Control actuation system, devices and methods for missiles, munitions and projectiles
AssigneeOrbital Research Inc.
InventorsMichael Jankowski, Anthony Opperman, Vincent Cozza
Life of this patent
Estimating the term…
Abstract
Systems and methods are presented for control of munitions, missiles and projectiles in flight and more particularly with the use of activatable or deployable flow effectors that remain stowed or inactive during launch or firing, and can be actuated after launch or firing on demand. More specifically, systems and methods are presented for control of munitions, missiles, and projectiles by activating and/or deactivating a control actuation system (CAS) based on measurements of an inertial measurement unit (IMU) and sensors integrated into such IMU, the IMU and sensors being at least part of a configurable guidance sensor suite (CGSS).
Claims14
A flight control system for missiles, munitions, or projectiles comprising:
- a control actuation system (CAS) comprising at least one deployable flow effector or control surface, and a deployment mechanism adapted to maintain a state of tension on the at least one flow effector or control surface until the tension is released and the at least one flow effector or control surface deploys, the CAS further comprising at least one position component adapted to maintain the position of the at least one flow effector or control surface in position during flight after being deployed;
- a configurable guidance sensor suite (CGSS) comprising at least one inertial measurement unit (IMU) adapted to measure flight data;
- at least one image or video sensor adapted to provide real-time image or video data;
- a transceiver adapted for two-way communication between the missile, munition, or projectile and a remote user interface;
- and
- a situational awareness subsystem comprising the at least one image or video sensor and the transceiver, the situation awareness subsystem adapted to transmit the real-time image or video data via the transceiver to a user to provide terminal guidance to the missile, munition, or projectile via the remote user interface,
- wherein the CAS, CGSS and transceiver are integrated into a single enclosure adapted to be placed within a missile, munition, or projectile body.
A missile, munition, or projectile containing a flight control system comprising:
- a missile, munition, or projectile body;
- a modular and scalable control actuation system (CAS) adapted to be placed within the body of the missile, munition, or projectile, the CAS comprising at least one deployable flow effector or control surface, and a deployment mechanism adapted to maintain a state of tension on the at least one flow effector or control surface until the tension is released and the at least one flow effector or control surface deploys;
- a configurable guidance sensor suite (CGSS) comprising at least one accelerometer, at least one gyroscope, and at least one magnetometer, together adapted to measure flight data;
- at least one image or video sensor adapted to provide real-time image or video data;
- a transceiver adapted for two-way communication between the missile, munition, or projectile and a remote user interface;
- and
- a situational awareness subsystem comprising the at least one image or video sensor and the transceiver, the situation awareness subsystem adapted to transmit the real-time image or video data via the transceiver to a user to provide terminal guidance to the missile, munition, or projectile via the remote user interface.
A flight control system for missiles, munitions, or projectiles comprising:
- a control actuation system (CAS) comprising at least one deployable flow effector or control surface, and a deployment mechanism adapted to maintain a state of tension on the at least one flow effector or control surface until the tension is released and the at least one flow effector or control surface deploys, the CAS further comprising at least one component adapted to maintain the position of the at least one flow effector or control surface in position during flight after being deployed;
- a configurable guidance sensor suite (CGSS) comprising at least one accelerometer, at least one gyroscope, and at least one magnetometer, together adapted to measure flight data;
- at least one image or video sensor adapted to provide real-time image or video data;
- a transceiver adapted for two-way communication between the missile, munition, or projectile and a remote user interface;
- and
- a situational awareness subsystem comprising the at least one image or video sensor and the transceiver, the situation awareness subsystem adapted to transmit the real-time image or video data via the transceiver to a user to provide terminal guidance to the missile, munition, or projectile via the remote user interface,
- wherein the CAS, CGSS and transceiver are integrated into a single enclosure adapted to be placed within a missile, munition, or projectile body.
Dependencies are inferred from the claim text.