A rotary-wing airborne UAV airdrop launcher

By designing a rotorcraft-borne UAV airdrop launch device and using digital servo motors to control the opening and closing of the projection base plate, the pitch angle problem during rotorcraft flight was solved, enabling rapid and stable UAV launch and improving launch accuracy and flexibility.

CN224277618UActive Publication Date: 2026-05-26HEFEI INTELLIGENT UNMANNED SYSTEM RESEARCH INSTITUTE CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
HEFEI INTELLIGENT UNMANNED SYSTEM RESEARCH INSTITUTE CO LTD
Filing Date
2025-07-31
Publication Date
2026-05-26

AI Technical Summary

Technical Problem

Traditional cannon-type launchers are large and heavy, making them difficult to transport. Furthermore, they cannot compensate for pitch angles during rotorcraft flight, resulting in unstable drone launches and failing to meet the requirements for speed and flexibility.

Method used

A rotary-wing airborne UAV airdrop launch device was designed, including a connecting base, a connecting support, a projection bay, a projection base plate, and an electronic drive mechanism. The opening and closing state of the projection base plate is controlled by a digital servo motor to counteract the pitch angle of the rotary-wing aircraft during flight, thereby achieving rapid deployment and stable projection.

Benefits of technology

It improves the accuracy and flexibility of UAV launches, adapts to complex mission requirements, and enables rapid and stable deployment of rotary-wing airborne UAVs.

✦ Generated by Eureka AI based on patent content.

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Abstract

This utility model discloses an airdrop launch device for a rotary-wing airborne unmanned aerial vehicle (UAV), belonging to the field of UAV technology. It includes: a connecting base, a connecting support column, a projection compartment, a projection base plate, and an electronic drive mechanism. The connecting base has a connecting groove at its bottom; the projection compartment has a connecting mechanism at its top, and a digital servo mounting slot is provided on the outer surface of one side wall of the projection compartment; the projection base plate is hinged to the bottom of the other side wall of the projection compartment; one end of the connecting support column is installed in the connecting groove, and the other end is connected to the connecting mechanism of the projection compartment; the electronic drive mechanism includes a digital servo, a servo shaft, a servo arm, and a servo fixing hole; the digital servo is installed in the digital servo mounting slot of the projection compartment; the digital servo is connected to the servo arm via the servo shaft. This utility model, by designing a fixed-angle projection compartment, can effectively compensate for the pitch angle of the rotary-wing UAV during flight, thereby improving launch accuracy and flexibility.
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Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a rotary-wing airborne UAV airdrop launch device. Background Technology

[0002] With the continuous advancement of drone technology, its applications in various fields, including logistics, agriculture, and scientific research, are constantly expanding. However, traditional artillery-style launchers face numerous challenges when launching drones. These traditional launchers are generally large and heavy, making them difficult to transport and lacking in speed and flexibility, thus limiting the ability to launch drones quickly and failing to meet the needs of rescue missions. Therefore, it is necessary to develop a launcher specifically designed for small drones.

[0003] Patent (publication number CN202185090U) discloses an automatic airdrop launch device. The automatic airdrop launch device is a box with a door at the top. Inside the box, there is a boom at the top, and the guardrail in the middle is movable, which can be easily arranged into the shape of the object to be airdropped. Above the airdrop window, on the box wall, there is an electric railing perpendicular to the guardrail. The other end of the guardrail passes through a push plate and connects to the box wall. The push plate is connected to an electric micro hydraulic push rod.

[0004] Although the above technical solutions have solved the technical problems of lightweighting and precise delivery, they still have the following drawbacks: they are not convenient to drop during the flight of the rotorcraft. Due to the box-shaped cubic design, the pitch angle generated during the flight of the rotorcraft cannot be offset, which cannot ensure the stability of the loading equipment and thus reduces the effectiveness of the drop. Utility Model Content

[0005] To address the aforementioned issues, this utility model discloses a rotary-wing airborne UAV airdrop launch device, comprising: a connecting base, a connecting support, a projection bay, a projection base plate, and an electronic drive mechanism;

[0006] The bottom of the connecting base is provided with a connecting groove;

[0007] The top of the projection cabin is provided with a connecting mechanism, and a digital servo motor assembly slot is provided on the outer surface of one side wall of the projection cabin.

[0008] The projection base plate is hinged to the bottom of the other side wall of the projection chamber;

[0009] One end of the connecting support column is installed in the connecting groove, and the other end is connected to the connecting mechanism of the projection chamber;

[0010] The electronic drive mechanism includes a digital servo motor, a servo motor shaft, a servo motor arm, and a servo motor mounting hole;

[0011] The digital servo has servo mounting holes on both sides;

[0012] The digital servo is installed in the digital servo assembly slot of the projection cabin through a servo fixing hole;

[0013] The digital servo is connected to the servo arm via a servo shaft; the electronic drive mechanism is used to control the opening and closing state of the projection base plate.

[0014] Furthermore, the connecting groove sidewall is provided with a plurality of first countersunk bolt holes.

[0015] Furthermore, one end of the connecting support column is provided with a plurality of first countersunk bolt holes, and the other end is provided with a plurality of second countersunk bolt holes;

[0016] One end of the connecting support column is connected to the connecting base groove by a bolt passing through the first countersunk bolt hole; the other end is connected to the projection cabin connecting mechanism by a bolt passing through the second countersunk bolt hole.

[0017] Furthermore, the edge of the connecting base is also provided with several first countersunk bolt holes.

[0018] Furthermore, the connecting base forms a 50° angle with the vertical direction.

[0019] Furthermore, the connecting support includes a strip frame and a polygonal frame fixedly connected to the strip frame.

[0020] Furthermore, the projection chamber is entirely recessed.

[0021] Furthermore, the connecting base is plate-shaped as a whole.

[0022] Furthermore, the projection base plate is plate-shaped as a whole.

[0023] Furthermore, the connecting mechanism includes multiple protrusions on the top of the projection chamber; each protrusion is provided with a second countersunk bolt hole.

[0024] Compared with the prior art, the beneficial effects of this utility model are: the rotary-wing airborne UAV airdrop launch device of this utility model is carried by a rotary-wing UAV. By designing a fixed-angle projection cabin, the pitch angle of the rotary-wing UAV during flight can be effectively offset, so as to achieve rapid deployment and stable projection, improve launch accuracy and flexibility, and adapt to complex mission requirements.

[0025] Other features and advantages of this invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained through the structures pointed out in the description and the accompanying drawings. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 A schematic diagram of the structure of a rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown;

[0028] Figure 2 A schematic diagram of the connecting base structure of the rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown;

[0029] Figure 3 A schematic diagram of the connecting support structure of the rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown;

[0030] Figure 4 A schematic diagram of the projection compartment structure of the rotary-wing airborne UAV airdrop launcher according to an embodiment of the present invention is shown;

[0031] Figure 5 A schematic diagram of the projection base plate structure of the rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown;

[0032] Figure 6 A schematic diagram of the electronic drive mechanism of a rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown.

[0033] Reference numerals: 1. Connecting base; 2. Connecting support column; 3. Projection chamber; 4. Projection base plate; 5. Electronic drive mechanism;

[0034] 101. Connecting groove; 102. First countersunk bolt hole;

[0035] 301. Connecting mechanism; 302. Second countersunk bolt hole; 303. Digital servo motor assembly slot;

[0036] 401. Hinge bolt hole;

[0037] 501. Digital servo motor; 502. Servo motor shaft; 503. Servo motor arm; 504. Servo motor mounting hole. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0039] Figure 1 A schematic diagram of the structure of a rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown. Figure 1 As shown, the present invention proposes a rotary-wing airborne UAV airdrop launch device, comprising: a connecting base 1, a connecting support column 2, a projection cabin 3, a projection base plate 4, and an electronic drive mechanism 5;

[0040] The bottom of the connecting base 1 is provided with a boss, and a connecting groove 101 is provided on the boss;

[0041] A connecting mechanism 301 is provided on the top of the projection cabin 3, and a digital servo motor mounting slot 303 is provided on the outer surface of one side wall of the projection cabin 3 (e.g., ...). Figure 4 (As shown); Projection bay 3, used for projecting fixed-wing UAVs.

[0042] The side of the projection base plate 4 is hinged to the bottom of the other side wall of the projection chamber 3;

[0043] The top end of the connecting support column 2 is installed in the connecting groove 101 of the connecting base 1, and the bottom end is connected to the connecting mechanism 301 of the projection chamber 3 by bolts.

[0044] like Figure 6 As shown, the electronic drive mechanism 5 includes a digital servo motor 501, a servo motor shaft 502, a servo motor arm 503, and a servo motor mounting hole 504.

[0045] The digital servo motor 501 has servo motor mounting holes 504 on both sides;

[0046] The digital servo motor 501 is installed in the digital servo motor mounting slot 303 of the projection cabin 3 through the servo motor fixing hole 504;

[0047] The digital servo motor 501 is fixedly connected to the servo motor arm 503 via the servo motor shaft 502;

[0048] When the projection base plate 4 is closed, the servo arm 503 is located below the projection base plate 4, and the two are in close contact, keeping the projection base plate 4 in a closed state; the electronic drive mechanism 5 is used to control the opening and closing state of the projection base plate 4. By setting the digital servo 501 to rotate, thereby driving the servo arm 503, the opening and closing of the projection base plate 4 can be effectively controlled, thus completing the projection task.

[0049] The rotary-wing airborne UAV airdrop launch device of this utility model is carried by a rotary-wing UAV. By designing a fixed-angle projection cabin 3, it can effectively counteract the pitch angle of the rotary-wing aircraft during flight, realize rapid deployment and stable projection, improve launch accuracy and flexibility, and adapt to complex mission requirements.

[0050] In some embodiments, multiple projection bays 3 are arranged side by side below the connecting strut 2, which can improve launch efficiency.

[0051] Figure 2 A schematic diagram of the connecting base structure of a rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown. Figure 2 As shown, in some embodiments, a plurality of first countersunk bolt holes 102 are provided on the left and right sidewalls of the connecting groove 101 to ensure the connection stability between the connecting base 1 and the connecting support 2. For example, two first countersunk bolt holes 102 are provided on each of the left and right sidewalls of the connecting groove 101.

[0052] In some embodiments, the connecting base 1 is further provided with a plurality of first countersunk bolt holes 102 at its edge, and is located around the connecting groove 101 for connecting the upper rotor base plate.

[0053] Figure 3 A schematic diagram of the connecting support structure of a rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown. Figure 3 As shown, in some embodiments, the top end of the connecting support column 2 is provided with a plurality of first countersunk bolt holes 102, and the bottom end is provided with a plurality of second countersunk bolt holes 302; for example, there are two first countersunk bolt holes 102 and four second countersunk bolt holes 302.

[0054] The top end of the connecting support column 2 is connected to the connecting groove 101 of the connecting base 1 by a bolt passing through the first countersunk bolt hole 102; the bottom end is connected to the connecting mechanism 301 of the projection chamber 3 by a bolt passing through the second countersunk bolt hole 302.

[0055] The connecting support column 2 is connected to the connecting base 1 and the projection chamber 3 respectively by countersunk bolts, which improves the connection strength and facilitates maintenance and disassembly.

[0056] In some embodiments, the connecting base 1 forms an angle of 50° with the vertical direction.

[0057] In some embodiments, the connecting support 2 includes a strip frame and a polygonal frame fixedly connected to the strip frame. The frame structure has the advantages of simple structure and strong practicality.

[0058] In some embodiments, the projection compartment 3 is generally recessed, which facilitates the loading of fixed-wing UAVs and the deployment of fixed-wing UAVs.

[0059] In some embodiments, the connecting base 1 is plate-shaped to facilitate connection with a rotorcraft.

[0060] Figure 5 A schematic diagram of the projection base plate structure of a rotary-wing airborne UAV airdrop launch device according to an embodiment of the present invention is shown. Figure 5 As shown, in some embodiments, the projection base plate 4 is generally plate-shaped, which is beneficial for launching fixed-wing UAVs.

[0061] Both the projection base plate 4 and the inner wall of the projection chamber 3 are provided with hinge bolt holes 401, and the two are hinged together by hinges.

[0062] In some embodiments, the connecting mechanism 301 includes a plurality of protrusions disposed on the top of the projection chamber 3; each protrusion is provided with a second countersunk bolt hole 302.

[0063] In some embodiments, the rotary-wing airborne UAV airdrop launcher further includes: a control unit;

[0064] The control unit is electrically connected to the digital servo motor 501 of the electronic drive mechanism 5 and is used to control the digital servo motor 501.

[0065] The working principle of this novel rotary-wing airborne UAV airdrop launch device is as follows:

[0066] First, the connecting base 1, connecting support column 2, projection cabin 3, and projection base plate 4 are fixedly connected. Then, the servo arm 503 is controlled to rotate, thereby opening the projection base plate 4. Next, the fixed-wing UAV is loaded into the projection cabin 3, and the servo arm 503 is controlled to rotate, thereby closing the projection base plate 4. The angle design of the connecting support column 2 can counteract the pitch angle generated during the flight of the rotorcraft, so that the entire device flies horizontally and stably. When the projection conditions are met, the servo arm 503 is controlled to rotate, thereby opening the projection base plate 4 and realizing the successful projection of the fixed-wing UAV.

[0067] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A rotary-wing airborne unmanned aerial vehicle (UAV) airdrop launch device, characterized in that, include: Connecting base (1), connecting support column (2), projection chamber (3), projection base plate (4) and electronic drive mechanism (5); The bottom of the connecting base (1) is provided with a connecting groove (101). The top of the projection cabin (3) is provided with a connecting mechanism (301), and a digital servo motor assembly slot (303) is provided on the outer surface of one side wall of the projection cabin (3). The projection base plate (4) is hinged to the bottom of the other side wall of the projection chamber (3); One end of the connecting support column (2) is installed in the connecting groove (101), and the other end is connected to the connecting mechanism (301) of the projection chamber (3); The electronic drive mechanism (5) includes a digital servo motor (501), a servo motor shaft (502), a servo motor arm (503), and a servo motor mounting hole (504). The digital servo motor (501) has servo motor mounting holes (504) on both sides. The digital servo (501) is installed in the digital servo mounting slot (303) of the projection cabin (3) through the servo mounting hole (504); The digital servo motor (501) is connected to the servo motor arm (503) via the servo motor shaft (502); the electronic drive mechanism (5) is used to control the opening and closing state of the projection base plate (4).

2. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, The connecting groove (101) has several first countersunk bolt holes (102) on its side wall.

3. The rotary-wing airborne UAV airdrop launch device according to claim 2, characterized in that, The connecting support (2) has a plurality of first countersunk bolt holes (102) at one end and a plurality of second countersunk bolt holes (302) at the other end. One end of the connecting support column (2) is connected to the connecting groove (101) of the connecting base (1) by a bolt passing through the first countersunk bolt hole (102); the other end is connected to the connecting mechanism (301) of the projection chamber (3) by a bolt passing through the second countersunk bolt hole (302).

4. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, Several first countersunk bolt holes (102) are also provided at the edge of the connecting base (1).

5. The rotary-wing airborne UAV airdrop launch device according to claim 1 or 4, characterized in that, The connecting base (1) has an angle of 50° with the vertical direction.

6. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, The connecting support (2) includes a strip frame and a polygonal frame fixedly connected to the strip frame.

7. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, The projection chamber (3) is generally grooved.

8. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, The connecting base (1) is plate-shaped.

9. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, The projection base plate (4) is plate-shaped as a whole.

10. The rotary-wing airborne UAV airdrop launch device according to claim 1, characterized in that, The connecting mechanism (301) includes a plurality of protrusions provided on the top of the projection chamber (3); each protrusion is provided with a second countersunk bolt hole (302).