﻿ Analytical Third Order Solution for Coupling Effects of Earth Oblateness and Direct Solar Radiation Pressure on the Motion of Artificial Satellites

International Journal of Astronomy and Astrophysics
Vol.04 No.03(2014), Article ID:49717,14 pages
10.4236/ijaa.2014.43049

Analytical Third Order Solution for Coupling Effects of Earth Oblateness and Direct Solar Radiation Pressure on the Motion of Artificial Satellites

Department of Astronomy, National Research Institute of Astronomy and Geophysics, Cairo, Egypt

Email: hassanselim@ yahoo.com   Received 21 June 2014; revised 18 July 2014; accepted 14 August 2014

ABSTRACT

Coupling effects of Earth oblateness and direct solar radiation pressure on the motion of an artificial satellite are evaluated. Secular and periodic terms are retained up to order three and two respectively, where the coefficient of the second zonal harmonic of the geopotential is considered of first order. The solution revealed the existence of secular terms at order three that arises from the couplings between terms, of lower orders, resulting from the solar radiation pressure.

Keywords: 1. Introduction

Analytical theories of celestial mechanics are usually more tractable when tackled within the domain of Hamiltonian mechanics, and fortunately most non-Hamiltonian systems of differential equations can be Hamiltonized by a simple technique   . As for as canonical perturbation methods are concerned, the basic demand is a canonical transformation such that the new Hamiltonian has fewer degrees of freedom, which results in integrals of motion equal in number to the number of ingrate coordinated, and thus successive transformations reduce the system to quadratures. If the Hamiltonian is a periodic function of time, a further requirement would be the averaging of the Hamiltonian to eliminate the time.

If the Hamiltonian admits a Taylor series expansion in powers of a small parameter at , a generator of the transformation can obtain a series of up to any desired power.

Many works deal with the effects of solar radiation pressure, Musen (1960)  derived first order expansion for the rate of change in the osculating elements using the method of variation of vector elements. Kosai (1961) and Brouwer (1962)   used Lagrange’s planetary equations to find the first order solutions with the integration performed between the times of exit from, and entry into, the shadow. The resonance effects produced by the commensurabilities between the different mean motions provided good field for detailed theoretical studies (e.g. Musen, 1960  ; Brouwer, 1962  and Hori, 1966  ). De Moraes (1981)  developed semi-ana- lytical theory including the joint effects of direct solar radiation pressure and atmospheric drag for satellites of perigee heights between 500 and 900 Kms. The difficulties arising from solar radiation pressure are analyzed in three very useful and interesting expositions given by Kampos (1968) and Sehnal (1970 and 1975)  -  . An interesting application is to use solar radiation pressure as means of spacecraft propulsion (solar sailing). The idea is described and its dynamics is studied by Mc Innes and Brouwn (1990)  .

It has been repeatedly stated by many authors (e.g. Kampos, 1968; Ferraz-Mello, 1972 and Anselono et al., 1983)    that there are no secular or long periodic changes of the semimajor axis and no second order terms (or even, by some author, no secular terms whatever the order). But Geyling and Westerman (1971), Lala (1972) and Sehnal (1975)    drew attention to secular terms which appear at higher orders. McMahon, Jay W., (2011)  modeled the solar radiation pressure acceleration as a Fourier series which depends on the Sun’s location in a body-fixed frame; a new set of Fourier coefficients are derived for every latitude of the Sun in this frame, and the series is expanded in terms of the longitude of the Sun. Lücking et al. (2012)  further explores a passive strategy based on the joint effects of solar radiation pressure and the Earth’s oblateness acting on a high area-to-mass-ratio object. In 2001, Cook found that the most significant effect relating to solar radiation pressure is the changing cross-sectional area of the satellite projected to the Sun  .

The present work is concerned with the effects of solar radiation pressure at higher orders to emphasize the effects of the couplings between them and with those resulting from the oblate gravity field of the Earth. The canonical equations of motion are formed in terms of the Delaunay elements augmented with the pair where is the mean longitude of the sun. The equations include the radiation pressure force and the geopotential up to . Two canonical transformations are made to eliminate the short and long period terms in succession respectively. The Hamiltonians and generator are assumed to be expandable as As expected secular terms arise at order 3 from the brackets and where the suffix refers to terms arising from solar radiation pressure.

2. Equation of Motion

In terms of the Delaunay variables the equations of motion of an artificial satellite about an oblate Earth and perturbed by direct solar radiation (1)

With the Hamiltonian (2) (3) (4)

And

is the solar constant, is the speed of light, is the mean distance Earth-Sun.

(5)

being is the mean motion of the sun, is a constant, is the obliquity of the ecliptic and is the equatorial radius of the Earth.

When deriving the above equations the Sun is assumed moving in a circular orbit so that its mean longitude is, and the direction and distance of the satellite from the Sun are considered similar to those of the Earth. Clearly represents the contribution of solar radiation pressure.

3. Short-Period Perturbations

Since depends only on, the angle will be a fast variable while the other angles are slow variables. Therefore, we shall perform two transformations to eliminate, in succession, the short and long period terms. Adopting the transformation techniques developed by Deprit (1969) and Kamel (1969)   , the identities for the short period transformation will be:

(6.1)

(6.2)

(6.3)

(6.4)

where is the Lie derivative generated by and the Hamiltonian and generating function at order n are obtained from (6.2) by choosing

(6.5)

Then

(6.6)

The elements of the transformation are obtained from

(7.1)

(7.2)

(7.3)

(7.4)

(8.1)

, n ≥ 1 (8.2)

, n ≥ 1 (8.3)

, n ≥ 1

(8.4)

Performing the operations described in Equations (6) with the secular and periodic terms retained up to the third and second order respectively, we arrive, after some lengthy manipulations, at the following results. All variables are understood to be single primed but the primes will be dropped out for the sake of simplicity of writing.

(9)

(10.1)

(10.2)

At the subsequent orders (order 2 and 3) we will be concerned only with terms arising from the radiation pressure and those due to the coupling between oblateness and radiation pressure effects. We thus separate as

(11)

where the suffixes and refer to gravity and radiation pressure, respectively. At the second order we have

(12.1)

(12.2)

where:

(13.1)

(13.2)

Regarding (6.3) we find that the manipulations at order 3 require evaluating

(14)

where:

Evaluating these brackets and performing the averaging process in Equation (6.5) we obtain, after lengthy calculations

(15.1)

(15.2)

(15.3)

(15.4)

So that

(16)

where the are functions of , the subscripts and mean partial derivatives with respect to each, and

(17.1)

(17.2)

For the elements of the transformations, substituting Equations (10.2) and (12.2) into Equation (8) yields

(18.1)

(18.2)

.

(18.3)

(19.1)

(19.2)

(19.3)

(19.4)

where:

where we note that consists only of terms arising from the oblateness effects and therefore need be taken into consideration.

Substitution of Equations (18) and (19) into (7) yields the transformation and inverse.

4. Perturbations of Long Period

After the short-period terms have been eliminated the problem is now reduced to the system of canonical equations with Hamitonian .

We now proceed to eliminate the long-period terms, i.e. those periodic in .

The transformation follows the procedure outlined in Equations (6)-(8) but with the averages and integrations, performed over . The basic identities are now

(20.1)

(20.2)

Performing the processes outlined in Equations (16.1),…, (16.6) and (20) to find and assuming no resonant conditions the following results follow (all variables are double primed)

4.1. Zero, First and Second Orders

Remembering that at orders 2 and 3, we are concerned only with the terms including radiation pressure effects we have

(21)

(22)

(23)

(24)

where:

And

4.2. Third Order

From (20.2)

(25.1)

(25.2)

where:

(26)

So, we can write

; ; (27)

By following the above scheme, the expressions for and can be deduce after a lengthily manipulation.

4.3. There Order

4.3.1. Expressions for and

From (16), (26) and (27)

(28.1)

Then

(28.2)

Where:

Clearly, Equation (28.2) holds as long as

4.3.2. Expressions for and Writing

(29)

Equation (26) can be decomposed such that

(30)

Regarding and, Equations (25) and (27) yield

(31)

(32)

(33)

where

And the primes on the summation signs en Equation (33) indicate that the terms is excluded. Clearly (33) holds as long as

For and we have

(34)

(35)

where

And

Equation (35) holds true as long as

Finally, for and, we have

(36)

(37)

where:

And

Again, Equation (37) holds true as long as the above conditions hold. Collecting we find that

(38)

(39)

4.3.3. Expressions for and

(40)

(41)

where

And

For and we have

(42)

(43)

Finally, for and we have

(44)

(45)

where:

4.3.4. Expressions for and

As Equation (23) and Equation (26) reduce to

So that

where:

The elements of transformation are easily obtained using Equations (7), (8) with replaced by, the unprimed elements replaced by single primed elements, and with the single primed elements replaced by double primed ones.

5. Effects of the Earth’s Shadow

In the proceeding developments, effects of entry into, or exit from, the Earth’s shadow are not taken into considerations.

To account for the shadow effects, we note that:

1) The integration processes to find the generators are not (directly) affected since they are more quadrates without integration limits.

2) What is affected and, indirectly, affects derivation of the generator is averaging process over the mean anomaly, performed to obtain the transformed Hamiltonian. To account for the shadow, let the time of exit from the shadow be where the mean anomaly is and let those corresponding to entrance into the shadow be and Then the averages are to be replaced by definite integrals between these 2 limits.

6. Secular Perturbations and Computation of Position and Velocity

After performing the long period transformation, the equation of motions are now reduced to

where are arbitrary constants

where the constants are be determined from the initial conditions.

Let be the values of the elements at a given initial epoch, then can be determined as follows:

1) From the elements of the inverse transformations we compute

2) Having determined and at time, we can compute the position and velocity by any known method.

7. Conclusion

Equation (32) reveals that, contrary to previous concept e.g. Kampos (1968)  , the direct solar radiation pressure produces secular effects at order 3 as long as the satellite is apart from the earth’s shadow. This emphasizes the importance of taking the effects of the solar radiation pressure into account in high order artificial satellite theories, particularly for those with high area-to-mass ratio flying at high altitudes.

Again, Equation (41) is valid away from the resonant conditions, i.e. as long as, , while (40) provides another secular part of to be add to.

Acknowledgements

Cite this paper

Hadia HassanSelim, (2014) Analytical Third Order Solution for Coupling Effects of Earth Oblateness and Direct Solar Radiation Pressure on the Motion of Artificial Satellites. International Journal of Astronomy and Astrophysics,04,530-543. doi: 10.4236/ijaa.2014.43049

References

1. 1. Kamel, A.A. (1971) Lie Transformation and the Hamiltonian of Non-Hamiltonian Systems. Celestial Mechanics, 4, 397-405. http://link.springer.com/article/10.1007%2FBF01231400

2. 2. Giacaglia, G.E.O. (1972) Perturbation Methods in Non-Linear Systems. Springer-Verlag, New York. http://dx.doi.org/10.1007/978-1-4612-6400-2

3. 3. Musen, P.J. (1960) The Influence of the Solar Radiation Pressure on the Motion of an Artificial Satellite. Journal of Geophysical Research, 6, 1391-1396.
http://onlinelibrary.wiley.com/doi/10.1029/JZ065i005p01391/abstract

4. 4. Kozai, Y. (1961) Effects of Solar Radiation Pressure on the Motion of an Artificial Satellite. Smithsonian Astrophys. Obs. Spec. Re, 56, 25-33.

5. 5. Brouwer, D. (1962) Dynamics of Satellites (Roy, M., Ed.). Springer, Berlin.

6. 6. Hori, G. (1966) Theory of General Perturbation with Unspecified Canonical Variable. Publications of the Astronomical Society of Japan, 18, 287. http://adsabs.harvard.edu/abs/1966PASJ...18..287H

7. 7. De Moraes, R.V. (1981) Combined Solar Radiation Pressure and Drag Effects on the Orbits of Artificial Satellites. Celestial Mechanics, 25, 281-292. http://link.springer.com/article/10.1007%2FBF01228965

8. 8. Kampos, B. (1986) Nasa CR1008-Guidance, Flight Mech. and Trajectory Optimization, Vol. IX.

9. 9. Sehnal, L. (1970) In Dynamics Satellites (Morando, Ed.). Springer, Berlin.

10. 10. Sehnal, L. (1975) In Satellite Dynamics (Giacalia, Ed.). Springer, Berlin.

11. 11. McInnes, C.R. and Browen, J.C. (1990) The Dynamics of Solar Sails with a Non-Point Source of Radiation Pressure Celestial Mechanics and Dynamical Astronomy, 49, 249-264.

12. 12. Feraz-Mello, S. (1972) Analytical Study of the Earth’s Shadowing Effects on Satellite Orbits. Celestial Mechanics, 5, 80-101. http://link.springer.com/article/10.1007%2FBF01227825

13. 13. Anselono, L., Bertotti, B., Farinella, P., Milani, A. and Mobili, A.M. (1983) Orbital Perturbation Due to Radiation Pressure for a Spacecraft of Complex Shape. Celestial Mechanics, 29, 27-43.

14. 14. Geyling, F.T. and Westerman, H.R. (1971) Introduction to Orbital Mech. Addison Wesley.

15. 15. Lála, P. (1972) Combined Gravitational and Solar Radiation Pressure Effects on The Semimajor Axis of the Earth’s Satellite. Bulletin of the Astronomical Institute of Czechoslovakia, 23, 342.