Ion Thruster Question from Year 12

In summary, an ion thruster is used to change the speed of a satellite by emitting charged particles, specifically positive xenon ions. These ions have a mass of 2.2x10^(-25) kg and a charge of 1.6x10^(-19) C. The potential difference between grid A and grid B in the ion thruster increases the speed of an ion by 44 km/s. To calculate this potential difference, conservation of energy can be used, assuming the ion starts at rest and must be accelerated to a speed of 44 km/s. The change in electrical potential energy of the ion can be compared to its kinetic energy at the exit to determine the potential difference between the grids.
  • #1
physicist101
4
0

Homework Statement


An ion thruster may be used to change the speed of a satellite, through the emmisions of charged particles. Positive xenons ions are accelerated by the potential difference(deltaV) in the region between grid A and grid B as they move towards the right of the diagram.

Xenon ions have a mass of 2.2x10^(-25) kg and a charge of 1.6x10^(-19) C

The potential diffrence in the ion thruster in the region between grid A and grid B increases the speed of an ion by 44 km^(-1)

Calculate the potential difference between Grid A and grid B. (assume that the ions enters the region between the grids with neglible speeds).

Homework Equations



we don't know!

The Attempt at a Solution



sure... with no equations? HELP!
 
Physics news on Phys.org
  • #2
to the eight ppl who looked at it...yes we would like an answer
 
  • #3
How about using conservation of energy. Assume a Xe ion starts at rest, and must be accelerated to a speed of 44 km/s. What is the kinetic energy of the ion at the exit? What is the change in electrical potential energy of the ion?
 
  • #4
thanks astronuc, helped a heap.
 
  • #5


I understand your frustration with being asked to solve a problem without any given equations. However, in this case, we can use some basic physics principles to determine the potential difference between grid A and grid B.

First, we need to understand the concept of potential difference. It is a measure of the work done per unit charge to move a charge from one point to another in an electric field. In this case, the potential difference is responsible for accelerating the xenon ions.

We also know that the kinetic energy of an object is equal to 1/2 times its mass times its velocity squared (KE = 1/2 mv^2). Since we are given the mass of the xenon ions and the increase in their speed (44 km^(-1)), we can calculate the change in their kinetic energy.

KE = 1/2 * 2.2x10^(-25) kg * (44 km^(-1))^2 = 4.2848x10^(-21) J

We can also use the equation for electric potential energy (PE = q*deltaV) to calculate the potential difference between grid A and grid B.

PE = 1.6x10^(-19) C * deltaV

Setting the two equations equal to each other, we can solve for the potential difference.

1.6x10^(-19) C * deltaV = 4.2848x10^(-21) J

deltaV = 4.2848x10^(-21) J / 1.6x10^(-19) C = 0.0268 volts

Therefore, the potential difference between grid A and grid B is 0.0268 volts. I hope this helps in your understanding of ion thrusters and potential difference.
 

1. What is an ion thruster?

An ion thruster is a type of spacecraft propulsion system that uses electric fields to accelerate ions (charged particles) to high speeds, creating thrust. It is commonly used in deep space missions and can provide continuous thrust for extended periods of time.

2. How does an ion thruster work?

An ion thruster works by using an electric field to accelerate ions out of the back of the spacecraft, creating thrust in the opposite direction. The ions are generated by a source, such as xenon gas, and then are ionized (given an electric charge) and accelerated by electrodes. This process creates a continuous stream of ions that provides thrust for the spacecraft.

3. What are the advantages of using an ion thruster?

One of the main advantages of using an ion thruster is its high specific impulse, which means it can provide a lot of thrust with a small amount of propellant. This makes it ideal for long-duration space missions. Additionally, ion thrusters are very efficient and can operate for extended periods of time, making them a cost-effective option for deep space exploration.

4. What are the limitations of ion thrusters?

One of the main limitations of ion thrusters is their low thrust compared to traditional chemical rockets. This means that they are not suitable for launching a spacecraft into orbit, but are better suited for in-space propulsion. Additionally, ion thrusters require a power source, such as solar panels, which can limit their use in certain environments.

5. What is the current state of ion thruster technology?

Ion thruster technology has been in use since the 1960s, and has continued to advance with new developments and improvements. Currently, ion thrusters are used in deep space missions, such as NASA's Dawn spacecraft, and are being researched for potential use in Earth-orbiting satellites and interplanetary travel. However, further advancements are needed to make ion thrusters a more widely used form of propulsion in space exploration.

Similar threads

  • Introductory Physics Homework Help
Replies
6
Views
171
  • Introductory Physics Homework Help
Replies
13
Views
2K
  • Introductory Physics Homework Help
Replies
1
Views
1K
  • Introductory Physics Homework Help
Replies
8
Views
2K
  • Introductory Physics Homework Help
Replies
3
Views
1K
  • Introductory Physics Homework Help
Replies
29
Views
3K
  • Introductory Physics Homework Help
Replies
8
Views
1K
  • Introductory Physics Homework Help
Replies
4
Views
4K
  • Introductory Physics Homework Help
2
Replies
46
Views
3K
  • Introductory Physics Homework Help
Replies
7
Views
6K
Back
Top