CN108284944A - A kind of mini foldable fixed-wing unmanned plane - Google Patents

Abstract

The invention relates to a small foldable fixed-wing unmanned aerial vehicle, which comprises a wing folding device, a body, a center of gravity adjustment mechanism, a power part, a rocket booster and a separation mechanism. The lateral size of the fuselage can be greatly reduced through the radial folding of the wings, empennage and vertical tail, so that they can be stored in a cylindrical launch tube, which is convenient for storage and transportation. When launching, there is no need to manually take out and assemble, boost the rocket point and then push the body out of the launch tube. After leaving the launch tube, the wings and tail are unfolded and fixed. When the fuel of the booster rocket is exhausted, it will be separated from the body, and the brushless motor will drive the folding paddles to rotate and start cruising. The body adopts elevator-aileron mixed control, which can effectively reduce the control surface and mechanical structure, which not only reduces costs but also improves reliability. This design can be widely used in small and medium-sized aircraft models, mobile carriers of fixed-wing UAVs, etc. On the other hand, the lateral size of the body during launch and transportation is reduced, the operation steps are simplified, and the control is easier.

Description

A small folding fixed-wing UAV

technical field

The invention belongs to the field of aircraft, and in particular relates to a small folding fixed-wing unmanned aerial vehicle.

Background technique

The quality and overall size of a small fixed-wing UAV are one of the important symbols of the technical level. An effective way to reduce the overall size of fixed-wing UAVs is to use folding wings. With the development of fixed-wing UAV technology, especially the advancement of launch technology, storage and transportation launchers are widely used. Folding the wings can also reduce the lateral size of the launch tube, which creates new opportunities for the integrated design of the launcher and fixed-wing UAV. conditions.

Contents of the invention

The purpose of the present invention is to provide a small foldable fixed wing unmanned aerial vehicle for the small foldable fixed wing unmanned aerial vehicle. When pushing away from the launch tube, the folded part of the wing releases the constraints at the specified time, automatically unfolds, and locks at the design position, and has the ability to withstand sufficient static and dynamic loads to ensure normal flight. It can effectively reduce the lateral size of the airframe and facilitate Storage and transportation, can be automatically deployed and launched.

The present invention solves technical problem and adopts following technical scheme:

A small folding fixed-wing unmanned aerial vehicle is characterized in that it comprises a wing folding device, a booster rocket, a power unit, a tail folding device, a wing, an equipment cabin, a center of gravity adjustment mechanism, a vertical tail folding device and a body.

Described wing folding device is made of wing, fixing pin, chute, fixing device, bearing and spring, and wing is connected with fixing device through bearing, and fixing pin and wing are fixedly connected and can move in chute, and through spring and Fixtures are attached. When the UAV is placed in the launch tube, the wing rotates forward around the bearing and drives the fixed pin to tension the spring. When the UAV leaves the launch tube, the spring pulls the wings to expand backward and is fixed by the fixing device. The equipment compartment and the center of gravity adjustment mechanism can move forward and backward along the carbon tube to adjust the center of gravity of the body to adapt to different task loads. The booster rocket is inserted in the carbon tube to push the body out of the launch tube, and make the body have a certain initial velocity. When the fuel is exhausted, that is, the thrust of the rocket is less than the elastic force of the spring, the booster rocket is ejected by the spring and separated from the body. The power device can drive the folding paddles to rotate by the brushless motor after the booster rocket is separated, so as to provide power for the cruise of the body.

The invention has the beneficial effects of greatly reducing the lateral size of the body during launch and transportation, simplifying the operation steps and making it easier to control.

Description of drawings

Fig. 1 is axonometric schematic view of the present invention;

Fig. 2 is a schematic diagram of the wing folding device of the present invention;

Fig. 3 is a schematic diagram of rocket boosting and separation of the present invention;

Fig. 4 is a schematic diagram of a power system of the present invention;

In the figure: 1 is the wing folding device, 2 is the booster rocket, 3 is the power device, 4 is the tail folding device, 5 is the wing, 6 is the equipment cabin and the center of gravity adjustment mechanism, 7 is the vertical tail folding device, 16 is the body.

Detailed ways

The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

Example

As shown in Figures 1 to 4, a small foldable fixed-wing UAV includes 1 as a wing folding device, 2 as a booster rocket, 3 as a power device, 4 as a tail folding device, 5 as a wing, 6 For the equipment compartment and the center of gravity adjustment mechanism, 7 is the vertical tail folding device, and 16 is the body. Described wing folding device 1 is made of wing 5, fixing pin 11, chute 10, fixing device 12, bearing 8, spring 9. The wing 5 is connected with the fixing device 12 through the bearing 8, and the fixed pin 11 is fixedly connected with the wing 5 and can move in the chute 12, and is connected with the fixing device 12 through the spring 9. When the drone was placed in the launch tube, the wing 5 rotated forward around the bearing 8 and drove the fixing pin 11 to tighten the spring 9 . When the UAV leaves the launch tube, the spring 9 pulls the fixing pin 11 and the wing 5 to expand backward and the fixing device 12 prevents the wing from turning over a predetermined angle, and the wing is in the design position under the action of the spring 9 and the fixing device 12 Keep locked, and have the ability to bear enough static and dynamic loads to ensure normal flight. The equipment cabin and the center of gravity adjustment mechanism 6 can move forward and backward along the carbon tube 13 to adjust the center of gravity of the body to adapt to different task loads. The booster rocket 2 is inserted in the carbon tube 13 to push the body out of the launch tube, and make the body have a certain initial velocity. When the fuel is exhausted, that is, the thrust of the rocket is less than the elastic force of the spring 14, the booster rocket 2 is ejected by the spring 14 and separated from the body . The speed when the booster rocket separates can be adjusted by setting the distance between the limit block 15 fixed in the carbon tube 13 of the fuselage and the booster rocket 2 . The power unit 3 can drive the folding paddle 18 to rotate by the brushless motor 17 after the booster rocket 2 is separated, so as to unfold the backward-folded paddle, and provide power for the body to cruise when a certain speed is reached.

Claims (3)

1. A folding fixed-wing unmanned aerial vehicle, characterized in that it includes a wing folding device (1), a booster rocket (2), a power unit (3), an empennage folding device (4), and a wing (5) , equipment compartment and center of gravity adjustment mechanism (6), vertical tail folding device (7) and body (16); ), fixing device (12), bearing (8) and spring (9), wherein the wing (5) is connected to the fixing device (12) through the bearing (8), and the fixing pin (11) is fixed to the wing (5) connected, and the fixed pin (11) can move in the chute (12), the fixed pin (11) is connected with the fixing device (12) through the spring (9); the equipment compartment and the center of gravity adjustment mechanism (6) can be moved along the carbon The tube (13) moves back and forth to adjust the center of gravity of the body to adapt to different task loads; the booster rocket (2) is inserted into the carbon tube (13) to push the body out of the launch tube and make the body have a certain initial velocity. When the thrust of the rocket is less than the elastic force of the spring (14), the booster rocket (2) is ejected by the spring (14) and separated from the body; the power unit (3) can be powered by a brushless The motor (17) drives the folding paddle (18) to rotate so as to provide power for the cruise of the body. 2. The folding fixed-wing UAV according to claim 1, characterized in that the wing folding device (1) can automatically open and fix the wing (5) backwards after leaving the launch tube. 3. The foldable fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: the equipment cabin and the center of gravity adjustment mechanism (6) can move back and forth along the carbon tube (13) to adjust the center of gravity of the aircraft.