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A reaction engine is an engine which provides propulsion by expelling reaction mass, in accordance with Newton's third law of motion. This law of motion is most commonly paraphrased as: "For every action force there is an equal, but opposite, reaction force".## Thrust

## Energy use

### Propulsive efficiency

For all reaction engines which carry their propellant onboard prior to use (such as rocket engines and electric propulsion drives) some energy must go into accelerating the reaction mass.
Every engine will waste some energy, but even assuming 100% efficiency, the engine will need energy amounting to### Cycle efficiency

All reaction engines lose some energy- mostly as heat.## Types of reaction engines

## See also

Examples include both jet engines and rocket engines, and more uncommon variations such as Hall effect thrusters, ion drives and mass drivers.

The force generated by a reaction engine is in accordance with Newton's second law:

- $vec\; F\; =\; \{mathrm\{d\}(m\; vec\; v)\; over\; mathrm\{d\}t\}$

where:

- $vec\; F!$ is the net force vector

- $m!$ is mass

- $vec\; v!$ is the velocity vector

- $t!$ is time.

- $begin\{matrix\}\; frac\{1\}\{2\}\; end\{matrix\}\; MV\_e^2$

(where M is the mass of propellent expended and $V\_e$ is the exhaust velocity)

which is simply the energy to accelerate the exhaust.

Comparing the rocket equation (which shows how much energy ends up in the final vehicle) and the above equation (which shows the total energy required) shows that even with 100% engine efficiency, certainly not all energy supplied ends up in the vehicle - some of it, indeed usually most of it, ends up as kinetic energy of the exhaust.

Interestingly, if the $I\_\{sp\}$ is fixed, for a mission delta-v, there is a particular $I\_\{sp\}$ that minimises the overall energy used by the rocket. This comes to an exhaust velocity of about ⅔ of the mission delta-v (see the energy computed from the rocket equation). Drives with a specific impulse that is both high and fixed such as Ion thrusters have exhaust velocities that can be enormously higher than this ideal, and thus end up powersource limited and give very low thrust. Where the vehicle performance is power limited, e.g. if solar power or nuclear power is used, then in the case of a large $v\_\{e\}$ the maximum acceleration is inversely proportional to it. Hence the time to reach a required delta-v is proportional to $v\_\{e\}$. Thus the latter should not be too large.

On the other hand if the exhaust velocity can be made to vary so that at each instant it is equal and opposite to the vehicle velocity then the absolute minimum energy usage is achieved. When this is achieved, the exhaust stops in space and has no kinetic energy; and the propulsive efficiency is 100% all the energy ends up in the vehicle (in principle such a drive would be 100% efficient, in practice there would be thermal losses from within the drive system and residual heat in the exhaust). However in most cases this uses an impractical quantity of propellant, but is a useful theoretical consideration.

Some drives (such as VASIMR or Electrodeless plasma thruster ) actually can significantly vary their exhaust velocity. This can help reduce propellant usage and improve acceleration at different stages of the flight. However the best energetic performance and acceleration is still obtained when the exhaust velocity is close to the vehicle speed. Proposed ion and plasma drives usually have exhaust velocities enormously higher than that ideal (in the case of VASIMR the lowest quoted speed is around 15000 m/s compared to a mission delta-v from high Earth orbit to Mars of about 4000m/s).

For a mission, for example, when launching from or landing on a planet, the effects of gravitational attraction and any atmospheric drag must be overcome by using fuel. It is typical to combine the effects of these and other effects into an effective mission delta-v. For example a launch mission to low Earth orbit requires about 9.3-10 km/s delta-v. These mission delta-vs are typically numerically integrated on a computer.

Different reaction engines have different efficiencies and losses. For example rocket engines can be up to 60-70% energy efficient in terms of accelerating the propellant- the rest is lost as heat primarily in the exhaust, but also a small amount lost as thermal radiation.

- Rocket-like
- Airbreathing
- solid exhaust

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Last updated on Monday July 21, 2008 at 11:53:29 PDT (GMT -0700)

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This article is licensed under the GNU Free Documentation License.

Last updated on Monday July 21, 2008 at 11:53:29 PDT (GMT -0700)

View this article at Wikipedia.org - Edit this article at Wikipedia.org - Donate to the Wikimedia Foundation

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