Universal warhead adapter, and missile and method incorporating same

FIELD OF THE INVENTION

The invention relates to warheads and missiles of the type commonly carried by aircraft for deployment therefrom. The invention relates more particularly to methods and devices facilitating commonality of missile configuration among a number of warheads of different configurations.

BACKGROUND OF THE INVENTION

A number of standard types of missiles have been developed for carriage and deployment by aircraft. For example, the AGM-130 uses a 2000-pound Mk-84 warhead forming the body portion of the missile. A tail assembly having a control section is attached to the aft end of the warhead. The AGM-130 missile has a range of about 40 miles. Because of its weight, it is generally unsuitable for carriage by most U.S. fighter aircraft with the exception of the F-15 aircraft.

Other missiles that incorporate the Mk-84 warhead as the missile body include the LGB, GBU-15, and JDAM missiles. In each case, a tail assembly is attached to the aft end of the Mk-84 warhead in order to convert the Mk-84 warhead from a free-fall bomb to a more-accurate guided missile having improved range over the Mk-84 warhead.

More recent warhead technology has enabled warheads having power equivalent to the Mk-84 to be made much lighter. Examples of modern warheads in the 500-pound to 1000-pound weight class include the Mk-82, Mk-83, AUP, I-1000, HTW, I-800, and JAST warheads. In order to enable these warheads to be used for making missiles, a dedicated tail assembly configuration would be needed for each type of warhead, since they are considerably smaller than the Mk-84 warhead and therefore are not compatible with the tail assemblies used in conjunction with the Mk-84 warhead. For example, the assignee of the present application currently has under development three different JDAM tail kits for converting Mk-84, Mk-83 (a 1000-pound warhead), and Mk-82 (a 500-pound warhead) into guided weapons. Still further tail kit configurations would be needed for other warheads.

There is a need for a solution to the problems of lack of commonality among a host of modem warheads and lack of systems for converting the warheads into missiles.

SUMMARY OF THE INVENTION

The above needs are met and other advantages are achieved by the present invention, which provides a universal warhead adapter for use in conjunction with any of a number of warheads of various configurations, thus enabling the warheads to be used with existing tail assemblies to make missiles that can be carried by aircraft using existing aircraft carriage assemblies. To this end, the invention in a preferred embodiment provides a universal warhead adapter comprising a tubular sleeve defining an internal cavity sized to receive a selected one of a plurality of warheads of different predetermined configurations such that the warhead is enclosed by the sleeve. The sleeve has a forward end and an aft end and is aerodynamically and structurally configured to function as a body portion of a missile. The adapter further includes an aft bulkhead at the aft end of the sleeve, the aft bulkhead being configured to permit mounting of a predetermined missile tail assembly onto the aft end of the sleeve. Thus, a common missile configuration is presented by the universal warhead adapter when assembled with a selected warhead and the tail assembly.

The invention thus enables warheads of many sizes, shapes, and weights to be installed into a sleeve of common configuration. The interface between the missile and an aircraft is therefore the same regardless of which warhead is used. A single tail assembly configuration can be used with the various warheads, since there is no need for the tail assembly to be attached directly to the aft end of the warhead. Furthermore, range extension kits such as wings or other control surfaces, rocket motors, or turbojet engines can be attached to the sleeve in order to provide increased range for the missile. Such range extension kits generally cannot be used with existing missiles such as the JDAM in which the warhead itself forms the body of the missile.

The universal warhead adapter preferably includes fastening mechanisms disposed within the sleeve and operable to fix a selected warhead in a predetermined position within the sleeve. The adapter preferably also includes fittings affixed to the sleeve, the fittings being configured to accept attachment lugs to permit the adapter to be carried by a munitions carrier of an aircraft.

The sleeve advantageously comprises a one-piece integral structure, and preferably is an extruded structure. In order to facilitate fuzing of the warhead, the sleeve preferably includes an access door formed through a side wall of the sleeve for access into the internal cavity of the sleeve. The adapter thus enables the practice of fuzing through the control section or tail kit to be eliminated.

An umbilical connector preferably is attached to the sleeve and projects outwardly therefrom, the connector being adapted to be releasably attached to an external wiring harness on an aircraft and to be connected to an internal umbilical disposed within the sleeve. The internal umbilical can be connected to a tail assembly of a missile formed from the universal warhead adapter. The invention thus facilitates the connection of the aircraft electrical system to the missile without having to route an umbilical externally along the missile.

The universal warhead adapter also facilitates the addition of a seeker to the missile. For example, a seeker can be contained within a nose fairing attached to the forward end of the sleeve.

The invention thus provides apparatus and methods enabling warheads of many different sizes, shapes, and weights to be assembled to form a universal missile having a common exterior body portion that can be fitted with tail kits, nose fairings, control surfaces, rocket motors, turbine engines, and other features.

BRIEF DESCRIPTION OF THE DRAWINGS

The above and other objects, features, and advantages of the invention will become more apparent from the following description of certain preferred embodiments thereof, when taken in conjunction with the accompanying drawings in which:

FIG. 1

is a perspective view of a universal warhead adapter in accordance with a preferred embodiment of the invention;

FIG. 2

is a top elevation of a universal warhead adapter in accordance with another embodiment of the invention;

FIG. 3

is a cross-sectional view taken on line

3

—

3

of

FIG. 2

, showing a warhead installed within the sleeve;

FIG. 4

is a view taken along line

4

—

4

of

FIG. 3

, showing fastening mechanisms for fixing the aft end of the warhead within the sleeve;

FIG. 5

is a view taken on line

5

—

5

of

FIG. 3

, showing a forward frame of the adapter for fixing the forward end of the warhead in the sleeve;

FIG. 6

is a side elevation of a missile formed from a universal warhead adapter assembled with a nose fairing and tail assembly; and

FIGS. 7A-E

are side elevations of various missile configurations formed with the universal warhead adapter assembled with various nose assemblies, tail assemblies, control surfaces, and/or propulsion packages.

DETAILED DESCRIPTION OF THE DRAWINGS

The present invention now will be described more fully hereinafter with reference to the accompanying drawings, in which preferred embodiments of the invention are shown. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like numbers refer to like elements throughout.

With reference to

FIG. 1

, a universal warhead adapter

20

in accordance with a preferred embodiment of the invention is shown. The adapter

20

comprises a tubular sleeve

22

having a forward end

24

and an aft end

26

, and an aft bulkhead

28

attached to the aft end

26

of the sleeve. The sleeve

22

is adapted to slidably receive a warhead within the sleeve such that the warhead is entirely contained with the sleeve. Fastening mechanisms including a forward frame

30

are used for fixing the warhead within the sleeve

22

.

FIGS. 2-5

depict another embodiment of the invention and illustrate in greater detail the manner in which a warhead may be fixed within the sleeve. The universal warhead adapter

40

is similar to the adapter

20

including a tubular sleeve

22

and aft bulkhead

28

, except that it includes a forward frame

50

of different construction from the forward frame

30

of the adapter

20

. The sleeve

22

preferably is a one-piece cylindrical member, and advantageously can be made by extrusion from aluminum alloy or other suitable material. The aft bulkhead

28

comprises a ring-shaped member partially received within the aft end

26

of the sleeve

22

and affixed therein by fasteners

42

that extend through the side wall of the sleeve into the aft bulkhead

28

. A portion of the aft bulkhead

28

projects from the aft end of the sleeve, and this projecting portion is configured to substantially replicate the aft end of a standard warhead, such as the Mk-84 warhead for example.

FIG. 3

illustrates that a warhead W can be inserted into one end of the sleeve

22

, and

FIGS. 4 and 5

depict fastening mechanisms for fixing the warhead W within the sleeve. More particularly, the aft end of the warhead W is affixed within the sleeve

22

by a plurality of fittings

44

(four fittings

44

being used in the embodiment shown in

FIGS. 3-5

) that are spaced about the circumference of the aft end of the warhead and fastened with fasteners to the side wall of the sleeve

22

. The fittings

44

present surfaces that engage the outer surface of the warhead to prevent radial movement thereof, and also include portions that extend radially inward of the outer surface of the warhead and engage the aft end, such portions preferably being fastened to the warhead so as to prevent both forward and aft movement of the warhead. The fittings

44

preferably include set screws

46

oriented radially. The set screws

46

can be turned in one direction or the other to adjust the fittings

44

for accommodating normal manufacturing tolerances of the various components, so that the warhead W is firmly engaged by the fittings

44

.

The forward end of the warhead W is fixed against movement by a forward frame

50

. The forward frame

50

includes a threaded hole

52

for receiving a threaded plug (not shown) formed on the forward end of the warhead W. The forward frame

50

is screwed onto the nose of the warhead W, and then the warhead with the frame attached is slid into the sleeve

22

. Screws

54

are screwed through the sleeve side wall into each of the legs of the frame

50

to secure the frame to the sleeve

22

.

The universal warhead adapter

40

also includes a pair of fittings

60

attached to the top side of the sleeve

22

for accepting standard lugs

62

(

FIG. 1

) that are configured to be engaged by an aircraft carriage and launching device (not shown), such that a missile having the adapter

40

can be carried by and launched from an aircraft. Each fitting

60

is formed preferably as a short section of circular pipe joined at one end to a circular-arc plate having a through-hole aligned with the hole in the pipe. Holes are formed through the side wall of the sleeve

22

, and the pipe portions of the fittings

60

are inserted from inside the sleeve into the holes and the circular-arc plate portions of the fittings

60

are screwed onto the sleeve side wall. The pipe portions of the fittings

60

are long enough to protrude slightly outward from the sleeve outer surface.

The universal warhead adapters

20

,

40

shown in the drawings also include a mating plate

70

attached to the top side of the sleeve

22

. The mating plate

70

was added for purposes of a flight testing program in which a missile having a universal warhead adapter in accordance with the invention was attached to the pylon assembly of an Air Force F-15 fighter aircraft. The purpose of the mating plate

70

was to conform the upper surface of the sleeve

22

, which interfaces with sway braces of the aircraft pylon assembly, to the configuration of a conventional AGM-130 missile. More particularly, a conventional AGM-130 missile has a body whose outer diameter is about 18 inches, and the sway braces of the aircraft pylon assembly are configured to mate with this body configuration. On the other hand, the sleeve of the universal warhead adapter that was tested had an outer diameter of about 16 inches. The mating plate

70

was designed to replicate the configuration of the 18-inch AGM-130 missile body so that the sway braces of the aircraft could be used without modification.

The universal warhead adapter

40

preferably also includes a cover

72

(

FIGS. 3-5

) attached to the inner surface of the sleeve

22

and extending most of the length of the sleeve. The cover

72

and inner surface of the sleeve

22

define a channel therebetween for routing an electrical wiring harness

74

(

FIG. 3

) from the forward end of the sleeve to the aft end of the sleeve so that a seeker (not shown) attached to the forward end of the sleeve can be electrically connected to a missile control section (not shown) attached to the aft end of the sleeve.

The universal warhead adapter of the invention enables a wide variety of missile configurations to be built having a common body portion formed by the sleeve

22

. Accordingly, by configuring the sleeve

22

to be compatible with existing aircraft carriage assemblies, a wide variety of warhead and missile types can be carried by existing aircraft without necessitating modifications to such aircraft.

FIG. 6

shows one such missile

80

generally corresponding to a JDAM missile. The missile

80

includes a universal warhead adapter

40

containing a warhead W shown schematically in dashed lines, a tail assembly

90

attached to the aft end of the adapter

40

, and a nose fairing

100

attached to the forward end of the adapter

40

.

FIG. 6

also illustrates that an internal umbilical

82

connected to the tail assembly

90

can be routed internally through the sleeve

22

and attached to an umbilical connector

84

that extends through the sleeve side wall and is exposed at the top side of the sleeve. The umbilical connector

84

can interface with an external umbilical or wiring harness (not shown) contained within an aircraft pylon or other carriage and launching device. When the missile

80

is launched and falls away from the aircraft, the external umbilical detaches from the connector

84

. The invention thus facilitates elimination of the conventional practice of attaching a sheet metal housing to the top of the missile body for routing the umbilical from the tail assembly to the aircraft wiring harness.

FIGS. 7A-E

show various other missile configurations that can be built using the warhead adapter of the present invention.

FIG. 7A

depicts a missile

110

corresponding generally to a GBU-24 missile. The missile

110

includes a tail assembly

112

and a nose assembly

114

with forward control surfaces

116

. The missile

110

provides a substantial weight reduction relative to a conventional GBU-24 missile by replacing the standard 2000-pound Mk-84 warhead with a 1000-pound warhead contained with the universal warhead adapter

40

(which weighs approximately 200 pounds).

FIG. 7B

depicts a missile

120

corresponding generally to a GBU-10 missile. The missile

120

includes a tail assembly

122

and a nose assembly

124

with forward control surfaces

126

. Again, the invention enables a substantial weight reduction relative to a conventional GBU-10 missile using a Mk-84 warhead.

FIG. 7C

depicts a missile

130

corresponding generally to a GBU-15 missile. The missile

130

includes a tail assembly

132

and a nose assembly

134

with forward control surfaces

136

.

FIG. 7D

depicts a missile

140

corresponding generally to an AGM-130 missile. The missile

140

includes a tail assembly

132

and nose assembly

134

identical to those of the missile

130

, but further includes a rocket motor

142

attached to the sleeve

22

for further extending the range of the missile.

FIG. 7E

depicts a missile

150

corresponding generally to an AGM-130 missile. The missile

150

includes the same tail assembly

132

as the missiles

130

and

140

. The missile

150

also includes a turbojet engine

152

attached to the sleeve

22

for extending the range of the missile. An extended nose assembly

154

is provided with forward control surfaces

156

.

Many modifications and other embodiments of the invention will come to mind to one skilled in the art to which this invention pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. Therefore, it is to be understood that the invention is not to be limited to the specific embodiments disclosed and that modifications and other embodiments are intended to be included within the scope of the appended claims. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.