WO2016200407A1 - Systèmes pour opérations dans l'espace proche - Google Patents

Systèmes pour opérations dans l'espace proche Download PDF

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Publication number
WO2016200407A1
WO2016200407A1 PCT/US2015/035668 US2015035668W WO2016200407A1 WO 2016200407 A1 WO2016200407 A1 WO 2016200407A1 US 2015035668 W US2015035668 W US 2015035668W WO 2016200407 A1 WO2016200407 A1 WO 2016200407A1
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WO
WIPO (PCT)
Prior art keywords
payload
human
structured
stratospheric
visit
Prior art date
Application number
PCT/US2015/035668
Other languages
English (en)
Inventor
Taber K. Maccallum
Jacob H. DANG
Robert Alan EUSTACE
John Zaniel Maccagnano
Julian R. NOTT
Sebastian A. Padilla
Sreenvinasan SHANKARNARAYAN
John Straus
Jared Leidich
Daniel Pieter Jacobus BLIGNAUT
Original Assignee
World View Enterprises, 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 World View Enterprises, Inc. filed Critical World View Enterprises, Inc.
Priority to PCT/US2015/035668 priority Critical patent/WO2016200407A1/fr
Publication of WO2016200407A1 publication Critical patent/WO2016200407A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/026—Aircraft not otherwise provided for characterised by special use for use as personal propulsion unit
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • B64B1/50—Captive balloons
    • 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
    • B64C31/036—Hang-glider-type aircraft; Microlight-type aircraft having parachute-type wing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D10/00—Flight suits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • 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
    • B64F1/12—Anchoring
    • B64F1/14—Towers or masts for mooring airships or balloons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D10/00—Flight suits
    • B64D2010/005—High altitude suits or garments, e.g. partial or total pressure

Definitions

  • This invention relates to providing a system for high altitude and near-space operations. More particularly, this invention relates to providing a system enabling safe manned and unmanned operations at extremely high altitudes (above about 70,000 feet). Even more particularly, this invention relates to providing such systems enabling stratospheric visits. And even more particularly, this invention relates to providing such systems enabling stratospheric visits using lighter-than-air vehicles.
  • a primary object and feature of the present invention is to provide a system addressing the above-mentioned need(s). It is a further object and feature of the present invention to provide such a system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). It is a further object and feature of the present invention to provide such a system enabling stratospheric visits using lighter-than-air vehicles. It is another object and feature of the present invention to provide such a system enabling a multi-crew, multi-passenger vehicle utilizing balloon accent and parawing recovery. It is a further object and feature of the present invention to provide such a system enabling "shirt-sleeve" crew/passenger operation.
  • a further primary object and feature of the present invention is to provide such a system that is efficient, inexpensive, and useful.
  • this invention provides a stratospheric- visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive- resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. Also, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • such a stratospheric-visit system wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso- coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive- resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. Even further, it provides such a stratospheric-visit system wherein such a payload
  • such parachute system comprises at least one parafoil. Additionally, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Also, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance- separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • such a stratospheric-visit system wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive- resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. Additionally, it provides such a stratospheric-visit system wherein such a payload ground
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than- air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support
  • a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload
  • a communication system structured and arranged to communicate within such stratospheric-visit system
  • a recovery system structured and arranged to recover at least the at least one human
  • such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground- traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system
  • such injury- minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system
  • such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system
  • payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Further, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • such a stratospheric-visit system wherein at least portions of such environmental control system and such communication system comprise at least one equipment module;
  • such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human;
  • such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises
  • compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Also, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive- resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. Even further, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module;
  • such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit
  • the at least one payload launches with such lighter-than-air propulsion system.
  • the payload system comprises a stratospheric-visit vehicle structured and arranged to transport multiple humans on the stratospheric visit; and wherein such stratospheric-visit vehicle comprises seating structured and arranged to serve the multiple humans environmental control structured and arranged to serve the multiple humans during a multiple hour stratospheric visit visual access structured and arranged to provide the multiple humans with viewing of Earth.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • such a stratospheric-visit system wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive- resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • a stratospheric-visit system further comprising a parachute pre-deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system.
  • parachute system comprises at least one parafoil.
  • parachute system comprises at least one drogue chute.
  • it provides such a
  • stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground- traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury- minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one
  • such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system
  • payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions.
  • payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit
  • environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human; wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch; wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply; and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control0 means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • it provides such a stratospheric-visit system wherein such distance separating means comprises anti- tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter- than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter- than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive- resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Also, it provides such a stratospheric-visit system wherein such distance separating means comprises anti- tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury- minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions.
  • such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. Additionally, it provides such a stratospheric-visit system further comprising a parachute pre-deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. Also, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. In addition, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute.
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one
  • the parachute system comprises at least one parafoil system. Further, it provides such a stratospheric-visit method wherein the parachute system comprises at least one drogue system.
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one
  • the step of distance- separating comprises the step of assisting prevention of tangling of the parachute system with the at least one payload. Even further, it provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting the parachute system to penetrate at least one burble confine during deployment of the parachute system.
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter- than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and assisting traversing of at least the at least one human across the ground; supporting, during launch, at least the at least one human, wherein the step of supporting comprises the steps of minimizing injury, during launch, to at least the at least one human and at least one accompanying human life support environment, conforming support to at least the at least one human and the at least one accompanying human life support environment, cushioning at least the at least one human and the at least one accompanying human life support environment, and permitting movement in both rotational and translational
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un- tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of tethering comprises the steps of coupling the lighter-than-air propulsion system to at least one lift-resisting ground restraint with at least one balloon-to-restraint coupler; coupling the at least one payload to the at least one balloon-to-restraint coupler; wherein the step of un- tethering comprises the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resist
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un- tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of controlling at least one human life support environment comprises the steps of coupling at least one equipment controller to a torso of the at least one human, providing a rigid adapter to closely abut a front of the torso of the at least one human, adjusting dimensions of the rigid adapter to fit the front of the torso of the at least one human prior to launch, rigidly attaching a mount, to attach an oxygen supply, to the rigid adapter, and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human.
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un- tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and providing a stratospheric-visit vehicle to transport multiple humans on the stratospheric visit; wherein the step of providing the stratospheric-visit vehicle comprises the steps of providing seating to serve the multiple humans, providing the at least one human life support environment to serve the multiple humans during a multiple hour stratospheric visit, and providing visual access to serve the multiple humans with viewing of Earth.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; .a travel control system structured and arranged to control, in the stratospheric visit,
  • parachute system comprises at least one parafoil.
  • parachute system comprises at least one drogue chute.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • this invention provides a stratospheric- visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than- air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit,
  • such injury- minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter- than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit
  • environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human; wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch; wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply; and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human.
  • this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit
  • such a stratospheric-visit system wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to transport multiple humans on the stratospheric visit; and wherein such stratospheric-visit vehicle comprises seating structured and arranged to serve the multiple humans environmental control structured and arranged to serve the multiple humans during a multiple hour stratospheric visit visual access structured and arranged to provide the multiple humans with viewing of Earth.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload.
  • such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system.
  • at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-suppl
  • a stratospheric-visit system further comprising: a payload ground- traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury- minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions.
  • such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. Further, it provides such a stratospheric-visit system further comprising a parachute deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. Even further, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. Moreover, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute.
  • such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved.
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un- tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and coupling the parachute system within the at least one payload; distance-separating the parachute system from the at least one payload; and controlling compressive resistance of the distance separation of the parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. And, it provides such a stratospheric-visit method wherein the step of distance- separating comprises the step of assisting prevention of tangling of the parachute system with
  • this invention provides a stratospheric-visit method, relating to a
  • stratospheric visit using lighter-than-air travel comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and untethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system;
  • the step of launching comprises the steps of lighter- than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one
  • FIG.1 shows a schematic diagram, illustrating a preferred flight of a preferred high- altitude
  • FIG.2 shows a schematic diagram, illustrating the preferred high-altitude operations apparatus, according to preferred systems of FIG.1.
  • FIG.3 shows a schematic diagram, illustrating the preferred high-altitude operations apparatus of FIG.1, in a descent and recovery configuration, according to a preferred
  • FIG.4A shows a high-level organizational overview of a stratospheric-visit system, including preferred function-enabling subsystems, according to preferred embodiments of the present invention.
  • FIG.4B shows a high-level organizational overview of a stratospheric-visit system, including preferred principal system functions, according to preferred embodiments of the present invention.
  • FIG.5 shows a schematic diagram, illustrating an alternate preferred flight of a single pilot flight vehicle, according to a preferred embodiment of the present invention.
  • FIGS.6A through FIG.6C show a series of diagrams, illustrating a preferred launch procedure for the single-pilot flight vehicle, according to preferred apparatus and methods of the present invention.
  • FIG.7 shows a front view of a pilot positioned within a payload ground-traversing system, according to a preferred embodiment of the present invention.
  • FIG.8 shows side view of the pilot positioned within the payload ground-traversing system of FIG.7.
  • FIG.9 shows a preferred drogue parachute of single-pilot embodiments of the
  • FIG.10 shows a diagrammatic rear view of a preferred stowed embodiment of the drogue parachute of FIG.9.
  • FIG.11 shows a diagrammatic rear view of another preferred stowed embodiment of the drogue parachute of FIG.9.
  • FIG.12 shows a preferred drogue parachute of the stratospheric-visit system, according to a preferred embodiment of the present invention.
  • FIG.13A through FIG.13C show a series of diagrams, illustrating a preferred launch 25procedure for the preferred high-altitude operations apparatus of FIG.1, according to preferred apparatus and methods of the present invention.
  • FIG.14A and FIG.14B show a preferred multi-passenger capsule according to a preferred embodiment of FIG.3.
  • stratospheric-visit system 100 For descriptive clarity, the present invention will be generally identified herein as stratospheric-visit system 100. The initial section of the present disclosure will describe preferred aspects of near-space operations utilizing Applicant's preferred systems and
  • FIG.1 is a schematic diagram, depicting a preferred representative flight of stratospheric-visit vehicle 102, according to a preferred embodiment of the present invention.
  • Stratospheric-visit vehicle 102 (at least embodying herein wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to go on the stratospheric visit) is preferably configured to transport multiple human passengers and crew members to the stratosphere, for example about 100,000 feet above the surface of the Earth, preferably using lighter-than-air propulsion.
  • Lighter-than-air propulsion functions are preferably implemented by at least one balloon 104 that preferably is filled with at least one lighter-than-air gas, preferably helium.
  • the crew and/or pilot preferably rise to a target altitude 138, for example, above about 125,000 feet above the earth, and preferably remain there for a pre-determined duration.
  • a target altitude 138 for example, above about 125,000 feet above the earth, and preferably remain there for a pre-determined duration.
  • One preferred mission profile includes about a 90-minute ascent and flight duration of just over about two-hours (it is noted that longer flights are within the capability of the present system for science missions and special tours).
  • Parawing 108 (at least embodying herein wherein the at least one payload launches with said lighter-than-air propulsion system and at least embodying herein wherein said parachute system comprises at least one parafoil) is preferably of a steerable design allowing a pilot to maneuver capsule 106 to a selected landing site.
  • balloon 104 is preferably deflated and brought to the ground to avoid it becoming an aviation hazard or falling into populated areas. This is preferably done with a ripping panel and line that are pulled when the payload is released.
  • balloon 104 is equipped with valve 142 at the top of the envelope that opens to release the helium gas.
  • capsule 106 Prior to launch, capsule 106 is preferably placed in a wheeled launch cradle 140 to enable towing of capsule 106 to the launch-site location.
  • the wheeled launch cradle 140 also preferably enables translational and rotational movement of capsule 106 during release of balloon 104 at launch.
  • launch cradle 140 separates from capsule 106 and remains on the ground after liftoff. Additional details of Applicant's preferred launch procedures are presented in FIG.13A through 13E.
  • FIG.2 shows a schematic diagram, illustrating a preferred stratospheric-visit vehicle 102, accordingto preferred systems of FIG.1.
  • FIG.3 shows a schematic diagram, illustrating the preferred stratospheric-visit vehicle 102 of FIG.1, in a descent and recovery configuration, according to a preferred embodiment of the present invention.
  • stratospheric-visit vehicle 102 comprises capsule 106, preferably a pressurized capsule, equipped with seating to serve multiple human passengers and crew, an Environmental Control and Life Support System (ECLSS) to maintain a habitable environment for the multiple humans during amultiple-hour stratospheric visit, and visual access (see, for example, FIGS. 14A and 14B) structured and arranged to provide the multiple humans with viewing of Earth.
  • stratospheric-visit vehicle 102 preferably implements travel-control functions, communication functions, recovery functions, balloon-separator functions, landing functions, etc.
  • Applicant's near-space operation systems 100 is the ability of the recovery system to return the capsule/payload from extremely high altitude (above 70,000 ft.) to the ground in a controlled fashion using parawing 108.
  • the need for a parafoil design capable of operating above a 50,000-foot altitude and capable of providing a precision return and gentle landing (rather than random dropped return and landing under a conventional round or semi- round parachute) was a driving factor for Applicant's development of the presently-disclosed recovery arrangements.
  • parawing 108 differs from conventional parafoil parachute technology in that Applicant's wing remains fixed in a "flight-ready" configuration at launch through flight and return to earth.
  • Parawing 108 preferably does not require moving air to maintain an aerodynamic shape; rather, the preferred wing design utilizes a stiffening system to maintain parawing 108 in the preferred flight-ready configuration during the assent phase of a mission. This precludes the need for the system to withstand dynamic deployment forces and removes the uncertainty of deployment actuation, unfurling, and proper deployment control.
  • Preferred stiffening systems utilize rigidizing members forming a geometry-controlling framework.
  • Stiffening members may comprise adapted equivalents of one or more ribs, spars, struts, braces, etc. Preferred stiffening members may also utilize tension members to transfer force loads within parawing 108. Alternately preferably, a stiffening frame composed of inflated cells is used.
  • Parawing 108 is preferably suspended from below the high-altitude balloon 104 and conformed to be fully deployed prior to release.
  • the preferred use of a parawing 108 already deployed and in a near-flight configuration results in less of a "drop" feeling by the payload or passengers when released from balloon 104 (or other carrier).
  • applicant's system allows for quick transition to controlled, directed flight. It is further noted that alternate preferred embodiments utilize an already descending balloon to further reduce the time from release to fully supported flight.
  • Parawing 108 preferably remains open, ready to glide capsule 106 to a safe landing at any time during the flight. This provides a significant safety feature if balloon 104 does not reach full altitude. In the unlikely event of a parawing failure, a drogue parachute and secondary parafoils are preferably deployed to provide backup recovery (see also FIG.12).
  • FIG.4A shows a high-level organizational overview of stratospheric-visit system 100, including preferred function-enabling subsystems, according to preferred embodiments of the present invention.
  • FIG.4B shows a high-level organizational overview of stratospheric-visit system 100, including preferred principal system functions, according to preferred embodiments of the present invention.
  • Stratospheric-visit System 100 is preferably enabled by implementation of a set of essential system functions, which are preferably implemented by the enabling subsystems outlined in system organization chart of FIG.4A.
  • Stratospheric-visit System Architecture of Stratospheric-visit System 100 preferably comprises Stratospheric-flight Elements 300 and Ground Elements 302, as shown.
  • Stratospheric- visit System 100 is further divided into Flight System 211 and Ground Support Equipment 212, each with four system modules.
  • Environmental-containment Module 201 preferably functions to enclose and contain a habitable environment around the human passengers, crew, and/or single pilot during a mission. Preferred implementations of the
  • Environmental-containment Module 201 are generally mission specific and preferably include pressure-containment capsules 106 (see FIG.2), pressure suits 202 (see FIG.6), along with various components of an Environmental Control and Life Support System (ECLSS).
  • ELSS Environmental Control and Life Support System
  • the Equipment Module 208 preferably provides a mounting location for components from a variety of subsystems.
  • the Flight Recovery module 203 preferably includes a parachute mounting structure or body harness, main parachute and reserve parachute.
  • parachute or “chute” may be used to identify system parafoils, parawings, and other devices used to slow the motion of the payload through an atmosphere by creating drag.
  • Flight Recovery module 203 includes everything needed to get the pilot away from balloon 104 and safely back to the ground.
  • the holding and release rigging preferably resides between the parachute container and the balloon(s). This connects the parachute harness (and the suit and pilot it is strapped to) to the balloon(s) and allows for the separation of the pilot from the balloon(s) at the appropriate time.
  • Flight Vehicle 205 preferably comprises the apparatus that lifts the payload to the target altitude and carries along with it supporting avionics 105. As such, Flight Vehicle 205 interfaces with many aspects of stratospheric-visit system 100. These interfaces preferably include atmospheric environment (physical/thermal), recovery systems (physical), ground infrastructure & facilities (physical/procedural), ground crew (physical/data/procedural/visual), pilot
  • Flight Vehicle 205 preferably interfaces the atmospheric environment in flight occurring in the Earth's atmosphere. Flight Vehicle 205 is in physical contact with the air, including buoyancy forces and wind. Flight Vehicle 205 preferably exchanges thermal energy through radiation exchange with the atmospheric environment, preferably through convection with surrounding air.
  • Flight Vehicle 205 works directly and in physical contact with Flight Vehicle 205 to prepare it for launch, during launch, and during recovery; this preferably includes working with balloon 104, avionics 105, rigging, attachments to pilot and the launch system equipment. Data preferably is sent to the ground crew via avionics 105. Further, mission control preferably can send commands to Flight Vehicle 205 through avionics 105.
  • Flight Vehicle 205 is physically attached to pilot release mechanism 241 (see FIG.6C), which is in turn attached to the support harness that is strapped to the Pressure Suit - Equipment Module Assembly. This attachment provides the mechanism to release the suited pilot.
  • Flight Vehicle 205 preferably includes balloon 104 and all of its associated components,luding dedicated avionics 105. The other four modules remain on the ground.
  • the balloonipment module of Flight Vehicle 205 preferably supports flight avionics 105, digital camera capture and transmission hardware, and mechanical and electrical interfaces to the Power, Avionics, Recovery, and Launch Balloon Subsystems.
  • Ground Support Equipment 212 preferably consists of all modules that remain on the ground during flight operations.
  • Preferred modules of Ground Support Equipment 212 include Mobile Pre-flight Unit 213 including a Ground Cart 214, Mission Control 216, Balloon Launch Equipment 218, and Ground Recovery 220.
  • Mission Control 216 preferably houses all of the equipment needed to track the mission and communicate with the crew and/or pilot.
  • Ground Recovery 212 preferably includes a helicopter to pick up the crew and/or pilot and all equipment needed to recover and refurbish the parachute (parafoil/parawing) and balloon 104.
  • the Balloon Launch Equipment 218 preferably comprises all items needed to unfurl and inflate balloon 104 prior to launch. From an organizational standpoint, the Stratospheric-flight
  • Elements 300 preferably comprise all of the system equipment that must be moved should a launch location change.
  • the Stratospheric-flight Elements 300 also consist of various subsystems.
  • the Environmental Control and Life Support Subsystem (ECLSS) preferably provides thermal control, oxygen, pressurization and other functions to keep the crew and/or pilot alive and comfortable.
  • the Launch Balloon Subsystem provides the preferred means for lifting the crew and/or pilot to a selected altitude.
  • Environmental-containment Module 201 preferably isolates the crew and/or pilot from the outside environment.
  • the Avionics subsystem preferably provides communication and tracking, receives and issues commands, and monitors sensors in other systems.
  • the Power subsystem preferably provides electrical power to all electrical components.
  • the Recovery subsystem preferably includes the parachute harness, parachute, and reserve parachute, as well as all equipment necessary to recover the pilot, parachute, and balloon after landing.
  • the Ground Elements preferably include all equipment and infrastructure to support the mission. This preferably includes cargo vans, helium trucks, storage facilities, helicopter pads, etc.
  • preferred system functions implemented within Stratospheric-visit System 100 preferably include payload functions 101, launch functions 103, environmental control functions 107, travel control functions 109, communication functions 111, and recovery functions 113, as shown.
  • the above-noted functions of the system preferably interact to enable delivery of payloads to the stratosphere and implement a safe return to Earth.
  • Payload functions 101 at least preferably provide for the transport of at least one human.
  • Preferred payload functions 101 further comprise actions relating to implementing the transport of system hardware that travels with the crewmember(s), including, for example, parachute apparatus supporting recovery functions 113 (i.e., parafoils/parawings).
  • This arrangement at least embodies herein a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system.
  • Launch functions 103 preferably include implementation of lighter-than-air propulsion functions 115, tethering functions 117, and un-tethering functions 119, as shown.
  • Lighter-than- air propulsion functions 115 are preferably enabled by balloon 104 (see FIG.2), which preferably functions to "lighter-than-air-propel" the payload from the ground to a target altitude (see also FIG.4 and FIG.5).
  • Tethering functions 117 preferably include initial tethering of balloon 104 (at least embodying herein a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload) to the ground, prior to launch (this arrangement at least embodying herein a tethering system structured and arranged to tether, initially to ground, said lighter-than-air propulsion system).
  • Un-tethering functions 119 preferably include the action of un-tethering balloon 104 from the ground to initiate vehicle launch (see also FIG.2 and FIG.3) (at least embodying herein an un-tethering system structured and arranged to un-tether, from the ground, said lighter-than-air propulsion system).
  • This arrangement at least embodies herein a launch system structured and arranged to launch the at least one payload.
  • Environmental control functions 107 preferably control, during the stratospheric visit, at least one human-life-support environment of the flight crew and/or pilot.
  • Travel control functions 109 preferably control, during the stratospheric visit, travel of the payload.
  • Communication functions 111 preferably include system operations associated with flight and ground communication within stratospheric-visit system 100.
  • Recovery functions 113 preferably enable recovery of the flight crew and/or pilot. Recovery functions preferably comprise balloon-separator functions 121, parachute-related functions 123, and landing functions 125, as shown.
  • Balloon-separator functions 121 preferably implement separation operations of at least the flight crew and/or pilot from balloon 104, or separation from similar lighter-than-air apparatus functioning to implement such lighter-than-air propulsion functions 115.
  • Parachute- related functions 123 preferably provide air-resistance-assisted deceleration of at least the flight crew and/or pilot after separation of the flight crew and/or pilot from balloon 104.
  • Preferred system embodiments enabling such parachute-related functions 123 preferably include parafoils 108.
  • parachute-related functions 123 are implemented by non-standard parawing of semi-rigid design.
  • preferred parachute functions 123, such payload descent stabilization are preferably implemented by at least one drogue parachute 130 (see FIG. 9 and FIG.12).
  • Landing functions 125 preferably implement landing of the flight crew and/or pilot.
  • Landing functions 125 preferably implement landing of the flight crew and/or pilot.
  • stratospheric-visit system 100 comprises operation-specific functions 127 for the implementation of mission-specific functions.
  • Mission-specific subsystems 127 of stratospheric-visit system 100 will be described in the following sections, as examples of preferred implementation of preferred system embodiments.
  • FIG.5 shows a schematic diagram, illustrating an alternate preferred flight of a single-pilot flight vehicle 205, according to a preferred embodiment of the present invention.
  • FIG.5 shows a diagrammatic depiction of a preferred example flight of a single-pilot flight vehicle 205.
  • pilot 204 preferably rises to target altitude 138 (generally above at least about 125,000 feet, more preferably at least about 135,000 feet above sea level) and maintains at target altitude 138 for a set duration.
  • Pilot 204 then initiates a separation procedure to separate from balloon 104 allowing pilot 204 to freefall back toward earth (at least embodying herein wherein wherein wherein wherein wherein wherein wherein wherein wherein wherein wherein said payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload).
  • a special drogue parachute 130 is preferably deployed at altitude 142 to stabilize and slow the descent velocity of pilot 204.
  • Pilot 204 preferably remains in controlled freefall until the main parachute 206 (preferably a parafoil) is deployed at altitude 144. The pilot will then float down to earth to complete the flight.
  • main parachute 206 is preferably deployed by pilot 204 at about 13,100 feet.
  • FIG 6A through FIG 6C shows a series of diagrams, illustrating a preferred launch procedure for single-pilot flight vehicle 205, according to preferred apparatus and methods of the present invention.
  • the single-pilot flight vehicle 205 is preferably moored to launch platform 234 prior to launch.
  • balloon 104 is preferably restrained to launch platform 234 using a tethering system 230 of Balloon Launch Equipment 218, as shown.
  • Tethering system 230 preferably comprises at least one lift-resisting ground restraint structured and arranged to resist upward lift imparted by balloon 104.
  • Tethering system 230 is preferably designed to tether balloon 104 to the ground, preferably using launch platform 234 as the mooring point.
  • Tethering system 230 preferably includes Balloon Equipment Module (BEM 232), which preferably functions to link balloon 104 to launch platform 234, and later to pilot 204 (at least embodying herein at least one balloon-to-restraint coupler structured and arranged to couple said lighter-than-air propulsion system to said at least one lift-resisting ground restraint).
  • BEM 232 Balloon Equipment Module
  • pilot 204 at least embodying herein at least one balloon-to-restraint coupler structured and arranged to couple said lighter-than-air propulsion system to said at least one lift-resisting ground restraint.
  • Avionics 105 are preferably housed on the balloon equipment module (BEM 232) at the base of the balloon assembly.
  • the BEM support structure is attached directly to the balloon base fitting and is the physical interface to the payload, the deployable avionics module, ballast, radar reflector, and a radiosonde.
  • Avionics 105 preferably includes: a SkySite computer equipped with two data acquisition boards (DAB), a transponder, two SPOT GPS units, a battery pack, a video camera, transmitter and antennae.
  • SkySite will be programmed to respond to ground signals to activate the ballast release, emergency payload release, and balloon destruct.
  • Balloon destruct is preferably accomplished by dropping the avionics module from the support structure.
  • the avionics module will be tied to a special gore on the balloon, which when dropped will tear out a hole in the gore.
  • SkySite will automatically generate a time-delayed signal to sever the line to the tear-away gore and a second time-delayed signal to release the parachute.
  • Pyrocutters preferably are used to activate mechanical releases.
  • Digital cameras preferably will also be used to capture images/video.
  • SkySite is a flight tested computer system designed and built by Space Data Corp. that was designed to provide all avionics functions of sounding balloon flights for data collection including lift gas vent and ballast control. This system is preferably being used with some modifications to perform telemetry and control functions for Flight Vehicle 205 and ECLSS (Environmental Control and Life Support System).
  • ECLSS Endormental Control and Life Support System
  • One SkySite system will be placed on flight vehicle 205, a second will be placed on the equipment module that supports the life support systems.
  • Each SkySite computer is integrated with a GPS receiver and transceiver. Along with GPS data, internal temperature, battery state and other information is relayed to the ground. The GPS data is presented on mapping software to show trajectory information including heading, ascent rate, etc.
  • SkySite's original configuration is in part designed to control a servomotor for lift gas venting.
  • the servomotor will for Space Dive be used to indirectly control the crown valve.
  • the servomotor will be used to toggle between one of three switches that can be used to either open or close the crown valve.
  • SkySite's original implementation of ballast dispersal is based on a servomotor-powered auger. It is alternately preferred that this servomotor will be replaced by a simple electronic relay that can power hot-wire cutters for ballast release.
  • Launch platform 234 preferably comprises a ballast member or ground mounting.
  • the process of filling and standing balloon 104 as described above requires that the base of balloon 104 be tethered to the ground.
  • the base of balloon 104 will be attached to the balloon equipment module (BEM 232) which is designed to be tethered to the ground via attachment points on each end of the BEM I-beam. Tethering directly to the ground was considered to have uncertainty in ground conditions, which would vary from site to site, and uncertainty in wind direction, which would require different ground anchor positions.
  • Launch platform 234 preferably comprises a heavy Launch Plate to serve as the ground anchor.
  • the launch plate preferably will support the lift and drag forces of the balloon under all but the most extreme conditions. To guard against the latter, the launch plate will preferably be in turn tethered to a set of secondary restraints.
  • the Launch Plate preferably comprises a weld assembly, comprising a 1-1/4" thick, 8' x 12' steel plate.
  • the Launch Plate preferably comprises a weight of approximately 49001bs.
  • the launch plate will require several anchor points.
  • the Launch Plate preferably comprises six tie- down rings welded at locations of three along each edge about one foot from the edges and three feet apart.
  • the launch tethers will attach to the steel Launch Plate via a pair of ratchet load binders.
  • the launch plate will be fitted with welded anchor points to which the ratchet load binders will attach.
  • Anchor points separated by 10 ft appear to provide sufficient space below the balloon-supported BEM 232.
  • the four corner rings will preferably be oriented at an angle of 31 degrees with respect to the preferred 8 foot-edges.
  • the welds of the middle two rings are to run parallel to the 8 ft edges. Aside from handling, the corner rings preferably are used to anchor the plate for additional anchoring reinforcement.
  • the middle two rings are preferably designated for balloon tethering.
  • balloon 104 is filled with lighter-than-air gas enabling the lighter-than-air propulsion functions 115 of the single-pilot flight vehicle 205.
  • spool vehicle 236 gradually approaches launch platform 234 and releases balloon 104, which preferably lifts BEM 232 into flight position, as shown in FIG.6B.
  • FIG.6B shows the single-pilot flight vehicle 205 in a preferred pre-launch configuration.
  • pilot 204 has been preconditioned for flight at Ground Cart 214.
  • a payload ground- traversing system 238 is used to transport pilot 204 across the ground to launch platform 234 after decoupling from Ground Cart 214.
  • Balloon 104 preferably comprises an envelope, preferably comprising polyethylene, preferably balloon grade linear low density polyethylene film, preferably ANTRIX (developed by Tada Institute of Fundamental Research (TIFR)). Preferred specifications for 70,000 foot, 90,000 foot, and 120,000 foot balloons are shown in Table 1, Table 2, and Table 3, respectively.
  • ANTRIX developed by Tada Institute of Fundamental Research (TIFR)
  • pilot 204 is preferably wheeled to a position directly underneath BEM 232 and attached to the BEM 232 using pilot release mechanism 241, as shown (at least embodying herein at least one payload coupler structured and arranged to couple the at least one payload to such at least one balloon-to-restraint coupler).
  • pilot release mechanism 241 at least embodying herein at least one payload coupler structured and arranged to couple the at least one payload to such at least one balloon-to-restraint coupler.
  • one or more electrical connection(s) are preferably made between the avionics module (AM) and the primary (remote) payload release pyrocutter.
  • un-tethering functions 119 of launch system are implemented by releasing each tether securing BEM 232 to the ground, thus allowing single-pilot flight vehicle 205 to lift pilot 204 out of payload ground-traversing system 238 and upward toward target altitude 138.
  • Each tether will be secured to BEM 232 with an interfacing 3-ring release mechanism.
  • the trigger line for each 3-ring release mechanism will be coupled together such that a single action (pull) will simultaneously disengage both 3-ring release mechanisms. This concept has been successfully tested by applicant.
  • said un-tethering system comprises at least one restraint-decoupling system structured and arranged to decouple said at least one balloon-to-restraint coupler from said at least one lift-resisting ground restraint, wherein the at least one payload, after decoupling said at least one balloon-to-restraint coupler from said at least one lift- resisting ground restraint, remains coupled to said lighter-than-air propulsion system by said at least one balloon-to-restraint coupler).
  • balloon 104 Upon release, under ideal conditions, balloon 104 pulls pilot 204 out of the launch sedan and both rise straight up. With a side wind, balloon 104 and payload will, after launch, have a tendency to rotate about the system's center of gravity until the crown of the balloon and the payload form a vector approximately parallel with that formed by gravity and drag. Payload ground-traversing system 238 is preferably designed to accommodate such translational and rotational motions.
  • FIG.7 shows a front view of pilot 204 positioned within payload ground-traversing system 238, according to a preferred embodiment of the present invention.
  • FIG.8 shows side view of pilot 204 positioned within payload ground-traversing system 238.
  • Payload ground- traversing system 238 preferably comprises payload support system 240 configured to support, during launch, the human pilot 204.
  • payload support system 240 comprises an injury- minimizing system 243 structured and arranged to minimize injury, during launch, to pilot 204 and their accompanying environmental control system equipment.
  • such injury- minimizing system 243 comprises at least one configuration that shape-conforms to pilot 204 and the accompanying ECLSS/Avionics hardware.
  • such injury-minimizing system 243 comprises at least one cushioning configured to cushion at least the pilot 204 and the accompanying ECLSS/Avionics hardware.
  • payload support system 240 comprises a motion direction system structured and
  • pilot 204 to move in both rotational and translational directions.
  • Such preferred motion direction system is enabled by wheels 242. All wheels are preferably of swivel design to maximize the ground maneuverability of pilot 204 during liftoff.
  • the preferred single-pilot system architecture has pilot 204 "directly" attached to the balloon; that is, unlike the preferred embodiment of FIG.1, pilot 204 is preferably protected inside of pressure suit 202 and will carry all needed equipment in an Equipment Module 208 that is preferably located adjacent the chest of pilot 204.
  • Equipment Module 208 preferably contains oxygen, communication equipment, electrical power and a heater and pump that will circulate warm water around the body of pilot 204.
  • the Stratospheric-flight Elements preferably comprise the collection of all modules that leave the ground: the Environmental-containment Module 201 (in this case pressure suit 202), Equipment Module 208, Flight Recovery Module 203, and Flight Vehicle 205.
  • Flight Vehicle 205 preferably comprises balloon 104 and all other components that adapt balloon 104 to manned flight. This preferably includes rigging and valving as well as avionics that announce the location of the balloon per Federal Aviation Administration (FAA)
  • FAA Federal Aviation Administration
  • Flight Vehicle avionics 105 are preferably housed on the balloon equipment module (BEM 232) at the base of the balloon assembly.
  • FIG.6C shows BEM 232 secured to the base fitting of balloon 104.
  • Environmental-containment Module 201 preferably consists of pressure suit 202 (at least embodying herein an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human), but also includes all ECLSS (Environmental Control and Life Support System) and avionics equipment inside of the suit.
  • ECLSS components include a neck dam, regulators, relief valves and water supply, etc.
  • Preferred avionics equipment include the microphone and headset that allow pilot 204 to communicate with the ground.
  • Equipment Module 208 consists of a frame that preferably serves as a mounting location for components of various subsystems.
  • Preferred example subsystems include the ECLSS oxygen tanks and components of the thermal fluid loop such as the pump, cold plate, heater and oxygen heat exchanger.
  • the avionics boxes preferably mount to the frame or the ECLSS cold plate.
  • the batteries are also preferably attached to the frame.
  • the Flight Recovery Module 203 preferably consists of the parachute harness, parachute components and the separation mechanism.
  • the harness is preferably placed on pressure suit 202.
  • Equipment Module 208 is attached to the front of the harness similar to a tandem skydiver.
  • the harness is preferably similar to a tandem sky-dive harness.
  • the harness is also the component that preferably functions to directly connected pilot 204 to Flight Vehicle 205.
  • Equipment Module 208 is rigidly mounted to pressure suit 202.
  • Ground Support Equipment 212 preferably consists of all modules that remain on the ground during flight operations.
  • Preferred modules of Ground Support Equipment 212 include Ground Cart 214, Mission Control 216, Balloon Launch Equipment 218, and Ground Recovery 220.
  • Ground Cart 214 provides oxygen, cooling, electrical power and
  • Pilot is preferably disconnected from Ground Cart 214 approximately 15 minutes before launch.
  • Mission Control 216 is where all data from the Flight System will be received, processed and interpreted. Preferably, multiple people monitor computers to evaluate the data from Flight System 222. This is also where direct verbal communication with the pilot will preferably take place.
  • Balloon Launch Equipment 218 preferably comprises apparatus needed to unfurl balloon 104, inflate it, keep it moored to the ground, and initiate release.
  • Ground Recovery 220 preferably includes all items needed to find the pilot 204 after landing, take pilot 204 to a medical center and to recover and refurbish all parachute and balloon components.
  • Equipment module 208 preferably includes the physical container that resides on the chest of pilot 204, the structure that attaches that container to pilot 204 and any tubes or wires extending to interfaces on other systems.
  • Equipment Module 208 preferably serves as the structural support for many of the components of the various subsystems of Flight System 211. These subsystems preferably include Avionics, Power and ECLSS.
  • the equipment is rather heavy, requiring significant structure. Preferred equipment is bulky and irregularly shaped;
  • a neoprene cover 304 is preferably placed over the equipment held by Equipment Module 208 to improve the aerodynamic characteristics of the assembly. Additional “spacers” are preferably provided, as required, to further smooth the shape underneath the cover to prevent aerodynamic moment forces.
  • Equipment Module 208 is preferably attached to the Recovery System harness via multiple hooks and straps. The intention is for the Equipment Module to be supported by the harness during ascent and loiter rather than being suspended from the pilot (in other words, the pilot is not part of the load path).
  • a primary component of Equipment Module 208 is the frame.
  • the frame is preferably constructed from 8020 extrusions which are cut to length and connected with standard fittings. Hooks are preferably attached to provide a mounting location to the harness of the Flight
  • the frame is alternately preferably a hard-mounted design using structural pick-up points on the torso region of pressure suit 202, as shown (at least embodying herein wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple said at least one equipment module to a torso of the at least one human). It is preferred that frame (at least embodying herein a torso-coupling system) fit closely about a front of the torso of pilot 204. Because pressure suit 202 is composed of soft goods, the manufacturing process does not produce a known location of structural pick-up points, with relation to individual suit components when the suit is inflated.
  • An adaptor plate was preferably implemented to allow for such large size adjustments in the main frame system (at least embodying herein wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch).
  • the adaptor plate also allows for adjustment in the roll and pitch translation modes (with the pilot's chest being "forward").
  • the Pressure Suit Module preferably includes pressure suit 202, the ECLSS, and the avionics subsystem.
  • the ECLSS of the pressure suit module preferably implements environmental control functions 107 to maintain the health of pilot 204 by supplying heating and cooling, providing oxygen and removing carbon dioxide, and maintaining a pressurized environment.
  • An avionics system preferably monitors sensors and preferably provides uplink and downlink communications.
  • Equipment Module 208 preferably houses a majority of the ELCSS components & oxygen storage, avionics, and batteries for the mission.
  • the ECLSS is preferably built on the heritage of the S1034 Pilot's Protective Assembly (PPA) and NASA's 51035 Advanced Crew Escape Suit (ACES). These ECLSS oxygen flow and pressure systems have similar features and in most cases similar components that are used in these heritage systems.
  • the S1034 PPA oxygen system is described in DN OOPSTP PPA 02 System.
  • the NASA ACES is described in some detail in USA009026, Crew Escape System 21002.
  • the ECLSS oxygen flow system preferably uses some of the same components (demand regulator and exhalation valves) as the S1034 PPA and S1035 ACES except that the ACES use a single demand regulator rather than a dual regulator.
  • the ECLSS of stratospheric-visit system 100 is more like the ACES system in that it preferably incorporates a neck dam and a larger helmet volume rather than the face seal and smaller oral/nasal cavity of the S1034 PPA.
  • the ECLSS of stratospheric-visit system 100 also includes a respiration mask to minimize the risk of fogging and encourage CO2 washout.
  • the ECLSS pressure system preferably uses the same dual suit controller as used in both the PPA and ACES systems, and a pressure relief valve similar to the ACES system.
  • Ground Cart 214 preferably provides oxygen, cooling, electrical power and
  • Ground Cart 214 provides oxygen, cooling, electrical power and communications for the pilot while the pre-breathe process is taking place.
  • the pilot is disconnected from the ground cart approximately 15 minutes before launch.
  • pilot 204 Prior to launch, pilot 204 must carry out a pre-breathe process. Because the absolute pressure inside of pressure suit 202 will be around 3.5 psi when at maximum mission altitude, any nitrogen in the pilot's blood stream will come out of solution and create gas bubbles. These bubbles can cause pain and even death. To prevent this, the pilot must breathe pure oxygen until the nitrogen is purged from his body. This means pilot 204 must don the pressure suit module to isolate himself from the ambient ground atmosphere. As a result, pilot 204 requires a supply of oxygen and requires heating and/or cooling via the liquid thermal garment and will need to communicate with the ground crew.
  • Ground Cart 214 is preferably designed to provide oxygen, cooling, power and communications without using the consumables intended for flight and adding complexity to Flight System 211.
  • the preferred ECLSS is designed to allow connections into the oxygen lines.
  • the oxygen is preferably supplied at 80 psi so that the 65 psi regulators of Flight System 211 do not open and expel oxygen from the flight tanks.
  • quick disconnect connections are provided in the water loop such that Ground Cart 214 can preferably provide water for cooling and/or warming.
  • Electrical power is preferably supplied to run the avionics so that
  • Mission Control preferably encompasses the hardware, software, and personnel involved in directing the execution of all flight procedures from flight planning through recovery.
  • Preferred Mission Control personnel include a flight director, mission meteorologist, medical specialist, ECLSS specialist, recovery system specialist, avionics specialist and flight vehicle specialist.
  • the flight director is preferably
  • Preferred procedures to be executed include, but are not limited to, weather forecasting, medical oversight, flight, ECLSS, recovery and launch hardware check and preparation, launch operations, system monitoring, and ground and air-based flight recovery.
  • FIG.9 shows a preferred drogue parachute 130 of the single-pilot embodiments of stratospheric-visit system 100.
  • FIG.10 shows a diagrammatic rear view of a preferred stowed embodiment of drogue parachute 130 of FIG.9.
  • FIG.11 shows a diagrammatic rear view of another preferred stowed embodiment of drogue parachute 130 of FIG.9.
  • Flight Recovery Module 203 preferably includes deceleration components, preferably including drogue parachute 130 that preferably functions to stabilize pilot 204 during descent and pulls main parachute 206 from parachute container 210 (see FIG.9, FIG.10, and FIG.11). Should there be a problem with main parachute 206, a reserve parachute is automatically deployed.
  • ground control preferably can activate any of the parachute systems should the pilot be unable.
  • the parachute activation system preferably comprises a line restraining a spring that upon release pulls the parachute release cord.
  • the system is preferably activated (by ground command) by a hotwire cutting the spring retaining line.
  • the pull cords and restraint cords are all held by passing through holes in the top plate and then tying a knot to keep the cords from passing back through.
  • the restrained spring load is ⁇ 13 lbf and the actuation stroke is ⁇ 3.0 inches, and it weighs about 0.3 lbs.
  • drogue parachute 130 is preferably deployed to both stabilize and slow the descent velocity of pilot 204.
  • Main parachute 206 is preferably deployed using the drogue to pull main parachute 206 from the rear-mounted parachute container 210.
  • pilot 204 After release from balloon 104, pilot 204 preferably remains in a controlled freefall using drogue parachute 130 to both stabilize the pilot and limit the descent velocity.
  • Applicant considered the dynamics of the freefall at the transonic velocities experienced by pilot 204 during the descent. Applicant determined that implementation of a stabilization parachute is preferred during the descent; however, the preferred point of deployment was selected only after significant research and experimental testing.
  • Drogue parachute 130 of parachute system 123 preferably comprises means for coupling drogue parachute 130 with the payload (in this case, pilot 204). In the present preferred embodiment such coupling is performed by parachute bridle line 226.
  • a key feature of parachute bridle line 226 is the preferred incorporation of at least one drogue stiffener 224 used to stiffen portions of parachute bridle line 226.
  • Drogue stiffener 224 preferably functions to provide a means for distance-separating drogue parachute 130 from pilot 204 (at least embodying herein wherein such coupling means comprises distance separating means for distance-separating of parachute system from the payload) and further provides a means for controlling compressive resistance of the stiffened parachute bridle line 226 to assist implementation of physical-distance separation of drogue parachute 130 from pilot 204 (at least embodying herein compressive- resistance control means for controlling compressive resistance of distance separating means to assist the distance separation of such parachute system from the payload).
  • This preferred arrangement prevents entanglement of drogue parachute 130 and preferably functions to push drogue parachute 130 beyond the wake (burble) at transonic velocities.
  • drogue stiffener 224 functions to restrict the bridle from wrapping around a falling vehicle structure, payload structure, parachutist's body, etc.
  • Applicant's preferred drogue parachute design is preferably configured to move in a relative manner with the vehicle structure/payload structure/parachutist as it spins or tumbles. This feature preferably prevents the drogue parachute from wrapping and tangling around the vehicle structure/payload
  • said distance separating means comprises anti-tangling means for assisting prevention of tangling of said coupling means with the at least one payload.
  • Preferred drogue stiffeners 224 preferably comprise a carbon fiber slit cylinder having a length of about 10 feet, or alternately preferably, three carbon-fiber rods, having a diameter of about 0.125 inch, such rods located inside a Kevlar sleeve.
  • the stiffening member is long enough so that the drogue parachute will not touch pilot 204 when the parachute folds back.
  • Three preferred examples of applicant's supported drogue are as follows:
  • Preferred rods are preferably tapered for a continuous moment resistance proportional to the length of the moment arm.
  • the coiled rod preferably comprises a diameter sufficiently small to fit inside of parachute container 210 (i.e., 12-inch diameter or smaller is preferred for a container supporting a single human parachutist) can be placed inside the pack under tension; and, when parachute container 210 is opened, the coil will spring straight keeping the parachute bag and drogue parachute a safe distance from the falling parachutist, even if they are spinning or tumbling.
  • a preferred material for this type of rod is carbon fiber. Alternately preferably, spring steel or a variety of composites is also sufficient.
  • a telescoping style ejection system (see FIG.10) where the rod is a short set of nestled rods which telescope out when pulled, this could nestle down to a size where it could fit on or in parachute container 210.
  • Applicant's drogue stiffeners 224 are generally useful in broader parachuting activities where the recovery profile includes periods of zero-gravity freefall. This occurs, for example, during high-altitude return-to-earth operations or any high atmospheric free-fall procedure.
  • FIG.12 shows a preferred drogue parachute 130 of a backup recovery system of the multi- passenger capsule 106 of FIG.1.
  • a drogue parachute 130 and secondary parafoils are preferably deployed to provide backup recovery.
  • drogue parachute 130 utilizes drogue stiffener 224 to restrict the bridle from wrapping around tumbling vehicle structures and preferably functions to assist drogue parachute 130 penetrate outward beyond the wake (burble) of the falling capsule 106 (at least embodying herein wherein said distance separating means comprises burble-confine penetrator means for assisting said parachute system to penetrate at least one burble confine during deployment of said parachute system).
  • FIG.13A through FIG.13C shows a series of diagrams, illustrating a preferred launch procedure for stratospheric-visit vehicle 102 of FIG.1, according to preferred apparatus and methods of the present invention.
  • balloon 104 is preferably restrained by spool vehicle 236 of Balloon Launch Equipment 218, as shown, as shown.
  • Balloon 104 is preferably coupled to parawing 108, which is preferably pre-deployed and is resting near the ground, as shown.
  • Parawing108 is preferably coupled to capsule 106, which is preferably resting in wheeled launch cradle 140, as shown.
  • a second hold down 320 is preferably located between parawing 108 and capsule 106, as shown.
  • the second hold down 320 may preferably comprise a fixed ballast member or may alternately preferably be designed to be movable relative to the ground during launch procedures.
  • balloon 104 is filled with lighter-than-air gas enabling the lighter-than-air propulsion functions 115 of stratospheric-visit vehicle 102.
  • spool vehicle 236 gradually approaches parawing 108, as shown in FIG.13B and releases balloon 104, which preferably lifts parawing 108 into flight position, as shown in FIG.13C.
  • stratospheric-visit vehicle 102 and second hold down 320 move together as shown in FIG.13C.
  • second hold down 320 is released , as shown in FIG.13D, and stratospheric-visit vehicle 102 is preferably lifted away from wheeled launch cradle 140, as shown in FIG.13E.
  • a stratospheric-visit method relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air- propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter- than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human;
  • stratospheric-visit system 100 preferably provides such a method wherein the parachute system comprises at least one drogue system.
  • this invention provides a stratospheric-visit method, relating to a
  • stratospheric visit using lighter-than-air travel comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at
  • stratospheric-visit system 100 preferably provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting the parachute system to penetrate at least one burble confine during deployment of the parachute system.
  • this invention provides a stratospheric- visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter- than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human
  • stratospheric-visit system 100 preferably provides such a stratospheric-visit method further comprising the step of terminating the step of supporting, during launch of the at least one payload.
  • this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the
  • stratospheric-visit system 100 preferably provides a stratospheric-visit method, relating to a stratospheric visit using lighter- than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter- than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of controlling at least one human life support environment comprises the steps of coupling at least one equipment controller to a torso of the at least one human, providing a rigid adapter to closely abut a front of the torso of the at least one human, adjusting dimensions of the rigid adapter to fit the front of the torso of the at least one human prior to launch, rigidly attaching a mount, to attach an oxygen supply, to the rigid adapter, and wherein the oxygen supply is positionable
  • stratospheric-visit system 100 preferably provides a stratospheric-visit method, relating to a stratospheric visit using lighter- than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter- than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human;
  • the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and providing a stratospheric-visit vehicle to transport multiple humans on the stratospheric visit; wherein the step of providing the stratospheric-visit vehicle comprises the steps of providing seating to serve the multiple humans, providing the at least one human life support environment to serve the multiple humans during a multiple hour stratospheric visit, and providing visual access to serve the multiple humans with viewing of Earth.
  • FIG.14A and FIG.14B show a preferred multi-passenger capsule according to a preferred embodiment of FIG.3.
  • stratospheric- visit vehicle 102 preferably comprises capsule 106.
  • Capsule 106 preferably permits at least one pilot to take additional passengers in a stratospheric visit.
  • Capsule 106 preferably comprises a habitable environment for the multiple humans during a multiple-hour stratospheric visit.
  • Capsule 106 preferably further comprises at least one view-port 410 to permit viewing the external environment while on stratospheric visit.
  • Capsule 106 preferably further comprises at least one landing system, preferably comprising landing gear 420.
  • Capsule 106 preferably further comprises avionics and recovery subsystems similar to single-pilot mission.
  • Capsule 106 preferably further comprises rigging couple points 430, permitting coupling to said lighter-than-air propulsion system, preferably balloon 104, and parawing 108.

Abstract

L'invention concerne un système permettant d'effectuer sans danger des opérations avec pilote et sans pilote à très hautes altitudes (supérieures à 70 000 pieds). Ce système utilise un système de lancement par ballon et un dispositif de récupération par parachute et/ou paraplane.
PCT/US2015/035668 2015-06-12 2015-06-12 Systèmes pour opérations dans l'espace proche WO2016200407A1 (fr)

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PCT/US2015/035668 WO2016200407A1 (fr) 2015-06-12 2015-06-12 Systèmes pour opérations dans l'espace proche

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FR3080095A1 (fr) * 2018-04-17 2019-10-18 Arianegroup Sas Systeme pour le lancement d'une aile de parapente depuis la stratosphere
CN114537635A (zh) * 2022-02-18 2022-05-27 中国科学院空天信息创新研究院 一种临近空间球载载荷服务舱及系统

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US6360988B1 (en) * 2000-04-04 2002-03-26 James I. Monroe Personnel lift device and amusement use thereof
US6626400B1 (en) * 1999-10-18 2003-09-30 William R. Booth Parachute deployment system and method
US20040089763A1 (en) * 2002-11-12 2004-05-13 Redmond Scott D. Personal flight vehicle and system
US20050288114A1 (en) * 2002-05-07 2005-12-29 Meadows Joseph S System and apparatus for propelling and carrying a user within a confined interior
US20120312919A1 (en) * 2011-06-13 2012-12-13 Stephen Heppe Lifting gas replenishment in a tethered airship system

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US6626400B1 (en) * 1999-10-18 2003-09-30 William R. Booth Parachute deployment system and method
US6360988B1 (en) * 2000-04-04 2002-03-26 James I. Monroe Personnel lift device and amusement use thereof
US20050288114A1 (en) * 2002-05-07 2005-12-29 Meadows Joseph S System and apparatus for propelling and carrying a user within a confined interior
US20040089763A1 (en) * 2002-11-12 2004-05-13 Redmond Scott D. Personal flight vehicle and system
US20120312919A1 (en) * 2011-06-13 2012-12-13 Stephen Heppe Lifting gas replenishment in a tethered airship system

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3080095A1 (fr) * 2018-04-17 2019-10-18 Arianegroup Sas Systeme pour le lancement d'une aile de parapente depuis la stratosphere
WO2019202257A2 (fr) 2018-04-17 2019-10-24 Arianegroup Sas Système pour le lancement d'une aile de parapente depuis la stratosphère
WO2019202257A3 (fr) * 2018-04-17 2020-01-30 Arianegroup Sas Système pour le lancement d'une aile de parapente depuis la stratosphère
CN114537635A (zh) * 2022-02-18 2022-05-27 中国科学院空天信息创新研究院 一种临近空间球载载荷服务舱及系统

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