CN214223881U - Novel duct formula flight bomb - Google Patents
Novel duct formula flight bomb Download PDFInfo
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- CN214223881U CN214223881U CN202022961385.1U CN202022961385U CN214223881U CN 214223881 U CN214223881 U CN 214223881U CN 202022961385 U CN202022961385 U CN 202022961385U CN 214223881 U CN214223881 U CN 214223881U
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- 238000012986 modification Methods 0.000 description 2
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Abstract
The utility model discloses a novel duct-type flying bomb, which belongs to the field of ducts and rotorcraft, and comprises a duct and a center shaft, wherein four groups of rotors are symmetrically arranged around the wall surface of the center shaft, and each rotor comprises a blade and an electric control blade trailing edge arranged at the blade trailing edge part; a plurality of groups of electric control surfaces are arranged below the rotor wing and between the middle shaft and the duct; the rear edge of the electric control paddle is made of intelligent piezoelectric materials, and the torsion angle of the electric control paddle is changed by changing the electrified voltage of the rear edge of the electric control paddle, so that the lift force of the paddle is changed; the electronic control surface is made of intelligent piezoelectric materials, and the torsion angle of the electronic control surface can be changed by changing the size of the electrified voltage of the electronic control surface, so that the size of the torque is changed, and finally, the novel ducted flying bomb is controlled by lowering, raising, yawing left, yawing right and rolling. This novel duct formula flight bomb of section not only can realize VTOL, control efficiently, can also keep the noise less when attacking.
Description
Technical Field
The utility model relates to a portable weapon device relates to duct, rotor craft field, specifically is a novel duct formula flight bomb.
Background
Micro-aircraft are of interest for particular applications. The most important application is military reconnaissance for enemy reconnaissance and surveillance. It is suitable for various war environments such as city, jungle, etc. Because of the advantages of convenient carrying, simple operation and good safety, the utility model can be equipped in large quantities in troops. The micro-aircraft under study are mainly of three types, one is a fixed wing model like an airplane, the second is a flapping wing model like insects and birds, and the third is a rotor wing model like a helicopter. However, the prior micro-rotor aircraft has the defects that the size of the aircraft is large due to the complexity of the operating mechanism, the operating efficiency of the operating mechanism is low, and the noise is large.
SUMMERY OF THE UTILITY MODEL
The utility model discloses to the problem that exists among the prior art, designed a novel duct formula flight bomb, the utility model discloses a novel duct formula flight bomb is equipped with the outside duct respectively, four paddles, eight automatically controlled rudder faces, and this kind of novel duct formula flight bomb not only can realize VTOL, control efficiently, can also keep the noise less when attacking.
The utility model discloses a realize like this:
the utility model provides a novel duct formula flight bomb, the flight bomb axis that includes duct and duct central point and set up. According to the different demands of military use, the camera can be adorned to the duct outside and surveyed the enemy, and the middle shaft part can install different weapons additional and attack the enemy. Four groups of rotors are symmetrically arranged on the periphery of the wall surface of the central shaft, and each rotor comprises a blade and an electric control blade trailing edge arranged at the blade trailing edge part; and a plurality of groups of electric control surfaces are arranged below the rotor wing and between the middle shaft and the duct.
The rear edge of the electric control paddle is made of intelligent piezoelectric materials, and the torsion angle of the electric control paddle is changed by changing the electrified voltage of the rear edge of the electric control paddle, so that the lift force of the paddle is changed; the automatically controlled control surface be intelligent piezoelectric material, can change the torsion angle of automatically controlled control surface through the circular telegram voltage size that changes automatically controlled control surface to change the size of moment of torsion, and then realize that novel duct formula flight bomb is low, new line, left driftage, right drift and roll over and control. The utility model discloses be equipped with outside duct, four paddles, eight automatically controlled rudder faces respectively. The electric control rotor wing can control the camber of the blade to realize vertical take-off and landing, the camber of the corresponding blade can be changed to realize forward flight and yaw, and the electric control surface is controlled to realize the rolling of flying missiles. The novel ducted flying bomb not only can realize vertical take-off and landing and high control efficiency, but also can keep the noise small during attack. In the process of battle, the bomb cannot be accurately thrown for hitting enemies due to the influence of terrain, so that the flying bomb which is low in noise, high in manipulation efficiency, and capable of taking off and landing vertically and flying forwards is needed.
Furthermore, eight electric control surfaces are arranged and connected with the duct and the middle shaft through connecting rods.
Furthermore, the middle shaft is streamline, the upper part of the middle shaft comprises a motor and a battery sensor part, and the lower part of the middle shaft is provided with a bomb device.
The utility model discloses with prior art my beneficial effect lie in:
1) has higher safety: due to the existence of the duct, when the flying bomb takes off and lands on the ground, the rotating rotor wing does not hurt pedestrians or influence or even cause danger to surrounding people, automobiles, buildings, plants and the like;
2) the noise is low: the design of the duct is added, and the electric control rotor is used, so that no interference noise between a rotor shaft and a propeller hub exists. Therefore, the noise is lower than that of the traditional rotor type aircraft;
3) the operation efficiency is good: the design of full electrification rotor wing and automatically controlled control plane alleviates the structural weight of flight bomb, improves flight bomb flight reliability, and maneuverability.
Drawings
Fig. 1 is a side view of a novel ducted flying bomb of the present invention;
fig. 2 is a front view of the novel ducted flying bomb of the present invention;
FIG. 3 is an isometric view of a novel ducted flying bomb of the present invention;
fig. 4 is a top view of the novel ducted flying bomb of the present invention;
the wind power generation system comprises a duct 1, a middle shaft 2, a blade 3, an electric control blade trailing edge 4, an electric control surface 5 and a connecting rod 6.
Detailed Description
In order to make the purpose, technical solution and effect of the present invention clearer and more clear, it is clear that the following list examples are to the present invention for further detailed description. It should be noted that the embodiments described herein are only for explaining the present invention and are not used to limit the present invention.
As shown in fig. 1-4, the utility model relates to a novel duct formula flight bomb, novel duct formula flight bomb be central symmetrical structure, include: the culvert comprises a duct 1, a middle shaft 2, blades 3, electric control blade trailing edges 4, an electric control surface 5 and a connecting rod 6.
The middle shaft 2 is in a streamline shape, front flying resistance is effectively reduced, a motor, a battery, a sensor and other parts are arranged above the middle shaft, and a bomb device is arranged below the middle shaft. The four groups of rotors are symmetrically arranged on the periphery of the wall surface of the central shaft 2, each rotor comprises a blade 3 and an electric control blade trailing edge 4 arranged at the trailing edge part of the blade 3, the electric control blade trailing edge 4 is made of an intelligent piezoelectric material, and the torsion angle of the electric control blade trailing edge 4 can be changed by changing the electrified voltage of the electric control blade trailing edge 4, so that the lift force of the blade 3 is changed.
And a plurality of groups of electric control surfaces 5 are arranged below the rotor wing and between the middle shaft 2 and the duct 1. The total number of the electric control surfaces 5 is 8, and the electric control surfaces 5 are connected with the duct 1 and the middle shaft 2 through connecting rods 6. The electric control surface 5 is made of intelligent piezoelectric materials, and the torsion angle of the electric control surface 5 can be changed by changing the electrified voltage of the electric control surface, so that the torque can be changed.
The utility model relates to a novel duct formula flight bomb's working method does:
1) when the flying bomb needs to bow, the electrified voltage in the blade is weakened at the front part, the trailing edge bending of the blade at the position is reduced, so that the lift force is reduced, the electrified voltage in the blade is increased at the rear part, the trailing edge bending of the blade at the position is increased, so that the lift force is increased, a head-down moment is generated, and the flying bomb is bow;
2) when the flying bomb needs to raise the head, the aircraft flies in a raising way by increasing the front lift force and weakening the rear lift force in the same way as the step 1);
3) when the flying bomb needs to yaw left, the left lift force is weakened and the right lift force is increased to yaw left in the same way as the step 1);
4) when the flying bomb needs to yaw right, increasing the left lift force and weakening the right lift force to yaw right in the same way as the step 1);
5) when the flight bomb carries out the roll operation, the lower wash-off of rotor hits and will make the control surface produce aerodynamic force on the control surface, changes the size of the power of the same direction of multi-disc control surface through adjusting control surface voltage size to the produced moment of torsion size of automatically controlled control surface of realization regulation, is equal to the rotor torque when this moment of torsion, and the aircraft is not rolled, is greater than the rotor torque when this moment of torsion and will roll clockwise, is less than the rotor torque and will roll anticlockwise when this moment of torsion.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications can be made without departing from the principles of the present invention, and these modifications should also be regarded as the protection scope of the present invention.
Claims (3)
1. The novel ducted flight bomb is characterized by comprising a duct (1) and a middle shaft (2) arranged at the center of the duct (1), wherein four groups of rotors are symmetrically arranged on the periphery of the wall surface of the middle shaft (2), and each rotor comprises a blade (3) and an electric control blade rear edge (4) arranged at the rear edge part of the blade (3); a plurality of groups of electric control surfaces (5) are arranged below the rotor wing and between the middle shaft (2) and the duct (1);
the rear edge (4) of the electric control paddle is made of an intelligent piezoelectric material, and the torsion angle of the rear edge (4) of the electric control paddle is changed by changing the power-on voltage of the rear edge (4) of the electric control paddle, so that the lift force of the paddle (3) is changed; the electric control surface (5) is made of an intelligent piezoelectric material, and the torsion angle of the electric control surface (5) can be changed by changing the size of the electrified voltage of the electric control surface (5), so that the torque of the electric control surface (5) is changed, and finally, the novel ducted flying bomb is controlled by lowering head, raising head, yawing left, yawing right and rolling.
2. The novel ducted flight bomb according to claim 1, characterized in that eight electric control surfaces (5) are provided, and the electric control surfaces (5) are connected with the duct (1) and the central shaft (2) through connecting rods (6).
3. The ducted flying bomb according to claim 1, which is characterized in that the central shaft (2) is streamlined, and the upper part of the inside of the central shaft comprises components of a motor, a battery and a sensor, and the lower part of the inside of the central shaft is provided with a bomb device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022961385.1U CN214223881U (en) | 2020-12-09 | 2020-12-09 | Novel duct formula flight bomb |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022961385.1U CN214223881U (en) | 2020-12-09 | 2020-12-09 | Novel duct formula flight bomb |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214223881U true CN214223881U (en) | 2021-09-17 |
Family
ID=77701382
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022961385.1U Active CN214223881U (en) | 2020-12-09 | 2020-12-09 | Novel duct formula flight bomb |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214223881U (en) |
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2020
- 2020-12-09 CN CN202022961385.1U patent/CN214223881U/en active Active
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