-
公开(公告)号：US20160039515A1
公开(公告)日：2016-02-11
申请号：US14747205
申请日：2015-06-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Matthew Carl VanBuskirk , Michael Scott Seifert , Michael Christopher Burnett , Mark Loring Isaac
CPC classification number: B64C5/02 , B64C1/26 , B64C5/10 , B64C29/0033
Abstract: According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion.
Abstract translation: 根据一个实施例，尾翼连接系统具有尾部附接机构和前向附接系统。 尾部附接机构被配置为联接到飞行器的主体的尾部部分和靠近尾翼的后翼梁的尾翼。 尾部附接机构限定俯仰轴线，使得后部附接机构允许尾翼围绕俯仰轴线旋转。 前向附接系统被配置为联接到身体的尾部和靠近尾翼的前翼的尾翼。 前向附接系统被配置为将尾翼围绕俯仰轴的旋转限制到允许的运动范围。
-
公开(公告)号：US11565800B2
公开(公告)日：2023-01-31
申请号：US16048869
申请日：2018-07-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Mark Mays , Michael Christopher Burnett
Abstract: Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.
-
公开(公告)号：US11440652B2
公开(公告)日：2022-09-13
申请号：US16056610
申请日：2018-08-07
Applicant: Bell Helicopter Textron Inc.
IPC: B29C70/30 , B64C27/473 , B29C70/54 , B32B1/08 , B32B5/12 , B32B5/02 , B32B5/26 , B32B37/18 , B32B38/18 , B29C70/32 , B29C53/56 , B64C11/26 , B29K105/08 , B29K105/24 , B29L31/08
Abstract: Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.
-
公开(公告)号：US10829199B2
公开(公告)日：2020-11-10
申请号：US16105215
申请日：2018-08-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey , Michael Christopher Burnett
Abstract: Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.
-
公开(公告)号：US20190106197A1
公开(公告)日：2019-04-11
申请号：US15728386
申请日：2017-10-09
Applicant: Bell Helicopter Textron Inc.
Abstract: A blade for an aircraft rotor has a trailing-edge tab, the tab being movable between a stowed position, in which substantially all of the tab is located within the blade, and a deployed position, in which at least a portion of the tab extends from a trailing edge of the blade. At least one actuator system is selectively operable to cause movement of the tab between the stowed position and the deployed position for changing a chord length of the blade.
-
Patent Agency Ranking
公开(公告)号：US10222297B2
公开(公告)日：2019-03-05
申请号：US15285569
申请日：2016-10-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Christopher Burnett , Kyle Thomas Cravener
Abstract: The present invention includes an apparatus and method for measuring hysteretic heating or stress of one or more bearings of a craft comprising: one or more non-contact temperature sensors attached to the craft and directed toward the one or more bearings; and a computer connected to the one or more non-contact temperature sensors that measure the temperature, the stress, or both of the one or more bearings before, during, or after operation of the craft, wherein the one or more non-contact temperature sensors measure a change in temperature in the one or more bearings to monitor for heating or stress of the bearings.
-
公开(公告)号：US20180346133A1
公开(公告)日：2018-12-06
申请号：US15608385
申请日：2017-05-30
Applicant: Bell Helicopter Textron Inc.
IPC: B64D15/12 , H05B3/02 , B64C27/46 , B64C27/467
Abstract: The present invention includes a first barrier layer configured to cover a leading edge of the blade or wing; one or more electrical bus bars disposed on the first barrier layer proximate to and substantially parallel with the leading edge; a ground bus bar disposed on the first barrier layer proximate to and substantially parallel with the leading edge; a second barrier layer disposed over the one or more electrical bus bars and the ground bus bar; one or more heating elements disposed on the second barrier layer, and each heating element electrically connected to one of the electrical bus bars and to the ground bus bar; and a third barrier layer disposed over the one or more heating elements.
-
公开(公告)号：US10710712B2
公开(公告)日：2020-07-14
申请号：US15935927
申请日：2018-03-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Joel J. McIntyre , Michael Christopher Burnett
IPC: B64C27/473 , B64C27/467 , B64C29/00 , B64C11/26
Abstract: An afterbody for a rotor blade of a rotorcraft is unitarily formed of a single material of construction. The afterbody includes an upper surface disposed from a lower surface, a concave leading edge connected to the upper surface and the lower surface, and a trailing edge formed at an intersection of the upper surface with the lower surface.
-
公开(公告)号：US20200055586A1
公开(公告)日：2020-02-20
申请号：US16105215
申请日：2018-08-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey , Michael Christopher Burnett
Abstract: Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.
-
公开(公告)号：US20200047879A1
公开(公告)日：2020-02-13
申请号：US16056610
申请日：2018-08-07
Applicant: Bell Helicopter Textron Inc.
IPC: B64C27/473 , B29C70/30 , B29C70/54 , B32B1/08 , B32B5/12 , B32B5/02 , B32B5/26 , B32B37/18 , B32B38/18
Abstract: Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.
-
-
-
-
-
-
-
-
-
Search Results
24
records
(took 0.017 seconds)
