Chapter 16 WEAPON PROPULSION AND ARCHITECTURE. Objectives 1. Know the different types of propulsion systems. 2. Understand the factors that control propellant burning rate. 3. Understand the definitions of the following terms: degressive, neutral, and progressive burning. 4. 5. 6. 7. 8. 9. Introduction Every weapon requires some type of propulsion to deliver its warhead to the intended target. The power required to propel a warhead to its target is obtained through the controlled release of stored energy. . (1) a chemical reaction (2) a compression of gases or liquids (3) the effect of gravity By method of launch, weapon propulsion systems are normally classified as: (1) impulse-propulsion or gun-type--a projectile (2) reaction--a missile or torpedo (3) gravity--a bomb Impulse propulsion systems include all weapons systems in which a projectile is ejected from a container (usually a long tube) by means of an initial impulse.
The expulsion of a projectile at the high velocities demanded by modern warfare requires tremendous forces. To o where. Aerospaceweb.org | Reference for Aviation, Space, Design, and En. Ask Us - Reducing Landing Distance. Reducing Landing Distance I've been wondering about thrust reversers, how many kinds are there and which are the most effective? - question from Shane Velazquez I am having a debate as to whether airplane engines reverse, or does something else happen when we land? - question from qfiles Is there any possibility to reverse the direction of an aircraft with the help of thrust reversing?
- question from Sandeep As discussed in a previous question, thrust reversing is a process used to help reduce the distance a plane travels during landing. As an aircraft touches down on a runway, it has a certain amount of kinetic energy that gives it forward momentum. This energy is proportional to the weight of the aircraft and the square of its speed. Stopping an aircraft during the early days of aviation was not all that difficult. Wheel brakes used on a typical light airplane Speed brake on the Su-27 Other devices serve multiple purposes depending on how they are used during the course of a flight. Rocket Propulsion - Supplement #1. Rocket Nozzle Design: Optimizing Expansion for Maximum Thrust A rocket engine is a device in which propellants are burned in a combustion chamber and the resulting high pressure gases are expanded through a specially shaped nozzle to produce thrust.
The function of the nozzle is to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the slow moving, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Gas velocities from 2 to 4.5 kilometers per second can be obtained in rocket nozzles. The nozzles which perform this feat are called DeLaval nozzles (after the inventor) and consist of a convergent and divergent section. The minimum flow area between the convergent and divergent section is called the nozzle throat. Hot exhaust gases expand in the diverging section of the nozzle. Let us now consider an example. The area at the nozzle throat is given by By Robert A. F-16.net - The ultimate F-16, F-22, F-35 reference.
Basics of Space Flight: Rocket Propulsion. Isaac Newton stated in his third law of motion that "for every action there is an equal and opposite reaction. " It is upon this principle that a rocket operates. Propellants are combined in a combustion chamber where they chemically react to form hot gases which are then accelerated and ejected at high velocity through a nozzle, thereby imparting momentum to the engine. The thrust force of a rocket motor is the reaction experienced by the motor structure due to ejection of the high velocity matter. This is the same phenomenon which pushes a garden hose backward as water flows from the nozzle, or makes a gun recoil when fired. Thrust Thrust is the force that propels a rocket or spacecraft and is measured in pounds, kilograms or Newtons. Figure 1.1 shows a combustion chamber with an opening, the nozzle, through which gas can escape.
Where q is the rate of the ejected mass flow, Pa the pressure of the ambient atmosphere, Pe the pressure of the exhaust gases and Ve their ejection speed. V. t.