Patent Application
20240328752
Certain aircraft are equipped with air-launched missile systems. In one type of system, the missiles may be stored inside the aircraft. In another type of system, the missiles may be mounted to an outer mold line of the aircraft.
Each type of system has its own advantages and disadvantages. For the first type of system, the aircraft hides the radar signature of the missiles. However, available internal volume is reduced for fuel, avionics, and other subsystems.
Moreover, the missiles are deployed from the aircraft and moved out into the airstream prior to launch. The missiles may be kinematically deployed by a kinematic mechanism such as a trapeze-type mechanism. The trapeze-type mechanism is relatively complex and heavy, and it further reduces internal volume. The trapeze mechanism also adds delay to the launch timeline due to the extension of a trapeze.
For the second type of system, the rail launchers are mounted to the outer mold line to maximize the internal volume impact. However, the radar signatures of the missiles are exposed. Moreover, the rail launchers and missiles increase aerodynamic drag.
According to an embodiment herein, an aircraft comprises a weapons pod mounted to an outer mold line of the aircraft, and at least one missile rail launcher mounted entirely within and fixed to the weapons pod.
According to another embodiment herein, a missile launch system mountable to an outer mold line of an aircraft comprises an enclosure having forward and aft doors, at least one rail launcher mounted entirely within and fixed to the enclosure, and a controller and drive mechanisms for opening the aft door and then the forward door to create an airstream through the enclosure prior to missile launch.
According to another embodiment herein, a weapons pod comprises an enclosure including a sidewall and a centerline keel, and a plurality of rail launchers fixed to the centerline keel. The sidewall surrounds the centerline keel and the rail launchers.
These features and functions may be achieved independently in various embodiments or may be combined in other embodiments. Further details of the embodiments can be seen with reference to the following description and drawings.
Reference is made to
The aircraft 100 further includes a weapons pod 140 mounted to the outer mold line (OML1) of the aircraft 100. The weapons pod 140 may be mounted to a lower outer mold line (OML1) of a wing 120. In the alternative, the weapons pod 140 may be mounted to a lower outer mold line (OML1) of the fuselage 110 (e.g., the lower centerline station).
The weapons pod 140 includes an enclosure 210, at least one missile rail launcher 142 mounted entirely within and fixed to the enclosure 210, and at least one air-launched missile 144. Examples of the rail launcher 142 include the LAU-128 rail launcher and LAU-129 rail launcher. Each rail launcher 142 carries an air-launched missile 144. Examples of the air-launched missile 144 include an air-to-air missile and an air-to-surface missile. Each missile 144 is enclosed entirely by the weapons pod 140 prior to launch.
A single weapons pod 140 is illustrated in
The aircraft 100 further includes avionics 150, which is typically housed within the fuselage 110. To launch a missile 144, the avionics 150 may pass target information to the missile 144, command doors of the weapons pod 140 to open and close, command a rail of the missile's rail launcher 142 to unlatch, and command the missile's rocket motor to fire.
Additional reference is made to
The sidewall 220 is stiff enough so the enclosure 210 maintains its original shape (and radar signature) following a missile launch. The sidewall 220 may be constructed from a fairing. In the alternative, the sidewall 220 may be constructed as a torque box, which provides optimum strength and stiffness while minimizing the weight. The torque box may include thin inner skin, thin outer skin, and frames between the inner and outer skin.
Inner surfaces of the sidewall 220 may be closed out and continuous. The continuous closed-out inner surfaces provide stiffness and strength and a better aerodynamic surface for instances when the doors 230 and 240 are open. The sidewall 220 may be made of composite material, and it may have a radar-absorptive coating.
The forward and aft doors 230 and 240 may also have thin inner skin, thin outer skin, and frames between the inner and outer skin. In the alternative, the forward and aft doors 230 and 240 may be constructed as shown in
Additional reference is made to
The centerline keel 250 may run the length of the sidewall 220. This helps to transfer aerodynamic loading on the interior and exterior of the enclosure 210 to attachment points on the weapons pod 140.
The attachment points may be standard military attachment points, such as two attachment lugs 260, for attaching the weapons pod 140 to the outer mold line of the aircraft 100. The weapons pod 140 may include a MIL-STD-1760 electrical connector 270.
Additional reference is now made to
At block 520, the aircraft 100 departs for a mission. At block 530, a decision is made to fire one of the missiles 144 during the mission.
At block 540, the forward and after doors 230 and 240 are opened to create an airstream for the missile 144 prior to launch. The aft door 240 may be opened before the forward door 230 so as not to create a closed pod end that captures air and reduces aerodynamic efficiency.
At block 550, the missile 144 is powered up. When the forward and aft doors 230 and 240 reach their fully open positions, the rail launcher 142 is unlocked, and the missile's rocket motor is initiated. The missile 144 is launched from the rail launcher 142 without kinematically deploying the missile 144 outside of the enclosure 210.
The weapons pod 140 will not be damaged by the hot plume of a missile 144 during a normal launch, since the sidewall 220 runs parallel to the path of the missile 144 and will only see glancing impact from the plume. In addition, the launch event happens so quickly that the sidewall 220 will not have time to heat up and be damaged.
In the event of a hang-fire, the rocket motor is launched but stays locked to the rail of the rail launcher 142. In this event the missile plume does not damage the enclosure 210 due to sustained heating because the aft door 240 is open and the missile plume exits the weapons pod 140.
At block 560, the forward and aft doors 230 and 240 are closed immediately after the missile 144 has cleared the enclosure 210. While the doors 230 and 240 are open, the aerodynamic and radar signature characteristics of the aircraft 100 are impacted. For this reason, the door opening and closing durations are minimized.
The weapons pod 140 may be jettisoned after all missiles 144 have been fired.
In some configurations of the weapons pod 140, including the configuration illustrated in
Each door 230 and 240 may be balanced. That is, the upper and lower sections 232 and 234 of the forward door 230 are of equal size and shape, and the upper and lower sections 242 and 244 of the aft door 240 are of equal size and shape. When the upper and lower sections 232 and 234 of the forward door 230 are closed, they make contact at a midplane (waterline) of the enclosure 210. Similarly, when the upper and lower sections 242 and 244 of the aft door 240 are closed, they make contact at the midplane. Balanced door sizes help to balance upward and downward loads and moments (pitch) on the weapons pod 140. If one of the sections were eliminated or made significantly larger than the other section, the loads would be unbalanced and would drive additional load into the enclosure 210. This would increase weight and complexity of the weapons pod 140.
Reference is now made to
The aft door 240 may be opened and closed by a similar drive mechanism 610. The forward and aft doors 230 and 240 may be driven independently by separate drive mechanisms 610.
Reference is now made to
The Store Management System provides an interface between the pilot and the missiles 144. The Store Management System may communicate to the ECU 810 and the PACU 820 information including status of the missile(s) 144, and it may initiate a launch command. Once the launch command has been received, the ECU 810 and the PACU 820 control the weapons pod 140, including the rail launchers 142, and the missiles 144.
By moving the missiles 144 into the weapons pod 140, internal volume of the aircraft 100 is freed up. In addition, aerodynamic drag on the rail launchers 142 and missiles 144 is reduced.
The combination of the fixed rail launcher 142 and forward and aft doors 230 and 240 eliminates the need for kinematically deploying the missiles 144 outside of the enclosure 210 prior to launch. As a result, weight and complexity is reduced. Deployment time of the missile is faster which significantly increases the overall missile launch time. Additionally, ejection launch drives significant load into the weapons pod frame and in turn reduces load and structural complexity.
A weapons pod 140 herein is not limited to forward and aft doors 230 and 240 that open and close. In some configurations, the forward and aft doors may be frangible. The frangible doors are closed after the missiles 144 are loaded, and they are broken prior to missile launch or they are broken by the missiles. The frangible doors do not close after launch.
