Solutions Manual for Interplanetary Astrodynamics, 1e by David
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Interplanetary Astrodynamics
Chapter 2 Problem Solutions
For all numerical problems, use 𝜇 = 398, 600 km3 /s2 as the gravitational parameter of the Earth.
Problem 1
Starting with the unperturbed two-body equations of motion, Equation (2.9), derive its state space
form in spherical coordinates.
Solution
Consider the Cartesian (𝑥, 𝑦, and 𝑧) formulation of the equations of motion for the two-body
problem:
𝜇𝑥
𝑥̈ = −
𝑟3
𝜇𝑦
𝑦̈ = − 3
𝑟
𝜇𝑧
𝑧̈ = − 3
𝑟
In order to convert between Cartesian and spherical coordinates, we use the following relationships
𝑥 = 𝜌 sin 𝜙 cos 𝜃
𝑦 = 𝜌 sin 𝜙 sin 𝜃
𝑧 = 𝜌 cos 𝜙
where 𝜌, 𝜙, and 𝜃 are the spherical coordinates.
Taking one time-derivative of the above equations for the 𝑥, 𝑦, and 𝑧 coordinates expressed in
terms of 𝜌, 𝜙, and 𝜃 gives
𝑥̇ = 𝜌̇ cos 𝜃 sin 𝜙 + 𝜌𝜙̇ cos 𝜙 cos 𝜃 − 𝜌𝜃̇ sin 𝜙 sin 𝜃
𝑦̇ = 𝜌̇ sin 𝜙 sin 𝜃 + 𝜌𝜙̇ cos 𝜙 sin 𝜃 + 𝜌𝜃̇ cos 𝜃 sin 𝜃
𝑧̇ = 𝜌̇ cos 𝜙 − 𝜌𝜙̇ sin 𝜙
1
Solutions Manual for
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Manual Astrodynamics,
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Astrodynamics,
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Taking another time-derivative:
𝑥̈ = 𝜌̈ cos 𝜃 sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜃 sin 𝜙 − 𝜃̇ 2 cos 𝜃 sin 𝜙 + 𝜌𝜙̈ cos 𝜙 cos 𝜃+
̈ sin 𝜙 sin 𝜃 + 2𝜌̇ 𝜙̇ cos 𝜙 cos 𝜃 − 2𝜌̇ 𝜃̇ sin 𝜙 sin 𝜃 − 2𝜌𝜙̇ 𝜃̇ cos 𝜙 sin 𝜃
− 𝜃𝜌
𝑦̈ = 𝜌̈ sin 𝜙 sin 𝜃 − 𝜌𝜙̇ 2 sin 𝜙 sin 𝜃 − 𝜌𝜃̇ 2 sin 𝜙 sin 𝜃 + 𝜌𝜙̈ cos 𝜙 sin 𝜃+
+ 𝜌𝜃̈ cos 𝜃 sin 𝜙 + 2𝜌̇ 𝜙̇ cos 𝜙 sin 𝜃 + 2𝜌̇ 𝜃̇ cos 𝜃 sin 𝜙 + 2𝜌𝜃̇ 𝜙̇ cos 𝜙 cos 𝜃
𝑧̈ = 𝜌̈ cos 𝜙 − 2𝜌̇ 𝜙̇ sin 𝜙 − 𝜌𝜙̈ sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜙
Equating each 𝑥, 𝑦, and 𝑧 acceleration expressed in spherical coordinates with its respective
acceleration terms gives us the equations of motion for the two-body problem in terms of spherical
coordinates 𝜌, 𝜙, and 𝜃
𝜌̈ cos 𝜃 sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜃 sin 𝜙 − 𝜃̇ 2 cos 𝜃 sin 𝜙 + 𝜌𝜙̈ cos 𝜙 cos 𝜃+
̈ sin 𝜙 sin 𝜃 + 2𝜌̇ 𝜙̇ cos 𝜙 cos 𝜃 − 2𝜌̇ 𝜃̇ sin 𝜙 sin 𝜃 − 2𝜌𝜙̇ 𝜃̇ cos 𝜙 sin 𝜃+
− 𝜃𝜌
𝜇 sin 𝜙 cos 𝜃
+ =0
𝜌2
𝜌̈ sin 𝜙 sin 𝜃 − 𝜌𝜙̇ 2 sin 𝜙 sin 𝜃 − 𝜌𝜃̇ 2 sin 𝜙 sin 𝜃 + 𝜌𝜙̈ cos 𝜙 sin 𝜃+
+ 𝜌𝜃̈ cos 𝜃 sin 𝜙 + 2𝜌̇ 𝜙̇ cos 𝜙 sin 𝜃 + 2𝜌̇ 𝜃̇ cos 𝜃 sin 𝜙 + 2𝜌𝜃̇ 𝜙̇ cos 𝜙 cos 𝜃
𝜇 sin 𝜙 sin 𝜃
+ =0
𝜌2
𝜇 cos 𝜙
𝜌̈ cos 𝜙 − 2𝜌̇ 𝜙̇ sin 𝜙 − 𝜌𝜙̈ sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜙 + =0
√
𝜌2
where we used the fact that 𝜌 = 𝑟 = 𝑥 2 + 𝑦 2 + 𝑧 2 .
2
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Problem 2
Prove that for the unperturbed two-body problem, orbital energy is constant.
Solution
𝑣2 𝜇
Start with the vis-viva equation, Equation (2.50): 𝐸 = 2
− 𝑟
To prove that energy is constant, we need to take its time derivative and show that it is equal to
zero:
= ( ) 𝑑𝑡 (𝐫 ⋅ 𝐫)1/2 ]
[
𝑑𝐸 𝑑 𝐯⋅𝐯 𝑑 𝜇
−
𝑑𝑡 𝑑𝑡 2
( ) [ 2 )
𝐯̇ ⋅ 𝐯 + 𝐯 ⋅ 𝐯̇ 1
= − 𝜇 − 𝐫−3 (2𝐫 ⋅ 𝐫)
̇
2
−𝜇𝐫
Recall that 𝐯̇ = 𝐫̈ = 𝑟3
and 𝐫̇ = 𝐯, so
=𝐯⋅( 3 )+ 3 ⋅𝐯
𝑑𝐸 −𝜇𝐫 𝜇𝐫
𝑑𝑡 𝑟 𝑟
= −𝐯 ⋅ (
𝑟3 )
𝜇𝐫 𝜇𝐫
+ 𝐯 ⋅ =0
𝑟3
𝑑𝐸
Thus, 𝑑𝑡
= 0 which means that orbital energy is constant.
3
Solutions Manual for
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Interplanetary
Manual Astrodynamics,
for Interplanetary
Solutions Manual
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Astrodynamics,
David
for Interplanetary
Spencer,
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by David
Astrodynamics,
Conte
Spencer,
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David
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Problem 3
Prove that the angular momentum vector and eccentricity vector are orthogonal to each other.
Solution
In order to prove that two vectors are orthogonal, or perpendicular, to each other, one must show
that their dot product is zero.
Starting with the definitions of eccentricity, Equation (2.27),
𝐯×𝐡 𝐫
𝐞= −
𝜇 𝑟
and angular momentum, Equation (2.41),
𝐡=𝐫×𝐯
we take the dot product between angular momentum and eccentricity,
( 𝜇 𝑟)
𝐯×𝐡 𝐫
𝐡⋅𝐞=𝐡⋅ −
1 1
= 𝐡 ⋅ (𝐯 × 𝐡) − (𝐫 × 𝐯) ⋅ 𝐫
𝜇 𝑟
where we used the definition of angular momentum for the second term. We then use the scalar
triple product on the above equation, which, for three generic vectors 𝐀, 𝐁, and 𝐂 is
𝐀 ⋅ (𝐁 × 𝐂) = 𝐁 ⋅ (𝐂 × 𝐀) = 𝐂 ⋅ (𝐀 × 𝐁)
This helps us simplify the first term as
1 1 1
𝐡 ⋅ (𝐯 × 𝐡) = 𝐯 ⋅ (𝐡 × 𝐡) = 𝐯 ⋅ 𝟎 = 0
𝜇 𝜇 𝜇
and the second term as
1 1 1
− 𝐫 ⋅ (𝐯 × 𝐫) = − 𝐯 ⋅ (𝐫 × 𝐫) = − 𝐯 ⋅ 𝟎 = 0
𝑟 𝑟 𝑟
which proves that 𝐡 ⋅ 𝐞 = 0 and thus 𝐡 ⟂ 𝐞 = 0.
4
Solutions Manual for
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Interplanetary
Manual Astrodynamics,
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Astrodynamics,
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for Interplanetary
Spencer,
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by David
Astrodynamics,
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Spencer, Davide Conte (Selective Chapters, 2-6)
Interplanetary Astrodynamics
Chapter 2 Problem Solutions
For all numerical problems, use 𝜇 = 398, 600 km3 /s2 as the gravitational parameter of the Earth.
Problem 1
Starting with the unperturbed two-body equations of motion, Equation (2.9), derive its state space
form in spherical coordinates.
Solution
Consider the Cartesian (𝑥, 𝑦, and 𝑧) formulation of the equations of motion for the two-body
problem:
𝜇𝑥
𝑥̈ = −
𝑟3
𝜇𝑦
𝑦̈ = − 3
𝑟
𝜇𝑧
𝑧̈ = − 3
𝑟
In order to convert between Cartesian and spherical coordinates, we use the following relationships
𝑥 = 𝜌 sin 𝜙 cos 𝜃
𝑦 = 𝜌 sin 𝜙 sin 𝜃
𝑧 = 𝜌 cos 𝜙
where 𝜌, 𝜙, and 𝜃 are the spherical coordinates.
Taking one time-derivative of the above equations for the 𝑥, 𝑦, and 𝑧 coordinates expressed in
terms of 𝜌, 𝜙, and 𝜃 gives
𝑥̇ = 𝜌̇ cos 𝜃 sin 𝜙 + 𝜌𝜙̇ cos 𝜙 cos 𝜃 − 𝜌𝜃̇ sin 𝜙 sin 𝜃
𝑦̇ = 𝜌̇ sin 𝜙 sin 𝜃 + 𝜌𝜙̇ cos 𝜙 sin 𝜃 + 𝜌𝜃̇ cos 𝜃 sin 𝜃
𝑧̇ = 𝜌̇ cos 𝜙 − 𝜌𝜙̇ sin 𝜙
1
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Interplanetary
Manual Astrodynamics,
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Spencer,
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Taking another time-derivative:
𝑥̈ = 𝜌̈ cos 𝜃 sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜃 sin 𝜙 − 𝜃̇ 2 cos 𝜃 sin 𝜙 + 𝜌𝜙̈ cos 𝜙 cos 𝜃+
̈ sin 𝜙 sin 𝜃 + 2𝜌̇ 𝜙̇ cos 𝜙 cos 𝜃 − 2𝜌̇ 𝜃̇ sin 𝜙 sin 𝜃 − 2𝜌𝜙̇ 𝜃̇ cos 𝜙 sin 𝜃
− 𝜃𝜌
𝑦̈ = 𝜌̈ sin 𝜙 sin 𝜃 − 𝜌𝜙̇ 2 sin 𝜙 sin 𝜃 − 𝜌𝜃̇ 2 sin 𝜙 sin 𝜃 + 𝜌𝜙̈ cos 𝜙 sin 𝜃+
+ 𝜌𝜃̈ cos 𝜃 sin 𝜙 + 2𝜌̇ 𝜙̇ cos 𝜙 sin 𝜃 + 2𝜌̇ 𝜃̇ cos 𝜃 sin 𝜙 + 2𝜌𝜃̇ 𝜙̇ cos 𝜙 cos 𝜃
𝑧̈ = 𝜌̈ cos 𝜙 − 2𝜌̇ 𝜙̇ sin 𝜙 − 𝜌𝜙̈ sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜙
Equating each 𝑥, 𝑦, and 𝑧 acceleration expressed in spherical coordinates with its respective
acceleration terms gives us the equations of motion for the two-body problem in terms of spherical
coordinates 𝜌, 𝜙, and 𝜃
𝜌̈ cos 𝜃 sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜃 sin 𝜙 − 𝜃̇ 2 cos 𝜃 sin 𝜙 + 𝜌𝜙̈ cos 𝜙 cos 𝜃+
̈ sin 𝜙 sin 𝜃 + 2𝜌̇ 𝜙̇ cos 𝜙 cos 𝜃 − 2𝜌̇ 𝜃̇ sin 𝜙 sin 𝜃 − 2𝜌𝜙̇ 𝜃̇ cos 𝜙 sin 𝜃+
− 𝜃𝜌
𝜇 sin 𝜙 cos 𝜃
+ =0
𝜌2
𝜌̈ sin 𝜙 sin 𝜃 − 𝜌𝜙̇ 2 sin 𝜙 sin 𝜃 − 𝜌𝜃̇ 2 sin 𝜙 sin 𝜃 + 𝜌𝜙̈ cos 𝜙 sin 𝜃+
+ 𝜌𝜃̈ cos 𝜃 sin 𝜙 + 2𝜌̇ 𝜙̇ cos 𝜙 sin 𝜃 + 2𝜌̇ 𝜃̇ cos 𝜃 sin 𝜙 + 2𝜌𝜃̇ 𝜙̇ cos 𝜙 cos 𝜃
𝜇 sin 𝜙 sin 𝜃
+ =0
𝜌2
𝜇 cos 𝜙
𝜌̈ cos 𝜙 − 2𝜌̇ 𝜙̇ sin 𝜙 − 𝜌𝜙̈ sin 𝜙 − 𝜌𝜙̇ 2 cos 𝜙 + =0
√
𝜌2
where we used the fact that 𝜌 = 𝑟 = 𝑥 2 + 𝑦 2 + 𝑧 2 .
2
Solutions Manual for
Solutions
Interplanetary
Manual Astrodynamics,
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Solutions Manual
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Astrodynamics,
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for Interplanetary
Spencer,
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Astrodynamics,
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Problem 2
Prove that for the unperturbed two-body problem, orbital energy is constant.
Solution
𝑣2 𝜇
Start with the vis-viva equation, Equation (2.50): 𝐸 = 2
− 𝑟
To prove that energy is constant, we need to take its time derivative and show that it is equal to
zero:
= ( ) 𝑑𝑡 (𝐫 ⋅ 𝐫)1/2 ]
[
𝑑𝐸 𝑑 𝐯⋅𝐯 𝑑 𝜇
−
𝑑𝑡 𝑑𝑡 2
( ) [ 2 )
𝐯̇ ⋅ 𝐯 + 𝐯 ⋅ 𝐯̇ 1
= − 𝜇 − 𝐫−3 (2𝐫 ⋅ 𝐫)
̇
2
−𝜇𝐫
Recall that 𝐯̇ = 𝐫̈ = 𝑟3
and 𝐫̇ = 𝐯, so
=𝐯⋅( 3 )+ 3 ⋅𝐯
𝑑𝐸 −𝜇𝐫 𝜇𝐫
𝑑𝑡 𝑟 𝑟
= −𝐯 ⋅ (
𝑟3 )
𝜇𝐫 𝜇𝐫
+ 𝐯 ⋅ =0
𝑟3
𝑑𝐸
Thus, 𝑑𝑡
= 0 which means that orbital energy is constant.
3
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Manual Astrodynamics,
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for Interplanetary
Spencer,
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Astrodynamics,
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Problem 3
Prove that the angular momentum vector and eccentricity vector are orthogonal to each other.
Solution
In order to prove that two vectors are orthogonal, or perpendicular, to each other, one must show
that their dot product is zero.
Starting with the definitions of eccentricity, Equation (2.27),
𝐯×𝐡 𝐫
𝐞= −
𝜇 𝑟
and angular momentum, Equation (2.41),
𝐡=𝐫×𝐯
we take the dot product between angular momentum and eccentricity,
( 𝜇 𝑟)
𝐯×𝐡 𝐫
𝐡⋅𝐞=𝐡⋅ −
1 1
= 𝐡 ⋅ (𝐯 × 𝐡) − (𝐫 × 𝐯) ⋅ 𝐫
𝜇 𝑟
where we used the definition of angular momentum for the second term. We then use the scalar
triple product on the above equation, which, for three generic vectors 𝐀, 𝐁, and 𝐂 is
𝐀 ⋅ (𝐁 × 𝐂) = 𝐁 ⋅ (𝐂 × 𝐀) = 𝐂 ⋅ (𝐀 × 𝐁)
This helps us simplify the first term as
1 1 1
𝐡 ⋅ (𝐯 × 𝐡) = 𝐯 ⋅ (𝐡 × 𝐡) = 𝐯 ⋅ 𝟎 = 0
𝜇 𝜇 𝜇
and the second term as
1 1 1
− 𝐫 ⋅ (𝐯 × 𝐫) = − 𝐯 ⋅ (𝐫 × 𝐫) = − 𝐯 ⋅ 𝟎 = 0
𝑟 𝑟 𝑟
which proves that 𝐡 ⋅ 𝐞 = 0 and thus 𝐡 ⟂ 𝐞 = 0.
4
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Manual Astrodynamics,
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Conte Spencer,
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2-6) Davide
Chapters,
Conte
2-6).pdf
(Selective Chapters, 2-6)
