公开(公告)号：US12116128B2

公开(公告)日：2024-10-15

申请号：US18504553

申请日：2023-11-08

申请人： KNIGHTWERX INC.

发明人： Daniel Baumgartner

IPC分类号： B64C39/00 ,  B64C11/46 ,  B64C25/32 ,  B64C29/02 ,  B64C39/02 ,  B64D9/00 ,  B64D17/80 ,  F41G3/06 ,  F41G3/08 ,  F41G3/16 ,  G02B23/10 ,  G05D1/00 ,  G09G3/00 ,  B64U10/25 ,  B64U50/13

CPC分类号： B64C39/024 ,  B64C11/46 ,  B64C25/32 ,  B64C29/02 ,  B64D9/00 ,  B64D17/80 ,  F41G3/06 ,  F41G3/08 ,  F41G3/165 ,  G02B23/10 ,  G05D1/106 ,  G09G3/001 ,  B64U10/25 ,  B64U50/13 ,  B64U2201/00 ,  G09G2320/0686

摘要： A tactical system includes a first HUD system mountable to a first weapon and a second HUD system mountable to a second weapon. The first HUD system includes sensors providing position and orientation data of the first weapon, a processor to calculate a target position based on the position and orientation data, and a communications module to communicate the target position over a network. The second HUD system includes sensors providing position and orientation data of the second weapon, a communications module configured to import the target position from the network, and a processor to: calculate a position and an orientation of the second weapon based on the position and orientation data of the second weapon; calculate a target vector based on the target position and the position of the second weapon; and generate a target finder visualization based on the target vector and the orientation of the second weapon.

公开(公告)号：US20240317410A1

公开(公告)日：2024-09-26

申请号：US18653441

申请日：2024-05-02

申请人： Harold Wright

发明人： Harold Wright

IPC分类号： B64D25/12 ,  B64C1/14 ,  B64D17/80

CPC分类号： B64D25/12 ,  B64C1/1476 ,  B64D17/80

摘要： A “G” load suppressing aircraft incorporating a fuselage having a nose end; a cavity, extending downwardly into the fuselage, the cavity opening upwardly at the fuselage's nose end; a cockpit capsule fitted for receipt within the cavity; explosive bolts for releasably attaching the cockpit capsule to the fuselage, the explosive bolts holding the cockpit capsule within the cavity; a liquid supply line for filling the cockpit capsule with a transparent liquid, the liquid supply line being connected operatively to the cockpit capsule; and rocket engines for ejecting the cockpit capsule from the cavity, the rocket engines being connected operatively to the cockpit.

公开(公告)号：US20240246701A1

公开(公告)日：2024-07-25

申请号：US18207649

申请日：2023-06-08

申请人： Zhishang Zhou

发明人： Zhishang Zhou

IPC分类号： B64G1/62 ,  B64D3/00 ,  B64D17/80 ,  B64G1/58 ,  B64U10/20 ,  B64U10/60 ,  B64U20/70 ,  B64U101/00 ,  B64U101/45

CPC分类号： B64G1/623 ,  B64D3/00 ,  B64D17/80 ,  B64G1/58 ,  B64G1/625 ,  B64U10/20 ,  B64U10/60 ,  B64U20/70 ,  B64U2101/00 ,  B64U2101/45

摘要： Systems and methods using VTOL (vertical take-off and landing) aircrafts including drones and helicopters for soft capture, preserving, and landing of a returning spacecraft from space are disclosed. The spacecraft is decelerated by parachutes. One or multiple VTOL drones transport a water impermeable pocket meeting and capturing the descending spacecraft in the air. The spacecraft is thus preserved inside the pocket and keeps descending and then softly lands in a body of water. In another embodiment, a recovery helicopter, one type of VTOL aircraft with heavy payload lifting capacity, is used to directly catch the returning spacecraft. One or multiple VTOL drones are coupled to the bottom end of a recovery cable hung from the helicopter. These drones bring a clutch quickly and precisely catching the descending spacecraft directly without interrupting the parachutes. The spacecraft is thus caught and preserved by the helicopter with lifting function of the parachutes maintained.

公开(公告)号：US11947352B2

公开(公告)日：2024-04-02

申请号：US17558170

申请日：2021-12-21

申请人： Kitty Hawk Corporation

发明人： Cameron Robertson ,  Joseph Roop ,  Todd Reichert ,  Damon Vander Lind

IPC分类号： G05D1/00 ,  B64D17/54 ,  B64D17/62 ,  B64D17/72 ,  B64D17/80 ,  B64D45/00 ,  B64U70/83 ,  G05D1/04 ,  G05D1/08

CPC分类号： G05D1/0061 ,  B64D17/54 ,  B64D17/62 ,  B64D17/80 ,  B64D45/00 ,  G05D1/042 ,  G05D1/0808 ,  B64D17/725 ,  B64D2045/0085 ,  B64U70/83

摘要： Sensor data that includes or more of the following: (1) aircraft state information associated with an aircraft or (2) parachute canopy state information associated with a parachute canopy is received. The parachute canopy is coupled to the aircraft at a point aft of a center of mass of the aircraft. It is determined, based at least in part on the sensor data, whether to generate a control signal associated with maneuvering the aircraft into a nose-up position. A recovery action is performed, including by deploying the parachute canopy; wherein a load on the parachute canopy is reduced in the event the aircraft is in the nose-up position compared to the aircraft being in a nose-down position.

公开(公告)号：US20240076038A1

公开(公告)日：2024-03-07

申请号：US18504553

申请日：2023-11-08

申请人： KNIGHTWERX INC.

发明人： Daniel Baumgartner

IPC分类号： B64C39/02 ,  B64C11/46 ,  B64C25/32 ,  B64C29/02 ,  B64D9/00 ,  B64D17/80 ,  F41G3/06 ,  F41G3/08 ,  F41G3/16 ,  G02B23/10 ,  G05D1/10 ,  G09G3/00

CPC分类号： B64C39/024 ,  B64C11/46 ,  B64C25/32 ,  B64C29/02 ,  B64D9/00 ,  B64D17/80 ,  F41G3/06 ,  F41G3/08 ,  F41G3/165 ,  G02B23/10 ,  G05D1/106 ,  G09G3/001 ,  B64U10/25

摘要： Systems and methods for a weapon mountable tactical heads-up display (HUD) are provided. The HUD may include a 9 degrees of freedom (9DOF) sensor, a target library, and a target finder visualization. The target library may store respective ballistic information for each target of a plurality of targets. The respective ballistic information may include a target vector for each target of the plurality of targets. The target vector may be calculated based on data received from the 9DOF sensor. The target finder visualization may allow a shooter to locate a selected target of the plurality of targets. The target finder visualization may be based on the target vector.

公开(公告)号：US11919650B2

公开(公告)日：2024-03-05

申请号：US17880488

申请日：2022-08-03

申请人： Kitty Hawk Corporation

发明人： Cameron Robertson ,  Joseph Roop ,  Todd Reichert ,  Damon Vander Lind

IPC分类号： B64D17/80 ,  B64D17/62 ,  B64D17/74 ,  B64D45/00 ,  B64U70/83

CPC分类号： B64D17/80 ,  B64D17/62 ,  B64D17/74 ,  B64D45/00 ,  B64U70/83

摘要： A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.

公开(公告)号：US20230406488A1

公开(公告)日：2023-12-21

申请号：US18461483

申请日：2023-09-05

申请人： William Swindt Butterfield

发明人： William Swindt Butterfield

IPC分类号： B64C27/08 ,  B64D17/80 ,  B64C27/52 ,  B64D27/24

CPC分类号： B64C27/08 ,  B64D17/80 ,  B64C27/52 ,  B64D27/24

摘要： An electrically-powered VTOL aircraft has a fuselage with a cabin flexibly connected to a powerplane assembly that includes a plurality of electrically-powered rotors and booms. The powerplane assembly can pitch and roll relative to and independently of the cabin, thereby generating efficient fore, aft and lateral thrust while the cabin attitude remains unchanged. This provides a stable passenger experience and enhanced performance and controllability with reduced cost and complexity. In some embodiments, the fuselage is vertically elongated and the powerplane assembly mounts above the fuselage such that a person may walk beneath the rotors completely erect. A VTOL docking station is also disclosed that is configured to allow the aircraft to land without the use of landing gear. The docking station also includes electrical components configured to automatically provide charging to the aircraft when the aircraft is docked with the docking station.

公开(公告)号：US11753173B2

公开(公告)日：2023-09-12

申请号：US17429056

申请日：2019-12-25

申请人： MINEBEA MITSUMI Inc.

发明人： Yuzuru Sakamoto ,  Shoji Shimohisa ,  Yoshihiro Mochida

IPC分类号： B64D17/80 ,  B64C39/02 ,  B64D17/72 ,  B64U10/13 ,  B64U30/20 ,  B64U70/83

CPC分类号： B64D17/80 ,  B64C39/024 ,  B64D17/72 ,  B64U10/13 ,  B64U30/20 ,  B64U70/83 ,  B64U2201/00

摘要： To provide a parachute device capable of quickly and reliably opening a parachute even when an airflow effect during flying or falling of a flight device cannot be immediately obtained. A parachute device (4) includes a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, and an ejection section (41) configured to hold the flying body and to eject the flying body held, and the flying body includes a flying body main body section (44) engaged with the ejection section, and a gas generating device (45) disposed in an internal space (440) defined by the ejection section and the flying body main body section, and configured to generate gas.

公开(公告)号：US11745874B2

公开(公告)日：2023-09-05

申请号：US17048414

申请日：2019-04-17

申请人： AVSS-AERIAL VEHICLE SAFETY SOLUTIONS INC.

发明人： Josh Ogden ,  Josh Boudreau ,  Robert D. Watters ,  Mike Sirois ,  Luc Boucher ,  Etienne Poisson

IPC分类号： B64C9/02 ,  B64C39/02 ,  B64D17/70 ,  B64D17/80 ,  B64U70/83

CPC分类号： B64C39/024 ,  B64D17/70 ,  B64D17/80 ,  B64U70/83 ,  B64U2201/20

摘要： An apparatus an unmanned aerial vehicle recovery system is provided. The apparatus includes a base to mount to an unmanned aerial vehicle. The apparatus further includes a housing to engage the base. In addition, the apparatus includes a parachute disposed within the housing. Also, the apparatus includes a deployment mechanism to deploy the parachute. The deployment mechanism is to eject the housing away from the base upon a triggering event.

公开(公告)号：US20230264821A1

公开(公告)日：2023-08-24

申请号：US18012556

申请日：2021-06-23

申请人： Boris POPOV ,  Urik POPOV

发明人： Boris POPOV ,  Urik POPOV

IPC分类号： B64D17/80 ,  B64D17/72

CPC分类号： B64D17/80 ,  B64D17/725

摘要： An aircraft emergency parachute deployment system (AEPDS) is disclosed. The AEPDS includes a parachute assembly coupled with an aircraft, a ballistic rocket assembly coupled to a top portion of the parachute assembly by a lanyard, an actuator for initiating launch of the ballistic rocket; and a control module configured to receive aircraft orientation measurements and controlling launch of the rocket when the spatial orientation the aircraft is within a pre-selected range of values.