Low-Cost Satellite Launch System—Aerodynamic Feasibility Study

Olejnik, Aleksander; Kiszkowiak, Łukasz; Zalewski, Piotr; Dziubiński, Adam

doi:10.3390/aerospace9060284

Cited by 5 publications

(2 citation statements)

References 8 publications

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“…The carrier platform for space operations was chosen as the Su-22M4 or MiG-29A combat aircraft, both staying at end-oflife operating phase in the Polish Air Force (Olejnik et al, 2020(Olejnik et al, , 2022a(Olejnik et al, , 2022b. They can fly supersonic and an operational ceiling of over 15,000 m, sufficiently high to consider the launch of a missile with a satellite payload as a viable concept.…”

Section: Configuration Of the Polish Air Launch Systemmentioning

confidence: 99%

Combat aircraft as airborne launch platforms for space rockets

Olejnik

Zalewski²,

Kiszkowiak³

et al. 2022

AEAT

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Purpose The purpose of this study was to analyze the possibility of using combat aircraft including decommissioned as a platform for launching and carrying space rockets with satellites (nano and microsatellites). Thus, an airborne-launcher-to-space-system may be attractive to countries without ground-based space rocket launch sites. Design/methodology/approach For considered launch-to-orbit system configurations, simulations of space rocket effects on aerodynamic characteristics were performed using computational fluid dynamics (CFD ANSYS Fluent) methods. In addition, experimental studies were performed in a wind tunnel to verify the numerical simulations. Discrete models of the aircraft structure were developed for analysis using finite element method (FEM). The analysis of simulated structural properties of the models was carried out to test its stiffness and mass characteristics important for solving the static and dynamic problems of the structure. The validation analyses of aircraft models were based on mass distribution estimation and matching the stiffness properties of the individual airframe structural assemblies. Findings The results of numerical analyses and tunnel tests indicate that the influence of carrier rockets on the change of aerodynamic and strength characteristics of the airframe is rather negligible. The aircraft can be used as launching platforms for space rockets. Simulations have indicated that the aircraft will successfully perform a mission of taking away and launching a rocket of at least about 1,000 kg total weight with a 10 kg space payload included. Practical implications The combat aircraft can be used as launch platforms for space rockets, and the air/rocket set can become the equivalent of responsive space assets for countries with small space budgets. Originality/value The work presents original results obtained by the authors during a preliminary design of a low-cost satellite launch system consisting of a carrier aircraft and a space rocket orbiter. The possibility of using decommissioned combat aircraft as air-launch-to-orbit platforms was taken into consideration. In the absence of aircraft design documentation, reverse engineering methods and techniques were used to develop aircraft geometry and airframe strength structure. Use of CFD, FEM and simulation methods to evaluate system capabilities was demonstrated. Numerical results from CFD simulations were finally verified in experimental tests.

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Section: Configuration Of the Polish Air Launch Systemmentioning

confidence: 99%

Combat aircraft as airborne launch platforms for space rockets

Olejnik

Zalewski²,

Kiszkowiak³

et al. 2022

AEAT

Self Cite

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“…The idea of using a carrier (aircraft) to lift a vehicle above the thickest part of the atmosphere can be also applied to rockets. A concept of using a rocket launched from an aircraft as a low-cost small satellites delivery system is considered in [18]. Regardless of the take-off technique, all those rocket planes perform a horizontal landing.…”

Section: Introductionmentioning

confidence: 99%

The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory

Kwiek

Figat

Goetzendorf‐Grabowski

2023

Aerospace

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The article presents the results of preliminary studies of the parameters of the return flight trajectory of a rocket plane for suborbital tourist flights into space. The rocket plane is designed as a tailless vehicle and has an unconventional arrangement of control surfaces: elevons and side plates that can rotate. The main aim of the research presented in this paper is to investigate the dynamic stability of the rocket plane and the response to control in the return suborbital flight. The secondary objective is to study the behavior of the rocket plane with respect to the initial state of the return flight. The key parameters taken into account in this study are the Mach number and G-load. Moreover, a study of the trim condition, dynamic stability and response to control of a rocket plane in the low part of the stratosphere is presented. The tests were carried out using a numerical simulation of the flight of a rocket plane. Dynamic stability was determined on the basis of time history analysis, and the results were compared with the results obtained by solving the eigenvalues problem. The results revealed that the rocket plane should be equipped with a Stability Augmentation System to improve short period damping at supersonic speeds at moderate altitudes. It can also be concluded that the maximum load G and Ma do not occur at the same height of flight. In terms of the effectiveness of the control surfaces, they start working at an altitude of 55 km. Due to the speed regime, the obtained results can be useful in the design of such objects as rocket planes, highly maneuverable and supersonic aircraft.

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