Sittiporn Channumsin Coauthors


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1 28 Oct 2014 Space Glasgow Research Conference Sittiporn Channumsin Sittiporn Channumsin Coauthors S. Channumsin
2 Outline Background Objective The model Simulation Results Conclusion and Future work 2
3 Space Debris Space debris  Artificial debris and natural debris.  Orbit with hypervelocity that can threat to active spacecraft leading to catastrophic breakups generating new space debris  Need to reduce the number of debris. Experiment Gravity movie 3
4 Space debris 4
5 Discover HAMR objects Collision and explosion  Fengyun1C Discovery in 2004 (GEO)  Iridium 33 and Cosmos 2251 Suspected objects High areatomass ratio (HAMR) objects Variations of light curves Variations of areatomass ratio (AMR) (Anselmo, L. and C. Pardini, 2010) Experiment  Shot micro satellite model Multilayer insulation (Murakami, J., et al 2008) 5
6 Objective 1. Develop a model of a thin, highly flexible MLItype membrane, in terms of multibody dynamics, and solved by using fundamental Newtonian mechanics 2. Investigate the orbital dynamics under J2 and the lunisolar third body gravitation and solar radiation pressure (SRP) by comparing with rigid body case 3. Investigate a selfshadowing effect to the orbital dynamics of flexible debris 6
7 flexible model 7
8 The flexible model Flat plate y Torsional Damper x Torsional spring Consider deformation in 2 D of xy plane 8
9 Simplification Flat plate Dimension 1 x 1 square meter l 1 = l 2 = 0.5 (m) Torsional Damper y m 1 m 2 m 3 0.5m 0.5m x Torsional spring 9
10 Simplification Triangular shape Torsional Damper y m 2 m 1 m 3 x Torsional spring 10
11 Multibody dynamics Newtonian equation F T F F m a F k i i s, i d, i i i Where i = mass of each (1,2 and 3) Spring and damper forces s s k s EI Length Fd c c DF Mk s Torsional Damper m 2 m 1 Torsional spring Constrained equation m 3 Where k s = rotational spring constant, θ = angle of deformation θ = angular velocity of the deformation, E = young modulus I = the moment of inertia of thin plate Length = the length of each rod and is c = Coefficient of torsion spring (N.m rad 1 ) DF= dissipation factor of material M = mass of rod (Kg) ( x x ) ( y y ) ( z z ) l i1 i i1 i i1 i i  Length of a rod = 0.5 m 11
12 Simulation of the model 12
13 Initial shape to test the model 13
14 Validation of spring The simulation results without external force and damper by activating torsional spring 14
15 The simulation with torsional spring and damper 15
16 Orbital dynamics and Perturbation 16
17 The modified equinoctial elements p i 2 p w p i, t p fi L w L f h L k L w g i, t i, n [ i, r sin [( 1) cos ] ( sin cos ) ] p gi L w L g h L k L w i, t i, n [ i, r cos [( 1) cos ] ( sin cos ) ] 2 p s hi cos Li, n 2w 2 p s ki cos Li, n 2w w 2 1 p Li p( ) ( hsin L k cos L) p w i, n w f w 2 p a(1 e ) i h tan( )sin 2 g esin( ) f ecos( ) i k tan( )sin 2 L Where = gravitational constant = right ascension of ascending node degree e = eccentricity = true anomaly a = semimajor axis(km) = argument of perigee i = Inclination L = true longitude p = semiparameter 17
18 J2 Perturbations and Third body J2 perturbations a a a R 3J R x 5x (1 ) I K j2, I 5 2 xi 2x x R 3J R x 5x (1 ) J K j2, J 5 2 xj 2x x R 3J R x 5x (3 ) K K j2, K 5 2 xk 2x x The third body a G M k k1,2 k x x x x x k k 3 3 x k k Where k = 1 and 2 (Sun and Moon) 18
19 Solar radiation pressure force Solar radiation pressure force N psr Ai cos CRd i Frad 2 CRs cos( ) (1 ) i inc n C i Rs s i i1 c 3 Reflection beam n sun s inci A 19
20 S i Average solar radiation pressure = [1,0,0] Rigid body case Average SRP force 2 1 F F d d avg rad, j s s Equivalent area Therefore xi x FAVG Aeq PSP ( R) x x i A eq Where P F SP avg ( ) E PSP R C x ( R) i A 2 x 2 20
21 Selfshadowing d n l p l ( v l) n( v l) or P = Mv P n. l d lxnx lxny lxnz lxd lynx n. l d lyny lynz lyd M lznx lzny n. l d lznz lzd nx ny nz n. l Where p= the projection of vertex v v = Vertex on the plane : n x d 0 l= a location of light source The planar shadow projection, the original technique invented by Blinn [15], allows shadows to be cast on plane surface l v p 21
22 Selfshadowing a) Change position of light source b) Change the geometry of debris 22
23 Simulation 23
24 Material properties Material type AMR [m2/kg] Young s Modulus [N/m2] Cs, Cd, Ca PET coated x Kapton coated x uncoated PET Kapton (Sheldahl, The red book (2012) 24
25 Initial position Geosynchronous Earth orbit (GEO) Six element Semimajor axes(km) Mean anomaly(degree) Argument of perigee(degree) Value 42, Ascending node(degree) Eccentricity Inclination(degree) Propagation in 12 days Start point 28 Oct 2014 S. Channumsin 25
26 J2 and SRP 26
27 Orbital dynamics 12 days PET 27
28 PET without selfshadowing 10 minutes 28
29 PET with selfshadowing 10 minutes 29
30 Comparison PET without selfshadowing PET with selfshadowing 30
31 Orbital dynamics under J2, third body and SRP 31
32 Orbital dynamics 12 days 32
33 PET Euler angles 1 st panel 2 nd panel 33
34 Kapton Euler angles 1 st panel 2 nd panel 34
35 Conclusion and Future work 28 Oct 2014 S. Channumsin 35
36 Conclusion 1. Orbital dynamics of flexible debris is different from that of rigid debris due to the effective area. 2. Direct solar radiation pressure is the most effect to the orbital dynamics of HAMR flexible model. 3. Selfshadowing effect lead to irregular attitude dynamics and deformation 36
37 Future work To set the deformation experiment to validate the flexible model Acknowledge This work was funded by Ministry of Science and Technology of the Thai government and the European Office of Aerospace Research and Development (project award FA ). 28 Oct 2014 S. Channumsin 37
38 Space Glasgow Thank you
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