A GLIDE BOMB AND METHODS OF USE THEREOF

Abstract

The present invention relates to a glide bomb and methods of use thereof for use with an unmanned or manned aerial vehicle or for operative deployment. In one form, the glide bomb is configured to be carried and released by an unmanned aerial vehicle (“UAV”) for flight towards a selected target. The glide bomb includes an elongate body having a nose and an opposed tail aligned along a longitudinal axis; a payload; a pair of wings extendable from opposed sides of the body for producing lift, said wings configured to be selectively moveable between a retracted position and an extended position; and two or more tail control surfaces operatively associated with the tail of the body for at least pitch and yaw control.

Claims

1. A glide bomb configured to be carried and released by an unmanned or manned aerial vehicle for flight towards a selected target, said glide bomb comprising: an elongate body having a nose and an opposed tail aligned along a longitudinal axis; a payload; a pair of wings extendable from opposed sides of the body for producing lift, said wings configured to be selectively moveable between a retracted position and an extended position; and two or more tail control surfaces operatively associated with the tail of the body for at least pitch and yaw control.

2. The glide bomb of claim 1, wherein the glide bomb is configured to be carried and released by an unmanned aerial vehicle (“UAV”).

3. The glide bomb of claim 1, wherein the glide bomb has a flight range from deployment to target of between about 2,000 m and about 4,000 m.

4. The glide bomb of claim 1, wherein each of the pair of wings is pivotally mountable to the elongate body about an inner end so that the outer end is pivotable between the retracted position and the extended position.

5. The glide bomb of claim 1, wherein the wings are selectively pivotable between the retracted position and the extended position relative to the elongate body over a range of between about 70° to about 90°.

6. (canceled)

7. The glide bomb of claim 1, wherein each of said wings can be selectively moved to a swept back position for one or more of high-speed flight, roll control and longitudinal trim of the glide bomb in flight.

8. The glide bomb of claim 1, wherein the wings are configured to be selectively pivoted at least partially between the retracted position and the extended position to enable the glide bomb to transition between a stowage and freefall mode, a low-speed flight mode, a high-speed flight mode and/or for roll control as required.

9. The glide bomb of claim 1, wherein the two or more tail control surfaces comprise at least one vertical stabiliser having at least one rudder and a pair of opposed horizontal stabilisers each having at least one elevator for control yaw and pitch motion of the glide bomb, respectively.

10. The glide bomb of claim 9, wherein the pair of opposed horizontal stabilisers are moveable between a retracted position in which the stabilisers are folded against the elongate body and an extended position in which the horizontal stabilisers are operable.

11. (canceled)

12. The glide bomb of claim 10, wherein the pair of horizontal stabilisers are selectively pivotable between the retracted position, the extended position and one or more positions therebetween.

13. (canceled)

14. The glide bomb of claim 2, wherein the glide bomb is mounted to an underside of the UAV by a release mechanism operatively associated with a firing mechanism for triggering deployment of the glide bomb from the UAV upon receiving a firing command.

15. The glide bomb of claim 1, further comprising at least one image capturing device for facilitating flight control of the glide bomb.

16. The glide bomb of claim 1, further comprising a range finder of determining a distance between the glide bomb and the selected target.

17. The glide bomb of claim 1, further comprising at least one guidance system for guiding flight of the guide bomb to the target when released and after having received target coordinates prior to release.

18. The glide bomb of claim 17, wherein the at least one guidance system comprises an inertial navigation system and a global navigational satellite system (“GNSS”).

19. The glide bomb of claim 18, wherein the at least one guidance system is configured to switch from the GNSS to the inertial navigation system as the glide bomb nears the target.

20. The glide bomb of claim 1, further comprising at least one controller for controlling flight of the glide bomb to target the target.

21. The glide bomb of claim 20, wherein the at least one controller is in communication with an external controller over a communications network for at least part of a flight of the glide bomb.

22. The glide bomb of claim 20, wherein the at least one controller is in communication with a like at least one controller of other like glide bombs deployed to coordinate at least one of a strike, a synchronous or near synchronous strike and collision avoidance.

23. (canceled)

24. A method of deploying a glide bomb from an unmanned or manned aerial vehicle, said method comprising: providing an aerial vehicle, said aerial vehicle carrying at least one glide bomb, comprising: an elongate body having a nose and an opposed tail aligned along a longitudinal axis; a payload; a pair of wings extendable from opposed sides of the body for producing lift, said wings configured to be selectively moveable between a retracted position and an extended position; and two or more tail control surfaces operatively associated with the tail of the body for at least pitch and yaw control; identifying a target and determining target information including a distance to target, a pitch angle, a yaw angle and an altitude required to strike the target with the at least one glide bomb; transmitting the target information to the at least one glide bomb; and releasing the at least one glide bomb.

25-29. (canceled)

Description

BRIEF DESCRIPTION OF DRAWINGS

[0149] Preferred features, embodiments and variations of the invention may be discerned from the following Detailed Description which provides sufficient information for those skilled in the art to perform the invention. The Detailed Description is not to be regarded as limiting the scope of the preceding Summary of Invention in any way. The Detailed Description will make reference to a number of drawings as follows:

[0150] FIG. 1 is an upper perspective view of a glide bomb according to an embodiment of the present invention with the wings shown in a retracted position;

[0151] FIG. 2 is an upper perspective view of the glide bomb of FIG. 1 having been recently released by a UAV and with its wings in an extended position;

[0152] FIG. 3 is an upper perspective view of a glide bomb according to another embodiment of the present invention with the wings and horizontal stabilisers in a retracted position;

[0153] FIG. 4 is an upper perspective view of the glide bomb of FIG. 3 with its wings and horizontal stabilisers in an extended position;

[0154] FIG. 5 is a flowchart showing steps in a method of releasing the glide bomb as shown in FIGS. 1 to 4 from a UAV; and

[0155] FIG. 6 is a flowchart showing steps in a flight trajectory method of the glide bomb as shown in FIGS. 1 to 4 when approaching a target.

DETAILED DESCRIPTION

[0156] FIGS. 1 to 4 show embodiments of a glide bomb (100) configured to be carried and released by an unmanned aerial vehicle (“UAV”; 900; shown only in FIG. 2).

[0157] FIGS. 1 and 2 show a first embodiment of the glide bomb (100).

[0158] Referring to FIG. 1, the glide bomb (100) includes: an elongate body (110) having a nose (112) and an opposed tail (114) aligned along a longitudinal axis; a payload (not visible); a pair of wings (120) extendable from opposed sides of the body (110) for producing lift and configured to be selectively moveable between a retracted position (shown) and an extended position (see FIG. 2); and two or more tail control surfaces (130) operatively associated with the tail (114) of the body (110) for at least pitch and yaw control.

[0159] The elongate body (110) is formed from lightweight material or materials with high stiffness, strength and fatigue performance, such as, e.g., aluminium or a carbon fire composite.

[0160] The body (110) includes an aerodynamic outer shell (140). The shell (140) is also formed from lightweight material or materials with high stiffness, strength and fatigue performance, such as, e.g., aluminium or a carbon fire composite.

[0161] The shell (140) has a substantially circular cross-sectional shape that tapers at or near each of the nose (112) and tail (114) of the body.

[0162] The shell (140) is configured to house internal components of the glide bomb (100), such as, e.g., the payload and internal electronic components. The shell (140) includes one or more openings defined therein for the protrusion of components, such as, e.g., sensors, antennas and the like.

[0163] As indicated, the pair of wings (120) are extendable from opposed sides of the body (110). Each wing (120) is an air foil sized and shaped to produce lift. In this regard, each wing (120) includes a rounded leading side edge and a sharp opposed trailing side edge.

[0164] Referring briefly to FIG. 2, the wings (120) when in the extended position span about 650 mm from tip to tip.

[0165] The wings (120) are formed from lightweight material or materials with high stiffness, strength and fatigue performance, such as, e.g., aluminium or a carbon fire composite.

[0166] Each wing (120) is pivotally mountable to the body such that the wing (120) is able to be selectively pivoted between a retracted position (as shown in FIG. 1) and the extended position as shown.

[0167] Each wing (120) is selectively pivotable relative to the body over a range of about 90°.

[0168] When the wings (120) are in the extended position, they provide lift to the glide bomb (100). Conversely, when the wings (120) are in the retracted position, lift and/or drag are reduced. Further, when the wings (120) are in the retracted position, interference with the UAV (900) may is reduced enabling two glide bombs (100, 100A) to be mounted to an underside of the UAV (900).

[0169] In addition to moving between the retracted and extended positions, the wings (120) are selectively moveable to variable sweep angles therebetween to achieve desired flight characteristics.

[0170] For example, the wings (120) can be moved to a swept back position for high-seed flight, for roll control, and/or for longitudinal trim of the glide bomb (100) in flight. For example, a left wing (120) can be selectively moved to the swept back position for a negative roll motion of the glide bomb (100). Conversely, a right wing (120) can be selectively moved to the swept back position for a positive roll motion of the glide bomb (100).

[0171] Pivoting of each wing (120) relative to the body (110) of the glide bomb (100) is actuated by a servomotor.

[0172] In use, selective pivoting of the wings (120) enables the glide bomb (100) to transition between a stowage and freefall mode, a low-speed flight mode, a high-speed flight mode and for roll control as required.

[0173] Referring back to FIG. 1, the glide bomb (100) includes two tail control surfaces (130) arranged in a V-shaped configuration protruding upwardly from the tail (114) of the body (110). The tail control surfaces (130) stabilise the yaw and pitch of the glide bomb (100).

[0174] Each control surface (130) includes at least one ruddervator (not visible) along a portion of a rear or aft edge of the control surface (130). The ruddervator is pivotable about and relative to a longitudinal axis of the control surface (130) for controlling the yaw motion and pitch motion of the glide bomb (100). Like the wings (120), movement of the ruddervators is actuated by a servomotor.

[0175] While not shown, the payload of the glide bomb (100) includes a HE-Frag warhead with a total mass of about 600 g, including 200 g of explosive. However, other types of both explosive and non-explosive payloads are envisaged, such as, e.g., 2-chlorobenzalmalononitrile or CS gas (i.e., tear gas), nuclear warheads, chemical warheads, biological warheads, communications nodes, IR beacons, shaped charges, electronic-warfare (“EW”) jammer or communications repeaters.

[0176] The warhead includes a detonator/fusing device. The detonator/fusing device can include a contact detonator, a proximity detonator, a remote detonator, a timed detonator, an altitude detonator or any combination thereof enabling both ground burst and airburst at differing altitudes.

[0177] Referring again to FIG. 2, the glide bomb (100A) is mounted to an underside of the UAV (900) by a release mechanism operatively associated with a firing mechanism of the UAV (900) for triggering deployment of the glide bomb (100) from the UAV (900) upon receiving a firing command.

[0178] The release mechanism is a glide bomb holder (not visible) attached to an underside of the UAV (900) and includes one or more locks or electromagnets configured to releasably fasten the glide bomb (100A) to the holder. The electromagnets or locks are configured to release the bomb (100) in a synchronous manner upon receiving the firing command.

[0179] The glide bomb (100) includes a guidance system for guiding flight of the glide bomb (100) to the target when released from the UAV (900) and after having received target coordinates from the UAV (900) prior to release via a wired connection. The guidance system includes an inertial navigation system and a global navigational satellite system (“GNSS”).

[0180] Upon release, the guidance system of the glide bomb (100) autonomously guides the glide bomb (100) to the target for target strike.

[0181] In use, the guidance system is configured to switch from the GNSS to the inertial navigation system as the glide bomb (100) nears a target. Advantageously, this reduces any interference to guidance caused by a loss of GNSS-signals, such as, e.g., when unavailable, disrupted or jammed.

[0182] FIGS. 3 and 4 show a second embodiment of the glide bomb (100). For convenience, features that are similar or correspond to features of the first embodiment will be referenced with the same reference numerals.

[0183] Referring to FIG. 3, the glide bomb (100) includes: an elongate body (110) having a nose (112) and an opposed tail (114) aligned along a longitudinal axis; a payload (not visible); a pair of wings (120) extendable from opposed sides of the body (110) for producing lift and configured to be selectively moveable between a retracted position (shown) and an extended position (see FIG. 4); and two or more tail control surfaces (130) operatively associated with the tail (114) of the body (110) for at least pitch and yaw control.

[0184] In this embodiment, the two or more tail control surfaces (130) include: a downwardly extending vertical stabiliser (131) having a rudder (132) pivotable about a vertical axis relative to the vertical stabiliser (131) for controlling yaw motion of the glide bomb (100); and a pair of horizontal stabilisers (133) mounted to and extending from either side of the tail (114). Each horizontal stabiliser (133) has an elevator (134) pivotable about a horizontal axis relative to the horizontal stabiliser (133) for controlling pitch motion of the glide bomb (100).

[0185] Each horizontal stabiliser (133) includes an inner end (135) mountable to the tail (114), an opposed outer end (136) and an elongate body (137) extending therebetween.

[0186] Like with the wings (120), the horizontal stabilisers (133) are selectively moveable between a retracted position (shown) in which the stabilisers (133) are folded, or pivoted, against the elongate body (110) of the glide bomb (100) and an extended position (see FIG. 4) in which the stabilisers (133) are operable.

[0187] When in the retracted position as shown, the outer end (136) of each stabiliser (133) is pivoted towards the nose (112) of the body (110) of the glide bomb (100).

[0188] Advantageously, when in the retracted position, any interference with a UAV carrying the glide bomb (100) is reduced.

[0189] Referring to FIG. 4, each horizontal stabiliser (133) is pivotally mountable to the body (110) at the tail (114) to be selectively pivotable between a retracted position (as shown in FIG. 3) and the extended position as shown.

[0190] In use, the glide bomb (100) is configured to pivot the horizontal stabilisers (133) to the extended position as soon as the glide bomb (100) is released from a UAV or operative to thereby provide at least partial flight control.

[0191] Like with the wings (120), pivoting of each horizontal stabiliser (133) relative to the body (110) of the glide bomb (100) is actuated by a servomotor.

[0192] Referring to both FIGS. 3 and 4, the glide bomb (100) like in the first embodiment is configured to be mounted to an underside of a UAV (not shown) by a release mechanism operatively associated with a firing mechanism of the UAV (not shown) for triggering deployment of the glide bomb (100) from the UAV (not shown) upon receiving a firing command.

[0193] The release mechanism includes two mounting forks configured to be at least partially received in mounting slots (310) defined on an upper surface of the body (110) of the glide bomb (100). The two mounting forks are configured to release the bomb (100) in a synchronous manner upon receiving the firing command.

[0194] Target information is transmitted via a severable wired serial link between the UAV (not shown) or operative (not shown) and the glide bomb (100) prior to the glide bomb being deployed. The wired serial link connects to inlet port (320) defined forward of the mounting slots (310) on the upper surface of the body (110) of the glide bomb (100). The link is configured to be severed when the glide bomb (100) is released.

[0195] As shown, the glide bomb (100) in this embodiment further includes a pitot probe (330) extending forward of the nose (112) of the body (110) for measuring fluid flow velocity and therefore airspeed.

[0196] A method (500) of releasing the glide bomb (100) from the UAV (900) as shown in FIGS. 1 to 4 is now described in detail with reference to FIG. 5.

[0197] At step 510, the UAV (900) targeting system identifies a target and determines target information, including a distance to target, and a pitch angle, a yaw angle and an altitude required to strike the target with the glide bomb (100).

[0198] At step 520, the UAV (900) transmits the target information to the glide bomb (100) via a wired serial link.

[0199] At step 530, the glide bomb (100) is released from the UAV (900) upon receiving a firing command from the UAV (900) operator.

[0200] A flight trajectory method (600) the glide bomb (100) as shown in FIGS. 1 to 4 is now described in detail with reference to FIG. 6.

[0201] At step 610, the UAV (900) targeting system identifies a target and determines target information, including a distance to target, and a pitch angle, a yaw angle and an altitude required to strike the target with the glide bomb (100). The UAV (900) then transmits the target information to the glide bomb (100) via a wired serial link short range RF radio link (e.g., Bluetooth).

[0202] At step 620, the glide bomb (100) is released from the UAV (900) upon receiving a firing command from the UAV (900) operator. The glide bomb (100) freefalls with the wings (120) in the retracted position until a desired velocity is attained to maintain glided flight towards the target.

[0203] The velocity is determined via a determination of the dynamic pressure of the glide bomb (100).

[0204] At step 630, upon reaching the desired velocity, the wings (120) of the glide bomb (100) transition from the retracted position at least partially towards the extended position to provide lift, flight control and an optimum glide ratio of between about 15 and about 17.

[0205] The guidance system of the glide bomb (100) autonomously guides the glide bomb (100) to the target for target strike.

[0206] In some embodiments, the method (400) further includes transitioning the glide bomb (100) to a terminal strike mode as the glide bomb (100) nears the target. For example, upon reaching a predetermined proximity to the target, the wings (120) of the glide bomb (100) at least partially retract and the glide bomb (100) pitches downwards to accelerate for target strike.

[0207] In the present specification and claims (if any), the word ‘comprising’ and its derivatives including ‘comprises’ and ‘comprise’ include each of the stated integers but does not exclude the inclusion of one or more further integers.

[0208] Reference throughout this specification to ‘one embodiment’ or ‘an embodiment’ means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, the appearance of the phrases ‘in one embodiment’ or ‘in an embodiment’ in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more combinations.

[0209] In compliance with the statute, the invention has been described in language more or less specific to structural or methodical features. It is to be understood that the invention is not limited to specific features shown or described since the means herein described comprises preferred forms of putting the invention into effect. The invention is, therefore, claimed in any of its forms or modifications within the proper scope of the appended claims (if any) appropriately interpreted by those skilled in the art.