Office Action 1: Non-Final Rejection (2024-12-19)
Rejection types: 102 - Lack of Novelty, 103 - Obviousness

CLAIMS:
Claims

1\. An aerial delivery system for carrying cargo from an aircraft to ground, the aerial delivery system comprising:a platform for supporting the cargo;
a main parachute for carrying the platform when the platform has exited the aircraft and is airborne and the main parachute is deployed;
a main parachute deployment line to deploy the main parachute;
an extraction parachute coupled to the platform and arranged for generating a drag force and exerting the drag force on the platform; and
a coupling arrangement switchable from an open configuration in which the main parachute deployment line is uncoupled from the extraction parachute, and a closed configuration in which the main parachute deployment line is coupled to the extraction parachute;
wherein the aerial delivery system is configured such that, when the extraction parachute exerts the drag force on the platform, the coupling arrangement is initially in the open configuration until the coupling arrangement is switched to the closed configuration to couple the main parachute deployment line to the extraction parachute.

2\. The aerial delivery system according to claim 1, comprising a coupling device to switch the coupling arrangement from the open configuration to the closed configuration.

3\. The aerial delivery system according to claim 1, comprising an extraction parachute release device arranged such that it is able to uncouple the extraction parachute from the platform when the coupling arrangement is in the open configuration such that release of the extraction parachute does not deploy the main parachute.

4\. The aerial delivery system according to claim 3, wherein the extraction parachute release device is arranged such that it is able to uncouple the extraction parachute from the platform when the coupling arrangement is in the closed configuration such that release of the extraction parachute deploys the main parachute via the coupling arrangement and the main parachute deployment line.

5\. The aerial delivery system according to claim 1, wherein the aerial delivery system comprise a unitary load path along which the drag force travels from the extraction parachute to

the platform, such that disconnection of the unitary load path removes the drag force from the extraction parachute to the platform.

6\. An extraction assembly for an aerial delivery system, the extraction assembly comprising:a coupling arrangement switchable from an open configuration to a closed configuration;
wherein the extraction assembly is arranged such that, during a drag force event comprising a drag force generated by an extraction parachute and exerted on a platform via the extraction assembly, the coupling arrangement is switched from the open configuration to the closed configuration;
wherein in the open configuration a main parachute deployment line is uncoupled from the extraction parachute, and in the closed configuration the main parachute deployment line is coupled to the extraction parachute.

7\. The extraction assembly according to claim 6, wherein the coupling arrangement comprises a first coupling portion coupleable to a second coupling portion,wherein in the open configuration of the coupling arrangement the first coupling portion is uncoupled from the second coupling portion such that the main parachute deployment line is uncoupled from the extraction parachute, and
wherein in the closed configuration of the coupling arrangement the first coupling portion is coupled to the second coupling portion such that the main parachute deployment line is coupled to the extraction parachute.

8\. The extraction assembly according to claim 7, wherein the second coupling portion comprises a clasp to retain the first coupling portion when the coupling arrangement is in the closed configuration and to release the first coupling portion when the coupling arrangement is in the open configuration.

9\. The extraction assembly according to claim 8, wherein the extraction assembly comprises a bias arrangement to bias the clasp closed.

10\. The extraction assembly according to claim 6, comprising a coupling device to switch the coupling arrangement from the open configuration to the closed configuration.

11\. The extraction assembly according to claims 10, wherein the coupling device comprises a drop arm, wherein the coupling device is arranged such that a movement of the drop arm causes the coupling arrangement to switch from the open configuration to the closed configuration.

12\. The extraction assembly according to claim 6, comprising an extraction parachute release device arranged to uncouple the extraction parachute from the platform.

13\. The extraction assembly according to claim 12, wherein the coupling arrangement comprises a first coupling portion coupleable to a second coupling portion,wherein in the open configuration of the coupling arrangement the first coupling portion is uncoupled from the second coupling portion such that the main parachute deployment line is uncoupled from the extraction parachute, and
wherein in the closed configuration of the coupling arrangement the first coupling portion is coupled to the second coupling portion such that the main parachute deployment line is coupled to the extraction parachute;
wherein the extraction parachute release device comprises:
a closed configuration wherein the extraction parachute release device retains the first coupling portion such that drag force generated by the extraction parachute is exerted on the platform via the first coupling portion, and
an open configuration wherein the extraction parachute release device releases the first coupling portion such that the extraction parachute is released from the platform.

14\. The extraction assembly according to claim 13, wherein the extraction parachute release device comprises a lever assembly configured such that:in the closed configuration of the extraction parachute release device the lever assembly retains the first coupling portion, and
in the open configuration of the extraction parachute release device the lever assembly releases the first coupling portion.

15\. The extraction assembly according to claim 14, wherein the lever assembly comprises a pair of pivotally mounted jaws configured to engage with the first coupling portion so as to retain the first coupling portion, and to disengage from the first coupling portion so as to release the first coupling portion.

16\. The extraction assembly according to claim 12, wherein the extraction parachute release device is configured to uncouple the extraction parachute from the platform in response to receiving a release force, optionally wherein the extraction assembly is configured to receive the release force via a cable.

17\. The extraction assembly according to claim 13, wherein the extraction parachute release device comprises an over centre locking device configured to lock the extraction parachute release device in the closed configuration, and to unlock so that the extraction parachute release device can move to the open configuration.

18\. The extraction assembly according to claim 12, wherein the extraction assembly is connected to an extraction parachute release assembly,wherein the extraction parachute release assembly comprises a drop arm, wherein the extraction parachute release assembly is configured to cause the extraction parachute release device to uncouple the extraction parachute from the platform in response to rotation of the drop arm.

19\. A method of airdropping cargo from an aircraft to the ground using an aerial delivery system, the aerial delivery system comprising:a platform for supporting the cargo;
a main parachute for carrying the platform when the platform has exited the aircraft and is airborne and the main parachute is deployed;
a main parachute deployment line to deploy the main parachute;
an extraction parachute coupled to the platform and arranged for generating a drag force and exerting the drag force on the platform; and
a coupling arrangement switchable from an open configuration in which the main parachute deployment line is uncoupled from the extraction parachute, and a closed configuration in which the main parachute deployment line is coupled to the extraction parachute;
the method comprising the steps of:
using the extraction parachute to exert the drag force on the platform, wherein initially the coupling arrangement is in the open configuration and the platform is in an initial position relative to the aircraft; and

wherein the coupling arrangement is switched to the closed configuration to couple the main parachute deployment line to the extraction parachute when the platform has moved under the action of the drag force from the initial position to a first position relative to the aircraft.

20\. The method according to claim 19, wherein the extraction parachute is uncoupled from the platform when the platform has moved under the action of the drag force from the first position to a second position relative to the aircraft.

OFFICE ACTION:
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 .
Claim Rejections - 35 USC § 102
The following is a quotation of the appropriate paragraphs of 35 U.S.C. 102 that form the basis for the rejections under this section made in this Office action:
A person shall be entitled to a patent unless –
(a)(1) the claimed invention was patented, described in a printed publication, or in public use, on sale, or otherwise available to the public before the effective filing date of the claimed invention.
(a)(2) the claimed invention was described in a patent issued under section 151, or in an application for patent published or deemed published under section 122(b), in which the patent or application, as the case may be, names another inventor and was effectively filed before the effective filing date of the claimed invention.
Claim(s) 1-16 and 18-19 is/are rejected under 35 U.S.C. 102(a)(1,2) as being anticipated by Leger (US 3,670,999).
Regarding claim 1: Leger teaches an aerial delivery system for carrying cargo (12) from an aircraft (fig. 1) to ground, the aerial delivery system comprising:
a platform (10) for supporting the cargo;
a main parachute (recovery parachute 22) for carrying the platform when the platform has exited the aircraft and is airborne and the main parachute is deployed (c. 2, ℓ. 1-19; c. 1, ℓ. 5-20);
a main parachute deployment line (21) to deploy the main parachute (c. 4, ℓ. 23-24: the extraction parachute can deploy the main parachute through the first and second links, the second link member connected to the extraction line of the main parachute; see also c. 2, ℓ. 1-19, figs. 3-4);
an extraction parachute (19) coupled to the platform and arranged for generating a drag force and exerting the drag force on the platform (c. 2, ℓ. 1-19, c. 3, ℓ. 65-66); and
a coupling arrangement (force transfer mechanism 23) switchable from an open configuration (fig. 3) in which the main parachute deployment line is uncoupled from the extraction parachute (c. 2, ℓ. 45-57: “In the position shown in FIG. 3 the link 49 is free to move out of link 50”; c. 2, ℓ. 37-39: links 49 and 50 are connected to the main parachute deployment line and extraction parachute, respectively), and a closed configuration (fig. 4) in which the main parachute deployment line is coupled to the extraction parachute (c. 2, ℓ. 47-48: “in the position shown in FIG. 4 the links 49 and 50 are connected together”);
wherein the aerial delivery system is configured such that, when the extraction parachute exerts the drag force on the platform, the coupling arrangement is initially in the open configuration until the coupling arrangement is switched to the closed configuration to couple the main parachute deployment line to the extraction parachute (c. 2, ℓ. 15-19: when tripping fixture 28 connects recovery parachute line 21 to extracting parachute line 18; see also c. 3, ℓ. 40-58).
Regarding claim 2: Leger teaches the aerial delivery system according to claim 1, comprising a coupling device (tripping fixture 28) to switch the coupling arrangement from the open configuration to the closed configuration (c. 2, ℓ. 15-19: tripping fixture 28 connects recovery parachute line 21 to extracting parachute line 18; see also c. 3, ℓ. 40-58).
Regarding claim 3: Leger teaches the aerial delivery system according to claim 1, comprising an extraction parachute release device (actuating pins 55, 56) arranged such that it is able to uncouple the extraction parachute from the platform when the coupling arrangement is in the open configuration such that release of the extraction parachute does not deploy the main parachute (c. 2, ℓ. 37-57: extraction parachute 19 is coupled to link 49, which is coupled to link 50 by actuating pins 55, 56; c. 3, ℓ. 19-26: link retainer 78 can operate actuating pins 55, 56 to uncouple links 49 and 50, such that in the position of fig. 3, “link 49 will be released without link 50”).
Regarding claim 4: Leger teaches the aerial delivery system according to claim 3, wherein the extraction parachute release device is arranged such that it is able to uncouple the extraction parachute from the platform when the coupling arrangement is in the closed configuration such that release of the extraction parachute deploys the main parachute via the coupling arrangement and the main parachute deployment line (c. 2, ℓ. 47-48, c. 3, ℓ. 24-26: in the position of fig. 4, links 49 and 50 are released together).
Regarding claim 5: Leger teaches the aerial delivery system according to claim 1, wherein the aerial delivery system comprises a unitary load path along which the drag force travels from the extraction parachute to the platform, such that disconnection of the unitary load path removes the drag force from the extraction parachute to the platform (c. 1, ℓ. 13-16: an excessive load will be applied to the aircraft if a floor latch fails to release and the extraction parachute is not released from the load; c. 4, ℓ. 24-28: releasing the link to the extraction parachute “to prevent excessive drag loading of the aircraft by the parachute”, meaning that disconnecting the links removes the drag force of the extraction parachute from the aircraft; c. 2, ℓ. 37-57: since this release if of link 49 from link 50, disconnecting the links would also remove the drag force of the extraction parachute from the platform).
Regarding claim 6: Leger teaches an extraction assembly for an aerial delivery system, the extraction assembly comprising:
a coupling arrangement (force transfer mechanism 23) switchable from an open configuration (such as shown in fig. 3) to a closed configuration (such as shown in fig. 4);
wherein the extraction assembly is arranged such that, during a drag force event comprising a drag force generated by an extraction parachute (extraction parachute 19) and exerted on a platform (platform 10) via the extraction assembly, the coupling arrangement is switched from the open configuration to the closed configuration (c. 2, ℓ. 15-19: when tripping fixture 28 connects recovery parachute line 21 to extracting parachute line 18; see also c. 3, ℓ. 40-58);
wherein in the open configuration a main parachute deployment line (21) is uncoupled from the extraction parachute (c. 2, ℓ. 45-57: “In the position shown in FIG. 3 the link 49 is free to move out of link 50”; c. 2, ℓ. 37-39: links 49 and 50 are connected to the main parachute deployment line and extraction parachute, respectively), and in the closed configuration the main parachute deployment line is coupled to the extraction parachute (c. 2, ℓ. 47-48: “in the position shown in FIG. 4 the links 49 and 50 are connected together”).
Regarding claim 7: Leger teaches the extraction assembly according to claim 6, wherein the coupling arrangement comprises a first coupling portion (link 49) coupleable to a second coupling portion (link 50),
wherein in the open configuration (fig. 3) of the coupling arrangement the first coupling portion is uncoupled from the second coupling portion such that the main parachute deployment line is uncoupled from the extraction parachute (c. 2, ℓ. 35-47: “In the position shown in FIG. 3 the link 49 is free to move out of link 50”), and
wherein in the closed configuration (fig. 4) of the coupling arrangement the first coupling portion is coupled to the second coupling portion such that the main parachute deployment line is coupled to the extraction parachute (c. 2, ℓ. 47-48: “in the position shown in FIG. 4 the links 49 and 50 are connected together”).
Regarding claim 8: Leger teaches the extraction assembly according to claim 7, wherein the second coupling portion (link 50) comprises a clasp (locking pin 51) to retain the first coupling portion (link 49) when the coupling arrangement is in the closed configuration (fig. 4) and to release the first coupling portion when the coupling arrangement is in the open configuration (c. 3, ℓ. 19-26: when locking pin 51 is in the position shown in fig. 3, link 49 is not retained by link 50 and when locking pin 51 is in the position shown in fig. 4, link 49 is retained by link 50).
Regarding claim 9: Leger teaches the extraction assembly according to claim 8, wherein the extraction assembly comprises a bias arrangement (spring engaging piston member 86) to bias the clasp closed (c. 2, ℓ. 58-72: “pin carrier 72 acts to move the actuating pins 55 and 56 from the position shown in FIG. 3 to the position shown in FIG. 4 to lock the links 49 and 50 together”, thereby also moving locking pin 51 as shown in figs. 3-4; pin carrier 72 is connected to expanding link 73 containing spring engaging piston member 86).
Regarding claim 10: Leger teaches the extraction assembly according to claim 6, comprising a coupling device (fig. 9: including link retainer 78, links 80, 81 and actuating link 87) to switch the coupling arrangement from the open configuration to the closed configuration (c. 2, ℓ. 73–c. 3, ℓ. 26).
Regarding claim 11: Leger teaches the extraction assembly according to claims 10, wherein the coupling device comprises a drop arm (fig. 9: link retainer 78), wherein the coupling device is arranged such that a movement of the drop arm causes the coupling arrangement to switch from the open configuration to the closed configuration (c. 3, ℓ. 24-26: “When link retainer 78 is operated by cam 46, the actuating pins 55 and 56 and locking pin 51 are in the position shown in FIG. 4, and links 49 and 50 are released together”).
Regarding claim 12: Leger teaches the extraction assembly according to claim 6, comprising an extraction parachute release device (actuating pins 55, 56) arranged to uncouple the extraction parachute from the platform (c. 2, ℓ. 37-57: extraction parachute 19 is coupled to link 49, which is coupled to link 50 by actuating pins 55, 56; c. 3, ℓ. 19-26: link retainer 78 can operate actuating pins 55, 56 to uncouple links 49 and 50, such that in the position of fig. 3, “link 49 will be released without link 50”).
Regarding claim 13: Leger teaches the extraction assembly according to claim 12, wherein the coupling arrangement comprises a first coupling portion (link 49) coupleable to a second coupling portion (link 50),
wherein in the open configuration (fig. 3) of the coupling arrangement the first coupling portion is uncoupled from the second coupling portion such that the main parachute deployment line is uncoupled from the extraction parachute (c. 2, ℓ. 35-47: “In the position shown in FIG. 3 the link 49 is free to move out of link 50”), and
wherein in the closed configuration (fig. 4) of the coupling arrangement the first coupling portion is coupled to the second coupling portion such that the main parachute deployment line is coupled to the extraction parachute (c. 2, ℓ. 47-48: “in the position shown in FIG. 4 the links 49 and 50 are connected together”);
wherein the extraction parachute release device comprises:
a closed configuration (also shown in fig. 4) wherein the extraction parachute release device retains the first coupling portion such that drag force generated by the extraction parachute is exerted on the platform via the first coupling portion (c. 2, ℓ. 49-; c. 3, ℓ. 24-26: when actuating pins 55, 56 are in the position of fig. 4, links 49 and 50 are released together), and
an open configuration (also shown in fig. 3) wherein the extraction parachute release device releases the first coupling portion such that the extraction parachute is released from the platform (c. 3, ℓ. 19-23: when actuating pins 55, 56 are in the position of fig. 3, “link 49 will be released without link 50 which is retained”, releasing the extraction parachute while retaining the platform).
Regarding claim 14: Leger teaches the extraction assembly according to claim 13, wherein the extraction parachute release device comprises a lever assembly (fig. 9: including link retainer 78) configured such that:
in the closed configuration (fig. 4) of the extraction parachute release device the lever assembly retains the first coupling portion (c. 3, ℓ. 24-26: “When link retainer 78 is operated by cam 46, the actuating pins 55 and 56 and locking pin 51 are in the position shown in FIG. 4, and links 49 and 50 are released together”), and
in the open configuration (fig. 3) of the extraction parachute release device the lever assembly releases the first coupling portion (c. 3, ℓ. 19-23: “when the link retainer 78 is operated by the solenoid, the actuating pins 55 and 56 and locking pin 51 are in the position shown in FIG. 3, and the link 49 will be released without link 50”).
Regarding claim 15: Leger teaches the extraction assembly according to claim 14, wherein the lever assembly comprises a pair of pivotally mounted jaws (figs. 8-10: link retainer 78 is pivotally mounted at 79 and is shown to comprise a pair of parallel members at least where it carries the pair of rollers 84 and 85 and is operated by the pair of links 80 and 81) configured to engage with the first coupling portion so as to retain the first coupling portion (figs. 9-10: link retainer 78 has a pair of rollers 84 and 85 which engage link 49; c. 3, ℓ. 24-26: link retainer 78 is configured to retain link 49), and to disengage from the first coupling portion so as to release the first coupling portion (c. 3, ℓ. 19-23: link retainer 78 is configured to release link 49).
Regarding claim 16: Leger teaches the extraction assembly according to claim 12, wherein the extraction parachute release device is configured to uncouple the extraction parachute from the platform in response to receiving a release force (c. 3, ℓ. 1-8, 19-23: when solenoid 90 is energized it exerts a force on actuating link 87 to operate the link retainer to move the actuating pins and locking pin to the position of fig. 3 and uncouple the extraction parachute), optionally wherein the extraction assembly is configured to receive the release force via a cable (c. 4, ℓ. 68–c. 5, ℓ. 4: cables connect the solenoids to the power supply; fig. 20: the power supply is connected through the switch 25 which energizes the solenoids).
Regarding claim 18: Leger teaches the extraction assembly according to claim 12, wherein the extraction assembly is connected to an extraction parachute release assembly (fig. 9: including link retainer 78, links 80, 81 and actuating link 87),
wherein the extraction parachute release assembly comprises a drop arm (fig. 9: link retainer 78), wherein the extraction parachute release assembly is configured to cause the extraction parachute release device to uncouple the extraction parachute from the platform in response to rotation of the drop arm (c. 3, ℓ. 19-23: “when the link retainer 78 is operated by the solenoid, the actuating pins 55 and 56 and locking pin 51 are in the position shown in FIG. 3, and the link 49 will be released without link 50”).
Regarding claim 19: Leger teaches a method of airdropping cargo (12) from an aircraft (fig. 1) to the ground using an aerial delivery system, the aerial delivery system comprising:
a platform (10) for supporting the cargo;
a main parachute (recovery parachute 22) for carrying the platform when the platform has exited the aircraft and is airborne and the main parachute is deployed (c. 2, ℓ. 1-19; c. 1, ℓ. 5-20);
a main parachute deployment line (21) to deploy the main parachute (c. 4, ℓ. 23-24: the extraction parachute can deploy the main parachute through the first and second links, the second link member connected to the extraction line of the main parachute; see also c. 2, ℓ. 1-19, figs. 3-4);
an extraction parachute (19) coupled to the platform and arranged for generating a drag force and exerting the drag force on the platform (c. 2, ℓ. 1-19, c. 3, ℓ. 65-66); and
a coupling arrangement (force transfer mechanism 23) switchable from an open configuration (such as shown in fig. 3) in which the main parachute deployment line is uncoupled from the extraction parachute (c. 2, ℓ. 45-57: “In the position shown in FIG. 3 the link 49 is free to move out of link 50”; c. 2, ℓ. 37-39: links 49 and 50 are connected to the main parachute deployment line and extraction parachute, respectively), and a closed configuration (such as shown in fig. 4) in which the main parachute deployment line is coupled to the extraction parachute (c. 2, ℓ. 47-48: “in the position shown in FIG. 4 the links 49 and 50 are connected together”);
the method comprising the steps of:
using the extraction parachute to exert the drag force on the platform, wherein initially the coupling arrangement is in the open configuration and the platform is in an initial position relative to the aircraft (c. 2, ℓ. 15-19: before tripping fixture 28 connects recovery parachute line 21 to extracting parachute line 18; see also c. 3, ℓ. 40-58); and
wherein the coupling arrangement is switched to the closed configuration to couple the main parachute deployment line to the extraction parachute when the platform has moved under the action of the drag force from the initial position to a first position relative to the aircraft (c. 2, ℓ. 24-33, c. 3, ℓ. 40-58: after crank arm engages tripping fixture 28, recovery parachute line 21 is connected to extracting parachute line 18).
Claim Rejections - 35 USC § 103
This application currently names joint inventors. In considering patentability of the claims the examiner presumes that the subject matter of the various claims was commonly owned as of the effective filing date of the claimed invention(s) absent any evidence to the contrary.  Applicant is advised of the obligation under 37 CFR 1.56 to point out the inventor and effective filing dates of each claim that was not commonly owned as of the effective filing date of the later invention in order for the examiner to consider the applicability of 35 U.S.C. 102(b)(2)(C) for any potential 35 U.S.C. 102(a)(2) prior art against the later invention.
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.
Claim(s) 15 and 17 is/are rejected under 35 U.S.C. 103 as being unpatentable over Leger (US 3,670,999) in view of Keich et al. (US 3,781,055).
Regarding claims 15 and 17: Leger teaches the extraction assembly according to claim 13. Leger does not specifically teach an over center locking device configured to lock the extraction parachute release device in the closed configuration and to unlock so that the extraction parachute release device can move to the open configuration.
Keich teaches an extraction parachute release device (c. 1, ℓ. 7-15) having a lever assembly comprising a pair of pivotally mounted jaws (figs. 3-4: hook 33 and latch member 34 are pivotally mounted to each other) configured to engage with and retain or release a coupling portion (c. 3, ℓ. 55-68; c. 5, ℓ. 40-50), and an over centre locking device (toggle linkage 37) configured to lock the extraction parachute release device in the closed configuration (c. 4, ℓ. 30-50), and to unlock so that the extraction parachute release device can move to an open configuration (c. 4, ℓ. 47-59; c. 5, ℓ. 40-49).
It would have been obvious to a person having ordinary skill in the art at the time the invention was filed to have configured the extraction assembly of Leger with an extraction parachute release device having pivotally mounted jaws and an over center locking device, such as taught by Keich, for the purpose of securely coupling the extraction parachute to support high tension loads while being able to release with little force (Keich c. 5, ℓ. 30-40) and to dissipate the energy generated by the pull of the extraction parachute without any sudden impacting of parts of the latch assembly (Keich c. 5, ℓ. 53-62).
Claim(s) 20 is/are rejected under 35 U.S.C. 103 as being unpatentable over Leger (US 3,670,999) in view of Jones (EP 3 293 116 A1).
Regarding claim 20: Leger teaches the method according to claim 19, but does not specifically teach that the extraction parachute is uncoupled from the platform when the platform has moved under the action of the drag force from the first position to a second position relative to the aircraft.
Jones teaches an extraction parachute which is uncoupled from the platform when the platform has moved under the action of the drag force from the first position to a second position relative to the aircraft (¶ [0030]: “allowing the extractor parachute to pull out the platform relative to the aircraft, and releasing the ejectable connector from the main body, thus releasing the extractor parachute from the platform”).
It would have been obvious to a person having ordinary skill in the art at the time the invention was filed to have configured the extraction assembly of Leger to uncouple the extraction parachute from the platform when the platform has moved under the action of the drag force from the first position to a second position relative to the aircraft, such as taught by Jones, for the purpose of waiting to release the extraction parachute at the correct time, when the platform leaves the aircraft (Jones ¶ [0062]-[0063]).
Conclusion

APPLICANT REBUTTAL: REMARKSThe Office Action has been received and carefully noted. The above amendments to the claims, and the following remarks, are submitted as a full and complete response thereto.Claims 6-9, 11, and 13-18 have been amended. Support for the claim amendments can be found at least in paragraphs [0020], [0021], [0027], [0043], [0044], [0052], [0054], [0067], [0068], [0124], [0130], [0151], and [0152] of the subject application. Claims 1-5, 10, 12, 19, and 20 have been cancelled without prejudice to or disclaimer of the subject matter recited therein. Claims 21- 29 have been added. Support for the new claims can be found in at least in paragraphs [0020], [0021], [0027], [0043], [0044], [0052], [0054], [0067], [0068], [0124], [0130], [0151], and [0152].No new matter is added. Claims 6-9, 11, 13-18, and 21-29 are currently pending in the application, of which claims 6, 28, and 29 are independent claims. Further examination and reconsideration of the application is respectfully requested.Claim Rejection - 35 U.S.C. §§ 102 / 103 The Office Action presented the following rejections.* Claims 1-16, 18, and 19 were rejected under 35 U.S.C. §§ 102(a)(1) and (2) as allegedly being anticipated by U.S. Patent No. 3,670,999 ("Leger").* Claims 15 and 17 were rejected under 35 U.S.C. § 103 as allegedly being unpatentable over Leger in view of U.S. Patent No. 3,781,055 ("Keich").* Claim 20 was rejected under 35 U.S.C. § 103 as allegedly being unpatentable over Leger in view of EP Patent No. 3,293,116 ("Jones").In the field of aerial delivery, it is typical that a cargo is extracted from a cargo bay of an aircraft under the action of an extraction parachute. After exiting the aircraft, the extraction parachute is released from the cargo and the main parachute is deployed to bring the cargo to the ground. The main parachute is typically deployed by the extraction parachute pulling on a main parachute deployment line after the extraction parachute has been released from the cargo.The aerial delivery system according to some embodiments includes two key assemblies - (1) an extraction assembly 100 and (2) extraction parachute release assembly 200. See Figures 1, 2 and 16 (reproduced below).---
Extraction asserbiv Extraction parachute release assembly The extraction assembly includes a coupling arrangement 120. In some embodiments, the coupling arrangement includes a first coupling portion 121 to which the extraction line 18 of the extraction parachute 16 is attached, and a second coupling portion 122 to which the main parachute deployment line 15 is attached. See Figures 4 and 5 below.12a13 1262 Fig ~~ 4 ~To ext~aCtion Paracute  yN........T cief  poto 1   a  t  s Rq 5 The extraction assembly 100 includes a coupling device 130 to switch the coupling arrangement 120 from an open configuration in which the first and second coupling portions 121, 122 are uncoupled, to a closed configuration in which they are coupled together.In some embodiments, the first coupling portion 121 includes lugs 125 and the second coupling portion includes legs 126. The first coupling portion 121 and the second coupling portion are coupled by closing the legs 126 over the lugs 125. The coupling device 130 includes a drop arm 160 and a cam mechanism arranged such that rotation of the drop arm 160 causes the legs 126 to close over the lugs 125. See Figures 2 and 5 below.126b  124b  2e  127b 1C   1   4
1 - 145- 15Legs Close
.~  la .!  ;.  :.'170
. 122 v   ,....
. c
29 IS  8  5
130 9C 4o24 ;2'z
Pushrod moves Fig. 2   Drop arm rotates
outwards The extraction assembly 100 also includes an extraction parachute release device 140 to release the extraction parachute 16. In certain embodiments, the extraction parachute release device 140 includes a pair of jaws 143 which retain the first coupling portion 121. The jaws 143 are arranged to move apart to allow the first coupling portion 121, and thus the extraction parachute 16, to fly free. The jaws 143 may allow the first coupling portion 121 to exit with minimal rotation.Fig 1 The extracio paacute releas deic 14   soeae
yaxrcinprcuerees .. . .. . .   . . . .   . .
17 '.................... .. .. iii..........::::,`::? .i   n:Fitt. 12 The extraction parachute release device 140 is operated by an extraction parachute release assembly 200. In some embodiments, the extraction parachute release assembly 200 includes another drop arm 231 which activates a trigger mechanism, which pulls a cable 202 which causes release of the jaws 143..............r\.\ \\ Fig. 16 The aerial delivery system may operate in a two-stage process. In a first stage, at a first predetermined moment during extraction of the platform 11, corresponding to a first predetermined position of the platform 11 relative to the aircraft 1, the coupling device 130 switches the coupling arrangement 120 from the open configuration to the closed configuration. In a second stage, at a second predetermined moment during extraction of the platform 11, corresponding to a second predetermined position of the platform 11 relative to the aircraft 1, the extraction parachute release assembly 200 causes the extraction parachute release device 140 to uncouple the extraction parachute 16. The above stages occur when the drop arms 160, 231, positioned at different points on the platform 11, rotate upon exiting the aircraft 1. In other embodiments, the determinations may be made by sensors. See paragraphs [0225] and [0228].Leger Leger discusses a force transfer mechanism 23 for connecting an extraction parachute line 18 to a main parachute deployment line 21. See Fig. 1.49 X16 /0
23 The force transfer mechanism 23 comprises a first link 49 for connection to the extraction parachute line 18, and a second link 50 for connection to the main parachute deployment line 21.During extraction, the first link 49 is initially retained by rollers 84, 85 which are positioned at the end of pivotally mounted link retainer 78. See Fig. 9. The second link 50 is nested within the first link 49, and initially the first and second links 49, 50 are not connected to each other. See Fig. 3.Theffr m m 2i
t   . - I t
I I-i The force transfer mechanism 23 has a crankshaft 37 which is rotated when a crank arm 38 passes a fixture 28 on the aircraft floor 16 during extraction. Rotation of the camshaft 37 causes a locking pin 51 to move and connect the first link 49 and the second link 50. See Fig. 4. Rotation of the crankshaft 37 also causes the rollers 84, 85 to move and release first link 49. With the first and second links 49, 50 connected and with the first link 49 released, the extraction parachute 19 can deploy the main parachute 22.In an emergency, the extraction parachute 19 can be released by energizing a solenoid 90, which causes the rollers 84, 85 to move and release the first link 49. Provided this is done before the platform 10 reaches the fixture 28 on the aircraft floor 16, the extraction parachute 19 is released without deploying the main parachute 22 because the first and second links 49, 50 are not connected to each other.Leger Does Not Disclose One or More Features of Claim 6 Claim 6 recites, in part, an extraction parachute release device configured to uncouple the extraction parachute from the platform;wherein the aerial delivery system comprises an extraction parachute release assembly arranged to cause the extraction parachute release device to uncouple the extraction parachute from the platform in response to the platform moving to a second predetermined position relative to the aircraft; and wherein the second predetermined position is a position reached by the platform after the platform has passed the first predetermined position Leger does not disclose these features.Instead, with respect to the force transfer mechanism of Leger, the locking pin 51 and the rollers 84, 85 are both caused to move when the crank arm 38 passes the fixture 28 on the floor of the aircraft. The force transfer mechanism of Leger thus has a single input means which is activated at a single point during extraction of the platform 10.The force transfer mechanism of Leger is thus configured to, in response to the platform reaching one single predetermined position relative to the aircraft, both: (a) couple the main parachute deployment line 21 to the extraction parachute line 18, and (b) release the extraction parachute.Thus, Leger does not disclose each and every feature of independent claim 6.Further, nothing was cited or found in the other cited art that cures the above-mentioned deficiencies of Leger with respect to independent claim 6. For at least these reasons, Applicant respectfully submits that independent claim 6 patentably distinguishes over the cited art.Applicant further submits that the dependent claims inherit the patentable features of base claim 6, and therefore, patentably distinguish over the cited art.Accordingly, withdrawal of the rejection is respectfully requested.New Claims New claims 21-29 have been added.New claims 21-27 inherit the patentable features of base claim 6, and therefore, patentably distinguish over the cited art.New claims 28 and 29, both of which have their own scope, have been added to recite one or more features that are similar to independent claim 6.Accordingly, withdrawal of the rejections is respectfully requested.CONCLUSIONIn view of the above, Applicant respectfully submits that the present application is in condition for allowance. Accordingly, Applicant respectfully requests that the claims be allowed and the application be passed to issue.Although Applicant has focused the remarks and/or amendments on or primarily on the independent claims in order to expedite the prosecution of the instant application, Applicant reserves the right to remark on and/or amend any of the dependent claims at any time. The mere fact that Applicant has not remarked on and/or amended any of the dependent claims at this time, either related to an Official Notice or not, is unequivocally not an admission of prior art.Although the present communication may include alterations to the application or claims, or characterizations of claim scope or referenced art, Applicant is not conceding in this application that previously pending claims are not patentable over the cited references. Rather, any alterations or characterizations are being made to facilitate expeditious prosecution of this application.Applicant reserves the right to pursue at a later date any previously pending or other broader or narrower claims that capture any subject matter supported by the present disclosure, including subject matter found to be specifically disclaimed herein or by any prior prosecution.Accordingly, reviewers of this or any parent, child or related prosecution history shall not reasonably infer that Applicant has made any disclaimers or disavowals of any subject matter supported by the present application.If for any reason the Examiner determines that the application is not now in condition for allowance, it is respectfully requested that the Examiner contact, by telephone, Applicant's undersigned representative at the indicated telephone number to arrange for an interview to expedite the disposition of this application.In the event this paper is not being timely filed, Applicant respectfully petitions for an appropriate extension of time. Any fees for such an extension together with any additional fees may be charged to Counsel's Deposit Account 50-5837.Respectfully submitted, /Sheetal S. Patel/ Sheetal S. Patel Attorney for Applicant Registration No. 59,326 Customer No. 94165 LEONARDPATEL PC9891 Irvine Center Drive, Suite 100 Irvine, California 92618 Tel.: 949-916-1500 Fax:  949-242-9711

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 .
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.
Authorization for this examiner’s amendment was given in an interview with Sheetal Patel on May 5, 2025.
The application has been amended as follows:
Claims 28 and 29 have been amended as shown below:
28.	(Currently Amended) An aerial delivery system for aerial delivery of cargo from an aircraft, the aerial delivery system comprising:
an extraction assembly comprising: a coupling device and a coupling arrangement, the coupling device being configured to switch the coupling arrangement from an open configuration in which a main parachute deployment line is uncoupled from an extraction parachute to a closed configuration in which the main parachute deployment line is coupled to the extraction parachute; and
an extraction parachute release assembly configured to cause an extraction parachute release device to uncouple the extraction parachute from the cargo;
wherein the coupling device comprises a first drop arm arranged to initially be held in a first configuration of the first drop arm by contact with an aircraft structure, wherein the coupling device is arranged to cause the coupling arrangement to switch from the open configuration to the closed configuration in response to activation of the first drop arm, the first drop arm being activated upon movement of the first drop arm from the first configuration of the first drop arm to a second configuration of the first drop arm as a position of the coupling device relative to the aircraft structure changes during extraction of the cargo from the aircraft; and
wherein the extraction parachute release assembly comprises a second drop arm arranged to initially be held in a first configuration of the second drop arm by contact with an aircraft structure, wherein the extraction parachute release assembly is configured to cause the extraction parachute release device to uncouple the extraction parachute from the  cargo in response to activation of the second drop arm, the second drop arm being activated upon movement of the second drop arm from the first configuration of the second drop arm to a second configuration of the second drop arm as a position of the extraction parachute release assembly relative to the aircraft structure changes during extraction of the cargo from the aircraft;
wherein the first drop arm and the second drop arm are arranged such that the first drop arm and the second drop arm are activated at different times during extraction of the cargo from the aircraft.
29.	(Currently Amended) An aerial delivery system for aerial delivery of cargo from an aircraft, the aerial delivery system comprising:
an extraction assembly comprising:
a coupling arrangement comprising a first coupling portion for connection to an extraction parachute and a second coupling portion for connection to a main parachute deployment line;
a coupling device being configured to switch the coupling arrangement from an open configuration of the coupling arrangement in which the first coupling portion is uncoupled from the second coupling portion such that the main parachute deployment line is uncoupled from the extraction parachute, to a closed configuration of the coupling arrangement in which the first coupling portion is coupled to the second coupling portion such that the main parachute deployment line is coupled to the extraction parachute upon movement of the cargo to a first position relative to the aircraft; and
an extraction parachute release device configured to uncouple the extraction parachute from the cargo upon movement of the cargo to a second position relative to the aircraft prior to or after movement of the cargo to the first position, the extraction parachute release device comprising a pair of jaws mounted to a body of the extraction assembly, each one of the jaws being configured to move, relative to the body, towards and away from another of the jaws;
wherein the extraction parachute release device comprises a closed configuration of the extraction parachute release device in which in which the jaws engage with opposing sides of the first coupling portion to retain the first coupling portion such that a drag force generated by the extraction parachute is exerted on the cargo via the first coupling portion; and
wherein the extraction parachute release device is movable to an open configuration of the extraction parachute release device in which the jaws are disengaged from the opposing sides of the first coupling portion to release the first coupling portion and thereby release the extraction parachute from the cargo, wherein the jaws are disengaged by moving, relative to the body, away from the first coupling portion.
Reasons for Allowance
The following is an examiner’s statement of reasons for allowance:
Aerial cargo delivery systems using an extraction parachute to deploy a main parachute are known where the extraction parachute may be jettisoned in the event of an emergency. Generally, for example in US 5,697,581 to Conroy et al., the extraction parachute is initially coupled to the main parachute and only decoupled if necessary. However, some prior art systems are known, such as US 3,670,999 to Leger and US 3,865,333 to Fielding et al., in which the extraction parachute is initially uncoupled from the main parachute, the extraction and main parachutes being coupled during extraction of the cargo while the cargo is still inside the aircraft.
Conroy teaches an aerial cargo delivery system where the extraction parachute may be released while connected to the main parachute (as shown in figures 3 and 8-10) or the extraction parachute may be jettisoned by itself in an emergency (as shown in figures 2 and 11-13), however in Conroy the extraction and main parachutes are interconnected to begin with and only decoupled in the event of an emergency.
In both Leger and Fielding, link members connected to the extraction parachute to the main parachute are interconnected and released simultaneously; Leger when a crank arm is tripped by a fixture on the floor at the aircraft exit and Fielding when a static line attached to the cargo is pulled taut. Since the same event performs both the interconnection and the release of the link members, neither Leger nor Fielding can be readily modified to perform the two operations at different predetermined positions or at different times during extraction.
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.”
Conclusion

CITED REFERENCE SUMMARIES: Ref US3670999A: [content unavailable]
Ref US3781055A: [content unavailable]
Ref US3670999: Claims:
1. A force transfer device for use in the extraction line between the extraction parachute and the main parachute in aircraft aerial delivery platforms, comprising: a first link member adapted to be connected to the extraction line of the extraction parachute; a second link member adapted to be connected to the extraction line of the main parachute; a two position link interconnection means positioned within said first and second link for leaving the links unconnected in the first position and for interconnecting the first and second link in the second position; means, including a crank arm, adapted to engage tripping mechanism on the aircraft floor near the platform exit, for moving the two position link interconnecting means to the second position and for releasing said links whereby the extraction parachute can deploy the main parachute; means, adapted to be operated in case of a hangup of a platform for releasing only the link connected to the extraction parachute while retaining the link connected to the main parachute to prevent excessive drag loading of the aircraft by the parachute.
2. A device as recited in claim 1 wherein said two position link interconnected means includes a locking pin positioned within the first and second link; a first pin actuating device held by the first link on one side of locking pin and having a portion adapted to extend beyond the outside edge of the first link; a second pin actuating device held by the first link on the other side of the locking pin and having a portion adapted to extend beyond the outside edge of the first link; the junction of the actuating devices and the locking pin being in alignment with the junction between the first link and the second link in the first position and being displaced therefrom in the second position; means in said first link adapter lock at least one of said actuating devices in the second position when the locking pin is moved to the second position.
3. A device as recited in claim 2 wherein the means for moving the two position link intercOnnecting means and for releasing the links include a shaft connected to said crank arm a plurality of cams secured to said shaft; means responsive to the movement of one of the cams attached to said shaft for moving the first and second pin actuating devices and the locking pin from said first position to said second position when the crank arm is turned by said tripping means; means responsive to the movement of a second cam so said shaft releasing said first and second link members when the crank arm is turned by said tripping means.
4. The device as recited in claim 3 wherein the means for releasing only the link connected to the extraction parachute includes a solenoid; means connected to said solenoid for operating the means for releasing the first and second links; means supported on said shaft and responsive to said one cam for locking the second link in position when the links are released by the solenoid and for releasing the second link when the crank drive is turned by said tripping means to release the links.
5. The device as recited in claim 4, including spring loaded means for engaging a third cam on said shaft for retaining the shaft in a predetermined position except when it is rotated by the crank arm.
6. The device as recited in claim 5 in combination with a plurality of load carrying platforms with a force transfer device secured to the aft portion of each platform; including a cable adapted for connecting the solenoids in each force transfer device to a power supply; a disconnect type terminal in said cable adjacent each force transfer device for disconnecting the cable to each platform as it leaves the aircraft; said disconnect type terminals including means for connecting the solenoid of the adjacent force transfer device to the power supply circuit only when the cable to the next platform is disconnected whereby only the solenoid on the aft most platform can be energized.
Ref US3781055: Claims:
1. In a coupling device for releasably connecting elements of a system under tension load comprising in combination a link assembly and a latch assembly, said link assembly comprising means for connecting same to one of said elements of said system and rotatably mounted cam means spaced from said connecting means, said latch assembly comprising means for connecting same to another of said elements of said system, a hook portion conformed to engage said rotatable cam means of said link assembly and to impart a rotating moment to said cam means when a tension load is applied longitudinally of said coupling device, said moment tending to dislodge said cam means from said hook portion, movable latch means adapted to releasably engage said cam means to prevent rotation thereof when said cam means is engaged in said hook portion and means for releasably locking said latch means in engagement with said cam means, that improvement wherein said means for releasably locking said latch means in engagement with said cam means comprises a toggle linkage, a freely rotatable lock link, and means for releasably locking said lock link against rotation, said toggle linkage being connected to said lock link at a point spaced from the axis of rotation thereof; whereby the energy created in the latch means by the release of said rotatable cam means is dissipated by free rotation of said lock link and the resulting reciprocative movement of said toggle linkage.
2. A coupling device according to claim 1, wherein said rotatable lock link is generally circular, a portion of the peripheral surface of said lock link having a concave configuration for mating with said means for releasably locking said toggle linkage.
3. A coupling device according to claim 2, wherein said means for releasably locking said toggle linkage comprises roller bearing means for mating with said rotatable lock link at said concave portion to maintain said toggle linkage in locked position, whereby said latch means is maintained in locked position.
4. A coupling device according to claim 3, wherein said means for releasably locking said toggle linkage comprises a fork, a shaft, and a slider, said roller bearing means being mounted on said fork, said fork being attached to said shaft, and said shaft being movable by said slider, whereby said roller bearing means is moved out of locking engagement with said rotatable rock link at said concave portion thereof.
5. A coupling device according to claim 4, wherein said means for releasably locking said toggle linkage comprises a leaf spring locking means for locking said shaft, said fork, and said roller bearing means in locking position while said slider remains free to move, said leaf spring locking means being mounted within said latch assembly, a locking pin being fixedly mounted on said shaft and passing through slotted openings in the sidewalls of said slider, said leaf spring locking means in combination with said locking pin being adapted to maintain said roller bearing means in locking engagement with said rotatable lock link at said concave portion thereof until said slider is purposely raised sufficiently to cause said leaf spring locking means to become disengaged from said locking pin, thereby permitting said roller bearing means to move out of locking engagement with said rotatable lock link.
6. A coupling device according to claim 5, wherein said latch assembly comprises movable means for visually indicating when said slider is properly positioned to permit locking of said shaft by said leaf spring locking means.
7. A coupling device according to claim 6, wherein said movable means for visual indication is a cylindrically shaped pushrod, said pushrod being loosely connected to said slider, one end of said pushrod extending outside of said latch assembly and having indicia thereon which visually indicate when said slider is properly positioned to permit locking of said shaft by said leaf spring locking means.