Comprehend the different types of rockets Comprehend the propulsion and flight of rockets Comprehend the types of launch vehicles Comprehend the factors and features of a rocket launch How Rockets Work

The Basic Principles of Rocket Science Thrust - the power produced by a rocket engine Mass is matter that is shot out of the engine Thrust = mass of the gases shot out of the engine x those gases acceleration Acceleration is a change in motion

Impulse A rocket produces thrust that pushes on a vehicle. Then what happens? If you push on a door, it opens. If you hit a ball with a bat, it flies to the outfield. Force applied to an object over time produces an impulse.

Specific Impulse To compare the performance of different types of rockets, we need something new called specific impulse, one of the most useful terms in rocket science. Specific impulse tells us the cost, in terms of the propellant mass, needed to produce a given thrust on a rocket. In other words, specific impulse tells us "bang for the buck" for a given rocket. The higher the specific impulse in relationship to the rocket’s overall mass = the better in terms of overall rocket efficiency.

Chemical Rockets All combustion reactions must have two things: A fuel (such as hydrogen) An oxidizer (such as oxygen) These two combine, freeing a vast amount of heat and creating by-products that form the exhaust. The heat transfers to the combustion products, raising their temperatures. This chemical reaction and energy transfer take place in the combustion chamber. Newton’s Third Law Bernoulli’s Principle/Law

Thermodynamic Rockets Chemical—rely on chemical energy (from breaking down or decomposing fuels or combustion of propellants) to produce heat. Thermoelectric—use the heat produced from electrical resistance.

Types of Chemical Rockets Chemical rockets fall into one of three general categories: Liquid Bipropellant Monopropellant Solid Hybrid

Types of Chemical Rockets Chemical rockets fall into one of two general categories: Liquid Bipropellant : 2 propellants mix together (fuel & oxidizer) in combustion chamber. Monopropellant: use only one propellant that is relatively unstable and easily decomposes through contact with a suitable catalyst

Solid-chemical Rockets A solid rocket contains a mixture of fuel, oxidizer, and binder, blended correctly and solidified into a single package called a motor. Because combustion in solid-rocket motors depends on the exposed propellant’s surface area, manufacturers must carefully mold the propellant mixture to prevent cracks. Burning occurs on any exposed surface, even along undetected cracks in the propellant grain.

Hybrid Rockets Hybrid-propulsion systems combine aspects of liquid and solid systems. A typical hybrid rocket uses a liquid oxidizer and a solid fuel. The molded fuel grain forms the combustion chamber, into which we inject the oxidizer. This approach offers the flexibility of a liquid system with the simplicity and density of a solid motor. Hybrid Rocket Motor

Thermodynamic Rockets Chemical—rely on chemical energy (from breaking down or decomposing fuels or combustion of propellants) to produce heat. Thermoelectric—use the heat produced from electrical resistance.

An arcjet thruster works by passing a propellant through an electric arc. This rapidly increases its temperature before expanding it out a nozzle. Arcjet systems can achieve relatively high specific impulse (up to 1000 seconds) with small but significant thrust levels (up to 1 newton). Thermoelectric Rockets: Arcjet Argos spacecraft

Electrodynamic Rockets Although thermodynamic rockets offer relatively high thrust over a very wide range, basic heat-transfer problems limit their specific impulse (efficiency) To achieve the higher efficiencies demanded by future, more challenging interplanetary and commercial missions, we need to take a different approach - electrodynamic rockets. Two main types of electrodynamic rockets are in use: Ion thrusters use electric fields to accelerate ions. Plasma thrusters use electric and magnetic fields to accelerate a plasma.

Ion Engines An ion engine is the simplest electrodynamic rocket. A thruster ionizes a propellant by stripping off the outer shell of electrons, making positive ions. It then accelerates these ions by applying a strong electric field.

Plasma Thrusters The interaction of the magnetic field with the resulting electric field creates a force that accelerates the positive ions in the plasma.

Launch Vehicle: Propulsion A launch vehicle’s propulsion system presents unique challenges that sets it apart from the same subsystem on a spacecraft: Thrust-to-weight ratio—must be greater than 1.0 to get off the ground. Throttling and thrust-vector control—may need to vary the amount and direction of thrust to decrease launch loads and to steer. Nozzle design—nozzles face varying expansion conditions from the ground to space. Since engineers cannot ideally create an expanded nozzle at fits all altitudes, they typically design them for ideal expansion two-thirds of the way up.

Launch Vehicle: Structure and Mechanisms Finally, we must design the launch vehicle’s structures and mechanisms to withstand severe loads and do many mechanical tasks with split-second timing. Because most of a launch vehicle’s volume consists of propellant tanks, these tanks tend to dominate the overall structural design. Often, the tanks become part of the main load-bearing structure.

Electrical-power requirements for launch vehicles typically are modest compared to a spacecraft’s. Launch vehicles need only enough power to run the communication and data-handling subsystems, as well as sensors and actuators. Because of their limited lifetimes, expendable launch vehicles typically rely on relatively simple batteries for primary power during launch. Launch Vehicle: Electrical

Staging Getting a payload into orbit isn’t easy. For example, current chemical rocket designs can generally deliver a maximum specific impulse of about 470 seconds. Designers must create a launch vehicle that is mostly propellant to achieve the velocity change of more than 8 kilometers per second needed to get into orbit, as well as to meet the hard realities of the rocket equation. In fact, more than 80% of a typical launch vehicle’s lift-off mass is propellant. Large propellant tanks, which also add mass, contain this propellant. The larger the mass of propellant tanks and other subsystems, the less mass is available for payload.

Staging One way of reducing the vehicle’s mass on the way to orbit is to get rid of stuff that’s no longer needed. After all, why carry along all that extra tank mass when the rocket engines empty the tanks steadily during launch? Instead, why not split the propellant into smaller tanks and then drop them as they empty? Why not use staging?

Stages consist of propellant tanks, rocket engines, and other supporting subsystems that are discarded to lighten the launch vehicle on the way to orbit. As the propellant in each stage is used up, the stage drops off, and the engines of the next stage ignite A two-stage vehicle can deliver more than twice the payload to orbit as a similar-sized, single-staged vehicle with the same total propellant mass. Staging

Comprehend the different types of rockets Comprehend the propulsion and flight of rockets Comprehend the types of launch vehicles Comprehend the factors and features of a rocket launch How Rockets Work