On the minimum flexing of arms of LISA (Laser Interferometer Space Antenna)

Transcription

1 On the minimum flexing of arms of LISA (Laser Interferometer Space Antenna) Dr. SUCHETA KOSHTI IISER, Pune, India. ICSW-7, IPM, Tehran,Iran Jun4, 27

2 Motivation Einstein s General theory of relativity (GR) is the most beautiful & successful theory of gravity. It has matched most of the tests of Gravitation remarkably well. Weak field, linearized GR predicts Gravitational radiation. Massless, propagating excitations of the 2 gravitational field. g = η + h + O( h ) μν μν μν h μν Strong, indirect evidence of Gravitational waves (GW) deduced from measured slow down of Binary pulsars due to GW emission. (Hulse & Taylor won the 1993 Nobel prize for physics for this work.) Intense international efforts is underway for direct detection of GW. =

3 Terrestrial GW observatories Weak interaction of Gravitational waves makes direct detection a major scientific challenge of this century. Number of Laser interferometers with Kilometer Scale arm length are already taking scientific data in hope of detecting GW signals from astrophysical sources. LIGO (U.S.A.) 4 km. GEO (Germany).6 km Virgo (Italy) 3km TAMA (Japan).3 km AIGO (Aus.)

4 4 kms LIGO Hanford Washington USA 4 kms LIGO Laser Interferometer Gravitational-Wave Observatory LIGO Livingston Louisiana, USA

5 Effect of GW on test masses

6 Effect of GW on a ring of test masses Interferometer mirrors as test masses

7 Detecting GW with Laser Interferometer A B Path A Path B Difference in distance of Path A & B Interference of laser light at the detector (Photodiode)

8 Path difference phase difference Equal arms: Dark fringe The effects of gravitational waves appear as a fluctuation in the phase differences between two orthogonal light paths of an interferometer. Unequal arm: Signal in PD

9 Challenge of Direct Detection Gravitational waves are very weak! Gravitational wave is measured in terms of strain, h (change in length/original length) δ 2 L = h L Expected amplitude of GW signals h Measure changes of one part in thousand-billion-billion!

10 GW OBSERVATORY IN SPACE LISA : Laser Interferometer Space Antenna (An ambitious world-wide project) NASA, ESA joint proposal for space based GW Observatory (expected launch 215).

11 Why a GW Observatory in space? Terrestrial GW observatories are limited to GW frequencies above 1 Hz due to seismic noise. ( 1 Hz 2 Hz.) Interesting sources abundant at sub-hertz frequencies (milli-hz to Hz range) are accessible. Easier to attain higher sensitivity with longer baselines.

12 LISA : Laser Interferometer Space Antenna A NASA, ESA joint proposal for space based GW Observatory ( launch 215). Frequency range: 1 4 Hz - 1 Hz A configuration of three `freely falling spacecrafts in earth-like orbit linked by optical laser beams working as an interferometer in space

13 The Orbit of LISA The spacecraft are freely falling in the Sun s field.

14 The Orbit of LISA The cluster rolls once per year The spacecraft are freely falling in the Sun s field.

15 GW Source for LISA h h

16 Terrestrial observatories and space observatories compliment each other

17 Technical Challenges of LISA Technical Challenges of LISA -- an extremely ambitious mission 1. Cancellation of Laser frequency noise. Laser frequency Fluctuations is orders of magnitude larger than the GW signal For terrestrial observatory, equal arm length of interferometer can be ensured automatic cancellation of laser frequency noise. For LISA, distances between spacecrafts do not remain constant.

18 Technical Challenges of LISA -- an extremely ambitious mission 2. Stable flight formation & configuration The spacecraft configuration needs to maintain rigidity Distances between spacecrafts should not change. We do detail analysis of orbits of LISA spacecrafts.

19 CW Frame and Equations CW: Clohessy-Wiltshire eqns. && x 2y& 3 && y + 2x& =, && z + 2 z =. 2 x =,

20 The general solution of CW equations Reference orbit circular: = constant. sin cos ) ( ), 2 ( ) 3(2 cos 2 )sin 4 (6 ) ( ), 2(2 )cos 2 (3 sin ) ( t z t z t z x y t y x t x t y x t y y x t y x t x t x + = = = & & & & & & & & Offset terms: + 2, 2 x y y x & &,,,,, z y x z y x o & & & Initial conditions:

21 Stability requirements 1. No offsets : 2. Constant distance from the origin of the CW Frame 2, 2 = = + x y y x & & tan, 4 ), cos( 2 3 ) ( ), sin( ) ( ), cos( 2 1 ) ( x y y x t t z t t y t t x = + = = ± = = φ ρ φ ρ φ ρ φ ρ where Orbits must lie in a plane making 6 angle with the ecliptic ±

22 Orbit equations First order in orbit eccentricity, e x y z k k k ( t) ( t) ( t) = = 2 = e 3 R er cos t ( k er 1) sin t ( k cos t ( k 2π 3 1) 1) 2π 3 2π 3 Coordinates of spacecraft, k x (), t y (), t z () t { } k k k

23 The distance between spacecraft = [( ) 2 + ( ) 2 + ( )] 2 2 ij i j i j i j l x x y y z z 1

24 To the first order in eccentricity, The distances between space craft Remain constant. But To the second order in eccentricity, The distances between space craft change This is called arm flexing.

25 Arm Length (million Kms.) Breathing modes for 6 ± tilt 2.3% Peak- peak variation Time (years)

26 Tuning the tilt of LISA plane We readjust the tilt of the plane of LISA triangle from 6 ± 6 ± +δ Then find the condition on δ.

27 Geometry of LISA

28 l 1 α = =, e = + αδ, ε = α + 2R α α α αδ 3 l (, t δ) = l+δl ( t, δ) α R 3 5 Δ l12( t, δ) = [48( δ1) 15cosθ+ 48( δ1)cos2θ cos3 θ)] π δ = αδ1 and θ = 2πt Δ l1 2( t, δ = ) = αl(6 5cosθ+ 1cos 2θ cos3θ) 32 3

29 Optimal variation in arm-length vs. time Tilt =6 ± Arm-length (million km.) 2.3%.96 % Optimal Tilt Time (in years)

30 Arm-length vs. time and tilt 6 ± 6.57 ± Time in years Tilt = π/3+ δ Arm-length (million km)

31 Maximum Variation of arm length for different tilts 6 ± Reduction by factor Variation is minimized around Tilt angle = 6 ± +.57 ±

32 Relative velocities ( Doppler shifts) Rel. velocity of spacecrafts (m/s) Optimal Tilt Tilt = 6 ± Time (in years) Optimal tilt: Maximum separation velocity is 5.6 times smaller!! Doppler shifts reduction is more crucial than arm length variation

33 Main results We show that there exist heliocentric orbits which can form stable flight configurations The inter-spacecraft distances remain constant during flight to the first order in eccentricity The configuration moves rigidly. The configuration can have any number of spacecraft and arbitrary shape Need not be an equilateral triangle (LISA).

34 Reducing flexing of arms of LISA At higher order in eccentricity : (Class.Quantum Grav., 23(26) ) LISA arms slowly change over the time scale of a year. This is called as flexing of arms or breathing modes. The maximum flexing amplitude is ~115 km (2.3% variation) if the configuration is in a 6 ± Plane with the ecliptic. The maximum flexing amplitude can be reduced further to ~48 km (.96% variation) by readjusting the tilt of the plane of LISA triangle.

35 Significance beyond LISA The stable constellation can consist of arbitrary number N of spacecraft and can have arbitrary shape. For LISA with N=3, the equilateral triangular configuration is not the only one.» N=4 square configuration has been proposed for detecting stochastic GW background. Big Bang Observer (NASA: Beyond Einstein program) would like to have several LISA like, but smaller (.5 million km. arm lengths) constellations flown simultaneously.

36 Thank you!!!

37 References Stable flight formation of LISA S.V. Dhurandhar, R. Nayak,S. Koshti & J-Y Vinet Class.Quantum Grav.22(25) On the minimum flexing of LISA s arms R. Nayak,S. Koshti, S.V. Dhurandhar, & J-Y Vinet Class.Quantum Grav.23(26)