AIAA/AAS Astrodynamics Specialist Conference and Exhibit 2004
DOI: 10.2514/6.2004-5393
|View full text |Cite
|
Sign up to set email alerts
|

Preliminary Design of Nuclear Electric Propulsion Missions to the Outer Planets

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
2
2
1

Citation Types

0
10
0

Year Published

2006
2006
2022
2022

Publication Types

Select...
4
3
1

Relationship

0
8

Authors

Journals

citations
Cited by 21 publications
(10 citation statements)
references
References 26 publications
0
10
0
Order By: Relevance
“…The Jupiter Icy Moons Orbiter, or JIMO, was a proposed NASA mission to Jupiter that was canceled owing to high cost [46][47][48][49][50]. Yam et al re-examined this problem using the Sims-Flanagan transcription and MBH in 2011 [13].…”
Section: F Example: Jupiter Icy Moons Orbiter (Jimo)mentioning
confidence: 99%
“…The Jupiter Icy Moons Orbiter, or JIMO, was a proposed NASA mission to Jupiter that was canceled owing to high cost [46][47][48][49][50]. Yam et al re-examined this problem using the Sims-Flanagan transcription and MBH in 2011 [13].…”
Section: F Example: Jupiter Icy Moons Orbiter (Jimo)mentioning
confidence: 99%
“…= thrust acceleration, m/s 2 a 0 = nominal acceleration spacecraft can deliver at launch, m/s 2 a * = characteristic acceleration, m/s 2 C 3 = launch energy, km/s 2 c = exhaust velocity, m/s c * = optimal exhaust velocity, m/s f (C 3 ) = launch-vehicle mass fraction G = gravitational vector, m/s 2 g = gravity constant defined as 9.8 m/s 2 I sp = specific impulse, s J 1 = payload mass fraction J 2 = quadratic cost function for constant-power variable I sp k 1 = control variable that determines the power fraction utilized by the spacecraft k 2 = path and time-dependent function that determines the maximum power fraction as a function of the power level at launch m = spacecraft mass, kg m prop = propellant mass, kg m ps = mass of power system, kg m * prop = propellant mass fractioṅ m = mass flow rate, kg/s P j = jet power, W P ppu = power into power processing unit, W r = position vector, m T = thrust, N t = time, s t burn = engine on time, s Z = power weighted burn time, ṡ Z = current-power-to-initial-power utilization ratio α = power system's specific mass, kg/W β = jet-power-to-spacecraft-mass ratio, W/kg β * 0 = optimal initial jet-power-to-mass ratio, W/kg = power mass fraction of spacecraft V = velocity change imparted by engine, m/s V * = normalized V ζ = launch mass utilization factor η = propellant tank coefficient η engine = efficiency of electric propulsion engine η ppu = efficiency of power processing unit = structural coefficient τ = integration dummy variable φ = tank and structural coefficient scaling factor ψ = propellant and tank scaling factor is an active and computationally difficult field of research. In particular, optimization of a combined trajectory, power, and propulsion system is computationally intensive because either a set of coupled two-point boundary-value problems has to be solved or a nonlinear programming problem has to be solved while optimizing over system-level parameters.…”
Section: Nomenclature Amentioning
confidence: 99%
“…The Jupiter Icy Moons Orbiter, or JIMO, was a proposed NASA mission to Jupiter that was cancelled due to high cost [33][34][35][36][37]. This problem was chosen for two reasons.…”
Section: Via Jupiter Icy Moons Orbiter (Jimo)mentioning
confidence: 99%