IL309827A - Rotating release launching system - Google Patents

Rotating release launching system

Info

Publication number
IL309827A
IL309827A IL309827A IL30982723A IL309827A IL 309827 A IL309827 A IL 309827A IL 309827 A IL309827 A IL 309827A IL 30982723 A IL30982723 A IL 30982723A IL 309827 A IL309827 A IL 309827A
Authority
IL
Israel
Prior art keywords
payload
deployment mechanism
configurable
payload deployment
hinge
Prior art date
Application number
IL309827A
Other languages
Hebrew (he)
Inventor
Nicholas Robert Alley
Jesse Owen Williams
Matthew Gordon Brasher
Original Assignee
Anduril Ind Inc
Nicholas Robert Alley
Jesse Owen Williams
Matthew Gordon Brasher
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
Priority claimed from US18/307,609 external-priority patent/US20230257117A1/en
Application filed by Anduril Ind Inc, Nicholas Robert Alley, Jesse Owen Williams, Matthew Gordon Brasher filed Critical Anduril Ind Inc
Priority claimed from PCT/US2023/020111 external-priority patent/WO2023239489A1/en
Publication of IL309827A publication Critical patent/IL309827A/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/10—Stabilising surfaces adjustable
    • B64C5/12—Stabilising surfaces adjustable for retraction against or within fuselage or nacelle
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
    • B64D1/12—Releasing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/40—Packs
    • B64D17/52—Opening, e.g. manual
    • B64D17/54—Opening, e.g. manual automatic
    • B64D17/60—Opening, e.g. manual automatic by static line
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • B64D25/08—Ejecting or escaping means
    • B64D25/12—Ejectable capsules
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F5/00—Launching-apparatus for gravity-propelled missiles or projectiles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
    • B64D7/08—Arrangements of rocket launchers or releasing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/56—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of parachute or paraglider type

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Toys (AREA)
  • Control Of Vending Devices And Auxiliary Devices For Vending Devices (AREA)
  • Peptides Or Proteins (AREA)
  • Nozzles (AREA)

Claims (20)

THE FOLLOWING IS CLAIMED:
1. A payload deployment mechanism, comprising: a body portion; a bay area partially defined by the body portion; a configurable payload operative to detachably connect to the body portion of the payload deployment mechanism; a force generating mechanism attached to the payload deployment mechanism, the force generating mechanism configured to impart force to the configurable payload to separate the configurable payload from the payload deployment mechanism; and a hinge mechanism configured to control the separation of the configurable payload from the payload deployment mechanism, the hinge mechanism being configured to pivot about a pivot point located external to the payload deployment mechanism.
2. The payload deployment mechanism of Claim 1, wherein the payload deployment mechanism is configured to retain the configurable payload by at least one latch assembly comprising at least one biasing mechanism.
3. The payload deployment mechanism of Claim 1, wherein the configurable payload is shaped to generate drag and create additional force to detach the configurable payload from the payload deployment mechanism as it separates from the payload deployment mechanism.
4. The payload deployment mechanism of Claim 3, wherein the configurable payload comprises at least one of a forward edge of the configurable payload or a side portion of the configurable payload configured to generate the drag.
5. The payload deployment mechanism of Claim 3, wherein the configurable payload is integrated into the payload deployment mechanism without affect to aerodynamics of the payload deployment mechanism while attached to the payload deployment mechanism.
6. The payload deployment mechanism of Claim 3, wherein the generated drag from the configurable payload causes separation of the configurable payload from the payload deployment mechanism.
7. The payload deployment mechanism of Claim 1, further comprising at least one vent configured to direct external airflow into the payload deployment mechanism.
8. The payload deployment mechanism of Claim 7, wherein the at least one vent directs the external airflow into the payload deployment mechanism to equalize air with external air pressure as the configurable payload separates form the payload deployment mechanism.
9. The payload deployment mechanism of Claim 1, wherein the hinge mechanism comprises a first hinge component and a second hinge component.
10. The payload deployment mechanism of Claim 9, wherein the first hinge component on the payload deployment mechanism and the second hinge component on the configurable payload separate to deploy the configurable payload.
11. The payload deployment mechanism of Claim 1, wherein the hinge mechanism is located at an aft end of the configurable payload.
12. The payload deployment mechanism of Claim 1, further comprising a parachute attached to the configurable payload.
13. The payload deployment mechanism of Claim 12, wherein the parachute is disposed within the payload deployment mechanism before deployment.
14. The payload deployment mechanism of Claim 12, wherein the parachute is configured to deploy due to the separation of the configurable payload from the payload deployment mechanism.
15. The payload deployment mechanism of Claim 12, wherein the parachute is a static line parachute.
16. The payload deployment mechanism of Claim 1, wherein the hinge mechanism is configured to prevent the configurable payload from contacting the payload deployment mechanism after separation of the configurable payload from the payload deployment mechanism.
17. The payload deployment mechanism of Claim 1, wherein the payload deployment mechanism is incorporated into an aerial vehicle.
18. The payload deployment mechanism of Claim 1, wherein the payload deployment mechanism is configured to be connected to an aircraft by a coupling assembly arranged between the payload deployment mechanism and a portion of the aircraft.
19. The payload deployment mechanism of Claim 1, wherein the bay area is partially defined by a cavity in the payload deployment mechanism.
20. The payload deployment mechanism of Claim 1, wherein the configurable payload comprises one or more of: a drone, a sensor, a buoy, a munition, an unmanned aerial vehicle, or an object suitable for deployment from within the payload deployment mechanism.
IL309827A 2023-04-26 2023-04-27 Rotating release launching system IL309827A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US18/307,609 US20230257117A1 (en) 2020-05-04 2023-04-26 Rotating release launching system
PCT/US2023/020111 WO2023239489A1 (en) 2023-04-26 2023-04-27 Rotating release launching system

Publications (1)

Publication Number Publication Date
IL309827A true IL309827A (en) 2024-02-01

Family

ID=88839999

Family Applications (1)

Application Number Title Priority Date Filing Date
IL309827A IL309827A (en) 2023-04-26 2023-04-27 Rotating release launching system

Country Status (3)

Country Link
EP (1) EP4330136A1 (en)
CA (1) CA3219454A1 (en)
IL (1) IL309827A (en)

Also Published As

Publication number Publication date
CA3219454A1 (en) 2023-11-09
EP4330136A1 (en) 2024-03-06

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