Office Action 1: Ex Parte Quayle Action (2024-11-27)

CLAIMS:
CLAIMS

1\. A projectile, comprising:
an exterior surface;
a field sensor configured to determine a relative rotation of the exterior surface with respect to an external field;
a motor, configured to have a selective mechanical response to a control signal; and
an automated controller, configured to generate the control signal, selectively dependent on feedback from the field sensor, to synchronize a phase of the mechanical response of the motor with a phase of the relative rotation of the exterior surface.

2\. The projectile according to claim 1, wherein the external field is a static magnetic field, and the field sensor is configured to determine the relative rotation of the exterior surface with respect to the static magnetic field.

3\. The projectile according to claim 1, wherein the field sensor is configured to determine the relative rotation of the exterior surface with respect to a radio frequency emission from the external field.

4\. The projectile according to claim 1, wherein the automated controller is further configured to receive a steering signal, to control a relationship of the phase of the mechanical response of the motor with respect to the phase of the relative rotation of the exterior surface.

5\. The projectile according to claim 1, wherein the automated controller is further configured to receive a transmitted modulated remote control steering signal, conveying information to control a relationship of the phase of the mechanical response of the motor with respect to the phase of the relative rotation of the exterior surface.

6\. The projectile according to claim 1, wherein the exterior surface has a radial axis of symmetry, and the motor comprises a rotor having an axis of rotation orthogonal to the radial axis of symmetry.

7\. The projectile according to claim 6, wherein the rotor selectively actuates an aerodynamic feature synchronized with an angle of rotation of the exterior surface with respect to the external field.
8\. The projectile according to claim 1, further comprising an activity sensor, wherein the automated controller shuts down the motor selectively dependent on an output of the activity sensor.

9\. The projectile according to claim 1, further comprising an air flow sensor configured to sense an air flow around the exterior surface, wherein the automated controller is further selectively responsive to an output of the air flow sensor.

10\. The projectile according to claim 1, wherein the motor selectively modulates a spatial property of a boundary layer separation of gas surrounding the exterior surface.

11\. A method of controlling a projectile having an exterior surface, comprising:
determining a relative rotation of the exterior surface with respect to an external field with a field sensor; and
driving a motor a selectively responsive to an automated control signal, selectively dependent on feedback of the determined relative rotation from the field sensor, to synchronize a phase of a response of the motor with a
phase of the relative rotation of the surface.

12\. The method according to claim 11, wherein the exterior field comprises at least one of an electromagnetic field and a magnetic field, and the field sensor comprises at least one of an electromagnetic field sensor and a magnetic field sensor that determines the relative rotation of the surface with respect to the field.

13\. The method according to claim 11 further comprising:
receiving a wirelessly communicated steering signal, and
controlling a relationship of the phase of the mechanical response of the motor with respect to the phase of the relative rotation of the surface based on the steering signal.

14\. The method according to claim 11, wherein the external surface has a radial axis of symmetry, and the motor rotates a rotor having an axis of rotation orthogonal to the radial axis of symmetry.

15\. The method according to claim 14, further comprising selectively actuating an aerodynamic element withy a rotor of the motor, synchronized with an angle of rotation of the exterior surface with respect to the exterior field.
16\. The method according to claim 11, further comprising automatically operating and deactivating the motor selectively dependent on an output of an activity sensor.

17\. The method according to claim 11, further comprising sensing an air flow around the exterior surface, and
selectively controlling the motor dependent on the sensed air flow.

18\. A projectile, comprising:
an exterior surface having a radial axis of symmetry, the projectile being dynamically balanced for rotation about the radial axis of symmetry;
a motor, having a movement about an axis which is non-parallel with the radial axis of symmetry, driven in response to a motor control signal; and
an automated controller, configured to generate the motor control signal, to synchronize a phase of the motor about the axis with a phase of a rotation of the exterior surface about the radial axis of symmetry.

19\. The projectile according to claim 18, further comprising a magnetometer configured to determine a relative rotation of the exterior surface with respect to the earth's magnetic field.

20\. The projectile according to claim 18, wherein the automated controller is configured to determine a launch state of the projectile, and to generate the motor control signal further dependent on the launch state. SMH-215.4- 107- SMH-215.4- 108- SMH-215.4- 109- 5 5 10 15 15 20 25 30 30

OFFICE ACTION:
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
DETAILED CORRESPONDENCE
This is the first Office Action on the merits of Application 17/580,586 filed on 1/20/22. Claims 1-20 are pending.
Claim Objections
Claims 1-20 are objected to because of the following informalities:
Claim 1
Line 4: “a motor, configured” should be amended as -- a motor configured --.
Line 5: “controller, configured” should be amended as -- controller configured --.
Claim 2
Line 1: “field, and” should be amended as -- field and --.
Claim 6
Line 1: “symmetry, and” should be amended as -- symmetry and --.
Claim 11
Line 3: “a motor a” should be amended as -- a motor --.
Claim 15
Line 1: “element withy” should be amended as -- element with --.
Claim 17
Line 1: “surface, and” should be amended as -- surface and --.
Claim 18
Line 6: “controller, configured” should be amended as -- controller configured --.
Appropriate correction is required.
Allowable Subject Matter
Claims 1-20 would be allowable if rewritten to overcome the objections stated above.
The following is a statement of reasons for the indication of allowable subject matter: The prior art of record fails to show or render obvious an automated controller, configured to generate the control signal, selectively dependent on feedback from the field sensor, to synchronize a phase of the mechanical response of the motor with a phase of the relative rotation of the exterior surface in combination with the remaining limitations of the claims.
Conclusion
The prior art made of record and not relied upon is considered pertinent to applicant's disclosure.
Davidson ‘002 teaches an aircraft with rotating outer shell.
Epperson Jr ‘150 teaches a gyroscopically steerable bullet.
Larkin ‘216 teaches a segmented projectile with de-spun joint.
This application is in condition for allowance except for the following formal matters:
See claim objections stated above.
Prosecution on the merits is closed in accordance with the practice under Ex parte Quayle, 25 USPQ 74, 453 O.G. 213, (Comm’r Pat. 1935).
A shortened statutory period for reply to this action is set to expire TWO (2) MONTHS from the mailing date of this letter. Extensions of time may be granted under  37 CFR 1.136 but in no case can any extension carry the date for reply to this Office action beyond the maximum period of SIX MONTHS set by statute (35 U.S.C. 133).

APPLICANT REBUTTAL: REMARKS
Claims 1-20 are in the application.
The claims are amended according to he Examiner's requests.
The specification is amended to correct typographical and grammatical errors. No new matter has been entered.
Recognizing that Internet communications are not secure, I hereby authorize the USPTO to communicate with the undersigned and practitioners in accordance with 37 CFR 1.33 and 37 CFR 1.34 concerning any subject matter of this application by video conferencing, instant messaging, or electronic mail. I understand that a copy of these communications will be made of record in the application file.
Respectfully submitted, /Steven M. Hoffberg/Steven M. HoffbergRegistration No.: 33,511HOFFBERG & ASSOCIATES29 Buckout RoadWest Harrison, NY 10604(914) 949-2300

NEXT OFFICE ACTION: Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
DETAILED CORRESPONDENCE
This is the second Office Action on the merits of application no. 17/580,586 filed 1/20/22. Claims 1-20 are pending.
EXAMINER’S AMENDMENT
An examiner’s amendment to the record appears below. Should the changes and/or additions be unacceptable to applicant, an amendment may be filed as provided by 37 CFR 1.312. To ensure consideration of such an amendment, it MUST be submitted no later than the payment of the issue fee.
The application has been amended as follows:
Claim 15
Line 3: “field.SMH-215.4- 109-“ has been amended as -- field. --.
Allowable Subject Matter
Claims 1-20 are allowed.
The following is an examiner’s statement of reasons for allowance:
Regarding claim 1, the prior art of record fails to show or render obvious an automated controller configured to generate the control signal, selectively dependent on feedback from the field sensor, to synchronize a phase of the mechanical response of the motor with a phase of the relative rotation of the exterior surface in combination with the remaining limitations of claim 1.
Regarding claim 11, the prior art of record fails to show or render obvious driving a motor selectively responsive to an automated control signal, selectively dependent on feedback of the determined relative rotation from the field sensor, to synchronize a phase of a response of the motor with a phase of the relative rotation of the surface in combination with the remaining limitations of claim 11.
Regarding claim 18, the prior art of record fails to show or render obvious an automated controller configured to generate the motor control signal, to synchronize a phase of the motor about the axis with a phase of a rotation of the exterior surface about the radial axis of symmetry in combination with the remaining limitations of claim 18.
Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee.  Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Response to Arguments
Applicant’s arguments filed 12/4/24 with respect to the claim objections has been fully considered and are persuasive. The objection of the claims has been withdrawn.
Conclusion

CITED REFERENCE SUMMARIES: Ref US20160376002A1: Claims:
An aircraft comprising: a main body defining a passenger compartment therein which is arranged to receive a plurality of passengers therein; an upper shell portion supported on the main body so as to be rotatable relative to the main body about a vertically oriented central axis of the main body, the upper shell portion spanning radially outward from the central axis across a top side of the main body to an outer perimeter edge of the upper shell portion; a lower shell portion supported on the main body so as to be rotatable relative to the main body about the central axis of the main body, the lower shell portion spanning radially outward from the central axis across a bottom side of the main body to an outer perimeter edge of the lower shell portion which is in proximity to the outer perimeter edge of the upper shell portion; a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another; the lower shell portion including a lower thrust opening communicating therethrough at the central axis of the main body; and an engine assembly supported on the main body in communication with the lower thrust opening and being arranged to provide upward thrust to the main body.
a main body defining a passenger compartment therein which is arranged to receive a plurality of passengers therein;
an upper shell portion supported on the main body so as to be rotatable relative to the main body about a vertically oriented central axis of the main body, the upper shell portion spanning radially outward from the central axis across a top side of the main body to an outer perimeter edge of the upper shell portion;
a lower shell portion supported on the main body so as to be rotatable relative to the main body about the central axis of the main body, the lower shell portion spanning radially outward from the central axis across a bottom side of the main body to an outer perimeter edge of the lower shell portion which is in proximity to the outer perimeter edge of the upper shell portion;
a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another;
the lower shell portion including a lower thrust opening communicating therethrough at the central axis of the main body; and
an engine assembly supported on the main body in communication with the lower thrust opening and being arranged to provide upward thrust to the main body.
The aircraft according to claim 1 wherein the upper shell portion is fully enclosed and fully spans a top side of the main body between the central axis of the main body and the outer perimeter edge of the upper shell portion.
The aircraft according to claim 1 wherein the lower shell portion fully spans a bottom side of the main body and is fully enclosed between the lower thrust opening and the outer perimeter edge of the lower shell portion.
The aircraft according to claim 1 wherein the upper shell portion includes a flange portion extending radially inward from the outer perimeter edge of the upper shell portion in overlapping configuration relative to the outer perimeter edge of the lower shell portion.
The aircraft according to claim 1 wherein the engine assembly provides sole thrust during take-off.
The aircraft according to claim 1 further comprising at least one idler wheel supported in rolling contact with both the upper shell portion thereabove and the lower shell portion therebelow, wherein the motor assembly directly drives rotation of one of the shell portions and another one of the shell portions is driven to rotate by said at least one idler wheel.
The aircraft according to claim 6 wherein the motor assembly is connected to the upper shell portion adjacent to a top side of the main body and directly drives the upper shell portion relative to the main body.
The aircraft according to claim 6 wherein said at least one idler wheel comprises a plurality of idler wheels at evenly spaced positions in a circumferential direction.
The aircraft according to claim 6 wherein said at least one idler wheel is supported on the main body for free floating movement relative to the main body in a vertical direction.
The aircraft according to claim 6 wherein said at least one idler wheel comprises a pneumatically inflated wheel of resilient material.
The aircraft according to claim 6 wherein said at least one idler wheel is in rolling contact with both an annular bearing surface on the upper shell portion in proximity to the outer perimeter edge thereof and an annular bearing surface on the lower shell portion in proximity to the outer perimeter edge thereof.
The aircraft according to claim 6 wherein the upper and lower shell portions are vertically adjustable relative to one another and wherein there is provided at least one hydraulic actuator acting between the upper and lower shell portions so as to be arranged to apply a hydraulic clamping force to diametrically opposed sides of said at least one idler wheel.
The aircraft according to claim 1 wherein the upper shell portion is vertically adjustable in position relative to the main body.
The aircraft according to claim 13 further comprising an upper support member vertically slidable relative to the main body adjacent the top end thereof at the central axis and a plurality of bearings coupled between the upper support member and the upper shell portion.
The actuator according to claim 14 further comprising a hydraulic actuator which is linear acting and which is coupled between the upper support member and the main body to control vertical position of the upper shell portion relative to the main body.
The aircraft according to claim 13 further comprising a gear supported on one of the main body and the upper shell portion, a rack supported on the other one of the main body and the upper shell portion in meshing engagement with the gear as the upper shell portion is vertically adjusted relative to the main body, and a lock member arranged to selectively engaged between the gear and the lock so as to lock the vertical position of the upper shell portion relative to the main body at a selected position.
The aircraft according to claim 1 wherein the lower shell portion is vertically adjustable relative to the main body.
The aircraft according to claim 17 further comprising a lower support member which is supported on the main body at a bottom end thereof for vertical sliding movement at the central axis, and bearings coupling the lower support member to the lower shell portion along an annular path about the lower thrust opening.
An aircraft comprising: a main body defining a passenger compartment therein which is arranged to receive a plurality of passengers therein; an upper shell portion supported on the main body so as to be rotatable relative to the main body about a vertically oriented central axis of the main body, the upper shell portion spanning radially outward from the central axis across a top side of the main body to an outer perimeter edge of the upper shell portion; a lower shell portion supported on the main body so as to be rotatable relative to the main body about the central axis of the main body, the lower shell portion spanning radially outward from the central axis across a bottom side of the main body to an outer perimeter edge of the lower shell portion which is in proximity to the outer perimeter edge of the upper shell portion; a motor assembly operatively connected between the upper shell portion, the lower shell portion and the main body so as to be arranged to drive rotation of the upper and lower shell portions relative to the main body in opposing directions relative to one another; the lower shell portion including a lower thrust opening communicating therethrough at the central axis of the main body; and an engine assembly supported on the main body in communication with the lower thrust opening and being arranged to provide upward thrust to the main body; the upper shell portion being fully enclosed and fully spanning a top side of the main body between the central axis of the main body and the outer perimeter edge of the upper shell portion; the lower shell portion fully spanning a bottom side of the main body and being fully enclosed between the lower thrust opening and the outer perimeter edge of the lower shell portion; and an outer surface of the aircraft being fully defined by the upper shell portion and the lower shell portion such that the lower thrust opening is the only opening in the outer surface.
an engine assembly supported on the main body in communication with the lower thrust opening and being arranged to provide upward thrust to the main body;
the upper shell portion being fully enclosed and fully spanning a top side of the main body between the central axis of the main body and the outer perimeter edge of the upper shell portion;
the lower shell portion fully spanning a bottom side of the main body and being fully enclosed between the lower thrust opening and the outer perimeter edge of the lower shell portion; and
an outer surface of the aircraft being fully defined by the upper shell portion and the lower shell portion such that the lower thrust opening is the only opening in the outer surface.
An aircraft comprising: a main body defining a passenger compartment therein which is arranged to receive a plurality of passengers therein; an upper shell portion supported on the main body so as to be rotatable relative to the main body about a vertically oriented central axis of the main body, the upper shell portion spanning radially outward from the central axis across a top side of the main body to an outer perimeter edge of the upper shell portion; a lower shell portion supported on the main body so as to be rotatable relative to the main body about the central axis of the main body, the lower shell portion spanning radially outward from the central axis across a bottom side of the main body to an outer perimeter edge of the lower shell portion which is in proximity to the outer perimeter edge of the upper shell portion; a motor assembly connected to the upper shell portion so as to be arranged to drive rotation of the upper shell portion relative to the main body; at least one idler wheel supported in rolling contact with both the upper shell portion thereabove and the lower shell portion therebelow such that the lower shell portion is driven to rotate relative to the main body in an opposing direction relative to the upper shell portion as the upper shell portion is driven to rotate relative to the main body; the lower shell portion including a lower thrust opening communicating therethrough at the central axis of the main body; and an engine assembly supported on the main body in communication with the lower thrust opening and being arranged to provide upward thrust to the main body.
a motor assembly connected to the upper shell portion so as to be arranged to drive rotation of the upper shell portion relative to the main body;
at least one idler wheel supported in rolling contact with both the upper shell portion thereabove and the lower shell portion therebelow such that the lower shell portion is driven to rotate relative to the main body in an opposing direction relative to the upper shell portion as the upper shell portion is driven to rotate relative to the main body;
Ref US4431150A: Claims:
A steerable bullet comprising: a projectile body having a longitudinal axis; a gyro mounted within the projectile body including a rotor and means for supporting the rotor for rotation about a spin axis initially coincident with the projectile axis and pivotable away from the projectile axis; means for spinning the rotor; means for providing steering commands; and means responsive to the steering commands for pivoting the spin axis of the rotor relative to the projectile axis during aerial flight of the projectile body so that the resulting precession torque of the spinning rotor will induce a change in the angle of attack between the projectile axis and the actual velocity vector of the projectile body whereby midcourse trajectory shaping will be achieved.
a projectile body having a longitudinal axis;
a gyro mounted within the projectile body including a rotor and means for supporting the rotor for rotation about a spin axis initially coincident with the projectile axis and pivotable away from the projectile axis;
means for spinning the rotor;
means for providing steering commands; and
means responsive to the steering commands for pivoting the spin axis of the rotor relative to the projectile axis during aerial flight of the projectile body so that the resulting precession torque of the spinning rotor will induce a change in the angle of attack between the projectile axis and the actual velocity vector of the projectile body whereby midcourse trajectory shaping will be achieved.
A steerable bullet according to claim 1 wherein the supporting means of the gyro includes: a post; a tiltable yoke mounted on one end of the post and extending through a hole extending centrally through the rotor; a bearing assembly rotatably mounting the rotor to the yoke.
a tiltable yoke mounted on one end of the post and extending through a hole extending centrally through the rotor;
a bearing assembly rotatably mounting the rotor to the yoke.
A steerable bullet according to claim 2 wherein the pivoting means includes; a linear actuator responsive to the steering commands; and linkage means for operatively coupling the yoke and the linear actuator.
a linear actuator responsive to the steering commands; and
linkage means for operatively coupling the yoke and the linear actuator.
A steerable bullet according to claim 1 wherein the means for spinning the rotor comprises means for transferring angular momentum from the projectile body to the rotor.
A steerable bullet according to claim 4 wherein the transferring means includes: means for locking the rotor to the projectile body with the spin axis and the projectile axis substantially coincident so that the rotor will be spun when the projectile body is spun about its axis during launch; means for unlocking the rotor after the projectile body and rotor have been spun during launch so that the rotor can spin freely; and means for de-spinning the projectile body relative to the rotor.
means for locking the rotor to the projectile body with the spin axis and the projectile axis substantially coincident so that the rotor will be spun when the projectile body is spun about its axis during launch;
means for unlocking the rotor after the projectile body and rotor have been spun during launch so that the rotor can spin freely; and
means for de-spinning the projectile body relative to the rotor.
A steerable bullet according to claim 5 wherein the de-spinning means comprises a jet mounted in the projectile body for generating a thrust for transferring angular momentum to the rotor.
A steerable bullet according to claim 1 wherein the means for providing steering commands includes: an on-board homing sensor.
an on-board homing sensor.
A steerable bullet according to claim 1 wherein the means for providing steering commands includes: an antenna mounted at the rear of the projectile body for receiving up-link data signals from a remote error sensor; and on-board electronic interface circuit means connected to the antenna for processing the up-link data signals to generate steering commands therefrom and for applying the steering commands to the rotor spin axis pivoting means.
an antenna mounted at the rear of the projectile body for receiving up-link data signals from a remote error sensor; and
on-board electronic interface circuit means connected to the antenna for processing the up-link data signals to generate steering commands therefrom and for applying the steering commands to the rotor spin axis pivoting means.
A steerable bullet according to claim 2 wherein the rotor spin axis pivoting means includes a spring and damper combination for allowing the spin axis and projectile axis to realign once the desired velocity vector for the projectile body determined by the steering command has been achieved.
A steerable bullet according to claim 1 wherein the rotor spin axis pivoting means includes means for selectively and independently pivoting the spin axis in two orthogonal control planes whose intersection coincides with the projectile axis.
A steerable bullet according to claim 1 wherein the means for spinning the rotor comprises: a plurality of notches spaced circumferentially about the rotor to define a turbine; and means for discharging a stream of pressurized gas against the notches.
a plurality of notches spaced circumferentially about the rotor to define a turbine; and
means for discharging a stream of pressurized gas against the notches.
Ref US5139216A: Claims:
A projectile for use in conjunction with an information system which delivers projectile spin rate information and deflection commands to the projectile, said projectile comprising: (a) a first segment defining a first longitudinal axis and a substantially longitudinally aligned second segment jointed thereto with a variable angle hinge joint; (b) said first segment mounting a joint module which includes said hinge joint and also includes angle drive means to vary the angle of said hinge joint; (c) said joint module being rotational inside said first segment, and including rotational drive means for rotating said module about the longitudinal axis of said first segment; and (d) control means mounted within said projectile and being operative with said information system to command said angle drive means to vary the angle of said hinge joint and to control said rotational drive means to rotate said module at a speed substantially equal and opposite to the rate of any rotation of said first segment to cause same to establish an orientation for said hinge joint which is substantially fixed in terms of earth coordinates.
(a) a first segment defining a first longitudinal axis and a substantially longitudinally aligned second segment jointed thereto with a variable angle hinge joint;
(b) said first segment mounting a joint module which includes said hinge joint and also includes angle drive means to vary the angle of said hinge joint;
(c) said joint module being rotational inside said first segment, and including rotational drive means for rotating said module about the longitudinal axis of said first segment; and
(d) control means mounted within said projectile and being operative with said information system to command said angle drive means to vary the angle of said hinge joint and to control said rotational drive means to rotate said module at a speed substantially equal and opposite to the rate of any rotation of said first segment to cause same to establish an orientation for said hinge joint which is substantially fixed in terms of earth coordinates.
Structure according to claim 1 wherein said projectile has a forward travel direction and each of said segments is configured such that it will support its own weight in flight and that its center of mass is substantially aligned, with its center of aerodynamic lift when traveling substantially in said forward travel direction.
Structure according to claim 1 wherein said drive means is a motor having a drive shaft substantially aligned with said first segment longitudinal axis and connected to said joint module.
Structure according to claim 1 wherein said second segment defines a second longitudinal axis and said hinge joint provides said second segment freedom of movement to
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