A flap control device for simulating an aircraft

Abstract

The present invention discloses a simulated aircraft flap control device, comprising a bracket, an upper cover and a lower cover, a rotating block and a rotating shaft, a guide rod and a reset mechanism, wherein when the lower cover drives the outer shaft to slide upward in the inner shaft, the guide rod disengages from the limiting groove of the guide groove, and when the outer shaft rotates, the rotating block and the rotating shaft are driven to rotate, thereby driving the potentiometer to rotate, and the rotation angle information of the potentiometer is sent to the background server of the flight simulator. The present invention adopts full mechanical movement, is used in various places, and is not easy to be damaged; it is used in the flap control of simulated aircraft, reducing the cost of flight training.

Description

Technical Field

[0001] The invention relates to a flap control device for a simulated aircraft, in particular to a device for controlling the flap of an aircraft on a simulated flight training device. Background Art

[0002] We know that an airplane needs enough lift to fly. Increasing the wing area or increasing the flight speed can increase the lift. However, when an airplane takes off and lands, in order to shorten the take-off and landing distance and ensure take-off and landing safety, the speed cannot be increased. Increasing the wing area will increase the weight of the airplane and consume a lot of energy. Therefore, in order to increase the lift of the airplane in low-speed stages such as take-off and landing, and to achieve comprehensive optimization in terms of load, speed, resistance and fuel consumption, flaps came into being. But why can flaps increase lift? Flaps can change the curvature of the airfoil, increase the wing area, and maintain laminar flow. According to theory, this can greatly increase the lift in the low-speed stage under a certain speed. Flaps are widely used in modern aircraft, and different aircraft should choose different flaps or a combination of several flaps according to their own requirements. Small military aircraft use more trailing edge flaps, while large aircraft use a combination of leading edge and trailing edge flaps at the same time, and often have multiple slats. The design and layout of flaps are also very sophisticated and can only be determined after a large number of wind tunnel tests. However, when flight trainees use simulation software to simulate the operation of aircraft ground flaps, they need to use a mouse or keyboard to operate the simulated aircraft ground flaps because there is no simulation operation device. They cannot feel the operation feel of operating the flaps of a real aircraft. Therefore, in order to improve the authenticity of flight simulation, an operation device that can simulate the flaps of a real aircraft is needed. Summary of the invention

[0003] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a flap control device for simulating an aircraft.

[0004] The technical solution adopted by the present invention to solve its technical problem is:

[0005] A simulated aircraft flap control device, characterized in that it comprises:

[0006] The bracket is provided with a guide groove, the upper wall of the guide groove is arc-shaped, and the lower wall is provided with a plurality of limiting grooves,

[0007] An upper cover and a lower cover, wherein the upper cover is connected to the inner shaft, the lower cover is connected to the outer shaft, and the outer shaft and the lower cover are slidably sleeved outside the inner shaft;

[0008] A rotating block and a rotating shaft, wherein the rotating block can be slidably sleeved outside the outer shaft, the outer shaft is provided with a radial through groove, the rotating shaft passes through the through grooves of the rotating block and the outer shaft and is rotatably connected to the bracket through a damping bearing, and one end of the rotating shaft is drivingly connected to a potentiometer;

[0009] A guide rod, the middle of which is connected to the outer shaft, and the guide rod is inserted into the guide groove of the bracket; and

[0010] A reset mechanism, the reset mechanism is installed between the outer shaft and the rotating block;

[0011] When the lower cover drives the outer shaft to slide upward inside the inner shaft, the guide rod disengages from the limiting groove of the guide groove, and when the outer shaft rotates, the rotating block and the rotating shaft are driven to rotate, thereby driving the potentiometer to rotate, and the rotation angle information of the potentiometer is sent to the background server of the flight simulator.

[0012] In another preferred embodiment, a radial through slot is provided on the inner shaft, and a sliding rod is provided on the lower cover, and the sliding rod can slide in the through slot.

[0013] In another preferred embodiment, the reset mechanism is a tension spring, and the outer shaft and the rotating block are respectively provided with screws for hanging two ends of the tension spring.

[0014] In another preferred embodiment, both ends of the rotating shaft are rotatably connected to the bracket via bearings.

[0015] In another preferred embodiment, the bracket includes a left fixing plate, a right fixing plate and a reinforcing plate connecting the left fixing plate and the right fixing plate, and there are two guide grooves, which are symmetrically arranged on the left fixing plate and the right fixing plate respectively.

[0016] In another preferred embodiment, the rotating shaft is drivingly connected to the first gear, the first gear meshes with the second gear, and the second gear is coaxially fixedly connected to the potentiometer.

[0017] In another preferred embodiment, it also includes an indicator plate, on which a rotational clearance groove and a logo are provided.

[0018] The beneficial effects of the present invention are:

[0019] The flap control device of the simulated aircraft pulls up the flap lower cover and then applies force forward or backward, driving the gear to rotate and converting it into a signal through the potentiometer transposition to make the flap of the simulated aircraft rise and fall, and the flap operating device returns to the designed position when there is no force through the force of the tension spring. The present invention adopts full mechanical movement, can be used in various places, and is not easy to be damaged; it is used in the flap control of simulated aircraft, reducing the cost of flight training.

[0020] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments; however, the aircraft flap control device simulated by the present invention is not limited to the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the decomposed structure of a preferred embodiment of the present invention.

[0022] Figure 2 It is a side schematic diagram of the installation structure of a preferred embodiment of the present invention.

[0023] Figure 3 It is a schematic diagram of the installation structure of a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0024] For example, see Figures 1 to 3 As shown, a simulated aircraft flap control device of the present invention includes an upper cover 1, an inner shaft 2, a lower cover 3, an outer shaft 4, an acrylic laser engraving plate 5, a nut 6, a screw 7, a right fixing plate 8, a first gear 9, a potentiometer 10, a potentiometer bracket 11, a guide rod 12, a second gear 13, a damping bearing 14, a rotating shaft 15, a reinforcing plate 16, a rotating block 17, a hexagon socket screw 18, a tension spring 19 and a right fixing plate 20.

[0025] The upper cover 1 is connected to the inner shaft 2, the lower cover 3 is connected to the outer shaft 4, and the lower cover 3 and the outer shaft 4 are sleeved outside the inner shaft 2. The acrylic laser engraving plate 5 is provided with a rotational clearance groove 51 and an indication mark, the outer shaft passes through the rotational clearance groove 51, the rotating block 17 can be slidably sleeved on the outer shaft 4, and the outer shaft 4 is provided with a radial through-slot 41. After the rotating shaft 15 passes through the rotating block 17 and the through-slot 41, its two ends are rotatably connected to the left fixed plate 8 and the right fixed plate 20 respectively through the damping bearing 14. One end of the rotating shaft drives the first gear 9, the first gear 9 meshes with the second gear 13, and the second gear 13 is coaxially fixedly connected to the potentiometer 10, and the potentiometer 10 is installed on the potentiometer bracket 11.

[0026] The middle of the guide rod 12 is fixedly connected to the end of the outer shaft 4, and the left fixed plate 8 and the right fixed plate 20 are respectively provided with symmetrical guide grooves 81 and 201. The upper wall of the guide groove 81 (201) is arc-shaped, and the lower wall is provided with multiple limiting grooves. The two ends of the guide rod 12 can slide in the guide grooves respectively.

[0027] The two sides of the rotating block 17 are respectively provided with hexagon socket screws 18, the upper part of the outer shaft is respectively provided with screws 7 and nuts 6, and the tension spring is hung between the hexagon socket screws 18 and the screws 7.

[0028] The operation process of this embodiment is as follows: pull up the flap lower cover 3, the guide rod 12 is free from the limit of the limit groove and can slide in the guide groove, the intermediate rotating block 17 rotates, the rotating shaft 15 drives the first gear 9 to rotate, the first gear 9 drives the second gear 13 to rotate, thereby driving the potentiometer 10 to rotate, and the potentiometer 10 sends the rotation angle information to the background server, and the background server converts the signal into the simulated aircraft flap, so that the simulated aircraft can realize the function of the flap to do the lifting and lowering movement. The flap operating device returns to the designed position when there is no force through the force of the tension spring.

[0029] The above embodiments are only used to further illustrate a simulated aircraft flap control device of the present invention, but the present invention is not limited to the embodiments. Any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention fall within the protection scope of the technical solution of the present invention.

Claims

1. A simulated aircraft flap control device, characterized in that: It includes: The bracket is provided with a guide groove, the upper wall of the guide groove is arc-shaped, and the lower wall is provided with a plurality of limiting grooves, An upper cover and a lower cover, wherein the upper cover is connected to the inner shaft, the lower cover is connected to the outer shaft, and the outer shaft and the lower cover are slidably sleeved outside the inner shaft; A rotating block and a rotating shaft, wherein the rotating block can be slidably sleeved outside the outer shaft, the outer shaft is provided with a radial through groove, the rotating shaft passes through the through grooves of the rotating block and the outer shaft and is rotatably connected to the bracket through a damping bearing, and one end of the rotating shaft is drivingly connected to a potentiometer; A guide rod, the middle of which is connected to the outer shaft, and the guide rod is inserted into the guide groove of the bracket, the bracket comprises a left fixing plate, a right fixing plate and a reinforcing plate connecting the left fixing plate and the right fixing plate, there are two guide grooves, which are symmetrically arranged on the left fixing plate and the right fixing plate, the upper wall of the guide groove is arc-shaped, and the lower wall is provided with a plurality of limiting grooves, and the two ends of the guide rod can slide in the guide groove respectively; and A reset mechanism, the reset mechanism is installed between the outer shaft and the rotating block; When the lower cover drives the outer shaft to slide upward inside the inner shaft, the guide rod is separated from the limiting groove of the guide groove, and when the outer shaft rotates, the rotating block and the rotating shaft are driven to rotate, thereby driving the potentiometer to rotate, and the rotation angle information of the potentiometer is sent to the background server of the flight simulator; Both ends of the rotating shaft are rotatably connected to the bracket through bearings; The rotating shaft is drivingly connected to the first gear, the first gear is meshed with the second gear, and the second gear is coaxially fixedly connected to the potentiometer; The reset mechanism is a tension spring, and screws for hanging two ends of the tension spring are respectively provided on the outer shaft and the rotating block.

2. A simulated aircraft flap control device according to claim 1, characterized in that: The inner shaft is provided with a radial through slot, and the lower cover is provided with a slide bar, and the slide bar can slide in the through slot.

3. The simulated aircraft flap control device according to claim 1, characterized in that: The invention also comprises an indicator plate, on which a rotational clearance groove and a mark are arranged.

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