Multidisciplinary optimisation of single-stage sounding rockets using solid propulsion

Okniński, Adam

doi:10.1016/j.ast.2017.09.039

Cited by 15 publications

(2 citation statements)

References 12 publications

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“…The purpose of this paper is to implement a mathematical model for the design of ion thrusters as a part of the propulsion module of the IDR/UPM CDF, taking as an example the approach used in different studies for solid and liquid chemical rockets (Leto et al, 2016;Okninski, 2017), where simple equations are used to provide a rapid and easy estimation of the main parameters. The equations included in the electric propulsion sub-module allow the calculation of optimum values for the main design parameters, considering as constant values the mass of the rest of subsystems and the velocity increment determined by the mission, which are provided by other modules.…”

Section: Electric Propulsionmentioning

confidence: 99%

Optimum preliminary design of ion thrusters in concurrent design facility

García-Pérez

2020

Concurrent Engineering

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In recent years, the development of new satellites has accelerated, especially for small satellites like university-class Cubesats, due to low design and manufacturing costs. The preliminary design of these spacecraft requires the utilization of new tools that improve the interrelation among the different subsystems and optimize the design. One of the most suitable approaches is the concurrent design facility, which connects specialists of each subsystem in the same room to facilitate the communication among them. This method provides different preliminary designs for the complete system by an iterative process in a reduced time, taking into account the simultaneity with the designs of the subsystems. One of the main subsystems of a spacecraft is the propulsion system, which plays a key role in the success of a mission by allowing the spacecraft to reach the final destination. Electric propulsion has become an interesting option due to the high value of the specific impulse, which provides the necessary velocity increment with a lower propellant mass compared to the traditional chemical rockets. The purpose of this paper is to present the equations implemented in the propulsion module of the concurrent design facility to obtain optimum designs of ion thrusters, which supposes a novelty compared to the traditional design approach of these systems, where there is no interaction with the design of the rest of subsystems. The objective is to help the designer to select the best options in a fast and easy way and improve the efficiency of the iterative work of the concurrent design facility.

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Section: Electric Propulsionmentioning

confidence: 99%

Optimum preliminary design of ion thrusters in concurrent design facility

García-Pérez

2020

Concurrent Engineering

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“…Over the years, that enabled assessing Scout orbital capabilities and reentry missions. The single-stage sounding rocket concept is now trending to replace old designs using surplus military rocket motor setups (Okninski, 2017), which is connected with the extensive development of hybrid engines (Faenza et al, 2017). Ramjet-based "aerospaceplanes" are being introduced (Russo & Voto, 2023) and the use of near space for the development of science through low-cost and adjustable suborbital flights is currently at its best (Fitzpatrick, 2020;Rasanova, 2022).…”

Section: Introductionmentioning

confidence: 99%

Lessons learned and the recent achievements of a three-stage suborbital rocket production

Cichocki,

Sokolowski

2023

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The project presented in this article, which consists in designing and launching a three-stage suborbital rocket with a 40 kg payload covers the subjects of the rapid development of a multi-stage proof-of-concept vehicle with a limited time to deploy. These finite resources and a negligible percentage of the technology available tested in-house in advance led to the implementation of chosen, well-known industrial solutions into the concept for a winning strategy. This paper presents the recent achievements and lessons learned from the production phase of the components, namely: the rocket motor, control section compartment, guidance and navigation bay, together with recent achievements and future challenges. This set of components, derived from the project, will fill the gap in the technological chain for future Polish launchers and munition. The three-stage suborbital rocket development project is divided into three phases, which will last a total of three years. The first phase is the conceptual design stage, along with laboratory tests of solutions and subsystems used in the rocket. The second phase consists in flight tests for individual stages, together with the decisive flight of a three-stage rocket made to reach the Kármán line. The final stage involves the commercialization of the developed technology and the creation of a service for carrying research loads of up to 40 kg. The project is valued at approximately USD 5 million. The project is co-financed by the National Centre for Research and Development (NCRD) as part of dedicated support for the Polish space industry.

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