Model airplane structure

Abstract

The utility model relates to a model plane structure which comprises a paddle mechanism and a plane body assembly, the paddle mechanism comprises a paddle shaft seat and at least two paddles, the paddle shaft seat is in running fit with the plane body assembly, the paddles are hinged to the paddle shaft seat, and the paddles can be unfolded or folded relative to the paddle shaft seat; the paddle shaft seat comprises a paddle shaft part and two connecting parts arranged on the periphery of the paddle shaft part, and the number of the connecting parts is in one-to-one correspondence with that of the paddles; each connecting part comprises two fixing lugs which are oppositely arranged at an interval, and the roots of the paddles are clamped between the two fixing lugs and are rotationally connected with the fixing lugs, so that the paddles move along with the paddle shaft seat and can rotate relative to the paddle shaft seat; the propeller blades have a first state that the propeller blades rotate along with the propeller shaft seat and are unfolded relative to the propeller shaft seat when the model aircraft lifts off, so that the climbing height of the model aircraft in the flying process is increased, and a second state that the propeller blades stand along with the propeller shaft seat and are folded relative to the propeller shaft seat when the model aircraft glides is facilitated. Therefore, the air resistance in the gliding process of the model plane is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of model aircraft, in particular to a model aircraft structure. Background Art

[0002] In the rubber band powered model airplanes currently available on the market, some technical structural problems of the model airplanes affect the speed of the model airplanes gliding forward; for example, most of the model airplanes in the prior art have a fixed propeller blade structure, so that the propeller blades of the model airplane always remain in an open state when the model airplane is in the gliding stage, thereby increasing the air resistance and reducing the lift generated by the wing; and when the lift of the model airplane decreases, the gliding altitude will sink. Utility Model Content

[0003] The technical problem to be solved by the utility model is to overcome the defects of short gliding time and distance of the model airplane in the gliding stage in the competition in the prior art, thereby providing a model airplane structure.

[0004] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0005] A model aircraft structure, comprising: a blade mechanism, a fuselage assembly,

[0006] The blade mechanism includes a blade shaft seat and at least two blades.

[0007] The propeller shaft seat is rotatably matched with the fuselage assembly, the propeller blade is hinged to the propeller shaft seat, and the propeller blade can be unfolded or folded relative to the propeller shaft seat;

[0008] The paddle shaft seat includes a paddle shaft portion and two connecting portions arranged on the outer periphery of the paddle shaft portion, and the number of the connecting portions is arranged in a one-to-one correspondence with the paddle blades; each of the connecting portions includes two relatively spaced fixing ears, and the root of the paddle blade is clamped between the two fixing ears and rotatably connected to the fixing ears, so that the paddle blade moves with the paddle shaft seat and can rotate relative to the paddle shaft seat.

[0009] Preferably, the fixing ear is provided with a fixing hole whose axis coincides with the axis, the root of the blade is provided with a connecting hole, and the root of the blade is located between the two fixing ears; it also includes a propeller shaft, the middle part of the propeller shaft is passed through the connecting hole, and the two ends are rotatably arranged in one of the fixing holes respectively; the aperture of the fixing hole is L1, the aperture of the connecting hole is L2, and the outer diameter of the propeller shaft is L3, satisfying the following relationship: L1>L3≥L2.

[0010] Preferably, one end of the paddle shaft is provided with a positioning opening.

[0011] The fuselage assembly includes a head seat, a rotating shaft, a frame and an elastic power part;

[0012] The headstock is fixed on the frame, and the rotating shaft is rotatably connected to the headstock.

[0013] One end of the rotating shaft is provided with a bending portion, and the other end is provided with a hook; one end of the elastic power member is fixed to the frame, and the other end is fixedly connected to the hook;

[0014] The paddle shaft portion is sleeved on the rotating shaft, and the bent portion is fixedly embedded in the positioning opening.

[0015] Preferably, the head seat further comprises a shaft sleeve, which is disposed in the head seat and has an interference fit with the head seat, and the shaft sleeve is rotatably connected to the rotating shaft.

[0016] Preferably, it also includes a gasket, which is sleeved on the rotating shaft and located between the propeller shaft seat and the head seat.

[0017] Preferably, the frame includes a fuselage rod, a tail hook, a tail rod, a tail wing platform and a wing part;

[0018] The tail rod is movably connected to the fuselage rod, and the tail rod can be extended or retracted relative to the fuselage rod;

[0019] The nose seat is fixedly connected to one end of the fuselage rod away from the tail rod, the tail wing platform is fixedly connected to one end of the tail rod away from the fuselage rod, the wing part and the tail hook are both arranged on the fuselage rod, and the wing part is located between the nose seat and the tail hook;

[0020] One end of the elastic power member away from the hook is connected to the tail hook.

[0021] Preferably, the wing portion includes a wing pressure plate, a wing bottom bracket and a wing bracket;

[0022] One side of the wing base is fixedly connected to the wing bracket, and the other side is fixedly connected to the wing pressure plate, and the wing is fixed between the wing pressure plate and the wing base;

[0023] In addition, at least two mounting holes are provided on the side of the wing bracket facing away from the wing base, and the wing bracket is mounted on the fuselage rod between the nose base and the tail hook through the two mounting holes.

[0024] Preferably, it also includes a fairing, which is arranged on a side of the propeller shaft seat having a positioning opening and is fixedly connected to the propeller shaft seat.

[0025] Preferably, the elastic power member includes a rubber band member.

[0026] Compared with the prior art, the beneficial effects of the present invention are:

[0027] A model aircraft structure provided in the above technical solution hinges the propeller blades to the propeller shaft seat so that the propeller blades can be unfolded or folded relative to the propeller shaft seat; through the rotational cooperation relationship between the propeller shaft seat and the fuselage assembly, the propeller blades have a first state in which they rotate with the propeller shaft seat when the model aircraft is launched and are unfolded relative to the propeller shaft seat, thereby helping to increase the climbing height of the model aircraft during flight, and a second state in which they remain stationary with the propeller shaft seat when the model aircraft is gliding and are folded relative to the propeller shaft seat, thereby reducing the air resistance of the model aircraft during gliding and effectively extending the gliding time and gliding distance of the model aircraft in the air. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0029] Figure 1 The present invention is a schematic diagram of the overall structure of a model airplane provided in one embodiment of the present invention.

[0030] Figure 2 for Figure 1 Schematic diagram of the exploded structure of the blade mechanism shown.

[0031] Figure 3 for Figure 1 The schematic diagram of the structure of the rack is shown.

[0032] Figure 4 for Figure 1 Schematic diagram of the exploded structure of the wing section is shown.

[0033] Figure 5 It is a schematic diagram of the structure of the wing part matching the wing.

[0034] Figure 6 A partial schematic diagram of the wing.

[0035] Description of reference numerals:

[0036] 1. Fairing; 2. Propeller shaft seat; 21. Propeller shaft; 211. Positioning port; 22. Fixing ear; 221. Fixing hole; 3. Bushing; 4. Gasket; 5. Nose seat; 6. Rotating shaft; 61. Hook; 7. Propeller shaft; 8. Propeller blade; 81. Connecting hole; 9. Wing pressure plate; 91. Second clamp; 10. Wing base; 101. Second clamp; 102. First clamp; 11. Wing bracket; 111. Mounting hole; 112. First clamp; 12. Fuselage rod; 13. Tail hook; 131. First connecting part; 132. Second connecting part; 14. Tail rod; 15. Tail wing platform; 16. Upper reverse gasket; 17. Elastic power part; 18. Wing. DETAILED DESCRIPTION

[0037] The technical solution of the utility model will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0038] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0039] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "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 a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] The utility model embodiment provides a model aircraft structure, such as Figure 1 and Figure 2As shown, it includes: a blade mechanism and a fuselage assembly; wherein the blade mechanism includes a propeller shaft seat 2 and at least two propeller blades 8, the propeller shaft seat 2 is rotatably matched with the fuselage assembly, and the propeller blades 8 are hinged to the propeller shaft seat 2, and based on the hinged relationship, the propeller blades 8 can be rotated relative to the propeller shaft seat 2 to be adjusted to an unfolded state or a folded state; specifically, the propeller shaft seat 2 includes a propeller shaft portion 21, and two connecting portions arranged on the periphery of the propeller shaft portion 21, and the connecting portions are used to be hinged with the propeller blades 8, that is, the number of the connecting portions is arranged one by one corresponding to the propeller blades 8; each connecting portion includes two fixing ears 22 arranged relatively spaced apart, and the root of the propeller blade 8 is clamped between the two fixing ears 22 and It is rotatably connected relative to the fixed ear 22 so that the blade 8 can follow the movement of the shaft seat and can rotate relative to the propeller shaft seat 2; then, when the model aircraft is launched, the blade 8 rotates with the propeller shaft seat 2 relative to the fuselage assembly, and under the action of the rotational inertia force, the blade 8 presents a first state of being unfolded relative to the propeller shaft seat 2, thereby providing lift for the model aircraft to take off; when the model aircraft enters the gliding stage, the blade 8 stays still relative to the fuselage assembly with the propeller shaft seat 2, and under the action of air resistance, the blade 8 presents a second state of being folded relative to the propeller shaft seat 2, thereby reducing the resistance of the model aircraft during the gliding process, and effectively extending the gliding time and gliding distance of the model aircraft.

[0041] The propeller blade 8 is hinged to the propeller shaft seat 2 so that the propeller blade 8 can be unfolded or folded relative to the propeller shaft seat 2; through the rotational cooperation relationship between the propeller shaft seat 2 and the fuselage assembly, the propeller blade 8 has a first state in which it rotates with the propeller shaft seat 2 when the model aircraft is launched and is unfolded relative to the propeller shaft seat 2, thereby helping to increase the climbing height of the model aircraft during flight, and a second state in which it stays still with the propeller shaft seat 2 when the model aircraft is gliding and is folded relative to the propeller shaft seat 2, thereby reducing the air resistance of the model aircraft during gliding, and effectively extending the gliding time and gliding distance of the model aircraft in the air.

[0042] like Figure 2 As shown, a fixing hole 221 with an axial line coincident with the fixing ear 22 is provided. It can be understood that a connecting hole 81 corresponding to the fixing hole 221 is also provided at the root of the blade 8, and the root of the blade 8 is located between the two fixing ears 22; further, a paddle shaft 7 is also provided at the connecting portion, and the middle part of the paddle shaft 7 is passed through the connecting hole 81, and the two ends of the paddle shaft 7 are rotatably arranged in the two fixing holes 221 respectively; wherein, the aperture of the fixing hole 221 is L1, the aperture of the connecting hole 81 is L2, and the outer diameter of the paddle shaft 7 is L3, and the three satisfy the following relationship: L1>L3≥L2.

[0043] Furthermore, a positioning hole 211 is also provided at one end of the propeller shaft portion 21, and the fuselage assembly includes a head seat 5, a rotating shaft 6, a frame and an elastic power member 17; and the head seat 5 is fixed on the frame, and the rotating shaft 6 is rotatably connected with the head seat 5 for transmitting power; specifically, a bending portion is provided at one end of the rotating shaft 6, and a hook 61 is provided at the other end, and the elastic power member 17 is used to provide power output for the model aircraft to take off, and one end of the elastic power member 17 is fixedly connected to the frame, and the other end is fixedly connected to the hook 61 of the rotating shaft 6. Preferably, the elastic power member 17 includes a rubber band; power transmission is then completed through the rotating shaft 6; further, the propeller shaft portion 21 of the propeller shaft seat 2 is sleeved on the rotating shaft 6, and the bending portion is correspondingly fixedly embedded in the positioning hole 211 of the propeller shaft portion 21, so that the rotating shaft 6 is fixedly connected to the propeller shaft seat 2.

[0044] When the elastic power member 17 outputs power, the rotating shaft 6 will rotate in the head seat 5 under the drive of the elastic power member 17. Based on the fixed embedding relationship between the bending portion of the rotating shaft 6 and the positioning opening 211 on the propeller shaft portion 21, the rotating shaft 6 will link the propeller shaft seat 2 and the blade 8 hinged on the propeller shaft seat 2 to rotate; thereby, under the action of the rotational inertia force, the blade 8 presents a first state of being unfolded relative to the propeller shaft seat 2; when the power of the elastic power member 17 is exhausted, the rotation speed of the propeller shaft seat 2 will gradually decrease to stop rotating, and the blade 8 will stay still with the propeller shaft seat 2 relative to the fuselage assembly, and present a second state of being folded relative to the propeller shaft seat 2.

[0045] Furthermore, in order to reduce the wear of the rotating shaft 6 on the head seat 5 during power transmission, the head seat 5 also includes a sleeve 3, and the sleeve 3 is arranged in the head seat 5 and has an interference fit with the head seat 5, and the rotating shaft 6 is rotatably connected with the sleeve 3; preferably, the sleeve 3 includes a wear-resistant metal material; at the same time, the reduced wear of the head seat 5 can also make the propeller shaft seat 2 and the propeller blade 8 rotate more stably, thereby helping the model aircraft to better increase the ascent altitude during the climbing process. Accordingly, the higher the climbing altitude of the model aircraft, the longer the gliding distance, that is, the time, when entering the gliding stage.

[0046] In order to reduce the friction loss between the propeller shaft seat 2 and the head seat 5 during rotation, the fuselage assembly also includes a gasket 4; specifically, the gasket 4 is sleeved on the rotating shaft 6, and the gasket 4 is located between the propeller shaft seat 2 and the head seat 5 to avoid direct contact and fit between the propeller shaft seat 2 and the head seat 5; on the one hand, the lubrication effect is activated to reduce the friction between the two, and on the other hand, the power output loss of the elastic power part 17 is reduced; preferably, the gasket 4 includes a metal material, and during the setting process, the side of the gasket 4 facing the head seat 5 is usually in contact with the part of the sleeve 3 extending out of the head seat 5.

[0047] like Figure 3As shown, the frame includes a fuselage rod 12, a tail hook 13, a tail rod 14, a tail wing platform 15 and a wing part; the tail rod 14 is movably plugged with the fuselage rod 12, and the tail rod 14 can extend or retract relative to the fuselage rod 12, and the nose seat 5 is fixedly connected to the end of the fuselage rod 12 away from the tail rod 14, the tail wing platform 15 is fixedly connected to the end of the tail rod 14 away from the fuselage rod 12, the wing part and the tail hook 13 are both arranged on the fuselage rod 12, and the wing part is located between the nose seat 5 and the tail hook 13; the end of the elastic power member 17 away from the hook 61 is hung on the tail Hook 13; specifically, in order to facilitate the adjustment and fixation of the tail rod 14 relative to the fuselage rod 12, the tail hook 13 includes an integrally formed first connecting portion 131 and a second connecting portion 132, and the connection diameter of the first connecting portion 131 is larger than the second connecting portion 132, the first connecting portion 131 is fixedly connected to the fuselage rod 12, and the tail rod 14 is movably inserted in the fuselage rod 12 through the second connecting portion 132; and, based on the matching relationship between the tail rod 14 and the second connecting portion 132, the tail rod 14 can be fixed relative to the fuselage rod 12 through the second connecting portion 132.

[0048] When adjusting the center of gravity of traditional model airplanes in the later stage, the wing part is usually adjusted by pulling it, and the wing part is very easy to be skewed during the pulling process; therefore, it is necessary to pull it repeatedly for correction during the adjustment process, and the repeated pulling will cause the wing part to deform, and in severe cases, it will cause the wing part to be damaged; it is understandable that the overall length of the frame can be adjusted through the matching relationship between the tail rod 14 and the fuselage rod 12, and then the center of gravity of the model airplane can be fine-tuned. On the one hand, the adjustment steps of the center of gravity of the model airplane are optimized, making it easier for users, especially novice users, to debug; on the other hand, the damage to the model airplane during the adjustment process can be reduced, which is convenient for the overall adjustment and maintenance of the model airplane; in addition, based on the matching relationship between the tail rod 14 and the fuselage rod 12, a test adjustment experiment can be carried out, and the changes in the flight attitude of the model airplane can be observed through the amplitude of multiple adjustments (the distance that the tail rod 14 extends or contracts relative to the fuselage rod 12), thereby increasing the playability of the model airplane.

[0049] like Figure 4 and Figure 5 As shown, the wing portion includes a wing 18, a wing pressure plate 9, a wing base 10 and a wing bracket 11; wherein, in the prior art, the assembly between the wing and the wing pressure plate 9, the wing base 10 and the wing bracket 11 is mostly fixed by gluing; which makes it very inconvenient to adjust or replace the wing 18 relative to the wing pressure plate 9, the wing base 10 and the wing bracket 11; and, the wing 18 is mostly made of soft material, and the gluing method can easily cause the wing 18 to tear during the adjustment or replacement process, which is not convenient for the secondary use of the wing 18.

[0050] In order to facilitate the disassembly and assembly of the wing 18, the wing pressure plate 9, the wing bottom bracket 10 and the wing bracket 11, one side of the wing bottom bracket 10 is fixedly connected with the wing bracket 11, and the other side is fixedly connected with the wing pressure plate 9, and the wing 18 is fixed between the wing pressure plate 9 and the wing bottom bracket 10; specifically, a plurality of first bayonet holes 102 and second bayonet holes 101 are provided on the wing bottom bracket 10, and the wing bracket 11 is provided with a first clamping head 112 corresponding to the first bayonet hole 102, and the wing pressure plate 9 is provided with a second clamping head 9 corresponding to the second bayonet hole 101. 1; and the first clamp 112 is clamped with the first clamp port 102 to fix the wing bracket 11 and the wing base 10, and the second clamp 91 is clamped with the second clamp port 101 to fix the wing 18 between the wing bracket 11 and the wing pressure plate 9; further, in order to facilitate the assembly of the wing part and the frame, at least two mounting holes 111 are further provided on the side of the wing bracket 11 facing away from the wing base 10, and the wing bracket 11 is mounted on the fuselage rod 12 between the head seat 5 and the tail hook 13 through the two mounting holes 111.

[0051] Preferably, the blade mechanism is also provided with a fairing 1, and the fairing 1 is arranged on a side of the propeller shaft seat 2 having a positioning opening 211, and is fixedly connected to the propeller shaft seat 2, specifically, it can be fixed by threaded connection or clamping; on the one hand, it can protect the propeller shaft seat 2 to prevent the propeller shaft seat 2 from being hit when the model aircraft lands, and on the other hand, the surface of the fairing 1 is streamlined, which is beneficial to reduce the air resistance to the model aircraft.

[0052] like Figure 5 and Figure 6 As shown, the structure is also provided with at least two upper reverse fixing plates 16, and the upper reverse fixing plates 16 are fixed on the wings 18 accordingly, and are used to adjust the angle of the wings 18 to change the flow of airflow, thereby enhancing the lift and stability of the model aircraft, so that the model aircraft can fly more smoothly in the air.

[0053] The above-mentioned implementation modes are only preferred implementation modes of the present invention, and cannot be used to limit the protection scope of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A model aircraft structure, characterized in that: include: Propeller mechanism, fuselage components, The blade mechanism comprises a blade shaft seat and at least two blades. The propeller shaft seat is rotatably matched with the fuselage assembly, the propeller blade is hinged to the propeller shaft seat, and the propeller blade can be unfolded or folded relative to the propeller shaft seat; The paddle shaft seat includes a paddle shaft portion and two connecting portions arranged on the outer periphery of the paddle shaft portion, and the number of the connecting portions is arranged in a one-to-one correspondence with the paddle blades; each of the connecting portions includes two relatively spaced fixing ears, and the root of the paddle blade is clamped between the two fixing ears and rotatably connected to the fixing ears, so that the paddle blade moves with the paddle shaft seat and can rotate relative to the paddle shaft seat.

2. The model aircraft structure according to claim 1, characterized in that: The fixing ear is provided with a fixing hole whose axis coincides with the axis, and the root of the blade is provided with a connecting hole, and the root of the blade is located between the two fixing ears; it also includes a propeller shaft, the middle part of which is passed through the connecting hole, and the two ends are rotatably arranged in one of the fixing holes respectively; the aperture of the fixing hole is L1, the aperture of the connecting hole is L2, and the outer diameter of the propeller shaft is L3, satisfying the following relationship: L1>L3≥L2.

3. The model aircraft structure according to claim 2, characterized in that: One end of the paddle shaft is provided with a positioning opening. The fuselage assembly includes a head seat, a rotating shaft, a frame and an elastic power part; The headstock is fixed on the frame, and the rotating shaft is rotatably connected to the headstock. One end of the rotating shaft is provided with a bending portion, and the other end is provided with a hook; one end of the elastic power member is fixed to the frame, and the other end is fixedly connected to the hook; The paddle shaft portion is sleeved on the rotating shaft, and the bent portion is fixedly embedded in the positioning opening.

4. The model aircraft structure according to claim 3, characterized in that: The headstock further comprises a shaft sleeve, which is arranged in the headstock and has an interference fit with the headstock, and the shaft sleeve is rotatably connected with the rotating shaft.

5. The model aircraft structure according to claim 3, characterized in that: It also includes a gasket, which is sleeved on the rotating shaft and located between the propeller shaft seat and the machine head seat.

6. The model aircraft structure according to claim 3, characterized in that: The frame includes a fuselage rod, a tail hook, a tail rod, a tail wing platform and a wing part; The tail rod is movably connected to the fuselage rod, and the tail rod can be extended or retracted relative to the fuselage rod; The nose seat is fixedly connected to one end of the fuselage rod away from the tail rod, the tail wing platform is fixedly connected to one end of the tail rod away from the fuselage rod, the wing part and the tail hook are both arranged on the fuselage rod, and the wing part is located between the nose seat and the tail hook; One end of the elastic power member away from the hook is connected to the tail hook.

7. The model aircraft structure according to claim 6, characterized in that: The wing part includes a wing, a wing pressure plate, a wing bottom bracket and a wing bracket; One side of the wing base is fixedly connected to the wing bracket, and the other side is fixedly connected to the wing pressure plate, and the wing is fixed between the wing pressure plate and the wing base; In addition, at least two mounting holes are provided on the side of the wing bracket facing away from the wing base, and the wing bracket is mounted on the fuselage rod between the nose base and the tail hook through the two mounting holes.

8. The model aircraft structure according to claim 3, characterized in that: It also includes a fairing, which is arranged on a side of the propeller shaft seat having a positioning opening and is fixedly connected to the propeller shaft seat.

9. The model aircraft structure according to claim 3, characterized in that: The elastic power member includes a rubber band member.

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