Unmanned aerial vehicle launching system capable of automatically controlling folding wings

Abstract

The utility model relates to an unmanned aerial vehicle launching system capable of automatically controlling folding wings, which comprises a launching mechanism and a fuselage, a plurality of foldable wing mechanisms are arranged on one side of the fuselage, and a control mechanism capable of controlling the wing mechanisms to unfold or fold and a landing mechanism for forced landing are arranged in the fuselage. A propelling mechanism capable of generating thrust is arranged at one end of the machine body; according to the utility model, the defect that the aerodynamic configuration cannot be adjusted in real time according to the flight state (such as high-speed cruising / low-speed hovering) due to the fact that the wings of the traditional ejection folding unmanned aerial vehicle are limited by the torsion spring and are in a fixed state after being launched is overcome. The dynamic folding design can feed back flight parameters (speed, height and attitude) in real time through a sensor, the wing unfolding proportion is controlled in combination with an algorithm, the flight efficiency is remarkably improved, the resistance is reduced by folding at a high speed, and the lift force is enhanced by unfolding at a low speed.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to an unmanned plane launching system of automatic control folding wing. BACKGROUND

[0002] The folding wing unmanned plane is a tactical unmanned plane system combining reconnaissance and attack ability, and is mainly portable and efficient. The biggest feature is that a folding wing design is adopted, the wing is closely attached to the fuselage and is stored in a tubular launcher in ordinary times, so that carrying and launching are convenient. After launching, the wing is automatically unfolded to become a fixed wing configuration, and relies on an electric propeller to fly, and has the advantages of flexible take-off and landing of a multi-rotor and long endurance of a fixed wing. This kind of unmanned plane is usually equipped with an optical-electrical camera and a navigation system, can transmit ground pictures in real time, and performs reconnaissance, monitoring or target indication tasks; some models are also used to carry small combat units, and are controlled by "man-in-the-loop" or locked automatically, so as to perform tasks by diving and hitting targets.

[0003] The application announcement No. CN119705890A discloses a catapult folding unmanned plane loaded with a black box, and the scheme unfolding mechanism assembly specifically includes a fixed part, that is, a fuselage, a folding part, a straight wing and a tail wing folded and stored when not launched, a torsional spring mechanism and a locking mechanism. The wing and the tail wing are folded and stored in the fuselage when not launched, are kept in the storage position by the space constraint of the launching barrel, the torsional spring serves as a pivot of the folding wing, is used to determine the fixed position of the folding wing and provide initial power for unfolding of the folding wing, and the locking mechanism ensures that the mechanical lock is automatically locked when the folding wing is unfolded to the specified position, so as to ensure the stability of unfolding.

[0004] However, the folding unmanned plane with this structure still has certain limitations: 1. After the unmanned plane is catapulted out, the wing is unfolded and always maintained in a fixed state, if some narrow mountain passes are encountered, the unmanned plane will inevitably be crashed due to the inability to control the wing by an automatic mode; 2. How to effectively use the configuration of the reflection type folding wing unmanned plane multiple times to play an economic role in some civil scenes is also one of the elements to be considered. SUMMARY

[0005] The utility model mainly aims at the problems existing in the unmanned plane work, and invents an unmanned plane launching system of automatic control folding wing, the traditional fixed wing unmanned plane needs to manually unfold the wing before launching, and cannot adjust the aerodynamic shape in real time according to the flight state. The dynamic folding design can feed back flight parameters in real time through a sensor, and the wing unfolding ratio is controlled in combination with an algorithm.

[0006] The utility model discloses an unmanned aerial vehicle launching system of automatic control folding wing, including launching mechanism and fuselage, one side of fuselage is equipped with a plurality of wing mechanism that can fold, the inside of fuselage is equipped with the control mechanism that can control wing mechanism to unfold or store and is used for forced landing's landing mechanism, one end of fuselage is equipped with the propulsion mechanism that can produce the thrust.

[0007] As preferred, each wing mechanism comprises a left wing, a left wing limiting plate, a left wing vertical shaft and a right wing assembly, the end of the left wing is provided with a left wing avoiding slot, the inside of the left wing avoiding slot is provided with a left wing limiting plate, the left wing limiting plate is integrally extended downward to provide a left wing vertical shaft, the surface of the left wing vertical shaft is connected with the right wing assembly.

[0008] As preferred, the right wing assembly comprises a right wing, a right wing limiting plate, a right wing shaft sleeve and a right wing shaft sleeve, the inside of the right wing shaft sleeve is connected to the surface of the left wing vertical shaft through a threaded mode, the upper portion of the right wing shaft sleeve is integrally connected with the right wing limiting plate, the left wing limiting plate and the right wing limiting plate are in different planes, the right wing is fixedly connected to the side wall of the right wing limiting plate, the inside of the fuselage is provided with a first driving motor for driving the left wing vertical shaft to rotate.

[0009] As preferred, one side of the fuselage is provided with a first air inlet, the end of the left wing and the right wing is provided with a second air inlet, the first air inlet and the second air inlet are coaxial when the left wing and the right wing are in a folded state, the inside of the fuselage is further provided with an air inlet channel communicated with the first air inlet, the other end of the air inlet channel is connected to the landing mechanism.

[0010] As preferred, the landing mechanism comprises a first landing support column, a second landing support column and a landing parachute, the inside of the first landing support column is hollow and slidably provided with the second landing support column, the side surface of the first landing support column is communicated with the air inlet channel, the inside bottom of the first landing support column is provided with an electromagnet for sucking the second landing support column, the bottom of the second landing support column is provided with a third air inlet, the inside of the second landing support column is provided with the landing parachute, the wind inside the air inlet channel can blow the second landing support column upward to slide until blowing the landing parachute to unfold when the electromagnet is not electrified.

[0011] As preferred, the inside of the first landing support column is further provided with a limiting groove, the bottom of the second landing support column is further provided with a limiting boss, the limiting boss is connected to the inside of the limiting groove, the end of the landing parachute is connected with a circular slide block, the top of the second landing support column is provided with a ring-shaped baffle for blocking the circular slide block.

[0012] As preferred, the propelling mechanism comprises a second driving motor, an aileron, a propeller and a metal spring, the second driving motor is arranged inside one end of the fuselage, a propeller is connected to the end of the rotating shaft of the second driving motor, an aileron capable of being unfolded and folded is arranged on the outer side of the fuselage close to the propeller, and the metal spring is arranged between the aileron and the fuselage.

[0013] As preferred, the launching mechanism comprises a launching barrel, a compressed gas tank, a launching support plate, a gas valve, a launching support plate and a launching support frame, the compressed gas tank and the launching support plate are arranged inside the launching barrel, the gas outlet end of the compressed gas tank is connected with the gas valve, the gas outlet end of the gas valve penetrates through the launching support plate, and the launching support frame is arranged outside the launching barrel.

[0014] Compared with the prior art, the utility model has the following beneficial effects: 1. the traditional ejection folding wing unmanned plane is in a fixed state after being launched and limited by the torsion spring, cannot be adjusted in real time according to the flight state (such as high-speed cruising / low-speed hovering), the dynamic folding design can feed back flight parameters (speed, height, attitude) in real time through a sensor, controls the wing unfolding proportion in combination with an algorithm, remarkably improves flight efficiency, reduces resistance when folding at high speed, enhances lift when unfolding at low speed, and the dynamic folding design can make the unmanned plane have more purposes in the fields of civil security patrol, long-distance transportation and high-altitude communication transfer; 2. the automatic parachute opening of the landing mechanism not only protects the machine body, but also prolongs the survival time of optical equipment and storage chips through parachute descent buffer, ensures task data recovery, the improvement makes the unmanned plane have longer service life, and has more civil economic purposes. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is a perspective view of the utility model;

[0016] Figure 2 It is a perspective view of the unmanned plane of the utility model;

[0017] Figure 3 It is a sectional view of the unmanned plane of the utility model;

[0018] Figure 4 It is an explosion view of the control mechanism of the utility model;

[0019] Figure 5 It is an enlarged view of the area A in the drawing of the utility model;

[0020] Figure 6 It is an enlarged view of the area B in the drawing of the utility model;

[0021] Figure 7The utility model discloses a cross section view of launching mechanism.

[0022] Marked in the drawing: 1, launching mechanism, 11, launching cylinder, 12, compressed gas tank, 13, launching support plate, 14, air valve, 15, launching support frame, 2, fuselage, 21, first air inlet, 22, air inlet channel, 3, wing mechanism, 31, left wing, 32, left wing limiting plate, 33, right wing assembly, 34, first drive motor, 35, second air inlet, 311, left wing avoiding groove, 321, left wing vertical shaft, 331, right wing, 332, right wing shaft sleeve, 333, right wing limiting plate, 5, landing mechanism, 51, first landing support column, 52, second landing support column, 53, parachute, 511, electromagnet, 521, third air inlet, 512, limiting groove, 522, limiting boss, 523, annular baffle, 6, propulsion mechanism, 61, second drive motor, 62, aileron, 63, metal spring, 64, propulsion rotor. DETAILED DESCRIPTION

[0023] The utility model will be further described in connection with the embodiment shown in the drawing:

[0024] As Figure 1 and Figure 7 Indicated, an unmanned aerial vehicle launching system of automatic control folding wing includes launching mechanism 1 and fuselage 2. Wherein launching mechanism 1 includes launching cylinder 11, compressed gas tank 12, launching support plate 13, air valve 14 and launching support frame 15, the inside of launching cylinder 11 is equipped with compressed gas tank 12 and launching support plate 13, the gas outlet end of compressed gas tank 12 is connected with air valve 14, the gas outlet end of air valve 14 passes through launching support plate 13, and the outside of launching cylinder 11 is equipped with launching support frame 15.

[0025] When needing to launch unmanned aerial vehicle, its wing is folded and inserted into the inside of launching cylinder 11, needs to tightly adhere to the gas outlet of air valve 14 on one side of unmanned aerial vehicle, and launching support plate 13 only plays the role of support and guidance at this time. The opening or closing of air valve 14 is controlled through remote controller, and when air valve 14 opens, the high-pressure air in compressed gas tank 12 can fly the whole unmanned aerial vehicle through the gas outlet of air valve 14.

[0026] In the embodiment, please refer to Figure 1 、 Figure 2 、 Figure 3 and Figure 4 . One side of fuselage 2 is equipped with two groups of wing mechanism 3 that can automatically fold or unfold. One end of fuselage 2 is equipped with propulsion mechanism 6 that can generate thrust.

[0027] The propelling mechanism 6 comprises a second driving motor 61, an aileron 62, a propeller 64 and a metal spring 63, the second driving motor 61 is arranged inside one end of the fuselage 2, the rotating shaft end of the second driving motor 61 is connected with the propeller 64, the fuselage 2 is arranged with the aileron 62 which can be unfolded and folded outside the propeller 64, the metal spring 63 is arranged between the aileron 62 and the fuselage 2.

[0028] When the whole unmanned aerial vehicle is launched, the aileron 62 will be unfolded under the elastic force of the metal spring 63, at the same time, the second driving motor 61 will drive the propeller 64 to rotate, the propelling force generated by the propeller 64 in the rotating process will make the whole unmanned aerial vehicle in the state of rushing forward.

[0029] Each set of wing mechanism 3 comprises a left wing 31, a left wing limiting plate 32, a left wing vertical shaft 321 and a right wing assembly 33, the end of the left wing 31 is arranged with the left wing avoiding slot 311, the inside of the left wing avoiding slot 311 is arranged with the left wing limiting plate 32, the left wing limiting plate 32 is integrally extended downward with the left wing vertical shaft 321, the surface of the left wing vertical shaft 321 is connected with the right wing assembly 33.

[0030] The right wing assembly 33 comprises a right wing 331, a right wing limiting plate 333, a right wing shaft sleeve 332 and a right wing shaft sleeve 332, the inside of the right wing shaft sleeve 332 is connected to the surface of the left wing vertical shaft 321 through the threaded mode, the upper part of the right wing shaft sleeve 332 is integrally connected with the right wing limiting plate 333, the left wing limiting plate 32 and the right wing limiting plate 333 are in different planes, the right wing 331 is fixedly connected to the side wall of the right wing limiting plate 333, the inside of the fuselage 2 is arranged with the first driving motor 34 which drives the left wing vertical shaft 321 to rotate.

[0031] When it is needed to control the left wing 31 and the right wing 331 to unfold or fold, the rotating shaft of the first driving motor 34 will start to rotate, thereby driving the left wing vertical shaft 321 and the left wing limiting plate 32 to rotate. In this process, the left wing vertical shaft 321 also drives the right wing shaft sleeve 332 to rotate, the right wing shaft sleeve 332 drives the right wing 331 to unfold or fold through the right wing limiting plate 333 in the rotating process. At the same time, the left wing limiting plate 32 will push the left wing 31 to unfold or fold through the left wing avoiding slot 311.

[0032] In this embodiment, please refer to Figure 1 , Figure 3 , Figure 5 and Figure 6The fuselage 2 is internally provided with a landing mechanism 5 for forced landing. One side of the fuselage 2 is provided with a first air inlet 21, and the ends of the left wing 31 and the right wing 331 are each provided with a second air inlet 35. When the left wing 31 and the right wing 331 are in the folded state, the first air inlet 21 and the second air inlet 35 are coaxial. The fuselage 2 is internally provided with an air inlet channel 22 connected to the first air inlet 21, and the other end of the air inlet channel 22 is connected to the landing mechanism 5.

[0033] When the left wing 31 and the right wing 331 are in the folded state, the wind will blow into the interior of the air inlet channel 22 through the first air inlet 21 and the second air inlet 35, and the air inlet channel 22 will blow the wind into the interior of the landing mechanism 5.

[0034] In this embodiment, the landing mechanism 5 includes a first landing support column 51, a second landing support column 52, and a landing parachute 53. The first landing support column 51 is hollow and slidably provided with the second landing support column 52. The side of the first landing support column 51 is in communication with the air inlet channel 22. The bottom of the interior of the first landing support column 51 is provided with an electromagnet 511 for attracting the second landing support column 52. The bottom of the second landing support column 52 is provided with a third air inlet 521. The interior of the second landing support column 52 is provided with the landing parachute 53. When the electromagnet 511 is not powered, the wind in the interior of the air inlet channel 22 can blow the second landing support column 52 upward until it blows the landing parachute 53 to unfold.

[0035] The interior of the first landing support column 51 is further provided with a limiting groove 512, and the bottom of the second landing support column 52 is further provided with a limiting boss 522 connected to the interior of the limiting groove 512. The end of the landing parachute 53 is connected with a circular slide block 531, and the top of the second landing support column 52 is provided with an annular baffle 523 for blocking the circular slide block 531.

[0036] When forced landing is needed for deceleration, the electromagnet 511 no longer works, and the adsorption of the second landing support column 52 disappears. The wind will slide upward through the second landing support column 52 until the wind can enter the interior of the second landing support column 52 through the third air inlet 521. At this time, the entire landing parachute 53 will break through the cover plate at the top of the first landing support column 51 to unfold, thereby realizing the function of deceleration forced landing.

[0037] The design of the limiting boss 522 connected to the limiting groove 512 is to prevent the wind from sneaking into the interior of the third air inlet 521 when the electromagnet 511 is in the working state. The design of the circular slide block 531 is to prevent the landing parachute 53 from detaching from the interior of the fuselage 2. It should be noted that the exterior of the fuselage 2 can be equipped with high-definition cameras and positioning devices according to needs.

[0038] The utility model working principle and use method:

[0039] Need to launch unmanned aerial vehicle when its wing is folded and is inserted into the inside of launching cylinder 11, need to tightly adhere to the air valve 14 of one side of unmanned aerial vehicle and the outtake, and at this time launching support plate 13 only plays the role of support and direction. The opening or closing of air valve 14 is controlled through remote controller, when air valve 14 opens, the high pressure air in compression gas tank 12 will fly the whole unmanned aerial vehicle through the outtake of air valve 14.

[0040] At this time aileron 62 will unfold under the elastic force of metal spring 63, and at the same time, second drive motor 61 will drive propeller rotor 64 to rotate, and the thrust generated in the rotating process of propeller rotor 64 will make the whole unmanned aerial vehicle be in the state of rushing forward, and the rapid unfolding of left wing 31 and right wing 331 makes the whole unmanned aerial vehicle be in the state of gliding.

[0041] The specific embodiments described in the present application are only examples of the spirit of the present application. Those skilled in the art of the present application can make various modifications or supplements to the described specific embodiments or use similar ways to replace them, but will not deviate from the spirit of the present application or exceed the scope defined by the appended claims.

Claims

1. An unmanned aerial vehicle launching system for automatically controlling a folding wing, comprising a launching mechanism (1) and a fuselage (2), characterized in that, The side of the fuselage (2) is provided with several wing mechanisms (3) capable of automatic folding or unfolding, the inside of the fuselage (2) is provided with a landing mechanism (5) for forced landing, and one end of the fuselage (2) is provided with a propulsion mechanism (6) capable of generating thrust.

2. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 1, wherein, Each of the wing mechanisms (3) comprises a left wing (31), a left wing limiting plate (32), a left wing vertical shaft (321) and a right wing assembly (33), the end of the left wing (31) is provided with a left wing avoiding groove (311), the inside of the left wing avoiding groove (311) is provided with a left wing limiting plate (32), the left wing limiting plate (32) is integrally extended downward to be provided with a left wing vertical shaft (321), and the surface of the left wing vertical shaft (321) is connected with a right wing assembly (33).

3. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 2, wherein, The right wing assembly (33) comprises a right wing (331), a right wing limiting plate (333), a right wing shaft sleeve (332) and a right wing shaft sleeve (332), the inside of the right wing shaft sleeve (332) is connected to the surface of the left wing vertical shaft (321) in a threaded manner, the upper part of the right wing shaft sleeve (332) is integrally connected with a right wing limiting plate (333), the left wing limiting plate (32) and the right wing limiting plate (333) are in different planes, the right wing (331) is fixedly connected to the side wall of the right wing limiting plate (333), and the inside of the fuselage (2) is provided with a first driving motor (34) for driving the left wing vertical shaft (321) to rotate.

4. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 3, wherein, One side of the fuselage (2) is provided with a first air inlet (21), the ends of the left wing (31) and the right wing (331) are provided with a second air inlet (35), the first air inlet (21) and the second air inlet (35) are coaxial when the left wing (31) and the right wing (331) are in a folded state, the inside of the fuselage (2) is further provided with an air inlet channel (22) communicated with the first air inlet (21), and the other end of the air inlet channel (22) is connected to the landing mechanism (5).

5. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 4, wherein, The landing mechanism (5) comprises a first landing support column (51), a second landing support column (52) and a landing parachute (53), the inside of the first landing support column (51) is hollow and slidably provided with the second landing support column (52), the side surface of the first landing support column (51) is communicated with the air inlet channel (22), the inside bottom of the first landing support column (51) is provided with an electromagnet (511) for attracting the second landing support column (52), the bottom of the second landing support column (52) is provided with a third air inlet (521), the inside of the second landing support column (52) is provided with a landing parachute (53), and when the electromagnet (511) is not electrified, the wind in the air inlet channel (22) can blow the second landing support column (52) upward until the landing parachute (53) is unfolded.

6. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 5, wherein, The inside of the first landing support column (51) is also provided with a limiting groove (512), the bottom of the second landing support column (52) is also provided with a limiting boss (522), the limiting boss (522) is connected to the inside of the limiting groove (512), the end of the parachute (53) is connected with a circular slide block (531), and the top of the second landing support column (52) is provided with an annular baffle (523) for blocking the circular slide block (531).

7. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 6, wherein, The propelling mechanism (6) comprises a second driving motor (61), an aileron (62), a propeller (64) and a metal spring (63), the inside of one end of the fuselage (2) is provided with the second driving motor (61), the rotating shaft end of the second driving motor (61) is connected with the propeller (64), the outer side of the fuselage (2) close to the propeller (64) is provided with the aileron (62) capable of being unfolded and folded, and the metal spring (63) is arranged between the aileron (62) and the fuselage (2).

8. The unmanned aerial vehicle launch system automatically controlling a folding wing according to claim 1, wherein, The launching mechanism (1) comprises a launching barrel (11), a compressed gas tank (12), a launching support plate (13), a gas valve (14) and a launching support frame (15), the inside of the launching barrel (11) is provided with the compressed gas tank (12) and the launching support plate (13), the gas outlet end of the compressed gas tank (12) is connected with the gas valve (14), the gas outlet end of the gas valve (14) penetrates through the launching support plate (13), and the outside of the launching barrel (11) is provided with the launching support frame (15).

Images