Mortar round glide kit
View Patent ↗Apparatus and methods provide a kit for converting a conventional mortar round into a glide bomb. Mortar rounds are readily available to combat personnel and are small and light enough to be carried by relatively small unmanned aerial vehicles (UAVs) such as the RQ-7 Shadow. Advantageously, the kit provides both guidance and relatively good standoff range for the UAV such that the kit-equipped mortar round can be dropped a safe distance away from the intended target so that the UAV is not easily observed near the intended target.
1. An apparatus comprising a kit for equipping a mortar round with the ability to glide when dropped from altitude, the apparatus comprising:
a housing configured to be attached to a rear portion of a mortar round;
a threaded joint configured to attach the housing to a rear portion of a mortar round, wherein the threaded joint is configured to engage with threads of a mortar round originally intended to engage with a tail section;
at least one wing configured to provide lift and two or more movable control surfaces configured to permit flight control, wherein the at least one wing and the two or more movable control surfaces permit a mortar round equipped with the kit to have a glide ratio of at least 1:1, wherein the glide ratio comprises a ratio of forward distance traveled to downwards distance traveled while gliding at constant speed;
at least one hard mounting point for coupling the housing, directly or indirectly, to a launcher;
one or more servos configured to actuate the movable control surfaces for flight control;
a control system configured to determine position and to guide the equipped mortar round via control of the servos to a designated target; and
at least one interface for transfer of data and/or power between a launcher of an unmanned aerial vehicle and the control system.
2. The apparatus of claim 1 , wherein the at least one wing is integrated with the housing.
3. The apparatus of claim 1 , wherein the apparatus further comprises a replacement fuze configured to replace a standard mortar round fuze, wherein the replacement fuze is configured to transition from an unarmed state to an armed state upon detection of at least one of mechanical separation from the launcher and/or speed.
4. The apparatus of claim 1 , wherein the control system comprises a global positioning system (GPS) receiver and a guidance and flight control computer, wherein the guidance and flight control computer is configured to have at least an ingress phase and a terminal phase of flight control, wherein the ingress phase and the terminal phase have different guidance and control laws, wherein the guidance and flight control computer is configured to initially select the ingress phase for control and then to switch to the terminal phase for a final approach to the target.
5. The apparatus of claim 1 , wherein the glide ratio is at least 2:1.
6. An apparatus comprising a kit for equipping a mortar round with the ability to glide when dropped from altitude, the apparatus comprising:
a wing assembly comprising one or more rigid portions and two or more movable control surfaces for lift and control;
a threaded joint configured to attach the wing assembly to a mortar round, wherein the threaded joint is configured to engage with threads of a mortar round originally intended to engage with a tail section, so that with the wing assembly equipped, the mortar round has a glide ratio of at least 1:1, wherein the glide ratio comprises a ratio of forward distance traveled to downwards distance traveled while gliding at constant speed;
at least one hard mounting point for coupling the wing assembly, directly or indirectly, to a launcher;
a plurality of servos configured to actuate the movable control portions of the wing assembly for flight control;
a control system configured to determine position and to guide the equipped mortar round via control of the servos to a designated target; and
at least one interface for transfer of data and/or power between a launcher of an unmanned aerial vehicle and the control system.
7. The apparatus of claim 6 , wherein the glide ratio is at least 2:1.
8. The apparatus of claim 6 , wherein a wingspan associated with the wing assembly is at least four times an outer diameter of the mortar round.
9. The apparatus of claim 6 , wherein a wing of the wing assembly has a wing aspect ratio greater than 4.
10. The apparatus of claim 6 , wherein the rigid portions of the wing assembly are fixed and extend such that the mortar round assembly does not fit into a mortar tube originally intended for the mortar round.
11. The apparatus of claim 6 , wherein the rigid portions of the wing assembly comprise one or more deployable wings having a retracted position and a deployed position, wherein even when the one or more deployable wings are in the retracted position, the mortar round assembly does not fit into a mortar tube originally intended for the mortar round.
12. The apparatus of claim 6 , wherein the control system comprises at least a global positioning system (GPS) receiver, and a guidance and flight control computer.
13. The apparatus of claim 6 , wherein the control system comprises a global positioning system (GPS) receiver, an inertial measurement unit, and a guidance and flight control computer.
14. The apparatus of claim 6 , wherein the control system comprises a global positioning system (GPS) receiver and a guidance and flight control computer, wherein the guidance and flight control computer is configured to have at least an ingress phase and a terminal phase of flight control, wherein the ingress phase and the terminal phase have different guidance and control laws, wherein the guidance and flight control computer is configured to initially select the ingress phase for control and then to switch to the terminal phase for a final approach to the target.