JPH02500661A - Quick connection cyclic control rod for co-pilot - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] name of invention Co-pilot control rod technology for quick connection The present invention provides an aircraft flight control system that can be quickly reconnected without sticking. Concerning free co-pilot operation.

Background of the invention In dual-control aircraft that utilize mechanical linkages, the co-pilot's control rod or The control stick is attached to the pilot's control stick, and the vertical bars on both sides are parallel to each other. It moves to ↓ sea urchin. Dual controls allow either pilot or co-pilot to fly This allows full control of the aircraft to be controlled at all times.

Some aircraft with dual controls, such as helicopters and military aircraft, have some flight It is advantageous to disengage the co-pilot's controls from the pilot's controls during the flight phase. Ru. For example, when the first officer is not actively flying the aircraft, this first officer perform other tasks such as navigation, radar operations, and computer system operations. be able to. While the co-pilot is performing these other tasks, If an unexpected shock or pressure is applied to the rod, it may cause undesirable damage to the aircraft control system. may result in unsafe input. This problem affects flight safety Since then, the co-pilot's control rod can now be disengaged from the aircraft control system. It is.

Disengageable copilot exit designed for convenience and safety. Edge vertical bars may be used when re-engaging these control bars is slow or difficult; A safety hazard may occur if the control rod becomes stuck during reconnection to the aircraft control system. Harmful. Disengage the co-pilot's control rods and remove them from the control rods while the aircraft is in flight. If there is a malfunction in the pilot interconnect (i.e. the pilot), the co-pilot will be unable to fly again. Requires quick reconnection of the co-pilot's control rod to be able to control the aircraft.

The current co-pilot chime vertical bars that can be disengaged are designed to prevent re-engagement of these control bars. Difficult or slow, or difficult and slow, and these control rods are co-pilots. sticks during reconnection if the control rod attempts to apply force prior to its full connection. I feel like I'm not getting enough satisfaction. Engagement is a slight side effect of sushi. The control chimney vertical bar carries a spring load into the socket at the bottom of a pot-shaped or inverted conical stopper. Utilize added balls or studs. These control rods overcome the force of the spring. Engage by removing the ball or stud from the socket in the bowl-shaped bottom. is removed. However, in the opposite direction of the force applied by the co-pilot through the control bar, If force is applied to the co-pilot's vertical bar, reconnection cannot be performed. Furthermore, a bowl-shaped stopper The receiver secures the ball or stud and prevents reinsertion of the ball into the socket of the stopper receiver. Particularly suitable for capturing dirt and foreign objects.

In other words, an engagement that can quickly reconnect to the aircraft control system is necessary for the co-pilot. The necessity of vertical chimney bars was confirmed. This kind of control is also sufficient. Before being connected to the In addition, the co-pilot must not allow any other foreign matter to accumulate or accumulate on the control rod. Even if a force opposite to the force applied through the vertical chime vertical bars is applied, it will not become stuck during reconnection. must not.

Summary of the invention The present invention provides a co-pilot quick connect system for dual-piloted aircraft. The iclick control stick is on the control stick for that purpose. co-pilot The control rods are easily disengaged from the aircraft control system and can be quickly disengaged without becoming stuck. It is ready to be reconnected.

The present invention provides a co-pilot ledge that is releasably coupled to a pivot assembly of a control rod base. It's on the vertical bar. The lower portion of this control rod is attached to a gimbal b mounted within the support assembly. It is joined by earing. The two prongs of this control rod, the gimbal member, and the pivot A single shaft extends through the single ball bearing of the kit assembly. Pilot Pibo When connected to a pivot assembly, the control rod and pivot assembly shall be one unit. The gimbal member can be pivoted to the left and right of the gimbal member and to the front and back of the axis. This control stick control the rolling and pitching of other aircraft by such movements.

The pivot assembly is located below the control rod. A star that extends upward along the front part along the axis of the s part. It is equipped with a pad. This stud is a conical or bowl-shaped stud attached to the control rod. Fits into the socket at the front upper end of the housing or stopper. The long part of this housing is slidably mounted within the sleeve of the control rod. The lever assembly is attached to the control rod. It is pivotably mounted and is attached to the stopper holder. By pivoting the lever assembly, Push and move the housing in a forward and upward direction within the control rod sleeve. lift the ring off the pivot assembly stud. This lever assembly The end furthest from the end attached to the Ussing can be pivoted to fit under the co-pilot's seat. The hook should be engaged with a hitch, and the lock/release hook should be fixed with gold. I can do it. This hook is caused by the engagement of the lever assembly with the tool, and the socket pivots. lock the control rod in the central fixed position. Miscellaneous Pivot assembly connected to the vertical pilot's control rod and aircraft control system by a link mechanism around the single ball bearing without interference from the misengaged co-pilot chime vertical bar. Pivot without restraint. The open bottom edge of the housing encloses the stand and pivots Limits the movement of the stand when the seat assembly moves without regard to the disengaged control rod. Define the boundaries.

The co-pilot's control rod can be locked/released to the aircraft control system by releasing it. Reconnect and allow the lever assembly to pivot back to its normal position. It's Nishide. The housing is spring-loaded within the sleeve of the control rod and is located at the bottom rearward. It should be pressed against the stud of the cut assembly. Inside the conical shape of the housing Align this housing with the stand so that the studs fit into the sockets of the housing. to re-engage the cut.

Since the housing of the present invention is opened downward, this housing can be attached to the control rod. Does not form a trap that traps dust or foreign objects that could cause the controls to stick during reconnection . The shape of this housing also allows for all movement of the stud during control rod disconnection. to ensure that the housing always confines the stud during control rod reconnection. It's Nishide. In addition, co-pilot input to the control rod during recoupling is possible by socketing the stand. The force of the housing on the studs may cause the aircraft control system to be damaged even before it is reinserted into the have at least a partial effect on the

Brief description of the drawing In order to explain the invention and further advantages thereof in more detail, reference is made to the accompanying drawings. A preferred embodiment will be described below. FIG. FIG. 3 is an exploded perspective view of the main parts of the control rod.

FIG. 2 is a partial side view with a portion of the control rod shown in FIG. 1 cut away.

Figure 3 is a bottom view of the housing of the present invention, taken along line 3-3 in Figure 2 and in the direction of the arrow. be.

Description of preferred embodiments Like reference numerals in the drawings indicate like parts. FIG. 1 and FIG. 2 show a diagram according to the present invention. The co-pilot quick-coupling iClick control control rod 10 is shown.

The control m1io is a support bolted to the floor of the aircraft under the co-pilot seat 13. It is attached to assembly 12. Gimbal member 14 pivots within support assembly 12. It is installed to be athletic. The control *io is equipped with two prongs 15 at its lower end. . The two prongs 15 include a bearing 16 and a shaft 17 extending through the bearing 16 and the gimbal member 14. In particular, it is attached to the outside of the gimbal member 14. In other words, the control rod 10 is It is pivotable left and right by the valve member 14 and pivotable back and forth by the shaft 17. Pilot l110 These pivot movements add roll and pitch control inputs to the aircraft flight control system. Ru.

The pivot member 18 can be mounted inside the siding member 14 by a single ball bearing 20. be. Shaft 17 extends through bearing 16, gimbal member 14 and single ball bearing 20. ing. The single ball bearing 20 allows the sibibot member 18 to move independently of the movement of the control rod 10. It can pivot left, right, front and back. The bearing 21 of the pivot member 18 The target link device 19 is connected to the aircraft control system.

The pivot member 18 also includes a stud 22 extending forwardly and upwardly from the pivot member 18. It is equipped with

A conical or bowl-shaped stopper or housing 24 is located between the two prongs 15 and is operable. It is slidably mounted within the sleeve 26 of the vertical bar 10. Coil inside sleeve 26 The spring 27 biases the housing 24 downwardly and rearwardly so that the stand 2 of the pivot member 18 2 fits into the socket 25 at the top of the housing 24. Star When fitting the rod 22 into the socket 25, insert the control rod 10 and 1?7x;/) member 1. 8 are fixed to each other and pivot together with the gimbal member 14 and the shaft 17.

A lever assembly 30 is pivotally attached to the control rod 10 and is also attached to the housing 2. It is attached to the arm 32 connected to 4. ;Ile spring 34 is the lever assembly 3 0 upwardly and away from the pivot member 18. lever assembly Actuation of 30 toward pivot member 18 moves housing 24 into sleeve 26. Slide the stud 22 forward and upward against the spring 27 to remove it from the socket 25. It will be done. When actuated as shown in FIG. 2, the lever assembly 30 pivots to A hook attached to or under the seat 13 engages the tool 40. Use the stopper 42 The lever assembly 30 is hooked and locked to the tool 40. Hook lever assembly 30 When locked to the fitting 40, the control sio is fixed in the central position and rotated from the pivot member 18. The engagement will be disengaged. This pivot member 18 has a single ball bearing 2 regardless of the control rod 10. It will be in a state where it can freely pivot to 0 rotation. However, the housing 24 2, the entire movement range of the stud 22 is covered (as shown by the chain line 22a1 in Figure 2). 22b), but during this time the pivot member 18 moves and maneuvers 1110. remains fixed.

The disengaged control rod 10, primarily as shown in FIG. Just like unlocking the 0, Kake quickly turns the lid on the aircraft control system by simply releasing the gold 42. can be engaged with each other. When Kake releases the money 42, the spring 34 causes the lever bar to be released. As the assembly 30 pivots, the hook pivots away from the fixture 40 as shown by the dashed line 30a. It moves away from the contact member 18 in the direction away from it. The spring 27 acting in cooperation with the spring 34 is Move the housing 24 downward and rearward toward the stud 22 as shown by the chain line 24a. strongly urge. In this case, the conical interior of the housing 24 allows the stand 22 to be The control rod 10 is fixed to the pivot member 18 again by guiding it into the socket 25.

In this case, the control rod 10 and the pivot member 18 are together with the gimbal member 14 and the shaft 17. Pivot to.

The control rod 10 according to the invention has a stud 22 that extends from the enclosure of the conical housing 24. It never comes out, so it doesn't lock up aircraft control loads during reconnection. Even more ha The housing 24 opens downward to prevent dust and foreign matter from falling into the socket 25. This is to avoid interfering with the reconnection of the control rod 10 to the pivot member 18.

Furthermore, the housing 24 of the present invention is such that the stud 22 is not inserted into the socket 25. When the housing 24 is moved toward the stud 22, the control system exert some input on the system.

Although the present invention has been described in detail with respect to its embodiments, the present invention still deviates from its spirit. It is clear that it is possible to perform various transformations without breaking away.

international search report December 6, 1999

Claims (10)

[Claims] 1. It has a gimbal means for attaching a control rod to an aircraft and a stud that projects upward. one pivot assembly; This pivot assembly is attached to the gimbal means and is connected to the control rod movement at the front. a swivel bearing for providing pivoting movement of the pivot assembly; It has a socket that engages the stud and allows the stud to be operated after the control rod is uncoupled. A bowl-shaped housing for mounting a control rod that surrounds the range of motion; Disengage the socket from the stud and remove it from the pivot assembly. an engagement disengagement means for disengaging the vertical bar; biasing means for biasing the housing toward the stud; and the housing guides the socket onto the stud to engage the pivot. A disengagement mechanism configured to reconnect the control rod to the control rod assembly. Aircraft control rod. 2. Claims where the pivot assembly is attached to a linkage connected to the aircraft control system. An aircraft control rod that can be engaged and disengaged as described in Item 1. 3. locking means for releasably locking the uncoupled control rod body in a fixed position; By releasing this locking means, the steering rod can be reconnected to the pivot assembly. The disengageable aircraft according to claim 1, further comprising a release means adapted to release the aircraft. Aircraft control stick. 4. gimbal means for pivotally attaching a control rod to the aircraft; a pivot member having an upwardly protruding stud and connected to an aircraft control device; This pivot member is attached to the gimbal means so that there is no pivoting movement regardless of the movement of the control rod. swivel bearing means for allowing the engages with the stud to fix the space between the control rod body and the pivot member; a control rod having socket means and enclosing the range of motion of said stud after uncoupling; With the attached bowl-shaped housing, said pivot member by disengaging said socket means from said stud. a disengaging means for disengaging the control rod from the control rod; locking means for releasably locking the uncoupled control rod body in a fixed position; a release means for releasing this locking means; biasing means for biasing the housing toward the stud; guiding said socket means to said stud by said bowl-shaped housing. By doing so, the control rod is reconnected to the pivot member. An aircraft control rod that can be disengaged. 5. 5. The apparatus of claim 4, further comprising a bifurcated assembly for attaching the control rod to the gimbal means. Aircraft control rod that can be connected and removed. 6. The disengagement function according to claim 4, wherein the swivel bearing means is constituted by a single ball bearing. Aircraft control rod. 7. the disengagement means; a control connection sleeve that slidably attaches the housing to the control rod body; is attached to the housing and slides the housing by actuation of a lever assembly. Slide the control rod away from the tad to disconnect the control rod from the pivot member. 5. The lever assembly according to claim 4, comprising: a lever assembly to which a control rod is attached; Aircraft control rod that can be connected and removed. 8. In the quick connection cyclic control rod for co-pilot, a support assembly secured to the aircraft; The cyclic control rod is pivoted from side to side and back and forth relative to the support assembly. a gimbal member that attaches the cyclic control rod to the support assembly; , a pin with an upwardly projecting stud that provides a linkage to the aircraft control system. Separately from the bot member and the cyclic control rod, the pivot member can be moved left, right, front and back. a single ball shaft connecting the pivot member to the gimbal member for pivoting to the gimbal member; has a receiver and a socket that engages the stud and slides onto the cyclic control rod. A freely installed bowl-shaped housing, By inserting the stud into the socket, the cyclic control rod and the bowl-shaped housing coupled to the pivot member for integral pivoting; biasing means for biasing the cyclic control rod toward the pivot member; and said bowl-shaped housing, said bowl-shaped housing being attached to said pivot. Slide the stud away from the member to disengage the stud from the socket. The cyclic control rod is uncoupled from the aircraft control device by a lever assembly that is actuated in a sliding manner; the lever assembly to hold the cyclic control rod in a fixed position; locking means for releasably locking the lock and releasing the locked lever assembly; The biasing means biases the socket onto the stud so that the socket is a release means for reconnecting the iclick control rod to the pivot member; A quick-connect cyclic control rod for the co-pilot. 9. The cyclic control rod is a bifurcated assembly for attachment to the gimbal means. 9. The quick-connect cyclic control rod for a co-pilot according to claim 8, further comprising a cyclic control rod for a co-pilot. 10. A shaft connects the bifurcated assembly, the gimbal member, and the single ball bearing. 10. A quick connection service for a co-pilot according to claim 9, which extends through and connects these parts. Ikrik control stick.