Патент USA US2409134код для вставки
Oct» 3» 1946- ' w. P. LEAR ' _ 2,409,131 SIREN FOR AIRCRAFT Original Filed Feb.. 21, 1942 K15 - INVENTOR wom?fe?war BY - 42W ,4; ATTORNEY Patented Oct. 8, 1946 ' * , 2,409,131 UNl'l‘ED STATES PATENT OFFICE-ii Calif., assign ' William P. Lear, North Hollywood,Lear, Incorpo or, by mesne assignments, to‘ rated, Grand Rapids, Mich, a corporation of Illinois (h'iginal application February 21, 1942, Serial No. 431,814. Divided and this application August 24, 1943, Serial No. 499,755 4 Claims. “ (01. 244-4) 1 This invention relates to high intensity sound producing systems for aircraft, and more particu larly to siren systems adapted to be incorporated ' siren systems 25 are so arranged as to be substane tially enclosed within the fuselage In ‘so as to offer no aerodynamic resistance to ?ight of the in the structure of an aircraft in such a way as to offer substantially no aerodynamic resistance. The present application is a division of my co pending application Serial No. 431,314 ?led Feb aircraft. Each siren system comprises a pivoted funnel intake section H to which is- secured a fuselage section or window l2 for movement ;as a unit therewith. Both the intake section and the fuselage section may be extended by a lever ruary 21, 1942, now Patent No. 2,392,394 issued l3 through the medium of a bell crankjarrange January 8, 1946. ' , ment i4. Lever 13 may extend to a position adja 10 In accordance with the present invention, sirens cent the pilot’s compartment for selective opera or similar sound producing devices are incorpo tion by the pilot or be remotely controlled,‘ ‘ rated within the surface structure or fuselage of The intake section l2 converges to a central an aircraft for operation by aerodynamic power conduit section It which encloses a siren 25 at generated during ?ight. The siren systems are its region of smallest cross-section. The conduit so arranged as to normally not interfere with the 15 section 15 ?ares outwardly from its narrowest aerodynamic characteristics of the aircraft, nor section to an outletsection l'i- which communi add any drag. When it is desired. to operate the cates with the exterior of the fuselageat an‘ open sirens to produce intense sounds, as for exampie ing l8. The conduit arrangement of intake_sec— during dive bombing maneuvers, the tremendous tion ll, conduit section l6 andoutlet section». I‘! aerodynamic forces associated with the aircraft 20 is generally in the shape of a_Venturi tube, so that in high speed ?ight are utilized for the operation. maximum air?ow intensity exists at the siren An important feature of the present invention 25 located at the narrow portion of section ‘I6, thus resides in the utilization of a substantial The walls of intake section ii are aligned and portion of the aerodynamic power generated by substantially coextensive with the walls of central an aircraft in ?ight to operate powerful sound 25 section [6 when section I l is in the illustrated ex, producing means. When it is considered that a tended position. Intake section I l scoopsup and modern combat plane exerts thousands of horse otherwise receives air at the high velocity of the power in full ?ight condition, a considerable array of siren means according to my invention can be driven without requiring auxiliary or standby power plants. The invention is particularly di rected to a novel arrangement for incorporating an array of powerful sirens within the structure aircraft in ?ight, and imparts the air in a sub stantially continuous and uninterrupted stream to the siren 25. The air thus drives the siren 25 and is discharged through the outlet section II to the outside and towards the rear of the aircraft. The general air ?ow through the conduit is indi of the aircraft, and for selectively operating them cated by the series of arrows in Fig. 3. into the inactive and into the sound producing 35 The sirens 25 may he of any suitable size or de conditions. The above and further advantages, capabilities and features of the present invention will appear in the following description of a specific embodi ment thereof and from the accompanying draw ing. In the drawing: Fig. 1 is an elevation view of an embodiment of the invention incorporated in the fuselage of an sign for emitting the powerful sounds required at the desired pitch. While two siren assemblies have been illustrated, it is to be understood that any other number may be employed. Preferably, all the siren systems are interconnected to a com mon operating control, such as the lever IS. The front'face of siren 25 is in the form of an annular face plate 2| attached to the corresponding cir cular minimum section of conduit I6. Face plate Fig. 2 is a cross-sectional view through the sys 45 2| has suitable spaced openings 22. A rotor 23 tem of Fig. 1 as taken along the line 2-2 of is arranged adjacent to plate 2 I, and is supported Fig. 1. between bearing 24 in plate 2| and bearing 26 in Fig. 3 is a longitudinal sectional view through a bracket 21 suitably secured to the walls of sec aircraft. the siren system of Figs. 1 and 2 as taken along 50 the line 3-3 of Fig. 2. In the embodiment of the invention shown in the drawing, the sirens are mounted within the fuselage H) of an aircraft [5 having a wing struc tion It. , The rectangular windows l2 are essentially sec tions of fuselage II) which correspond to the re spective components required by the intake sec tions I l in their extended position. Each window I2 is secured to its conduit section II along the of the lower portion of fuselage Ill as shown. The 55 ture 20. Two siren assemblies, one on each side 3 2,409,131 central longitudinal region. Thus, when a section II is retracted as shown by the dotted line indi cation Ha in Fig. 3, window I2 is flush with fuse lage H] as shown by dotted line I211. Intake sec tion H in its retracted position fits into a corre sponding shaped receptacle 28 joined With the forward edge of the central conduit section l8... Receptacle 28 is constructed so as to prevent air leakage from the conduit siren arrangement into 4 and extending on either end to air intake and air outlet openings in the fuselage, each of said ducts converging from each end toward its center; said sirens being supported at substantially the nar rowest cross-sectional region in said ducts; air scooping means attached to said fuselage at said intake openings; said air scoop means each hav ing a fuselage section secured thereto and con the interior of the fuselage. The bell crank l5 10 forming with the surface contour of the fuselage when said scoop means is retracted; said ducts for mounting the intake section II and-window being formed with receptacle portions receiving I2 is pivoted on a suitable pivotal mounting 29 in said scoop means in the retracted position; and fuselage [0. common operating means for extending and re Normally, the intake section H is in the re tracted position shown in dotted lines in Fig. 3. 15 tracting said scoop means in unison. 3. The combination with an aircraft of sirens When it is desired to operate the sirens, lever i3 ?xedly mounted within the fuselage of the air is actuated and through bell crank l4 intake sec craft; an air duct surrounding each of said sirens tion I l is extended to scoop up air and cause op and extending on either end to air intake and air eration of the sirens. It will be noted that, in outlet openings in the fuselage, each of said ducts the retracted position, the intake section II and window I 2 form a substantially unitary part of 20 converging from each end toward its center; said sirens being supported at substantially the nar the fuselage l0 and offer no aerodynamic resist rowest cross-sectional region in said ducts; air ance to ?ight of the aircraft. scooping means attached to said fuselage at said While a speci?c embodiment of the invention intake openings; said air scoop means each hav has been shown and described to illustrate the ap plication of the principles thereof, it will be un 25 ing a fuselage section secured thereto and con forming with the surface contour of the fuselage derstood that the invention may otherwise be when said scoop means is retracted; said ducts embodied without departing from such principles. being formed with receptacle portions receiving What I claim is: saidscoop means in the retracted position; and l. The combination with an aircraft of sirens ?xedly mounted within the fuselage of the air 30 common operating means comprising an arm connected to each scoop means and levers con craft; an air duct surrounding each of‘said sirens nected to said arms for extending and retracting and extending on either end to air intake and air said scoop means in unison. outlet openings in the fuselage, each of said ducts 4. The combination with an aircraft of an air converging from each end toward its center; said siren ?xedly mounted within the structure of the sirens being supported at substantially the nar aircraft; an air duct, in the form of a Venturi rowest cross-sectional region in said ducts; air tube, surrounding said air siren and extending on scooping means attached to said fuselage at said either end to ?aring forwardly and rearwardly intake openings; said air scoop means each hav directed openings in the structure; said siren be ing a fuselage section secured thereto and con ing located at the smallest cross-section of said forming with the surface contour of the fuselage air duct; a tubular air scoop hinged to said struc when said scoop means is retracted; and said ture at said ?aring forwardly directed opening ducts being formed with receptacle portions re and constituting a movable section of said duct; ceiving said scoop means in the retracted position. and mechanism for controlling the extension of 2. The combination with an aircraft of sirens said scoop to conduct an air ?ow through said ?xedly mounted within the fuselage of the air duct to operate said siren. craft; an air duct surrounding each of ‘said sirens WILLIAM P. LEAR.