MISC RE AIRPLANE IS DESIGNED AROUND TWO PRATT AND WHITNEY J-58 AFTERBURNING ENG

Created: 3/18/1959

OCR scan of the original document, errors are possible

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TABLE OF

SECTION

Description

Description

Erreiroment

System

Systems

Fuel

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SlrMAHT

The airplane herein proposed, Is designed aroundratt and8 aftorburning engines using HEFtype fuel in theandn tho engines, The fuel load is> HEP oo3_feet no HEF fuel ia burned ln order to avoid undesirable smoke and contamination.

The airplaneco n. ml, mission radius atnd crosses the target atsfeet as shown inn the "Performance" section of this report.

Provisions are maderow of oneominal design psyloadbs. The design strength is consistent with transport criteria, Kodern titanium alloys are used extensively in the interest of simplicity and weight saving. The strength-temperature characteristics of these titanium alloys providetretch in airplane speed to. This is compatible with8 engine stretch potential,

Ihe Configuration is as shown inn the "Generalsection of this report. It consists basicallyow aspect ratio triangular planform wingong slender fuselage and thengine nacelles underneath the wings. This arrangement

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Is consistent with the naximio In structural siinplicity andc performance. In this mannor the size and weight of the airplane is hold to the ralnimiun consistent with cdsslon requirement.

In the section entitled "Alternate Fuel" it is shown that the same airplane can usentirely and accomplish, the. mi. mission radius ateet less altitude.

AcMm/ aircraft corporation

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OSNERAL

This airplane Is an extremely high altitudeeconnaiaance vehicle designed torew of oneound payload.

The configuration is characterisedong thinery thin triangular wing, and under-wing mounted engines. Croas-seotional area of the fuselage ia determined by the reconnaiaance equipment, its length by fuel volume and balance considerations. The wing, while only

hick, haaarge root chord that Ita physical thickness results

in large Internal fuel volume and relatively low loads. Engine positioning under the wing results in excellent accessibility and serviceability, and also contributes to the lightness of the airplane by relieving wing bending loads and eliminating long intake ducts and tailpipes. The conventional tricycle landing gear Is for-ard-retracting and is designed to free-fall.

The military equipment bay, immediately aft of the pilot's compartment. Isnches long and Is accessible through two removable doors, one top and one bottom, each approximatelyinches long. Equipment la Installed and removed through the bottom door, approximately ti feet wide. Thus the provisions for payload are equal to or better than those presently existing inirplanes.

Airplane structure is almost entirelyew titanium alloy having very high strength-to-weight ratio at elevated temperatures, and good formabllity. Extensive use will be made of spotwelcting in sub-assetabliea. The fuselage is of skin, ring, and longeron design.

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The wing and vertical tall consist of miltiple beans, widely spaced ribs,overing of skin stiffened by corrugated inner skins.

Airplane systems, such as controls, hydraulic, cooling and pressurlzatlon, are discussed in succeeding sections of this report.

Followingrief weight summary)

Empty

Oil, Unusable Fuel

Zero Fuel Weight

Fuel

fuel

Takeoff Weight

bs.

Original document.

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