Performances Evaluation for Microlauncher, Mathematical Model

International Journal of Modeling and Optimization, 2019

The paper presents aspects regarding six degree of freedom model used for attitude control of the three stages micro-launcher with a payload up to 50 kg. This work uses two separate attitude control models dedicated for different flight phases. In the ascending phases, we will control the attitude angles related to the start frame, and in injection phases we will control the attitude angles related to the geographical frame. The results analyzed will be the flight parameters in longitudinal, in lateral and in roll movement. Using this model, the attitude control of the launcher can be evaluated. The novelty of the paper consists in alternative attitude angles used for control and in description of guidance signal.

2021

The overarching goal of this research is to prove the feasibility of the application of hybrid rockets for space application in view of its numerous comparative advantages over the solid and liquid propellant rockets. The study provided for the preliminary design and sizing of a 3-stage rocket to launch a 30kg spy satellite into a low Earth orbit of 350 km. The design was validated against three launch vehicles, VEGA, ARAINE, and FALCON rocket with the margin of error between the simulated result and the live launch well within less than 7%. The preliminary design software was developed based on the validated methodologies. The program is capable of sizing a rocket based on user input (target altitude or parking orbit, payload). The software outputs, the number of rocket stages, required thrust, Characteristic Velocity “delta-V”, diameter and length of each stage of the rocket, and other pertinent data. In addition, software was developed to perform trajectory analysis to determine if the vehicle designed would achieve the intended mission of placing a satellite into space. A MATLAB program was written for the computation of the mathematical models used in the design of the nanosatellite. The design software is robust enough to accommodate scaling and utility for a high-end reclusive satellite based on requirement and user input. The Second Phase of the research work hinged on the design of an unconventional rocket-seated unmanned Aerial Vehicle capable of being launched from a rocket. A detailed design of the surveillance UAV was carried out with the necessary features to facilitates its deployment from a 0.65m diameter rocket, launched into suborbital altitudes defined by the user. Simulation of the UAV launch from the rocket at an altitude of 100 m above sea level was presented. The simulation was carried out with the aid of OPEN ROCKET software. A total of 39 performance plots were generated and presented. The tools developed as part of this thesis are; Rocket design and sizing software, Rocket Optimization Software, Satellite Design Software, and Trajectory Analysis Software.

Journal of Aerospace Technology and Management, 2024

Understanding of various aerodynamic factors involved in flight trajectories is fundamental to design launch vehicles. First and foremost, computer simulation is an efficient way of predicting its behavior in the movement across the atmosphere. Considering that the available Brazilian version of Analysis, Simulation and Trajectory Optimization Software for Space Applications (Astos) does not simulate a controlled vehicle in six degrees of freedom (DoF), the aim of this article is to complement the Astos outcomes, particularly evaluating the trajectory of a controlled launch vehicle from liftoff to orbit injection, considering the model of rigid body dynamics with a six DoF. This approach carried out with an in-house developed simulator called Scott that simulated a multistage launcher with three flight configurations. In the Scott computer program, a launcher was modeled with differential equations in six DoF, coupled axes attitude control system, and aerodynamic coefficients that changed as a function of Mach number. These features improved the results generated by Astos software for the same configurations and the same initial conditions. Additionally, the results provided by Scott were close to actual vehicle in terms of attitude change and Mach number reached.

Acta Astronautica, 2018

Multistage launch vehicles of reduced size, such as "Super Strypi" or "Sword", are currently investigated for the purpose of providing launch opportunities for microsatellites. Currently, microsatellites are launched according to timing and orbit requirements of the main payload. The limited costs of mi

Advances in Space Research, 2018

The number of small satellites launched into orbit has enormously increased in the last twenty years. The introduction of new standards of micro-satellites has multiplied the launch demand around the world. Nevertheless, not all the missions can easily have access to space: not all kinds of micro-satellites have granted a deployer system and, furthermore, once a micro-satellite is able to reach it, it cannot usually choose its final orbit. Recently two new platforms have been introduced for the release of micro-satellites as piggy-backs. These platforms are totally operative spacecrafts that act like motherships, and allow to select some parameters of the final orbit of the piggy-backs. They provide a solution for three different nano-satellites standard, and at the same time they are being developed in order to reach more powerful orbital release capabilities in the future. The design and the mission of these platforms are described in this paper.

HAL (Le Centre pour la Communication Scientifique Directe), 2018

As an answer to Europe's need of an independent access to space for small satellites, for which the market is expected to grow, the ALTAIR project (Air Launch space Transportation using an Automated aircraft and an Innovative Rocket) has been launched in the frame of the European Union's Horizon 2020 research innovation program. The project, which is currently in its third and last year, aims at demonstrating the economic and technical viability of an innovative air-launch system whose carrier is a reusable automated aircraft designed specifically for the launch mission. The reference target mission is the launch of the 150 kg total payload weight into a Sun-Synchronous target orbit. The paper presents the main projects results, lessons learned and perspective. In the first part of the paper, we remind the project's objectives, organization and methodology. The objective of cost reduction, which is of paramount importance in the project, is achieved through the use of Multidisciplinary Design Optimization (MDO) approach and appropriate system and technology choices. The second part of the paper is devoted to the technical results of the study. We present the consolidated design of the ALTAIR system, made of a reusable unmanned carrier, an expendable rocket using hybrid propulsion for the main stages and a ground system. We also present the preliminary results analysis of the flight experiments performed with the small scale EOLE demonstrator, which are focused of the carrier/launcher release and the innovative launcher avionics system. In the third part, we present the outline of ALTAIR's business plan and development roadmap.

International Journal of Modeling and Optimization, 2017

The paper presents some aspects regarding the mathematical model and performance evaluation for a two stages strap-on boosters launcher. This work uses two separate models dedicated for each flight phase. For the ascending phase, we will use a three degrees of freedom model in quasi-velocity frame. For the orbital phase, we will use a Gauss perturbing model. The results analysed will be in quasi-velocity frame but also some orbital parameters will be presented. Using these models, the strap-on boosters launcher performances will be evaluated. The novelty of the paper consists in orbital injection approach, with optimal manoeuvre description Index Terms-Mathematical model, orbital injection, strap-on booster launcher performances.

INCAS BULLETIN, 2022

The paper presents the influence of the main design requirements on the optimal two-stage small launcher configuration. The influence of target orbit altitude, payload mass, typical missions, and the type of liquid propellant (oxidizer - fuel pair) used on the launcher characteristics is quantified. The launchers are obtained using a multidisciplinary design optimisation (MDO) algorithm, where the lowest mass configuration capable of accurately inserting the payload into the target orbit is considered to be optimal.

Communications to SIMAI Congress, 2009

The optimization of trajectories performed by air-dropped launcher is a new subject in spaceflight optimization problems. Some analytical formulas are here used to drive numerical algorithms to convergence to optimal solutions. The joint use of analytical ...

This research focuses on the numerical investigation of the aerodynamic and stability characteristics of a Vertical Takeoff and Landing (VTOL) Micro Air Vehicle (MAV). The numerical investigation is divided into two parts: statics and dynamics. In the static analysis, the full configuration of the VTOL MAV as well as various design and operating parameters are investigated. The dynamic analysis is conducted to obtain the dynamic stability derivatives due to angular rate variations. Time and computational costs have always been the issue in the numerical investigation. As a solution, an innovative method termed the Improved-Component Buildup Method (I-CBM) is developed. The results obtained indicate that the VTOL MAV has favorable aerodynamic performances and static stability quality in the longitudinal and directional modes, although it tends to be unstable in the lateral mode. The results also show that the I-CBM provides fast and reasonably accurate prediction of the aerodynamic and stability properties of the MAV.