DETAILED 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 .
Election/Restrictions
Applicant’s election without traverse of Invention I, claims 1-7 in the reply filed on 30 October 2025 is acknowledged.
Claim Rejections - 35 USC § 103
In the event the determination of the status of the application as subject to AIA 35 U.S.C. 102 and 103 (or as subject to pre-AIA 35 U.S.C. 102 and 103) is incorrect, any correction of the statutory basis (i.e., changing from AIA to pre-AIA ) for the rejection will not be considered a new ground of rejection if the prior art relied upon, and the rationale supporting the rejection, would be the same under either status.
The following is a quotation of 35 U.S.C. 103 which forms the basis for all obviousness rejections set forth in this Office action:
A patent for a claimed invention may not be obtained, notwithstanding that the claimed invention is not identically disclosed as set forth in section 102, if the differences between the claimed invention and the prior art are such that the claimed invention as a whole would have been obvious before the effective filing date of the claimed invention to a person having ordinary skill in the art to which the claimed invention pertains. Patentability shall not be negated by the manner in which the invention was made.
Claims 1, 2, and 5-7 are rejected under 35 U.S.C. 103 as being unpatentable over Izraelevitz et al. (U.S. Patent Application Publication 2021/0107645) in view of Kahlon et al. (U.S. Patent Application Publication 2018/0244402).
Regarding claim 1, Izraelevitz et al. discloses a drone assembly (10) comprising a drone (12) and a launch tube (78) therefor (Figs. 7A-7C; Fig. 8 – launch tube and drone; paragraph [0110] – prior to launch, SQUID (Streamlined Quick-Unfolding Investigator Drone) rests in folded state/configuration 802 inside the launch tube 708, which is generally pointed upwards), wherein in an un-deployed position of the drone assembly, the drone is stowed in a stowed position within the launch tube (Fig. 8 – launch tube and drone; paragraph [0110] – prior to launch, SQUID (Streamlined Quick-Unfolding Investigator Drone) rests in folded state/configuration 802 inside the launch tube 708, which is generally pointed upwards), in a deployed position of the launch tube, the launch tube is open and the drone is peripherally exposed and capable of passing from an un-deployed position of the drone to a deployed position of the drone when the drone still rests in the launch tube (Fig. 8 – launch tube and drone; paragraph [0110] – prior to launch, SQUID (Streamlined Quick-Unfolding Investigator Drone) rests in folded state/ configuration 802 inside the launch tube 708, which is generally pointed upwards; paragraph [0111] – after launch 804 is triggered, the compressed gas accelerates SQUID through the tub 708). However, Izraelevitz et al. fails to disclose in an un-deployed position of the drone assembly, the launch tube is closed.
Referring to the Kahlon et al. reference, Kahlon et al. discloses a drone assembly comprising a drone and a launch tube therefor, wherein in an un-deployed position of the drone assembly, the launch tube is closed (Fig. 1; paragraph [0034] – the launch tube 10 has a frontal opening 12 for takeoff and launching of the UAV that the launch tube body 11 contains – this opening is normally closed by a square-shaped cover 14).
Therefore, it would have been obvious to one of ordinary skill in the art before the effective filing date of the invention to have had the launch tube be closed when it is an un-deployed position of the drone assembly as disclosed by Kahlon et al. in the drone assembly disclosed by Izraelevitz et al. in order to prevent the drone from being damaged while being stored in the tube.
Regarding claim 2, Izraelevitz et al. in view of Kahlon et al. discloses all of the limitations as previously discussed with respect to claim 1 including that wherein the drone (12) comprises a generally cylindrical frame (14) and a longitudinal axis (A), the frame comprises four beams (16) that extend between a lower base (18) and an upper base (20), an arm support (28) is connected between each beam and the upper base, an arm (30) is connected between each two adjacent arm supports, each arm is rotatable with respect to its adjacent arm supports around and arm axis (B) that is perpendicular to a plane passing through the longitudinal axis and through the arm (Izraelevitz et al.: Figs. 1A and 1B; abstract – three or more foldable arms are attached to the central body frame via a hinge and exist in two states – a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis; paragraph [0044] – Fig. 1A illustrates a design of a SQUID in different stages in accordance with one or more embodiments of the invention – the different stages are illustrated from left to right: ballistic configuration view 102, multirotor configuration view 104, and section view 106 with a hinge zoom/closer look 108 – similarly, Fig. 1B illustrates the key design elements of the design from a launch/ballistic configuration 102 to a deployed/multirotor configuration section view 106 in accordance with one or more embodiments of the invention), wherein in an un-deployed position of the drone, the arms are positioned parallel to each other and to the longitudinal axis (Izraelevitz et al.: Figs. 1A and 1B; abstract – three or more foldable arms are attached to the central body frame via a hinge and exist in two states – a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis; paragraph [0044] – Fig. 1A illustrates a design of a SQUID in different stages in accordance with one or more embodiments of the invention – the different stages are illustrated from left to right: ballistic configuration view 102, multirotor configuration view 104, and section view 106 with a hinge zoom/closer look 108 – similarly, Fig. 1B illustrates the key design elements of the design from a launch/ballistic configuration 102 to a deployed/multirotor configuration section view 106 in accordance with one or more embodiments of the invention), and in a deployed position of the drone, the arms are perpendicular to the longitudinal axis (Izraelevitz et al.: Figs. 1A and 1B; abstract – three or more foldable arms are attached to the central body frame via a hinge and exist in two states – a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis; paragraph [0044] – Fig. 1A illustrates a design of a SQUID in different stages in accordance with one or more embodiments of the invention – the different stages are illustrated from left to right: ballistic configuration view 102, multirotor configuration view 104, and section view 106 with a hinge zoom/closer look 108 – similarly, Fig. 1B illustrates the key design elements of the design from a launch/ballistic configuration 102 to a deployed/multirotor configuration section view 106 in accordance with one or more embodiments of the invention).
Regarding claim 5, Izraelevitz et al. in view of Kahlon et al. discloses all of the limitations as previously discussed with respect to claim 1 including that wherein the drone (12) comprises at least one camera (74) that provides video images and/or thermal video images (Izraelevitz et al.: Fig. 6 – camera 632; paragraph [0088] – camera 632; paragraph [0092] – camera 632 (e.g., FLIR CHAMELEON3); paragraph [0149] – further use cases include use in applications ranging from farmland and structural inspection to consumer platforms for personal video - take photos – investigate intrusions on perimeter of a fixed protected area).
Regarding claim 6, Izraelevitz et al. in view of Kahlon et al. discloses all of the limitations as previously discussed with respect to claim 1 including that wherein the drone (12) is provided with built-in Al for autonomously controlling launch, ascent, navigation, hovering, and descent to landing, and wherein the built-in Al uses multiple sensors for navigation, including motion sensors for inertial navigation, camera looking at ground for optical flow, and object anchoring and identification for navigation (Izraelevitz et al.: Fig. 6 – onboard computer 614 (e.g., TX2); paragraph [0088] – the layout of key components is illustrated in Fig. 6 – onboard computer 614 (e.g., TX2) – the onboard computer 614 may receive input from various sensors 632-638 – further, the onboard camera 614 may include a processor, memory, and/or other components that enable the computer 636 to execute a set of instructions thereby autonomously stabilizing the vehicle 600 and/or controlling vehicle flight; paragraph [0092] – vehicle embodiment 2 also requires a perception system comprising a camera 632, rangefinder 634, IMU/barometer 636, and onboard computer 614 to achieve full autonomous stabilization; paragraph [0124] – active stabilization; paragraph [0161] – an autonomy pipeline that carries the platform from launch detection to full 6-degree of freedom stabilization using only onboard sensing (IMU, barometer, rangefinder, and camera) and without the need for GPS; a TX2 computer is a fast, power-efficient embedded AI computing device).
Regarding claim 7, Izraelevitz et al. in view of Kahlon et al. discloses all of the limitations as previously discussed with respect to claim 1 including that wherein the launch tube has a power switch (112) and an arming and deployment switch (116) that enables launching of the drone even if no mobile phone, computer, tablet computer, or laptop computer are connected or paired to the drone (Kahlon et al.: Fig. 3; paragraph [0035] – referring now also to Fig. 3, the rear end portion 16 may include a safety mechanism means 31 which is used to help prevent an accidental launching of a UAV in the pneumatic launcher 10 and helping to insure safer handling – the rear end portion 16 may further include a trigger 32 and/or a launching mechanism – the safety mechanism means 30 can include a safety pin 31 or a switch, a button, or a lever that when set to the “safe” position, prevents the activation of the pneumatic launcher 10 – the safety mechanisms 31 can be a block or latch that prevents the trigger 32 and/or launching mechanism from moving – the rear end portion 16 may further includes an electrical switch 35 for electrically activating the UAV electrical power source(s)).
Allowable Subject Matter
Claims 3 and 4 are objected to as being dependent upon a rejected base claim, but would be allowable if rewritten in independent form including all of the limitations of the base claim and any intervening claims.
The following is a statement of reasons for the indication of allowable subject matter: Prior art, singularly or in combination, fails to teach or fairly suggest, in combination with all of the other elements claimed:
wherein each arm comprises, in an inward portion (54) thereof, a toothed portion (56) that extends at a sector of 90-degrees,an operating pin (58) is positioned between the toothed portions of the arms, the operating pin has a flat pin head (60) and four toothed racks (62) extending downwardly therefrom, each toothed rack conforms in shape and position to a toothed portion of an arm that is in contact therewith, a tensioning bolt (64), having a bolt head (66) and a threaded portion (68) extending upwardly from the bolt head, is threadingly engaged into a lower portion (70) of the operating pin, an activating spring (72) is compressed between the bolt head and the lower portion of the operating pin, wherein in the deployed position of the launch tube, a tension of the activating spring urges the operating pin to a downward movement until the pin head abuts against the upper base of the drone, and wherein during the downward movement of the operating pin, each of the four toothed racks rotates a mating toothed portion of an arm, and, each arm rotates a 90-degrees rotation about its arm axis, and the drone gets into a deployed position (dependent claim 3, which depends from claims 1 and 2; claim 4 depends from claim 3).
Conclusion
The prior art made of record and not relied upon is considered pertinent to applicant's disclosure.
Gautier (U.S. Patent Application Publication 2025/0197039) discloses a device for pneumatic launching of a drone that includes a launch tube, a pressurization chamber situated at the rear of the tube, and a device for temporarily closing the passage opening. The temporary closing device is arranged to change from a closed configuration to an open configuration instantaneously under the action of the gas pressure inside said chamber, after the latter has reached a trigger pressure, and the cross section of the passage opening is sufficiently large that, instantaneously with the change to the open configuration, the gas pressure prevailing in the chamber and the space located behind the drone, then in communication with each other, is the desired launching pressure for the drone (abstract).
Chaudhari (WO 2024/171045 A1) discloses an underwater an unmanned aerial vehicles (UAVs) launching system (WO) that comprises a torpedo (launch) tube (Figs. 2 and 3).c. Kuperman (EP 3908516 B1) discloses a system and method for launching or deploying a capsule containing an Unmanned Aerial Vehicle (UAV) and releasing the UAV from the capsule into the air (Figs. 1 and 1A; paragraph [0018]).
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/HEATHER R JONES/Primary Examiner, Art Unit 2481
November 12, 2025