Conceptual design of a hybrid rocket powered upper stage (HRPUS) demonstrator

1996 ◽  
Author(s):  
P. LaSarge ◽  
S. Ford ◽  
R. Frederick
Keyword(s):  
Conceptual Design ◽  
Hybrid Rocket ◽  
Upper Stage

scholarly journals Conceptual Design of Single-stage Rocket Using Hybrid Rocket byMeans of Genetic Algorithm

2015 ◽  
Vol 99 ◽  
pp. 198-207 ◽  
Author(s):  
Masahiro Kanazaki ◽  
Atthaphon Ariyairt ◽  
Kazuhisa Chiba ◽  
Koki Kitagawa ◽  
Toru Shimada
Keyword(s):  
Genetic Algorithm ◽  
Conceptual Design ◽  
Single Stage ◽  
Hybrid Rocket

scholarly journals Multi-Stage Hybrid Rocket Conceptual Design for Micro-Satellites Launch using Genetic Algorithm

2012 ◽  
Vol 55 (4) ◽  
pp. 229-236 ◽  
Author(s):  
Yosuke KITAGAWA ◽  
Koki KITAGAWA ◽  
Masaki NAKAMIYA ◽  
Masahiro KANAZAKI ◽  
Toru SHIMADA
Keyword(s):  
Genetic Algorithm ◽  
Conceptual Design ◽  
Hybrid Rocket ◽  
Multi Stage

Conceptual design of a hybrid rocket engine utilizing lunar-derived propellants

1990 ◽  
Author(s):  
D. BROWER ◽  
W. ADAMS ◽  
T. KELLY ◽  
C. EWING ◽  
T. WIERSEMA
Keyword(s):  
Conceptual Design ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

Conceptual design studies of an electrically propelled upper stage for deployment of a multi-plane orbital constellation of small spacecraft

2021 ◽  
pp. 76-87
Author(s):  
Aleksandr LEVANDOVICH ◽  
◽  
Dmitry MOSIN ◽  
Aleksandr TYUTYUKIN ◽  
Igor URTMINTSEV ◽  
...  
Keyword(s):  
Conceptual Design ◽  
Electric Propulsion ◽  
Aerodynamic Drag ◽  
Orbital Plane ◽  
Design Studies ◽  
Small Spacecraft ◽  
Solar Arrays ◽  
Upper Stage ◽  
The Difference ◽  
Orbital Constellation

The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper (a space tug) with main engines arrays. It addresses the problem stage (EPUS) — a space transportation stage based on electric propulsion powered by solar of deploying a multi-plane orbital constellation of to in of small spacecraft (SSC) using an electrically propelled upper stage. It proposes change the SSC operational orbital planes based on the effect of precession rates between the parking and the working orbits eccentricity in the Earth gravitational field. Requirements owing have the difference to the effect been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn. It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type.

Uncertainty Analysis and Robust Design for a Hybrid Rocket Upper Stage

2019 ◽  
Vol 56 (5) ◽  
pp. 1424-1431 ◽  
Author(s):  
L. Casalino ◽  
F. Masseni ◽  
D. Pastrone
Keyword(s):  
Uncertainty Analysis ◽  
Robust Design ◽  
Hybrid Rocket ◽  
Upper Stage
Sign in / Sign up

Export Citation Format

Share Document