GB2219777A - Flying object recovery system - Google Patents

Flying object recovery system Download PDF

Info

Publication number
GB2219777A
GB2219777A GB8913423A GB8913423A GB2219777A GB 2219777 A GB2219777 A GB 2219777A GB 8913423 A GB8913423 A GB 8913423A GB 8913423 A GB8913423 A GB 8913423A GB 2219777 A GB2219777 A GB 2219777A
Authority
GB
United Kingdom
Prior art keywords
parasail
filamentary material
riser portions
boom
sub
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB8913423A
Other versions
GB8913423D0 (en
Inventor
Douglas Richard Taylor
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems Electronics Ltd
Original Assignee
GEC Marconi Ltd
Marconi Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by GEC Marconi Ltd, Marconi Co Ltd filed Critical GEC Marconi Ltd
Publication of GB8913423D0 publication Critical patent/GB8913423D0/en
Publication of GB2219777A publication Critical patent/GB2219777A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
    • B64F1/029—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables using a cable or tether
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/30—Launching, take-off or landing arrangements for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Refuse Collection And Transfer (AREA)
  • Catching Or Destruction (AREA)
  • Refuse-Collection Vehicles (AREA)

Abstract

A flying object, e.g. an unmanned aircraft (29) recovery system comprising a recovery site arrester sub-system (1) incorporating hook means (13) and an object-borne sub-system (27) incorporating parasail lift means (31) and looped filamentary material (33) connected between the object and the parasail lift means. In operation, upon deployment of the object-borne system whilst the object is in flight, the looped filamentary material is aerially extended and supported by action of the parasail lift means, thereby facilitating engagement of the filamentary material with the hook means. <IMAGE>

Description

Flying Object Recovery Systems This invention relates to flying object recovery systems.
More especially, although not exclusively, the invention relates to such systems suitable for the recovery of unmanned aircraft to ships.
Known methods of recovering unmanned aircraft to ships fall under one or other of four headings; controlled vertical landing; flight into a vertically disposed net; landing on an open deck; and parachute descent into the sea. Controlled vertical landing is only open to aircraft which can generate sufficient vertical thrust, e.g. helicopters. Flight into a vertically disposed net is successful only for aircraft of suitable configuration, e.g. narrow delta; for a straight winged aircraft the method has the severe disadvantage that high loadings are placed upon the wings and since first encounter is likely to be at a point forward of the centre of gravity of the aircraft, the aircraft tends to tumble In retardation, resulting in a high probability of damage to the aircraft.For a fixed wing aircraft the space requirements for landing on an open deck are prohibitive and the piloting or control problems associated with this method are considerable; also, In the case of a missed recovery the probably of damage to the ship or Injury to personnel is high.
The disadvantages of the method of parachute descent into the sea include possible damage on Impact, water contamination and the remaining problem of recovery to the ship.
It is an object of the present invention to provide an system for use in the recovery of a flying object whereby the above difficulties may be overcome.
According to the present Invention there is provided a flying object recovery system comprising: a recovery site arrester sub-system incorporating hook means; and an object-borne sub-system incorporating parasail lift means and looped filamentary material connected between said object and the parasail lift means so that, in flight of the object, upon deployment of the object-borne sub-system, the looped filamentary material is aerially extended and supported by action of the parasail lift means so as to facilitate engagement of the filamentary material with the hook means.
In one embodiment of the invention said parasail lift means comprises a single parasail member and said filamentary material comprises a first portion incorporated into the leading edge of the parasail member so as to extend spanwise on deployment of the parasail member, and at least two riser portions each extending between the first portion and the object.
In another embodiment of the invention said parasail lift weans comprises first and second parasail members, and said filamentary material comprises, for each said parasail member, a first portion incorporated into the leading edge of the parasall member so as to extend spanwise on deployment of the parasail ember, and two riser portions each extending between the first portion and the object, and a third portion extending between one of the riser portions associated with one of the parasail members and one of the riser portions associated with the other parasail member.
In a further embodiment of the invention said parasail lift means comprises first and second parasail members, and said filamentary material comprises, for each parasail member, a first portion incorporated into the leading edge of the parasail member so as to extend spanwise on deployment of the parasail member, and two riser portions each extending between the first portion and the object, a first further portion extending between the end remote from the first parasail member of one of the riser portions associated with the first parasall member and the end remote from the second parasail member of one of the riser portions associated with the second parasail member, and second and third further portions each of which extends between the object and the end remote from its associated parasail member of a respective other one of the riser portions.
In one particular system according to the invention said hook means is secured to a boom which is mounted at one end for rotation about a substantially vertical axis in a substantially horizontal plane on engagement of said filamentary material with said hook means in operation of the system, and the recovery site sub-system further includes means for retarding rotation of said boom.
In one such particular system said hook means Is detachably secured to said boom and connected with said boom and said means for retarding by way of a wire so that on engagement of said filamentary material with said hook means in operation of the system, said hook means is detached from the boom thereby to cause the boom to rotate against the restraining force of the retarding means.
One recovery system is accordacne with the invention for recovering unmanned aircraft to a ship will now be described,by way of example, with reference to the accompanying drawings in which: Figure 1 is a general view of the system; Figure 2 is a plan view from above of a ship-borne sub-system of the recovery system in four consecutive positions during recovery; Figures 3, 4 and 5 illustrate various possible forms of an aircraft-borne sub-system of the recovery system.
Referring to Figures 1 and 2, the recovery system includes a recovery site arrester sub-system 1 mounted on the ship 3. The sub-system 1 includes a swingable boom 5 pivotally mounted at one end to the side of the ship 3 for rotation about a vertical axis in a substantially horizontal plane.
The boom 5 is supported by a guy wire 7 extending upwardly from the end of the boom 5 remote from the ship 3 to a point on the ship, and a forestay 9 extending generally horizontally from the end of the boom 5 remote from the ship 3 to a point forward of the boom 3 in the direction of flight of an aircraft during recovery to a tensioner 11 for the stay 9 mounted on the ship 3.
The sub-system 1 also includes an aircraft arresting hook 13 which is detachably secured to the boom 5 at a position at the end of the boom remote from the ship by a catch (not shown) prior to a recovery operation. The hook 13 carries a sheave 15 and a second sheave 17 is hingedly secured to the boom 5 near its end remote from the ship 3. The sheaves 15 and 17 co-operate with a length of arrester wire 18 which is secured at each end to the end of the boom 5 remote from the ship 3, and between its ends passes in turn around the hook sheave 15, then the boom sheave 17 and then a third sheave 21 which is attached to one end of a retardation wire 23 the other end of which is attached to an arrester unit 25 mounted on the ship 3 which controls the speed which the retardation wire 23 is paid out.
Referring now also to Figure 3, the recovery system further includes an aircraft-borne sub-system 27 mounted on the -unmanned aircraft 29 to be recovered. The sub-system 27 comprises a parasail lift means 31 and looped filamentary material 33 connected with the parasail lift means 31 and attached to the aircraft.
In operation of the recovery system on approach of the aircraft 29 to the ship 3 the sub-system 27 is deployed from the aircraft causing the filamentary material 33 to engage the hook 13 In its position at the end of the boom 5. It will be appreciated that the material 33 typically first contacts and moves along the boom 5 before engaging the hook 13.
Referring particularly to Figure 2, after the hook 13 has been engaged by the filamentary material 33 with the hook 13 and boom 5 positioned as shown at I in Figure 2, the hook 13 Is first pulled off the boom 5 forwardly of the boom 5. Consequently, the arrester wire 13 is also pulled forwardly of the boom 5 with consequent movement of the sheave 21 such as to pull on the retardation wire 23 against the restraining force of the arrester unit 25. After the inertia of the boom 5 is overcome, the boom 5 rotates forwardly on its pivot, further pulling on the retardation wire 23, as shown at II and III in Figure 2. The forward motion of the aircraft 29 is consequently rapidly retarded until it eventually comes to rest with the aircraft 29 hanging beneath the boom 5 suspended from the hook 5 by the filamentary material 33, clear of the side of the ship 3, as shown at IV in Figure 2.The boom 5 is then swung inboard of the ship 3 and the aircraft 29 unhooked.
In the embodiment of the aircraft-borne sub-system 27 shown in Figures 1 and 3 the parasail lift means 31 comprises a single parasail member. The filamentary material 33 comprises a portion 33A incorporated into the leading edge of the parasail member 31 so as to extend spanwise on deployment first and second riser portions 33B formed as a unitary member with the portion 33A and each leading from a respective end of the spanwise extending portion 33A and attached at its end remote from the spanwise extending portion 33A to the aircraft 29, two further riser portions 33C extending from the aircraft 29 to intermediate points along the spanwise extending portion 33A and cross portions 33D extending between the riser portions 33B, C. The further riser portions 33C and cross portions 33D may be omitted, If desired.
Further risers 35 of filamentary material extending between the aircraft 29 and the rear edge of the parasail 31 are also provided, but these may be of a less strong material than the material 33, since they play no part in the recovery action.
In a second embodiment of the sub-system 27, shown in Figure 4, the parasail lift means comprises two parasail members 37 and 39 and the filamentary material comprises, for each of the parasail member 37and 39, a spanwise extending portion 41A or 43A incorporated into the leading edge of the associated parasail member 37 or 39, two riser portions 41B and 41C or 43B and 43C formed as a unitary member with their associated spanwise extending portion 41A or 43A and each leading from a respective end of its associated spanwise extending portion 41A or 43A, and attached at its end remote from the associated spanwise extending portion 41A or 43A to the aircraft 29. In addition, a cross portion 45 is connected between the inner two riser portions 41C and 43B at their ends adjacent the parasail members 37, 39.
In a third embodiment of the sub-system 27 shown in Figure 5 the parasail lift means comprises two parasail members 47 and 49 and the filamentary material comprises, for each of the parasail members 47 and 49, a spanwise extending portion 51A or 53A incorporated into the leading edge of the associated parasail member 47 or 49, and two riser portions 51B and 51C or 53B and 53C formed as a unitary member with their associated spanwise extending portion 51A or 53A and each leading from a respective end of its associated spanwise extending portion 51A or 53A and attached at its end remote from the associated spanwise extending portion to the aircraft 29. In addition the filamentary material includes three further portions 55A, 55B and 55C, one 55A of which extends between the end of the inner riser portion 51C remote from the associated spanwise extending portion 51A and the corresponding end of the inner riser portion 53B, and the other two 55B and 55C of which each extends from the end of a respective one of the two outer riser portions 51B and 53C and the aircraft 29.
The embodiments of the aircraft-borne sub-system 27 shown in Figures 4 and 5 find application where the single parasail member of the embodiment of Figure 3 results In excessive drag.

Claims (10)

1. A flying object recovery system comprising: a recovery site arrester sub-system incorporating hook means; and an object-borne sub-system incorporating parasail lift means and looped filamentary material connected between said object and the parasail lift means so that, in flight of the object, upon deployment of the object-borne sub-system, the looped filamentary material Is aerially extended and supported by action of the parasail lift means so as to facilitate engagement of the filamentary material with the hook means.
2. A system according to Claim 1 wherein said parasail lift means comprises a single parasail member and said filamentary material comprises a first portion incorporated into the leading edge of the parasail member so as to extend spanwise on deployment of the parasail member, and at least two riser portions each extending between the first portion and the object.
3. A system according to Claim 2 wherein said filamentary material includes at least one further portion extending between adjacent riser portions.
4. A system according to Claim 1 wherein said parasail lift means comprises first and second parasail members, and said filamentary material comprises, for each said parasail member, a first portion incorporated into the leading edge of the parasail member so as to extend spanwise on deployment of the parasail member, and two riser portions each extending between the first portion and the object, and a third portion extending between one of the riser portions associated with one of the parasail members and one of the riser portions associated with the other parasail member.
5. A system according to Claim 4 wherein said third portion extends between the ends of said riser portions adjacent the parasail members.
6. A system according to Claim 1 wherein said parasail lift means comprises first and second parasail members, and said filamentary material comprises, for each parasail member, a first portion incorporated into the leading edge of the parasail member so as to extend spanwise on deployment of the parasall member, and two riser portions each extending between the first portion and the object, a first further portion extending between the end remote from the first parasail member of one of the riser portions associated with the first parasail member and the end remote from the second parasail member of one of the riser portions associated with the second parasail member, and second and third further portions each of which extends between the object and the end remote from its associated parasail member of a respective other one of the riser portions.
7. A system according to any one of Claims 2 to 6 wherein, for the or each said parasail member, said first portion and said two riser portions are formed as a unitary member.
8. A system according to any one of the preceding claims wherein said hook means is secured to a boom which is mounted at one end for rotation about a substantially vertical axis in a substantially horizontal plane on engagement of said filamentary material with said hook means in operation of the system, and the recovery site sub-system further includes means for retarding rotation of said boom.
9. A system according to Claim 8 wherein said hook means is detachably secured to said boom and connected with said boom and said means for retarding by way of a wire so that on engagement of said filamentary material with said hook means in operation of the system, said hook means is detached from the boom thereby to cause the boom to rotate against the restraining force of the retarding means.
10. A flying object recovery system substantially as hereinbefore described with reference to Figures 1, 2 and 3, Figures 1, 2 and 4, or Figures 1, 2 and 5.
GB8913423A 1988-06-15 1989-06-12 Flying object recovery system Withdrawn GB2219777A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB888814178A GB8814178D0 (en) 1988-06-15 1988-06-15 Aircraft recovery systems

Publications (2)

Publication Number Publication Date
GB8913423D0 GB8913423D0 (en) 1989-08-02
GB2219777A true GB2219777A (en) 1989-12-20

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GB888814178A Pending GB8814178D0 (en) 1988-06-15 1988-06-15 Aircraft recovery systems
GB8913423A Withdrawn GB2219777A (en) 1988-06-15 1989-06-12 Flying object recovery system

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Application Number Title Priority Date Filing Date
GB888814178A Pending GB8814178D0 (en) 1988-06-15 1988-06-15 Aircraft recovery systems

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2231011A (en) * 1989-05-03 1990-11-07 Marconi Gec Ltd Aircraft capture system
DE4301671A1 (en) * 1992-01-22 1993-07-29 Nord Systemtechnik Recovery system for drone etc. - has catch line held in frame to lock into hook held above drone, with retarding mounting for line.
WO2001007318A1 (en) * 1999-07-23 2001-02-01 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US6874729B1 (en) 1999-07-23 2005-04-05 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US7578467B2 (en) 2006-10-30 2009-08-25 Insitu, Inc. Methods and apparatuses for indicating and/or adjusting tension in pliant tension members, including aircraft recovery lines
US7712702B2 (en) 2003-01-17 2010-05-11 Insitu, Inc. Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and breaking subsequent grip motion
US7798445B2 (en) 2008-01-25 2010-09-21 Insitu, Inc. Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft
US7806366B2 (en) 2007-07-10 2010-10-05 Insitu, Inc. Systems and methods for capturing and controlling post-recovery motion of unmanned aircraft
US8944373B2 (en) 2010-09-27 2015-02-03 Insitu, Inc. Line capture devices for unmanned aircraft, and associated systems and methods
US9266610B2 (en) 2011-11-15 2016-02-23 Insitu, Inc. Controlled range and payload for unmanned vehicles, and associated systems and methods
US9896222B2 (en) 2014-11-20 2018-02-20 Insitu, Inc. Capture devices for unmanned aerial vehicles, including track-borne capture lines, and associated systems and methods
US9944408B2 (en) 2009-04-24 2018-04-17 Insitu, Inc. Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft
US10399674B2 (en) 2014-07-28 2019-09-03 Insitu, Inc. Systems and methods countering an unmanned air vehicle
US10407181B2 (en) 2016-06-27 2019-09-10 Insitu, Inc. Locking line capture devices for unmanned aircraft, and associated systems and methods
US10767682B2 (en) 2017-06-29 2020-09-08 Insitu, Inc. Frangible fasteners with flexible connectors for unmanned aircraft, and associated systems and methods
US10933997B2 (en) 2015-10-02 2021-03-02 Insitu, Inc. Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods
US11066185B2 (en) 2018-05-04 2021-07-20 Insitu, Inc. Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods
US11142339B2 (en) 2018-05-04 2021-10-12 Insitu, Inc. Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1471583A (en) * 1974-04-03 1977-04-27 British Aircraft Corp Ltd Aircraft recovery means and method
GB2036668A (en) * 1978-12-02 1980-07-02 Messerschmitt Boelkow Blohm Horizontal landing arrangement for a flying body
US4311290A (en) * 1979-11-01 1982-01-19 The United States Of America As Represented By The Secretary Of The Navy Arrestment system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1471583A (en) * 1974-04-03 1977-04-27 British Aircraft Corp Ltd Aircraft recovery means and method
GB2036668A (en) * 1978-12-02 1980-07-02 Messerschmitt Boelkow Blohm Horizontal landing arrangement for a flying body
US4311290A (en) * 1979-11-01 1982-01-19 The United States Of America As Represented By The Secretary Of The Navy Arrestment system

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2231011A (en) * 1989-05-03 1990-11-07 Marconi Gec Ltd Aircraft capture system
US5054717A (en) * 1989-05-03 1991-10-08 Gec Marconi Limited Aircraft capture systems
GB2231011B (en) * 1989-05-03 1992-09-30 Marconi Gec Ltd Aircraft capture systems
DE4301671A1 (en) * 1992-01-22 1993-07-29 Nord Systemtechnik Recovery system for drone etc. - has catch line held in frame to lock into hook held above drone, with retarding mounting for line.
US8517306B2 (en) 1999-07-23 2013-08-27 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US8864069B2 (en) 1999-07-23 2014-10-21 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US6874729B1 (en) 1999-07-23 2005-04-05 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
AU782704B2 (en) * 1999-07-23 2005-08-25 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
EP1233905A4 (en) * 1999-07-23 2005-09-28 Advanced Aerospace Technologie Launch and recovery system for unmanned aerial vehicles
US7097137B2 (en) 1999-07-23 2006-08-29 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
WO2001007318A1 (en) * 1999-07-23 2001-02-01 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
EP1233905A1 (en) * 1999-07-23 2002-08-28 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US8567718B1 (en) 1999-07-23 2013-10-29 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US9669946B2 (en) 1999-07-23 2017-06-06 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US8167242B2 (en) 1999-07-23 2012-05-01 Advanced Aerospace Technologies, Inc. Launch and recovery system for unmanned aerial vehicles
US7712702B2 (en) 2003-01-17 2010-05-11 Insitu, Inc. Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and breaking subsequent grip motion
US7578467B2 (en) 2006-10-30 2009-08-25 Insitu, Inc. Methods and apparatuses for indicating and/or adjusting tension in pliant tension members, including aircraft recovery lines
US7806366B2 (en) 2007-07-10 2010-10-05 Insitu, Inc. Systems and methods for capturing and controlling post-recovery motion of unmanned aircraft
US7798445B2 (en) 2008-01-25 2010-09-21 Insitu, Inc. Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft
US10843817B2 (en) 2009-04-24 2020-11-24 Insitu, Inc. Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft
US9944408B2 (en) 2009-04-24 2018-04-17 Insitu, Inc. Systems and methods for recovering and controlling post-recovery motion of unmanned aircraft
US9340301B2 (en) 2010-09-27 2016-05-17 Insitu, Inc. Line capture devices for unmanned aircraft, and associated systems and methods
US10981671B2 (en) 2010-09-27 2021-04-20 Insitu, Inc. Line capture devices for unmanned aircraft, and associated systems and methods
US9856036B2 (en) 2010-09-27 2018-01-02 Insitu, Inc. Line capture devices for unmanned aircraft, and associated systems and methods
US8944373B2 (en) 2010-09-27 2015-02-03 Insitu, Inc. Line capture devices for unmanned aircraft, and associated systems and methods
US10501178B2 (en) 2011-11-15 2019-12-10 Insitu, Inc. Controlled range and payload for unmanned vehicles, and associated systems and methods
US9868527B2 (en) 2011-11-15 2018-01-16 Insitu, Inc. Controlled range and payload for unmanned vehicles, and associated systems and methods
US9266610B2 (en) 2011-11-15 2016-02-23 Insitu, Inc. Controlled range and payload for unmanned vehicles, and associated systems and methods
US10399674B2 (en) 2014-07-28 2019-09-03 Insitu, Inc. Systems and methods countering an unmanned air vehicle
US11161610B2 (en) 2014-07-28 2021-11-02 Insitu, Inc. Systems and methods for countering an unmanned air vehicle
US10513350B1 (en) 2014-11-20 2019-12-24 Insitu, Inc. Capture devices for unmanned aerial, vehicles, including track-borne capture lines, and associated systems and methods
US9896222B2 (en) 2014-11-20 2018-02-20 Insitu, Inc. Capture devices for unmanned aerial vehicles, including track-borne capture lines, and associated systems and methods
US11053024B2 (en) 2014-11-20 2021-07-06 Insitu, Inc. Capture devices for unmanned aerial vehicles, including track-borne capture lines, and associated systems and methods
US10933997B2 (en) 2015-10-02 2021-03-02 Insitu, Inc. Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods
US11858631B2 (en) 2015-10-02 2024-01-02 Insitu, Inc. Aerial launch and/or recovery for unmanned aircraft with submersible devices, and associated systems and methods
US10407181B2 (en) 2016-06-27 2019-09-10 Insitu, Inc. Locking line capture devices for unmanned aircraft, and associated systems and methods
US10967987B2 (en) 2016-06-27 2021-04-06 Insitu, Inc. Locking line capture devices for unmanned aircraft, and associated systems and methods
US10767682B2 (en) 2017-06-29 2020-09-08 Insitu, Inc. Frangible fasteners with flexible connectors for unmanned aircraft, and associated systems and methods
US11066185B2 (en) 2018-05-04 2021-07-20 Insitu, Inc. Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods
US11142339B2 (en) 2018-05-04 2021-10-12 Insitu, Inc. Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods
US11603216B2 (en) 2018-05-04 2023-03-14 Insitu, Inc. Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods

Also Published As

Publication number Publication date
GB8814178D0 (en) 1988-11-16
GB8913423D0 (en) 1989-08-02

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