Linkage mechanism of nose landing gear and vertical empennage of ultra-light aircraft
Through the linkage mechanism between the front landing gear and the vertical tail wing, the pilot uses his feet to control the steering of the aircraft, solving the problems of high maneuverability and serious tire wear of the ultra-light aircraft, achieving stable steering of the aircraft on the ground and in the air, and simplifying the rudder structure.
Patent Information
- Application Number
- CN202421708392.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-18
- Publication Date
- 2025-07-25
- Estimated Expiration
- 2034-07-18
AI Technical Summary
Existing ultralight aircraft have high handling difficulty, severe tire wear and rollover risks in steering control, especially due to the handling complexity and wheel lateral slip problems caused by the non-retractable landing gear and centralized rudder design.
The linkage mechanism between the front landing gear and the vertical tail wing is adopted, and the left foot lever and the right foot lever are connected to the front landing gear and the vertical tail wing respectively. The driver can control the steering angle of the aircraft on the ground and in the air by stepping on these pedals, realize the control of both feet, simplify the rudder structure and avoid the lateral sliding of the wheels through linkage.
It simplifies the difficulty of aircraft handling, reduces tire wear, and prevents aircraft from rolling over. It is suitable for aircraft steering control on the ground and in the air, conforms to driving habits and is easy to operate.
Smart Images
Figure CN223148685U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of ultra-light aircraft, in particular to a linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft. Background Technique
[0002] Ultra-light aircraft are characterized by small size, light weight, simple structure, simple operation, short take-off distance, and low requirements for take-off sites.
[0003] An aircraft has a nose landing gear and two main landing gears. To meet the design requirements of light weight and simple structure, current light aircraft and ultra-light aircraft usually adopt non-retractable landing gears. However, for the aircraft to turn on the ground, it is necessary to brake the wheels on one of the main landing gears. Its disadvantages are mainly reflected in three aspects: First, the steering angle is difficult to control, and over-braking on one side is likely to cause the aircraft to roll over; second, the wheels will have lateral slip, resulting in serious tire wear; third, the vertical tail is used to achieve the aircraft's turning in the air. Currently, it is necessary to turn the rudder to control the vertical tail. Due to the over-concentration of the rudder's functions, it not only increases the complexity of the rudder manufacturing but also increases the pilot's difficulty in operating the aircraft. Content of the Utility Model
[0004] In order to overcome the deficiencies in the background technique, the utility model discloses a linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft, and its purposes are:
[0005] 1. Change the aircraft's operation method, enabling the pilot to use both feet to control the steering angle of the aircraft on the ground and prevent the aircraft from rolling over;
[0006] 2. Solve the problem of serious wear of the tires due to lateral slip;
[0007] 3. Through the linkage between the nose landing gear and the vertical tail, enable the pilot to use both feet to control the steering angle of the aircraft in the air and achieve an in-air turn.
[0008] Specifically, the utility model adopts the following technical solution:
[0009] A linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft, including a cockpit, a fixed steering riser tube, and a nose landing gear that can rotate within the steering riser tube. In the cockpit, a left foot pedal rod and a right foot pedal rod are hinged. One end of the left foot pedal rod and the right foot pedal rod are respectively hinged to the nose landing gear through connecting rods, and the other ends are respectively connected to the vertical tail through pull rods or cables. Stepping on the left foot pedal rod or the right foot pedal rod can cause the nose landing gear and the vertical tail to turn simultaneously.
[0010] After implementing the above technical solution, the beneficial effects produced are:
[0011] 1. Before takeoff or after landing, the pilot can use both feet to control the steering angle of the aircraft on the ground to prevent the aircraft from tipping over. After the aircraft takes off, the pilot can use both feet to control the steering angle of the aircraft in the air to achieve an in-air turn.
[0012] 2. The control structure of the rudder is simplified, reducing the difficulty for the pilot to operate the aircraft.
[0013] 3. Since the nose landing gear can turn, each wheel only rolls and does not slip laterally, so the tires will not be severely worn due to lateral slip.
[0014] Furthermore, in the improved technical solution, when the left foot pedal rod is stepped on alone, the nose landing gear and the vertical tail can be turned to the left; when the right foot pedal rod is stepped on alone, the nose landing gear and the vertical tail can be turned to the right; when the left foot pedal rod and the right foot pedal rod are stepped on simultaneously with the same force, the nose landing gear and the vertical tail can be in the forward state.
[0015] After adopting the above technical solution, the beneficial effects are as follows: Such a control method is more in line with people's driving habits and is not prone to misoperation. Particularly important is the control method of the linkage between the nose landing gear and the vertical tail, which is applicable not only to the stage when the aircraft is taxiing on the ground but also to the stage when the aircraft is flying in the air.
[0016] When the aircraft is taxiing on the ground, when the left foot pedal rod is stepped on alone, the nose landing gear can be turned to the left, and at this time the aircraft turns to the left; when the right foot pedal rod is stepped on alone, the nose landing gear can be turned to the right, and at this time the aircraft turns to the right; when the left foot pedal rod and the right foot pedal rod are stepped on simultaneously with the same force, the nose landing gear can be in the forward state, and at this time the aircraft taxis straight.
[0017] When the aircraft is flying in the air, when the left foot pedal rod is stepped on alone, the vertical tail can be turned to the left, and at this time the aircraft turns to the left; when the right foot pedal rod is stepped on alone, the vertical tail can be turned to the right, and at this time the aircraft turns to the right; when the left foot pedal rod and the right foot pedal rod are stepped on simultaneously with the same force, the vertical tail can be in the forward state, and at this time the aircraft flies straight.
[0018] Furthermore, in the improved technical solution, both the left foot pedal rod and the right foot pedal rod are composed of a pedal cross bar, a rotating shaft and a rocker arm. Among them, the rotating shaft is horizontally hinged on the floor of the cockpit through a shaft sleeve. The pedal cross bar is located above the rotating shaft, and the rocker arm is located below the rotating shaft; the rocker arm is hinged to the connecting rod, and the pedal cross bar is connected to the pull rod or wire rope.
[0019] After adopting the above technical solution, the beneficial effects are as follows: Such a design is simple, reliable and easy to operate, and can generate a large torsional moment on the nose landing gear and the vertical tail.
[0020] Further improve the technical solution. Baffles are provided at both ends of the footrest crossbar, and the pull rod or wire is connected to the outermost baffle.
[0021] After adopting the above technical solution, the beneficial effects are as follows: The baffle can prevent the driver from slipping sideways when stepping on the footrest crossbar. Secondly, the baffle is provided with through holes, which is beneficial to connecting the pull rod or wire.
[0022] Further improve the technical solution. There are two footrest crossbars on the left footrest rod and the right footrest rod, which are respectively arranged at both ends of the rotating shaft; let the leftmost footrest crossbar on the left footrest rod be A, the rightmost footrest crossbar be C, the leftmost footrest crossbar on the right footrest rod be B, and the rightmost footrest crossbar be D. Then the footrest crossbars are arranged in the order of ABCD from left to right.
[0023] After adopting the above technical solution, the beneficial effects are as follows: This technical solution is applicable to the situation where there are two driver seats, the main driver seat and the co-driver seat, in the cockpit, and both the main driver and the co-driver have driving authority. Both the main driver and the co-driver can step on the left footrest rod and the right footrest rod to turn the front landing gear and the vertical tail simultaneously.
[0024] Further improve the technical solution. A steering wheel is provided on the front landing gear, and ball head bolts are fixed on the left and right sides of the steering wheel. The ball heads of the ball head bolts are hinged to the ball sockets at the ends of the connecting rod.
[0025] After adopting the above technical solution, the beneficial effects are as follows: The protruding steering wheel and ball head bolts are beneficial to realizing the hinge connection between the connecting rod and the front landing gear. In addition, the hinge connection between the ball head bolt and the ball socket of the connecting rod has multiple degrees of freedom and can realize spatial transmission.
[0026] Further improve the technical solution. The ball socket is screwed on the connecting rod, and the ball socket is adjustable in the length direction of the connecting rod.
[0027] After adopting the above technical solution, the beneficial effects are as follows: Such a design can shorten or increase the length of the connecting rod, and further adjust the stepping angles of the left footrest rod and the right footrest rod.
[0028] Further improve the technical solution. Pull springs are installed on the left and right sides of the steering wheel. When the driver does not step on the left footrest rod or the right footrest rod, a pair of pull springs generate torsional moments with opposite directions of rotation on the front landing gear, so that the front wheels on the front landing gear are in the forward state.
[0029] After adopting the above technical solution, the beneficial effects are as follows: During straight flight, a pair of pull springs can ensure that the front wheels and the vertical tail are in the forward state, and the driver does not need to step on the left footrest rod and the right footrest rod.
[0030] Further improve the technical solution. The vertical tail is hinged to the tail of the aircraft. There are a left connecting plate and a right connecting plate at the bottom of the vertical tail. The left foot pedal is connected to the left connecting plate through a pull rod or a wire rope, and the right foot pedal is connected to the right connecting plate through a pull rod or a wire rope.
[0031] After adopting the above technical solution, the beneficial effects are as follows: When stepping on the left foot pedal alone, the nose landing gear and the vertical tail can turn to the left; when stepping on the right foot pedal alone, the nose landing gear and the vertical tail can turn to the right; when stepping on the left foot pedal and the right foot pedal simultaneously with the same force, the nose landing gear and the vertical tail can be in the forward state.
[0032] Further improve the technical solution. The wire rope is a stay wire with a flexible sheath.
[0033] After adopting the above technical solution, the beneficial effects are as follows: The pull rod is a rigid rod, which can bear both tensile force and compressive force, but it cannot be routed along the fuselage in a curved manner. The wire rope is a flexible part, which can only bear tensile force and also cannot be routed along the fuselage in a curved manner. The stay wire with a flexible sheath can be routed along the fuselage in a curved manner, which is beneficial to improving the utilization rate of the internal space of the aircraft. Brief Description of the Drawings
[0034] Figure 1 Fig. shows the overall structural schematic diagram of the linkage mechanism in Embodiment 1.
[0035] Figure 2 Fig. shows the Figure 1 partial structural schematic diagram of the linkage mechanism in
[0036] Figure 3 Fig. shows the structural schematic diagram of the right foot pedal in Embodiment 1.
[0037] Figure 4 Fig. shows the structural schematic diagram of the connection between the vertical tail and the wire rope.
[0038] Figure 5 Fig. shows the structural schematic diagram of the linkage mechanism in Embodiment 2.
[0039] Figure 6 Fig. shows the structural schematic diagram of the right foot pedal in Embodiment 2.
[0040] Figure 7 Fig. shows the structural schematic diagram of the linkage mechanism in Embodiment 3.
[0041] In the attached drawings: 1, cockpit; 2, steering column; 3, front landing gear; 3.1, steering wheel; 3.2, front wheel; 3.3, ball head bolt; 4, connecting rod; 5, left foot pedal rod; 6, right foot pedal rod; 6.1, foot pedal cross bar; 6.2, rotating shaft; 6.3, rocker arm; 6.4, baffle; 7, bushing; 8, tension spring; 9, vertical fin; 10, cable; 11, left connecting plate; 12, right connecting plate; 13, tightener. Detailed implementation manners
[0042] The preferred implementation manners of the present utility model will be described below with reference to the attached drawings. Those skilled in the art should understand that these implementation manners are only used to explain the technical principle of the present utility model and are not intended to limit the protection scope of the present utility model. It should be noted that in the description of the present utility model, the terms indicating directions or positional relationships such as "front", "rear", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the attached drawings. This is only for convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, so it cannot be understood as a limitation to the present utility model. It should also be noted that in the description of the present utility model, unless otherwise clearly specified and limited, the terms "installation", "connection", "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, or the internal communication of two elements. For those skilled in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.
[0043] Embodiment 1:
[0044] Refer to the attached Figure 1 ... It can be seen from the attached Figure 1 drawings that the linkage mechanism includes a cockpit 1, a steering column 2 fixed to the front end of the cockpit 1, a vertical fin 9 hinged to the tail of the aircraft, and a front landing gear 3 installed in the steering column 2. The front landing gear 3 mainly consists of a steering shaft, a shock absorber, a front fork, and a front wheel 3.2. Among them, the steering shaft can rotate left and right in the steering column 2.
[0045] To solve the problems in the background technology, a left foot pedal rod 5 and a right foot pedal rod 6 are hinged in the cockpit 1. One ends of the left foot pedal rod 5 and the right foot pedal rod 6 are respectively hinged to the front landing gear 3 through a connecting rod 4, and the other ends are respectively connected to the vertical fin 9 through a cable 10. Stepping on the left foot pedal rod 5 or the right foot pedal rod 6 can make the front landing gear 3 and the vertical fin 9 turn simultaneously.
[0046] Refer to the attached Figure 2 drawings and Figure 3 ... It can be seen from the attachedFigure 2 and the attached Figure 3 As can be seen, the left footrest lever 5 and the right footrest lever 6 are both composed of a footrest cross bar 6.1, a rotating shaft 6.2 and a rocker arm 6.3. Among them, the rotating shaft 6.2 is horizontally hinged to the floor of the cockpit 1 through a bushing 7. The footrest cross bar 6.1 is located above the rotating shaft 6.2, and the rocker arm 6.3 is located below the rotating shaft 6.2, and the rocker arm 6.3 is hinged to the connecting rod 4. Baffles 6.4 are provided at both ends of the footrest cross bar 6.1, and through holes are provided on the baffles 6.4. The baffles 6.4 have two functions. One is to prevent the driver from slipping sideways when stepping on the footrest cross bar 6.1, and the other is to connect the cable 10.
[0047] A protruding steering wheel 3.1 is provided on the nose landing gear 3. Ball head bolts 3.3 are fixed on the left and right sides of the steering wheel 3.1. The ball heads of the ball head bolts 3.3 are hinged to the ball sockets at the ends of the connecting rod 4. Since the hinge between the ball head bolt 3.3 and the ball socket of the connecting rod 4 has multiple degrees of freedom, when stepping on the left footrest lever 5 or the right footrest lever 6, the nose landing gear 3 can be driven to turn through the connecting rod 4. At the same time, the vertical tail 9 can be driven to turn through the cable 10.
[0048] Furthermore, ball sockets are screwed at both ends of the connecting rod 4, and the ball sockets are adjustable in the length direction of the connecting rod 4. Obviously, such a design can shorten or increase the effective length of the connecting rod 4, and further adjust the stepping angles of the left footrest lever 5 and the right footrest lever 6.
[0049] Refer to the attached Figure 4 . From the attached Figure 4 As can be seen, the vertical tail 9 is hinged to the tail of the aircraft. A left connecting plate 11 and a right connecting plate 12 are fixedly connected to the bottom of the vertical tail 9. The left footrest lever 5 is connected to the left connecting plate 11 through a cable 10 and a tensioner 13. The right footrest lever 6 is connected to the right connecting plate 12 through a cable 10 and a tensioner 13. Both ends of the tensioner 13 have a threaded structure, and its function is to tighten the cable 10 and eliminate the dead travel.
[0050] When the aircraft is taxiing on the ground, when stepping on the left footrest lever 5 alone, the nose landing gear 3 can be turned to the left, and at this time the aircraft turns to the left; when stepping on the right footrest lever 6 alone, the nose landing gear 3 can be turned to the right, and at this time the aircraft turns to the right; when stepping on the left footrest lever 5 and the right footrest lever 6 simultaneously and with the same force, the nose landing gear 3 can be in a forward state, and at this time the aircraft taxis straight.
[0051] When the aircraft is flying in the air, when stepping on the left footrest lever 5 alone, the vertical tail 9 can be turned to the left, and at this time the aircraft turns to the left; when stepping on the right footrest lever 6 alone, the vertical tail 9 can be turned to the right, and at this time the aircraft turns to the right; when stepping on the left footrest lever 5 and the right footrest lever 6 simultaneously and with the same force, the vertical tail 9 can be in a forward state, and at this time the aircraft flies straight.
[0052] Obviously, such a control method is more in line with people's driving habits and is not prone to misoperation. Moreover, the steering angle of the aircraft on the ground is easy to control. The wheels only roll and do not slip laterally, so the tires will not be severely worn due to lateral slip. Particularly importantly, the control method in which the nose landing gear 3 is linked with the vertical tail 9 is applicable not only to the taxiing stage of the aircraft on the ground but also to the flight stage of the aircraft in the air.
[0053] It should be noted that the cable 10 can also be replaced by a rod. The rod is a rigid rod that can bear both tensile force and compressive force. However, both the cable and the rod must be in a straight state, which will occupy the internal space of the aircraft. Therefore, a better technical solution is to use a tension cable with a flexible sheath, which can be routed along the fuselage in a curved manner, facilitating the improvement of the utilization rate of the internal space of the aircraft.
[0054] Embodiment 2:
[0055] Refer to the attached Figure 5 and the attached Figure 6 In this embodiment, different from Embodiment 1, there are two pedal crossbars 6.1 on both the left pedal lever 5 and the right pedal lever 6, which are respectively arranged at both ends of the rotating shaft 6.2.
[0056] Let the pedal crossbar 6.1 on the left side of the left pedal lever 5 be A, the pedal crossbar 6.1 on the right side be C, the pedal crossbar 6.1 on the left side of the right pedal lever 6 be B, and the pedal crossbar 6.1 on the right side be D. Then the pedal crossbars 6.1 are arranged in the order of A, B, C, D from left to right.
[0057] The technical solution in this embodiment is applicable to the situation where there are two pilot seats, a main seat and a co-pilot seat, in the cockpit 1 and both the main and co-pilot seats have driving authority. Specifically, the left and right feet of the left pilot step on the pedal crossbars 6.1A and 6.1B respectively, and the left and right feet of the right pilot step on the pedal crossbars 6.1C and 6.1D respectively. In this way, both the main and co-pilot can operate the left pedal lever 5 and the right pedal lever 6 to turn the nose landing gear 3 and the vertical tail 9.
[0058] Embodiment 3:
[0059] Refer to the attached Figure 7 In this embodiment, different from Embodiment 2, the same-specification tension springs 8 are symmetrically installed on both the left and right sides of the steering wheel 3.1. When the driver does not step on the left pedal lever 5 or the right pedal lever 6, a pair of tension springs 8 generate torsional moments with opposite directions of rotation on the nose landing gear 3, making the nose landing gear 3 and the vertical tail 9 in a forward state.
[0060] In this way, when the aircraft is flying in a straight line, a pair of tension springs 8 can ensure that the front wheel 3.2 and the vertical tail 9 are in the forward state. At this time, the pilot does not need to step on the left foot pedal 5 and the right foot pedal 6, liberating both feet. When the aircraft takes off or lands, the pilot does not need to use a large stepping force to keep the front wheel 3.2 in the forward state. In addition, the front wheel 3.2 in the forward state has a small windward area, which can reduce wind resistance.
[0061] The parts not described in detail are the prior art. Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The protection scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A linkage mechanism for the nose landing gear and vertical tail of an ultra-light aircraft, comprising a cockpit, a fixed steering riser, and a nose landing gear capable of rotating within the steering riser, characterized in that: A left foot pedal rod and a right foot pedal rod are hinged inside the cockpit. One ends of the left foot pedal rod and the right foot pedal rod are respectively hinged to the nose landing gear through connecting rods, and the other ends are respectively connected to the vertical tail through pull rods or cables. Stepping on the left foot pedal rod or the right foot pedal rod can turn the nose landing gear and the vertical tail simultaneously.
2. The linkage mechanism between the nose landing gear and the vertical tail of a super-light aircraft as claimed in claim 1, characterized in that: When stepping on the left foot pedal rod alone, the nose landing gear and the vertical tail can turn to the left; when stepping on the right foot pedal rod alone, the nose landing gear and the vertical tail can turn to the right; when stepping on the left foot pedal rod and the right foot pedal rod simultaneously with the same force, the nose landing gear and the vertical tail can be in the forward state.
3. The linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft as claimed in claim 1, characterized in that: Both the left foot pedal rod and the right foot pedal rod are composed of a foot pedal cross bar, a rotating shaft and a rocker arm. Among them, the rotating shaft is horizontally hinged to the floor of the cockpit through a shaft sleeve. The foot pedal cross bar is located above the rotating shaft, and the rocker arm is located below the rotating shaft; the rocker arm is hinged to the connecting rod, and the foot pedal cross bar is connected to the pull rod or cable.
4. The linkage mechanism between the nose landing gear and the vertical tail of a super-light aircraft as claimed in claim 3, characterized in that: Baffles are provided at both ends of the foot pedal cross bar, and the pull rod or cable is connected to the baffle on the outer side.
5. A linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft according to claim 3 or 4, characterized in that: There are two foot pedal cross bars on both the left foot pedal rod and the right foot pedal rod, which are respectively arranged at both ends of the rotating shaft; let the foot pedal cross bar on the left side of the left foot pedal rod be A, and the foot pedal cross bar on the right side be C, the foot pedal cross bar on the left side of the right foot pedal rod be B, and the foot pedal cross bar on the right side be D, then each foot pedal cross bar is arranged in the order of ABCD from left to right.
6. The linkage mechanism between the nose landing gear and the vertical tail of a ultra-light aircraft as claimed in claim 1, characterized in that: A steering wheel is provided on the nose landing gear, and ball head bolts are fixed on the left and right sides of the steering wheel. The ball heads of the ball head bolts are hinged to the ball sockets at the ends of the connecting rods.
7. The linkage mechanism between the nose landing gear and the vertical tail of a super-light aircraft according to claim 6, characterized in that: The ball socket is screwed on the connecting rod, and the ball socket is adjustable in the length direction of the connecting rod.
8. The linkage mechanism between the nose landing gear and the vertical tail of a ultra-light aircraft according to claim 6, characterized in that: Pull springs are installed on the left and right sides of the steering wheel. When the driver does not step on the left foot pedal rod or the right foot pedal rod, a pair of pull springs generate torsional moments with opposite directions of rotation on the nose landing gear, so that the front wheels on the nose landing gear are in the forward state.
9. The linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft as described in claim 2, characterized in that: The vertical tail is hinged to the tail of the aircraft. Left and right connecting plates are provided at the bottom of the vertical tail. The left foot pedal rod is connected to the left connecting plate through a pull rod or cable, and the right foot pedal rod is connected to the right connecting plate through a pull rod or cable.
10. The linkage mechanism between the nose landing gear and the vertical tail of an ultra-light aircraft according to claim 9, characterized in that: The cable is a tension cable with a flexible sheath.