WO2018204826A1 - Ensemble soupape - Google Patents

Ensemble soupape Download PDF

Info

Publication number
WO2018204826A1
WO2018204826A1 PCT/US2018/031155 US2018031155W WO2018204826A1 WO 2018204826 A1 WO2018204826 A1 WO 2018204826A1 US 2018031155 W US2018031155 W US 2018031155W WO 2018204826 A1 WO2018204826 A1 WO 2018204826A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
silicone
loop
opening
valve body
Prior art date
Application number
PCT/US2018/031155
Other languages
English (en)
Inventor
Zachary Cawvey
Amber Mcdonald
Original Assignee
Indemnis, Inc.
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 Indemnis, Inc. filed Critical Indemnis, Inc.
Publication of WO2018204826A1 publication Critical patent/WO2018204826A1/fr

Links

Classifications

    • 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
    • B64D17/62—Deployment
    • B64D17/72—Deployment by explosive or inflatable means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L3/00—Electric devices on electrically-propelled vehicles for safety purposes; Monitoring operating variables, e.g. speed, deceleration or energy consumption
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/028—Hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/0285—Safety devices
    • 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
    • B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K13/00—Other constructional types of cut-off apparatus; Arrangements for cutting-off
    • F16K13/04—Other constructional types of cut-off apparatus; Arrangements for cutting-off with a breakable closure member
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K17/00—Safety valves; Equalising valves, e.g. pressure relief valves
    • F16K17/40—Safety valves; Equalising valves, e.g. pressure relief valves with a fracturing member, e.g. fracturing diaphragm, glass, fusible joint
    • F16K17/403—Safety valves; Equalising valves, e.g. pressure relief valves with a fracturing member, e.g. fracturing diaphragm, glass, fusible joint with a fracturing valve member

Definitions

  • the present disclosure pertains to the controlled release of pressurized gas and, more particularly, to a lightweight electrically-actuated valve suitable for aerial vehicles that enables an in-flight rapid release of a pressurized fluid for the deployment of a decelerator system.
  • UAV Unmanned Aerial Vehicles
  • a UAV is generally considered to be a "powered, aerial vehicle that does not carry a human operator, uses aerodynamic forces to provide vehicle lift, can fly autonomously or be piloted remotely, can be expendable or recoverable, and can carry a lethal or nonlethal payload.”
  • UAVs have application in military uses such as reconnaissance, attack, defense against other UAVs, and targets for training, such as for criminal and terrorist attacks. They are also used in civil applications, including hobby and recreational use, commercial aerial surveillance, professional aerial surveying, commercial and motion picture filmmaking, journalism, law enforcement, search and rescue, scientific research, pollution monitoring, oil, gas and mineral exploration and production, disaster relief, archaeology, transport, agriculture, and much more.
  • UAVs Due to the multitude of uses and varying altitudes at which UAVs are flown, people and structures in the surrounding area are at risk for severe damage when the UAV fails and control is lost. UAVs are not built to the same standards as manned aerial vehicles, and frequently fail. In addition, government regulation of UAV construction and piloting is increasing, particularly with respect to the use of safety devices. Therefore, it is necessary to utilize some means to arrest an uncontrolled descent of a UAV. Current proposals include the use of non-inflatable or spring-loaded aerodynamic decelerator launch system, such as a parachute, to protect the people and structures in the surrounding area during a failure.
  • non-inflatable or spring-loaded aerodynamic decelerator launch system such as a parachute
  • parachute systems present an entirely new set of issues, including failure to deploy properly, and entanglement of the parachute lines in the propellers and control surfaces of the UAV due to improper deployment.
  • inflatable deployment techniques that ensure rapid and tangle-free opening of the parachute.
  • the present disclosure is directed to an apparatus for use in deploying a decelerator for resisting or arresting uncontrolled descent of an aerial vehicle. More particularly, the present disclosure apparatus addresses unmanned single and multi-rotor aerial vehicles, but has a purpose in other lightweight manned vehicles.
  • a solid state (no moving mechanical parts) design in which a rapid escape of pressurized fluid is provided through controlled rupture of a membrane positioned between the pressurized gas and the intended application, such as a deployment apparatus.
  • the membrane is formed of a material that is breeched by a controlled application of heat.
  • a solid state valve for use with high pressure fluid in an aerial vehicle, the valve including a valve body with an opening to permit the high pressure fluid to pass through the opening and out of the valve body, a membrane positioned over the opening in the valve body to retain the high pressure fluid in the valve body, and a wire on the membrane that is capable of burning the membrane in response to application of electricity to the wire, and thereby release the pressurized fluid from the opening in the valve body.
  • a solid state valve in accordance with yet another aspect of the present disclosure, includes a valve body, a membrane, preferably in the form of a wafer or layer of fibrous material, and wire on the fibrous material, preferably a loop of exposed Nichrome wire, and a cover.
  • a membrane preferably in the form of a wafer or layer of fibrous material
  • wire on the fibrous material preferably a loop of exposed Nichrome wire, and a cover.
  • multiple layers of silicone membranes and fasteners ae provided.
  • Application of electricity to the loop of wire causes selective failure of the membrane (or fibrous material) that results in a rapid release of a large amount of pressurized gas.
  • a valve assembly for use with an aerial vehicle.
  • the assembly includes a valve body having an internal axial bore, an intake port, and an exit port, the intake port and the exit port in fluid communication with the bore, the body having a substantially planar top face with an opening in the exit port.
  • a first layer of self-healing silicone material capable
  • a second layer of self-healing silicone material capable of being placed over the loop of exposed wire and in contact with the layer of fibrous material, the second layer of silicone material having an opening formed therein with a diameter that is sized slightly smaller than the loop of exposed wire and shaped to align with the loop of exposed wire, the opening in the first layer of silicone material, and the exit port opening to permit the passage of gas through the second layer of silicone material, a washer of silicone with a central opening having a diameter greater than the diameter of the opening in the second layer of silicone material, the washer sized and shaped to be placed over the second layer of silicone material without extending beyond the layer of fibrous material, and a cover sized and shaped to be placed over the top face of the valve body and capable of being held in place with fasteners to secure the first and second layers of silicone material, the layer of fibrous material, the loop of wire, and the washer in concentric alignment.
  • a system to deploy a parachute on an aerial vehicle includes a tank capable of storing pressurized gas; a parachute storage device; and a pneumatic valve assembly capable of coupling to the pressurized gas tank and the parachute storage device.
  • the pneumatic valve assembly includes a valve body having an internal axial bore, an intake port, and an exit port, the intake port and the exit port in fluid communication with the bore, the body having a substantially planar top face with an opening in the and partially defining the exit port.
  • a second layer of self-healing silicone material capable of being placed over the loop of exposed wire and in contact with the layer of fibrous material, the second layer of silicone material having an opening formed therein with a diameter that is sized slightly smaller than and shaped to align with the loop of exposed wire, the opening in the first layer of silicone material, and the exit port opening to permit the passage of gas through the second layer of silicone material, a washer of silicone with a central opening having a diameter greater than the diameter of the opening in the second layer of silicone material, the washer sized and shaped to be placed over the second layer of silicone material without extending beyond the layer of fibrous material, and a cover sized and shaped to be placed over the top face of the valve body and capable of being held in place with fasteners to secure the first and second layers of silicone material, the layer of fibrous material, the loop of wire, and the washer in concentric alignment.
  • the solid state design of the device avoids issues created by using moving parts, which has simplicity of design allowing for less room for failure of parts.
  • the device is not mechanically actuated and therefore not susceptible to environmental conditions and potential flight situations.
  • the device must be mechanically fastened to a pressure vessel. When triggered, the device allows compressible fluid to travel from the pressure vessel, through the device, and to the deployment apparatus, therefore causing the inflatable structure to inflate rapidly to a rigid state, moving the actual opening of the aerodynamic decelerator clear of the rotors and allowing it to function properly.
  • the device creates reliable and consistent functioning of the aerodynamic decelerator launch system in the event of UAV system failure.
  • FIG. 1 is an exploded pictorial view of a valve assembly formed in accordance with the present disclosure
  • FIG. 2 is a pictorial view of the valve assembly of FIG. 1 in a fully assembled configuration
  • FIG. 4 is a pictorial view of the valve body of FIG. 3 with a first layer of silicone material over the O-ring in accordance with the present disclosure
  • FIG. 5 is a pictorial view of the valve body of FIG. 4 with a layer of fibrous material over the first layer of silicone material in accordance with the present disclosure
  • FIG. 6 is a pictorial view of the valve body of FIG. 6 with a wrap of insulation around a portion of the wire in accordance with the present disclosure
  • FIG. 7 is a pictorial view of the valve body of FIG. 7 with a second layer of silicone material over the loop of wire and a portion of the layer of fibrous material in accordance with the present disclosure.
  • FIG. 8 is a pictorial view of the valve body of FIG. 8 with a silicone washer placed over the second layer of silicone material.
  • aerial vehicle refers to a powered airborne object controlled by a user or autonomously, such as through an automated position-control system.
  • aerial vehicles can include, without limitation, unmanned aerial vehicles, drones, manned aerial vehicles, quad copters, rockets, and the like.
  • an aerodynamic "decelerator” refers to any number of devices used to decelerate an aerial vehicle during flight, free fall, or uncontrolled flight, including without limitation a parachutes, drogue chutes, canopies, shrouds, umbrella-like devices, streamers, and inflatable devices such as airbags, balloons, and the like.
  • an aerodynamic decelerator system be properly deployed with a launch mechanism that removes the aerodynamic decelerator away from the control surfaces, thrust generators, landing gear, propellers, and rotors of the aerial vehicle in order to prevent entanglement.
  • a compressible pressurized gas is utilized. To be effective, the gas must inflate the decelerator apparatus instantaneously.
  • the present disclosure utilizes a solid-state (without moving parts) mechanism that provides a rapid release of a compressible fluid, such as pressurized gas, which causes the decelerator to instantaneously deploy and accelerate while avoiding entanglement with the aerial vehicle.
  • a compressible fluid such as pressurized gas
  • FIGS. 1 and 2 illustrate an exploded view and an assembled view of a valve assembly 20 formed in accordance with the present disclosure.
  • the valve assembly 20 includes a valve body 22, an O-ring 24, a first layer of silicone material 26, a membrane in the form of a layer of fibrous material 28, a loop of wire 30, a second layer of silicone material 32, a silicone ring or washer 34, a cover 36, and fasteners 38 that secure the cover 36 to the valve body 22.
  • FIG. 2 shows the assembled valve assembly 20 attached to the top of an air tank 40.
  • the valve body 22 is shown having an internal axial bore 42, an intake port 44, and an exit port 46, the intake port 44 and the exit port 46 in fluid communication with the bore 42.
  • the body includes a substantially planar top face 48 with an opening in the exit port 46.
  • a circular channel 50 is formed in the top face 48 that is sized and shaped to receive the O-ring 24 that itself is sized and shaped to encircle the exit port opening 46. This is shown in FIG. 3, in which the valve assembly is in the first stage of construction.
  • the first layer of self-healing silicone material 26 is placed over the O-ring 24 and in contact with the valve body top face 48.
  • the first layer of silicone 26 has an opening 52 formed therein with a diameter that is sized slightly smaller than, and shaped to align with, the exit port opening 46 to permit the passage of gas through the first layer of silicone 26;
  • the first layer of fibrous material 28 is placed over the first layer of silicone 26 and in contact with the valve body face 48 as shown in FIG. 5.
  • a circle 54 is drawn or printed on the first layer of fibrous material 28 to indicate alignment with the exit port opening 46.
  • the fibrous material 28 is cut into a circular shape to form a wafer, preferably out of Dyneema ® composite fabrics material, and holes are created for the screws 38 to pass through.
  • a 5/16" circle is drawn or printed in the center of the wafer of fibrous material 28.
  • the membrane or layer of fibrous material 28 is strong enough that it will hold the pressure, but melts at 180 degrees F.
  • high-strength fibrous materials include, but are not limited to, reinforced laminates, and composite fabrics, such as Spectra, Dyneema ® , Dyneema ® composite fabrics, Cuben Fiber, and Zylon ® , and other antiballistic material, such as ABC -Matrix ® , nanocellulose and Kevlar ® .
  • Other high-strength fibrous materials include ultra-high-molecular-weight polyethylene (UHMWPE) fibers, composites, and fiber-reinforced laminates having UHMWPE fibers.
  • UHMWPE ultra-high-molecular-weight polyethylene
  • the loop of wire 30 is shown having first and second ends 56, 58 attached to insulated first and second wire leads 60, 62, respectively.
  • the loop of exposed wire 30 is sized and shaped to have a diameter slightly larger than the diameter of the opening 52 in the first layer of silicone 26.
  • the loop 30 needs to extend just outside of the O-ring 24.
  • the pattern of the way the Nichrome wire 30 is arranged allows a partial hole to burn quickly, and essentially forms a flap in the membrane, allowing the air to pass through.
  • the insulated wire leads 60, 62 are wrapped with an insulation, such as a silicone self-healing tape 64 that extends from the loop of wire 30 to beyond the valve body 22 as shown.
  • the wire leads 60, 62 are silicone insulated 22G lead wires with insulation removed less than or equal to 1/8" from the ends.
  • the loop of exposed wire 30 is positioned on top of the layer of fibrous material 28 and in alignment with the opening 52 in the first layer of silicone 26 below the layer of fibrous material 28, with the first and second insulated wire leads 60, 62 extending beyond the valve body 22 for connection to a source of electricity.
  • the wire loop is 32G Nichrome 80 wire that is cut to a length to 1 3/4" long. It is to be understood that the wire need not be formed in a loop, and other shapes may be used depending on the design of the valve body. Any shape that creates a flap when the membrane or fibrous material is burned is suitable and preferred. By creating a flap, the material that separates from the membrane or layer of fibrous material will be partially retained or connected, and not be blown into the deployment apparatus by the escaping fluid.
  • the second layer of self-healing silicone 32 is positioned over the loop of exposed wire 30 and in contact with the layer of fibrous material 28.
  • the second layer of silicone 32 has an opening 66 formed therein with a diameter that is sized slightly smaller than, and shaped to align with, the loop of wire 30, and hence to align with the exit port opening 46, and hence the opening 52 in the first layer of silicone 26, and the loop of wire 30 to permit the passage of gas through the second layer of silicone 32.
  • FIG. 8 shows the washer of silicone 34 with a central opening 68 having a diameter greater than the diameter of the opening 66 in the second layer of silicone 32.
  • the central opening is a 7/16" hole in this implementation.
  • the washer 34 is sized and shaped to be placed over the second layer of silicone 32 material without extending beyond the layer of fibrous material 28.
  • the washer is 1/16" thick silicone and cut into 1 1/8" circular disk, and it functions to prevent pressurized gas from escaping when the valve assembly 20 opens to let air flow from the tank 40.
  • FIG. 2 it shows the cover 36 sized and shaped to be placed over the top face 48 of the valve body 22 and held in place with the plurality of threaded fasteners 38 to secure the first and second layers of silicone 26, 32, the layer of fibrous material 28, the loop of wire 30, and the washer 34 in concentric alignment.
  • Removable fasteners are preferred in order to enable reuse of the valve assembly 20 by replacing the layer of fibrous material 28 and the loop of wire 30.
  • the cover 36 includes a cylindrical extension 69 with internal threads for connection to a container for the decelerator, such as a parachute.
  • valve assembly is constructed out of machined metal, 3D printed metal, or 3D printed plastic.
  • This valve body 22 includes a one-way fill port 70 and a mechanical or digital pressure gauge 72, as well as internal materials not relevant to this disclosure.
  • valve assembly 20 is just one component of an aerodynamic decelerator launch system.
  • a proprietary control system uses an algorithm to auto detect failure in the UAV flight characteristics. Upon detection of failure, it will trigger a storage capacitor to send 12 V of power to the wires 60, 62, and the Nichrome loop of wire 30 instantly heats, burning a partial hole through the membrane or layer of fibrous material, which allows the pressurized fluid, such as air, to rapidly dump from the tank, through the valve body, through the membrane, and into the decelerator container, thus launching the aerodynamic decelerator.
  • a 16V capacitor is used, and the voltage optimal range is 9-12 V.
  • the valve assembly 20 was created for high pressure use, in one implementation at 3,000 psi or below so that it can be easily recharged locally.
  • a burst disc is a standard safety feature required on all high pressure vessels and is located on the side of the valve body 22 in the event the tank is overfilled.
  • the device is lightweight and small, having little impact on speed and performance of the aerial vehicle. It also has simplicity of design, thus avoiding failure of mechanical parts.
  • the device is not mechanically actuated and therefore is not susceptible to environmental conditions and potential flight situations.
  • the device must be mechanically fastened or welded to a pressure vessel. When triggered, the device allows compressible fluid to travel from the pressure vessel, through the device, and to the deployment apparatus, therefore causing the inflatable structure to rapidly inflate to a rigid state, moving the actual opening of the aerodynamic decelerator clear of the rotors and allowing it to properly function.
  • the device creates reliable and consistent functioning of the aerodynamic decelerator launch system in the event of UAV system failure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Power Engineering (AREA)
  • Transportation (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

La présente invention concerne une soupape à l'état solide comprenant : un corps de soupape, doté d'une ouverture destinée au passage d'un fluide haute pression ; une membrane, positionnée au-dessus de l'ouverture pour retenir le fluide haute pression dans le corps de soupape ; et un fil, sur la membrane, l'application de l'électricité au fil provoquant une défaillance sélective de la membrane conduisant à une libération rapide d'une grande quantité de fluide sous pression à travers le corps de soupape et à travers la membrane.
PCT/US2018/031155 2017-05-05 2018-05-04 Ensemble soupape WO2018204826A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762501920P 2017-05-05 2017-05-05
US62/501,920 2017-05-05

Publications (1)

Publication Number Publication Date
WO2018204826A1 true WO2018204826A1 (fr) 2018-11-08

Family

ID=64016743

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2018/031155 WO2018204826A1 (fr) 2017-05-05 2018-05-04 Ensemble soupape

Country Status (1)

Country Link
WO (1) WO2018204826A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3967906A1 (fr) * 2020-09-11 2022-03-16 SISTO Armaturen S.A. Agencement de membrane à des propriétés d'auto-guérison

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040021307A1 (en) * 2002-08-01 2004-02-05 Ziolo Melissa S. Airbag module using active venting membrane
US20100180953A1 (en) * 2006-04-11 2010-07-22 University Of South Florida Thermally Induced Single-Use Valves and Method of Use
US8383256B1 (en) * 2009-11-06 2013-02-26 Advanced Numicro Systems, Inc. MEMS safety valve for batteries

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040021307A1 (en) * 2002-08-01 2004-02-05 Ziolo Melissa S. Airbag module using active venting membrane
US20100180953A1 (en) * 2006-04-11 2010-07-22 University Of South Florida Thermally Induced Single-Use Valves and Method of Use
US8383256B1 (en) * 2009-11-06 2013-02-26 Advanced Numicro Systems, Inc. MEMS safety valve for batteries

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3967906A1 (fr) * 2020-09-11 2022-03-16 SISTO Armaturen S.A. Agencement de membrane à des propriétés d'auto-guérison

Similar Documents

Publication Publication Date Title
US9527596B1 (en) Remote controlled aerial reconnaissance vehicle
US10435153B2 (en) Nets and devices for facilitating capture of unmanned aerial vehicles
US10996041B2 (en) Devices and methods for facilitating blast and dispersion mitigation
US9033281B1 (en) Remote controlled aerial reconnaissance vehicle
AU2016337362B2 (en) Parachute control system for an unmanned aerial vehicle
US8708285B1 (en) Micro-unmanned aerial vehicle deployment system
US6260797B1 (en) Transformable gun launched aero vehicle
US10618663B2 (en) Intelligent parachute rescue system for manned and unmanned aerial vehicles
US6142421A (en) Vehicle refueling system
US9889941B1 (en) Inflatable deployment apparatus for descent-restraint system for aerial vehicles
US11231254B1 (en) System for physically defeating unmanned aerial vehicles
US11958619B2 (en) Aircraft provided with a secondary flight assembly
US20220299296A1 (en) Decoy system
US20240043108A1 (en) Drogue deployment for lighter than air vehicle descent
WO2018204826A1 (fr) Ensemble soupape
US3282539A (en) Recovery system
RU141797U1 (ru) Универсальная система спасения космического аппарата на старте, использующая двигатель разгонного блока
CN109204769B (zh) 一种空中投放的小型零风层浮空气球
US20170225755A1 (en) Weapons Control System-Deployable Life Support Apparatus
Xiong et al. Structure and control design of air-droppable ground-based surveillance equipment
RU2544023C1 (ru) Система спасения космического аппарата
ITPV20130003A1 (it) Sistema per espulsione di paracadute, in particolare per drone
KR20180024731A (ko) 회전익 드론 안전착륙팩
Hintzke et al. Demonstration of a parafoil based mid-air retrieval system for an unmanned air vehicle

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18794563

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18794563

Country of ref document: EP

Kind code of ref document: A1