Celestial Mechanics of Asteroid Systems

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1 Celestial Mechanics of Asteroid Systems D.J. Scheeres Department of Aerospace Engineering Sciences The University of Colorado 1

2 Granular Mechanics and Asteroids Asteroid systems are best modeled as self-gravitating granular systems under self-attraction and cohesion 2

3 Motivated by Observations All images courtesy JAXA/ISAS Muses Sea TD1 Site

4 Motivated by Observations All images courtesy JAXA/ISAS Muses Sea TD1 Site

5 Discrete Granular Mechanics and Celestial Mechanics The theoretical mechanics of few-body systems can shed light on more complex aggregations and their evolution 4

6 Discrete Granular Mechanics and Celestial Mechanics The theoretical mechanics of few-body systems can shed light on more complex aggregations and their evolution Movies by S.A. Jacobson 4

7 Fundamental and Simple Question: What are the expected configurations for collections of self-gravitating grains? 5

8 Fundamental Concepts: The N-body problem: Mass: m i r i i = 1, 2,...N U = 0 = G 2 NX j=1 NX j=1 m j r j NX k=1,6=i m j m k r jk r jk = r k In the Newtonian N-Body Problem each particle has a total mass mi modeled as a point mass of infinite density r j r jk = r k r j 6

9 Fundamental Concepts: Angular Momentum: NX H = m j r j ṙ j j=1 = 1 2M NX j=1 NX k=1 m j m k r jk ṙ jk M = NX j=1 m j Mechanical angular momentum is conserved for a closed system, independent of internal physical processes. The most fundamental conservation principle in Celestial Mechanics. 7

10 Fundamental Concepts: Energy: E = T + U NX T = 1 2 j=1 m j ṙ j ṙ j = 1 4M NX j=1 NX k=1 m j m k ṙ jk ṙ jk Not necessarily conserved for a closed system Additional non-modeled physical effects internal to the system can lead to dissipation of energy (e.g., tidal forces, surface friction) Physically occurs whenever relative motion exists within a system motivates the study of relative equilibria 8

11 Leads to a more precise question... Q: What are the minimum energy configurations for the Newtonian N-body problem at a fixed Angular Momentum? A: There are none for N 3. A surprising and untenable result all mechanical systems should have a minimum energy state... 9

12 Sundman s Inequality To investigate this we start with Sundman s Inequality Apply Cauchy s Inequality to the Angular Momentum H 2 = 1 4M 2 NX j,k=1 m j m k r jk ṙ jk 2 apple 1 4M 2 0 j,k=1 1 m j m k rjk 2 A NX j,k=1 1 m j m k ṙjk 2 A =2IT Sundman s Inequality is: H 2 apple 2IT I = NX i=1 m i r 2 i = 1 2M NX j,k=1 m j m k r 2 jk Polar Moment of Inertia 10

13 Minimum Energy Function and Relative Equilibrium Leads to a lower bound on the energy of an N-body system by defining the minimum energy function Em (also known as the Amended Potential). H 2 apple 2IT T = E U E m (Q) = Em is only a function of the relative configuration Q of an N-body system Theorem: Stationary values of Em are relative equilibria of the N-body problem at a fixed value of angular momentum (Smale, Arnold) Equality occurs at relative equilibrium Can be used to find central configurations and determine energetic stability H2 2I(Q) + U(Q) apple E Q = {r ij : i, j =1, 2,...,N} 11

14 Example: Point Mass 2-Body Minimum Energy Configurations Point Mass 2-Body Problem: Minimum is a circular orbit E m = h2 1 2d 2 = h2 d d 2 2 E 2 E m = d = h 2 1 2h 2 = 3h2 d 4 2 d 3 = 1 h 6 > 0 Energy Angular Momentum Separation 12

15 Point Mass N-Body Minimum Energy Configurations, N 3 Point Mass 3-Body Problem: Relative equilibria occur at the Lagrange and Euler Solutions Euler solutions are always unstable minimum energy solutions Lagrange solutions are never minimum energy solutions Point Mass N-Body Problem: Central configurations are never minimum energy configurations, c.f. proof by R. Moeckel. For any Point Mass N 3 Problem, Em can always > - while maintaining a constant level of angular momentum For the Point Mass N 3 Problem there are no nonsingular minimum energy configurations... does our original question even make sense? 13

16 Non-Definite Minimum of the Energy Function for N 3 Consider the minimum energy function for N=3: E m = H 2 m 3 [d d d2 31 ] Gm 2 apple 1 d d d 31 Choose the distance and velocity between P1 and (P2, P3) to maintain a constant value of H. Choose a zero-relative velocity between (P2, P3) and let d23 > 0, forcing Em > - while maintaining H. P 3 P 2 P 1 Under energy dissipation, there is no lower limit on the systemlevel energy until the limits of Newtonian physics are reached. 14

17 Non-Definite Minimum of the Energy Function for N 3 Consider the minimum energy function for N=3: E m = H 2 m 3 [d d d2 31 ] Gm 2 apple 1 d d d 31 Choose the distance and velocity between P1 and (P2, P3) to maintain a constant value of H. Choose a zero-relative velocity between (P2, P3) and let d23 > 0, forcing Em > - while maintaining H. P 3 P 2 d 12 d 13 P 1 d 23! 0 Under energy dissipation, there is no lower limit on the systemlevel energy until the limits of Newtonian physics are reached. 14

18 The Role of Density The lack of minimum energy configurations in the Point Mass N- body problem arises due to the infinite density of Point Masses The resolution of this problem is simple and physically well motivated allow for finite density but has profound consequences:!1 < 1 d! 0 d>0 Bodies with a given mass must now have finite size, when in contact we assume they exert surface normal forces and frictional forces Moments of inertia, rotational angular momentum, rotational kinetic energy and mass distribution must now be tracked in I, H, T and U, even for spheres. For low enough angular momentum the minimum energy configurations of an N-body problem has them resting on each other and spinning at a constant rate 15

19 Finite Density (Full-Body) Considerations Energy, angular momentum and polar moment of inertia all generalize to the case of finite density, along with the Sundman Inequality (Scheeres, CMDA 2002): E = T + U + 1 NX j I j j 2 NX j=1 NX 1 H = m j m k r jk ṙ jk + I j j 2M j,k=1 j=1 0 1 NX 1 I = m j m k r 2 2M jk + 1 NX 2 I A j j,k=1 j=1 H 2 apple 2IT E m = H2 2I + U apple E 16

20 Modified Sundman Inequality A sharper version of the Sundman Inequality can be derived for finite body distributions (Scheeres, CMDA 2012): Define the total Inertia Dyadic of the Finite Density N-Body Problem: NX I = mi ri 2 U r i r i + A i I i A T i i=1 Define the angular momentum unit vector Ĥ I H = Ĥ I Ĥ The modified Sundman Inequality is sharper and defines an updated Minimum Energy Function H 2 apple 2I H T apple 2IT E m apple E m = H2 2I H + U apple E 17

21 Minimum Energy Configurations Theorem: For finite density distributions, all N-body problems have minimum energy configurations. Proof (Scheeres, CMDA 2012): Stationary values of E m are relative equilibria, and include (for finite densities) resting configurations. For a finite value of angular momentum H, the function E m is compact and bounded. By the Extreme Value Theorem, the minimum energy function has a Global Minimum. Resolves the problem associated with minimum energy configurations of the Newtonian (Point Mass) N-Body Problem. E m 18

22 ... back to the original question Question: What is the Minimum Energy configuration of a finite density N-Body System at a specified value of Angular Momentum? Answer: The Minimum Value of configurations, both resting and orbital. For Simple Spheres... E m (Q F )= E m across all stationary H2 2I(Q F ) + U(Q F ) apple E Q F = {r ij r ij (d i + d j )/2,i,j =1, 2,...,N} Relative Equilibrium Q 0 8 Admissible Q Stability 2 E = 2 Q > 0 19

23 Minimum Energy Configurations of the Spherical Full Body Problem For definiteness, consider the simplest change from point mass to finite spheres (then U is unchanged) For a collection of N spheres of diameter d i the only change in is to I H I H = 1 10 NX NX m i d 2 i + m i ri 2 i=1 i=1 But this dramatically changes the structure of the minimum energy configurations... take the 2-body problem for example with equal size spheres, normalized to unity radius E m E m = h2 1 2d 2 d versus E m = h 2 2(0.4+d 2 ) 1 d 20

24 2-Body Problem Point Mass Case Separation Finite Density Case Only one stationary orbit energy configuration Angular Momentum Energy Angular Momentum Energy Zero or Two stationary orbit energy configurations per AM Separation Separation E m = h2 1 2d 2 d E m = h 2 2(0.4+d 2 ) 1 d 21

25 Reconfiguration and Fission As a system s AM is increased, there are two possible types of transitions between minimum energy states: Reconfigurations, dynamically change the resting locations Fissions, resting configurations split and enter orbit about each other Reconfiguration: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Lagrange solution Multiple resting configurations can exist at one angular momentum. Resting and orbital stable configurations can exist at one angular momentum. 22

26 Reconfiguration and Fission Reconfiguration: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Lagrange solution Multiple resting configurations can exist at one angular momentum. Resting and orbital stable configurations can exist at one angular momentum. 22

27 Reconfiguration and Fission Reconfiguration: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Lagrange solution Multiple resting configurations can exist at one angular momentum. Resting and orbital stable configurations can exist at one angular momentum. 22

28 Reconfiguration and Fission Reconfiguration: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Lagrange solution Fission: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Euler solution Multiple resting configurations can exist at one angular momentum. Resting and orbital stable configurations can exist at one angular momentum. 22

29 Reconfiguration and Fission Reconfiguration: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Lagrange solution Fission: Occurs once the relative resting configuration becomes unstable. For the 3BP occurs at a rotation rate beyond the Euler solution Multiple resting configurations can exist at one angular momentum. Resting and orbital stable configurations can exist at one angular momentum. 22

30 2-Body Results: Internal Degrees of Freedom for Spherical Grains Contact case has 0 degrees of freedom Orbit case has 1 degree of freedom 3-Body Results Contact case has 1 degree of freedom Contact + Orbit case has 2 degrees of freedom Know all of the orbit configurations 4-Body Results Contact case has 2 degrees of freedom, multiple topologies Many more possible Orbit + Contact configurations 3-dimensional configurations Don t even know precisely how many orbit configurations exist... but they are all energetically unstable (Moeckel)! 23

31 All minimum energy states can be uniquely identified in the finite density 3 Body Problem Static & Variable Resting Configurations Mixed Configurations Orbiting Configurations Minimum Energy Configurations Lagrange Resting Aligned Mixed Lagrange Orbiting Euler Resting V Resting Transverse Mixed Euler Orbiting

32 Bifurcation Chart H

33 -1 E E -1.5 E E -2 E -2.5 E = Excess Energy Increasing AM Decreasing AM H 2

34 Finite Density 4 Body Problem Static Resting Equilibrium Configurations Mixed Equilibrium Configurations Variable Resting Equilibrium Configurations A E B C F G D

35 = 180 = Static Rest Configurations 0 and Static Rest Configurations 1, 2, 5 Static Rest Configurations 1, 3, 4

36 Configuration A B C D E H 2

37 -2 Detail Configuration A B C D Ea -2.5 Eb E -3 E2,3 Ec,d H 2

38 Generalizations to Non-Spherical Bodies 31

39 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003)

40 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Slow rotation

41 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Slow rotation

42 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Slow rotation

43 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Intermediate rotation

44 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Fast rotation

45 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Fast rotation

46 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) Fast rotation

47 Migration of Surface Material If an asteroid s rotation rate changes the minimum energy resting points of particles will change (Guibout & Scheeres, Celestial Mechanics 2003) For an ellipsoid, transition rotation rates are related to the Jacobi Sequence

48 From Miyamoto et al., Science, 2007

49 Minimum Energy Configurations ω 0 As spin rate increases or decreases, an aggregate can be placed into a non minimum energy state. (K 0,E 0 ) (K 1 = K 0, E 1 < E 0 ) ω 1 A perturbation can trigger a shape change, conserving AM, decreasing energy, and dissipating excess energy via friction and seismic waves.

50 Generalization to Non-Spherical Bodies The theory of minimum energy configurations can be extended to arbitrary finite density shapes, e.g. an equal density ellipsoid/ellipsoid system Minimum energy configuration for small Angular Momentum Minimum energy configuration for large Angular Momentum ω ω

51 ω ω ω (Icarus 189: )

52 Rubble pile partitions As spin rate increases, the transition limit for each mutual set should be computed and compared with each other.

53 Fission Conditions For fission of an arbitrary rubble pile split into two collections I and J the general condition becomes: For mass distributions only a weak form of Euler s Theorem of Homogenous functions applies which allows us to reduce this inequality to: where R IJ!! R IJ α > 1 M I + M J M I M J T IJ + U IJ 0 This is equivalent to the two components with the largest separation between their centers of mass will fission first at the lowest spin IJ R IJ 38

54 Asteroid Itokawa s peculiar mass distribution will fission when its rotation period < 6 hours spin period can change due to the YORP Effect, slowly changes total angular momentum... Body = 490 x 310 x 260 meters Head = 230 x 200 x 180 meters BODY HEAD ω

55 -1 E E -1.5 E E -2 E -2.5 E = Excess Energy Increasing AM Decreasing AM H 2

56 Reconfigurations and Fission Events When a Local Minimum reaches its reconfiguration or fission state it cannot directly enter a different minimum energy state Excess energy ensures a period of dynamics where dissipation may occur Movie by S.A. Jacobson 41

57 Fission Fission can be a smooth transition for a rubble pile Energy and AM are ideally conserved, but are decomposed: Kinetic Energy Potential Energy The mutual potential energy is liberated and serves as a conduit to transfer rotational and translational KE

58 Fission Fission spin rate is the minimum rate for two partitions of the asteroid to enter orbit. Corresponds to the maximum center of mass separation across all possible partitions

59 Orbital Evolution

60 Post-Fission Dynamics The problem changes to the dynamical motion of two arbitrary mass distributions orbiting about each other Strong coupling between translational and rotational motion Generalized version of a classical celestial mechanics problem

61 Orbit Mechanics after Fission The relevant energy for orbital motion is the free energy, which is conserved under dynamical evolution: Energy transfer between orbit and rotation happen rapidly If E Free > 0, system can catastrophically disrupt If E Free < 0, system cannot catastrophically disrupt Orbits with E Free > 0 are highly unstable and usually will send the components away on hyperbolic orbits

62 Stability of a fissioned system Ideal Stability of a Sphere-Sphere System Ground State Equilibrium for initially touching bodies E > 0 Unstable Fissioned binaries with a mass ratio < ~0.2 have sufficient energy to escape in a timescale of days to months (Scheeres, Celestial Mechanics & Dynamical Astronomy 2009). 47

63 Fission Dynamics of a proto 1999 KW4 System Movie by S. Jacobson Initial conditions are chosen at the precise fission limit when the two components enter orbit about each other. Total movie duration is several days.

64 Separation Distance Primary Radius Jacobson & Scheeres, Icarus 2011 Zero Free Energy for Two Spheres Mass Ratio Fissioned Asteroids with mass ratios < 0.2 eventually escape, the closer to the cutoff, the more energy is drawn from the primary spin.

65 Primary Spin Period Asteroid Pair Primary Spin vs Mass Ratio Pravec et al., Nature 2010 Prediction: The mass ratio between asteroid pairs should be < 0.2 The primary spin period should grow long near the cut-off Observation: The mass ratios and primary spin periods of Main Belt asteroid pairs match with our Asteroid Fission Theory Comment: The theory matches two independent outcomes, mass ratio cut-off and primary spin period lengthening

66 Energetics of a fissioned system When a body fissions, it s components enter a chaotic dynamical phase: Fissioned binaries with a mass ratio < ~0.2 have sufficient energy to evolve to escape in a timescale of days to months (Scheeres, Celestial Mechanics & Dynamical Astronomy 2002). The theory makes specific predictions that are consistent with observations of Asteroid Pairs Prior to escape, a sizable fraction of the secondaries are spun fast enough to undergo fission again Inner satellite usually impacts the primary, should cause reshaping Outer satellite is stabilized This sequence can repeat and, along with gravity, friction, and sunshine, can create the observed class of NEA asteroid systems (Jacobson & Scheeres, Icarus 2011). 51

67 q 0.2 YORP Process yrs Chaotic Binary Tidal Process yrs Doubly Synchronous Binary Contact Binary BYORP Process yrs Asteroid Pair Tidal Process yrs Asteroid Chaotic Ternary Stable Ternary 1.1 ± 1.1% Dynamic Processes 1 yrs q 0.2 YORP Process yrs Chaotic Binary Tidal Process yrs Synchronous Binary 8.6 ± 4.0% BYORP Process yrs Re-Shaped Asteroid Dynamic Processes 1 yrs Asteroid Pair Jacobson & Scheeres, Icarus 2011 Re-Shaped Asteroid 28.3 ± 6.6% Asteroid Pair 64.2 ± 7.1%

68 53

69 Precise Modeling of the Mechanics of an Asteroid System M 1 M 2 r 12 M 1 + M r = r 2 r 1 Ḣ 1 = H M 1 Ḣ 2 = H M 2 1 = I1 1 H 1 2 = I2 1 A H 2 Ȧ = A 1 2 A Z Z dm 1 dm 2 U 12 (r, A) = G r + 1 A 2 Ȧ 1 = A High dimensional system with coupled rotational and translational motions. Interest in both short-time dynamics and evolutionary dynamics. 54

70 Summary Study of asteroids leads directly to study of minimum energy configurations of self-gravitating grains Only possible for bodies with finite density For finite density bodies, minimum energy and stable configurations are defined as a function of angular momentum by studying the minimum energy function: E m = H2 + U 2I H only a function of the system configuration Globally minimum energy configurations are denumerable Simple few body systems can be fully explored Need theories for polydisperse grains and N >> 1 55

Constraints on Bounded Motion and Mutual Escape for the Full 3-Body Problem

arxiv:1611.09997v1 [astro-ph.ep] 30 Nov 2016 Constraints on Bounded Motion and Mutual Escape for the Full 3-Body Problem D.J. Scheeres Department of Aerospace Engineering Sciences The University of Colorado