Flight control system and method for aircraft

Abstract

The present invention relates to a flight control system and method for an aircraft. The system includes: a first controller for a first flight control surface; a second controller for controlling a second flight control surface; and a first override system including a mechanical linkage device located between the first controller and the second controller. The first override system is configured so that: (i) while applying a force less than a first threshold amount to the mechanical linkage device, the movement of the first controller causes the second controller to perform a corresponding movement, and vice versa; and (ii) while applying a force greater than the first threshold amount to the mechanical linkage device, the first controller and the second controller move separately. The system also includes a second override system, which is operable to permanently disconnect the mechanical linkage device in response to a force greater than a second threshold amount applied to the mechanical linkage device. The second threshold amount of force is greater than the first threshold amount of force.

Description

Technical Field

[0001] The present disclosure relates generally to a flight control system for an aircraft, and more particularly to a flight control system including an override system that can permanently disconnect two controllers when a jam occurs in the flight control system. Background Art

[0002] Generally speaking, an aircraft includes a flight control system that can be used to control the attitude and flight path of the aircraft. In some cases, a jam may occur in the flight control system, which may damage the flight control system. Summary of the invention

[0003] In one example, a system is described that includes: a first controller configured to control a first flight control surface of an aircraft; a second controller configured to control a second flight control surface of the aircraft; and a first override system that includes a mechanical linkage between the first controller and the second controller. The first override system is configured such that: (i) while the first controller and the second controller apply a force less than a first threshold amount to the mechanical linkage, movement of the first controller causes a corresponding movement of the second controller, and movement of the second controller causes a corresponding movement of the first controller; and (ii) while the first controller and the second controller apply a force greater than the first threshold amount to the mechanical linkage, the first controller and the second controller move apart relative to each other.

[0004] The system also includes a second override system operable to permanently disconnect the mechanical linkage between the first controller and the second controller in response to the first controller and the second controller applying a force to the mechanical linkage that is greater than a second threshold amount of force, the second threshold amount of force being greater than the first threshold amount of force.

[0005] In another example, a method of operating an aircraft is described. The aircraft includes: a first controller configured to control a first flight control surface; a second controller configured to control a second flight control surface; a first override system including a mechanical linkage between the first controller and the second controller; and a second override system. The method includes: applying a first force less than a first threshold amount of force to the mechanical linkage via the first controller and the second controller to cause the first controller to move with the second controller. In response to applying the first force, the method includes actuating the first flight control surface and the second flight control surface.

[0006] Additionally, the method includes applying, by the first controller and the second controller, a second force greater than the first threshold amount of force to the mechanical linkage to move the first controller and the second controller apart relative to each other. In response to applying the second force, the method includes actuating one of the first flight control surface and the second flight control surface. The method also includes applying, by the first controller and the second controller, a third force greater than the second threshold amount of force to the mechanical linkage to disconnect the mechanical linkage between the first controller and the second controller. The second threshold amount of force is greater than the first threshold amount of force.

[0007] The features, functions, and advantages that have been discussed can be achieved independently in various examples or may be combined in yet other examples further details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The novel features believed to be characteristic of the illustrative examples are set forth in the appended claims. However, these illustrative examples and preferred modes of use, as well as further objects and description thereof, will be better understood by reference to the following detailed description of illustrative examples of the present disclosure when read in conjunction with the accompanying drawings, in which:

[0009] Figure 1 A perspective view of an aircraft is shown according to one example.

[0010] Figure 2 A simplified block diagram of a flight control system for an aircraft is shown according to one example.

[0011] Figure 3 A perspective view of a flight control system for an aircraft is shown according to one example.

[0012] Figure 4A A perspective view of a portion of a flight control system in a first state is shown according to an example.

[0013] Figure 4B shows a second state according to an example Figure 4A A perspective view of a portion of a flight control system.

[0014] Figure 5 A flow chart is shown of an example process for operating an aircraft according to one example.

[0015] Figure 6 Shows that it is possible to Figure 5 The described processes are used together with a flowchart of an example process for operating an aircraft.

[0016] Figure 7 Shows that it is possible to Figure 6 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0017] Figure 8 Shows that it is possible to Figure 5 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0018] Fig. 9 Shows that it is possible to Figure 5 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0019] Fig.10 Shows that it is possible to Figure 5 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0020] Fig.11 Shows that it is possible to Figure 5 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0021] Fig.12 Shows that it is possible to Fig.11 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0022] Fig.13 Shows that it is possible to Fig.11 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0023] Fig.14 Shows that it is possible to Figure 5 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft.

[0024] Fig.15 Shows that it is possible to Figure 5 The illustrated process is used in conjunction with a flowchart of an example process for operating an aircraft. DETAILED DESCRIPTION

[0025] The disclosed examples will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all, of the disclosed examples are shown. Indeed, several different examples may be described, and these examples should not be construed as limited to the examples set forth herein. Rather, these examples are described in order to make this disclosure comprehensive and complete, and to fully convey the scope of this disclosure to those skilled in the art.

[0026] As mentioned above, an aircraft typically includes a flight control system that can be used to control the attitude and flight path of the aircraft. In general, the flight control system includes one or more controllers for controlling one or more flight control surfaces of the aircraft. These flight control surfaces can be actuated to adjust the pitch, roll or yaw of the aircraft in flight. For example, these flight control surfaces can include one or more elevators, rudders, ailerons, flaps, spoilers, leading edge flaps, leading edge slats and / or trim tabs.

[0027] In some cases, the flight control system includes a first controller for a first pilot in a cockpit of the aircraft and a second controller for a second pilot in the cockpit. The flight control system can be arranged so that the first controller is connected to the first flight control surface and the second controller is connected to the second flight control surface. In addition, the flight control system can include a mechanical linkage device located between the first controller and the second controller. Under normal operating conditions, the mechanical linkage device can move the first controller and the second controller together. In this way, the mechanical linkage device can provide for the first pilot or the second pilot to move the first flight control surface and the second flight control surface simultaneously under normal operating conditions by moving the respective controllers of the first pilot or the second pilot.

[0028] As a safety precaution, the aircraft may include one or more features for addressing the relatively remote possibility that a jam may occur in the flight control system. As used herein, the term "jam" refers to a condition in which the movement of one or more components of the flight control system is impaired. If a first controller or a second controller jams, both the first controller and the second controller may be damaged due to the mechanical linkage between the first controller and the second controller.

[0029] In order to provide controllability to the aircraft in the event that one control has become stuck, the aircraft may include a reset override system. The reset override system may cause the mechanical linkage to temporarily decouple the first control from the second control to allow the first control to move independently of the second control. Once separated, the unstuck control is able to actuate the flight control surface to which it is coupled. Thus, although a jam may damage one flight control surface, the aircraft may still be able to be controlled using the remaining flight control surfaces.

[0030] To temporarily decouple the first and second controls, the pilot of the unstuck control provides an input force to the unstuck control that is sufficient to overcome the breakaway force threshold for resetting the override system. However, the pilot of the unstuck control must maintain this input force as long as the first and second controls are in different positions (e.g., for the duration of flight after the jam occurs). If the pilot must maintain this input force for a long period of time, this can result in over-application and increased pilot workload.

[0031] The example systems and methods described herein can advantageously address at least some of the deficiencies of existing flight control systems. In these examples, the flight control system includes a first controller for controlling a first flight control surface, a second controller for controlling a second flight control surface, a first override system, and a second override system. The first override system can be a reset override system. In this way, the first override system includes a mechanical linkage device between the first controller and the second controller. While the first controller and the second controller apply a force less than a first threshold amount to the mechanical linkage device, the movement of the first controller causes the second controller to perform a corresponding movement, and the movement of the second controller causes the first controller to perform a corresponding movement. When the first controller and the second controller apply a force greater than the first threshold amount to the mechanical linkage device, the first controller and the second controller move separately relative to each other.

[0032] The second override system is operable to permanently disconnect the mechanical linkage between the first controller and the second controller in response to a force greater than a second threshold amount of force applied to the mechanical linkage by the first controller and the second controller. In these examples, the second threshold amount of force is greater than the first threshold amount of force. By "permanently disconnected" is meant that the connection between the first controller and the second controller is physically broken permanently, such that after the permanent disconnection, movement of the first controller does not result in corresponding movement of the second controller, and vice versa.

[0033] In this arrangement, when a jam occurs in one of the controls, the pilot is first able to provide an input force to the unjammed control, which causes the first and second controls to apply a force to the mechanical linkage that is greater than a first threshold amount of force and less than a second threshold amount of force. As long as the pilot maintains the input force, the first override system temporarily decouples the first control from the second control, which allows the pilot to control the aircraft using the flight control surfaces coupled to the unjammed control.

[0034] If the pilot determines that the input force may need to be maintained for a relatively long period of time, and that doing so is not desirable, the pilot can actuate the second override system to permanently disconnect the mechanical linkage (i.e., permanently disconnect the stuck controller from the unstuck controller). In detail, the pilot can increase the input force so that the first controller and the second controller apply a force greater than a second threshold amount of force to the mechanical linkage. Once the mechanical linkage is permanently disconnected, the stuck controller can remain stuck. However, the unstuck controller can operate with a relatively low input force to control the flight control surface coupled to the unstuck controller.

[0035] The disclosed system and method can thus allow the pilot to select whether it is advantageous to disconnect the first controller and the second controller while maintaining the benefits of resetting the override system. Thus, the system and method of operating an aircraft can enhance the mechanics of the flight control system and / or enhance operational safety associated with the flight control system.

[0036] Now refer to Figure 1 , depicts a perspective view of an aircraft 100 according to an example. Figure 1 In FIG. 1 , the aircraft 100 is a fixed-wing aircraft. Figure 1 , the aircraft 100 includes a fuselage 110 extending in a longitudinal direction 112 and a pair of wings 114 extending from the fuselage 110 in a transverse direction relative to the longitudinal direction 112. Although the aircraft 100 is depicted as Figure 1 1. The fixed-wing aircraft in FIG. 1 is a fixed-wing aircraft, but in other examples, the aircraft 100 may be a helicopter, a light aircraft and / or a spacecraft. More specifically, the aircraft 100 may be any aircraft that can travel by air.

[0037] like Figure 1 As shown, the aircraft 100 includes a plurality of flight control surfaces 116 that can be actuated to adjust the pitch, roll, and / or yaw of the aircraft 100 during flight. For example, the flight control surfaces 116 may include one or more elevators, rudders, ailerons, flaps, spoilers, leading edge flaps, leading edge slats, and / or trim tabs. Figure 1 For example, flight control surfaces 116 include a plurality of spoilers 118 and ailerons 120 on each wing 114 , a pair of elevators 122 on a horizontal stabilizer 124 of aircraft 100 , and a rudder 126 on a vertical stabilizer 128 of aircraft 100 .

[0038] Now refer to Figure 2 , depicts a simplified block diagram of a flight control system 230 according to one example. Figure 2As shown, the flight control system 230 includes a plurality of flight control surfaces 216A-216B, a first controller 232, a second controller 234, a first override system 236, and a second override system 238. Figure 2 In the embodiment, the flight control surfaces 216A-216B include a first flight control surface 216A and a second flight control surface 216B. As described above, the flight control surfaces 216A-216B may include, for example, one or more elevators, rudders, ailerons, flaps, spoilers, leading edge flaps, leading edge slats, and / or trim tabs.

[0039] Also like Figure 2 As shown, the first flight control surface 216A is connected to the first controller 232 by the first control path 240, and the second flight control surface 216B is connected to the second controller 234 by the second control path 242. The first control path 240 and the second control path 242 can provide corresponding mechanical and / or fly-by-wire connections between the first controller 232 and the first flight control surface 216 and between the second controller 234 and the second flight control surface 216B. In other words, the flight control system 230 can provide reversible and / or irreversible connections between the first controller 232 and the first flight control surface 216A and between the second controller 234 and the second flight control surface 216B. Thus, in this embodiment, the first controller 232 can control the first flight control surface 216A, and the second controller 234 can control the second flight control surface 216B.

[0040] In these examples, first controller 232 may include a first control column, a first control stick, a first wheel, and / or first rudder pedals operable by a first pilot in a cockpit of aircraft 100 to control first flight control surface 216A. Similarly, second controller 234 may include a second control column, a second control stick, a second wheel, and / or a second plurality of pedals operable by a second pilot in a cockpit to control second flight control surface 216B.

[0041] like Figure 2As shown, the first override system 236 includes a mechanical linkage 244 located between the first controller 232 and the second controller 234. The first override system 236 is a reset override system. For example, the mechanical linkage 244 may include a load limiter 246 such as, for example, a pogo or a pungee. More generally, the load limiter 246 may provide a mechanism for (i) coupling the first controller 232 and the second controller 234 when the first controller 232 and the second controller 234 apply a force less than a first threshold amount of force to the mechanical linkage 244; and (ii) temporarily separating the first controller 232 and the second controller 234 when the first controller 232 and the second controller 234 apply a force greater than a first threshold amount of force to the mechanical linkage 244. “Temporarily disengaged” means that the mechanical linkage 244 restores the connection between the first controller 232 and the second controller 234 when the force applied to the mechanical linkage 244 is reduced to below a first threshold amount of force (as long as the mechanical linkage 244 has not been permanently disconnected by the second override system 238, as described below).

[0042] Thus, the first override system 236 is configured such that: (i) when the first controller 232 and the second controller 234 apply a force less than a first threshold amount to the mechanical linkage device 244, movement of the first controller 232 causes the second controller 234 to perform a corresponding movement, and movement of the second controller 234 causes the first controller 232 to perform a corresponding movement; and (ii) when the first controller 232 and the second controller 234 apply a force greater than the first threshold amount to the mechanical linkage device 244, the first controller 232 and the second controller 234 move separately from each other.

[0043] Thus, when a jam occurs along first control path 240 and impairs operation of first controller 232, first override system 236 allows actuation of second flight control surface 216B using second controller 234. Similarly, when a jam occurs along second control path 242 and impairs operation of second controller 234, first override system 236 allows actuation of first flight control surface 216A using first controller 232. Thus, even though a jam may impair operation of one of first flight control surface 216A and second flight control surface 216B, aircraft 100 can still be safely controlled using the other of first flight control surface 216A and second flight control surface 216B.

[0044] For example, in an implementation where the first controller 232 and the second controller 234 are wheels, in one example, the first threshold amount of force may be a value between approximately 35 pounds and approximately 50 pounds, and in another example, may be a value between approximately 40 pounds and approximately 45 pounds. For another example, in one example, in an implementation where the first controller 232 and the second controller 234 are columns, the first threshold amount of force may be a value between approximately 55 pounds and approximately 75 pounds, and in another example, may be a value between approximately 60 pounds and approximately 70 pounds.

[0045] In another example, the first threshold amount of force may be an amount that is unlikely to actuate the first override system 236 under certain flight conditions, such as when the aircraft 100 is stalled. This can advantageously reduce (or prevent) accidental separation of the first controller 232 and the second controller 234. The term "approximately" with respect to a reference quantity or measurement value means that the referenced feature, parameter, or value need not be achieved exactly. Rather, deviations or variations (including, for example, tolerances, measurement errors, measurement precision limitations, and other factors known to those skilled in the art) may occur in these quantities, but these quantities do not preclude the effects that these features are intended to provide.

[0046] As described above, it may be desirable to permanently disconnect the mechanical linkage 244, thereby allowing the first controller 232 and the second controller 234 to move apart from each other with a reduced input force for the remainder of the flight. The second override system 238 is operable to permanently disconnect the mechanical linkage 244 between the first controller 232 and the second controller 234 in response to the first controller 232 and the second controller 234 applying a force greater than a second threshold amount to the mechanical linkage 244. After the mechanical linkage 244 is disconnected by the second override system 238, the first controller 232 and the second controller 234 are able to move apart from each other in response to any force (e.g., a force less than the first threshold amount of force applied to the mechanical linkage 244 by the first controller 232 and the second controller 234).

[0047] In some examples, the second override system 238 can be a device located external to the mechanical linkage 244. For example, in some examples, the second override system 238 can include a bolt cutter, a wire cutter, and / or a cable cutter that can be actuated to physically break or sever the mechanical linkage 244 between the first controller 232 and the second controller 234. In other examples, the mechanical linkage 244 can include the second override system 238. For example, in some examples, the second override system 238 can include a shear pin, a solenoid-actuated coupler, and / or a frangible nut along the mechanical linkage 244 between the first controller 232 and the second controller 234.

[0048] Generally, the second threshold amount of force is greater than the first threshold amount of force. For example, in one example, the second threshold amount of force may be a value greater than or equal to approximately 75 pounds (e.g., for an implementation where the first controller 232 and the second controller 234 are wheels). In another example, the second threshold amount of force may be greater than or equal to approximately 120 pounds (e.g., for an implementation where the first controller 232 and the second controller 234 are sticks). In another example, the second threshold amount of force may be an amount of force that is between approximately 30% and approximately 100% greater than the first threshold amount of force.

[0049] Additionally, in some examples, the second threshold amount of force may be an amount of force that reduces (or prevents) an accidental disconnection of mechanical linkage 244 between first controller 232 and second controller 234. This is beneficial because once second override system 238 disconnects mechanical linkage 244, the connection between first controller 232 and second controller 234 may be restored during flight. Conversely, mechanical linkage 244 may be restored after flight by repairing and / or replacing mechanical linkage 244.

[0050] Now refer to Figure 3 , Figure 3 is a perspective view of components of a flight control system 230 according to one example. Figure 3 As shown, first controller 232 is coupled to first flight control surface 216A via first control path 240, and second controller 234 is coupled to second flight control surface 216B. Figure 3 , first controller 232 is a first wheel extending from cockpit floor 348, and second controller 234 is a first wheel extending from cockpit floor 348. As described above, in other examples, first controller 232 and second controller 234 may additionally or alternatively include joysticks and / or rudder pedals.

[0051] In addition, Figure 3 In the embodiment, first flight control surface 216A is a first elevator, and second flight control surface 216B is a second elevator. In other examples, first flight control surface 216A and second flight control surface 216B may additionally or alternatively include one or more rudders, ailerons, flaps, spoilers, leading edge flaps, leading edge slats, and / or trim tabs.

[0052] like Figure 3 As shown, the first override system 236 includes a mechanical linkage 244 between the first controller 232 and the second controller 234. Figure 3 , the second override system 238 is a shear pin along the mechanical linkage 244 at the first override system 236 .

[0053] In this arrangement, the first pilot and / or the second pilot may fly aircraft 100 under normal operating conditions when first controller 232 and second controller 234 are not stuck. Under such conditions, either pilot may apply an input force to first controller 232 or second controller 234, which causes first controller 232 and second controller 234 to apply a first force less than a first threshold amount of force to mechanical linkage 244. Under these conditions, the input force causes first controller 232 to move with second controller 234 and simultaneously actuate first flight control surface 216A and second flight control surface 216B.

[0054] When one of first control 232 and second control 234 becomes stuck, the first pilot and / or the second pilot may detect the sticking by sensing an increase in resistance to movement of first control 232 and / or second control 234. As described above, the sticking may be along at least one of: (i) first control path 240 between first control 232 and second control surface 216A; or (ii) second control path 240 between second control 234 and second control surface 216B. In either case, the input force used to move first control 232 and second control 234 is increased due to mechanical linkage 244 between first control 232 and second control 234.

[0055] In response to detecting a jam, the first pilot or the second pilot may apply an input force to the unjammed controller, which causes first controller 232 and second controller 234 to apply a second force greater than the first threshold amount of force to mechanical linkage 244. This causes first override system 236 to temporarily decouple first controller 232 and second controller 234. Thus, the second force causes first controller 232 and second controller 234 to move apart relative to each other, thereby actuating one of first flight control surface 216A and second flight control surface 216B (i.e., flight control surface 216A coupled to unjammed controller 232, 234).

[0056] In order to reduce the input force used to control aircraft 100, first pilot and / or second pilot may decide to actuate second override system 238. In this case, first pilot or second pilot may apply an input force to an unstuck controller of first controller 232 and second controller 234, which causes first controller 232 and second controller 234 to apply a third force greater than the second threshold amount of force to mechanical linkage 244. This causes second override system 238 to disconnect mechanical linkage 244 between first controller 232 and second controller 234.

[0057] After applying the third force to disconnect mechanical linkage 244, the first pilot or the second pilot can move first controller 232 separately from second controller 234 with a reduced input force. Specifically, the first pilot or the second pilot moves first controller 232 separately from second controller 234 so that one of first flight control surface 216A and second flight control surface 216B can be actuated even if first controller 232 and second controller 234 apply a force to mechanical linkage 244 that is less than the first threshold amount.

[0058] Figure 4A and Figure 4B Depicted are perspective views of a portion of the flight control system 230 before and after the second override system 238 is actuated to disconnect the mechanical linkage 244. Figure 4A As shown, the first controller 232 is coupled to the second controller 234 before the second override system 238 disconnects the mechanical linkage 244. Thus, in this first state, (i) while the first controller 232 and the second controller 234 apply a force less than a first threshold amount to the mechanical linkage 244, movement of the first controller 232 causes corresponding movement of the second controller 234, and movement of the second controller 234 causes corresponding movement of the first controller 232, and (ii) while the first controller 232 and the second controller 234 apply a force greater than the first threshold amount to the mechanical linkage 244, the first controller 232 and the second controller 234 move apart relative to each other.

[0059] like Figure 4B As shown, the first controller 232 and the second controller 234 move independently of each other after the second override system 238 disconnects the mechanical linkage 244. That is, the mechanical linkage 244 is physically broken so that moving the first controller 232 does not cause the second controller 234 to make a corresponding movement, and moving the second controller 234 does not cause the first controller 232 to make a corresponding movement.

[0060] Now refer to Figure 5 , a flow chart of a process 500 for operating an aircraft according to one example is shown. The aircraft includes a first controller configured to control a first flight control surface, a teach controller configured to control a second flight control surface, a first override system including a mechanical linkage between the first controller and the second controller, and a second override system.

[0061] like Figure 5 As shown, at block 510 , process 500 includes applying, by a first controller and a second controller, a first force less than a first threshold amount of force to a mechanical linkage to cause the first controller to move with the second controller.

[0062] In response to applying the first force at block 510 , process 500 includes actuating the first flight control surface and the second flight control surface at block 512 .

[0063] At block 514 , process 500 includes applying, by the first controller and the second controller, a second force greater than a first threshold amount of force to the mechanical linkage to move the first controller and the second controller apart relative to each other.

[0064] In response to applying the second force at block 516 , process 500 includes actuating one of the first flight control surface and the second flight control surface at block 516 .

[0065] At block 518, process 500 includes applying, by the first controller and the second controller, a third force greater than a second threshold amount of force to the mechanical linkage to disconnect the mechanical linkage between the first controller and the second controller. The second threshold amount of force is greater than the first threshold amount of force.

[0066] Figures 6 to 15 Additional aspects of process 500 according to other examples are described. Figure 6 As shown, process 500 also includes moving the first controller apart from the second controller at block 520 after applying a third force to disconnect the mechanical linkage at block 518 .

[0067] like Figure 7 As shown, moving the first controller apart from the second controller at block 520 may include applying a force less than a first threshold amount to the mechanical linkage at block 522 .

[0068] like Figure 8 As shown, process 500 may also include, at block 524, detecting a jam along at least one of: a first control path between the first controller and the first control surface; or (ii) a second control path between the second controller and the second control surface. Figure 8 As shown, applying the second force at block 514 may be performed in response to detecting a sticking at block 524 .

[0069] like Fig. 9 As shown, applying the third force to disconnect the mechanical linkage at block 518 may include actuating a shear pin to disconnect the mechanical linkage 526 at block 526 .

[0070] like Fig.10 As shown, applying the third force to disconnect the mechanical linkage at block 518 may include actuating at block 528 at least one of the group consisting of: a bolt cutter, a wire cutter, a cable cutter, a solenoid-actuated coupling, and a frangible nut.

[0071] like Fig.11 As shown, applying the first force at block 510 may include moving the first controller to cause a corresponding movement of the second controller at block 530 .

[0072] like Fig.12 As shown, moving the first controller at block 530 may include moving a first wheel in the cockpit of the aircraft to cause a corresponding movement of a second wheel in the cockpit at block 532 .

[0073] like Fig.13 As shown, moving the first control at block 530 may include moving a first rudder pedal in a cockpit of the aircraft at block 534 to cause a corresponding movement of a second rudder pedal in the cockpit.

[0074] like Fig.14 As shown, actuating the first flight control surface and the second flight control surface at block 512 may include actuating a first aileron of the aircraft and a second aileron of the aircraft at block 536 .

[0075] like Fig.15 As shown, actuating the first flight control surface and the second flight control surface at block 512 may include actuating a first elevator of the aircraft and a second elevator of the aircraft at block 538 .

[0076] Figures 6 to 15 One or more modules, segments or parts of the block diagram shown in the program code are represented, and the program code includes one or more instructions that can be executed by a processor to realize a specific logical function or step in the process. The program code can be stored on any type of computer-readable medium or data storage (such as, for example, a storage device (including a disk or hard disk drive)). In addition, the program code can be encoded on a computer-readable storage medium in a machine-readable format or encoded when other non-temporary contacts or products are contacted. Computer-readable media include non-temporary computer-readable media or memory, such as computer-readable media that store data in a short period of time, such as register memory, processor cache and random access memory (RAM). Computer-readable media also include non-temporary media, such as secondary or permanent long-term memory, such as read-only memory (ROM), optical disk or disk, optical disk read-only memory (CD-ROM). Computer-readable media can also be any other volatile or non-volatile storage system. Computer-readable media can be considered to be, for example, tangible computer-readable media.

[0077] Additionally, this disclosure includes examples according to the following clauses:

[0078] Clause 1. A system 230, comprising:

[0079] a first controller 232 configured to control a first flight control surface 216A of the aircraft 100;

[0080] a second controller 234 configured to control a second flight control surface 216B of the aircraft 100;

[0081] A first override system 236 includes a mechanical linkage 244 between the first controller 232 and the second controller 234, wherein the first override system 236 is configured such that:

[0082] (i) movement of the first controller 232 causes corresponding movement of the second controller 234, and movement of the second controller 234 causes corresponding movement of the first controller 232, while the first controller 232 and the second controller 234 apply a force less than a first threshold amount to the mechanical linkage 244; and

[0083] (ii) the first controller 232 and the second controller 234 move apart relative to each other while the first controller 232 and the second controller 234 apply a force greater than the first threshold amount to the mechanical linkage 244; and

[0084] a second override system 238 operable to permanently disconnect the mechanical linkage 244 between the first controller 232 and the second controller 234 in response to the first controller 232 and the second controller 234 applying a force to the mechanical linkage 244 that is greater than a second threshold amount; and

[0085] Wherein the second threshold amount of force is greater than the first threshold amount of force.

[0086] Clause 2. The system of clause 1, wherein the second override system 238 comprises a shear pin configured to permanently disconnect the mechanical linkage 244.

[0087] Clause 3. The system of clause 1 or 2, wherein the second override system 238 comprises at least one of the group consisting of: a bolt cutter, a wire cutter, a cable cutter, a solenoid-actuated coupling, and a frangible nut.

[0088] Clause 4. The system of clause 1 or 2, wherein the first override system 236 comprises a load limiter 246 .

[0089] Clause 5. The system of clause 1 or 2, wherein the first controller 232 comprises a first rudder pedal located in a cockpit of the aircraft 100 , and the second controller 234 comprises a second rudder pedal located in the cockpit of the aircraft 100 .

[0090] Clause 6. The system of clause 1 or 2, wherein the first controller 232 comprises a first wheel located in a cockpit of the aircraft 100 , and the second controller 234 comprises a second wheel located in a cockpit of the aircraft 100 .

[0091] Clause 7. The system of clause 1 or 2, wherein the first flight control surface 216A comprises a first aileron 120 of the aircraft 100 , and the second flight control surface 216B comprises a second aileron 120 of the aircraft 100 .

[0092] Clause 8. The system of clause 1 or 2, wherein the first flight control surface 216A comprises a first elevator 122 of the aircraft 100 , and the second flight control surface 216B comprises a second elevator 122 of the aircraft 100 .

[0093] Clause 9. A system according to clause 1 or 2, wherein, after the mechanical linkage 244 is disconnected by the second override system 238, the first controller 232 and the second controller 234 are configured to move separately from each other in response to a force less than a first threshold amount applied to the mechanical linkage 244 by the first controller 232 and the second controller 234.

[0094] Clause 10. A method of operating an aircraft 100, wherein the aircraft 100 includes: a first controller 232, the first controller 232 configured to control a first flight control surface 216A; a second controller 234, the second controller 234 configured to control a second flight control surface 216B; a first override system 236, the first override system 236 including a mechanical linkage 244 located between the first controller 232 and the second controller 234; and a second override system 238, the method comprising:

[0095] applying a first force less than a first threshold amount of force to the mechanical linkage 244 by the first controller 232 and the second controller 234 to move the first controller 232 and the second controller 234 together;

[0096] actuating the first flight control surface 216A and the second flight control surface 216B in response to applying the first force;

[0097] applying a second force greater than the first threshold amount of force to the mechanical linkage 244 by the first controller 232 and the second controller 234 to move the first controller 232 and the second controller 234 apart from each other;

[0098] In response to applying the second force, actuating one of the first flight control surface 216A and the second flight control surface 216B; and

[0099] applying a third force greater than a second threshold amount of force to the mechanical linkage 244 through the first controller 232 and the second controller 234 to disconnect the mechanical linkage 244 between the first controller 232 and the second controller 234,

[0100] Wherein the second threshold amount of force is greater than the first threshold amount of force.

[0101] Clause 11. The method according to clause 10, further comprising:

[0102] After applying a third force to disconnect the mechanical linkage 244 , the first controller 232 is moved separately from the second controller 234 .

[0103] Clause 12. The method of clause 11, wherein moving the first controller 232 apart from the second controller 234 comprises applying a force to the mechanical linkage 244 that is less than a first threshold amount.

[0104] Clause 13. The method of clause 10 or 11, further comprising detecting a jam along at least one of: (i) a first control path 240 between the first controller 232 and the first control surface; and (ii) a second control path 242 between the second controller 234 and the second control surface,

[0105] The second force is applied in response to detecting the sticking.

[0106] Clause 14. The method of claim 10 or 11, wherein applying a third force to disconnect the mechanical linkage 244 comprises actuating a shear pin to disconnect the mechanical linkage 244.

[0107] Clause 15. The method of clause 10 or 11, wherein applying the third force to disconnect the mechanical linkage 244 comprises actuating at least one of the group consisting of: a bolt cutter, a wire cutter, a cable cutter, a solenoid-actuated coupling, and a frangible nut.

[0108] Clause 16. The method of clause 10 or 11, wherein applying a first force comprises moving the first controller 232 to cause a corresponding movement of the second controller (234).

[0109] Clause 17. The method of clause 16, wherein moving the first controller 232 comprises moving a first wheel in a cockpit of the aircraft 100 to cause a corresponding movement of a second wheel in the cockpit.

[0110] Clause 18. The method of clause 16, wherein moving the first controller 232 comprises moving a first rudder pedal in a cockpit of the aircraft 100 to cause a corresponding movement of a second rudder pedal in the cockpit.

[0111] Clause 19. The method of clause 10 or 11, wherein actuating the first flight control surface 216A and the second flight control surface 216B comprises actuating a first aileron 120 of the aircraft 100 and a second aileron 120 of the aircraft 100 .

[0112] Clause 20. The method of clause 10 or 11, wherein actuating the first flight control surface 216A and the second flight control surface 216B comprises actuating a first elevator 122 of the aircraft 100 and a second elevator 122 of the aircraft 100 .

[0113] In some cases, components of the devices and / or systems described herein are configured to perform some functions, such that these components are actually constructed and structured (using hardware and / or software) to achieve these performances. Example configurations thus include one or more processors that execute instructions to cause the system to perform these functions. Similarly, components of the devices and / or systems are configured to be arranged to, suitable for, capable of, or adapted to perform these functions, such as when operating in a specific manner.

[0114] Descriptions of different advantageous arrangements have been provided for purposes of illustration and description, and are not intended to be exhaustive or limited to examples of the disclosed form. Many modifications and variations will be apparent to those skilled in the art. In addition, different advantageous examples may describe different advantages compared to other advantageous examples. The selected example or examples are selected and described to illustrate the principles and practical applications of these examples, and to enable those skilled in the art to understand that the present disclosure for various examples has various variations suitable for the specific applications contemplated.

Claims

1. A flight control system (230), the flight control system (230) comprising: a first controller (232) configured to control a first flight control surface (216A) of the aircraft (100); a second controller (234) configured to control a second flight control surface (216B) of the aircraft (100); A first override system (236) comprising a mechanical linkage (244) between the first controller (232) and the second controller (234), wherein the first override system (236) is configured such that: (i) while the first controller (232) and the second controller (234) apply a force less than a first threshold amount to the mechanical linkage (244), movement of the first controller (232) causes corresponding movement of the second controller (234), and movement of the second controller (234) causes corresponding movement of the first controller (232); and (ii) the first controller (232) and the second controller (234) move apart relative to each other while the first controller (232) and the second controller (234) apply a force greater than the first threshold amount to the mechanical linkage (244); as well as a second override system (238) operable to permanently physically disconnect a mechanical linkage (244) between the first controller (232) and the second controller (234) in response to the first controller (232) and the second controller (234) applying a force greater than a second threshold amount to the mechanical linkage (244); and wherein the second threshold amount of force is greater than the first threshold amount of force, and wherein, after the mechanical linkage (244) is disconnected by the second override system (238), the first controller (232) and the second controller (234) are configured to move apart relative to each other in response to a force less than a first threshold amount applied to the mechanical linkage (244) by the first controller (232) and the second controller (234).

2. The flight control system according to claim 1, wherein: The second override system (238) includes a shear pin configured to permanently disconnect the mechanical linkage (244).

3. The flight control system according to claim 1 or 2, wherein: The second override system (238) includes at least one of the group consisting of: a bolt cutter, a wire cutter, a cable cutter, a solenoid actuated coupling, and a frangible nut.

4. The flight control system according to claim 1 or 2, wherein: The first override system (236) includes a load limiter (246).

5. The flight control system according to claim 1 or 2, wherein: The first controller (232) includes a first rudder pedal located in a cockpit of the aircraft (100), and the second controller (234) includes a second rudder pedal located in the cockpit of the aircraft (100).

6. The flight control system according to claim 1 or 2, wherein: The first controller (232) includes a first wheel located in a cockpit of the aircraft (100), and the second controller (234) includes a second wheel located in the cockpit of the aircraft (100).

7. The flight control system according to claim 1 or 2, wherein: The first flight control surface (216A) comprises a first aileron (120) of the aircraft (100), and the second flight control surface (216B) comprises a second aileron (120) of the aircraft (100).

8. The flight control system according to claim 1 or 2, wherein: The first flight control surface (216A) comprises a first elevator (122) of the aircraft (100), and the second flight control surface (216B) comprises a second elevator (122) of the aircraft (100).

9. A method of operating an aircraft (100), wherein the aircraft (100) comprises: a first controller (232) configured to control a first flight control surface (216A); A second controller (234) configured to control a second flight control surface (216B); a first override system (236) including a mechanical linkage (244) between the first controller (232) and the second controller (234); and a second override system (238), the method comprising: applying a first force less than a first threshold amount of force to the mechanical linkage (244) via the first controller (232) and the second controller (234) so ​​that the first override system (236) causes the first controller (232) to move with the second controller (234); actuating the first flight control surface (216A) and the second flight control surface (216B) in response to applying the first force; applying a second force greater than the first threshold amount of force to the mechanical linkage (244) via the first controller (232) and the second controller (234) so ​​that the first override system (236) causes the first controller (232) and the second controller (234) to move apart relative to each other; actuating one of the first flight control surface (216A) and the second flight control surface (216B) in response to applying the second force; applying a third force greater than a second threshold amount of force to the mechanical linkage (244) via the first controller (232) and the second controller (234) so ​​that the second override system (238) permanently physically disconnects the mechanical linkage (244) between the first controller (232) and the second controller (234); and The first controller (232) and the second controller (234) move apart relative to each other in response to a force less than a first threshold amount applied to the mechanical linkage (244) by the first controller (232) and the second controller (234) after the mechanical linkage (244) is disconnected by the second override system (238), Wherein the second threshold amount of force is greater than the first threshold amount of force.

10. The method of claim 9, further comprising detecting a jam along at least one of: (i) a first control path (240) between the first controller (232) and the first flight control surface; and (ii) a second control path (242) between the second controller (234) and the second flight control surface, The second force is applied in response to detecting the sticking.

11. The method according to claim 9 or 10, wherein: Applying a third force to disconnect the mechanical linkage (244) includes actuating a shear pin to disconnect the mechanical linkage (244).

12. The method according to claim 9 or 10, wherein: Moving the first controller (232) includes moving a first rudder pedal in a cockpit of the aircraft (100) to cause a corresponding movement of a second rudder pedal in the cockpit.

13. The method according to claim 9 or 10, wherein: Actuating the first flight control surface (216A) and the second flight control surface (216B) includes actuating a first aileron (120) of the aircraft (100) and a second aileron (120) of the aircraft (100).

14. The method according to claim 9 or 10, wherein: Actuating the first flight control surface (216A) and the second flight control surface (216B) includes actuating a first elevator (122) of the aircraft (100) and a second elevator (122) of the aircraft (100).

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