The propulsion science

Chapter 1: Introduction

Introduction

The propulsion science has been developed for thousands of years, and it was developed based on the idea that mass can be driven one way by expelling part in the other. Different methods are used for propulsion, each of which has benefits, drawbacks, and most of them with a range of inherent risks. However, the need for device checking even before mission operation is common to all the current rocket propulsion systems. In Europe, there are just a few propulsion system research plants. The Lampoldshausen site in Germany – operated by the German Aerospace Center or German Aerospace Center (DLR) since 1962 could be the most widely used and most long-lasting site in operation. Originally designed to test liquid rocket engines, the site is currently being used for research in many fields connected to propulsion systems (Honkawa and Yoozbashizadeh 2019). However, these types of installations are primarily or solely marketable and are required to build propulsion system test platforms. Test platforms are mostly designed for the production and operation of space propulsion systems.

Background

The system’s functioning and efficiency are important to assess not just each part of the system. Full propulsion programs are generally used in a static framework (or testing platform) to perform the practical testing whereby system processes can indeed be directly controlled and regulated. Rocket propulsion testing is also not valuable for manufacturing and business companies. It also plays an important part in academia. Many researchers and students must be eligible to utilize theoretical expertise in reality from learning. Practical propulsion experiments can be carried out for rocket research using potentially predetermined parameter values on a secure, complicated, and stable test platform (Armburster et al., 2020). This will also give researchers the possibility of designing and evaluating novel propulsion technology; for example, additively produced thrust reservoirs.

1.3 Problem Statement

1.4 Aims

The aim of the paper would be to-

Perform a risk and safety review.
Current machine roles and specifications, both technological and practical.
Weigh vulnerability and recommend technological solution(s) for the functionality of the device.
Identify the part of the chosen technological solution(s) for hardware and software products to perform the device’s roles.
conduct proper project cost estimation.
Show the machine architecture preliminary.

1.5 Objectives

This thesis focuses on preparing a full platform for evaluating rocket propulsion systems for primary university use. The propulsion system is small in dimension; it is powered with liquid propellants and is propelled by chemical ignition (Andersson, 2019). It is built in three main words: security, easiness, and trustworthiness. The job would consist of:

to figure out the machinery’s configuration for the device, including the chamber where the thrust is made and the assembly for propellant feeding the chamber.
to check the machine Software Architecture, which consists of a digital control system User interface (DCIS).
to test the propellant by the use of DCIS software by simulated specifications

1.6 Research Questions

The research questions are-

How to figure out the machinery’s configuration for the device, including the chamber where the thrust is made and the assembly for propellant feeding the chamber?
What is the requirement to check the machine Software Architecture, which consists of a digital control system User interface (DCIS)?
How to test the propellant by the use of DCIS software by simulated specifications?

1.7 Rationale

1.8 Hypothesis

1.9 Significance of study 200

1.10 Structure 150

1.11 Summary 150

Reference

Andersson, E., 2019. Preliminary design of a small-scale liquid-propellant rocket engine testing platform.

Armbruster, W., Hardi, J.S., Miene, Y., Suslov, D., and Oschwald, M., 2020. Damping device to reduce the risk of injection-coupled combustion instabilities in liquid propellant rocket engines. Acta Astronautica, 169, pp.170-179.

Honkawa, D.Y. and Yoozbashizadeh, M., 2019. Modular Liquid Propellant Launch Vehicle Design. In AIAA Propulsion and Energy 2019 Forum (p. 3936).