Presentation is loading. Please wait.

Presentation is loading. Please wait.

Low-Thrust Transfers from GEO to Earth-Moon Lagrange Point Orbits Andrew Abraham Moravian College, 2013.

Published byOlivia Hood Modified over 9 years ago

Similar presentations

Presentation on theme: "Low-Thrust Transfers from GEO to Earth-Moon Lagrange Point Orbits Andrew Abraham Moravian College, 2013."— Presentation transcript:

1 Low-Thrust Transfers from GEO to Earth-Moon Lagrange Point Orbits Andrew Abraham Moravian College, 2013

2 Newton’s Laws

3 Orbits: Inertial Reference Frame

4

5 Orbital Trajectories

6 Circular Orbit

7 Applications of Various Orbits

8 Low Earth Orbit (LEO)

9 Medium Earth Orbit (MEO)

10 Geosynchronous Earth Orbit (GEO)

11 Molniya Orbit (HEO) Russia Visible 83% of the time

12 Non-Chemical vs. Chemical Fuel + Oxidizer Ions + Electric/Magnetic Fields

13 Atmospheric Operation Ion Engine Chemical Engine

14 Rocket ACTION RE-ACTION

15 Rocket Equation

16 Mass vs. Specific Impulse (I sp ) Chemical Propellant: I sp = 200 - 300s %Mass = 25.0% Low Thrust: I sp = 3000s %Mass = 89.5%

17 Ion Engine

18 Constant Thrust of 500-700mN About the weight of 8 quarters or 0.1lbs Consumes 2-8KW of electrical power from solar arrays

19 High Thrust (Chemical) Low Thrust (Ion) Orbit Maneuvers: High vs. Low Thrust

20 Example: LEO to GEO

21 Add the Moon!?

22 The 3 Body Problem

23 Make Simplifying Assumptions

24 24 Circular Restricted 3-Body Problem (CR3BP) Define: WARNING!!! Non-Inertial Reference Frame (Rotating)

25 25 CR3BP Equations of Motion

26 26 CR3BP: 5 Equilibrium (Lagrange) Points

27 27 Characterization of Lagrange Points m m Pendulum (Stable) Inverted Pendulum (Unstable)

28 28 Unstable Lagrange Point L2L2 Applications: Communications Navigation (GPS) Observation

29 29 Lyapunov, Halo, and Lissajous Orbits Image Credit: NASA Moon L1L1 L1L1 Earth Halo Lyapunov Lissajous

30 30 Merging Low-Thrust & Halo Orbits in the Earth-Moon System L4L4 L5L5 L3L3 L1L1 L2L2 moon

31 31 Merging Low-Thrust & Halo Orbits in the Earth-Moon System L3L3 Different View L5L5 L4L4 L2L2 L1L1 moon

32 32 One More View 1000kg Spacecraft 69kg of fuel used for 60 day flight GEO-like orbit to Halo orbit

33 33 NASA Space Station Resupply Mission(s)

34 34 Thank You! Questions?

35 35 Applications: Sun-Earth System Wilkinson Microwave Anisotropy Probe (WMAP) 1.Solar & Heliospheric Observatory (SOHO) @ Sun-Earth L 1 2.WMAP, James Webb Telescope, Plank @ Sun-Earth L 2 3.Planet-X @ Sun-Earth L 3 4.Trojan Asteroids @ Sun-Earth L 4 & L 5

36 Centrifugal Force

37 “Weightlessness” (Non-Inertial Reference Frame) y x FgFg v FcFc F = ma F = F g + F c = 0

38 Orbits: Inertial Reference Frame y x FgFg v

Download ppt "Low-Thrust Transfers from GEO to Earth-Moon Lagrange Point Orbits Andrew Abraham Moravian College, 2013."

Similar presentations

Orbital Mechanics Mike Rodning 27 April 2005. Introduction Survey of interesting celestial mechanical phenomena and techniques Types of Earth Orbits Coriolis.

Orbital Mechanics Mike Rodning 27 April Introduction Survey of interesting celestial mechanical phenomena and techniques Types of Earth Orbits Coriolis.
15th AAS/AIAA Space Flight Mechanics Meeting, Copper Mountain, Colorado Low Energy Interplanetary Transfers Using the Halo Orbit Hopping Method with STK/Astrogator.

15th AAS/AIAA Space Flight Mechanics Meeting, Copper Mountain, Colorado Low Energy Interplanetary Transfers Using the Halo Orbit Hopping Method with STK/Astrogator.
Lagrange Points Joseph Louis Lagrange was an 18th century mathematician who tackled the famous three-body problem in the late 1700s. The problem cannot.

Lagrange Points Joseph Louis Lagrange was an 18th century mathematician who tackled the famous "three-body problem" in the late 1700s. The problem cannot.
More Satellite Orbits Introduction to Space Systems and Spacecraft Design Space Systems Design.

More Satellite Orbits Introduction to Space Systems and Spacecraft Design Space Systems Design.
Solar Imaging Radio Array (SIRA) Trajectory and Formation Analysis Flight Dynamics Analysis Branch Code 595 (572) Dave Folta 6-6082 Bo Naasz 6-3819 Frank.

Solar Imaging Radio Array (SIRA) Trajectory and Formation Analysis Flight Dynamics Analysis Branch Code 595 (572) Dave Folta Bo Naasz Frank.
Jordi Isern Institut de Ciències de l’Espai (CSIC-IEEC) MSc in Economics of Science & Innovation Innovation & Challenges: Nanotechnology & Space (2) Orbits.

Jordi Isern Institut de Ciències de l’Espai (CSIC-IEEC) MSc in Economics of Science & Innovation Innovation & Challenges: Nanotechnology & Space (2) Orbits.
Satellites and Orbits Once a vehicle has climbed above the atmosphere (approx 100 miles altitude for Earth) and achieved a velocity of 17,500 miles per.

Satellites and Orbits Once a vehicle has climbed above the atmosphere (approx 100 miles altitude for Earth) and achieved a velocity of 17,500 miles per.
Low-thrust trajectory design ASEN5050 Astrodynamics Jon Herman.

Low-thrust trajectory design ASEN5050 Astrodynamics Jon Herman.
Rocket Engines Liquid Propellant –Mono propellant Catalysts –Bi-propellant Solid Propellant –Grain Patterns Hybrid Nuclear Electric Performance Energy.

Rocket Engines Liquid Propellant –Mono propellant Catalysts –Bi-propellant Solid Propellant –Grain Patterns Hybrid Nuclear Electric Performance Energy.
Part 5 Rockets Chap. 21- Rocket Fundamentals

Part 5 Rockets Chap. 21- Rocket Fundamentals
6. Space research and exploration of space increases our understanding of the Earth‘s own environment, the Solar System and the Universe. 4. Rapid advances.

6. Space research and exploration of space increases our understanding of the Earth‘s own environment, the Solar System and the Universe. 4. Rapid advances.
The Interplanetary Transport Network: Space Transportation Architecture for the 21st Century 5 May 2004 Shane Ross Everhart Lecture Series Control & Dynamical.

The Interplanetary Transport Network: Space Transportation Architecture for the 21st Century 5 May 2004 Shane Ross Everhart Lecture Series Control & Dynamical.
Thruster failure recovery strategies for libration point missions Maksim Shirobokov Keldysh Institute of Applied Mathematics Moscow Institute of Physics.

Thruster failure recovery strategies for libration point missions Maksim Shirobokov Keldysh Institute of Applied Mathematics Moscow Institute of Physics.
Asteroid Tour Trajectory D. Hyland Nov 21, 2012. Voyage Concepts We sketch potential trajectories for our deep space vessel: –Initial voyage from LEO.

Asteroid Tour Trajectory D. Hyland Nov 21, Voyage Concepts We sketch potential trajectories for our deep space vessel: –Initial voyage from LEO.
Sect. 3.12: The Three Body Problem So far: We’ve done the 2 Body Problem. –Central forces only. –Eqtns of motion are integrable. Can write as integrals.

Sect. 3.12: The Three Body Problem So far: We’ve done the 2 Body Problem. –Central forces only. –Eqtns of motion are integrable. Can write as integrals.
AAE450 Spring 2009 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12, 2009 1.

AAE450 Spring 2009 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12,
Spacecraft Propulsion Dr Andrew Ketsdever Lesson 13 MAE 5595.

Spacecraft Propulsion Dr Andrew Ketsdever Lesson 13 MAE 5595.
GN/MAE155A1 Orbital Mechanics Overview MAE 155A Dr. George Nacouzi.

GN/MAE155A1 Orbital Mechanics Overview MAE 155A Dr. George Nacouzi.
Orbital Mechanics Overview

Orbital Mechanics Overview
Circular Motion and Gravitation. Centripetal Acceleration Recall linear acceleration vivi vfvf 1. Speeding up a vivi vfvf 2. Slowing down a 3. Going around.

Circular Motion and Gravitation. Centripetal Acceleration Recall linear acceleration vivi vfvf 1. Speeding up a vivi vfvf 2. Slowing down a 3. Going around.

Similar presentations

Ads by Google