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Earth, Moon & Spacecraft - Stars A, B & Planet 17 November 2006 Wes Kelly

Earth, Moon & Spacecraft - Stars A, B & Planet 17 November 2006 Wes Kelly Triton Systems, LLC www.stellar-j.com Desk1Triton@aol.com (281) 286-3680 17000 El Camino Real – Suite 210A Houston, TX 77058 PART I: INTRODUCTION. Moon with Respect to Earth and Sun

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Earth, Moon & Spacecraft - Stars A, B & Planet 17 November 2006 Wes Kelly

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  1. Earth, Moon & Spacecraft - Stars A, B & Planet 17 November 2006 Wes Kelly Triton Systems, LLCwww.stellar-j.com Desk1Triton@aol.com (281) 286-3680 17000 El Camino Real – Suite 210A Houston, TX 77058 PART I: INTRODUCTION Earth-Moon-S/C: Star A, B, Planet

  2. Moon with Respect to Earth and Sun Ecliptic, Equatorial and Lunar Orbit Planes Earth-Moon-S/C: Star A, B, Planet

  3. Earth-Moon-S/C: Star A, B, Planet

  4. What was missing from the previous illustrations of the moon? A representation of the binary nature of the Earth Moon System: Revolution about the System Barycenter. Earth-Moon-S/C: Star A, B, Planet

  5. Crew Exploration Vehicle (CEV) operations to the Moon & elsewhere near-Earth could include flight to the vicinity of Equilibrium Points related to 1.) the Earth-Moon Binary & 2.) the Earth/Moon-Sun Systems. Also called Lagrangian Points, They can be divided into two sets: - 3 collinear points between the 2 finite bodies L1, L2 & L3 - 2 remaining equilateral points L4 & L5 supplying the remaining vertices defining equilateral triangles. The line between the 2 finite bodies forms their common base. As features of celestial mechanics Equilibrium or Libration Points Occupy 5 positions around 2 finite gravitating bodies Revolving about their Common Barycenter. Earth-Moon-S/C: Star A, B, Planet

  6. Applications for Co-Linear Points L1: Between the 2 finite masses, nearer the smaller of the two ( M2 if M1> M2). Sun-Earth L1: Ideal for making observations of the Sun. Objects here never shadowed by the Earth or Moon. The Solar and Heliospheric Observatory (SOHO) is stationed in a halo orbit around L1. Earth-Moon L1: Allows easy access to lunar and earth orbits with minimal delta-v. Potential for a half-way manned space station to transport cargo and personnel to the Moon and back. L2: Lies on the line defined by the two large masses, beyond the smaller of the two. Moving out from Earth away from the Sun, the orbital period of an object would normally increase, but Earth's gravity decreases orbital period, and locked at the L2 point that orbital period becomes equal to the Earth's. Sun-Earth L2: A good spot for space-based observatories needing thermal shielding ( e.g., Earth Shadow). The Wilkinson Microwave Anisotropy Probe is already in orbit around the Sun-Earth L2. The proposed James Webb Space Telescope will be placed at the Sun-Earth L2. Earth-Moon L2: A candidate location for a communications satellite covering the Moon's far side. Orbiting about the L2 point would allow view of both back side and earth simultaneously. Earth-Moon-S/C: Star A, B, Planet

  7. What’s still missing from the previous slide? Representation of the ELLIPTIC Earth-Moon System Eccentricity influences the stability and existence of Equilibrium Points, Escape & Capture Trajectories Earth-Moon-S/C: Star A, B, Planet

  8. Alpha Centauri A&B: Nearest Binary Star System (e = 0.52) Two Stars Orbit about Barycenter Terrestrial Planet traces about each star in Habitable Zone Larger, brighter (blue) star Traces smaller ellipse Inversely proportional to Mass ratio RA/RB = MB/MA Earth-Moon-S/C: Star A, B, Planet

  9. Every 78 years at Stellar Pericentron Passage, Terrestrial Planet At 1.246 AU Semi-Major Axis (400 K T-local) Increases Eccentricity Measured by DR/R0 Terrestrial Planet Orbiting Alpha Centauri A In Alpha Centauri Stellar Binary Planets Positioned Further from A experience faster cycles and Higher eccentricities until they become unstable. Over 8000 Earth Years Planet Perihelion Rotates 360 degrees As eccentricity cycles between near 0 and 0.07 Earth-Moon-S/C: Star A, B, Planet

  10. Astrometry Data Sun Position w.r.t. System Barycenter Scale: +/- 1 Milli-Arcsec Trace from 1960-2025 Large Circles Radius 4 Million km Tangential Velocity (for Doppler) ~65m/s Doppler Velocity Data Spectral Line Shifts of First Few Stars Determined to Possess Large Planets ~1995 51 Pegasi: +/-60 m/s 47 Ursae Majoris: +40 -60 m/s View from 10 Parsec Distance “North Pole of Ecliptic” LGM “Evidence for Jupiter & Saturn” 1 Parsec = 3600*180/p = 206,264.8 AUs 70 Virginis: +400 -220 m/s Earth-Moon-S/C: Star A, B, Planet

  11. Which is easier? Calculating trajectories to Mars or to the Moon? Lunar Sphere of Influence (SOI) Earth at Origin X-Rel: Earth Moon Line (Earth Radii) +11.2, -12.6 E-Radii By pocket calculator, Mars; the planetary SOIs involved more smoothly connect small, local “patched conic” regions. Lunar SOI is embedded within the Earth’s so closely that “border calculations” are significant efforts in themselves. For Mars, V-infinity is half the problem. CEV flights returning to the Moon imply more complex missions than the Apollo series. (e.g, Polar regions or the Lagrangian points of Earth-Moon or Earth-Sun Systems). Yet even Apollo flight plans require astrogation skills not used during the Shuttle era. Apollo mission reviews hold lessons for a new generation of flight specialists. Example: Determining launch angles for trans-lunar or trans-Earth burns. Earth-Moon-S/C: Star A, B, Planet

  12. While Earth-Moon system dynamics in the Apollo era seemed unique, Not so since 1995, the Era of Extra Solar Planets. New Star-Brown Dwarf or - Jovian Planet binaries orbit in paths about common centers of mass Like binary star systems, newly discovered planets/binaries have large eccentricities and Could influence smaller unseen (e.g., terrestrial) planets Illustrative cases provided based on integrations of the Restricted Elliptic 3-Body Problem (RE3BP). Earth-Moon-S/C: Star A, B, Planet

  13. Article in American Scientist ( Sept.-Oct. 2006, Vol. 94, No. 5) by Gregory P. Laughlin, Astronomy Dept. UC, Santa Cruz. The Orion Nebula, ~1500 light years from Earth, a well-known nursery for stars and the planets that form around many of them. Optical images increasing in magnitude show location of newborn stars within the Orion constellation & one of many proto-stellar disks, at 17x Solar System scale. Images from - European Southern Observatory - Max Planck Institute - NASA & Rice University. Earth-Moon-S/C: Star A, B, Planet

  14. Earth-Moon-S/C: Star A, B, Planet

  15. Earth-Moon-S/C: Star A, B, Planet

  16. Earth-Moon-S/C: Star A, B, Planet

  17. Development of late 1990s: Extra-Solar Planets, Brown Dwarfs Frequently Detected with High Eccentricity Where Triangular Libration Points Vanish “Meta-Stable” L1 & L2 Become Less Stable Derivation of Lagrangian Equations Shows How Contours of Zero Velocity for m=1/82 Valid for: Earth-Moon, If Eccentricity Near or Equal 0. G2 Star with Brown Dwarf or “ “ Red Dwarf (M9) with Jupiter “ “ Earth-Moon-S/C: Star A, B, Planet

  18. Stellar Main Sequence: Hydrogen Fusion into Helium + Energy Release Source of Luminosity down to 0.08 Mass of Sun ( M0) Jupiter Mass ~0.001 M0 or 330 Earths; Brown Dwarf Deuterium Fusion into Helium M > 0.013M0 or M >13MJ Main Sequence Mass-Luminosity Relation L*/L0 =(M*/M0)3.5 HERTZSPRUNG – RUSSELL DIAGRAM Solar Effective Surface Temperature ~5800 o K (G2) Surface Radius ~700,000 km. L= 4s p R2 Teff4 For T= f(R) 1 AU “Flux Temperature” 400o K ( Teff @ R=1AU ) Simple Defining Line of Habitability Zone Earth-Moon-S/C: Star A, B, Planet

  19. Earth-Moon-S/C: Star A, B, Planet

  20. Hierarchy of Modeling Methods for Lunar Applications --------------------------------------------------------------------------------------------------------------------------------------- 2-Body & Patched Conic model provides: Estimates of times, geometries, delta velocities Works better with interplanetary trajectories owing to sphere of influence sizes relative to free trajectories. --------------------------------------------------------------------------------------------------------------------------------------- Restricted Circular 3-Body model provides Uniformly rotating coordinate system with two fixed bodies A & B Stability analysis based on integral solutions to equations of motions – zero velocity coefficient contours Solution sets such as Lagrangian points, special orbits Numerical integration involved in some solutions vs. 2-Body – Patched Conic Assumptions do not address angular and translational accelerations of primary bodies in elliptic orbits ------------------------------------------------------------------------------------------------------------------------------------ Restricted Elliptic 3-Body model provides Two principal bodies in inversely proportional to mass ellipses about barycenter Refined solution analysis of Lagrangian points (esp L1 & L2), system sensitivity to eccentricity Solutions require numerical 3rd body integration amid Kepler equation propagation ( position-time) of 2 primaries. ---------------------------------------------------------------------------------------------------------------------------------------- Beyond? --------------------------------------------------------------------------------------------------------------------------------------- 4-Body (e.g., add Sun) or Solar System N-Body Ephemeris provides: Sun-Moon-Earth interactions such as weak interactions and additional Lagrangian points --------------------------------------------------------------------------------------------------------------------------------------- -Collocation or Non-Linear Programming Methods: Address constraints difficult for Calculus of Variations formulation. Caveat Emptor: Formulation is principally geometric vs. physical. Earth-Moon-S/C: Star A, B, Planet

  21. Analysis Tool Origins & Directions • 1980s:– Bistar FORTRAN Code • Derived from terrestrial orbital finite burn, re-entry and launch simulations • 1985-1997: • Bistar used to examine terrestrial planet stability in “habitable” regions of • Well known binary systems (Alpha Centauri, Procyon, Sirius…); • Gravity model shifted from terrestrial units and second times to solar units and “day” increments; • In inertial field, 2 bodies propagate on Keplerian orbits about barycenter; • Gravity forces attract third. • 1995-1998: • Later studies include newly found binaries (70 Virginis, 47 Ursae Majoris) involving • Sub-stellar objects (Brown Dwarf or Jovian Planets) where Terrestrial Planets • In habitable zones could be satellites or Perturbed by close-by massive companions • ( Now over 200 such extra-solar planets). • 2004 to Present: • Bistar Restricted Elliptic 3-Body Code adapted to lunar or planetary studies • Gravity model converted form solar units to planetary units & “second” time steps. • Future Direction: • Re-integrate finite burns and entry atmospheric drag models. • Typical issue: In elliptic binary system, what are suitable navigation coordinates? • Additional perturbing bodies • (e.g., Ballistic Captures with Solar assistance such as Japanese Hiten mission) Earth-Moon-S/C: Star A, B, Planet

  22. Earth-Moon-S/C: Star A, B, Planet

  23. Ifthe Moon were a target without mass, Then 2-body aim strategy reduces to time of arrival at lunar orbit. For elliptic and parabolic transfers of ~116 and 48 hours And 27.32-day Lunar period or 13.176o/day angular rate, LEO departure angles advance from initial Earth-Moon line by 63.6o and 26.35o. But… A Hohmann transfer delivers on node line; All others ( higher energy ellipses and escape paths) have off-sets. The Moon’s angular rate as well as distance changes – and Its gravity distorts Earth-based conic paths. Shoot for the Moon with Naïve Assumptions Parabolic / Escape Trajectory along Initial Line of Nodes. Moon Moves 26 degrees in 2 Days Conic Bends in Opposite Direction Earth-Moon-S/C: Star A, B, Planet

  24. Two Body Offset Angle Calculation: Solve for True Anomaly by Combining Two Conic Equations rp = p / ( 1 + e cos f) = p /( 1+ e ) = R0 + 400 km ( where p is undefined by parabola, substitute h2/m) r ( lunar orbit) = p / ( 1 + e cos f) ~ 59R0 -------------------------------------------------------------------------------------------------------------------- cos (f ) = [( 1 + e)( rp / r) – 1] / e Offset angle : y = 180 – f ------------------------------------------------- parabola : ~ 15.4 degrees hyperbolas : >15.4 apogee of an ellipse : 0 larger ellipses : 15.4 > y > 0 -------------------------------------------------------------------------------------------------------------------- Two-Body Departure Angle for Parabolic Trajectory to Moon: Transit ( 2-days): 26.66 o Offset: 15.42 o ----------------------------------------- Departure Angle: 41.08 o Earth-Moon-S/C: Star A, B, Planet

  25. Restricted Elliptic 3-Body Simulation Results Close Lunar Flyby Results form 45o Departure Angle Earth-Moon-S/C: Star A, B, Planet

  26. Earth-Moon Parameters Departure Angle 45 Degrees, Escape Velocity Inertial Velocity (kfps) & Distance (E-radii) to Moon ^ Inset vs. X-rel to Moon Center^ Time (minutes – reads to left) Radial Distance ( n. mi.) Relative Velocity (fps) Y: E-M Line Offset Distance (n. mi.) Earth-Moon-S/C: Star A, B, Planet

  27. Lunar Flyby: Continuously Calculating Orbital Elements Watch Eccentricity Shift from Parabolic to Elliptic Value for Return Leg <<Transformation 2 Days Out But what does this mean for return to Earth? Earth-Moon-S/C: Star A, B, Planet

  28. Nice shot, but… Departure at V-Escape with 45o Departure Angle Return Path Perigee Insufficiently Low for Emergency Earth Return Considerations for Lunar Trajectories: -Altitude of Passage, - Lunar Orbit coverage - Time of Flight & - Return Trajectory Parameters Governed by - V departure ( Elliptic, Hyperbolic, Parabolic) - Departure Angle & - Inclination w.r.t. Earth-Moon Orbital Plane Earth-Moon-S/C: Star A, B, Planet

  29. Lower Altitude Return Trajectory Obtained: Control Adjustments are Velocity and Departure Angle Lunar Fly-Around: Earth Departure Angle 47 o Vp = 35,400 fps (vs. 35,580) Earth-Moon-S/C: Star A, B, Planet

  30. Now what about getting back from the Moon normally? Apollo 15 Departure Delta V = 3000 fps. Hyperbolic Exit Velocity Blue: Earth Track about Earth-Moon Barycenter Re-Entry between Red Plots at Far Left Retrograde Lunar Orbit Departure at -31 Degrees Earth-Moon-S/C: Star A, B, Planet

  31. Revised DV for Lunar Perigee Exit Anticipate Return Trajectory Partials for Orbit Phase Operationally, residual entry errors also corrected With mid-course maneuvers Circle: Earth Surface Earth-Moon-S/C: Star A, B, Planet

  32. Earth Injection with 2821.5 fps DVelocity from Low Lunar Orbit Altitude, True Anomaly and Flight Path Angle w.r.t. Earth Earth-Moon-S/C: Star A, B, Planet

  33. “Houston, we have a problem…” Difficulties not anticipated with 2-Body, “Back of the Envelope” Calculations Earth Departure on Escape Trajectory Bent Back and Crashes Lunar Elliptical Trajectories at Departure Angles of 60 and 70o Fail to escape and crash Earth-Moon-S/C: Star A, B, Planet

  34. Barycentric Inertial Coordinates: Moon and Escape Trajectory V= 7549 fps or DV = 2211 fps Initiated at 60 o Departure Angle (Prograde Orbit) Earth-Moon-S/C: Star A, B, Planet

  35. Stability of Orbits and Lagrangian Points Stability Earth-Moon-S/C: Star A, B, Planet

  36. Lurking Instability… Earth-Moon-S/C: Star A, B, Planet

  37. Crew Exploration Vehicle (CEV) operations to the Moon & elsewhere near-Earth could include flight to the vicinity of Equilibrium Points related to 1.) the Earth-Moon Binary & 2.) the Earth/Moon-Sun Systems. Also called Lagrangian Points, They can be divided into two sets: - 3 collinear points between the 2 finite bodies L1, L2 & L3 - 2 remaining equilateral points L4 & L5 supplying the remaining vertices defining equilateral triangles. The line between the 2 finite bodies forms their common base. As features of celestial mechanics Equilibrium or Libration Points Occupy 5 positions around 2 finite gravitating bodies Revolving about their Common Barycenter. Earth-Moon-S/C: Star A, B, Planet

  38. Wikipedia Definition: The Lagrangian points, (also L-point, or libration point) are the 5 positions in space where a small object can be stationary with respect to two larger objects, such as a satellite with respect to the Earth and Moon). They are analagous to geosynchronous orbits in that they allow an object to be in a "fixed" position in space rather than an orbit in which its relative position changes continuously. More precisely, Langrangian points are stationary solutions of the Circular Restricted 3-Body Problem. Given 2 massive bodies in circular orbits around their common center of mass, there exist 5 positions in space where a 3rd body, of comparatively negligible mass, could be placed which would then maintain its position relative to the 2 massive bodies. As seen in a frame of reference rotating with the same period as the 2 co-orbiting bodies, the gravitational fields of 2 massive bodies combined with the centrifugal force are in balance at the Lagrangian points, allowing the 3rd body to be stationary with respect to the first 2 bodies. Earth-Moon-S/C: Star A, B, Planet

  39. History and Concepts (Abridged and Adapted from Wikipedia) In 1772, French mathematician Joseph Louis Lagrange while working on the broad 3-body problem obtained several interesting results. Lagrange sought to calculate the gravitational interaction between arbitrary numbers of bodies in a system. Newtonian mechanics had concluded that such systems result in bodies orbiting chaotically until there is a collision, or a body is thrown out of the system so that equilibrium can be achieved. Including more than 2 bodies in the system complicated mathematical calculations considerably. Seeking to make calculations simpler, Lagrange noted: The trajectory of an object is determined by finding a path that minimizes the action over time. This is found by subtracting the potential energy V from the kinetic energy T… L = T - V ( …and seeking zeros for systems of partial and temporal derivatives related to position and velocity – WDK). Lagrange thus re-formulated classical Newtonian Mechanics into Lagrangian Mechanics. Earth-Moon-S/C: Star A, B, Planet

  40. Earth-Moon-S/C: Star A, B, Planet

  41. In the more general case of elliptical binaries, there are no longer stationary points in the same sense: Points become more like Lagrangian “areas” where the 3rd bodies make odd-shaped orbits about the invisible Lagrangian points; these orbits are commonly referred to as halo orbits. The Lagrangian points constructed at each point in time as in the circular case form stationary elliptical orbits which are similar to the orbits of the massive bodies. This is due to the fact that Newton's second law, p = mv (p the momentum, m the mass, and v the velocity), remains invariant if force and position are scaled by the same factor. … Controversy: “A body at a Lagrangian point orbits with the same period as the 2 massive bodies in the circular case, implying that it has the same ratio of gravitational force to radial distance as they do. This fact is independent of the circularity of the orbits, and it implies that the elliptical orbits traced by the Lagrangian points are solutions of the equation of motion of the 3rd body.” Our analyses indicate that the last statement does not apply to the co-linear points. See our discussion.] Earth-Moon-S/C: Star A, B, Planet

  42. To the Rescue… Forest Ray Moulton 1872 - 1952 Member, then Director, Dept. of Astronomy, Univ. of Chicago, 1898-1927. Research Associate at the Carnegie Institution, 1908-1923. Director of Utilities Power and Light Corporation, 1920-1938. AAAS offices held: Permanent Secretary, 1937 - 1946 Administrative Secretary, 1946 - 1948 Author of Celestial Mechanics, 2nd Edition (1914) Chapter 8, The Problem of 3 Bodies, Articles 151-169 A Dover paperback. Earth-Moon-S/C: Star A, B, Planet

  43. Stability The first three Lagrangian points are technically stable only in the plane perpendicular to the line between the two bodies. This can be seen most easily by considering the L1 point. A test mass displaced perpendicularly from the central line would feel a force pulling it back towards the equilibrium point. This is because the lateral components of the two masses' gravity would add to produce this force, whereas the components along the axis between them would balance out. However, if an object located at the L1 point drifted closer to one of the masses, the gravitational attraction it felt from that mass would be greater, and it would be pulled closer. (The pattern is very similar to that of tidal forces.) Although the L1, L2, and L3 points are nominally unstable, it turns out that it is possible to find stable periodic orbits around these points, at least in the restricted 3-body problem. These perfectly periodic orbits, referred to as "halo" orbits, do not exist in a full n-body dynamical system such as the solar system. However, quasi-periodic (i.e. bounded but not precisely repeating) Lissajous orbits do exist in the n-body system. These quasi-periodic orbits are what all libration point missions to date have used. Although they are not perfectly stable, a relatively modest effort at station-keeping can allow a spacecraft to stay in a desired Lissajous orbit for an extended period of time. At least in the case of Sun-Earth L1 missions, it is actually preferable to place the spacecraft in a large amplitude (100,000 - 200,000 km) Lissajous orbit instead of sitting at the libration point; this keeps the spacecraft off of the direct Sun-Earth line and thereby reduces the impacts of solar interference on the Earth-spacecraft communications links. Another interesting property of collinear libration points and their associated Lissajous orbits is that they serve as "gateways" to control the chaotic trajectories of the Interplanetary Superhighway. By contrast, L4 and L5 are stable equilibria (cf. attractor), provided the ratio of the masses M1/M2 is > 24.96. This is the case for the Sun/Earth and Earth/Moon systems, though by a smaller margin in the latter. When a body at these points is perturbed, it moves away from the point, but the Coriolis force then acts, and bends the object's path into a stable, kidney bean-shaped orbit around the point (as seen in the rotating frame of reference). Earth-Moon-S/C: Star A, B, Planet

  44. Earth-Moon-S/C: Star A, B, Planet

  45. Mean, Perigee & Apogee Equilibrium Points from Eq. 12a Y Axis Accelerations (ft/sec**2) Acceleration Level at X distance for Moon at Perigee Apogee Mean Earth-Moon-S/C: Star A, B, Planet

  46. Earth-Moon-S/C: Star A, B, Planet

  47. Earth-Moon-S/C: Star A, B, Planet

  48. Earth-Moon-S/C: Star A, B, Planet

  49. Earth-Moon-S/C: Star A, B, Planet

  50. Instability at Lagrangian Points: Is it bad - or a good thing? It depends on what you are selling. Lunar Way Stations will requires orbit adjusts every two weeks. But if you drop a hammer in the right direction, you could send it off to Mars. L2 Initial Condition Xdot0 Ydot0 Variations (fps): -67.5 0 -65.0 0 -65.0 10 -67.0 -10 Earth-Moon-S/C: Star A, B, Planet

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