JP3310870B2 - Straight-sliding mechanism for tail wheeled aircraft - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a straight-sliding mechanism for a tail-wheeled airplane which solves the above-mentioned disadvantages (problems) of a tail-wheeled airplane having very poor straight-sliding performance during takeoff gliding (especially at low speed taxiing). It is about.

[0002]

2. Description of the Related Art A tail-wheeled airplane has a very poor straight-sliding property, which is a characteristic of the aircraft, and is very difficult to maneuver during take-off gliding. However, a tail wheel type airplane that has solved the above-mentioned difficulties has not been manufactured.

[0003]

The tail wheel type airplane has a very poor straight running property, which is a characteristic of the aircraft, and is very difficult to maneuver during takeoff gliding, sometimes causing a ground loop or the like. Sometimes it led to an accident. In contrast to the tail-wheeled airplane, the front-wheeled airplane has good straight-sliding properties, so that most modern airplanes have become front-wheeled airplanes. However, the front wheel type airplane has a disadvantage that the mechanism of the front wheel is complicated and heavy, which is expensive, that the front wheel becomes harmful, and that the front wheel becomes a retractable leg due to space limitations. Compared with the front wheel type airplane, the tail wheel type airplane has a simple tail wheel mechanism, is lightweight, is less expensive, and has less harmful resistance of the tail wheel. In addition, the tail wheel type airplane is advantageous in that the main wheel and the tail wheel are used as retractable legs. As described above, the tail-wheeled airplane has the advantages as described above over the front-wheeled airplane, however, the straight-running glide property is very poor, and the maneuvering during takeoff gliding is very difficult. The present invention has solved the above-mentioned difficulties (problems) of the tail wheel type airplane.

[0004]

Means for solving the problem will be described below. As described above, the tail-wheeled airplane has a very poor straight-ahead glide property, and is very difficult to maneuver during takeoff gliding. In order to solve the difficulties (problems) at the time of takeoff of the airplane (by straight running), the left and right main wheels (1)
2) must be rotated the same (the rotation speeds of the left and right main wheels are made the same). Therefore, the present invention provides a coaxial (14) having both ends fixed by a coaxial gear (15) as a method of rotating the left and right main wheels by the same rotation. The coaxial gear and the main wheel gear (13) fixed to the axle of each of the left and right main wheels (or the connecting gear (24) in the machine) are connected to each other, and the left and right main wheels are rotated coaxially or the like, Based on the above-mentioned operation, this is a method in which the aircraft is slid straight. On the other hand, during taxiing, if the left and right main wheels rotate the same, the aircraft cannot change its direction from left to right. In this case, when the main wheel gear (or the connection gear) connected to the coaxial gear is released and the left and right main wheels are independently rotated during straight running or the like, the aircraft can be easily changed in the left-right direction. In the present invention, in order to intermittently connect the coaxial gear and the main wheel gear (or connection gear), the two gears are connected to each component such as a rudder pedal (4), a pedal connection bracket (5), a rudder cable (3). The two gears are interlocked (coupled) via a gear to intermittently connect the two gears. If the coaxial gear and the main wheel gear (or connection gear) are connected, the aircraft will slide straight,
If the two gears are separated, the body can be easily changed in the left-right direction. If the tail wheel airplane does not depress the rudder pedal (if it is not operated), the coaxial gear and the main wheel gear (or coupling gear) are connected, and when the rudder pedal is depressed,
The two gears separate. In addition, the control method during takeoff and landing or taxiing of the aircraft is the same as that of a general airplane, which is very convenient.

[0005]

Embodiments of the present invention will be described below. 1. Actual machine: an operating lever having upper and lower portions (the invention of claim 1) This is shown in FIGS. 1 to 6. The tip of a pedal connecting bracket (5) is connected to each of the left and right rudder pedals (4). The upper ends (6) of the left and right operating levers are joined to the slide grooves of the pedal connection fitting. The rear end of the pedal connection fitting and the lower end of the operating lever (8) are connected to the respective pulleys (9) or connected by wires (7) which are separated from each other. Attach the upper end of the main connecting rod (16) to the fitting integrated with each of the left and right operating levers. The lower end of the main connecting rod is connected to the tip of the intermittent fitting (19). The left and right ends of the coaxial (14), both ends of which are fixed by coaxial gears (15), are respectively attached to the distal end portions of the left and right intermittent fittings. The main wheel and the main wheel gear (13) are fixed to the axles of the left and right main wheels (12). 2. Actual machine: One with an operating lever only at the top (Claim 2
This is shown in FIGS. 7 to 12. A pedal connecting bracket (21) is connected in front of the left and right rudder pedals (4). The left and right rear ends of the pedal connection bracket are connected to the upper ends of the left and right operating levers 2 (22), respectively. The upper ends of the main connecting rods (16) are attached to metal fittings integrated with the operating lever 2, respectively. The lower part from the above structure is
This is the same as the structure of the invention of the first aspect. 3. Actual machine: without operating lever (invention of claim 3) This is shown in FIG. 13 and FIG. A pedal connecting bracket (21) is connected in front of the left and right rudder pedals (4), and left and right rear ends of the pedal connecting bracket are connected to left and right interrupted bars (23), respectively. Coaxial gears at both ends (1
The left and right ends of the coaxial (14) fixed in 5) are attached to the lower ends of the intermittent rods, respectively. The main wheel and the main wheel gear (13) are fixed to the axles of the left and right main wheels (12). The main wheel gear is connected to a connection gear (24) in the lower part of the machine using two upper and lower chain connection gears (25) and a chain (26). 4. Tail-wheeled radio-controlled model airplane: with a working tube lever (invention of claim 4) This is shown in FIGS. The present invention is an application of the invention of a real machine to a tail wheel type radio control model airplane (hereinafter, referred to as a radio control machine). When the nose is viewed from the front, the operating rods (32) are attached to the right and left of the servo horn (31) attached to the rudder servo (30).
An operating pipe (33) which is pushed forward by the operating rod is provided, and a tip of the operating pipe is connected to an upper end of an operating pipe lever (34). The lower end of the operating tube lever and the upper end of the operating plate (36) are connected by the upper interlocking rod (35). At the lower end of each of the left and right interrupted rods (23), the left and right ends of a coaxial (14) whose both ends are fixed by a coaxial gear (15) are attached. A lower end of the operation plate and a lower end of the interrupting rod are connected by a lower interlocking rod. The main wheel and the main wheel gear (13) are fixed to the axles of the left and right main wheels (12). The main wheel gear is connected to a connection gear (24) in the lower part of the machine using two upper and lower chain connection gears (25) and a chain (26).

[0006]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the present invention and application (change) embodiments thereof will be described below. 1) Actual machine: An operation lever is provided at an upper portion and a lower portion (the invention of claim 1). The tip of a pedal connecting bracket (5) is connected to each of the left and right rudder pedals (4). The upper ends (6) of the left and right operating levers are joined to the slide grooves of the pedal connection fitting. The slide groove of the pedal connecting bracket is a groove in which when the right or left rudder pedal is depressed, the upper end of the operating lever can slide forward and backward in conjunction therewith. The upper end of the operation lever is located at the rear end of the slide groove of the pedal connection fitting. The rear end of the pedal connection fitting and the lower end of the operating lever (8) are connected to the respective pulleys (9) or connected by wires (7) which are separated from each other. When connecting with the wire, the wire is connected to each pulley as shown in FIG.
At this time, the wires are kept tight. The main connecting rod (16) is attached to the bracket integrated with each of the left and right operating levers.
And the upper end of the auxiliary connecting rod (17). The lower end of the main connecting rod is connected to the lower end of the main leg (18) and the tip of an intermittent fitting (19) that moves up and down. The lower end of the sub-connecting rod is connected to the tip of a crimp fitting with a spring (20) which is attached to the intermittent fitting and moves up and down. The left and right ends of the coaxial (14), both ends of which are fixed by the coaxial gear (15), are respectively attached to the leading end portions of the left and right intermittent fittings. The main wheel and the main wheel gear (13) are fixed to the axles of the left and right main wheels (12). The coaxial gear and the main wheel gear are a combination of flat gears. The present invention has a structure in which the coaxial gear and the main wheel gear are intermittently connected via a coaxial shaft when the rudder pedal is depressed or released. Next, the operation of the present invention (how to use
(Use state) will be described. A) During takeoff run This is shown in Figs. 1 and 2. During takeoff run, point the machine in the direction of takeoff run and do not operate the rudder pedal (do not step on it). If the rudder pedal is not depressed, the left and right coaxial gears and the main wheel gears are always connected by the action of the left and right springs (11), the main connecting rod, the auxiliary connecting rod, etc. The two gears are crimped. This is because the main connecting rod and the auxiliary connecting rod attached to the metal fittings integrated with the left and right operating levers work in conjunction with each other, so that the coaxial gear and the main wheel gear are securely crimped, and the takeoff run The trouble that the two gears are disengaged at the time does not occur. From the above operation, if the machine slides, the coaxial gear and the main wheel gear are connected to each other, and the left and right main wheels rotate the same through the coaxial, and naturally the rotational speeds of the left and right main wheels become the same. The aircraft glides straight. A) During taxiing This is shown in FIGS. To turn the machine right (or left) during taxiing, depress the right (or left) rudder pedal. The right and left rudder pedals are
Since they are connected via the left and right ladder cables (3) and the ladder (2), they work in conjunction. The state of the tail wheel, rudder and the like at this time are shown in FIG. 3 and FIG. FIG.
The machine has just depressed the right rudder pedal while taxiing (when turning right). FIG. 4 shows a state where the left rudder pedal is depressed (at the time of turning left). FIG.
5 shows the state when the right rudder pedal is depressed, and the position of the upper end of the right operating lever. When the right (or left) rudder pedal is depressed, the pedal connecting bracket connected to the rudder pedal moves forward. The upper end of the operating lever connected to the pedal connection fitting is also pulled forward by the pedal connection fitting and advances (at this time, the wire does not loosen). On the other hand, since the left (or right) rudder pedal on the opposite side is connected to the right (or left) rudder pedal, it is pulled backward by the left (or right) rudder cable and moves backward. FIG. 6 shows the operating positions of the left rudder pedal, the pedal connecting bracket, the upper end of the operating lever, and the like when the right rudder pedal is depressed in FIG. From the above, the pedal connection fitting connected to the left (or right) rudder pedal is also retracted. Due to the above operation, the lower end of the operating lever is also retracted by being pulled by the wire attached to the rear end of the left (or right) pedal connection fitting, and the upper end of the operating lever integrated with the lower end of the operating lever moves forward in reverse. (At this time, the wire is connected to each pulley.) From the above series of operations, the upper ends of the left and right operation levers always move forward simultaneously when the right or left rudder pedal is depressed. From the above, by depressing the right or left rudder pedal, the main connecting rod and the auxiliary connecting rod attached to the fittings integrated with the left and right operating levers are pulled upward. Due to the above operation, the left and right intermittent fittings and the spring-loaded crimp fittings connected to the two connecting rods also rise. When the intermittent fitting is raised, the coaxial (coaxial gear) attached thereto is also raised, and the left and right coaxial gears and the main wheel gears respectively connected thereto are simultaneously separated by the above-described action. If the coaxial gear and the main wheel gear are separated, the left and right main wheels rotate independently, so that the aircraft can be easily changed in the left-right direction during taxiing. As an advantage of this mechanism, when the right or left rudder pedal is depressed, as described above, the upper ends of the left and right operating levers always move forward at the same time. Accordingly, the left and right coaxial gears and the main wheel gears respectively connected thereto are simultaneously separated by the above-mentioned action in conjunction with the main connecting rod, the sub connecting rod, etc. attached to the metal fitting integrated with the left and right operating levers. It is very convenient for. If the gear is configured to be separated by only one of the right and left gears, the opposite gear will be one-sided, causing a failure or the like. In all the inventions described below, the main wheel gear or the connecting gear (2) respectively connected to the left and right coaxial gears.
4) are separated at the same time by the action described above. The operating lever, the pulley, and the like are mounted on a bracket mounting plate (10) mounted on the inner side plate using bolts and nuts. According to the present invention, the left and right coaxial gears and the main wheel gears are connected to each other unless the rudder pedal is depressed when the take-off run is performed with the aircraft (tail wheel type airplane) because of the above-described mechanism. Glide straight. Also, when turning the machine to the right or left during taxiing, depressing the right or left rudder pedal separates the left and right coaxial gears from the connected main wheel gears, which is easy. Can be. 2) Actual machine: one with an operating lever only at the top (Claim 2)
Invention of the invention) A pedal connecting bracket (2) is provided in front of the left and right rudder pedals (4).
1), and the left and right rear ends of the pedal connecting bracket,
The upper ends of the left and right operating levers 2 (22) are connected respectively. When the right or left rudder pedal is depressed, the pedal connection bracket is a bracket that is pushed by the rudder pedal and moves only forward from an original position, and moves forward and backward within the range (3 and 4 described later). The effect of the pedal joint fitting is the same. ). When viewed from above, the pedal connection bracket is a U-shaped bracket in which the left and right sides are integrated. As described above, the pedal connection brackets are connected to the front of the left and right rudder pedals and extend rearward, and the left and right rear rudder pedals respectively. The ends are respectively connected to the upper ends of the left and right operating levers 2. Also, the structure is
According to the first aspect of the present invention, the structure from the pedal connection fitting to the upper end of the operating lever (6) is simplified, and the number of parts is reduced. The upper ends of the main connecting rod (16) and the sub-connecting rod (17) are attached to the fitting integrated with the operating lever 2 respectively. The structure from the above to the lower part is the same as the invention of the above item 1). Next, the operation (use method / use state) of the present invention will be described. (1) During takeoff run This is shown in FIGS. 7 and 8. During takeoff run, point the machine in the direction of takeoff run and do not operate the rudder pedal (do not step on it). If the rudder pedal is not depressed, the left and right coaxial gears (15) and the main wheel gear (13) are always connected to each other by the action of the spring (11) and the main connecting rod in the machine. The two gears are pressed by the action. From the above operation, when the machine slides, the coaxial gear and the main wheel gear are connected, and the left and right main wheels (12) rotate the same via the coaxial (14), so that the body slides straight. (2) Taxiing This is shown in FIGS. 9 to 12. To turn the machine right (or left) during taxiing, depress the right (or left) rudder pedal. From the above, the pedal joint fitting that is linked (joined) with the rudder pedal moves forward, and the upper ends of the left and right operating levers 2 connected to the left and right rear ends of the pedal joint fitting also move forward at the same time. From the above action,
Each of the left and right main connecting rods and sub connecting rods attached to the fitting integrated with the operating lever 2 is pulled upward. On the other hand, the left (or right) rudder pedal on the opposite side is retracted by being pulled by the left (or right) rudder cable (3).
At this time, only the rudder pedal slides rearward, and the left and right integrated (coupled) pedal joints are:
Do not move while moving forward. Accordingly, the upper ends of the left and right operating levers 2 remain forward, and the left and right main connecting rods and sub-connecting rods remain pulled upward. In this mechanism, as in the first aspect of the invention, when the right or left rudder pedal is depressed, the upper ends of the left and right operating levers 2 always move forward at the same time. The operation after the above is the same as that of the invention of the preceding item 1). Since the left and right coaxial gears and the connected main wheel gears are simultaneously separated and the left and right main wheels rotate independently, the airframe during the taxiing on the ground Can easily be changed from side to side. 3) Actual machine: No actuation lever (invention of claim 3) In the present invention, the inventions of the preceding items 1) and 2) have a harmful resistance because the coaxial (14) is located at the lower part of the fuselage. It is stored in the cabin. The above structure is a simpler structure in which the operating lever 2 (22), the main connecting rod (16), the intermittent fitting (19), etc. of the invention of the preceding item 2) are omitted. A pedal connecting bracket (21) is connected in front of the left and right rudder pedals (4), and left and right rear ends of the pedal connecting bracket are connected to left and right interrupted bars (23), respectively. The left and right ends of the coaxial (14) whose both ends are fixed by the coaxial gear (15) are respectively attached to the lower ends of the interrupted bars. The intermittent bar operates back and forth in conjunction with the pedal connection fitting. The main wheel and the main wheel gear (13) are fixed to the axles of the left and right main wheels (12). A chain connecting gear (25), which is always connected to the main wheel gear, is attached to a lower portion of the main leg (18). A chain connecting gear is also mounted on the lower part of the machine, and this is connected to the chain connecting gear mounted on the lower part of the main leg by a chain (26) or a belt. A connecting gear (24) that is always connected to the chain connecting gear in the lower part of the machine is mounted behind the coaxial gear in the lower part of the machine. The connecting gear and the main wheel gear have a horizontal gear axis, but the chain connecting gear has a bevel gear (a bevel gear) because the lower part of the main leg is opened to the left and right from the body mounting portion of the main leg. ) So as to mesh with the gear. The structure and operation of the rudder pedal and the pedal fitting are the same as those of the invention of the above item 2). Further, in the above structure, when the main wheel gear (main wheel) rotates, the connection gear always rotates in conjunction with the above (via a chain or the like). The present invention has a structure in which the right and left rudder pedals are depressed or released, and the left and right interrupted rods simultaneously act back and forth, and the left and right coaxial gears and the connection gear are interrupted. Next, the operation (use method / use state) of the present invention will be described. Depress the right or left rudder pedal,
When the pedal is released, the pedal connecting bracket is operated back and forth, and the left and right intermittent rods connected to the pedal are simultaneously operated back and forth. When the intermittent rod retreats, the left and right coaxial gears and the connecting gear are connected, respectively, and when the intermittent rod moves forward, the coaxial gear and the connecting gear separate. From the above operation, the left and right main wheels rotate coaxially or independently. If the left and right main wheels rotate the same during takeoff run,
If the aircraft slides straight and the left and right main wheels rotate independently, it is easy to change the aircraft's lateral direction during taxiing. FIG.
FIG. 14 and FIG. 14 show a state in which the machine runs straight. Further, by using a chain or the like instead of the coaxial, the same operation as the coaxial can be performed. In the above structure, the bevel gears are connected to each other by a chain or the like using a bevel gear that meshes at right angles with the left and right coaxial gears. In this case, a chain or the like is crossed into a figure eight. Next, models suitable for equipping the invention mechanisms of the preceding paragraphs 1), 2) and 3) are high-wing aircraft, biplanes or triplanes, and those having main legs attached to the fuselage are suitable. However, when the main landing gear is attached to the lower part of the main wing, the following applied embodiment will be adopted. 4) Application example of the invention of the above item 3) (the invention of the item 3) In the invention of the item 3), the coaxial (14) is housed in the lower part of the machine. The main landing gear is attached to the lower part of the main wing. A. When there is no dihedral angle on the main wing This is shown in FIG. 15 and FIG. In the above structure, an extension shaft (28) is provided in each of the left and right main wings (27), and a connection gear (24) is fixed on both sides of the extension shaft on the inside of the machine and an extension shaft gear (29) is fixed on the wing end side. I do. The extension shaft gear is connected to the main wheel gear (13) via a chain (26) or the like.
Therefore, the structure is such that the main wheel gears (main wheels) are constantly rotated (connected) from the connecting gears in the machine. The structure is basically the same as the structure described in the item 3). The extension shaft and the extension shaft gear are simply mounted in the left and right wings. B. When the main wing has a dihedral angle, a universal joint is attached to both ends of the extension shaft, and the universal joint is connected to a connection gear on the inside of the machine and an extension shaft gear on the wing end side, respectively. Therefore, even when there is a dihedral angle, the coaxial gear (15) on the inside of the machine and the connecting gear, and the main wheel gear and the extension shaft gear can be connected without difficulty. Further, when the main wheel gear (main wheel) rotates, the connection gear in the machine always rotates via a chain, an extension shaft and the like. Next, the operation (use method / use state) of the present invention is substantially the same as the invention of the above item 3). In the low-wing aircraft having the above-described structure, the fixed legs are used. However, the fixed legs may be used as the retractable legs equipped with the present mechanism. The material of the pedal gear and the like used in the manufacture of the present invention is made lightly and durably by using those commonly used (general). Further, it is necessary to make a coaxial or the like light and strong by making a tube inside the shaft. The main landing gear and the like are covered to prevent troubles such as gears caused by intrusion of mud and the like, and to reduce harmful resistance. Next, a comparison will be made between the maneuvering method of the tail-wheel type airplane equipped with the present mechanism during takeoff / landing and taxiing and the maneuvering method of a general airplane. If the control method of this mechanism is different from that of a general airplane, the control may be confused and dangerous. However, in all of the above inventions, the maneuvering is not different from a general airplane, which is very convenient. 5) Radio control machine: one having an operating tube lever (invention of claim 4) The present invention is an application of the invention of the above 2) and 3) to a radio control machine. This is shown in FIGS.
This mechanism uses one ladder servo (30) and ladder (2)
And straight running and taxiing of the main wheel (12) can be controlled. The mounting position of the ladder servo is
When viewed from the upper surface of the fuselage, the center of the servo horn (31) attached to the rudder servo is located on the center line of the fuselage. When the nose is viewed from the front, an actuation rod (32) for alternately moving forward and backward is attached to the right and left of the servo horn (if the rudder is controlled to the right or left).
An operating tube (33) is provided which is pushed by the operating rod and moves forward. The working tube is provided with a groove through which a working rod joined thereto can slide back and forth. The slide groove,
This is the length from a to b shown in FIG. The length is set to be at least twice as long as the operation rod moves forward by operating the ladder servo to the full operation amount. The structure described above is comparable to the relationship between the rudder pedal (4) and the pedal fitting (21) described in the actual machine. The distal end of the working tube and the upper end of the working tube lever (34) are connected. The lower end of the operating tube lever and the upper end of the operating plate (36) are connected by an upper interlocking rod (35). Coaxial (14) with both ends fixed to the lower end of each left and right interrupted bar (23) by a coaxial gear (15)
Attach the left and right ends of the A lower end of the operation plate and a lower end of the interrupting rod are connected by a lower interlocking rod. The intermittent bar operates back and forth in conjunction with the operating plate and the like. Further, as shown in FIG. 17, the relational position of the intermittent rod and the operating pipe lever viewed from the front is that the operating pipe lever is located immediately after the intermittent rod, so that the lower part from the axis of the operating pipe lever is:
It cannot be seen because it overlaps with the intermittent rod. The present invention has a structure in which the left and right coaxial gears and the connection gear (24) are intermittently controlled if the rudder is controlled to the right or left or no operation is performed. The structure from the above to the lower part is the same as the structure of the actual machine in the above item 3). The materials and the like used for manufacturing the gears and the like of the present invention are the same as or similar to those used for radio-controlled models and the like, and are light and durable. Next, the operation (use method / use state) of the present invention will be described. 1) During takeoff run This is shown in FIGS. 17 and 18. During takeoff run,
If the machine is pointed in the direction of takeoff run and the rudder is not operated, the left and right coaxial gears and the connecting gears are always connected by the action of the left and right springs (11) and the like, so that the aircraft runs straight. 2) Taxiing This is shown in FIGS. 19 and 20. When the machine turns right (or left) during taxiing, the rudder servo operates by controlling the rudder to the right (or left). From the above operation, the right (or left) working rod attached to the servo horn pushes the working tube forward, and the upper end of the working tube lever connected to the working tube also advances. When the upper end of the operating pipe lever moves forward, the upper interlocking rod connected to the lower end of the operating pipe lever retreats, and the left and right integrated operation plate (single plate) connected to the interlocking rod is connected. The lower end tilts forward about the horizontal axis (37). From the above operation, the lower interlocking rod connected to the lower left and right ends of the operation plate simultaneously pulls the left and right interrupted rods forward, and the left and right coaxial gears (coaxial) attached to the interrupted rods are connected gears. Move away from On the other hand, due to the operation of the rudder servo, the tip of the (opposite) left (or right) operating rod attached to the servo horn is shown in FIG.
Retreats from a to b of the slide groove. At this time, only the left operating rod is retracted, and the left operating tube is connected to the upper and lower interlocking rods / operating plate on the right side, so that the lower end of the operating plate is inclined forward as described above. In this state, the working tube does not move while moving forward. Therefore, when the rudder is controlled, the above-described series of operations causes the left and right coaxial gears and the connecting gears respectively connected to each other to be simultaneously separated,
Because the left and right main wheels rotate independently via a chain, etc.,
The aircraft can be easily turned from side to side during taxiing. Of course, in the radio-controlled machine, the coaxial gear and the main wheel gear (13) can be connected and disconnected by attaching the coaxial to the lower part of the main leg.
This is the next application example. 6) Radio Controlled Machine: Application Example of Invention 5) (Invention of Claim 4) This is shown in FIGS. 21 to 24. In this application example, a coaxial (14) (coaxial gear (15)) is attached to the lower part of the main landing gear, and an operating rod (32), an operating pipe (33), and an operating pipe lever used in the radio control machine described in 5) above. (34) and the like (excluding the operation plate and the like in the invention of the preceding item 5) and a simple connecting rod (39) is newly attached. Also,
The radio control machine (in which the coaxial is attached to the lower part of the main landing gear) of the item (6) is similar in structure to the actual machine of the invention of the item (2) (the invention of the item (2)). Looking at the above-mentioned operation (use method / use state), the operation up to the working tube lever is the same as the operation of the radio-controlled machine described in the above item 5). The function of the lower part from the above is the same as the function of the invention of the above item 2) (actual machine), but the crimp fitting is not particularly attached. The structure in which the coaxial (14) of the above item 5) is attached to the lower part inside the radio control machine is similar to the structure of the actual machine in which the coaxial of the item 3) (the invention of claim 3) is attached to the lower part inside the device. The structure of these radio control machines is essentially the same as the actual structure of the present invention. Hereinafter, the corresponding structure is shown. Rudder pedal of the actual machine and operating rod of the radio control machine, pedal connecting bracket of the actual machine and operating pipe of the radio control machine, operating lever of the actual machine and operating pipe lever of the radio control machine, main connecting rod of the actual machine and connecting rod of the radio control machine + operating plate, etc. The relationship is This mechanism can be easily applied to various tail wheel type radio control machines.

[0007]

The tail wheel type airplane equipped with this mechanism is suitable for a training aircraft because it can easily perform straight running and taxiing on the ground. The operation method of the airframe equipped with this mechanism during takeoff / landing and taxiing is not different from a general airplane, which is very convenient. The aircraft stabilizes even if it touches down while skidding. In an airframe equipped with a brake in this mechanism, since a one-sided effect does not occur even when the brake is applied, it is possible to safely stop without causing a ground loop or the like. Also, if the brake is applied when the machine comes into contact with the ground while skidding, it can be safely stopped without causing a ground loop or the like as described above. This mechanism can be easily applied to a radio control machine.

[Brief description of the drawings]

FIG. 1 is a front view of the present invention.

FIG. 2 is a sectional view of the present invention, but a side view of only a ladder portion. In all the sectional views shown below, only the ladder portion is a side view.

FIG. 3 is a front view of the present invention.

FIG. 4 is a front view of the present invention.

FIG. 5 is a sectional view of the present invention.

FIG. 6 is a sectional view of the present invention.

FIG. 7 is a front view of the present invention.

FIG. 8 is a sectional view of the present invention.

FIG. 9 is a front view of the present invention.

FIG. 10 is a front view of the present invention.

FIG. 11 is a sectional view of the present invention.

FIG. 12 is a sectional view of the present invention.

FIG. 13 is a front view of the present invention.

FIG. 14 is a sectional view of the present invention.

FIG. 15 is a front view to which the present invention is applied.

FIG. 16 is a sectional view to which the present invention is applied.

FIG. 17 is a front view in which the present invention is applied to a radio control device.

FIG. 18 is a cross-sectional view in which the present invention is applied to a radio control device.

FIG. 19 is a sectional view in which the present invention is applied to a radio control machine.

FIG. 20 is a sectional view in which the present invention is applied to a radio control machine.

FIG. 21 is a front view in which the present invention is applied to a radio control device.

FIG. 22 is a cross-sectional view in which the present invention is applied to a radio control device.

FIG. 23 is a sectional view in which the present invention is applied to a radio control machine.

FIG. 24 is a sectional view in which the present invention is applied to a radio control machine.

[Explanation of symbols]

 REFERENCE SIGNS LIST 1 tail wheel 2 rudder 3 rudder cable 4 rudder pedal 5 pedal connecting bracket 6 operating lever upper end 7 wire 8 operating lever lower end 9 pulley 10 bracket mounting plate 11 spring 12 main wheel 13 main wheel gear 14 coaxial 15 coaxial gear 16 main connecting rod 17 Secondary connecting rod 18 Main leg 19 Intermittent fitting 20 Crimp fitting 21 Pedal joint fitting 22 Operating lever 2 23 Disconnecting rod 24 Connecting gear 25 Chain connecting gear 26 Chain 27 Main wing 28 Extended shaft 29 Extended shaft gear 30 Rudder servo 31 Servo horn 32 Operating rod 33 Working pipe 34 Working pipe lever 35 Interlocking rod 36 Working plate 37 Horizontal axis 38 Rudder rod 39 Connecting rod

Claims (4)

(57) [Claims] (1) The tip of a pedal connecting bracket (5) is connected to each of the left and right rudder pedals (4), and an upper end (6) of an operating lever is connected to a slide groove of the pedal connecting bracket to connect the pedals. The rear end of the bracket and the lower end (8) of the operating lever are connected to each pulley (9) or are connected by wires (7) which are separated. (B) The upper end of the main connecting rod (16) is attached to the metal fitting integrated with each of the left and right operating levers, and the lower end of the main connecting rod and the tip of the intermittent metal fitting (19) are connected. Coaxial (1) fixed at both ends to the tip with coaxial gears (15)
4) Attach the left and right ends of each, and install the left and right main wheels (1
2) The main wheel and the main wheel gear (13) are fixed to the axle. A straight-running gliding mechanism for a tail-wheeled airplane having the above configuration. 2. A pedal joint fitting (21) is joined in front of the left and right rudder pedals (4), and the left and right rear ends of the pedal joint fitting and the upper ends of the left and right operating levers 2 (22) are connected. 2. The straight-running sliding mechanism of a tail wheel type airplane according to claim 1, wherein the linear running mechanism is connected to each other. 3. A left and right rudder pedal (4) is connected with a pedal connecting fitting (21) in front of the left and right rudder pedals (4), and the left and right rear ends of the pedal connecting fitting are connected with the left and right connecting bars (23), respectively. The left and right ends of a coaxial shaft (14), both ends of which are fixed by a coaxial gear (15), are respectively attached to the lower ends of the interrupted bars, and the main wheel and the main wheel gear (13) are mounted on the axles of the left and right main wheels (12). And a straight running mechanism of a tail wheel type airplane in which the main wheel gears and a connecting gear (24) in the aircraft are connected via a chain (26) and the like. (A) When the nose is viewed from the front, operating rods (32) are mounted on the right and left sides of a servo horn (31) mounted on a rudder servo (30), and are pushed forward by the operating rods. An operating pipe (33) is provided, which connects the tip of the operating pipe to the upper end of the operating pipe lever (34), and connects the lower end of the operating pipe lever and the upper end of the operating plate (36) to an upper interlocking rod (35). ), And the left and right ends of a coaxial (14), both ends of which are fixed by coaxial gears (15), are attached to the lower ends of the left and right interrupted bars (23), respectively. And are connected by the lower connecting rod. (B) A main wheel and a main wheel gear (13) are fixed to the axles of the left and right main wheels (12), and the main wheel gear and a connection gear (24) in the lower part of the machine are connected via a chain (26) and the like. connect. A straight-running gliding mechanism for a tail-wheeled airplane having the above configuration.