CN217227916U - Direct-emission autonomous cruise suicide type unmanned aerial vehicle - Google Patents
Direct-emission autonomous cruise suicide type unmanned aerial vehicle Download PDFInfo
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- CN217227916U CN217227916U CN202122593441.5U CN202122593441U CN217227916U CN 217227916 U CN217227916 U CN 217227916U CN 202122593441 U CN202122593441 U CN 202122593441U CN 217227916 U CN217227916 U CN 217227916U
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Abstract
The utility model relates to an unmanned air vehicle technique field specifically is a direct transmission is suicide type unmanned aerial vehicle that independently cruises, include: the robot comprises a robot body, wherein the robot body is in a triangular streamline shape, a motor is arranged in the robot body, the output end of the motor is a driving shaft, and a propelling paddle is arranged at the tail end of the driving shaft; two wings, namely a first wing and a second wing, are movably mounted on two sides of the fuselage respectively; the movable assembly is arranged on the fuselage and is simultaneously connected with the first wing and the second wing; a laser guidance system is arranged in the machine body; direct transmission independently cruise suicide type unmanned aerial vehicle carry out the improved design to the unmanned aerial vehicle structure, can realize stretching and the shrink to first wing and the second wing that unmanned aerial vehicle fuselage both sides set up through the movable assembly that sets up, the firing equipment of being convenient for can also take off with higher speed unmanned aerial vehicle through firing equipment when concentrating on carrying a large amount of unmanned aerial vehicles, improves the combat effect.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field specifically is a direct transmission is from suicide type unmanned aerial vehicle that cruises oneself.
Background
The unmanned aerial vehicle is provided with no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar.
Compared with manned aircraft, it has the advantages of small volume, low cost, convenient use, low requirement on the operational environment, strong battlefield viability and the like. Since the unmanned aircraft has important significance for future air battles, the research and development work of the unmanned aircraft is carried out in all major military countries in the world.
Most wings of the unmanned aerial vehicle in the prior art are fixed in unfolded positions, so that the size of the whole unmanned aerial vehicle body structure is large and the unmanned aerial vehicle is not convenient to place; when the unmanned aerial vehicle with longer wings and larger space volume takes off, the unmanned aerial vehicle generally first accelerates to slide and displace on the ground and then takes off, and the series of processes are longer; in addition, although there are vertical take-off and landing unmanned aerial vehicles, the wings of the unmanned aerial vehicle are unknown and fixed, and the unmanned aerial vehicle cannot be mounted on launching equipment to realize concentrated mass launching.
To the problem in the above-mentioned background art, the utility model aims at providing a direct transmission is suicide type unmanned aerial vehicle that independently cruises.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a direct transmission is from suicide type unmanned aerial vehicle that cruises oneself to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a direct-emitting autonomous-cruise suicide unmanned aerial vehicle, comprising:
the aircraft body is in a triangular streamline shape, a motor is arranged in the aircraft body, the output end of the motor is a driving shaft, and the tail end of the driving shaft is provided with a propelling paddle which is in a shape of two blades;
two wings, namely a first wing and a second wing, are movably mounted on two sides of the fuselage respectively; the movable assembly is arranged on the fuselage and is simultaneously connected with the first wing and the second wing; the laser guidance system is arranged in the machine body.
As a further aspect of the present invention: the movable assembly comprises a sliding block and a pneumatic push rod, a second fixing plate is arranged on the machine body, one end of the pneumatic push rod is connected with the second fixing plate, the other end of the pneumatic push rod is connected with the middle of the sliding block, and movable grooves are formed in two sides of the surface of the sliding block; a first fixing plate is also arranged on the machine body, and cross rods are fixedly arranged on two sides of the first fixing plate; the sliding blocks are arranged and are arranged on the cross rods fixedly arranged on the two sides of the first fixing plate in a sliding mode.
As a further aspect of the present invention: the end of the first wing facing the fuselage and the end of the second wing facing the fuselage are both provided with a limiting column, and the limiting column arranged on the first wing and the limiting column arranged on the second wing are respectively and movably arranged in a movable groove formed on the sliding block; the middle of the first wing and the middle of the second wing are movably arranged on the machine body through rotating shafts.
Compared with the prior art, the beneficial effects of the utility model are that:
direct transmission independently cruise suicide type unmanned aerial vehicle carry out the improved design to the unmanned aerial vehicle structure, can realize stretching and the shrink to first wing and the second wing that unmanned aerial vehicle fuselage both sides set up through the movable assembly that sets up, the firing equipment of being convenient for can also take off with higher speed unmanned aerial vehicle through firing equipment when concentrating on carrying a large amount of unmanned aerial vehicles, improves the combat effect.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following descriptions are only some embodiments of the present invention.
Fig. 1 is the utility model discloses a direct transmission is from dynamic cruise suicide formula unmanned aerial vehicle's schematic structure.
Fig. 2 is the utility model discloses a direct transmission is from top view of independently cruising suicide unmanned aerial vehicle.
In the figure: 1-propelling propeller, 2-driving shaft, 3-fuselage, 4-first wing, 5-second wing, 6-first fixed plate, 7-cross bar, 8-slide block, 9-rotating shaft, 10-movable groove, 11-spacing column, 12-pneumatic push rod and 13-second fixed plate.
Detailed Description
In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to illustrate the present invention in further detail. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
Examples
Referring to fig. 1 and 2, an embodiment of the present invention provides a direct-emitting autonomous cruise suicide unmanned aerial vehicle; direct transmission is from dynamic cruise suicide formula unmanned aerial vehicle includes:
the aircraft body 3 is in a triangular streamline shape, a motor is arranged in the aircraft body 3, the output end of the motor is a driving shaft 2, the tail end of the driving shaft 2 is provided with a propelling paddle 1, and the propelling paddle 1 is in a shape of two blades; starting a motor, wherein the motor runs to transmit kinetic energy to the propelling paddle 1 through the driving shaft 2, and the propelling paddle 1 rotates at a high speed to generate power for the whole direct-emission autonomous-cruise suicide type unmanned aerial vehicle during flying propulsion;
two wings, namely a first wing 4 and a second wing 5, are movably mounted on two sides of the fuselage 3 respectively; the fuselage 3 is provided with a movable assembly which is connected with the first wing 4 and the second wing 5 at the same time;
a laser guidance system is arranged in the machine body 3, and the laser guidance system is the prior art and is not further explained herein;
when the direct-emission autonomous cruise suicide unmanned aerial vehicle is used, the direct-emission autonomous cruise suicide unmanned aerial vehicle is loaded on an emission device, the emission device comprises an individual soldier emission tube, a vehicle-mounted emission tube and an airborne emission tube, and the setting can be carried out according to the actual combat simulation requirement; after the launching equipment launches the direct-launching autonomous cruise suicide unmanned aerial vehicle, the unmanned aerial vehicle generates a certain flight acceleration, and after a certain speed is reached, a motor arranged inside the body 3 and a movable assembly arranged outside the body 3 are started; the motor generates power to push the propulsion propeller 1 to rotate at a high speed, and the power generated when the whole direct-emitting autonomous-cruise suicide unmanned aerial vehicle flies is generated; the movable assembly can simultaneously unfold the first wing 4 and the second wing 5 to generate the lift force when the direct-launching autonomous cruise suicide unmanned aerial vehicle flies; in addition, the whole direct-emitting autonomous cruise suicide unmanned aerial vehicle realizes accurate striking on the target through the cooperation of a laser guidance system arranged in the body 3 and the laser irradiation target emitted by the emitting equipment;
furthermore, the movable assembly comprises a sliding block 8 and a pneumatic push rod 12, a second fixing plate 13 is arranged on the machine body 3, one end of the pneumatic push rod 12 is connected with the second fixing plate 13, the other end of the pneumatic push rod 12 is connected with the middle of the sliding block 8, and movable grooves 10 are formed in two sides of the surface of the sliding block 8; a first fixing plate 6 is further arranged on the machine body 3, and cross rods 7 are fixedly arranged on two sides of the first fixing plate 6; the arranged slide block 8 is arranged on a cross rod 7 which is arranged and fixed on two sides of the first fixing plate 6 in a sliding way;
specifically, one end of the first wing 4 facing the fuselage 3 and one end of the second wing 5 facing the fuselage 3 are both provided with a limiting column 11, and the limiting column 11 arranged on the first wing 4 and the limiting column 11 arranged on the second wing 5 are respectively and movably arranged in a movable groove 10 formed in the sliding block 8; the middle of the first wing 4 and the middle of the second wing 5 are movably arranged on the fuselage 3 through a rotating shaft 9;
when the movable assembly is used for unfolding and contracting the first wing 4 and the second wing 5 arranged on two sides of the fuselage 3, the pneumatic push rod 12 is started, the pneumatic push rod 12 operates to push the sliding block 8 to slide on the cross rod 7 for displacement, and because the limiting column 11 arranged at one end of the first wing 4 and the limiting column 11 arranged at one end of the second wing 5 are both movably arranged in the movable groove 10 formed in the sliding block 8 in a limiting manner, when the sliding block 8 slides on the cross rod 7 for displacement, the arranged first wing 4 and the arranged second wing 5 rotate through the installed rotating shaft 9, so that the first wing 4 and the second wing 5 of the wings are contracted and expanded;
the embodiment of the utility model provides a theory of operation is:
the direct-emission autonomous cruise suicide unmanned aerial vehicle can realize the contraction and extension of the first wing 4 and the second wing 5 through the installed movable components, so that the space volume is conveniently reduced, a large amount of storage is facilitated in the emission equipment, the emission equipment can simultaneously emit a large amount of direct-emission autonomous cruise suicide unmanned aerial vehicle to accurately strike a target, and the combat effect is improved; and the firing equipment can also exert acceleration to unmanned aerial vehicle, improves direct transmission is from the take-off speed of cruising suicide unmanned aerial vehicle.
In the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (3)
1. A direct-launch autonomous cruise suicide drone, comprising: a body (3); the method is characterized in that:
the machine body (3) is in a triangular streamline shape, a motor is arranged in the machine body (3), the output end of the motor is a driving shaft (2), the tail end of the driving shaft (2) is provided with a propelling propeller (1), and the propelling propeller (1) is in a two-blade shape;
two wings, namely a first wing (4) and a second wing (5), are movably mounted on two sides of the fuselage (3) respectively; the movable assembly is arranged on the airplane body (3) and is connected with the first wing (4) and the second wing (5) at the same time; the laser guidance system is arranged in the machine body (3).
2. The direct-launch autonomous cruise suicide drone of claim 1, wherein: the movable assembly comprises a sliding block (8) and a pneumatic push rod (12), a second fixing plate (13) is arranged on the machine body (3), one end of the pneumatic push rod (12) is connected with the second fixing plate (13), the other end of the pneumatic push rod (12) is connected with the middle of the sliding block (8), and movable grooves (10) are formed in two sides of the surface of the sliding block (8); a first fixing plate (6) is further arranged on the machine body (3), and cross rods (7) are fixedly arranged on two sides of the first fixing plate (6); the arranged slide blocks (8) are slidably arranged on the cross rods (7) fixedly arranged on the two sides of the first fixing plate (6).
3. The direct-launch autonomous cruise suicide drone of claim 2, wherein: limiting columns (11) are respectively arranged at one end of the first wing (4) facing the fuselage (3) and one end of the second wing (5) facing the fuselage (3), and the limiting columns (11) arranged on the first wing (4) and the limiting columns (11) arranged on the second wing (5) are respectively and movably arranged in a movable groove (10) formed in the sliding block (8); the middle of the first wing (4) and the middle of the second wing (5) are movably arranged on the fuselage (3) through a rotating shaft (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122593441.5U CN217227916U (en) | 2021-10-27 | 2021-10-27 | Direct-emission autonomous cruise suicide type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122593441.5U CN217227916U (en) | 2021-10-27 | 2021-10-27 | Direct-emission autonomous cruise suicide type unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217227916U true CN217227916U (en) | 2022-08-19 |
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ID=82816940
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122593441.5U Active CN217227916U (en) | 2021-10-27 | 2021-10-27 | Direct-emission autonomous cruise suicide type unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217227916U (en) |
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2021
- 2021-10-27 CN CN202122593441.5U patent/CN217227916U/en active Active
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