• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    MODULAR SUSPENDED BRAKE AND TRUCK CONTROL SYSTEM A modular brake and rudder control system usable in an aircraft. The modular system mounts above the cockpit floor (16) without penetrating the floor when the system is operationally connected to the aircraft's fly-by-wire rudder and brake systems. The pedal assemblies (66) extending from the housing (40) are rotatable and longitudinally movable with respect to the housing. A brake control system fully contained in the housing is connected to the pedal assemblies and provides a signal via an electrical connector (28) to the fly-by-wire brake system by rotating the pedals. A rudder control system is fully contained in the housing and is operated independently of the brake control system. The rudder control system detects the longitudinal movement of the pedal assemblies and provides a signal via an electrical connector (28) to the fly-by-wire rudder system. The housing, electrical connectors, pedal assemblies, brake control system and rudder control system define an installable and removable modular cockpit component as a unit.
    公开号:BR112015010717B1
    申请号:R112015010717-6
    申请日:2013-11-11
    公开日:2021-06-08
    发明作者:Fred Carner；Bijan Salamat
    申请人:Mason Electric, Co；
    IPC主号:
    专利说明:

    CROSS REFERENCE ON RELATED REQUEST
    [001]This non-provisional patent application claims priority to and benefits from provisional US patent application No. 61/724,815 entitled ABOVE-THE-FLOOR RUDDER AND BRAKE CONTROL SYSTEM, filed November 9, 2012, which is incorporated herein in its entirety by reference. TECHNICAL FIELD
    [002] The modalities of this description are directed to flight surface controls and brake controls for aircraft. FUNDAMENTALS
    [003] Conventional fixed-wing aircraft have a plurality of control surfaces, including the rudder, operated by mechanical connections and cabling to interconnect the pilot-controlled rudder pedals to the actual control surface at the rear of the aircraft. Connections and cabling typically extend the length of the aircraft under the flight deck. These connections and cabling can be difficult to access, maintain and even install during initial fabrication. Conventional aircraft brake systems have similar disadvantages. Electric fly-by-wire control systems have been contemplated for flight control systems and aircraft brake systems. However, there is a need to create a highly accurate and reliable electrical wire control rudder control system and/or brake control system for use on the aircraft while remaining in a compact space envelope. SUMMARY
    [004] The present description is directed to an above-floor modular brake and rudder control system that overcomes the disadvantages of the prior art and provides other benefits. At least one embodiment of the present description is directed to a modular rudder and brake control system for use in an aircraft having a cockpit with a flight deck floor. The aircraft has a wired control brake system and a wired control rudder system. The modular rudder and brake control system comprises a housing with opposite sides, and the housing is configured to be mounted fully above the flight cabin floor without penetrating the flight cabin floor when the rudder and brake control system modular is operatively connected to the rudder and brake systems by wired control. Electrical connectors are connected to the housing and are operably connectable to the rudder and brake systems by wired control. A pair of pedal assemblies attach to the housing and protrude from the sides. Each pedal assembly has a foot pedal engageable by a pilot or other operator, and each pedal assembly can be independently rotated about an axis of rotation in response to operator engagement. Each pedal assembly can also be moved longitudinally with respect to the housing.
    [005] The modular brake and rudder control system also has a brake control system fully contained in the housing and connected to the pedal assemblies. The brake control system has a first motion sensor operatively coupled to at least a first of the pedal assemblies and is connected to at least a first of electrical connectors that connect to the brake system by wired control. The first motion sensor is configured to detect the rotational movement of the pedal assembly and to provide a first signal through the first electrical connector to the wired control brake system for actuating the wired control brake system as a a function of the range or rate of rotary movement of the pedal assembly.
    [006] The modular brake and rudder control system also has a rudder control system fully contained in the housing and operationally independent of the brake control system. The rudder control system has a second motion sensor operably coupled to the pedal assemblies independently of the first sensor and connected to a second one of the electrical connectors that connects to the rudder system by wired control. The second motion sensor is configured to detect the longitudinal movement of the pedal assemblies and to provide a second signal through the second electrical connector to the wired control rudder system as a function of the longitudinal movement of the pedal assembly with respect to the housing. .
    [007] The modular brake and rudder control system also has a brake control system fully contained in the housing and connected to the pedal assemblies. The brake control system has a first motion sensor operatively coupled to at least a first of the pedal assemblies and is connected to at least a first of the electrical connectors that connect the brake system by wired control. The first motion sensor is configured to detect the rotary movement of the pedal assembly and provide a first signal through the first electrical connector to the wired control brake system for actuation of the wired control brake system as a function of the range or rate of rotation of the pedal assembly.
    [008] The modular brake and rudder control system also has a rudder control system fully contained in the housing and operationally independent of the brake control system. The rudder control system has a second motion sensor operably coupled to the pedal assemblies independently of the first sensor and connected to a second of the electrical connectors that connects the rudder system by wired control. The second motion sensor is configured to detect the longitudinal movement of the pedal assemblies and to provide a second signal through the second electrical connector to the wired control rudder system as a function of the longitudinal movement of the pedal assembly with respect to the housing. .
    [009] The modular brake and rudder control system also has a position adjustment system operated independently of the brake control system and rudder control system. The position adjustment system is connected to the pedal assemblies and is adjustable to simultaneously move the pedal assemblies in the same direction to change a longitudinal position of the pedal assemblies with respect to the housing between the forward and reverse positions.
    [010] Another embodiment provides a modular brake and rudder control system for use in a vehicle having a control center with a flight deck floor and having an electronically controlled brake system and an electronically controlled rudder system. The modular rudder and brake control system comprises a housing that is mounted in the control center fully above the flight deck floor without penetrating through the floor when the modular rudder and brake control system is operatively connected to the control systems. rudder and brake. Electrical connectors are connected to the housing and are operably connectable to the brake and rudder systems. A pair of pedal assemblies protrude from the housing, and each pedal assembly has an operator-engaging pedal. Each pedal assembly is independently rotated and moved longitudinally with respect to the housing.
    [011]The modular brake and rudder control system has a brake control system fully contained in the housing and connected to the pedal assemblies. The brake control system has a first motion sensor operatively coupled to at least one of the pedal assemblies and connected to at least one of the first electrical connectors that connects to the brake system. The first sensor is configured to detect the first movement of the pedal assembly and provide a first signal through the first electrical connector to the brake system to actuate the brake system as a function of the range of the first movement of the pedal assembly.
    [012]The modular brake and rudder control system has a rudder control system fully contained in the housing and operationally independent of the brake control system. The rudder control system has a second motion sensor operably coupled to the pedal assemblies and connected to a second of the electrical connectors that connects to the rudder system. The second motion sensor is configured to detect the longitudinal movement of the pedal assemblies and provide a second signal through the second electrical connector to the rudder system as a function of the longitudinal movement of the pedal assembly.
    [013] Another modality provides a modular rudder and brake control system for use in an aircraft having a cockpit with a flight deck floor, and having an electrical wire control brake system and a rudder system by control by electrical wire. The modular rudder and brake control system comprises a housing with a frame and a cover over the frame. The frame is detachably attached to the flight deck floor without penetrating the floor when the modular rudder and brake control system is operatively connected to the rudder and brake systems. The electrical connectors are connected to the housing and are operably connectable to the rudder and brake systems. A pair of pedal assemblies extend from the housing, and each pedal assembly is rotatably and longitudinally moved with respect to the housing.
    [014]A brake control system is fully contained in the housing and is carried by the frame. The brake control system is connected to the pedal assemblies and to at least one of the first electrical connectors that connect the brake system. The brake control system detects the rotary movement of the pedal assembly and provides a first signal through the first electrical connector to the brake system to actuate the brake system. A rudder control system is fully contained in the housing and is carried by the frame. The rudder control system is connected to the pedal assemblies and is operated independently of the brake control system. The rudder control system is connected to at least one second of the electrical connectors that connect the rudder system. The rudder control system detects the longitudinal movement of the pedal assemblies and provides a second signal through the second electrical connector to the rudder system. The housing, electrical connectors, pedal assemblies, brake control system and rudder control system define a modular component that can be installed and removed from the cockpit as a unit. BRIEF DESCRIPTION OF THE DRAWINGS
    [015] Figure 1 is an isometric view of an aircraft having a rudder and brake control system above the floor according to one or more embodiments of the present description;
    [016] Figure 2 is an isometric rear view of a rudder and brake control assembly above the floor of the system of Figure 1 according to one or more embodiments of the present description;
    [017] Figure 3 is a side elevation view of the rudder and brake control assembly of Figure 2;
    [018] Figure 4 is a rear isometric view of the rudder and brake control assembly of Figure 2 with the cover removed for illustration purposes;
    [019] Figure 5 is a front isometric view of the rudder and brake control assembly of Figure 2 with the cover not shown for clarity;
    [020] Figure 6 is a side elevation view of the rudder and brake control assembly of Figure 3 with the cover not shown for illustration purposes;
    [021] Figure 7 is a schematic illustration of at least parts of an illustrated brake control assembly removed from the brake and rudder control assembly of Figure 6, where the brake control assembly is in a "No Brake" condition ";
    [022] Figure 8 is a schematic illustration of the brake control assembly of Figure 7 shown in a "Brake applied" condition;
    [023] Figure 9 is a front isometric view of the rudder and brake control assembly of Figure 4 with parts of a rudder control assembly not shown to avoid obscuring aspects of the brake control assembly;
    [024] Figure 10 is a front isometric view of the rudder and brake control assembly of Figure 4 with parts of the brake control assembly not shown to avoid obscuring aspects of the rudder control assembly;
    [025] Figures 11 and 12 are partial side elevation views of the illustrated rudder control assembly components removed from the assembly of Figure 10 for illustration purposes;
    [026] Figures 13 and 14 are partial isometric views illustrating the rudder control assembly components removed from the assembly of Figure 10 for illustration purposes;
    [027] Figure 15 is an enlarged isometric view of a portion of the illustrated rudder control assembly removed from the assembly of Figure 10 for purposes of illustration;
    [028] Figure 16 is an isometric view of a pair of rudder and brake control assemblies in accordance with the present description interconnected by an interconnecting rod for simultaneous and identical operation of each unit;
    [029] Figure 17 is an isometric view of the pair of brake and rudder control units of Figure 16 and with the covers not shown for illustration purposes;
    [030] Figure 18 is an enlarged isometric view of a rudder feedback assembly of the rudder control assembly of Figure 4, the rudder feedback system illustrated in a "neutral rudder" position;
    [031] Figure 19 is an enlarged isometric view of the rudder return assembly of Figure 18 shown in a "left rudder" position;
    [032] Figure 20 is an enlarged isometric view of the rudder return assembly of Figure 18 shown in a "right rudder" position;
    [033] Figure 21 is a partial isometric view of the rudder and brake control assembly of Figure 4 with parts of a pedal assembly not shown to avoid obscuring a pedal position adjustment assembly, which is shown in an intermediate position ;
    [034] Figure 22 is a side elevation view of the pedal position adjustment assembly of Figure 21, with the pedal assemblies illustrated in a more forward position;
    [035] Figure 23 is a side elevation view of the pedal position adjustment assembly of Figure 21, with the illustrated pedal assemblies in a more rearward position;
    [036] Figure 24 is a partial side elevation view of the pedal position adjustment assembly of Figure 21, with the pedal assemblies shown in an intermediate position. DETAILED DESCRIPTION
    [037] A rudder and brake control system for use with an aircraft having wireline control systems in accordance with the embodiments of the present description is illustrated in the drawings for illustration purposes. Various details specific to modalities are presented in the description that follows, and the figures provide an in-depth understanding of certain modalities in the description. Those skilled in the art, however, will understand that the present invention may have additional embodiments, and that other embodiments may be practiced without various specific features described below.
    [038] Figure 1 schematically illustrates an aircraft 12 having a wired control rudder control system 13 operatively connected to a rudder 14. The aircraft 12 also has a wired control brake control system electric 15 operatively connected to aircraft brakes. Aircraft 12 has a modular wireline control rudder and brake control assembly above floor 10 that electrically interfaces with and provides control signals to control rudder control system 13 and brake control system 15 The modular brake and rudder control assembly 10 is mounted above the flight deck floor 16 in the aircraft cockpit 18 in a position for operationally engaging by a pilot controlling the aircraft 12. In the illustrated embodiment, the cockpit Aircraft control 18 includes a commander station 20 and a first officer station 22, each of which includes a rudder and brake control assembly 10 for use by the respective pilot to help control the aircraft.
    [039] As noted in Figure 2, the rudder and brake control assembly 10 is a self-contained modular unit having a base plate 24 affixed to the upper surface 26 of the floor of the flight deck 16 without needing to penetrate through the flight deck. This modular rudder and brake control system, above floor 10 includes a plurality of electrical connectors 28 on the front surface that operatively connects the aircraft's wired control rudder control system, brake control system, and targeting system. This modular construction without needing to penetrate the flight deck allows for quick and easy installation, maintenance, and replacement while maintaining a compact envelope to minimize space requirements within cockpit 18 (figure 1).
    [040] The brake and rudder control assembly 10 is described here with respect to the front and rear entry and exit reference frame, as would be a typical orientation in cockpit 18 of aircraft 12. It should be understood that the assembly brake and rudder control panel 10 may or may not have other orientations relative to a selected mounting surface. Additionally, the brake and rudder control assembly 10 illustrated in the figures is discussed below with respect to the commander's station 20 on the aircraft 12. The modular rudder and brake control assembly 10 is, however, interchangeable between the commander's station 20 and the season of the first officer 22.
    [041] Referring to Figures 2 and 3, the brake and rudder control assembly 10 has a rear part 30, a front part 32, an input part 34, and an output part 36 with respect to the commander's station in the port side of the centerline of the aircraft. The brake and rudder control assembly 10 has an inner frame 38 that includes the base plate 24 and that supports a removable cover 40. Each side wall 42 of the cover 40 includes an elongated pedal partition 42 oriented substantially parallel to the floor of the cabin. flight 16 on which the base plate 24 is mounted. A portion of an inner pedal assembly 44 projects through partition 42 in the inner casing sidewall of the cover 40, and a part of an outer pedal assembly 46 projects through the partition 42 in the outer casing side wall. Partitions 42 are shaped and sized to accommodate horizontal movement of pedal assemblies 44 and 46 with respect to the floor of flight deck 16 during operation of a rudder control assembly and during position adjustment of pedal assemblies 44 and 46, as discussed in more detail below.
    [042] Figures 4 and 5 are isometric views of the brake and rudder control assembly 10 with the cover 40 removed from the inner frame 38 to illustrate the internal components of the system. Frame 38 has base plate 24 connected to front and rear frame portions 48 and 50 and to inner and outer side panels 52 and 54 spanning between front and rear portions 48 and 50. Frame 38 also has a frame element top 56 substantially aligned with the longitudinal centerline of the frame and connected to the front and rear frame portions 48 and 50.
    [043] Brake and rudder control assembly 10 has three independent systems operatively interconnected to frame 38. The three systems include a brake control assembly 60, a rudder control assembly 62, and a steering adjustment assembly. 64 pedal, each of which is controlled and operated independently of the other sets. The three systems interface with the rider through inner and outer pedal assemblies 44 and 46. Each pedal assembly has a foot pedal 66 outside of frame 38 and cover 40 (figure 2) and positioned for engagement by the rider's foot. Foot pedal 66 has an upper forefoot portion 68 and a lower heel portion 70. A pedal attachment shaft 72 is attached to the lower heel portion 70 and extends through the horizontal partition 42 (Fig. 3) in the side wall of the cover toward an inner area of the frame 38. The pedal attachment axis 72 has a longitudinal axis 74 substantially perpendicular to the centerline of the frame 38, and the pedal attachment axis is attached to the foot pedal 66 of so that the foot pedal 66 and the clamping shaft 72 can rotate as a unit about the longitudinal axis of the shaft 74. This pedal assembly arrangement provides the input frame that allows the rider to control the brake system of the foot. aircraft. BRAKE CONTROL SYSTEM
    [044] The brake control assembly 60 is configured so that the pilot can push the forefoot portion 68 of the inner and/or outer foot pedal 66 to cause activation of the aircraft's brake system. Brake control assembly 60 is identical for each of the inner and outer pedal assemblies 44 and 46, so only one will be described. The pedal assembly attachment shaft 72 extends horizontally away from the foot pedal 66, through a lower end 76 of a crank element 94, and is secured to a rear end 78 of a brake lever 80. brake 80 projects forward and away from the clamping shaft 72 and terminates in a front end portion 82. The brake lever 80 is rigidly clamped to the clamping shaft 72, so that the foot pedal 66, the shaft of attachment 72 and brake lever 80 all articulate as a unit around the longitudinal axis of axis 74.
    [045] The front end portion 82 of the brake lever 80 is attached to a brake sensor mechanism that detects the articulated movement of the foot pedal 66. In the illustrated embodiment, the brake sensor mechanism is a Linear Variable Differential Transformer ("LVDT") 84 affixed at its lower end to the front end of brake lever 80. The LVDT 84 is electrically coupled to at least one of the electrical connectors 28 carried in the front portion 48 of frame 38, thus providing a connection with the aircraft's wired control brake system. The upper end 86 of the LVDT 84 is attached to an upper connecting element 88 which remains in a fixed position when the pilot pushes the foot pedal to activate the aircraft's brake system. The LVDT 84 is configured to detect the range and rate of movement of brake lever 80 by rotating foot pedal 66 about longitudinal axis 74 and to generate a brake control signal as a function of range and/or brake lever movement rate 80.
    [046] When the rider pushes the forefoot portion 68 of any pedal 66, the pedal and its associated brake lever 80 rotate about the longitudinal axis of the clamping shaft 74. This rotation pulls down on the bottom of the LVDT 84 to extend the LVDT 84 with respect to the upper connecting element 88, causing the LVDT 84 to generate and send a signal for activation of the aircraft brake control system 15 through one or more of the connectors 28. In the illustrated embodiment, the LVDT 84 provides a selected resistance to pedal rotation during brake application to provide a brake feel force and a break force detectable by the rider's foot while applying the brakes. For example, LVDT 84 can utilize redundant springs to provide feel to the pilot as he pushes against pedal 66 to apply the aircraft's brakes.
    [047] Although the illustrated embodiment uses an LVDT 84 to detect the pilot's brake register command, other embodiments may use other sensor mechanisms to detect the movement of the brake lever 80 and to provide the brake input signal to the aircraft's brake system via connectors 28. Each of the inner and outer pedal assemblies 44 and 46 are connected to independent brake systems that can each be activated by the pilot, individually or together, to provide the signal. control system for the aircraft brake system 15 (figure 1).
    [048] Figures 7 and 8 are illustrations of parts of the illustrated brake control assembly 60 removed from the frame 38 and other components of the brake and rudder control assembly 10 to avoid obscuring the characteristics of the brake control assembly 60. Figure 9 is a partial anterior isometric view of the rudder and brake control assembly 10 with portions of the rudder control assembly 62 not illustrated for purposes of discussion and to avoid obscuring the features of the brake control assembly 60. As seen in the figures , the brake control assembly 60 includes a stop rod 90 connected to the brake lever 80 ahead of the pedal clamp shaft 72. The upper end of the stop rod 90 is secured to the upper connecting member 88. The stop rod 90 is configured to allow brake lever 80 to pivot through a brake step having the selected range of motion between a "no brake" position (figure 7) and a "brake" position io total" (figure 8). In the illustrated embodiment, stop rod 90 allows brake lever 80 to rotate through a range of approximately 0 to 15 inclusive, around the longitudinal axis of clamping axis 74.
    [049] In the illustrated mode, this range of rotation movement of the brake lever 80 corresponds to approximately 2.54 cm of axial travel of the LVDT 84 by rotating the foot pedal 66 between the "no brake" position and the " full brake". In other embodiments, the inner and outer pedal assemblies 44 and 46 can be configured to provide a different brake pitch between the "no brake" and "full brake" positions. For example, a shorter or longer brake lever 80 can be used to provide a different range of foot pedal movement for activating the brakes. Such variation in brake step length may be based on pilot preference and/or other operational or ergonomic factors. Brake control assembly 60 may also include guidance elements coupled to the LVDT 84 or other brake component that push the brake foot pedals to the "no brake" position. HELM CONTROL SYSTEM
    [050] The rudder control assembly 62 operates independently of the brake control assembly 60, so the pilot can provide rudder control input through the foot pedals 66 regardless of activation of the brake control assembly 60. rudder control set 62 can also be activated simultaneously with brake control set 60 as required.
    [051] Figure 10 is a partial front isometric view of the brake and rudder control assembly 10 with parts of a brake control assembly 60 not shown (for example, the brake lever 80, LVDT 84 and stop rod 90) for purposes of discussion and to avoid obscuring the features of the rudder control assembly 62. The rudder control assembly 62 includes a substantially identical configuration for each of the inner and outer pedal assemblies 44 and 46 so that only one is described. in detail here. As seen in the figures, each pedal assembly 44 and 46 is connected to an inverted L-shaped crank element 94 having a generally vertical extension 96 and a generally horizontal extension 98. The vertical extension 96 is pivotally connected at its end 100 lower than the pedal attachment shaft 72 between the foot pedal 66 and the brake lever 80 (figure 10). The upper end of the vertical extension 102 forms an intersection and is integrally connected to the rear end 104 of the horizontal extension 98. The crank element 94 has an intermediate hinged portion 106 at the intersection of the vertical and horizontal extensions 96 and 98 spaced above the attachment axis crank arm 72. The crank element 94 is pivotally connected at its intermediate pivot portion 106 to a tiller crank support shaft 108 coupled to the frame 38 so as to allow the crank element 94 to pivot with respect to the frame. 38 around the crank support shaft 108.
    [052] The crank support axis 108 is oriented with its longitudinal axis 110 substantially parallel to the longitudinal axis 74 of the pedal clamp axis 72. Accordingly, the forward and backward movement of the heel portion of the foot pedal 70 causes the lower end 100 of the vertical extension of the crank element 96 to move forward or backward with respect to the frame 38. As illustrated in Figures 11 and 12, this movement causes the crank element 94 to pivot on its part. intermediate pivot 106 about crank support shaft 108, causing the front end 112 of horizontal extension 98 to move up or down with respect to frame 38. A rudder support 114 is pivotally secured at its upper end to the front end 112 of the horizontal extension of the crank 98. The lower end of the rudder support 118 is fixedly connected to a foot pedal interconnect assembly 120 which interconnects operatively the inner and outer pedal assemblies 44 and 46.
    [053] As illustrated in Figure 10, the foot pedal interconnect assembly 120 has a rudder control shaft 122 rotatably carried by the frame 38 substantially parallel to the base plate of the frame 24. A rear end 124 of the wheel shaft rudder control 122 is rotatably fixed to the rear of the frame 50 and the front end of the axle 126 is rotatably fixed to the front of the frame 48 so that the longitudinal axis of the rudder control axle 122 is substantially aligned with the centerline of the frame and is perpendicular to the pedal attachment axis 72. The rudder control shaft 122 carries a crank attachment 128 so that the rudder control shaft and the crank attachment rotate as a unit with respect to the frame 38.
    [054] As illustrated in Figures 13 and 14, the crank fitting 128 has an opposite pair of free end portions 130 spaced apart from the rudder control shaft 122. Each free end portion 130 is secured to a lower end 118 of a of the respective rudder mounts 114. Accordingly, the rudder mounts 114 interconnect the rudder control shaft 122 with the L-shaped crank elements 94 and their associated foot pedals 66 to effect movement in equal and opposite directions with respect to the rudder control shaft. 122. For example, when a rider depresses a foot pedal 66 in an anterior direction with respect to frame 38 (Figure 10), the associated crank element 94 pivots about the crank support shaft 108, thus raising the horizontal extension 98 and its associated rudder support 114, which pulls up the corresponding free end portion 130 of the crank fitting 128 and rotates the rudder control axis 122 about its longitudinal axis. This rotation of the rudder control shaft 122 in the counterclockwise direction, as illustrated in Figures 13 and 14, pulls the other free end portion 130 of the crank fitting 128 downward, thus pulling the attached rudder holder 114 and the horizontal extension of the crank element 98 downwards, which articulates the crank element 94, and pushes the other foot pedal 66 in the rearward direction with respect to the frame 38 (figure 10). Accordingly, the inner and outer pedal assemblies 44 and 46 are interconnected to move in equal and opposite directions when a rider pushes against the heel portion 70 of a foot pedal 66. Guiding elements such as one or more springs Torsionals concentric with the rudder control shaft 122, can be used to provide torque to continuously oppose the rudder movement and return the pedals 66 to a neutral position, thus providing selected tactile feedback to the pilot.
    [055] The rudder control shaft 122 is coupled to one or more rotary motion sensing elements 132 illustrated in Figure 15. The rotary sensing elements 132 are configured to detect rotary motion of the rudder control shaft around of its longitudinal axis in response to pilot registration through pedal assemblies 44 and 46 (figure 10), or in response to registration of an autopilot system. In the illustrated embodiment, rotary motion sensing elements 132 include a plurality of Rotary Variable Differential Transformers ("RVDTs") mounted at the front end of the rudder control shaft 122 and operatively coupled to one or more of the electrical connectors 28 at the front part of frame 38 (figure 10). RVDTs provide one or more signals, such as variable angular displacement data related to the control axis as a function of the pilot register via foot pedals 66. These signals are provided via electrical connectors 28 for rudder manipulation and control. 14 of the aircraft helm control system (figure 1). Accordingly, the rudder control assembly 62 can be easily and quickly connected, via electrical connectors 28, to the aircraft's wired control flight control system to control the movement of the aircraft's rudder 14 (figure 1 ), without having to go through the flight cabin.
    [056] As best seen in Figures 15 and 16, at least one embodiment of the rudder control assembly 62 includes a station interconnect assembly 136 that operatively interconnects the rudder control assemblies 62 of the rudder control assemblies. and adjacent modular brake 10, such as the commander and first officer stations on the aircraft. Station interconnect assembly 136 includes an adjustable interconnect shaft 138 that mechanically interconnects and identically transports the helm control record from the assembly at one pilot station to the assembly at another pilot station.
    [057] In the illustrated embodiment, the interconnect axis 138 is substantially perpendicular to the rudder control axis 122 (figure 15). Each end of the interconnecting shaft 138 is operatively connected to an interconnecting flange 140 (figure 15) secured to the front end portion of the rudder control shaft 122. The interconnecting flange 140 rotates with the rudder control shaft 122 as a unit, such that a free end 142 of the interconnecting flange 140 spaced apart from the rudder control axis 122 moves along an arcuate path as the rudder control axis 122 rotates about its longitudinal axis. The free end 142 of the interconnecting flange 140 is pivotally connected to the end of the interconnecting shaft 138. Accordingly, rotation of the rudder control shaft 122 and the interconnecting flange 140 drives the interconnecting shaft 138 laterally in the left direction. or right, depending on the direction of rotation of the rudder control axis. This lateral movement of the interconnecting shaft 138 creates equal rotation of the rudder control shafts 122 of the two modulator assemblies 10 to which the ends of the interconnecting shaft are attached. Accordingly, a pilot helm control record at one pilot station will be substantially identically mirrored at the other pilot station via station interconnect assembly 136.
    [058] As noted in Figures 10 and 18 through 20, the rudder control assembly 62 has a rudder centering assembly 146 connected to the rear end portion 124 of the rudder control shaft 122. The rudder centering assembly 146 provides guidance forces that push rudder control assembly 62 to a neutral "rudderless" position. The rudder centering assembly 146 of the illustrated embodiment has a pair of redundant torsion springs 148 or other rotation guidance elements connected to the rudder control shaft 122. Each torsion spring 148 is secured to the rudder control shaft 122 with a spring capture element 150 which captures the torsion springs while allowing the rudder control shaft 122 to rotate relative to the frame 38.
    [059]Each spring 148 has inner and outer engagement lugs 152 projecting away from the rudder control shaft 122. Adjustable inner and outer spring stops 154 are mounted on the rear of the frame 50 adjacent to the torsion springs 148. Each adjustable spring stop 154 is positioned to lock the respective inner and outer flexible tabs 152 preventing them from moving past the stop as the rudder control shaft 122 rotates away from the neutral or "no rudder" position. Accordingly, torsion springs 148 provide torsional resistance for rotating the rudder control shaft 122 away from the neutral position and, upon rotation, pushing the shaft back to the neutral position. In the illustrated embodiment, the redundant torsion springs 148 are configured to provide a torque of approximately 184 inch-pounds, which is the equivalent of approximately 40 pounds of rider feel on foot pedals 66 during full rudder pitch in either direction. . In one embodiment, the rudder centering assembly 146 may be mounted on an adjustable bracket configured to allow adjustment of spring stops 154 and to allow adjustment of the neutral position with respect to a second neutral rating selected when the control assembly rudder and brake 10 is installed on the aircraft.
    [060] In one embodiment, the rudder and brake control assembly 10 may include an adjustment lever secured to the rear end portion 124 of the rudder control shaft 122. The adjustment lever has an opening that aligns with an opening in the rear of frame 50 when rudder is in neutral position. The aligned openings are configured to receive a rigging pin or similar so that the rigging pin blocks the rudder control shaft preventing its rotation, thereby effectively keeping the aircraft rudder in the neutral position. Additional alignable openings in the adjustment lever and rear of the frame can be provided to receive the rigging pin and hold the aircraft rudder at full left and right rudder positions or other selected intermediate positions. PEDAL ADJUSTMENT SYSTEM
    [061] The rudder and brake control system pedal adjustment assembly 64 is operatively independent of the brake control assembly 60 and the rudder control assembly 62 discussed above. The 64 Foot Pedal Adjustment Kit allows adjustment of the position of the 66 Foot Pedals. The extent of adjustment can be selected based on ergonomic and human factors data for riders of different sizes. In the illustrated embodiment, the pedal adjustment assembly 64 allows angular and longitudinal adjustment of the foot pedals 66 in the anterior and posterior directions with respect to the frame 38 without changing the pedal step length and without interfering with the rudder control assembly. 62 or set of brake set 60.
    [062] The pedal adjustment assembly 64 is configured to allow the foot pedals 66 to move between a more forward position (figure 22), for example, for a long-legged rider, and a more rearward position (figure 23 ), for example, for a rider with shorter legs. In the illustrated embodiment, the pedal adjustment assembly 64 is configured to provide an adjustment pitch of approximately 23 cm of horizontal travel with respect to the base plate of the frame 24. The pedal adjustment assembly 64 is also configured to change orientation. angle of the foot pedals 66 through a range of approximately 18 with respect to the base plate of the frame 24 to accommodate the typical foot orientation of taller and shorter pilots while seated in the aircraft pilot seat. Other modalities may provide other adjustment ranges including longer and shorter adjustment steps and larger or smaller ranges of angular adjustment.
    [063] Figure 24 is a partial side elevation view of the rudder and brake control assembly 10 with the shroud and other selected components not shown to avoid obscuring other features of the pedal adjustment assembly 64. As best seen in the figures 21 and 24, the pedal adjustment assembly 64 includes an upper guide bar 160 secured at the front and rear ends to the front and rear portions of the frame 48 and 50. The guide bar 160 is substantially parallel to the base plate of the frame 24 and is aligned with the center line of the frame. Guide bar 160 extends through a translatable central guide structure 162 configured to slideably move over guide bar 160 between the front and rear adjustment positions with respect to frame 38. The central guide structure 162 is also disposed between two crank elements 94 and in alignment with the centerline of the frame.
    [064] The central guide frame 162 has a top 164 with an opening 166 therethrough that carries the crank support shaft 108 that connects to the inverted L-shaped crank elements 94. Accordingly, the guide frame center 162 moves with the inner and outer pedal assemblies 44 and 46 as a unit between the front and rear adjustment positions. The central guide frame 164 also has sets of longitudinally aligned top and bottom openings 168 and 170 (Fig. 21). The upper guide bar 160 is slidably disposed in the set of upper openings 168. A horizontal drive shaft 172 is positioned below and vertically aligned with the upper guide bar 160. The drive shaft 172 extends through the set of lower openings 170 in the central guide frame 162 and is rotatably supported at its front and rear ends by frame 38.
    [065] In the illustrated embodiment, the drive shaft 172 is a threaded drive shaft, and at least one of the lower openings 170 of the center guide support 162 includes mating internal threads that operatively engage the threads in the drive shaft 172. drive motor 174 is connected to a front end portion of drive shaft 172 and is activated to rotate drive shaft 172 about its longitudinal axis. When the drive motor 174 rotates the drive shaft 172, threaded engagement between the drive shaft and the center support structure 162 causes the center support structure to move forward or backward along the drive shaft 172 and along the upper guide bar 160. This translation of the center support structure 162 simultaneously moves the pedal assemblies 44 and 46 in the anterior and posterior directions with respect to the frame 38. The threaded drive shaft 172 can be manually rotated for manual adjustment. of pedal positions with respect to frame 38. Although the illustrated embodiment utilizes a drive motor and threaded drive shaft to adjust the pedal assemblies, other embodiments may utilize other drive mechanisms to translate the pedal assemblies horizontally along. your tuning step.
    [066] The center guide frame 162 is also fixedly connected at its bottom 176 to a ball joint nut 178 carried by the rudder control shaft 122. The ball joint nut 178 is also securely connected to the fitting crank 128 (FIG. 21) of foot pedal interconnect assembly 120. In the illustrated embodiment, crank fitting 128 is a bell-type crank fitting secured to ball joint nut 178 so as to move axially and rotatably as a unit with the ball joint nut 178. The ball joint nut 178 is slidably disposed on a ball joint shaft portion 180 of the rudder control shaft 122. The ball joint port 178 has a central opening 182 with an or plus inner grooves that slidingly coincide with elongated joints 184 on the outer diameter of the ball joint shaft portion 180. Accordingly, this joint interface makes the ball joint nut 178 the accessory. the crank 128 and the rudder control shaft 122 (through the ball joint shaft portion 180) rotate as a unit around the longitudinal axis of the shaft when one foot pedal 66 moves forward and the other foot pedal 66 moves backward to adjust the rudder position. Ball joint nut 178 is also axially translatable along ball joint shaft portion 180 as threaded drive shaft 172 rotates and adjusts the forward/reverse position of pedal assemblies 44 and 46 along its pitch. of horizontal adjustment, without impacting the operation of the rudder control assembly 62 or brake control assembly 60.
    [067]Pedal Adjustment Set 64 is also configured to modify the angular orientation of each foot pedal 66 as the pedal sets are translated in the forward or reverse direction through the adjustment step. As best seen from Figures 22 to 24, the upper connecting elements 88, discussed above with respect to the brake control assembly 60, are coupled on top of each pedal assembly 44 and 46 and are positioned adjacent the upper member. of frame 56. In the illustrated embodiment, the upper connecting elements 88 for each of the inner and outer pedal assemblies 44 and 46 are integrally connected to one another. In other embodiments, the upper connecting elements 88 for each of pedal assemblies 44 and 46 may be independent, non-integrally connected to one another. The rear end of each connecting element 88 is pivotally secured to the crank support shaft 108 adjacent the crank elements 94. The upper connecting element 88 has a front end portion 188 connected to a cam follower 190 which is slidably disposed in a cam partition 192 formed at the front of the upper frame member 56.
    [068]The cam partition 192 on the upper frame member 56 is angled downwardly from an upper advancing end 194 to a lower trailing end 196 of the partition. Cam follower 190 travels along cam partition 192 as pedal assemblies 44 and 46 are axially positioned at or between their front and rear positions. When pedal assemblies 44 and 46 are in their most anterior position, cam follower 190 is positioned at the upper front end of cam partition 194. As pedal assemblies 44 and 46 are adjusted in the posterior direction by means of the rotation of the threaded drive shaft 172, cam follower 190 follows the downward slope of cam partition 192. When pedal assemblies 44 and 46 are at the rearmost position of the adjustment step, cam follower 190 is positioned at the end. lower rear 196 of cam partition 192.
    [069] As pedal assemblies 44 and 46 are moved through the adjustment step from the rear most forward position toward the most anterior position, each foot pedal 66 pivots away from the horizontal plane and further toward near the vertical plane, thus changing the angular orientation of the foot pedal to engagement by the rider's foot. In the illustrated embodiment, when the pedal assemblies 44 and 46 are in the rearmost position and the cam follower 190 is at the lower rear end 196 of the cam partition 192, the pedal angle has an inclination of approximately 37 to 39 with respect to the vertical plane. As pedal assemblies 44 and 46 move forward through the adjustment step, the angular orientation of foot pedals 66 increases through a range of approximately 18 until the pedal assemblies are oriented at approximately 21 with respect to vertical plane when the pedal assemblies are in their most anterior position with the cam follower 190 at the upper front end 194 of the cam partition 192.
    [070]The angular orientation of the foot pedals 66 configured to provide improved comfort and fit for the pilot while seated in the pilot's seat in the aircraft cockpit. Other modalities may provide a different range of angular adjustments for the foot pedals 66, or provide different angular orientations for the foot pedals at either end of the adjustment step. For example, one or more other embodiments can provide different angular orientations of the pedal assemblies by providing a cam partition with a different angle relative to the horizontal plane. A larger angle oriented cam partition can provide an increased range of angle pedal adjustment. A shallower angle can provide less angular shift of the foot pedals as they sound moved between the most anterior and most posterior positions.
    [071] As seen in Figure 24, the upper connecting element 88 cooperates with the LVDT of the brake system 84 and/or the stop rod of the brake system 90, the brake lever 80, and the vertical extension 96 of the brake element. crank 94 to provide a four-bar connection arrangement for each pedal assembly. This four-bar connection arrangement provides a coherent, rigged, "no brake" position independent of the adjusted pedal position and rudder position. Accordingly, in the "no brake" position, the LVDT 84 opposes and is the same length as the vertical extension of the crank element 96, so the four-bar connection allows the pedal assemblies 44 and 46 to move to any position along the adjustment step without inadvertently applying or activating the brakes. The operation and performance of the brake control assembly 60 and rudder control assembly 62 remains independent of the position of the pedal assemblies throughout the adjustment step.
    [072] These three independent control systems within a modular rudder and brake control unit provide a compact and highly versatile unit that can be easily and quickly attached to the upper surface of the flight cabin without having to penetrate through the flight cabin. flight to interconnect with other systems inside the aircraft. Electrical connectors on the front end of the modular unit allow for quick and easy interconnection and disconnection with the aircraft's other braking, steering, and rudder positioning systems via the wired control interface. The modular design also allows for quick and easy installation, maintenance and/or replacement, such as during original manufacture, retrofit or while the aircraft is in the field.
    [073] From the foregoing, it will be appreciated that specific embodiments of the invention have been described herein for purposes of illustration, but that various modifications can be made without deviating from the invention. Additionally, aspects of the invention described in the context of the particular embodiments or examples may be combined or eliminated in other embodiments. While advantages associated with certain embodiments of the invention have been described in the context of those embodiments, other embodiments may also exhibit such advantages. Additionally, not all embodiments necessarily exhibit such advantages to fall within the scope of the invention. Accordingly, the invention is not limited except by the appended claims.
    权利要求:
    Claims (22)
    [0001]
    1. Modular rudder and brake control system for use in an aircraft having a cockpit with a flight deck floor, and having a braking system and a rudder system, the rudder and modular brake control system being CHARACTERIZED by the fact that it comprises: a housing with opposite sides, the housing having a frame and a cover substantially enclosing the frame, the frame having front and rear parts, a longitudinal axis extending between the front and rear parts, and a base extending between the front and rear parts, the base being configured to be mounted fully above the floor of the cabin without penetrating through the floor of the cockpit, the housing having a guide element extending between the front parts and later; electrical connectors connected to the housing and operatively connectable to the rudder and brake systems by wired control; a pair of pedal assemblies coupled to the frame and having mounting elements protruding from the sides on opposite sides of the cover, each pedal assembly having a foot pedal coupled to the mounting elements and being exterior to the cover and adjacent to the respective ones. sides of the cover and capable of being engaged by an operator, each pedal assembly being able to rotate independently, and being connected to a guide frame movably connected to the guide element, the pedal sets and guide frame being movable as a unit between front and rear pedal positions with respect to the housing; a brake control system in the housing and connected to the pedal assemblies, the brake control system having a first motion sensor operatively coupled to at least a first of the pedal assemblies and connected to at least a first of the electrical connectors , the first motion sensor configured to detect rotational movement of the pedal assembly and provide a first signal via the first electrical connector to the brake system for actuating the brake system; a rudder control system in the housing and being operationally independent of the brake control system, the rudder control system having a rotating rudder control axis and having a control accessory movable longitudinally along the rudder control axis and rotating with the rudder control shaft, the control accessory being coupled to the guide frame and movable longitudinally with the pedal assemblies relative to the guide element between the front and rear pedal positions, the rudder control system having a second motion sensor operationally coupled to the pedal assemblies and connected to a second of the electrical connectors connecting the rudder system, the second motion sensor configured to detect longitudinal movement of the foot pedals and configured to provide a second signal through the second electrical connector to the rudder system; and a position adjustment system operatively connected to the pedal assemblies and the guide structure and being adjustable so that the guide structure moves along the guide element to simultaneously move the pedal assemblies in the same direction to change a position. longitudinal of the pedal assemblies with respect to the frame on opposite sides of the cover between the front and rear positions without changing a vertical position of the foot pedal mounting elements and their axis of rotation.
    [0002]
    2. Modular rudder and brake control system, according to claim 1, CHARACTERIZED by the fact that the base is a base plate mounted above the floor of the flight cabin.
    [0003]
    3. Modular rudder and brake control system, according to claim 1, CHARACTERIZED by the fact that the housing, pedal assemblies, brake control system, rudder control system, and control system Positions define a modular unit detachably mounted above the flight deck floor.
    [0004]
    4. Modular rudder and brake control system, according to claim 3, CHARACTERIZED by the fact that the cockpit has first and second pilot stations, and in that the modular unit is configured to be interchangeably positioned in the first and second pilot stations.
    [0005]
    5. Modular rudder and brake control system according to claim 1, CHARACTERIZED by the fact that the pedal sets are the first pedal sets and the rudder control system is a first rudder control system, and further comprises an interconnection connected to the first rudder control system, the interconnection being connectable to a second rudder control system of a second rudder control system and adjacent modular brake, wherein the interconnection transfers longitudinal movement of the pedal assemblies of the first rudder control system for the longitudinal movement of the second pedal sets and the second rudder control system for the second rudder control system and modular brake.
    [0006]
    6. Modular rudder and brake control system, according to claim 1, CHARACTERIZED by the fact that the cover has opposite side walls located between the foot pedals and has elongated partitions therein, in which the mounting elements extend across the partitions and are longitudinally moved across the partitions.
    [0007]
    7. Modular rudder and brake control system, according to claim 1, CHARACTERIZED by the fact that the brake control system includes a brake lever that interconnects the first motion sensor and the first of the pedal assemblies, the brake lever and the first of the pedal assemblies being rotatable as a unit with respect to the housing, wherein the brake lever translates movement from the first of the pedal assemblies to the first motion sensor.
    [0008]
    8. Modular rudder and brake control system, according to claim 7, CHARACTERIZED by the fact that the first motion sensor is a linear motion detection element configured to detect a range and rate of movement of the brake lever upon the rotation of the first of the pedal sets and to generate a brake control signal as a function of brake lever range and rate of movement.
    [0009]
    9. Modular rudder and brake control system, according to claim 1, CHARACTERIZED by the fact that the rudder control system rotatably interconnects the pedal assemblies, in which the rotation of the rudder control axis corresponds to the longitudinal movement of each pedal assembly with respect to the housing in equal and opposite directions.
    [0010]
    10. Modular rudder and brake control system, according to claim 9, CHARACTERIZED by the fact that the second motion sensor is a rotary motion detection element coupled to the rudder control shaft and configured to detect rotary motion of the rudder control axis by the longitudinal movement of the pedal assemblies and to generate the rudder control signal as a function of the longitudinal movement of the pedal assemblies.
    [0011]
    11. Modular rudder and brake control system for use in a vehicle having a control center with a flight deck floor, and having an electronically controlled braking system and an electronically controlled rudder system, the rudder control system and modular brake being CHARACTERIZED by the fact that it comprises: a housing comprising a cover enclosing an inner frame with a base part that is mounted in the control center entirely above the flight cabin floor, the frame having front and rear parts and a longitudinal axis extending therein, a guide rod being coupled at the front and rear parts; electrical connectors connected to the housing and operatively connectable to the rudder and brake systems; a pair of pedal assemblies movably coupled to the guide rod and being longitudinally movable relative to the housing between the front and rear positions, the pedal assemblies each have a foot pedal outside and adjacent to opposite sides of the cover. and a mounting member secured to the foot pedal and extending at least partially past the cover, each foot pedal capable of being engaged by an operator, each pedal assembly being independently rotated and being moved longitudinally with respect to the housing; a brake control system in the housing and connected to the pedal assemblies, the brake control system having a first motion sensor operatively coupled to at least a first of the pedal assemblies and connected to at least a first of the electrical connectors connecting the brake system, the first sensor configured to provide a first signal through the first electrical connector to the brake system for actuating the brake system; and a rudder control system in the housing and having a rotary rudder control shaft extending between the rear and front parts of the frame, the rudder control system having a control fitting longitudinally movable along the rudder control shaft. and rotatable with the rudder control shaft, the control accessory being coupled to the guide frame and longitudinally movable with the pedal assemblies relative to the guide element between the front and rear pedal positions, the rudder control system configured to detect rotational movement of the rudder control axis caused by equal and opposite longitudinal movement of the foot pedals and configured to provide a second signal to the rudder system.
    [0012]
    12. Modular rudder and brake control system, according to claim 11, CHARACTERIZED by the fact that it additionally comprises a position adjustment system capable of operating independently of the brake control system and the rudder control system , the position adjustment system being connected to the pedal sets and the guide frame and being adjustable so that the guide frame moves along the guide element to simultaneously move the pedal sets in the same direction to change a position of the pedal assemblies with respect to the frame between the front and back positions.
    [0013]
    13. Modular rudder and brake control system, according to claim 11, CHARACTERIZED by the fact that the guide element and the rudder control shaft are substantially parallel and connected to the front and rear parts of the frame.
    [0014]
    14. Modular rudder and brake control system, according to claim 11, CHARACTERIZED by the fact that the housing, the pedal assemblies, the brake control system, the rudder control system, and the control system Positions define a modular unit detachably mounted above the flight deck floor.
    [0015]
    15. Modular rudder and brake control system, according to claim 14, CHARACTERIZED by the fact that the control center has first and second operator stations, and in that the modular unit is configured to be interchangeably positionable in the first and second operator stations.
    [0016]
    16. Modular rudder and brake control system, according to claim 11, CHARACTERIZED by the fact that the brake control system includes a brake lever that interconnects the first motion sensor and the first of the pedal assemblies, the brake lever and the first of the pedal assemblies being rotatable as a unit with respect to the housing, wherein the brake lever translates movement from the first of the pedal assemblies to the first motion sensor.
    [0017]
    17. Modular rudder and brake control system according to claim 11, CHARACTERIZED by the fact that the rudder control shaft is a grooved shaft and the control fittings slide axially along the grooved shaft, and is rotatable with the splined shaft as a unit, wherein the rotation of the rudder control shaft corresponds to the longitudinal movement of each foot pedal with respect to the housing in equal and opposite directions.
    [0018]
    18. Modular rudder and brake control system, according to claim 11, CHARACTERIZED by the fact that the rudder control system is fully contained in the housing and is operable independently of the brake control system, the control system rudder has a second motion sensor operably attachable to the pedal assemblies and connected to a second of the electrical connectors that connect the rudder system, the second motion sensor configured to detect longitudinal movement of the pedal assemblies and provide a second signal through from the second electrical connector to the rudder system as a function of longitudinal movement of the pedal assembly.
    [0019]
    19. Modular rudder and brake control system for use in an aircraft having a cockpit with a flight deck floor, and having an electric cable control braking system and an electric cable control rudder system, the modular rudder and brake control system being CHARACTERIZED by the fact that it comprises: a housing comprising a frame and a cover over the frame, the frame having a base portion removably attached above the floor of the flight deck without penetrating the floor when the modular rudder and brake control system is operatively connected to the rudder and brake systems, the housing having a guide element; electrical connectors connected to the housing and operatively connected to the rudder and brake systems; a pair of pedal assemblies coupled to the housing, connected to a guide frame movably connected to the guide element, the pedal assemblies and guide frame being movable as a unit between the front and rear pedal positions with respect to the housing, each pedal assembly being rotatable and longitudinally movable with respect to the housing, wherein the pedal assemblies each have a foot pedal and a mounting element, wherein the mounting elements protrude from the sides. opposites of the housing with the cover located between the foot pedals; a brake control system in the housing and connected to the pedal assemblies, the brake control system providing a first signal to the brake system for actuating the brake system; and a rudder control system in the housing and carried by the frame, the rudder control system being connected to the pedal assemblies and being operable independently of the brake control system, the rudder control system having a rudder control shaft rotary and having a control fitting longitudinally movable along the rudder control axis and rotatable with the rudder control axis, the control fitting being coupled to the guide frame and longitudinally movable with the pedal assemblies with respect to the steering element. guide between the front and rear pedal positions, the rudder control system being connected to at least one of the first electrical connectors that connects to the rudder system, the rudder control system detects the longitudinal movement of the pedal assemblies and provides a second signal through the first of the electrical connectors to the rudder system; where the housing, electrical connectors, pedal assemblies, brake control system and rudder control system define a modular component that can be installed and removed from the cockpit as a unit.
    [0020]
    20. Modular rudder and brake control system, according to claim 19, CHARACTERIZED by the fact that it additionally comprises a position adjustment system capable of operating independently of the brake control system and the rudder control system , the position adjustment system being connected to the pedal assemblies and being adjustable to simultaneously move the pedal assemblies in the same direction to change a longitudinal position of the pedal assemblies with respect to the housing.
    [0021]
    21. Modular rudder and brake control system according to claim 20, CHARACTERIZED in that it further comprises an interconnection connected to the rudder control system, the interconnection being connectable to a second rudder control system of a second adjacent modular brake and rudder control system, where the interconnect transfers the longitudinal movement of the pedal sets to the longitudinal movement of the second pedal sets and the second helm control system of the second modular brake and helm control system.
    [0022]
    22. Modular rudder and brake control system, according to claim 19, CHARACTERIZED by the fact that the brake control system is connected to at least one second of the electrical connectors that connect the brake system, the control system The brake switch detects rotational movement of the pedal assembly and provides the first signal through the second electrical connector to the brake system.
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    同族专利:
    公开号 | 公开日
    BR112015010717A2|2020-04-22|
    US20140131523A1|2014-05-15|
    CA2891096C|2017-09-26|
    IL238683D0|2015-06-30|
    IL238683A|2018-12-31|
    US20170174324A1|2017-06-22|
    WO2014075023A1|2014-05-15|
    US10377468B2|2019-08-13|
    CA2891096A1|2014-05-15|
    EP2917102A1|2015-09-16|
    RU2592967C1|2016-07-27|
    EP2917102B1|2016-09-28|
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    法律状态:
    2018-11-21| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-07-14| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-04-13| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-06-08| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 11/11/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201261724815P| true| 2012-11-09|2012-11-09|
    US61/724,815|2012-11-09|
    PCT/US2013/069509|WO2014075023A1|2012-11-09|2013-11-11|Modular, above-the-floor rudder and brake control system|
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