The space shuttle used 2 Solid Propellant Boosters (SRBs, white) and a tank of LOX/LH2 (large orange tank)
Jet aircraft designed to fly in Earth's atmosphere carry just fuel, and rely on atmospheric O2, which is supplied in excess, to burn the fuel. Rockets designed for interplanetary flight need to supply both a fuel and an oxidant for their propulsion, and the ratio of the two has to be exactly right for maximum propulsion and minimum mass. If the wrong size tanks for fuel and oxidizer are designed, some portion of such a reactant will be left unchanged after the reaction. Conversely, at least one reagent is usually completely consumed. When it is gone, the other excess reactants have nothing to react with and they cannot be converted to products. The substance which is used up first is the limiting reagent.
Principle of Rocket Operation
Newton's Third Law of Motion is "every action is accompanied by an equal and opposite reaction." A rocket operates on this principle. The force exerted by the rocket on the ejected reaction products equals the force of the ejected particles on the rocket. So the "impulses" (the product of the force and time that it acts) are equal in magnitude and opposite in direction. Since the impulse (F × t) equals the momentum (m × v), the momentum of the spent fuel in one direction equals the momentum of the rocket in the other. The fuel and oxidant must be designed to rapidly heat and eject combustion products in one direction, causing motion of the rocket in the opposite direction.
The gauge of efficiency for rocket propellants is specific impulse, stated in seconds. The higher the number, the "hotter" the propellant.
Specific Impulse (Isp is the period in seconds for which a 1-pound (0.45-kilogram) mass of propellant (total of fuel and oxidizer) will produce a thrust of 1 pound (0.45- kilogram) of force. The specific impulse for a fuel may vary somewhat due to conditions
NASA and commercial launch vehicles use four types of propellants: (1) petroleum; (2) cryogenics; (3) hypergolics; and (4) solids. Examples involving cryogenics (liquid hydrogen and liquid oxygen) and solids (aluminum and ammonium perchlorate, or Ammonium Perchlorate Composite Propellants, APCPs) are give below. Hypergolics are compounds that react upon mixing (without an ignition source), like nitrogen tetroxide and hydrazine which we'll discuss later. Petroleum derivatives include RP-1 (Rocket Propellant or Refined Petroleum-1), which is similar to kerosene and used with an oxidant like liquid oxygen.
|Max Specific Impulse||~353||258||~250||444 |
|Oxidizer to Fuel Ratio||2.56:1||0.77:1||calculate below||calculate below|
Example 1: LH2 + LOX
a. Which is the limiting reagent?
b. What mass of product will be formed?
c. Did NASA make a mistake?
Solution The balanced equation
2 H2 + O2 → H2O
tells us that according to the atomic theory, 2 mol H2 is required for each mole of O2. That is, the stoichiometric ratio S(H2/O2) = 2 mol H2/ 1 mol O2. Let us see how many moles of each we actually have
If all the H2 were to react, the stoichiometric ratio allows us to calculate the amount of O2 that would be required:
This is more than the amount of oxygen present,so oxygen is the limiting reactant and H2 is present in excess.
If all the O2 reacts, the stoichiometric ratio allows us to calculate the amount of H2 that would be required:
We require less than the amount of H2 present, so it is the excess reactant.
When the reaction ends, 3.934 x 107 mol of H2 will have reacted with 1.967 x 107 mol O2 and there will be
(5.271 x 107 mol - 3.934 x 107 mol) = 1.337 x 107 mol H2 left over. Oxygen is therefore the limiting reagent.
b. Since the hydrogen doesn't all react, we need to calculate the amount of water produced from the amount of oxygen consumed, by using the stoichiometric ratio:
The mass of water is then calculated by using the molar mass:
c. The excess hydrogen is not a mistake. The reaction is so exothermic that it ejects some of the unreacted hydrogen. This doesn't matter, since any ejected mass contributes to the backward momentum of fuel, and the forward momentum of the rocket. Since the mass of hydrogen is small, its velocity is large, and it can contribute to a large forward velocity of the rocket.
These calculations can be organized as a table, with entries below the respective reactants and products in the chemical equation. We can calculate (hypothetically) how much of each reactant would be required if the other were completely consumed to demonstrate which is in excess, and which is limiting. We use the amount of limiting reagent to calculate the amount of product formed.
|2 H2||+ O2||→ H2O|
|m (g)||1.063 x 108||6.293 x 108|
|n (mol)||5.271 x 108||1.967 x 108||--|
|if all O2 reacts||-3.934 x 107||-1.967 x 107||+3.934 x 107|
|-3.933 x 107||-1.967 x 107||+3.933 x 107|
|-7.930 x 107||-6.293 x 108||+7.086 x 108|
In the end, 1.063 x 108 - 7.930 x 107 = 2.70 x 107 g of H2 will remain, along with 7.08 x 108 g of water, for a total of 7.35 x 108 g. The mass of the reactants was also 1.063 x 108 + 6.29 x 108 = 7.35 x 108 g.
General Strategy for Limiting Reactant Problems
From this example you can begin to see what needs to be done to determine which of two reagents, X or Y, is limiting. We must compare the stoichiometric ratio S(X/Y) with the actual ratio of amounts of X and Y which were initially mixed together. In Example 1 this ratio of initial amounts
was less than the stoichiometric ratio
This indicated that there was not enough O2 to react with all the hydrogen, and oxygen was the limiting reagent. The corresponding general rule, for any reagents X and Y, is
Of course, when the amounts of X and Y are in exactly the stoichiometric ratio, both reagents will be completely consumed at the same time, and neither is in excess.
As you can see from the example, in a case where there is a limiting reagent, the initial amount of the limiting reagent must be used to calculate the amount of product formed. Using the initial amount of a reagent present in excess would be incorrect, because such a reagent is not entirely consumed.
APCP Solid Propellants
Solid Rocket Boosters (SRBs) are the type implicated in the infamous Challenger Disaster, where a poor seal allowed escape of hot gases. Each SRB motor contains a propellant mixture (weighting about 590,000kg) consisting of ammonium perchlorate (oxidizer, 69.6% by weight), and aluminum (fuel,16%). A catalyst (iron oxide, 0.4%), a binder (which also acts as secondary fuel, 12.04%), and a curing agent (1.96%). This propellant is commonly referred to as Ammonium Perchlorate Composite Propellant (APCP).
a. An amateur rocketeer wants to make 100g of propellant. He mixes the propellant with 69.6 g of ammonium perchlorate (the required 69.6%), but he has no binder, so uses 16.0 g of Al plus another 12.0 g Al in place of the binder (which is also a fuel), or 28% aluminum in the mixture. Is this ratio correct? b. If not, which is the limiting reactant? c. Calculate the mass of Al2O3 produced by the first reaction below.
6 NH4ClO4 + 10 Al → 5 Al2O3 + 6 HCl + 3 N2 + 9 H2O or 6 NH4ClO4 + 10 Al → 4 Al2O3 + 2 AlCl3 + 3 N2 + 12 H2O
The stoichiometric ratio connecting Al and NH4ClO4 is
The initial amounts of Al and NH4ClO4 are calculated using appropriate molar masses
Their ratio is
Since this ratio is larger than the stoichiometric ratio, you have more than enough Al to react with all the NH4ClO4. NH4ClO4 is the limiting reagent, so the ratio isn't stoichiometric.
b) The amount of product formed in a reaction may be calculated via an appropriate stoichiometric ratio from the amount of a reactant which was consumed. Some of the excess reactant Al will be left over, but all the initial amount of NH4ClO4 will be consumed. Therefore we use nNH4 ClO4 (initial) to calculate how much Al2O3 can be obtained
You may want to verify the rest of the values in the table:
|6 NH4ClO4||+ 10 Al →||5 Al2O3||+ 6 HCl||+ 3 N2||+ + 9 H2O|
|if all NH4ClO4 reacts||-0.592||-0.987|
- ↑ http://en.wikipedia.org/wiki/Space_shuttle
- ↑ http://www-pao.ksc.nasa.gov/nasafact/count2.htm
- ↑ http://www.nasa.gov/
- ↑ http://cnx.org/content/m33041/latest/
- ↑ http://en.wikipedia.org/wiki/RP-1
- ↑ http://en.wikipedia.org/wiki/Titan_II_GLV
- ↑ http://en.wikipedia.org/wiki/Ammonium_perchlorate_composite_propellant
- ↑ http://www-pao.ksc.nasa.gov/nasafact/count2.htm
- ↑ http://en.wikipedia.org/wiki/Space_Shuttle_external_tank
- ↑ http://en.wikipedia.org/wiki/Space_Shuttle_Solid_Rocket_Booster#Challenger disaster
- ↑ http://science.ksc.nasa.gov/shuttle/technology/sts-newsref/srb.html
- ↑ http://www.nasa.gov/returntoflight/system/system_SRB.html