A mission planning method for use with a weapon is disclosed. The method comprises: obtaining a first training data set describing the performance of the weapon; using the first training data set and a Gaussian Process (GP) or Neural Network to obtain a first surrogate model giving a functional approximation of the performance of the weapon; and providing the first surrogate model to a weapons system for use in calculating a performance characteristic of the weapon during combat operations.

A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s).

A flying vehicle is disclosed with a projectile module or component that contains a projectile for projecting at another flying device. The flying vehicle receives an identification of a target flying device and applies a projectile model which generates a determination that indicates whether a projectile, if fired from the projectile component, the projectile will hit the target flying device. The projectile model taking into account one or more of a wind modeling in an area around the flying vehicle based on an inference of wind due to a tilt of the flying vehicle, a projected path of the target device based on its identification and a drag on the projectile as it deploys from the projectile component. When the determination indicates that the projectile will hit the targeted device according to a threshold value, the flying vehicle fires the projectile at the targeted flying device.

A navigation system includes a star camera having a field of view. The star camera includes a sun shields that selectively block portions of the star camera's field of view, to prevent unwanted light, such as light from the sun or moon, reaching image sensors of the star cameras. Some sun shields include x-y stages or r-θ stages to selectively position a light blocker to block the unwanted light. Some sun shields use positionable partially overlapping orthogonally polarized filters to block the unwanted light. Some sun shields use counter-wound spiral windows that are selectively rotated to block the unwanted light. Some sun shields a curved surface that defines a plurality of apertures fitted with individual mechanical or electronic shutters.

A computer implemented method for integrating a platform, different stores, and/or carriage racks is implemented in an electronics control system that is communicatively couplable to each of the platform, the different stores, and/or the carriage racks. The computer implemented method includes defining parameters for a plurality of predetermined electrical interfaces for predetermined platforms, stores, and carriage racks, and message sets corresponding thereto, identifying electrical interfaces of the platform, at least one store and/or at least one carriage rack based on the defined parameters, communicating different messages between the platform, the store and/or the carriage rack without affecting an Operational Flight Program (OFP) of the platform, with each communication between the platform, and the store and/or the carriage rack being independent, translating messages between the platform and the store and/or the carriage rack, and controlling operation of the carriage rack and/or the store based on the messages.

A technique of managing communications among multiple modules of a munition interconnected using a computer network includes receiving, by a first module of the munition, a first set of messages from a second module of the munition. The first set of messages is received in a first protocol, the first protocol being used for communicating among the modules of the munition over the computer network. The technique further includes translating, by an interface assembly of the first module, the first set of messages in the first protocol into a second set of messages in a second protocol. The second protocol is a native protocol of the first module and is different from the first protocol. The technique still further includes providing the second set of messages from the interface module to an operational component of the first module, the operational component then responding to the second set of messages for performing a function of the munition.

A munitions interface adapter including a rail adapter body. A plurality of mounting shoes may be coupled to the rail adapter body, and configured to mechanically couple the rail adapter body to a munitions rail of an installed munitions interface. A fire control connector may be configured to communicatively couple with an installed munitions fire control system. An adapter control interface may be included for adapting fire control signals from the installed munitions fire control system to an adapted munitions fire control signals. One or more adapted munitions deployment fixtures may be positioned on the rail adapter body. The one or more adapted munitions deployment fixtures are configured to retain and deploy one or more adapted munitions.

A flying vehicle is disclosed with a projectile module or component that contains a projectile for projecting at another flying device. The flying vehicle receives an identification of a target flying device and applies a projectile model which generates a determination that indicates whether a projectile, if fired from the projectile component, the projectile will hit the target flying device. The projectile model taking into account one or more of a wind modeling in an area around the flying vehicle based on an inference of wind due to a tilt of the flying vehicle, a projected path of the target device based on its identification and a drag on the projectile as it deploys from the projectile component. When the determination indicates that the projectile will hit the targeted device according to a threshold value, the flying vehicle fires the projectile at the targeted flying device.

A launched flying object is configured to continue to transmit a signal to a launching device. The launching device is configured to continue to receive the signal from the launched flying object, continue to calculate a probability when the launched flying object intercepts a target from a distance, a relative velocity and a relative angle between the launched flying object and the target, and output a final interception probability when communication from the launched flying object is stopped.

A threat degree of each of targets is numerized based on data obtained by observing the targets after launching of the flying objects. Also, the firepower of flying object is numerized based on the state of flying object after the launching. The optimal assignment of firepower is calculated based on the numerized threat degrees and firepower, and is shared by the flying objects. Each flying object intercepts the target specified based on the optimal assignment.