Integrated roll control and power supply system and method

Claim 2

An integrated roll control and power supply system for a missile, comprising: (a) a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) means for sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and being operable to generate output signals corresponding thereto; (c) a pair of power flow control (PFC) units connected to said sensing means and coupled between said FMG units and an electrical load in the missile, said PFC units being operable to receive said output signals from said sensing means and to cause selected dissipation of the roll torque of said FMG units by supplying electrical power from said FMG units to the electrical load in the missile and thereby produce roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; and (d) a first and second means coupled to the power flow control units for transferring energy directly between the two FMG units.

Claim 3

The integrated system of claim 1 wherein said sensing means is an accelerometer.

Claim 4

The integrated system of claim 1 further comprising: first and second means coupled to said PFC units for receiving electrical power from said PFC units and dissipating said electrical power as heat; and first and second means coupled to said PFC units and engagable with said FMG units for receiving electrical power from said PFC units and engaging said FMG units to correspondingly dissipate said roll torque thereof.

Claim 5

The integrated system of claim 3 wherein said first and second dissipating means are a pair of resistance heaters.

Claim 6

The integrated system of claim 3 wherein said first and second engaging means are a pair of clutch/brake devices.

Claim 7

The integrated system of claim 3 wherein said PFC units are operable to cause selected dissipation of the roll torque of said FMG units by also supplying electrical power from said FMG units to said first and second dissipating means and first and second engaging means and thereby produce additional roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile.

Claim 8

An integrated roll control and power supply system for a missile, comprising: (a) a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) means for sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and being operable to generate output signals corresponding thereto; (c) a pair of power flow control (PFC) units connected to said roll sensor and coupled between said FMG units and an electrical load in the missile, said PFC units also being coupled between said FMG units and said first and second dissipating means, said PFC units being operable to receive said output signals from said roll sensor and to cause selected dissipation of the roll torque of said FMG units by supplying electrical power from the FMG units to the electrical load in the missile and to said first and second dissipating means and thereby produce roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; (d) first and second means coupled to said PFC units for receiving electrical power from said PFC units and dissipating said electrical power as heat; and (e) a first and second means coupled to the power flow control units for transferring energy directly between the two FMG units.

Claim 9

An integrated roll control and power supply system for a missile, comprising: (a) a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) means for sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and being operable to generate output signals corresponding thereto; (c) a pair of power flow control (PFC) units connected to said roll sensor and coupled between said FMG units and an electrical load in the missile, said PFC units also being coupled between said FMG units and said first and second dissipating means, said PFC units being operable to receive said output signals from said roll sensor and to cause selected dissipation of the roll torque of said FMG units by supplying electrical power from the FMG units to the electrical load in the missile and to said first and second dissipating means and thereby produce roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; (d) first and second means coupled to said PFC units for receiving electrical power from said PFC units and dissipating said electrical power as heat; and (e) a first and second means coupled to the power flow control units for transferring energy directly between the two FMG units.

Claim 10

The integrated system of claim 7 wherein said sensing means is an accelerometer.

Claim 11

The integrated system of claim 7 wherein said first and second dissipating means are a pair of resistance heaters.

Claim 12

An integrated roll control and power supply system for a missile, comprising: (a) a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) a roll sensor for sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and being operable to generate output signals corresponding thereto; (c) a pair of power flow control (PFC) units connected to said sensing means and coupled between said FMG units and an electrical load in the missile, said PFC units also being coupled between said FMG units and said first and second engaging means, said PFC units being operable to receive said output signals from said sensing means and to cause selected dissipation of the roll torque of said FMG units by supplying electrical power from the FMG units to the electrical load in the missile and to said first and second engaging means and thereby produce roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; (d) first and second means coupled to said PFC units and engagable with said FMG units for receiving electrical power from said PFC units and engaging said FMG units to correspondingly dissipate said roll torque thereof; and (e) a first and second means coupled to the power flow control units for transferring energy directly between the two FMG units.

Claim 13

An integrated roll control and power supply system for a missile, comprising: (a) a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) a roll sensor for sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and being operable to generate output signals corresponding thereto; (c) a pair of power flow control (PFC) units connected to said sensing means and coupled between said FMG units and an electrical load in the missile, said PFC units also being coupled between said FMG units and said first and second engaging means, said PFC units being operable to receive said output signals from said sensing means and to cause selected dissipation of the roll torque of said FMG units by supplying electrical power from the FMG units to the electrical load in the missile and to said first and second engaging means and thereby produce roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; (d) first and second means coupled to said PFC units and engagable with said FMG units for receiving electrical power from said PFC units and engaging said FMG units to correspondingly dissipate said roll torque thereof; and (e) a first and second means coupled to the power flow control units for transferring energy directly between the two FMG units.

Claim 14

The integrated system of claim 10 wherein said sensing means is an accelerometer.

Claim 15

The integrated system of claim 10 wherein said first and second engaging means are a pair of clutch/brake devices.

Claim 16

An integrated roll control and power supply method for a missile, comprising the steps of: (a) providing on an airframe of a missile a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and generating output signals corresponding thereto; (c) in response to said output signals, causing selected dissipation of the roll torque of said FMG units by supplying electrical power from the FMG units to the electrical load in the missile and thereby producing roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; and (d) in response to said output signals, transferring electrical power as needed from one FMG unit to the other FMG unit.

Claim 17

An integrated roll control and power supply method for a missile, comprising the steps of: (a) providing on an airframe of a missile a pair of flywheel-motor-generator (FMG) units being axially aligned with one another and respectively operable in clockwise and counterclockwise directions so as to produce bi-directional roll torque and generate electrical power; (b) sensing roll accelerations in clockwise and counterclockwise directions in an airframe of a missile and generating output signals corresponding thereto; (c) in response to said output signals, causing selected dissipation of the roll torque of said FMG units by supplying electrical power from the FMG units to the electrical load in the missile and thereby producing roll-damping torques in the airframe for control of any undesirable roll in the airframe of the missile; and (d) in response to said output signals, transferring electrical power as needed from one FMG unit to the other FMG unit.

Claim 18

The integrated method of claim 13 further comprising the step of: in response to said output signals, causing selected dissipation of the roll torque of said FMG units by also supplying electrical power from said FMG units to a pair of resistance heaters to correspondingly dissipate the electrical power as heat.

Claim 19

The integrated method of claim 13 further comprising the step of: in response to said output signals, causing selected dissipation of the roll torque of said FMG units by also supplying electrical power from said FMG units to clutch/brake devices to cause corresponding braking engagement thereof with said FMG units.

Claim 20

The integrated method of claim 15 further comprising the step of: in response to said output signals, causing selected dissipation of the roll torque of said FMG units by also supplying electrical power from said FMG units to a pair of resistance heaters to correspondingly dissipate the electrical power as heat.