So I'm looking at the following problem;

Arrow type configuration in orbit. Each end of the arrow has a mass and a cross sectional area (we can assume the head and tail are connected by a negligibly thin beam). The arrow start facing directly away from the Earth (Zenith), but it has normal orbital properties (speed = ~7.7km/s). Drag in orbit is considered not negligible.

 

Does the arrow align it's self with the velocity vector? My intuition is that it does, but I've tried to do some calculations on this and I get the arrow swinging back and forth from Zenith to Nadir, with increasing angles (I expected the angles to slowly decrease).

Any advice on what I'm doing wrong here would be great.

My method in detail;

1. Calculate the drag area of the tail (this is reduced if the head is in front of the tail, but the head can never completely cover the tail).
2. Calculate the drag area of the head (the tail never goes in front of the head from my starting configuration, but since the angle changes the wetted area of the head changes)
3. Calculate the linear speed of the head and tail based on the current rate of rotation about the CoM.
4. Calculate the drag on both head and tail (velocity = orbital velocity +/- linear speed based on rate of rotation) This is done using D = 0.5pV^2CdA
5. Calculate the resultant moment about the CoM. M = F*r, Since the two forces will always be in opposition one moment - the other
6. Calculate the induced angular acceleration from a = M/I (moment/moment of inertia)
7. Calculate the angular velocity from V = U + at
8. Calculate the Angle from S = Ut + 0.5at^2

I do all this with a time step model on excel. Unfortunately this gives me increases maximum angle of rotation (it swings back further than it originated). Any advice/comments welcome.

So I'm looking at the following problem;

Arrow type configuration in orbit. Each end of the arrow has a mass and a cross sectional area (we can assume the head and tail are connected by a negligibly thin beam). The arrow start facing directly away from the Earth (Zenith), but it has normal orbital properties (speed = ~7.7km/s). Drag in orbit is considered not negligible.

Does the arrow align it's self with the velocity vector? My intuition is that it does, but I've tried to do some calculations on this and I get the arrow swinging back and forth from Zenith to Nadir, with increasing angles (I expected the angles to slowly decrease).

Any advice on what I'm doing wrong here would be great.

My method in detail;

1. Calculate the drag area of the tail (this is reduced if the head is in front of the tail, but the head can never completely cover the tail).
2. Calculate the drag area of the head (the tail never goes in front of the head from my starting configuration, but since the angle changes the wetted area of the head changes)
3. Calculate the linear speed of the head and tail based on the current rate of rotation about the CoM.
4. Calculate the drag on both head and tail (velocity = orbital velocity +/- linear speed based on rate of rotation) This is done using D = 0.5pV^2CdA
5. Calculate the resultant moment about the CoM. M = F*r, Since the two forces will always be in opposition one moment - the other
6. Calculate the induced angular acceleration from a = M/I (moment/moment of inertia)
7. Calculate the angular velocity from V = U + at
8. Calculate the Angle from S = Ut + 0.5at^2

I do all this with a time step model on excel. Unfortunately this gives me increases maximum angle of rotation (it swings back further than it originated). Any advice/comments welcome.

So I'm looking at the following problem;

Arrow type configuration in orbit. Each end of the arrow has a mass and a cross sectional area (we can assume the head and tail are connected by a negligibly thin beam). The arrow start facing directly away from the Earth (Zenith), but it has normal orbital properties (speed = ~7.7km/s). Drag in orbit is considered not negligible.

Does the arrow align it's self with the velocity vector? My intuition is that it does, but I've tried to do some calculations on this and I get the arrow swinging back and forth from Zenith to Nadir, with increasing angles (I expected the angles to slowly decrease).

Any advice on what I'm doing wrong here would be great.

My method in detail;

1. Calculate the drag area of the tail (this is reduced if the head is in front of the tail, but the head can never completely cover the tail).
2. Calculate the drag area of the head (the tail never goes in front of the head from my starting configuration, but since the angle changes the wetted area of the head changes)
3. Calculate the linear speed of the head and tail based on the current rate of rotation about the CoM.
4. Calculate the drag on both head and tail (velocity = orbital velocity +/- linear speed based on rate of rotation) This is done using D = 0.5pV^2CdA
5. Calculate the resultant moment about the CoM. M = F*r, Since the two forces will always be in opposition one moment - the other
6. Calculate the induced angular acceleration from a = M/I (moment/moment of inertia)
7. Calculate the angular velocity from V = U + at
8. Calculate the Angle from S = Ut + 0.5at^2

I do all this with a time step model on excel. Unfortunately this gives me increases maximum angle of rotation (it swings back further than it originated). Any advice/comments welcome.

So I'm looking at the following problem;

Arrow type configuration in orbit. Each end of the arrow has a mass and a cross sectional area (we can assume the head and tail are connected by a negligibly thin beam). The arrow start facing directly away from the Earth (Zenith), but it has normal orbital properties (speed = ~7.7km/s). Drag in orbit is considered not negligible.

Does the arrow align it's self with the velocity vector? My intuition is that it does, but I've tried to do some calculations on this and I get the arrow swinging back and forth from Zenith to Nadir, with increasing angles (I expected the angles to slowly decrease).

Any advice on what I'm doing wrong here would be great.

My method in detail;

1. Calculate the drag area of the tail (this is reduced if the head is in front of the tail, but the head can never completely cover the tail).
2. Calculate the drag area of the head (the tail never goes in front of the head from my starting configuration, but since the angle changes the wetted area of the head changes)
3. Calculate the linear speed of the head and tail based on the current rate of rotation about the CoM.
4. Calculate the drag on both head and tail (velocity = orbital velocity +/- linear speed based on rate of rotation) This is done using D = 0.5pV^2CdA
5. Calculate the resultant moment about the CoM. M = F*r, Since the two forces will always be in opposition one moment - the other
6. Calculate the induced angular acceleration from a = M/I (moment/moment of inertia)
7. Calculate the angular velocity from V = U + at
8. Calculate the Angle from S = Ut + 0.5at^2

I do all this with a time step model on excel. Unfortunately this gives me increases maximum angle of rotation (it swings back further than it originated). Any advice/comments welcome.