Igniting the Minds of Space Pioneers: Successful Publication of First Issue of Acceleron Aerospace Journal

We are thrilled to present the inaugural issue of Acceleron Aerospace Journal, a momentous milestone in our journey towards fostering scientific innovation and exploration in the realm of aerospace sciences. The successful publication of our first issue stands as a testament to the unwavering dedication and collaborative efforts of our student scholars, contributors, devoted reviewers, and the entire editorial team

Expression of Complete Elliptic Integrals of the First and Second Kind in Terms of Elementary Functions in the Tunnel Mathematics Space

Analytical expressions in closed form of complete elliptic integrals of the first and second kind are obtained in terms of elementary functions. These expressions model the tabular values of integrals quite well, so they can be used for differentiation and integration, as well as for solving certain applied problems. When deriving these expressions in tunnel mathematics space, an additional dependence on the azimuthal angle φ as a parameter appears. Precise adjustment of this parameter allows reducing the error in modeling

Interpreted Investigation Report: Loss of Vikram Lander During Lunar Landing Phase

This article examines India's first science lander mission on 22 July 2019, attempting a historic landing on the Lunar South Pole Region. Communication was lost at 2.1 km above the lunar surface during the rough braking phase. The cause of the Chandrayaan 2 lander "Vikram" failure remains undisclosed. Possible factors such as vibrations, thruster issues, and power depletion are considered. Recommendations include backup power sources and direct communication systems for interplanetary missions. Despite the setback, ISRO proposed "Chandrayaan 3" to explore the lunar polar region. Chandrayaan 2's legacy influences future missions, shaping India's aspirations for pioneering space endeavors. Gratitude is expressed to ISRO for insights gained during live coverage.Comment: Acceleron Aerospace Journal, Volume 1, Issue 2, pp-39-4

A Short Review on ISRO Rocket Engines

The advancement of Indian-class rocket engines has marked a significant milestone, notably with the successful launch of a record-breaking number of satellites into orbit. This achievement is attributed to the successful development of robust rocket engines, such as the Vikas engine. The ongoing efforts to enhance rocket engine capabilities underscore the continuous progress in this domain. In light of this, we have conducted a comprehensive review of all indigenously developed rocket engines in India, assessing their developmental status and reliability. The objective of this study is to highlight the preparedness of ISRO's potent rocket engines and their potential for future orbital launch systems

Design and Analysis of Novel Human Mars Exploration Rover

This paper presents the design and analysis of a NASA human exploration rover, emphasizing the maintenance of strength, stiffness, and stability. The annual competition challenges college students to design, build, and race human-powered, collapsible vehicles over simulated lunar terrain. Key focus areas include manufacturability, cost reduction, and weight optimization. The selected optimal design is validated using conventional hand calculations

Theoretical Design and Overview of Steam Propelled and Nuclear Powered Interplanetary Transit Vehicle for Human Crewed Extraterrestrial Exploration

This article provides a theoretical overview of a spacecraft that utilizes extraterrestrial water resources and controlled nuclear fission to propel itself during interplanetary travel. The spacecraft is equipped with a water extraction module to supply water to a large water-boiler container, a small nuclear reactor, a nuclear heat coupler, and an exhaust nozzle for steam propulsion. When the reactor is activated, the water is transformed into steam through nuclear heat and is stored in a pressurized steam chamber. Once the steam reaches a specific pressure limit, it is released through the nozzle, resulting in steam propulsion and the movement of the spacecraft. The velocity of the spacecraft can be adjusted by controlling the injection of steam into the propulsion chamber. In this study, we have examined the feasibility, design overview, and constraints associated with constructing this type of spacecraft in Low Earth Orbit (LEO). The proposed spacecraft aims to provide faster and more reliable interplanetary transit beyond Mars, utilizing renewable energy resources. Since water resources can be found beyond Mars through asteroids, comets, and moons, the challenge lies not in finding water but in the extraction process. Furthermore, the scientific community requires faster transit vehicles for human exploration of Mars and Ceres. However, no architecture has been proposed for crewed exploration beyond this point. Ultimately, it is hoped that this type of spacecraft will enable future astronauts to undertake deep space exploration missions in the coming decades. The manuscript will delve into the design strategy, challenges, launch vehicles needed for deploying assembling instruments, and the assessment of dimensions and crew capability

Sharp Cone-Broad Cone-Disk: Analytical Solutions in the Tunnel Mathematics Space to the Steady Navier-Stokes Equations in the Area of Boundary Layer for Incompressible Symmetric Flows Entrained by these Rotating Bodies

More than 150 years of history of efforts to solve the Navier-Stokes equation have clearly shown that, applying standard mathematical tools, it is possible to do this in only a small number of simple cases. Therefore, to solve such equations, we can try non-standard methods of mathematical modeling. In this case, the emphasis should be placed not on the mathematical accuracy of the proposed solutions, but on their correspondence to experimental data or solutions to the Navier-Stokes equations obtained by numerical methods. We believe that tunnel mathematics is such a method of mathematical modeling. Main theorem of tunnel mathematics allows us to reduce a system of the steady Navier-Stokes equations to simple ordinary differential equations that give solutions in planes parallel to the basic xy plane. Collecting such solutions, we finally obtain full 3D solution of a system of the steady Navier-Stokes equations. Approximate solutions for a system Sharp cone—Broad cone—Disk in the area of boundary layer can be obtained without use of specific software (including case of turbulent motion of fluid). We get solution for a rotating disk as a limit transition for a broad cone. If such solution will be similar with famous Karman`s solution for a rotating disk (we mean laminar flows), then we could conclude that our theory is successive

Orbital Lifetime Estimation of Rocket Bodies in Eccentric Low Earth, Low Inclination Orbits

The dense population of Low Earth Orbit (LEO) due to frequent launches necessitates precise knowledge of the orbital lifetime of rocket bodies in this region. This study focuses on estimating the orbital lifetime of rocket bodies in eccentric, low-inclination LEO. Using the open-source software General Mission Analysis Tool (GMAT), the orbital lifetimes of rocket bodies with masses of 1000 kg, 1200 kg, and 1400 kg were calculated for altitudes ranging from 250 km to 500 km and inclinations of 0˚, 10˚, and 20˚. The orbital lifetimes of the defunct rocket bodies ranged from 3 to 832 days. GMAT-derived orbital lifetimes were compared with those obtained using Systems Tool Kit (STK). A subsequent 2D interpolation code was developed to interpolate the lifetime for a user-provided configuration of mass and orbital altitude. The Python code interpolated the orbital lifetimes for the given configurations with a maximum error of 5% compared to the GMAT-simulated lifetime values. This approach provides essential data for assessing post-mission disposal plans for rocket bodies and ensuring alignment with the Inter-Agency Space Debris Coordination Committee (IADC) 25-year guideline. Key findings reveal that the orbital lifetime of a rocket body increases with inclination. Additionally, it was observed that the orbital lifetime increases with mass due to slower orbital decay

Beyond Earth: Space Elevators as Catalysts for a Sustainable Multiplanetary Economy

This proposal explores the potential of space elevators to revolutionize space development and establish a multiplanetary economy. It envisions a future where space elevators enable cost-effective access to space and the transportation of heavy payloads, transforming the way we utilize space. The proposal outlines a plan for constructing space infrastructure, including transportation systems, space settlements, and space factories, all facilitated by space elevators. It also addresses the importance of utilizing space resources to restore Earth\u27s environment and create a sustainable future. Furthermore, the proposal discusses the potential applications of space elevators in various fields, including power generation, tourism, defense, and even the preservation of human civilization

From Earth Escape to Lunar Touchdown: A Simulated Lunar Lander Mission

This report investigates the application of design thinking principles to optimize the trajectory and operations of a lunar lander. By considering the spacecraft as the "user" within the design thinking framework, we aim to identify and address critical challenges during key mission phases: Earth Escape, Orbital Insertion, Lunar Transfer Trajectory Injection, and Powered Descent & Lunar Landing. Leveraging the General Mission Analysis Tool (GMAT), we translate design thinking solutions into testable virtual prototypes, allowing for iterative refinement and optimization of the mission plan. This approach prioritizes efficiency and functionality, ultimately paving the way for more cost-effective and successful lunar exploration endeavors