CN108100287B - Unmanned aerial vehicle empty base emitter - Google Patents

Abstract

The invention discloses an unmanned aerial vehicle air-based launching device. The device comprises a slide rail, a transmitting bracket and a transmitter. Each launcher is provided with a plurality of launcher tubes, each launcher tube comprises an ejection device, and the ejection device comprises a single-double lug structure, a spring device and a steel cable and can be used for placing a plurality of swarm unmanned aerial vehicles. Before the transmission, place unmanned aerial vehicle in the launching tube earlier, then emit the transmitter through the transmission support. During the transmission, take out dead spring assembly's of lock steel cable, unblock spring assembly with the help of the thrust that spring assembly produced in the jettison device releases unmanned aerial vehicle launch canister when not damaging unmanned aerial vehicle structure and equipment, accomplishes unmanned aerial vehicle's transmission. Compared with the existing launching mode, the method has the advantages that the space utilization efficiency is high, a certain number of unmanned aerial vehicles can be launched simultaneously, and the time consumed by the unmanned aerial vehicle cluster in the launching process is shortened; the secondary preparation time of the emitter is short, and the working efficiency is high.

Description

A UAV space-based launcher

technical field

The invention discloses an unmanned aerial vehicle air-based launching device based on a launch tube with an ejection device, which belongs to the unmanned aerial vehicle launching field of aeronautical aircraft technology.

Background technique

Since the 1930s, people have begun to yearn for the realization of the space-based launch of the aircraft. This launch method transports the child aircraft to the mission area through the mother aircraft with a large range and a large load, which can greatly increase the cruising radius of the child aircraft and get rid of the The ground airport restrictions are increased, and the flexibility of the take-off and landing of the sub-aircraft is increased. However, limited by technology, risk and cost, aircraft space-based launch technology has not been well developed.

In recent years, with the development of UAV technology and the recent proposal of swarm UAV tactics, the air-based launch technology of small UAVs has attracted more and more attention in the aviation field. Small UAS have proven their worth on the battlefield and are used by both conventional and special operations forces to provide point, route, and environmental reconnaissance, target acquisition, battle damage assessment, and other innovative applications. Small unmanned aerial systems will enhance or redefine air combat power through the concept of "game-changing". Various new forms of UAV combat emerge in an endless stream, and swarm UAV tactics are one of them. However, the inherent disadvantages of small UAVs still restrict the swarm UAV tactics from being practical on the battlefield. Small UAVs are light in weight, low in speed, much smaller in flight time and range than large UAVs, have a limited combat radius, and have poor ability to advance in combat. The advantages of group operations have become an obstacle to the implementation of innovative combat concepts and combat missions of small and medium-sized UAVs. The most direct and effective way to solve the inherent disadvantages of small UAVs is to choose the space-based launch and recovery method. Use a large transport aircraft as an air carrier to bring small drones to the mission area, and then launch them in the air quickly. Taking advantage of the swarm combat advantages of drones, reconnaissance and strikes are carried out on sensitive areas of the target. Swarms of drones for recovery.

Existing UAV air-based rapid launch devices, such as patents CN205345355U, CN105109685A and CN205256690U, all use ejection equipment to realize the UAV launch process. The main disadvantage of these methods is that only one UAV can be launched at a time, the preparation time required for the secondary launch is long, and the launch efficiency is low. For a large number of small UAVs to be launched at the same time, a large number of transmitters are required, which requires a large amount of space on the parent aircraft, and at the same time requires a large number of operators.

SUMMARY OF THE INVENTION

In view of the above problems, the present invention mainly solves the problem of the rapid launch of the UAV space-based, and proposes a new-structured UAV space-based rapid launch device.

The technical scheme adopted in the present invention is as follows:

An air-based launching device for an unmanned aerial vehicle, the air-based launching device includes: a sliding rail, a retractable launcher bracket and a launcher, and a plurality of the launchers are mounted on the sliding rail, so that one launcher can complete the launch Switch with the next launcher after the mission;

One end of the retractable launcher bracket is installed on the slide rail, which can slide along the slide rail; the other end is connected to the launcher; one end of the launcher bracket can also be rotated around the root hinge, which can be launched according to different The angle requirement adjusts the alignment direction of the launcher, so that the small UAV can launch horizontally, vertically or at any angle; the launcher is a multi-tube launching device, which includes a plurality of launch tubes, each of the A small unmanned aerial vehicle in a folded and stored state is placed in the launch cylinder, and an ejection device is arranged in each launch cylinder.

Preferably, the ejection device includes a single-dual-tab structure, a spring device and a steel cable, one end of the spring device is connected to the launch cylinder, and the other end is connected to the folded state through the single-dual-tab structure. Small drone connection; the steel cable passes through the single-double lug structure to lock the spring device.

Preferably, the transmitter brackets are multiple sets.

Preferably, the sliding rail is installed and fixed on the floor in the main machine body.

Preferably, the slide rail is a double rail slide structure.

Preferably, when launching, the steel cable locking the spring device is pulled out, the spring device is unlocked, and the small drone is sent out of the launch tube by the force generated when the spring device is released to complete the launch of the small drone.

Preferably, when the small unmanned aerial vehicle is in a folded storage state, it is stored in the body of the parent aircraft while maintaining the vertical launch direction.

Preferably, the launcher bracket is driven and slid on the slide rail by a driving device. The driving device can be a servo motor, a pulley or other devices known in the art.

The advantages of the present invention are:

(1) A set of launch equipment is used to realize the simultaneous launch of small UAVs in batches to improve the efficiency of space-based launch.

(2) The launch bracket can control and adjust the launch direction of the UAV, and can realize the launch of the UAV at any and selected angles.

(3) The operation is simple, and there are fewer participants in the operation process;

(4) Multiple transmitters can be configured in one parent aircraft, and other transmitters can be used to continue to launch during the preparation of one launch, which can save a lot of time.

Description of drawings

FIG. 1 is a schematic diagram of the position of the transmitter and its constituent mechanism when the UAV air-based launching device of the present invention is launched horizontally.

FIG. 2 is a schematic diagram of the position of the transmitter and its constituent mechanism when the UAV air-based launching device of the present invention is vertically launched.

FIG. 3 is a schematic diagram of the state of the UAV air-based launching device stored in the parent machine in a folded and stored state of the present invention.

FIG. 4 is a schematic diagram of the operation of multiple launchers in the slide rail in the UAV air-based launch device in the main body of the present invention.

FIG. 5 is a schematic diagram of the state in the launch tube of the UAV air-based launch device of the present invention before launch.

6 is a structural diagram of the composition of the ejection device in the launch tube of the UAV air-based launch device of the present invention.

FIG. 7 is a schematic diagram of the unmanned aerial vehicle space-based launch device of the present invention after it is released when it performs a horizontal launch task.

Among them, 1 is the mother machine, 2 is the slide rail, 3 is the launcher bracket, 4 is the launcher, 5 is the launch tube, 6 is the small drone in the folded storage state, and 7 is the small drone in the unfolded state. 8 is a spring device, 9 is a single-double lug structure, 10 is a steel cable, and 11 is a driving device.

Detailed ways

As shown in Figure 1, the Y-8 is used as the mother machine 1. The mother machine 1 carries the UAV air-based launcher, and the small folding UAV with a weight of 10kg and a range of 150km is transported to the mission site 600km away. The UAV air-based launching device includes: a slide rail 2 with a double-track slideway structure, a retractable launcher bracket 3 and three launchers 4, and three launchers 4 are mounted on the slide rail 2. , it is convenient for one launcher 4 to switch with the next launcher 4 after completing the launch task; the slide rail 2 is installed and fixed on the floor in the main body of the host machine 1; one end of the retractable launcher bracket 3 is installed on the slide rail 2 It can slide along the slide rail 2; the other end is connected to the launcher 4; one end of the launcher bracket 3 can also be rotated around the root hinge, which can align the launcher 4 according to the needs of different launch angles. Make adjustments to enable the small drone 6 to launch horizontally, vertically or at any angle; the launcher 4 includes 10 launch tubes 5, and each of the launch tubes 5 places a small drone in a folded storage state. Man-machine 6, an ejection device is arranged in each of the launch cylinders 5;

The ejection device includes a single-double lug structure 9, a spring device 8 and a steel cable 10. One end of the spring device 8 is connected to the launch cylinder 5, and the other end is connected to the spool through the single-double lug structure 9. The small unmanned aerial vehicle 6 in the folded state is connected; the steel cable 10 passes through the single-double lug structure 9 to lock the spring device 8 .

The launching device includes three launchers 4 , the launchers are 760mm long, 300mm wide, and the depth of the launch tube is 1100mm. The device is designed with 10 launch tubes 5 , which can simultaneously launch 10 small UAVs 6 . During the flight of the base aircraft 1, the three launchers 4 are in the storage state and mounted on the slide rail 2, as shown in Figure 3; after arriving at the mission site, the operator sends an instruction to perform a horizontal launch. After receiving the instruction, the program controls to release and extend the transmitter 4 to the outside of the main machine 1, and the transmitter bracket 3 adjusts the transmitter 4 to the horizontal launch angle according to the instruction, as shown in FIG. 1 . After the launcher 4 is in place, the operator issues a launch command, pulls out the steel cable 10 , triggers the spring device 8 , and pushes the small drone 6 in the launch tube 5 out of the launcher 4 to complete the launch of the small drone 6 .

Contents that are not described in detail in the specification of the present invention belong to the prior art known to those skilled in the art. The above-mentioned embodiments of the present invention are intended to illustrate the solutions and cannot be used to limit the present invention. Any changes within the meaning and scope equivalent to the protection scope of the present invention should be considered to be included in the protection scope of the present invention.

Claims (7)

1. an unmanned aerial vehicle air-based launcher, is characterized in that, this air-based launcher comprises: slide rail (2), retractable launcher bracket (3) and launcher (4), in described slide rail ( 2) mounting a plurality of said transmitters (4) on it, so that one transmitter (4) can switch with the next transmitter (4) after completing the launch task; One end of the retractable transmitter bracket (3) is mounted on the sliding rail (2), which can slide along the sliding rail (2); the other end is connected to the transmitter (4); the transmitter bracket ( 3) One end can also be rotated around the root hinge, and the alignment direction of the launcher (4) can be adjusted according to different launch angle requirements, so that the small drone (6) can be launched horizontally, vertically or at any other angle; The launcher (4) is a multi-tube launching device, which includes a plurality of launch cylinders (5), and a small unmanned aerial vehicle (6) in a folded storage state is placed in each launch cylinder (5), An ejection device is arranged in each of the launch cylinders (5); The ejection device comprises a single-double ear piece structure (9), a spring device (8) and a steel cable (10). The single-double lug structure (9) is connected with the small unmanned aerial vehicle (6) in a folded state; the steel cable (10) passes through the single-double lug structure (9) to lock the spring device (8). 2. An air-based launching device for unmanned aerial vehicle as claimed in claim 1, characterized in that, the launcher brackets (3) are multiple sets. 3. An unmanned aerial vehicle air-based launching device according to claim 1, characterized in that, the slide rail (2) is installed and fixed on the floor in the body of the mother machine (1). 4. An air-based launching device for unmanned aerial vehicle according to claim 1, characterized in that, the slide rail (2) is a double-track slideway structure. 5. An unmanned aerial vehicle air-based launching device as claimed in claim 1, characterized in that when launching, the steel cable (10) of the locking spring device (8) is drawn out, the spring device (8) is unlocked, and the The force generated when the spring device (8) is released sends the small unmanned aerial vehicle out of the launch tube (5) to complete the launch of the small unmanned aerial vehicle. 6. An unmanned aerial vehicle air-based launching device as claimed in claim 1, characterized in that, when the small unmanned aerial vehicle is in a folded and stored state, the direction during vertical launch is kept and stored in the body of the parent machine (1). . 7. An air-based launching device for unmanned aerial vehicle according to claim 1, characterized in that, the launcher bracket (3) is driven and slid on the slide rail by a driving device.

Images