Passive Magnetic Attitude Control For CubeSat Spacecraft

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SSC10-XXXX-XPassive Magnetic Attitude Control for CubeSatSpacecraftDavid T. GerhardtUniversity of Colorado, Boulder, CO 80309Scott E. PaloAdvisor, University of Colorado, Boulder, CO 80309The National Science Foundation has begun funding CubeSats for space weather investigation. Many of thesemissions are to measure charged particles in a highly inclined Low Earth Orbit (LEO). The charged particlesspiral around magnetic field lines as they reach LEO. Passive Magnetic Attitude Control (PMAC) aligns aCubeSat to within 15 of the Earth’s local magnetic field line throughout each orbit, maximizing particlecounts available for onboard science instrumentation. Also, given typical CubeSat mass ( 4 kg) and power( 6W insolated without deployable solar panels) constraints, PMAC is ideal as it performs using low mass( 50g) and no power. The design of a PMAC system is discussed for a 3U CubeSat, considering externaltorques acting on the craft, parametric resonance, and apparent permeability of the hysteresis rod. Next, thedevelopment of a PMAC Matlab simulation is discussed, including equations of motion, an Earth magnetic fieldmodel, and hysteresis rod response. Key steps are outlined with sufficient detail to recreate the simulation.Finally, the simulation is used to verify the PMAC system onboard the NSF-funded Colorado Student SpaceWeather Experiment (CSSWE).IntroductionSOLUTIONS for satellite attitude control must beweighed by trade of resources vs. performance.CubeSats are a unique form factor varing from one (1U)to three (3U) stacked cubes of dimensions 10 10 10cm. For these small satellites, Passive Magnetic AttitudeControl (PMAC) is a robust attitude solution particularly useful for space weather investigation. PMAC iscomposed of a bar magnet to supply restoring torqueand a hysteresis rod to supply dampening torque. As apassive system, PMAC draws no system power and, formicrosatellites and smaller, uses less than 50 grams ofmass. The concept was space-tested in 1960 on Transit1B, and has been used moderately since then. PMAC issometimes not a desirable solution because its pointingis typically limited to oscillations 15 about the localmagnetic field.1 However, when a mission has low resource availability and benefits from alignment with theEarth magnetic field, PMAC is a wise solution.Figure 1. CSSWE Magnetic Components.particles which spiral around magnetic field lines. Aligning with the local magnetic field maximizes the particlesavailable for the CSSWE science instrument: the Relativistic Electron Particle Telescope integrated little experiment (REPTile).3 All calculations and simulationsassume a 600 km, 55 inclination orbit, required to reachthese high-energy particles. The attitude control systemof CSSWE has two performance requirements:The National Science Foundation began fundingCubeSats for space weather investigation in 2008 withMichigan’s RAX CubeSat. The Michigan team chosePMAC for their CubeSat, and have developed an airbearing testbed in lieu of modeling the system behavior.2The University of Colorado’s Colorado Student SpaceWeather Experiment (CSSWE) has also chosen a PMACsystem. Its mission involves sensing high-energy charged1. The attitude control system shall have a settlingtime of less than 7 days.2. Once settled, the CubeSat shall stay within 15 ofthe local magnetic field lines.The ability to meet these requirements is entirely dependent on the PMAC system design; the requirements are1D. T. Gerhardt24th Annual AIAA/USUConference on Small Satellites

SSC10-XXXX-Xstrength for the UNISAT-4 student satellite:5Table 1. 3U CubeSat Environmental Torques TorqueValue[N·m]AerodynamicGravity GradientRadiometricRMS Sum m 10(2)where TRM S is the root means squared sum of independent environmental torques, Bmin is the minimum fieldstrength at 600 km (2.0E 5 Tesla), and βmax is thedesired pointing accuracy (10 ).8E 86E 81E 81E 7Bar Magnet DesignAssuming 600 km orbitThe bar magnet design is concerned with finding asuitable bar magnet magnetic moment. Equation 2 hasbeen modified from Santoni and Zelli5 to decrease thestrength of the bar magnet, thus decreasing the requiredhysteresis material within the volume-limited CubeSat.This equation gives CSSWE the minimum m 0.29A·m2 .A second constraint on the chosen bar magnetstrength is parametric resonance, which can occur forpolar orbits. The magnetic moments which resonate aregiven by the following system of equations:validated by a Matlab model. Figure 1 shows CSSWEwith magnetic components highlighted in red.There are two sources of error in effect when using aPMAC system. The first is steady state error, in whichthe hysteresis rod magnetic moment causes the totalmagnetic moment to be misaligned with the long axisof the spacecraft, decreasing pointing accuracy. Becausethe hysteresis rod polarity switches, this effect cannotbe canceled using a particular hysteresis rod orientation.Steady state error becomes noticeable when the torquesupplied by the bar magnet is on par with the hysteresisrod torque (when the angle between the CubeSat longaxis and the local magnetic field is small). The second, oscillatory error, occurs because the magnetic fieldchanges as the spacecraft travels, causing a delay beforealignment with the current field.4 The oscillatory error is directly related to the PMAC settling time, whichmay be of critical importance for a short mission duration. As hysteresis material is increased, the oscillatoryerror and settling time decrease at the cost of increasedsteady-state error, while decreasing the material has theopposite effect. A good PMAC system design will findthe balance between these two errors when determiningthe hysteresis material needed for a given bar magnetstrength.Ixxη 2.63k 2 0.49 0.51IyyIxxη 2.63k 2 4.25 1.25IyymRES, (3)(4)Iyy · n20 · ηBeq(5)Iyy · n20 · η Beq(6)mRES where k is an integer, Ixx is the minor axis moment ofinertia, Iyy is the major axis moment of inertia, n0 isthe orbit mean motion, and Beq is the magnetic fluxdensity at the equator. Note Equations 5 and 6 are corrected from Santoni and Zelli.5 For CSSWE and mostCubeSats, Iyy Izz ; mRES and mRES, should be recalculated for Izz if Iyy 6 Izz . Table 2 shows resonatingmagnetic moments for CSSWE surrounding the threshold set by Equation 2. This table assumes Beq 2.3E 5Tesla, Ixx 3.6E 3 kg·m2 , Iyy 1.7E 2 kg·m2 , and600 km orbit altitude. Considering the minimum valuefor m set by Equation 2 and the resonating values shownin Table 2, CSSWE has chosen m 0.3 A·m2 .PMAC System DesignA successful attitude system design begins with ananalysis of external torques experienced by the spacecraft. Table 1 shows the torques experienced by a 3UCubeSat at 600 km. The torque supplied by a magneticmoment in a magnetic field is quite simple: T m B.TRM SBmin · sin(βmax )Hysteresis Rod Design(1)Once a bar magnet magnetic moment has been chosen,the hysteresis rod dimensions and quantity should be determined. Typically, hysteresis rods are mounted in pairsorthogonal to the bar magnet to maximize dampeningper rod. Thus, we set the bar magnet in alignment withthe long axis (X-axis) of the CubeSat, and place hysteresis rods in alignment with both short axes (Y and Z is the magnetic flux density vector and mwhere B isthe magnetic moment vector for the bar magnet, thoughthis equation is valid for the torque from a hysteresis variesrod magnetic moment as well. At 600 km, B from 0.20 0.45 Gauss. The author presents a modifiedversion of Santoni and Zelli’s recommended bar magnet2D. T. Gerhardt24th Annual AIAA/USUConference on Small Satellites

SSC10-XXXX-XTable 2. CSSWE Parametric Resonanceskηη mRES mRES, [A·m2 ] [A·m2 . The rods supply dampening by shifting polaritiesin delayed response to the magnetic field changes, converting rotational energy into heat. A hysteresis loopdescribes the rod’s induced magnetic flux density fora given magnetic field strength, and is generally characterized by three magnetic hysteresis parameters: thecoercive force Hc , the remanence Br , and the saturation induction Bs , shown in Figure 2. These parametersare important in describing the shape of the hysteresisloop, the area of which determines the dampening per cycle per unit volume. However, the magnetic parametersvary with rod length to diameter L/D ratio, material,and external field strength. The dimensions and number of rods are set in response to the estimated magnetichysteresis parameters.There are a number of ways to estimate the magnetichysteresis parameters: Levesque uses true permeabilityrated material numbers regardless of rod dimensions,4Santoni and Zelli estimate the apparent permeability ofthe rod based on dimensions and applied field parameter values,5 while Flatley and Henretty use empiricallydetermined values for a specific rod.6 While empiricalcalculations are ideal, the design of a testing apparatusis beyond the scope of this paper. Instead, the authoroutlines a process to estimate the apparent hysteresis rodparameters. To begin, the magnetic moment supplied bya hysteresis rod is given by:mhyst Bhyst · Vhystµ0Figure 2. Hysteresis loop diagramwith H and Bhyst and is non-linear,5 as shown in Figure 2. The apparent permeability may be defined as:µ0hyst (9)where N is the demagnetizing factor of the rod and µhystis the true relative permeability of the rod which varieswith H.5 Note that µhyst is always greater than µ0hyst ,and the discrepancy between the two grows with N . Thedemagnetization factor for the long axis of a cylinder isgiven by:7 1L4 2N .(10)DπClearly, the hysteresis rod L/D ratio affects the valueof N , and thus the efficiency of the rod. We combineEquations 8 - 10 to estimate the expected hysteresis rodapparent saturation induction: Bs0 µ0 µ0hyst Hs µ0 (7)µhyst (Hs ) 1 HsL 41 µhyst (Hs ) D 2π(11)where Hs is the magnetic field strength at saturation (Hwhen B Bs ). Typical values of L/D are 100 300,1and CubeSat interior dimensions set an upper limit soL 9.5 cm. Recognizing this, we use L/D 95 andfind D 1 mm (for ease of manufacturing). The chosenhysteresis rod material (HyMu-80) has a material saturation field strength Hs 100 A/m.5 Using this Hs andFigure 3, we find µhyst (Hs ) 1.5E 4. Using Equation 11 with these values estimates Bs0 0.0268 Tesla.However, Hc0 and Br0 cannot be calculated the same way,so we instead estimate their values equivalent to thosewhere mhyst is the magnetic moment of the hysteresisrod aligned with its long axis, Bhyst is the magnetic fluxinduced in the rod, Vhyst is the volume of the rod, and µ0is the permeability of free space.6 The induced magneticflux is broken down to:Bhyst µ0 µ0hyst Hµhyst (H)1 N µhyst (H)(8)where H is the magnetic field strength and µ0hyst isthe apparent relative permeability of the rod. Becausethe hysteresis rod is ferromagnetic material, µ0hyst varies3D. T. Gerhardt24th Annual AIAA/USUConference on Small Satellites

SSC10-XXXX-XMatlab Attitude SimulationThe attitude simulation begins with a choice of attitude coordinates. The author has chosen 3-2-1 Eulerangles; this attitude coordinate set results in the following kinematic differential equation of motion: θ10sθ3cθ3ωx1 0 cθ3 cθ2 sθ3 cθ2 ωy θ 2 cθ2 cθ2 sθ3 sθ2 cθ3 sθ2ωzθ3(12)where θ1 , θ2 , θ3 are the Euler angles , θ 1 , θ 2 , θ 3 are theEuler angle rates and ωx , ωy , ωz are the body-fixed angular velocities of the X Y Z axes respectively. Also notethat cθ is cos θ and sθ is sin θ. Now we assume a bodyframe aligned with the principal axes of the CubeSat(constant diagonal mass matrix) and use Euler’s separated rotational equations of motion to complete theequation set:Figure 3. Hysteresis rod true permeability8 Estimated value151HyMu-800.960.350.74120.0040.025 (13)Iyy ω y (Ixx Izz )ωz ωx Ly(14)Izz ω z (Iyy Ixx )ωx ωy Lz(15)where Ixx , Iyy , Izz are the mass moment of inertias ofthe principal axes which align with the body fixed X YZ axes respectively, ω x , ω y , ω z are the body fixed angular accelerations for the X Y Z axes respectively, andLx , Ly , Lz are the external torques on the X Y Z axesrespectively.9 With the equations of motion are defined,we investigate the external torques acting on the CubeSat.Table 3. Hysteresis Rod ComparisonPropertyUNISAT-45 CSSWERod Length [cm]Rod Diameter [mm]MaterialMaterial Hc [A/m]8Material Br [Tesla]4Material Bs [Tesla]8Apparent Hc0 [A/m]Apparent Br0 [Tesla]Apparent Bs0 [Tesla]Ixx ω x (Izz Iyy )ωy ωz Lx9.51HyMu-800.960.350.7412 0.004 0.027 External Torque: Bar MagnetWhile the bar magnet torque is simply given by Equa varies with both orbit location, andtion 1, the value of B the current attitude configuration. Keep in mind that Bis the magnetic field experienced by the bar magnet andmust be examined in a body-fixed frame. The simulation has two frames: body-fixed and the Earth CenteredEarth Fixed (ECEF) inertial frame. The Direction Cosine Matrix (DCM) which allows rotation from inertialto body-fixed frame for 3-2-1 Euler angles is given below: cθ2 cθ1cθ2 sθ1 sθ2 sθ3 sθ2 cθ1 cθ3 sθ1 sθ3 sθ2 sθ1 cθ3 cθ1 sθ3 cθ2 cθ3 sθ2 cθ1 sθ3 sθ1 cθ3 sθ2 sθ1 sθ3 cθ1 cθ3 cθ2(16)The DCM is defined as{b̂} [C(θ1 , θ2 , θ3 )]{n̂} where {b̂} is the body-framevector, [C(θ1 , θ2 , θ3 )] is the DCM, and {n̂} is the inertialframe vector.9 We now have the tools to use a modelof the Earth’s magnetic field strength in the simulation.Rauschenbakh et al. define the following dipole modelCalculated valueempirically derived from a similar rod.5 This assumption is valid because the calculated Hs0 is very close tothe UNISAT-4 value. Table 3 compares the hysteresisrod properties of UNISAT-4 and CSSWE. Note that thevalues of Hc and Br are estimated values and shouldbe empirically tested before completing the design ofa PMAC system. Now that the physical properties ofeach rod have now been estimated, an attitude simulation is developed to determine the number of rods peraxis needed to satisfy the pointing requirements.4D. T. Gerhardt24th Annual AIAA/USUConference on Small Satellites

SSC10-XXXX-XH as seen by the rod must be available at each timestepto define dH/dt. However, the previous time need notbe saved as only the threshold of dH/dt above or belowzero matters for this model.This model ensures that Hc and Br cross the X andY axes as shown in Figure 2. The material hysteresisparameters in Equations 20 and 21 may be interchangedfor the apparent hysteresis parameters to simulate nonideal, realistic rods. Figure 4 shows the hysteresis loopgenerated by using the apparent parameters in Table 3with the models for Earth magnetic field and hysteresis developed thus far. The hysteresis loop is cut offbecause the maximum variation of the Earth magneticfield strength component is 25.8 A/m at 600 km; theEarth magnetic forcing is not large enough to induce Bs0 .Note an ideal assumption associated with this model: weuse only one hysteresis loop to model the hysteresis response. In reality, a different hysteresis loop is generatedfor each field strength cycle range. If empirical data forvarious field strength loops are available, the hysteresisresponse for multiple field strength ranges may be simulated.6Figure 4. Modeled Apparent Hysteresis Loopin ECEF frame:H1 3Heq sin i cos i sin2 u(17)H2 3Heq sin i sin u cos u(18)22H3 Heq (1 3 sin i sin u)(19)Matlab ODE Solver Pitfallswhere Heq is the equatorial magnetic field strength magnitude at 600 km (18.3 A/m), i is the orbit inclination(55 ), u is the argument of latitude, and H1 , H2 , H3 isthe magnetic field strength in the ECEF direction vectors 1,2,3 respectively.10 An argument of latitude valueis linked to each timestep, simulating the CubeSat motion through each orbit. At each timestep the DCM isused to determine the magnetic field seen by the CubeSat, which is then used to determine the external torquedue to the bar magnet.Through a series of unfortunate events, the author hasdiscovered a few pitfalls associated with built-in MatlabODE numerical solvers. The first of these pitfalls is toassume the absolute and relative tolerances may be setto default values 1E 6 and 1E 3 respectively. To testthis, we developed a simplified two-dimensional model tosimulate the basic dynamics, using the Hysteresis Modelshown above to simulate one hysteresis rod in a constantmagnetic field. This model was given an initial rotationrate and run using Matlab’s ode45 numeric integrator.Figure 5 shows the behavior of the model for varyingvalues of relative and absolute tolerance. The dynamicresponse for each Matlab ODE solver converges at a tolerance of 1E 7; this value is used for all subsequentMatlab ODE solver inputs.The second pitfall is to assume all Matlab solvers behave equally. Figure 6 shows the results from the sametwo-dimensional model, this time run with different Matlab ODE solvers (tolerance: 1E 7). The results showthat the slope of the angular velocity envelope, directlycorrelated with the settling time of the simulation, variesby solver. However, the author has chosen to use theode45 solver due to its known robustness.External Torque: Hysteresis RodsSimulating the hysteresis response begins by developing a hysteresis loop model. Flatley and Henrettydevelop the following model:6 1πBrp tan(20)Hc2Bs 2Bhyst Bs tan 1 p(H Hc )(21)πwhere p is a constant for a given set of magnetic hysteresis parameters and H is the component of the magneticfield strength aligned with the hysteresis rod. Notice the Hc term of Equation 21. A value of Hc is used whendH/dt 0 and Hc is used when dH/dt 0. This termis essential in defining the delay of the hysteresis loop,though it does create a headache when coding the modelin an ODE solver such as Matlab’s ode45. Because theangular position of the rod defines the component of themagnetic field aligned with the rod, the previous value ofSimulation ResultsThe input assumptions for the Matlab PMAC simulation are shown in Tables 3 (apparent values) and 4. Thefirst model run simulates one hysteresis rod on the Y andZ axes. The angular velocity decay over time is shown in5D. T. Gerhardt24th Annual AIAA/USUConference on Small Satellites

SSC10-XXXX-XFigure 7. Angular Velocity, 1 Rod / AxisFigure 5. Matlab Tolerance EffectFigure 8. Beta, 1 Rod / AxisFigure 6. Matlab Solver EffectFigure 7. Figure 8 shows the angle β, the angle betweenthe CubeSat long axis and the local magnetic field, vs.time. Clearly, there is not enough dampening material tomeet the required 7 day settling time. Next, the simulation is run adding another rod on the Y and Z axes. Theangular velocity decay with two rods per axis is shownin Figure 9. Figure 10 shows that the settling time requirement of 7 days is met, while the zoomed 11 shows βwithin the 15 requirement. However, Figure 11 mustbe viewed with equation 2 in mind. Because the PMACsystem was designed for βmax 10 , at β 10 , themagnetic torques enter the domain of the environmentaltorques shown in Table 1, where they will disturb theattitude of the CubeSat. The total estimated mass ofthe 4 hysteresis rods8 bar magnet is 8.6 grams (notincluding mounting structure).Table 4. CSSWE Input AssumptionsInputValueRods per axis Y Z(θ10 , θ20 , θ30 ), [ ](ωx0 , ωy0 , ωz0 ), [ /sec]Ixx [kg·m2 ]Iyy [kg·m2 ]Izz [kg·m2 ]Relative ToleranceAbsolute Tolerance2(0,0,0)(10,5,5)0.005510.025520.025651E 71E 76D. T. Gerhardt24th Annual AIAA/USUConference on Small Satellites

SSC10-XXXX-XConclusionWe describe the Passive Magnetic Attitude Control (PMAC) system for the Colorado Student SpaceWeather Experiment (CSSWE) CubeSat. PMAC is awise choice for the mission due to its ability to align theCubeSat within 15 of the Earth’s magnetic field at acost of 8.6

OLUTIONS for satellite attitude control must be weighed by trade of resources vs. performance. CubeSats are a unique form factor varing from one (1U) to three (3U) stacked cubes of dimensions 10 10 10 cm. For these small satellites, Passive Magnetic Attitude Control (PMAC) is a robust attitude solution particu-

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