CN211223839U

CN211223839U - Protection device for slowing down landing speed of airplane

Info

Publication number: CN211223839U
Application number: CN201921019643.5U
Authority: CN
Inventors: 丁芮
Original assignee: Jiangxi Jinkeli Industry Co ltd
Current assignee: Jiangxi Jinkeli Industry Co ltd
Priority date: 2019-07-02
Filing date: 2019-07-02
Publication date: 2020-08-11
Anticipated expiration: 2029-07-02

Abstract

The utility model relates to an aircraft emergency equipment technical field just discloses a protection device for slowing down aircraft speed-per-hour that descends, including the fuselage, the both sides fixed mounting of fuselage has the wing, and the top fixed mounting of wing has the spoiler, and the equal fixed mounting in both ends of spoiler back one side has the rectangle case, and the roller bearing has been cup jointed in the inner chamber activity of rectangle case, and the electric putter has been cup jointed in the activity on the roller bearing, and the other end and the slider activity of electric putter are cup jointed, and the slider is close to the recess sliding connection that slider one side was seted up with the fuselage, and the bottom fixed mounting of wing has the engine ship cover. This a protection device for slowing down aircraft speed per hour that descends through setting up electric push rod, when aircraft descending spoiler opens, electric push rod supports the spoiler, and electric push rod, spoiler and fuselage constitute a triangle-shaped just this moment, have certain stability, and compare with preceding device, the position of spoiler is more firm.

Description

Protection device for slowing down landing speed of airplane

Technical Field

The utility model relates to an aircraft emergency equipment technical field specifically is a protection device for slowing down aircraft speed-per-hour that descends.

Background

With the development of science and technology, airplanes become the most common vehicles, and the safety factor of the airplanes is high, and the airplanes can be classified into propeller airplanes and jet airplanes according to the types of engines.

The airplane has extremely high flying speed, a plurality of protection devices are required to be installed on the airplane to slow down the landing speed of the airplane, the common airplane generally utilizes spoilers installed on wings to slow down the airplane, but the spoiler cannot be supported because the protection devices of the spoilers are not arranged on the airplane, so that the pressure value of air flow born by the spoilers is reduced.

SUMMERY OF THE UTILITY MODEL

The utility model provides a be not enough to prior art, the utility model provides a protection device for slowing down aircraft speed per hour possesses the advantage that improves the supporting effect, has solved the spoiler that common aircraft generally utilized the installation on the wing and has carried out the deceleration to the aircraft, but is not equipped with the protection device of spoiler on the aircraft, can't support the spoiler to the problem of the pressure value of the air current that the spoiler bore has been reduced.

The utility model provides a following technical scheme: a protection device for slowing down the landing speed of an airplane comprises a fuselage, wings are fixedly mounted on two sides of the fuselage, a spoiler is fixedly mounted at the top of each wing, a rectangular box is fixedly mounted at both ends of one side of the back of the spoiler, a roller is movably sleeved in an inner cavity of the rectangular box, an electric push rod is movably sleeved on the roller, the other end of the electric push rod is movably sleeved with a slider, the slider is slidably connected with a groove formed in one side, close to the slider, of the fuselage, an engine boat cover is fixedly mounted at the bottom of each wing, vertical rods are fixedly mounted on two sides of the front end and the rear end of the bottom of the fuselage, oblique rods are fixedly mounted on two sides of the rear end of the bottom of the fuselage respectively, the oblique rods fixedly mounted on two sides of the rear end of the bottom of the fuselage are fixedly connected with the vertical rods through connecting rods, and a cross, fixed frame has been cup jointed in the activity respectively at the both ends of horizontal pole, the fixed cover of inner chamber of fixed frame has connect the tire, the sleeve has been cup jointed in the equal activity in both sides at fixed frame inner chamber middle part, and telescopic quantity is two, two one side that the sleeve is relative cup joints through the screw rod screw thread, one side fixed mounting that the horizontal pole was kept away from to the sleeve has the diaphragm, the middle part fixed mounting of screw rod has from the driving wheel, from driving wheel and action wheel meshing, the action wheel cup joints with the output shaft of motor is fixed, motor fixed mounting is on the inner chamber of fixed frame.

Preferably, one side of the inner cavity of the fixing frame, which is close to the sleeve, is provided with a through hole matched with the sleeve, and the through hole arranged on one side of the inner cavity of the fixing frame, which is close to the sleeve, is movably sleeved with the sleeve.

Preferably, the driven wheel and the driving wheel have the same radius value and width value.

Preferably, the rotation directions of the two ends of the screw are opposite.

Preferably, one side of the transverse plate close to the sleeve is provided with a groove, and the groove arranged on the side of the transverse plate close to the sleeve is movably sleeved with the sleeve.

Compared with the prior art, the utility model discloses possess following beneficial effect:

1. this a protection device for slowing down aircraft speed per hour that descends through setting up electric push rod, when aircraft descending spoiler opens, electric push rod supports the spoiler, and electric push rod, spoiler and fuselage constitute a triangle-shaped just this moment, have certain stability, and compare with preceding device, the position of spoiler is more firm.

2. This a protection device for slowing down aircraft speed-per-hour that lands, through setting up screw rod and diaphragm, when the aircraft lands, drive the diaphragm through the screw rod rotation and outwards extend, under the pressure of air current, diaphragm self takes place the rotation and drives the tire rotation, then the aircraft tire before falling to the ground has rolled, and compared with the aircraft wheel motionlessness before falling to the ground, this method has reduced the friction between tire and the ground, and the tire of aircraft has received better protection.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a top view of the spoiler of the present invention;

fig. 3 is a schematic view of the electric push rod of the present invention;

fig. 4 is a schematic view of the tire of the present invention.

In the figure: 1. a body; 2. a diagonal bar; 3. a cross bar; 4. a fixing frame; 5. a tire; 6. a driving wheel; 7. a motor; 8. a driven wheel; 9. a screw; 10. a sleeve; 11. a transverse plate; 12. an airfoil; 13. a spoiler; 14. an engine boat cover; 15. a rectangular box; 16. an electric push rod; 17. a roller; 18. a slider; 19. a vertical rod; 20. a connecting rod.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, a protection device for slowing down the landing speed of an airplane comprises a fuselage 1, wings 12 are fixedly installed on two sides of the fuselage 1, spoilers 13 are fixedly installed on the tops of the wings 12, rectangular boxes 15 are fixedly installed on two ends of one side of the back of each spoiler 13, a roller 17 is movably sleeved in an inner cavity of each rectangular box 15, an electric push rod 16 is movably sleeved on each roller 17, when the airplane lands, each spoiler 13 is opened, the electric push rods 16 are started to support the spoilers 13, the electric push rods 16, the spoilers 13 and the fuselage 1 just form a triangle, and have certain stability, so that the position of each spoiler 13 is more stable, the other ends of the electric push rods 16 are movably sleeved with sliders 18, the sliders 18 are slidably connected with grooves formed in one side of the fuselage 1, which is close to the sliders 18, an engine boat cover 14 is fixedly installed at the bottom of each wing 12, fuselage 19 is fixedly installed on two sides of the front end and the rear end of the, the two sides of the rear end of the bottom of the machine body 1 are respectively and fixedly provided with an inclined rod 2, the inclined rods 2 fixedly arranged on the two sides of the rear end of the bottom of the machine body 1 are fixedly connected with a vertical rod 19 through a connecting rod 20, the other end of the vertical rod 19 fixedly arranged on the front end of the bottom of the machine body 1 is fixedly provided with a cross rod 3, two ends of the cross rod 3 are respectively and movably sleeved with a fixed frame 4, one side of the fixed frame 4 close to the cross rod 3 is provided with a sleeve hole matched with the cross rod 3, one side of the fixed frame 4 close to the cross rod 3 is provided with a sleeve hole movably sleeved with the cross rod 3, an inner cavity of the fixed frame 4 is fixedly sleeved with a tire 5, two sides of the middle part of the inner cavity of the fixed frame 4 are respectively and movably sleeved with a sleeve 10, one side of the inner cavity of the fixed frame, the opposite sides of the two sleeves 10 are in threaded sleeve connection through screw rods 9, the rotating directions of the two ends of each screw rod 9 are opposite, one side of each sleeve 10, which is far away from the transverse rod 3, is fixedly provided with a transverse plate 11, one side of each transverse plate 11, which is close to the corresponding sleeve 10, is provided with a groove, the groove, which is arranged on one side of each transverse plate 11, which is close to the corresponding sleeve 10, is movably sleeved with the corresponding sleeve 10, the width value of one side of each transverse plate 11, which is far away from the corresponding screw rod 9, is larger than that of one side of each transverse plate 11, which is close to the corresponding screw rod 9, when the corresponding sleeve 10 reaches the edge of the corresponding screw rod 9, the plane on which the width change sideline of each transverse plate 11 is positioned coincides with the plane on one side of the corresponding fixed frame 4, the middle part of each screw rod, when the aircraft lands, starter motor 7, screw rod 9 rotate and drive diaphragm 11 and outwards extend, and under the pressure of air current, thereby diaphragm 11 self takes place to rotate and drives tire 5 rotatory, and then the aircraft tire 5 has rolled before falling to the ground, and tire 5 is rotatory to have reduced the friction between tire 5 and the ground for tire 5 of aircraft has received better protection.

According to the working principle, when the airplane descends, the spoiler 13 automatically rises, the electric push rod 16 is started, one side, close to the roller 17, of the electric push rod 16 rotates around the roller 17, at the moment, the slider 18 slides along a groove formed in one side, close to the slider 18, of the airplane body 1, when the spoiler 13 is stable, the electric push rod 16 is closed, at the moment, the electric push rod 16 plays a supporting role on the spoiler 13, and the spoiler 13 is guaranteed to be more stable;

when the aircraft is falling to the ground soon, starting motor 7, drive wheel 6 meshes with from driving wheel 8, then drive wheel 6 rotates and drives from driving wheel 8 and rotate, from driving wheel 8 rotates and drives screw rod 9 and rotate, because the direction of rotation of screw rod 9 both ends screw thread is opposite, then sleeve 10 moves to both ends respectively along screw rod 9, diaphragm 11 moves to the direction of keeping away from driving wheel 8 place this moment, when sleeve 10 moves the edge of screw rod 9, close motor 7, diaphragm 11 begins to rotate just under the effect of air current, diaphragm 11 is rotatory to drive fixed frame 4 rotatory, fixed frame 4 is rotatory to drive tire 5 rotatory, then the aircraft is when falling to the ground, tire 5 has already begun to rotate along with the frequency of air current, reduce the wearing and tearing of aircraft tire 5 and ground, protect tire 5, can.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A protection device for slowing down the landing speed of an aircraft, comprising a fuselage (1), characterized in that: the both sides fixed mounting of fuselage (1) has wing (12), the top fixed mounting of wing (12) has spoiler (13), the equal fixed mounting in both ends of spoiler (13) back one side has rectangle case (15), roller bearing (17) have been cup jointed in the inner chamber activity of rectangle case (15), electric putter (16) have been cup jointed in the activity on roller bearing (17), the other end and the slider (18) activity of electric putter (16) are cup jointed, slider (18) are close to the recess sliding connection that slider (18) one side was seted up with fuselage (1), the bottom fixed mounting of wing (12) has engine ship cover (14), the equal fixed mounting in both sides of fuselage (1) bottom front end and bottom rear end has montant (19), the both sides of fuselage (1) bottom rear end fixed mounting respectively has down tube (2), fuselage (1) bottom rear end both sides fixed mounting's down tube (2) pass through connecting rod (20) fixed mounting down with montant (19) down tube (19) A cross bar (3) is fixedly arranged at the other end of a vertical bar (19) fixedly arranged at the front end of the bottom of the machine body (1), two ends of the cross bar (3) are respectively movably sleeved with a fixed frame (4), the inner cavity of the fixed frame (4) is fixedly sleeved with a tire (5), sleeves (10) are movably sleeved on two sides of the middle part of the inner cavity of the fixed frame (4), the number of the sleeves (10) is two, one opposite side of the two sleeves (10) is sleeved by a screw rod (9) in a threaded manner, a transverse plate (11) is fixedly arranged on one side of the sleeve (10) far away from the cross rod (3), a driven wheel (8) is fixedly arranged in the middle of the screw rod (9), the driven wheel (8) is meshed with the driving wheel (6), the driving wheel (6) is fixedly sleeved with an output shaft of the motor (7), and the motor (7) is fixedly installed on an inner cavity of the fixing frame (4).

2. A protective device for slowing the rate of descent of an aircraft according to claim 1, wherein: one side of the inner cavity of the fixing frame (4) close to the sleeve (10) is provided with a through hole matched with the sleeve (10), and the through hole arranged on one side of the inner cavity of the fixing frame (4) close to the sleeve (10) is movably sleeved with the sleeve (10).

3. A protective device for slowing the rate of descent of an aircraft according to claim 1, wherein: the driven wheel (8) and the driving wheel (6) are equal in radius value and width value.

4. A protective device for slowing the rate of descent of an aircraft according to claim 1, wherein: the rotation directions of the two ends of the screw (9) are opposite.

5. A protective device for slowing the rate of descent of an aircraft according to claim 1, wherein: one side of the transverse plate (11) close to the sleeve (10) is provided with a groove, and the groove arranged on one side of the transverse plate (11) close to the sleeve (10) is movably sleeved with the sleeve (10).