US3461802A

US3461802A - Heat shield for missile flare

Info

Publication number: US3461802A
Application number: US704746A
Authority: US
Inventors: Raymond I Ayers
Original assignee: US Department of Navy
Current assignee: US Department of Navy
Priority date: 1968-02-12
Filing date: 1968-02-12
Publication date: 1969-08-19
Anticipated expiration: 1986-08-19

Description

Aug. 19, 1969 R. L yzgs 3 HEAT SHIELD Fonmssnm; FLARE Filed Feb. 12, 1968 2 Sheets-Sheet 1 ATTORNEYS Aug. 9, 1969 R. L AYERS 3,461,802

HEAT SHIELD FOR MISSILE FLARE Filed Feb. 12, 1958 v 2 Sheets-Sheet 2 United States Patent 3,461,802 HEAT SHIELD FOR MISSILE FLARE Raymond I. Ayers, Camarillo, Qalifl, assignor to the United States of America as represented by the Secretary of the Navy Filed Feb. 12, 1968, Ser. No. 704,746 Int. 'Cl. F42b 15/00, 13/40; E04c 2/02 US. Cl. 102-87 5 Claims ABSTRACT OF THE DISQLOSURE A heat shield having fastening means for mounting the shield adjacent the discharge nozzle of an airborne missile, saidt. shield having a portion thereof coated with a heat resistant material. The shield protects a tracking flare located adjacent the missile nozzle from the hot gases of the missile motor blast emitting from the nozzle and prevents premature consumption and failure of the flare.

The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

BACKGROUND OF THE INVENTION Field of the invention This invention relates generally to heat protective shields and more particularly to heat protective shields readily attached at an area adjacent a missile exhaust nozzle and adapted to prevent an instrument or a flare mounted near such area from being adversely affected by the excessive heat generated in such area.

Description of the prior art In the operation of the various guided missiles, one method for determining the missile flight is by attaching a tracking flare to the missile thereby permitting a clear observance of said missile over a considerable period of time and to a maximum distance. However, in some missiles it is desirable to recess an instrument or a flare such as a tracking flare near the missile exhaust and in fact to notch the periphery of the exhaust nozzle in order to locate the flare or the like closer to the longitudinal axis of the nozzle. Unfortunately, such notching permits the hot exhaust gases from the missile to impinge upon the after portion of the attached device.

SUMMARY The foregoing as well as other attendant disadvantages have been overcome in the present invention by employing a heat protective shield having fastening means for mounting the shield on the flare adjacent the notched area of the propulsion nozzle, said device having a portion thereof coated with a heat resistant material. The present device shields a tracking flare or other device so located from the hot exhaust gases emitting from the nozzle and prevents premature consumption and failure of said flare. Accordingly an object of this invention is to provide a flare heat shield mounted on a missile in which a portion of the shield is coated with a heat resistant material,

Another object of the invention is to provide a flare heat shield simple in design, easily installed in the field by relatively inexperienced personnel and requiring no modification of the missile on which it is attached.

A further object of this invention is to provide a light and inexpensive flare heat shield which is uniformly effective in operation.

Other objects, advantages, and novel features of the invention will become apparent from the following de- 3,461,802 Patented Aug. 19, 1969 tailed description of the invention when considered in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWING FIGURE 1 is a plan view of a shield constructed in accordance with the present invention.

FIGURE 2 is a plan view of the opposite side of the device of FIG. 1 with the related flare and missile parts depicted in phantom.

FIGURE 3 is a longitudinal sectional view taken along a line substantially corresponding to line 3-3 of FIG. 2.

FIGURE 4 is a rear end elevational view taken from a position substantially corresponding to line 4-4 of FIGURE 1.

FIGURE 5 is a front elevational view taken along a line substantially corresponding to line 5--5 of FIG- URE 1.

DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to the embodiment shown, there is indicated a shield 10 shaped from a suitable material which may be substantially .020 inch thick and preferably is of stainless steel but other suitable heat resistant materials wellknown in the art will suflice. The shield 10 has oppositely and angularly directed pairs of

tabs

12, 14 and 16, 18 connected by an arched intermediate web 20. The

tabs

16 and 18 are slotted at 22 and 24 with the slots being reinforced by the addition of the notched discs 26 (FIG. 2) positioned on the interior surface thereof. The arched web 20 is provided on the outside with a suitable bonding agent, such as a nickel-chrome or molybdenum composition, over which is applied a coating of zirconium oxide 28 (FIG. 4). The combined thickness of binder and zirconium oxide may vary between the range of .025 to .030 inch.

The installation of the shield 10 on the missile is easily accomplished by positioning the angled

rear tabs

12 and 14 so as to overlap the inner face of the nozzle wall. The

front tabs

16 and 18 are placed in position by sliding the

slots

22 and 24 thereof under the holding bracket regularly employed to support the flare. The standard butterfly nuts are then merely retightened to hold the shield 10 in place.

The present invention does not require any re-design or reworking of the propulsion nozzle. It is inexpensive, lightweight and trouble free in installation, requiring no special tools and less than three minutes time expenditure.

What is claimed is:

1. A flare heat resistant shield for installation on a missile and adapted to prevent heat from missile propulsion system from accelerating flare combustion comprising:

an arched protective member adapted for mounting on said missile adjacent said missile nozzle; and

an ablative compound coated on the exterior surface of said protective member and designed to enhance the heat resistance thereof,

the exterior surface of said protective member with the ablative compound thereon being positioned nearest the missile nozzle;

thereby preventing excessive exposure of said flare to the missile motor blast.

2. The heat shield of claim 1 wherein said arched protective member has oppositely directed pairs of tabs in order to provide improved mounting structures for positioning said shield on said missile.

3. A flare heat resistant shield for installation on a missile and adapted to prevent heat from the missile propulsion system from accelerating flare combustion comprising:

3,461,802 3 4 an arched protective member adapted for mounting on References Cited said missile adjacent said missile nozzle; and an ablative compound coated on the exterior surface of UNITED STATES PATENTS said protective member and designed to enhance the 2 4 4 0 1/1950 Anderson 244 324 X heat resistance thereof, said ablative compound being 5 2,829,596 4/1958 Loedding 102 87 zirconlum oxide and present in a coatm'g thickness of 2 926 606 3/1960 Banos et a1 1O2 87 between .025 and .030 inch and the said protective 2986999 6/1961 Fiedcler 6t 102 87 member being formed from material substantially 3182469 5/1965 Kirchner H X th about 9 3,243,313 3/1966 Aves ereby preventing excesslve exposure of said flare to 10 3 300 139 1/1967 F81 dman 102 105 the missile motor blast 4. The heat shield of claim 3 wherein said material from which the said protective member is formed is stainless steel.

5. The heat shield of claim 3 wherein a bonding agent 15 X- is provided on the exterior surface of the protective mem- 102-105 ber prior to application of said zirconium oxide.

VERLIN R. PENDEGRASS, Primary Examiner