Aviation aircraft device capable of assisting steering

Abstract

The utility model discloses an aviation aircraft device capable of assisting steering, and relates to the technical field of aviation aircrafts. The aircraft comprises an aircraft body, side wings are fixedly connected to the left side and the right side of the aircraft body, an empennage is fixedly connected to the tail end of the top of the aircraft body, auxiliary wings are arranged on the back face of the empennage, auxiliary assemblies are arranged at the tail ends of the back faces of the two side wings, each auxiliary assembly comprises two protruding plates, and the two protruding plates are symmetrically arranged. The auxiliary assembly is arranged, specifically, in the steering process, the auxiliary assembly in the same direction as the steering direction is started, the hydraulic cylinder drives the movable rod to move backwards, the fixed rod pushes the two fixed frames to move through the two push shafts, and therefore the two protruding plates are pushed to be unfolded, and after the protruding plates are unfolded, wind resistance can be increased; the air flow difference between the two sides of the aircraft is increased, so that more efficient steering work is achieved, the sailing distance is reduced, and the energy consumption of the aircraft is reduced.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aviation aircraft technology, in particular to a kind of aviation aircraft device of auxiliary steering. BACKGROUND

[0002] Aviation aircraft refers to the various aircrafts that can be controlled in atmosphere and are collectively referred to as aviation aircraft.

[0003] The existing aviation aircraft usually uses the adjustment of auxiliary wing on tail wing to control the direction of aviation aircraft, but this way will cause aviation aircraft to need to fly large arc to complete the required steering when turning, not only increases the navigation distance, but also the large-arc turning mode will increase the energy consumption of aviation aircraft, thereby reducing the endurance of aviation aircraft, therefore we propose a kind of aviation aircraft device of auxiliary steering. CONTENT OF UTILITY MODEL

[0004] The utility model aims at providing a kind of aviation aircraft device of auxiliary steering, by setting up auxiliary assembly, specifically in steering process, the auxiliary assembly same with steering direction is started, then hydraulic cylinder drives moving rod to move to rear, fixed rod is moved to two fixed frame movement by two push shafts, to push two lugs to unfold, after lug unfolding, it can increase wind resistance, improve the airflow difference of aircraft both sides, to realize more efficient steering work, reduce navigation distance, reduce the energy consumption of aircraft, solve the problem that the existing aviation aircraft usually uses the adjustment of auxiliary wing on tail wing to control the direction of aviation aircraft, but this way will cause aviation aircraft to need to fly large arc to complete the required steering when turning, not only increases the navigation distance, but also the large-arc turning mode will increase the energy consumption of aviation aircraft.

[0005] To solve the above technical problem, the utility model is realized by the following technical solutions:

[0006] The utility model discloses an aviation aircraft device of supplementary steering, including aircraft, the left side and the right side of aircraft are all fixedly connected with side wing, aircraft top tail end fixedly connected with tail wing, the back of tail wing is provided with auxiliary wing, two the back of side wing end is all provided with auxiliary assembly, the auxiliary assembly includes two lugs, two the lug is symmetrically set up, two the lug front is all through the pivot rotation connection has the lug, the lug is fixedly connected with the back of side wing, the inner wall fixedly connected with the baffle of side wing, the back of baffle center is fixedly connected with hydraulic cylinder, the output end fixedly connected with the moving rod of hydraulic cylinder back, the left side and the right side of moving rod are all fixedly connected with fixed link, two the fixed link corresponding side is all fixedly connected with push axle, two the lug corresponding side is all fixedly connected with fixed frame, the inside of fixed frame is provided with straight slot, the straight slot inside of fixed frame is set up on the push axle, when moving rod moves back, will spread two lugs, then two lugs will be pulled to close when moving rod moves forward.

[0007] Further, the left and right sides of the hydraulic cylinder are provided with outer rods, the front surfaces of the two outer rods are fixedly connected with the back surface of the partition plate, the interiors of the two outer rods are slidably connected with inner rods, the back surfaces of the inner rods penetrate through the outer rods and extend to the surface of the moving rod to be fixedly connected, the two lugs are triangular and the tail ends thereof are mutually attached, and the fixed link is slidably connected with the fixed frame through the push axle.

[0008] Further, the rear sides of the two side wings are provided with amplification assemblies, the tail end inside of the aircraft is provided with an inner groove, the amplification assembly comprises a turnover wing, one side of the turnover wing close to the aircraft is fixedly connected with a pivot, the pivot penetrates through the aircraft and extends to the interior of the inner groove, and one side of the pivot away from the turnover wing is fixedly connected with a bevel gear one; when the motor is started to drive the bevel gear two to rotate, the bevel gear two drives the pivot to rotate through the bevel gear one, so that the turnover wing rotates, the angle of the turnover wing is adjusted, and different steering requirements are met.

[0009] Further, the inner groove inner wall is fixedly connected with two support seats, the front surfaces of the two support seats are fixedly connected with motors, the back surface output ends of the two motors are fixedly connected with bevel gears two, and the bevel gears two are meshingly connected with the bevel gears one.

[0010] Further, the outer surface of the pivot is fixedly connected with two limiting convex rings, the two limiting convex rings are distributed on the inner side of the inner groove and the outer side of the aircraft, the pivot is rotatably connected with the aircraft, and a gap is left between the side of the turnover wing close to the aircraft and the aircraft.

[0011] The utility model has the following beneficial effects:

[0012] 1, the utility model discloses a auxiliary assembly is set up, specifically in the steering process, the auxiliary assembly of starting with the same direction of steering is driven, then the hydraulic cylinder is driven the moving rod to move to rear, and the fixed rod is through two push shafts and promotes two fixed frame movements to two convex boards are promoted and are unfolded, and the convex board is unfolded, can increase the wind resistance, improves the airflow difference of aircraft both sides to realize more efficient steering work, reduces the navigation distance, reduces the energy consumption of aircraft.

[0013] 2, the utility model discloses an amplification component is set up, specifically in the steering process, the motor of starting with the same direction of steering drives bevel gear no.

[0014] Of course, any product of implementing the utility model does not necessarily need to reach all advantages described above simultaneously. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical scheme of the embodiment of the utility model, the following will be needed to use the drawing of the embodiment to make a brief introduction, and obviously, the drawing in the following description is only some embodiments of the utility model, and for those skilled in the art, other drawings can be obtained according to these drawings without creative labor.

[0016] Figure 1 It is the overall structure schematic diagram of the utility model;

[0017] Figure 2 It is the internal section structure schematic diagram of the utility model side wing;

[0018] Figure 3 It is the right view section structure schematic diagram of the utility model side wing;

[0019] Figure 4 It is the overall structure schematic diagram of the utility model moving rod;

[0020] Figure 5 It is the overall structure schematic diagram of the utility model Figure 4 It is the amplification structure schematic diagram of the utility model A;

[0021] Figure 6 It is the aircraft tail section structure schematic diagram of the utility model.

[0022] In the drawing, the component list represented by each sign is as follows:

[0023] 1, aircraft; 11, side wing; 111, tail wing; 12, auxiliary assembly; 121, convex plate; 122, convex block; 123, partition; 231, hydraulic cylinder; 232, outer rod; 233, inner rod; 124, moving rod; 241, fixed rod; 242, push shaft; 125, fixed frame; 13, amplification assembly; 131, flip wing; 132, rotating shaft; 133, limit convex ring; 134, bevel gear one; 14, inner groove; 141, support seat; 142, motor; 143, bevel gear two. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0025] Please refer to Figures 1-6 The utility model discloses an auxiliary turning aircraft device, which comprises an aircraft 1, a side wing 11 fixedly connected to the left side and the right side of the aircraft 1, a tail wing 111 fixedly connected to the top end of the aircraft 1, an auxiliary wing arranged on the back of the tail wing 111, an auxiliary assembly 12 arranged at the end of the back of the two side wings 11, the auxiliary assembly 12 comprising two convex plates 121, the two convex plates 121 being symmetrically arranged, a convex block 122 rotatably connected to the front of the two convex plates 121 through a rotating shaft, the convex block 122 being fixedly connected to the back of the side wing 11, a partition 123 fixedly connected to the inner wall of the side wing 11, a hydraulic cylinder 231 fixedly connected to the center of the back of the partition 123, a moving rod 124 fixedly connected to the output end of the back of the hydraulic cylinder 231, a fixed rod 241 fixedly connected to the left side and the right side of the moving rod 124, a push shaft 242 fixedly connected to the side of the fixed rod 241, a fixed frame 125 fixedly connected to the side of the two convex plates 121, a straight slot arranged in the fixed frame 125, and the push shaft 242 arranged in the straight slot of the fixed frame 125. During the turning process, the auxiliary assembly 12 in the same direction as the turning direction is started, the hydraulic cylinder 231 drives the moving rod 124 to move backward, the fixed rod 241 drives the two fixed frames 125 to move through the two push shafts 242, so that the two convex plates 121 are pushed to expand, the convex plate 121 expands to increase the wind resistance and improve the airflow difference on both sides of the aircraft 1, thereby realizing more efficient turning work, reducing the sailing distance and reducing the energy consumption of the aircraft 1.

[0026] The outer rods 232 are fixedly connected to the back of the partition 123, and the inner rods 233 are slidably connected to the inner rods 232.

[0027] The aircraft 1 is internally provided with an inner groove 14 at the tail end, and the amplification assembly 13 comprises a turnover wing 131, the turnover wing 131 is fixedly connected to a shaft 132 near one side of the aircraft 1, the shaft 132 penetrates through the aircraft 1 and extends into the inner groove 14, and a bevel gear one 134 is fixedly connected to the side of the shaft 132 away from the turnover wing 131.

[0028] The inner groove 14 is internally provided with two support seats 141, the two support seats 141 are fixedly connected to the front of the two motors 142, and the two motors 142 are fixedly connected to the back of the two bevel gears two 143.

[0029] The shaft 132 is rotatably connected to the aircraft 1, and a gap is left between the side of the turnover wing 131 close to the aircraft 1 and the aircraft 1.

[0030] One specific application of the embodiment is as follows:

[0031] When the aircraft 1 needs to turn in the flight state, first, the auxiliary wings on the tail 111 begin to flip left or right, at this time, the auxiliary assembly 12 on the side wing 11 in the same flipping direction starts, the hydraulic cylinder 231 drives the moving rod 124 to move backward, at this time, the moving rod 124 drives the two inner rods 233 to slide in the two outer rods 232, which plays a limiting role, and the moving rod 124 drives the two fixed rods 241 to move at the same time, the two fixed rods 241 drive the two fixed frames 125 to move through the two push shafts 242, since the convex plates 121 rotate on the auxiliary assembly 12 through the rotating shaft, the two fixed frames 125 push the two convex plates 121 to unfold when moving, after the convex plates 121 unfold, the wind resistance can be increased, so that the airflow on both sides of the aircraft 1 is different when turning, and the unfolding of the convex plates 121 can increase the difference between the airflows on both sides, so that more efficient turning work is realized, and the navigation distance is reduced, when stronger maneuverability is needed, the same direction motor 142 can be started to drive the bevel gear two 143 to rotate, then the bevel gear two 143 drives the rotating shaft 132 to rotate through the bevel gear one 134, so that the flipping wing 131 rotates with the rotating shaft, and stops after rotating ninety degrees, at this time, the flipping wing 131 is in a vertical state, so that the airflow difference is increased again, the turning efficiency is higher, the maneuverability is improved, and the flipping wing 131 can be rotated to different angles, which can be suitable for different turning maneuvering needs.

[0032] In the description of the present specification, the description of the terms "one embodiment", "example", "specific example" and the like means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0033] The preferred embodiments of the above disclosed application are only used to help explain the application. The preferred embodiments do not describe all the details, nor limit the application to the specific embodiments described. Obviously, according to the content of the specification, many modifications and changes can be made. The specification selects and describes these embodiments in order to better explain the principles and practical applications of the application, so that those skilled in the art can well understand and utilize the application. The application is limited by the claims and their entire scope and equivalents.

Claims

1. An auxiliary steerable aircraft device, comprising an aircraft (1), the left and right sides of the aircraft (1) are fixedly connected with side wings (11), the top tail end of the aircraft (1) is fixedly connected with a tail wing (111), the back of the tail wing (111) is provided with an auxiliary wing, characterized in that: Both said side wings (11) back end are provided with auxiliary assembly (12), auxiliary assembly (12) includes two lugs (121), two said lugs (121) are symmetrically arranged, two said lugs (121) front are rotatably connected with lug (122) through pivot, lug (122) is fixedly connected with side wing (11) back, side wing (11) inner wall is fixedly connected with partition (123), partition (123) back center is fixedly connected with hydraulic cylinder (231), the output end of hydraulic cylinder (231) back is fixedly connected with moving rod (124), the left side and the right side of moving rod (124) are fixedly connected with fixed rod (241), two said fixed rods (241) corresponding side are fixedly connected with push shaft (242), two said lugs (121) corresponding side are fixedly connected with fixed frame (125), the inside of fixed frame (125) is provided with straight slot, push shaft (242) is arranged in the inside of straight slot on fixed frame (125).

2. An assisted-turning aerial vehicle device according to claim 1, wherein, The left and right sides of the hydraulic cylinder (231) are provided with outer rods (232), the front surfaces of the two outer rods (232) are fixedly connected with the back surface of the partition (123), and the interiors of the two outer rods (232) are slidably connected with inner rods (233). The back surface of the inner rod (233) penetrates the outer rod (232) and is fixedly connected to the surface of the moving rod (124).

3. An assisted-turning aerial vehicle device according to claim 2, wherein, Two said lugs (121) are triangular and mutually adhere at the tail ends, and the fixed rod (241) is slidably connected with the fixed frame (125) through the push shaft (242).

4. An assisted-turning aerial vehicle device according to claim 3, wherein, Both said side wings (11) back are provided with amplification assembly (13), the inside of the tail end of aircraft (1) is provided with inner groove (14), the amplification assembly (13) includes turnover wing (131), the side close to aircraft (1) of turnover wing (131) is fixedly connected with pivot (132), pivot (132) penetrates aircraft (1) and extends to the inside of inner groove (14), the side away from turnover wing (131) of pivot (132) is fixedly connected with bevel gear one (134).

5. An assisted-turning aerial vehicle device according to claim 4, wherein, The inner wall of the inner groove (14) is fixedly connected with two support seats (141), the front surfaces of the two support seats (141) are fixedly connected with motors (142), the back surfaces of the output ends of the two motors (142) are fixedly connected with bevel gear two (143), and the bevel gear two (143) is meshedly connected with the bevel gear one (134).

6. An assisted-turning aerial vehicle device according to claim 5, wherein, The outer surface of the pivot (132) is fixedly connected with two limiting convex rings (133), and the two limiting convex rings (133) are distributed on the inner side of the inner groove (14) and the outer side of the aircraft (1).

7. An assisted-turning aerial vehicle device according to claim 6, wherein, The pivot (132) is rotatably connected with the aircraft (1), and a gap is left between the side close to the aircraft (1) of the turnover wing (131) and the aircraft (1).

Images