Another important factor is the density of a propellant. A given weight of dense propellant can be carried in a smaller, lighter tank than the same weight of a low-density propellant. Liquid hydrogen, for example, is energetic and its combustion gases are light. However, it is a very bulky substance, requiring large tanks. The dead weight of these tanks partly offsets the high specific impulse of the hydrogen propellant. Other criteria must also be considered in choosing propellants.
http://www.history.nasa.gov/conghand/propelnt.htm
Combustion of Solid Propellants Small thermocouples imbedded in the burning sample allow to measure the temperature profile, Fig. 34, the surface temperature, in the vicinity of 800 K, Fig. 36, and from the heat balance at the surface an evaluation of the heat evolved in the condensed phase is obtained, Fig.
http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA425264
1 The oxidizer and metallic fuel are then added in the form of small particles which are a few to a couple of hundred microns in diameter. 2  After mixing with the liquid organic fuel, the mixture is cured to allow the binder to solidify. 3  Composite/double base: Combinations of composite and double-base propellants.
http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
Its mass density is about 1750 kg/m 3. The molar mass of the combustion gases is about 34,75 gram/mol and the combustion temperature is about 2600 K. Regression rate is about 9 mm/s @ 1 MPa and increases with 9 mm/s/MPa. A disadvantage of black powder is that it produces over half its weight of solid residue.
http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
Another substance mentioned for use as a propellant in the nuclear rocket is ammonia. While offering only about one-half the specific impulse of hydrogen for the same reactor temperature as a consequence of its greater molecular weight, it is a liquid at reasonable temperatures and is easily handled.
http://www.history.nasa.gov/conghand/propelnt.htm
The choice of fuel-binder does not normally have a strong influence upon the specific impulse of the propellant. It is much more associated with propellant processing. Ordinary composite propellants burn relative clean with not much solid matter in the combustion products.
http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
The sensitivity of the motor operation to temperature depends upon the propellant burning rate sensitivity to both the temperature and the pressure. As can be seen on Fig. 2, the pressure exponent, in the usual empirical law v b ~ p n, is around 0.7 and increases to nearly 1 at high pressure. Super-rate effects (Fig.
http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA425264
Solid rocket propellants and their properties. A solid propellant is characterized by that the fuel and oxidizer are stored in a condensed, solid state of matter. We distinguish: 1  Black powder or gun powder is a low explosive, composed essentially of a mixture of potassium nitrate or sodium nitrate, charcoal, and sulfur.
http://www.lr.tudelft.nl/en/organisation/departments/space-engineering/space-systems-engineering/expertise-areas/space-propulsion/design-of-elements/rocket-propellants/solids/
Occasionally a separate propellant is used to operate the gas generator which supplies the gas to drive the turbopumps of liquid rockets. In the V-2, for example, hydrogen peroxide was decomposed to supply the hot gas for the main turbopumps, although the main rocket propellants were alcohol and liquid oxygen.
http://www.history.nasa.gov/conghand/propelnt.htm
A list showing solid-and liquid-propellant performance is given in table 1. TABLE 1.-Specific impulse of some typical chemical propellants 1. Liquid oxygen is the standard oxidizer used in the largest United States rocket engines.
http://www.history.nasa.gov/conghand/propelnt.htm
how do propellant work in temperature
The sensitivity of the motor operation to temperature depends upon the propellant burning rate sensitivity to both the temperature and the pressure.