By Dan Linehan
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Extra info for SpaceShipOne: An Illustrated History
05 AglmJ anti IM scale height ja 7770 m. In order to use this simple model for 1I1e task al band, we adjust 1I1e global seale heighl and surface conditions such that the relevant part ofthe atmosphere is most c10sely matched. 05 kgIm3 and a density scale heighl of 7770m (see Fig. 4). This model was used in aoalytical solutioos for parame1rie analysis studies, since it is accurate enough for such analyses, yet simple enough to facilitate easy mathematical treatment An even more accurate possibility is to model the atmosphere through several isothermal layers, all with individual density scale heights.
In summary, one can state that the effect of a lower ballistic coefficient raises the entire deceleration profile to a regime where the atmosphere is less deuse (a higber altitode), prolongs descent time and lowers the aerothennodynamic heating load that the vehicle will have to absorb. This translates into the following capabilities: Increasing payload dwell time in the atmosphere during descent. Increasing the accessible altitude range for direct measurements. Landing at a site with such a high altitude that heavier and speedier probes cannot land on thern because they cannot decelerate in time for a safe landing (such as Tharsis on Mars).
Cal stmosphcrc model at band. A good model is a simple cxponcntial relation bctwccn dcnaity and altitudc. To undcmtand ia cffccI: on miuion lDalysis and its usability Iimits, we will b:riefLy explore the underlying thcmy. Iidcr for dUs purpoIC that the dcnsity and preuure in an atmosphcre la:ycr dcpcnd on the weight ofthe atmolphcrc above it and that the relation bctwccn preuure IOd dcnsity ja thaI: of ID. ideal ps. This re:rults in the followiDg relatiOlll far 1hc dcmity md pRlsure in tc:rnw of the height h from the bottotn : -~ -l> P = Po'~H" = Po·~H, p (11) whm: P andparclocalambicntdcnsityandpreuureand Po and Po theaimosphcric deIIlIIity and pressu;re at the bottom of the layer where h-O.