1. Institute of Applied Astronomy,
Start the solution of the task of human exploration of the Solar System and of Defending the Earth from Potentially Hazardous Objects
David W. Dunham
Moscow Institute of Electronics and Mathematics/Higher School of Economics
26 December 2012 at
Institute of Applied Astronomy,
St. Petersburg, Russia

2. Overview KinetX and some administrative information
Attraction of the Sky – My early history, Occultations & Moonwatch
Libration Points – ISEE-3/ICE Mission; SOHO
Asteroids – NEAR Mission to Eros; Clementine
Work of the megagrant – extending human exploration and defense against hazardous objects
The US Team
A Historic Opportunity

3. KinetX, Inc.
 Founded 1992 in California  Headquarters in Tempe, Arizona  Iridium navigation and operations  In 2003, Space Navigation and Flight Dynamics (SNAFD) Section established in Simi Valley, Calif. by some key members of the JPL Navigation Section who left JPL  SNAFD navigates MESSENGER (Mercury orbiter) and New Horizons (mission to Pluto) – the ends of the Solar System!  Other KinetX employees live in Maryland and Virgina  I joined SNAFD in 2009 to provide trajectory design expertise & work part-time on MESSENGER on-site at the Johns Hopkins University’s Applied Physics Laboratory in Laurel, Maryland

4. US International Traffic in Arms Regulations (ITAR)
Technical Assistance Agreement (TAA) submitted to U. S. State Department on 28 October 2011
It was approved “with provisos” on 12 January 2012

5. The rest of this presentation is based on publications in the open literature, including Bob Farquhar’s June 2011 book, or references given in it; in my American Astronautical Society Brouwer Award Lecture, “Trying Something Different”, in Advances in the Astronautical Sciences, Paper AAS , Vol. 119, pp , Univelt, San Diego, 2005; and in Farquhar, R., Dunham, D., and Veverka, J., “An Affordable Program of Human Missions beyond Low Earth Orbit”, Paper IAC-08-A presented at the 59th International Astronautical Congress, Glasgow, United Kingdom, September 29-October 3, 2008.

6. Attraction of the Sky
My father worked on design for a modern fish harbor in Karachi, Pakistan
Desert Skies – I learned the Constellations
Oct. 29,  Capricorni/Moon Appulse
Moonwatch Project
Lunar Grazing Occultations
International Occultation Timing Association

7. Disappearance of 6.1-mag. 1 Capricorni from La Cañada, California, October 29, 1957 at 9:25 pm PST

8. Appulse of 3.1-mag. 2 Capricorni from La Cañada, California, October 29, 1957, min. dist. 5 at 9:47 pm PST
I was fascinated – the star looked like a spacecraft flying over the Moon

9. Southern Limit of the 2 Capricorni Occultation, 1957 October 29
My Location

10. Lunar Grazing Occultations
First calculations in March 1962 for graze of Aldebaran south of San Jose, Calif.
First successful expedition, Len Kalish from Los Angeles to Castaic Junction, 1962 Sept.
First computer program written to calculate grazes using FORTRAN, late 1962
My first success, 1963 March 31 near Roseville, Calif., with Bruce Bowman, at this meeting
International Occultation Timing Association founded in 1975
I observed a graze of 2 Cap with 12 others near Ashland, VA on 1977 June 5.

11. Video of 1990 April Aldebaran Grazing Occultation from Poland

12. Lunar Profile from Graze of delta Cancri – 1981 May 9-10
Circled dots are Watts’ predicted limb corrections

13. Lunar Graze of Mars recorded in Florida
A few years ago

14. Sputnik 1, also October 1957

15. SAO’s Moonwatch Project
In 1958, my introduction to artificial satellite orbits working with
the Sacramento (California) Moonwatch Team

16. Plotting Satellite Orbits, 1957

17. 26 years after 1957, I flew a spacecraft over the Moon!

18. International Sun-Earth Explorer 3/ International Cometary Explorer
First Libration-Point Mission
Finding a Way to Giacobini-Zinner –
Double Lunar Swingby Orbits
Printer Plots of the trajectories
An Unused Trajectory to L2
September 11, 1985 – the first comet flyby
Earth return in 2014 – more than halfway

19. ISEE-3 Spacecraft

21. Double Lunar Swingby Orbit Lunar Orbit Plane Inertial View

22. Double Lunar Swingby Orbit Lunar Orbit Plane, Fixed Earth-Moon Line

23. Double Lunar Swingby Orbit Lunar Orbit Plane, Fixed Sun-Earth Line

24. Visualizing Trajectories in 1982
To Sun
This and many of the following plots use the rotating geocentric solar ecliptic reference frame, a plot in the ecliptic plane with a fixed Sun – Earth horizontal axis

31. Near Earth Asteroid Rendezvous Spacecraft

32. NEAR’s Planned Trajectory

33. U-turn to Eros after RND-1 Abort

34. Descending Orbits about Eros JPL Nav, & APL Ops and Science Teams

35. Eros Images - Courtesy of Successful DV’s
Northern Hemisphere (from 200 km)
Eastern & Western Hemispheres (from 355 km)

36. Range 3 km, 2001 Jan. 28 Close Flyby

41. Overview
“Megagrant” received from the Russian Ministry of Education and Science to study orbital options for human exploration and planetary protection during ; I am required to be at MIEM at least 4 months of each year
Laboratory at MIEM, completed this month
Stepping Stone approach to exploration with reusable vehicles

42. Interesting Geology of the Moon’s Far Side
Ancient huge impact basin: South Pole-Aitken Basin
Diverse terrain accessible in a short, flat area near the north side of Tsiolkovsky crater (above), considered for the Apollo 17 Mission

43. Transfers to the Earth-Moon L2 Point Trajectories shown in rotating system with fixed horizontal Earth-Moon line, lunar orbit plane projection

44. Mission Profile for a Lunar Shuttle System with (Earth-Moon L2) Halo Orbit Staging Adding a mirror image of the bottom of the previous slide, proposed by Robert Farquhar in 1971
With certain geometries, very low V’s might be possible near L2 for a trajectory that might be used for a quick mission that might spend about a week above the lunar far side.

45. 17-day Trajectory to Earth-Moon L2 Region Rotating lunar orbit-plane view with fixed horizontal Earth-Moon line
Total post-launch
V 386 m/s 
Return
July 10, 2021
S1 June 27
h 49 km, V 191 m/s
S2 July 6
h 50 km, V 171 m/s 
Earth
Launch
June 23, 2021
C km2/s2
Moon L2  
Orbit normal
V 24 m/s
July 4 

46. 17-day Trajectory to Earth-Moon L2 Region Rotating ecliptic-plane view with fixed horizontal Sun-Earth line
Orbit
Normal V
July 4
24 m/s  
Total post-launch
V 386 m/s 
Lunar
Orbit
S1 Lunar Swingby
June 27, 2021
h = 49 km
 V 191 m/s
S2 Lunar Swingby
July 6, 2021
h = 50 km, V = 171 m/s  
Launch
June 23, 2021
C km2/s2
To Sun 
 outbound, 101-min. eclipse
Earth 
Return July 10, 2021
The June 23rd launch date is not optimum for this mission. It was selected for longer missions that will be shown later.

47. 17-day Trajectory to Earth-Moon L2 Region View from the Earth towards the Moon The spacecraft tries to enter an expanding Lissajous pattern starting at the S1 lunar swingby, so in order to counter-act it, to achieve S2, an orbit normal V is needed
to Earth    
Moon
S1 June 27, 2021
h 49 km, V 191 m/s
S2 July 6, 2021
h 50 km, V 171 m/s 
from Earth 
Orbit normal
V 24 m/s
July 4

48. Trajectory to Earth-Moon L2 Halo Orbit Rotating lunar orbit-plane view with fixed horizontal Earth-Moon line 
V 54 m/s
July 14 
Launch
June 23, 2021
C km2/s2
Halo
Insertion V
96 m/s
July 17
Moon  L2
Lunar Swingby
June 27, 2021
h = 54 km
V 186 m/s
Earth

49. Trajectory to Earth-Moon L2 Halo Orbit View from the Earth towards the Moon
Insertion
V 96 m/s
July 17  
V 54 m/s 
July 14  
Halo Orbit 
From
Earth   
Moon
Lunar Swingby
June 27, 2021
h = 54 km
V 186 m/s  

50. Ideas for Extending Human Exploration beyond the Moon’s Orbit
A human mission could service a space observatory in a Sun-Earth L2 halo orbit, which could also serve as an uncrewed storage area between missions
“Phasing orbit rendezvous” during highly elliptical “inner loops” between lunar swingbys of double lunar swingby trajectories that are used to move the line of apsides to desired departure directions
Trajectories to near-Earth asteroids, and later Phobos or Deimos, require significantly less V at departure and arrival perigees from these high-energy orbits
Ideas developed under International Academy of Astronautics (IAA) exploration working group
International collaboration will be essential for the success of such a large effort

51. Trajectories to the Sun–Earth L1 Libration Point
Trajectories shown with respect to fixed Sun-Earth line

52. Fast Transfers: Low-Earth Orbit (LEO) to Sun–Earth L2 Point

53. Deep-Space Shuttle
Service Module with a Chemical Propulsion System and Crew Quarters that could Support 3 to 4 People for Flight Times of up to 50 Days.
Detachable Apollo-Style Re-Entry Capsule (Orion?)
One and a Half Stage Vehicle (I.e., Core Stage with Drop Tanks)
Total ∆V Capability
-- 5 to 6 km/sec
-- 2 to 3 km/sec with Earth Departure Stage

54. Scenario for Telescope Servicing near the Sun-Earth L2 Libration Point
(1) Deep-Space Shuttle (DSS) leaves low-Earth orbit (V 3230 m/sec). First set of drop tanks discarded. (Alternative: use expandable high-performance kick stage for injection into L2 transfer orbit.).
(2) DSS enters L2 orbit (V 900 m/sec).
(3) DSS services L2 telescope (stay time 5 days).
(4) DSS exits L2 orbit (V 900 m/sec). Second set of drop tanks discarded.
(5) Crew returns to Earth in re-entry capsule. DSS returns to low-Earth orbit using multiple aerobraking maneuvers.

55. Simplified Double Lunar Swingby*
*Could be used to transfer an L2 telescope to and from an elliptical Earth orbit.
Phasing orbit rendezvous during smaller orbits between S2 and S1

56. Alternative Locations for Servicing L2 Telescopes

57. Approximate Round-Trip DV Requirements for Transfers from LEO

58. Interplanetary Transfer Vehicle
Crew Module that could Support 5 to 6 People for Flight Times of up to
3 Years
-- Substantial Radiation Protection
-- Spacious Living Quarters
A Detachable Re-Entry Capsule
Propulsion Module
-- Reusable or Expendable?
-- Nuclear Thermal Propulsion? (specific impulse ~ 900 seconds)

59. Interplanetary Transfer Vehicle Mission Scenario
Sun-Earth L2
Halo Orbit
Phasing trajectories using lunar gravity-assist maneuvers.
Phasing trajectories using lunar gravity-assist maneuvers.
Crew Earth return via Apollo-style capsule
Perigee ∆V for Earth capture
Crew arrival via DSS “taxi
Perigee ∆V for Earth escape
Destinations
Near-Earth Asteroids
Phobos/Deimos
Mars

60. Five-Month Mission to Near-Earth Asteroid

61. ITV Trajectory to 1999 AO10 with Respect to Fixed Sun-Earth Line

62. ΔV Costs for ITV Missions to Near-Earth Asteroids and Martian Moons using L2 Staging

63. Bob Farquhar and I near Lenin’s tomb, 1989

64. Conclusions
Architecture for Human Spaceflight that will Generate Public Enthusiasm by doing Things that have Never Been Done Before.
Develop Deep-Space Shuttle
-- Trips to Geosynchronous Orbit
-- Circumlunar Flights
-- Constructing and Maintaining L2 Telescopes
Delvelop Interplanetary Transfer Vehicle
-- Trips to Near-Earth Asteroids & Planetary Defense
-- Mission to Phobos or Deimos
The megagrant gives us a truly historic opportunity, to lay the foundations for leaving “cradle Earth” and extending human presence beyond the Moon into the Solar System.
We can lead the way!