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Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 EDMUND B.HAMMOND Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet F. G. m?Assaa asood AFAZA 45AZ2 | N - - Y |- r. 6Cam) ??? : ????? ??????? ?. ?. ???? “?azij “ ???? 4ooo ?? ???? 70o (?w 9000 0000 /000 ,000 5000 /000 6000 /??? NVENTOR EDMUND B.HAMMOND, JR. AORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. l, 1951 2. Sheets-Sheet 2 acosavadav avera/7AApaaaayoA/A6 Aosavaow aaayaa A Aapatafova A AMMAZZA ABAE4A1f aesavvoy F. G. 5 NVENTOR EDMUND B. HAMMOND, JR ORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet 5 Fl G. 6 | /N@ 32 //7 24 20 26 8 4 7aagavadava/ow A Pos/7/OMY/7 = Osaec.) N.VENOR EDMUND B. HAMMOND, JR TTORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. l, 951 2l Sheets-Sheet 5 C2772 ·772zzz NVENTOR DMUND B. HAMMOND, JR. ? ???? ?? ???? ?? AORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM 6222 Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM -!02/g|*9 NVENTOR EDMUNDB. HAMMOND, JR. |ço, EY 21611. ATORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM EDMUND B. HAMMOND, JR BY ?? '??? ATTORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet l) TrAAAYADØYYAY adaawase aaaaaa. Apavadea X awasas Alaa Aasa. F. G. 20 Aw fa AVa, AAASA NVENTOR EDMUND B. HAMMOND, JR. ATTORNEY Jan. 18, 1966 3,230,348 Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet l? ~)???-----_-~ NVENTOR EDMUNDB. HAMMON D, JR. BY z/* ATTORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM NVENTOR EDMUNDB ???/ATORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 2. Sheets-Sheet 14 NVENTOR DMUND?? B . HAMMOND, JF ATORNY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 2. Sheets-Sheet 5 ZAVAZZg%2.22:2=Z35.--->/2 (279o------- A977 6792 2,3º9|-} NVENOR EDMUND B. HAMMOND, JR. BY ?? 7. AORNEY E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM 2. Sheets-Sheet 16 ? ^—~~~~–??????????????????????????” NVENOR EDMUNDB. HAMMOND, JR. EY (,AORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet 17 Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet l8 az, SPEA o é eE74ce swiftwa AEZAE/477/OW ARAPA247AP AETAPAGPAP H-3F = F. G. 3 O NVENTOR EDMUND B.HAMMOND, JR. ORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 2. Sheets-Sheet l9 (?) - G) - GQ a/awad CoAv7apoal ???? as: wavy Ni ??7aaoag ??? af ???? AS3 avao-7afaelag ORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet 20 Na ? - x Aalacaw (ZY Crsaw:/V2:w aasavata 34 70AQA MultiP!/ER ame 3 y J% COPAWS7. ASASAPAGP/MWG ARAZaq Y all of COW7A0A AwaZ 2 ? 5AA5/77W/7Y COMA/7EAR 22 2Zassa, ArV ?3? avywala eaawaay k %cos 6a NVENTOR Aabaa EDMUND B. HAMMOND, JR ARAAWIGA ATORNEY Jan. 18, 1966 E. B. HAMMOND, JR 3,230,348 MISSILE GUIDANCE SYSTEM Filed Sept. 1, 1951 21. Sheets-Sheet 2l az7470/7Afaa Awaf aaa.oe 2?/? (k-1)/4y-Ksy ) --- - -" za 22 wrzzex -- ??%\ ???? sz/ NVENTOR F. G. 34 UND B. HAMMONDJR. TTORNEY 3,230,348 United States Patent Office Patented Jan. 18, 1966 1. 2 quired to follow sight line trajectories. It can be shown 3,230,348 MSSLE GUEDANCE SYSTEM that the sight line trajectory is identical with the constant Edmund B. Hammond, Jr., Merrick, N.Y., assignor to bearing trajectory provided that the fighter simultane Sperry Rand Corporation, a corporation of Delaware ously executes a constant bearing approach toward the Filed Sept. 1, 1951, Ser. No. 244,761 target. This leads to the conclusion that, in order to 22 Claims. (Cl. 235-61.5) minimize the lateral kinematic missile acceleration re This invention relates to missile guidance systems, and quired for following a sight line trajectory, the fighter particularly, to flight path computers for use with Such should follow a constant bearing path toward the target systems. during the time-of-flight of the missile. O It would be fairly easy to obtain this condition pro The system of which this invention forms a part is vided that the missile could be launched and captured designed primarily to control the guidance of an air-to by the radar beam while the fighter is following a con air missile currently designated as Sparrow XAAM-2, stant bearing trajectory. However, this procedure is im Pilotless Aircraft, although it will be apparent that the practical because of the size of the missile, the difficulty basic features of the invention may readily be applied of building flexible missile launchers, and the dispersion to control the guidance of other types of missiles. By difficulties which would be encountered in launching mis way of illustration, the Sparrow missile configuration siles at large angles of attack. Therefore, it is considered (see FIG. 24) comprises an eight inch diameter body ecessary to launch the missile directly forward relative about ten feet long, with an ogive nose and cruciform to the fighter. This means that the missile must be wings and tail surfaces. Its components include a proX 20 launched with the radar beam pointing almost directly imity fuse, a warhead, a control servo system, stored en forward; consequently the fighter must follow a course ergy, a microwave receiver and a solid-fuel motor. Vari similar in nature to a pursuit course prior to launching able incidence wings of delta planform provide lateral the missile. control in the yaw and pitch planes, and delta tail Sur Although the missile must be launched in the manner faces provide aerodynamic stability. Roll control is in 25 just described, it is considered advantageous to have the corporated by differential operation of two of the wings. fighter turning toward a constant bearing path during the As presently contemplated, Sparrow missiles are to be time-of-flight of the missile. In order to obtain the carried by high-speed, carrier-based aircraft whose pri maximum reduction in the kinematic lateral missile ac mary function is to defend the parent aircraft carrier, celeration, this turn should be made as quickly as possi other ships, and shore installations against attacks by 30 ble. Even though the fighter rate-of-turn is limited by enemy aircraft. Normally, the fighter will be on patrol the allowable lateral fighter acceleration value of 100 within twenty-five miles of the carrier when the enemy ft./sec./sec., this turn occasionally makes it possible to aircraft is first detected, although an interception could reduce the final lateral missile acceleration by several g’s. be started from the deck of the carrier if the detection This is particularly important in the case of the Sparrow, range of the carrier's early warning radar Set is large 35 because it is a boost-glide type of missile and has less and the fighter rate of climb is high. available wing lift near the end of its trajectory because In either event, the missile-carrying fighter is to be of decreasing missile velocity. vectored to within range of its acquisition radar by a This line of reasoning led to the adoption of a specific long-range fighter director radar system. At this point type of fighter maneuver during the missile launching the fighter will commence the attack, tracking the target 40 and guidance periods. The maneuver comprises, essen and launching the missile in accordance with calcula tially, following a “continuous release' path during the tions made by a computer, and guiding the missile on missile launching period, a transition from the "contin the tracking beam to within its lethal range from the uous release' path to a constant bearing path during and target. immediately after the missile propulsion period, and con In the present embodiment the missile guidance sys 45 tinuing the constant bearing path until the missile is tem is a single beam, beam-rider type, with intelligence detonated, unless a pilot warning signal is generated. transmitted through the conically scanned target-track The missile is launched subsequent to the start of the ing beam. Dual pulses are transmitted, one in each of "continuous release” path, when the measured values of the four quadrants with different spacing between each sight line angular rate, target range, target range rate, of the pulse pairs for quadrant identification. 50 Kinematic studies indicate that one of the best ways, sight line deflection angle, etc. indicate that the missile if not the best way, in which a missile can approach a will lie approximately at the center of the radar beam target is to follow a constant bearing path. This type of at the end of its propulsion period. approach is characterized by the fact that an imaginary In order to assist the fighter pilot in the execution of line passing through the missile and the target maintains this maneuver it is necessary to provide computing means its initial direction throughout the time-of-flight of the to derive the required flight path components relative to missile.
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