Log in

Relevant bibliographies by topics / Ascent propulsion systems

Contents

Journal articles
Dissertations / Theses
Books
Book chapters
Conference papers

Academic literature on the topic 'Ascent propulsion systems'

Author: Grafiati

Published: 4 June 2021

Last updated: 17 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Ascent propulsion systems.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Ascent propulsion systems"

1

Mukundan, Vijith, Arnab Maity, Shashi Ranjan Kumar, and U. P. Rajeev. "Ascent Trajectory Optimization of Launch Vehicles with Air-Breathing Propulsion." IFAC-PapersOnLine 52, no. 12 (2019): 274–79. http://dx.doi.org/10.1016/j.ifacol.2019.11.255.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Noor, Ahmed K., and James A. Cuts. "Space Calls." Mechanical Engineering 126, no. 11 (2004): 31–36. http://dx.doi.org/10.1115/1.2004-nov-1.

Full text

Abstract:

This article focuses on the exploration of our solar system that has, in a very literal sense, extended the reach of mankind. Developing the technology of that exploration has extended immensely the capacity of engineering. The new technologies and key capabilities being developed include intelligent robotics, advanced propulsion systems, power generation, avionics, telecommunications, and instruments. Technology for sample acquisition and return encompasses power and propulsion, robust landing, sensors, handling and packaging systems, ascent vehicles, and autonomous rendezvous and capture systems. Measures are needed to ensure that the samples are not contaminated during collection or the return to Earth, and that samples cause no harm to the Earth's environment. Some of the future solar system missions will experience extreme environments. The extreme cold and intense radiation around Europa, or the searing heat and crushing pressure of Venus, would limit the lifetime of systems built with present technology to just minutes. Improved pressure vessels, thermal control, environmentally tolerant electronics, and low-power systems are needed to prolong the lives of vehicles and instruments for these missions.

APA, Harvard, Vancouver, ISO, and other styles

3

Casalino, Lorenzo, Filippo Masseni, and Dario Pastrone. "Optimal Design of Electrically Fed Hybrid Mars Ascent Vehicle." Aerospace 8, no. 7 (2021): 181. http://dx.doi.org/10.3390/aerospace8070181.

Full text

Abstract:

The optimal design of the propulsion system for a potential Mars Ascent Vehicle is analyzed, in the context of the Mars Sample Return Mission. The Mars Ascent Vehicle has to perform an initial ascent phase from the surface and then circularize into a 170 km orbit. A two-stage launcher is taken into account: the same hybrid rocket engine is considered for both stages in order to limit the development costs. A cluster of two, three or four engines is employed in the first stage, whereas a single engine is always used in the second stage. Concerning the feeding system, three alternatives are taken into consideration, namely a blow down, a regulated and an electric turbo-pump feed system. The latter employs an electric motor to drive the oxidizer turbopump, whereas the power is supplied to the motor by lithium batteries. All the design options resulted in viable Mars Ascent Vehicle configurations (payloads are in the range of 70–100 kg), making the hybrid alternative worth considering for the sample return mission. The use of an electric turbo-pump feed system determines the highest vehicle performance with an estimated 10–25% payload gain with respect to gas-pressure feed systems.

APA, Harvard, Vancouver, ISO, and other styles

4

Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Modular Impulsive Green Monopropellant Propulsion System (MIMPS-G): For CubeSats in LEO and to the Moon." Aerospace 8, no. 6 (2021): 169. http://dx.doi.org/10.3390/aerospace8060169.

Full text

Abstract:

Green propellants are currently considered as enabling technology that is revolutionizing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft, and to overcome the growing challenges, particularly related to overcrowded LEOs, and to modern space application orbital maneuver requirements. Green monopropellants are gaining momentum in the design and development of small and modular liquid propulsion systems, especially for CubeSats, due to their favorable thermophysical properties and relatively high performance when compared to gaseous propellants, and perhaps simpler management when compared to bipropellants. Accordingly, a novel high-thrust modular impulsive green monopropellant propulsion system with a micro electric pump feed cycle is proposed. MIMPS-G500mN is designed to be capable of delivering 0.5 N thrust and offers theoretical total impulse Itot from 850 to 1350 N s per 1U and >3000 N s per 2U depending on the burnt monopropellant, which makes it a candidate for various LEO satellites as well as future Moon missions. Green monopropellant ASCENT (formerly AF-M315E), as well as HAN and ADN-based alternatives (i.e., HNP225 and LMP-103S) were proposed in the preliminary design and system analysis. The article will present state-of-the-art green monopropellants in the (EIL) Energetic Ionic Liquid class and a trade-off study for proposed propellants. System analysis and design of MIMPS-G500mN will be discussed in detail, and the article will conclude with a market survey on small satellites green monopropellant propulsion systems and commercial off-the-shelf thrusters.

APA, Harvard, Vancouver, ISO, and other styles

5

Iliffe, Thomas M., and Curt Bowen. "Scientific Cave Diving." Marine Technology Society Journal 35, no. 2 (2001): 36–41. http://dx.doi.org/10.4031/002533201788001901.

Full text

Abstract:

Cave diving is one of the most technical and potential dangerous forms of diving done today. It may involve use of multiple tanks, regulators and gas mixtures or rebreathers, in combination with powerful long-range diver propulsion vehicles, to penetrate thousands of meters into submerged cave systems where direct ascent to the surface in the case of emergencies is impossible. In order to carry out scientific studies under such difficult conditions, individuals must be highly competent and experienced cave divers. In spite of these problems, numerous scientific investigations in the fields of biology, ecology, microbiology, geology, hydrology and archaeology have carried out by cave diving scientists. Exploratory cave divers have provided the initial impetus for this research by exploring and mapping underwater caves.

APA, Harvard, Vancouver, ISO, and other styles

6

Al-Nuaimi, Ohood A., and Dimitrios C. Kyritsis. "Bioalcohol Electrosprays for Practical Propulsion Systems." Journal of Energy Engineering 145, no. 1 (2019): 04018069. http://dx.doi.org/10.1061/(asce)ey.1943-7897.0000584.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Jia, Yongnan, and Long Wang. "Three-dimensional swimming robotic fish with slide-block structure: design and realization." Robotica 32, no. 5 (2013): 823–34. http://dx.doi.org/10.1017/s0263574713001173.

Full text

Abstract:

SUMMARYThis paper focuses on the mechanism design of a slide-block structure and its application on a biomimetic modular robotic fish for three-dimensional swimming. First, as a barycenter-adjustor, the slide-block structure is integrated into a mechanical design of a robotic fish, which is constructed by a control module, a driving module, and a fan-shaped caudal fin. The three-dimensional locomotion of robotic fish is decomposed into two-dimensional locomotion in horizontal plane and ascent–descent locomotion in vertical plane. Both the kinematics of the horizontal swim and the dynamics of the ascent–descent swim are analyzed by the curve fitting method. Finally, experimental results validate the three-dimensional swimming capability of the robotic fish. Furthermore, the impact of two design parameters on the swimming capability of the robotic fish is discussed by the experimental method. The experimental results confirm that the robotic fish with one driving module and a fan-shaped low-aspect-ratio caudal foil can produce higher propulsive speed than other parameter combinations.

APA, Harvard, Vancouver, ISO, and other styles

8

Chaney, Christopher S., Justin K. Bahrami, Patrick A. Gavin, Elijah D. Shoemake, Eric S. Barrow, and Konstantin I. Matveev. "Car-Top Test Module as a Low-Cost Alternative to Wind Tunnel Testing of UAV Propulsion Systems." Journal of Aerospace Engineering 27, no. 6 (2014): 06014005. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000425.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

KIRILIN, Aleksandr N., Ravil N. AKHMETOV, Aleksandr I. BAKLANOV, et al. "Main design characteristics of small scientific and applied-purpose spacecraft based on the Aist-2 unified platform." Space engineering and technology, December 15, 2020, 5–20. http://dx.doi.org/10.33950/spacetech-2308-7625-2020-4-5-20.

Full text

Abstract:

The description of the unified platform of small spacecraft AIST-2 is presented. The platform is intended to accommodate various types of science equipment, Earth remote sensing equipment and onboard support systems. The description of the unified platform design, main onboard systems, ground control facilities, data acquisition and processing is given. The results of design studies, construction and operation of small spacecraft built on the basis of the AIST-2 unified platform are presented. The design, onboard composition, technical characteristics and results of operation of the first small spacecraft in the line – AIST-2D which it was launched on April 28, 2016 in the scope of the first launch campaign from the Vostochny Cosmodrome by the Soyuz-2.1a launch vehicle with the Volga ascent unit are described in detail. The results of design studies on the development of advanced small spacecraft based on the AIST-2 platform capable of functioning as part of the space monitoring system are described. Key words: small spacecraft, unified platform, design configuration, remote sensing of the Earth, stereoscopic image equipment, electro-rocket propulsion system.

APA, Harvard, Vancouver, ISO, and other styles

Dissertations / Theses on the topic "Ascent propulsion systems"

1

Cheng, Wu-Lang, and 程武郎. "Optimal ascent to GEO using laser propulsion system." Thesis, 1993. http://ndltd.ncl.edu.tw/handle/76990549601277075095.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Chang, Chi-Yi, and 張吉毅. "Optimal direct ascent to GEO using laser propulsion system." Thesis, 1994. http://ndltd.ncl.edu.tw/handle/47327631886770076419.

Full text

Abstract:

碩士<br>國立中央大學<br>機械工程研究所<br>82<br>The optimal trajectory for direct ascent to the geosynchronous earth orbit (GEO) with prescribed longitudinal displacement will be solved by using parameter optimization method. The time derivative of the velocity mangitude of the vehicle is assumed to be a polynomial function of the flight time, with the coefficients as free parameters to be selected. The required thrust magnitude and angle are then derived as functions of the state variables and the polynomial. For the thrust acceleration and dynamic pressure constrained, we can fined seven trajectories. Finally there are three equally located launching stations along the Earth's equator.

APA, Harvard, Vancouver, ISO, and other styles

3

Liu, Jia-Ming, and 劉佳明. "Optimal Ascent to GEO Using Laser and Chemical Propulsion System." Thesis, 1995. http://ndltd.ncl.edu.tw/handle/69126595477717857258.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Ascent propulsion systems"

1

In-situ propellant rocket engines for Mars mission ascent vehicle. National Aeronautics and Space Administration, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

2

United States. National Aeronautics and Space Administration., ed. In-situ propellant rocket engines for Mars mission ascent vehicle. National Aeronautics and Space Administration, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

3

United States. National Aeronautics and Space Administration., ed. In-situ propellant rocket engines for Mars mission ascent vehicle. National Aeronautics and Space Administration, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

4

Propulsion systems using in situ propellants for a Mars ascent vehicle. National Aeronautics and Space Administration, 1992.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

5

Minimum Hamiltonian ascent trajectory evaluation (MASTRE) program (update to automatic flight trajectory design, performance prediction, and vehicle sizing for support of shuttle and shuttle derived vehicles) engineering manual: Final report. Marshall Space Flight Center, National Aeronautics and Space Administration, 1993.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

6

-C, Chou H., Bowles J, and United States. National Aeronautics and Space Administration., eds. Near-optimal operation of dual-fuel launch vehicles. American Institute of Aeronautics and Astronautics, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

7

-C, Chou H., Bowles J, and United States. National Aeronautics and Space Administration., eds. Near-optimal operation of dual-fuel launch vehicles. American Institute of Aeronautics and Astronautics, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

8

-C, Chou H., Bowles J, and United States. National Aeronautics and Space Administration., eds. Near-optimal operation of dual-fuel launch vehicles. American Institute of Aeronautics and Astronautics, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

9

-C, Chou H., Bowles J, and United States. National Aeronautics and Space Administration., eds. Near-optimal operation of dual-fuel launch vehicles. American Institute of Aeronautics and Astronautics, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Ascent propulsion systems"

1

Kara, Ozan, and Arif Karabeyoglu. "Hybrid Propulsion System: Novel Propellant Design for Mars Ascent Vehicles." In Propulsion - New Perspectives and Applications [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.96686.

Full text

Abstract:

This chapter briefly introduces hybrid rocket propulsion for general audience. Advantageous of hybrid rockets over solids and liquids are presented. This chapter also explains how to design a test setup for hybrid motor firings. Hybrid propulsion provides sustainable, safe and low cost systems for space missions. Therefore, this chapter proposes hybrid propulsion system for Mars Ascent Vehicles. Paraffin wax is the fuel of the rocket. Propulsion system uses CO2/N2O mixture as the oxidizer. The goal is to understand the ignition capability of the CO2 as an in-situ oxidizer on Mars. CO2 is known as major combustion product in the nature. However, it can only burn with metallic powders. Thus, metallic additives are added in the fuel grain. Results show that CO2 increase slows down the chemical kinetics thus reduces the adiabatic flame temperature. Maximum flammability limit is achieved at 75% CO2 by mass in the oxidizer mixture. Flame temperature is 1700 K at 75% CO2. Ignition quenches below the 1700 K.

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Ascent propulsion systems"

1

WADEL, MARY, and ELIZABETH RONCACE. "Propulsion systems using in situ propellants for a Mars Ascent Vehicle." In 28th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3445.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Pescetelli, Fabrizio, Edmondo Minisci, Christie Maddock, Ian Taylor, and Richard Brown. "Ascent Trajectory Optimisation for a Single-Stage-to-Orbit Vehicle with Hybrid Propulsion." In 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-5828.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Prince, Andrew, Rachel McCauley, Timothy Kibbey, Lisa McCollum, Britt Oglesby, and Philip Stefanski. "Mars Ascent Vehicle Propulsion System Solid Motor Technology Plans." In 2019 IEEE Aerospace Conference. IEEE, 2019. http://dx.doi.org/10.1109/aero.2019.8741851.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Guernsey, Carl. "Mars Ascent Propulsion System (MAPS) technology program - Plans and progress." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3664.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

MORTON, BLAISE. "Dispersion analysis of propulsion system performance in ascent-to-orbit missions." In 25th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2342.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Oglesby, Britt, Andrew Prince, George Story, and Ashley Kam. "Qualification of a Hybrid Propulsion System for a Mars Ascent Vehicle." In 2019 IEEE Aerospace Conference. IEEE, 2019. http://dx.doi.org/10.1109/aero.2019.8741599.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Chandler, Ashley, Brian Cantwell, G. Scott Hubbard, and Arif Karabeyoglu. "A Two-Stage, Single Port Hybrid Propulsion System for a Mars Ascent Vehicle." In 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-6635.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Kara, Ozan, Miray Karpat, and M. Arif Karabeyoglu. "Propulsion System Design for Mars Ascent Vehicles by using the In-Situ CO2." In AIAA Propulsion and Energy 2021 Forum. American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-3248.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Kremer, Frans G. J. "Balance of Moments for Hypersonic Vehicles." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-251.

Full text

Abstract:

Ramjet engines propelling hypersonic flight vehicles will be highly integrated into the vehicle, resulting in strong interactions between the vehicle and the engine. An assessment of these interactions in relation to the flight mission is made by simple but adequate modeling of the flight vehicle aerodynamics and the engine performance. Especially moments associated with the propulsion system are of interest. This paper deals with the pitch moments introduced by the ramjet related forces, which are evaluated by one-dimensional engine performance and by modeling of the inlet and nozzle flow. Furthermore, it discusses the balance of moments for the first stage of a two stage transportation system for an ascent trajectory.

APA, Harvard, Vancouver, ISO, and other styles

10

Matsumura, Shin, and Kimberly Armstrong. "Effects of the Ascent Trajectory on the Operation and Performance of a TSTO ACES Propulsion System." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4649.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!