Office Action 2: Notice of Allowance (2025-05-12)

CLAIMS:
IN THE CLAIMS:

The listing of claims will replace all prior versions, and listings, of claims in the application.

1-5. (Cancelled)24

6\. (Currently Amended) An aerial delivery systemfor aerial delivery of cargo from an aircraft, the cargo being provided on an aerial delivery platform, the aerial delivery system comprising:
an extraction assembly for transmitting to the platform a drag force generated by an extraction parachute, the extraction assembly comprising:
a coupling arrangement configured to couple a main parachute deployment line to the extraction parachute, the coupling arrangement being switchable from an open configuration in which the main parachute deployment line is uncoupled from the extraction parachute to a closed configuration in which the main parachute deployment line is coupled to the extraction parachute;
a coupling device configured to switch the coupling arrangement from the open configuration to the closed configuration in response to the platform moving to a first predetermined position relative to the aircraft; and
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; andwherein the second predetermined position is a position reached by the platform after the platform has passed the first predetermined position;
.

7\. (Currently Amended) The aerial delivery system 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\. (Currently Amended) The aerial delivery system according to claim 7, wherein one of the first coupling portion and the second coupling portion comprises a clasp to retain an other of the first coupling portion and the second coupling portion when the coupling arrangement is in the closed configuration and to release the other of the first coupling

portion and the second coupling portion when the coupling arrangement is in the open configuration.

9\. (Currently Amended) The aerial delivery system according to claim 8, wherein the extraction assembly comprises a bias arrangement to bias the clasp closed.

10\. (Cancelled)

11\. (Currently Amended) The aerial delivery system according toclaims6 ,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\. (Cancelled)

13\. (Currently Amended) The aerial delivery system according to claim 7 ,

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\. (Currently Amended) The aerial delivery system 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\. (Currently Amended) The aerial delivery system 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\. (Currently Amended) The aerial delivery system according to claim 6 , wherein the extraction parachute release device is configured to uncouple the extraction parachute from the platform in response to receiving a release force transmitted from the extraction parachute release assembly, optionally wherein the extraction assembly is configured to receive the release force via a cable.

17\. (Currently Amended) The aerial delivery system 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\. (Currently Amended) The aerial delivery system according to claim6 ,
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 movement of the drop arm.

19-20. (Cancelled)

21\. (New) The aerial delivery system according to claim 6, wherein the extraction parachute release device is configured 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.

22\. (New) The aerial delivery system according to claim 6, wherein the extraction parachute release assembly is configured such that it is able to cause the extraction parachute release device to uncouple the extraction parachute from the platform, prior to the platform reaching the second predetermined position relative to the aircraft, in response to an input from a jettison assembly, the jettison assembly being configured to effect a user initiated jettison of the extraction parachute from the platform.

23\. (New) The aerial delivery system according to claim 22, wherein the jettison assembly comprises a jettison initiation device for operation by the user, the jettison initiation device being configured to generate a release force which is transmitted to the extraction parachute release assembly.

24\. (New) The aerial delivery system according to claim 6, wherein the extraction assembly comprises a body to which the coupling arrangement, the coupling device and the extraction parachute release device are directly attached and/or supported.

25\. (New) The aerial delivery system according to claim 24, wherein the aerial delivery system comprises a pivotal coupling configured to pivotally couple the extraction assembly to the platform.

26\. (New) An aerial delivery system according to claim 6, the aerial delivery system comprising:
the platform for supporting the cargo;
the main parachute for carrying the platform when the platform has exited the aircraft and is airborne and the main parachute is deployed;
the main parachute deployment line to deploy the main parachute; and
the extraction parachute coupled to the platform and arranged for generating the drag force and exerting the drag force on the platform.

27\. (New) A method of operating the aerial delivery system according to claim 26, the method comprising:
using the extraction parachute to generate the drag force which is exerted via the extraction assembly on the platform, the drag force initially being exerted whilst the coupling arrangement is in the open configuration such that the main parachute deployment line is uncoupled from the extraction parachute;
when the platform has moved to the first predetermined position relative to the aircraft, the coupling device switching the coupling arrangement from the open configuration to the closed configuration such that the main parachute deployment line is coupled to the extraction parachute;
when the platform has moved to the second predetermined position relative to the aircraft, the extraction parachute release assembly causing the extraction parachute release device to uncouple the extraction parachute from the platform; and
the extraction parachute deploying the main parachute via the main parachute deployment line.

28\. (New) 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 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 platform 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.

29\. (New) 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; and
an extraction parachute release device configured to uncouple the extraction parachute from the cargo, 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

Response dated March 7, 2025 Reply to Office Action of December 19, 2024 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.

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

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


CITED REFERENCE SUMMARIES: Ref US3267089A: Claims:
A COMPOUND HAVING THE FOLLOWING STRUCTURE:
Ref US3865333A: [content unavailable]
Ref US5697581A: Claims:
A towplate for retaining a flexible tension member that connects cargo to a drogue parachute, the towplate comprising: a strap engaging member having a strap engaging surface for engagement with the flexible tension member; an eccentric cam pivotally mounted relative to the member to be pivotable between a first position in which the cam engages the flexible tension member to wedge the flexible tension member between the cam and the strap engaging surface, and a second position in which the cam releases the flexible tension member; a flexible tension member retaining pin removably mounted adjacent to the cam; and a pin actuator means for removing the pin, wherein the flexible tension member follows a serpentine path past the eccentric cam and around the pin.
a strap engaging member having a strap engaging surface for engagement with the flexible tension member;
an eccentric cam pivotally mounted relative to the member to be pivotable between a first position in which the cam engages the flexible tension member to wedge the flexible tension member between the cam and the strap engaging surface, and a second position in which the cam releases the flexible tension member;
a flexible tension member retaining pin removably mounted adjacent to the cam; and
a pin actuator means for removing the pin, wherein the flexible tension member follows a serpentine path past the eccentric cam and around the pin.
The towplate of claim 1 wherein the pin actuator is a hydraulic actuator.
The towplate of claim 1 wherein the eccentric cam has a knurled surface.
The towplate of claim 1, further comprising a cutter mounted adjacent the pin, and a cutter activator means for activating the cutter.
The towplate of claim 4 wherein the cutter includes a blade and the actuator comprises a hydraulic cylinder.
A towplate for retaining a flexible tension member that connects a cargo to a drogue parachute, the towplate comprising: a strap engaging member having a strap engaging surface; a friction element movably mounted relative to the strap engaging member to be movable towards and away from the strap engaging surface to wedge the flexible tension member between the strap engaging member and the friction element, the strap engaging member and friction element being mounted relative to each other so as to be urged towards each other by the flexible tension member when force is exerted on one end of the flexible tension member; and strap releasing means for releasing the flexible tension member.
a strap engaging member having a strap engaging surface;
a friction element movably mounted relative to the strap engaging member to be movable towards and away from the strap engaging surface to wedge the flexible tension member between the strap engaging member and the friction element, the strap engaging member and friction element being mounted relative to each other so as to be urged towards each other by the flexible tension member when force is exerted on one end of the flexible tension member; and
strap releasing means for releasing the flexible tension member.
The towplate of claim 6 wherein the friction element comprises an eccentric cam.
The towplate of claim 7 wherein the eccentric cam has a knurled surface.
The towplate of claim 7 wherein the releasing means comprises: a removable pin mounted relative to the strap engaging member and cam such that the flexible tension member follows a serpentine path around the cam and the pin; and a pin actuator means for removing the removable pin.
a removable pin mounted relative to the strap engaging member and cam such that the flexible tension member follows a serpentine path around the cam and the pin; and
a pin actuator means for removing the removable pin.
The towplate of claim 9 wherein the pin actuator means is a hydraulic actuator.
The towplate of claim 6, further comprising a remotely actuatable cutting device to sever the flexible tension member.
The towplate of claim 11 wherein the cutting device comprises a blade and an actuator that includes a hydraulic cylinder.
A method of controlling the release of aerially delivered cargo using a towplate wherein a flexible tension member connects a cargo to a drogue parachute, the method comprising the steps of: threading the flexible tension member between an eccentric cam and a flexible tension member engaging surface, and around a removable pin to generate a frictional holding force between the cam and the engaging surface; and removing the pin at a desired moment to release the flexible tension member.
removing the pin at a desired moment to release the flexible tension member.
The method of claim 13 further comprising the steps of: cutting the flexible tension member in the event of the drogue parachute not deploying properly.
cutting the flexible tension member in the event of the drogue parachute not deploying properly.
A method of controlling the release of aerially delivered cargo wherein a flexible tension member connects a cargo to a drogue parachute, the method comprising the steps of: placing a portion of-the flexible tension member between two elements having friction producing surfaces; transmitting a retaining force onto at least one of the elements causing the friction producing surfaces to apply a force directly to the flexible tension member to retain the flexible tension member between the elements; and releasing the retaining force at the desired moment to release the flexible tension member.
placing a portion of-the flexible tension member between two elements having friction producing surfaces;
transmitting a retaining force onto at least one of the elements causing the friction producing surfaces to apply a force directly to the flexible tension member to retain the flexible tension member between the elements; and
releasing the retaining force at the desired moment to release the flexible tension member.
A method of controlling the release of aerially delivered cargo using a towplate having a releasable clevis assembly comprising the steps of: connecting the cargo to the clevis assembly; connecting a drogue parachute to the clevis assembly, the drogue parachute connected to the clevis assembly by means of a releasable drogue cylinder held captive between two parts of the clevis assembly, the parts being movable relative to each other between a locked position in which the drogue cylinder is held captive, and a release position; removing the two parts relative to each other to their release position when a problem is detected requiring the drogue parachute to be jettisoned; deploying the drogue parachute; and counteracting the force exerted by the drogue parachute on the clevis assembly by moving a retaining arm into engagement with a load bearing surface on the clevis assembly, wherein the load bearing surface faces in the direction of the force exerted by the drogue parachute; and disengaging the retaining arm from the load bearing surface at the desired moment.
connecting the cargo to the clevis assembly;
connecting a drogue parachute to the clevis assembly, the drogue parachute connected to the clevis assembly by means of a releasable drogue cylinder held captive between two parts of the clevis assembly, the parts being movable relative to each other between a locked position in which the drogue cylinder is held captive, and a release position;
removing the two parts relative to each other to their release position when a problem is detected requiring the drogue parachute to be jettisoned;
deploying the drogue parachute; and
counteracting the force exerted by the drogue parachute on the clevis assembly by moving a retaining arm into engagement with a load bearing surface on the clevis assembly, wherein the load bearing surface faces in the direction of the force exerted by the drogue parachute; and
disengaging the retaining arm from the load bearing surface at the desired moment.
A method of claim 16, wherein connecting the cargo to the clevis assembly includes connecting a flexible tension member to the clevis assembly, the flexible tension member being connected to an extraction parachute bag, wherein an extraction parachute is housed in the bag and is connected to the cargo.
A method of claim 16, wherein the retraining arm is moved by means of a hydraulic actuator.
A method of claim 18, wherein the two parts are moved relative to each other by means of a jettison hydraulic actuator.
A method of claim 19, wherein the two parts are maintained in a locked position by means of a detent.
A method of claim 20, wherein the jettison hydraulic actuator engages the detent to release it.
A method of claim 18, wherein the one part is movable and the other part is stationary, the movable part forming a recess for accommodating the drogue cylinder, and the stationary part having a lip for holding the drogue cylinder captive in the recess when the movable part is in its locked position.
Ref US5697581: Claims:
1. A towplate for retaining a flexible tension member that connects cargo to a drogue parachute, the towplate comprising:a strap engaging member having a strap engaging surface for engagement with the flexible tension member; an eccentric cam pivotally mounted relative to the member to be pivotable between a first position in which the cam engages the flexible tension member to wedge the flexible tension member between the cam and the strap engaging surface, and a second position in which the cam releases the flexible tension member; a flexible tension member retaining pin removably mounted adjacent to the cam; and a pin actuator means for removing the pin, wherein the flexible tension member follows a serpentine path past the eccentric cam and around the pin.
2. The towplate of claim 1 wherein the pin actuator is a hydraulic actuator.
3. The towplate of claim 1 wherein the eccentric cam has a knurled surface.
4. The towplate of claim 1, further comprising a cutter mounted adjacent the pin, and a cutter activator means for activating the cutter.
5. The towplate of claim 4 wherein the cutter includes a blade and the actuator comprises a hydraulic cylinder.
6. A towplate for retaining a flexible tension member that connects a cargo to a drogue parachute, the towplate comprising:a strap engaging member having a strap engaging surface; a friction element movably mounted relative to the strap engaging member to be movable towards and away from the strap engaging surface to wedge the flexible tension member between the strap engaging member and the friction element, the strap engaging member and friction element being mounted relative to each other so as to be urged towards each other by the flexible tension member when force is exerted on one end of the flexible tension member; and strap releasing means for releasing the flexible tension member.
7. The towplate of claim 6 wherein the friction element comprises an eccentric cam.
8. The towplate of claim 7 wherein the eccentric cam has a knurled surface.
9. The towplate of claim 7 wherein the releasing means comprises:a removable pin mounted relative to the strap engaging member and cam such that the flexible tension member follows a serpentine path around the cam and the pin; and a pin actuator means for removing the removable pin.
10. The towplate of claim 9 wherein the pin actuator means is a hydraulic actuator.
11. The towplate of claim 6, further comprising a remotely actuatable cutting device to sever the flexible tension member.
12. The towplate of claim 11 wherein the cutting device comprises a blade and an actuator that includes a hydraulic cylinder.
13. A method of controlling the release of aerially delivered cargo using a towplate wherein a flexible tension member connects a cargo to a drogue parachute, the method comprising the steps of: threading the flexible tension member between an eccentric cam and a flexible tension member engaging surface, and around a removable pin to generate a frictional holding force between the cam and the engaging surface; andremoving the pin at a desired moment to release the flexible tension member.
14. The method of claim 13 further comprising the steps of:cutting the flexible tension member in the event of the drogue parachute not deploying properly.
15. A method of controlling the release of aerially delivered cargo wherein a flexible tension member connects a cargo to a drogue parachute, the method comprising the steps of:placing a portion of-the flexible tension member between two elements having friction producing surfaces; transmitting a retaining force onto at least one of the elements causing the friction producing surfaces to apply a force directly to the flexible tension member to retain the flexible tension member between the elements; and releasing the retaining force at the desired moment to release the flexible tension member.
16. A method of controlling the release of aerially delivered cargo using a towplate having a releasable clevis assembly comprising the steps of:connecting the cargo to the clevis assembly; connecting a drogue parachute to the clevis assembly, the drogue parachute connected to the clevis assembly by means of a releasable drogue cylinder held captive between two parts of the clevis assembly, the parts being movable relative to each other between a locked position in which the drogue cylinder is held captive, and a release position; removing the two parts relative to each other to their release position when a problem is detected requiring the drogue parachute to be jettisoned; deploying the drogue parachute; and counteracting the force exerted by the drogue parachute on the clevis assembly by moving a retaining arm into engagement with a load bearing surface on the clevis assembly, wherein the load bearing surface faces in the direction of the force exerted by the drogue parachute; and disengaging the retaining arm from the load bearing surface at the desired moment.
17. A method of claim 16, wherein connecting the cargo to the clevis assembly includes connecting a flexible tension member to the clevis assembly, the flexible tension member being connected to an extraction parachute bag, wherein an extraction parachute is housed in the bag and is connected to the cargo.
18. A method of claim 16, wherein the retraining arm is moved by means of a hydraulic actuator.
19. A method of claim 18, wherein the two parts are moved relative to each other by means of a jettison hydraulic actuator.
20. A method of claim 19, wherein the two parts are maintained in a locked position by means of a detent.
21. A method of claim 20, wherein the jettison hydraulic actuator engages the detent to release it.
22. A method of claim 18, wherein the one part is movable and the other part is stationary, the movable part forming a recess for accommodating the drogue cylinder, and the stationary part having a lip for holding the drogue cylinder captive in the recess when the movable part is in its locked position.
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 US3865333: Claims:
1. In a parachute extraction system for airdropping heavy equipment and other cargo loads, an open link-safety rigged to the cargo load to be extracted and comprising; a first, recovery parachute link and first link pin for attachment to the deployment line of a recovery parachute mountable to the top of the cargo load to be extracted; a second, extraction parachute link and second link pin to which one end of the extraction line of an extraction parachute may be attached disposed in nestled relation within the end of said first-named link remote from the said recovery prachute link pin; quick-release means normally providing the sole interconnection and attachment between said first and second links; an extraction link-mounted link-locking means initially disposed in a first, link-open position relative to said second, extraction link pin and selectiv
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