characteristics were simulated with the application of the SDSA software package which was previously validated only for angles of attack smaller than stall angle. Therefore, experimental validation was necessary. However, because of excessive technical problems caused by the application of Froude scales it was not possible to perform a conventional test with a dynamically scaled model. Therefore, the geometrically scaled model was built and flight tested. Then a separate simulation of the experiment with the application of this model was performed. Results of this separate simulation were compared with the results of the flight test. This comparison allowed to draw the conclusion on the applicability of the SDSA software for post-stall analyzes and, indirectly, on the applicability of the proposed rocket-plane for tourist suborbital flights. This approach to the experimental verification of numerical simulations is quite unique. Finally, a quite original method of the model launching during flight test experiment was applied.

Details

Aircraft Engineering and Aerospace Technology, vol. 93 no. 9
Type: Research Article
ISSN: 1748-8842

Keywords

Article
Publication date: 1 October 1955

THIS sixth Congress was perhaps the most momentous one in view of the fact that for the first time Russian delegates attended one of these gatherings, and that both the United…

Abstract

THIS sixth Congress was perhaps the most momentous one in view of the fact that for the first time Russian delegates attended one of these gatherings, and that both the United States and the Soviet Union announced that satellite vehicles would be established in the near future. At the conclusion of the Congress many of the delegates still found it hard to believe that at last something practical was being done in astronautics.

Details

Aircraft Engineering and Aerospace Technology, vol. 27 no. 10
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 August 1959

COST AND EFFICIENCY. The economics of corrosion, like the economics of society, is a matter of continuous debate. In any attempt to cost the effects of corrosion and…

Abstract

COST AND EFFICIENCY. The economics of corrosion, like the economics of society, is a matter of continuous debate. In any attempt to cost the effects of corrosion and anti‐corrosion measures what criterion should be selected as the most important? The extent of damage due to corrosion; the cost of applying protection; the probable extent of damage had protection measures not been applied? These, and other factors, have all to be taken into account before any rational approach to the problem can be made. It is a matter of regret that, in this country at least, there has been no real systematic study of the corrosion problem with a view to establishing valid criteria for costing corrosion and anti‐corrosion procedures in industry.

Details

Anti-Corrosion Methods and Materials, vol. 6 no. 8
Type: Research Article
ISSN: 0003-5599

Article
Publication date: 2 October 2018

Agnieszka Kwiek

The purpose of this research is a study into a mathematical approach of a tailless aircraft dynamic stability analysis. This research is focused on investigation of influence of…

Abstract

Purpose

The purpose of this research is a study into a mathematical approach of a tailless aircraft dynamic stability analysis. This research is focused on investigation of influence of elevons (elevator) on stability derivatives and consequently on the aircraft longitudinal dynamic stability. The main research question is to determine whether this impact should be taken into account on the conceptual and preliminary stage of the analysis of the longitudinal dynamic stability.

Design/methodology/approach

Aerodynamic coefficients and longitudinal stability derivatives were computed by Panukl (panel methods). The analysis of the dynamic stability of the tailless aircraft was made by the Matlab code and SDSA package.

Findings

The main result of the research is a comparison of the dynamic stability of the tailless aircraft for different approaches, with and without the impact of elevator deflection on the trim drag and stability derivatives.

Research limitations/implications

This paper presents research that mostly should be considered on the preliminary stage of aircraft design and dynamic stability analysis. The impact of elevons deflection on the aircraft moment of inertia has been omitted.

Practical implications

The results of this research will be useful for the further design of small tailless unmanned aerial vehicles (UAVs).

Originality/value

This research reveals that in case of the analysis of small tailless UAVs, the impact of elevons deflection on stability derivatives is bigger than the impact of a Mach number. This impact should be taken into consideration, especially for a phugoid mode.

Details

Aircraft Engineering and Aerospace Technology, vol. 91 no. 3
Type: Research Article
ISSN: 1748-8842

Keywords

Content available
Article
Publication date: 9 November 2021

Tomasz Goetzendorf-Grabowski

Abstract

Details

Aircraft Engineering and Aerospace Technology, vol. 93 no. 9
Type: Research Article
ISSN: 1748-8842

Article
Publication date: 1 March 1946

P. Bielkowicz

THE task of any recoil engine consists in transforming the chemical energy of fuel into the kinetic energy of gases leaving the nozzle. This article gives a brief survey of…

Abstract

THE task of any recoil engine consists in transforming the chemical energy of fuel into the kinetic energy of gases leaving the nozzle. This article gives a brief survey of problems connected with transformations which the energy undergoes on the way from the fuel containers to the end of the nozzle. I have simplified as far as possible the problem, examining only the conditions in a rocket engine, without a gas turbine. Even in these simplified schemes the phenomena inside the combustion chamber and the nozzle are rather complicated and require careful examination.

Details

Aircraft Engineering and Aerospace Technology, vol. 18 no. 3
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 1 April 1976

BARRINGTON NEVITT

Having substituted abstract Nature for actual existence, we vainly strive to reduce percepts to concepts and the simultaneous harmonies of living to the sequential logic of…

Abstract

Having substituted abstract Nature for actual existence, we vainly strive to reduce percepts to concepts and the simultaneous harmonies of living to the sequential logic of thinking. Our feedback controls can only react to common denominators derived from past stabilities. When change itself becomes the new norm, the old ground‐rules and controls alike break down. Only by using all our common senses can we recognize the new process patterns of the present situation. We can then feed these patterns forward to bypass their hitherto inevitable consequences. Today, freedom is the anticipation of necessity.

Details

Kybernetes, vol. 5 no. 4
Type: Research Article
ISSN: 0368-492X

Article
Publication date: 1 September 1939

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory…

Abstract

Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Committee, Reports and Technical Notes of the U.S. National Advisory Committee for Aeronautics and publications of other similar research bodies as issued

Details

Aircraft Engineering and Aerospace Technology, vol. 11 no. 9
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 30 November 2004

David J. LePoire

Information Technology (IT) has ushered in not only large societal opportunities but also large uncertain ‐ ties and risks. Future developments, like ubiquitous networked embedded…

Abstract

Information Technology (IT) has ushered in not only large societal opportunities but also large uncertain ‐ ties and risks. Future developments, like ubiquitous networked embedded systems, are technologies society may face. Such technologies offer larger opportunities and uncertainties because of their ability to widely distribute power through their small, inexpensive, and ubiquitous characteristics. Many interpretations of how these technologies may develop have been postulated, ranging from the conservative Precautionary Principle, to uncontrolled development leading to “singularity.” With so much uncertainty and so many predictions about the benefits and consequences of these technologies, it is important to raise ethical questions, determine potential scenarios, and try to identify appropriate decision points and stakeholders. Rather than going along an unknown path, perhaps lessons could be learned from recently deployed technologies, such as nuclear technology, that were controversial but offered similarly large potential benefits and risks. The experience of nuclear technology development, with its various successes and failures, is recalled and compared with potential scenarios in the development of networked embedded systems

Details

Journal of Information, Communication and Ethics in Society, vol. 2 no. 4
Type: Research Article
ISSN: 1477-996X

Keywords

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