exist. They are NOX(NO, N02, or NO3), H0x (H, OH, H02, H202, or HNO3). and Clx (HC1, Cl, or CIO). Stratospheric mixing ratios of these compounds on the order of a part per billion can be a problem. By scaling the stratospheric deposition rate of the space shuttle to the HLLV, then it can be concluded that a launch frequency of 1 HLLV per year will come to a global equilibrium mixing ratio in about 10 years of 0.1 parts per billion, by volume, (PPBV) of exhaust products. Therefore, 4700 HLLV's per year would produce an equilibrium of 470 PPBV of exhaust products. Thus, the composition of the exhaust products is important. In order to determine this composition, an RP-1, liquid oxygen fuel was assumed, with a chamber pressure of 4000 psi, an oxygen mass to fuel mass ratio of 2.6, a hydrogen to carbon atom ratio of 1.9423 for the RP-1 fuel, and a combustion temperature of 6900°R. Mr. Sanford Gordon of Lewis Research Center calculated the following combustion products, in a manner similar to that described in reference 2. These products are at the exit plane of the nozzle. They will after burn to a slightly different composition, as shown for the Space Shuttle in references 2 and 3. The main differences will be in the CO and N0x fractions. As shown in reference 2, essentially all of the CO will after burn to C02. H and OH may also after burn to H20, but this calculation has not yet been made. Thus, these compounds may not be significant. However, the N0x produced by afterburning and plume shock may be significant. Although the amount of N0x produced in this manner by the Space Shuttle is only about 0.01% to 0.1% of the propellant (ref 4), it could vary significantly for a different configuration. For example.
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