Large release ratio soft wing unmanned aerial vehicle

Abstract

The application discloses a large-delivery-ratio soft-wing unmanned aerial vehicle, the lower part of the wing parachute is provided with at least two groups of front and rear connected sling belts, each of the sling belts is provided with a pre-delivery hanging point and a post-delivery hanging point, the sling cabin is provided with a pre-delivery connecting point and a post-delivery connecting point corresponding to each of the pre-delivery hanging point and the post-delivery hanging point, the pre-delivery connecting point corresponding to the pre-delivery hanging point is connected through a pre-delivery connecting rope, the post-delivery connecting point corresponding to the post-delivery hanging point is connected through a post-delivery connecting rope, the pre-delivery connecting rope is shorter than the post-delivery connecting rope, and the pre-delivery connecting rope can be disconnected from the pre-delivery connecting point after the task load is delivered. The application realizes the synchronous movement of the sling cabin hanging point and the sling cabin gravity center after the task load is delivered, reduces the flight angle of attack, and has the capacity of delivering large-size and large-weight loads.

Description

Technical Field

[0001] The present invention relates to a flexible-wing UAV, in particular to a flexible-wing UAV with a large launch ratio. Background Art

[0002] The power pod of a flexible-wing drone is suspended under its wings, and its climb and descent rely primarily on controlling engine speed. When the engine speed increases, the system tilts its head up to climb, and when the engine speed decreases, it tilts its head down to descend. When the material being dropped is too large relative to the system's weight, the pod's weight is significantly reduced after release. With the engine speed unchanged, the system will tilt its head up to climb, unable to maintain its original level flight speed, resulting in a significant decrease in flight performance. Therefore, current flexible-wing drones, both domestic and international, can only drop small amounts of materials such as leaflets and advertising materials, and are unable to drop large and heavy items, severely limiting their application. Summary of the Invention

[0003] The purpose of the present invention is to provide a flexible-wing UAV with a large delivery ratio, which realizes the synchronous movement of the pod hanging point and the pod center of gravity after the mission payload is delivered, and reduces the flight angle of attack, and has the ability to deliver large-size and heavy loads.

[0004] The technical solution adopted in the present invention is:

[0005] A flexible-wing UAV with a large release ratio is provided with at least two groups of front-to-back connected slings on the lower part of the paraglider, each group of slings is provided with a front-to-release hanging point and a rear-to-release hanging point, and a pod is provided with a front-to-release connection point and a rear-to-release connection point corresponding to each group of front-to-release hanging points and rear-to-release hanging points. The corresponding front-to-release hanging points are connected to the front-to-release connection points by a front-to-release connecting rope, and the corresponding rear-to-release hanging points are connected to the rear-to-release connecting point by a rear-to-release connecting rope, and the front-to-release connecting rope is shorter than the rear-to-release connecting rope; after the mission payload is released, the front-to-release connecting rope can be driven to disconnect from the front-to-release connection point.

[0006] Furthermore, each set of slings on the pod corresponds to a number of connection points arranged in a row, which are selected as the pre-delivery connection points and post-delivery connection points according to the center of gravity position of the pod before and after the delivery of different mission payloads.

[0007] Furthermore, the front and rear lifting points are sewn onto the slings, and are set according to the optimal flight angle of attack before and after the launch of different mission payloads.

[0008] Furthermore, the end of the pre-delivery connecting rope is sleeved on the pre-delivery connection point and limited by the pin, and the mission load is connected to the pin through the pull rope; after the mission load is delivered, the pin is pulled out by pulling the rope, and the pre-delivery connecting rope is disconnected from the pre-delivery connection point.

[0009] Furthermore, the bottom of the pod is expanded and opened, and the mission payload is installed on the mission payload mounting frame. The mission payload mounting frame is installed on the bottom of the pod through the mounting points on all sides. When the mission payload needs to be dropped, the flight control system releases the mounting point through the actuator, and the mission payload is dropped together with the mission payload mounting frame.

[0010] Furthermore, the pre-dropping hanging point is located behind the post-dropping hanging point, and the pre-dropping connecting point is located in front of the post-dropping connecting point.

[0011] Furthermore, two sets of front-to-back connected slings are respectively provided on both sides of the lower part of the parafoil.

[0012] The beneficial effects of the present invention are:

[0013] Before the mission payload is released, since the pre-release connecting rope is shorter than the post-release connecting rope, the pre-release connecting rope is straightened and the post-release connecting rope is relaxed, and the parafoil is connected to the pod through the sling, the pre-release hanging point, the pre-release connecting rope, and the pre-release connecting point in sequence. After the mission payload is released, since the mission payload drives the pre-release connecting rope to be disconnected from the pre-release connecting point, the pre-release connecting rope is relaxed and the post-release connecting rope is straightened, and the parafoil is connected to the pod through the sling, the post-release hanging point, the post-release connecting rope, and the post-release connecting point in sequence; that is, before and after the mission payload is released, the sling's sling point position and the pod's connection position are switched, among which the sling is connected front and back and the total length remains unchanged, so the change of the sling point position can reduce the parafoil. The flight angle of attack is adjusted so that the speed of the system does not drop significantly when the system weight is reduced, and the change in the connection position of the pod can keep the pod hanging point and the pod center of gravity in a straight line in the vertical direction, so that the parafoil maintains the best flight state; from the above, it can be seen that the present invention uses the mission load delivery to adjust the flight angle of attack and the position of the pod hanging point, and realizes the synchronous movement of the pod hanging point and the pod center of gravity after the mission load is delivered, and realizes the reduction of the flight angle of attack after the mission load is delivered. Under the condition that the system weight and center of gravity change significantly after delivery, the flight speed of the soft-wing UAV is not significantly reduced, and the flight performance is maintained, so that the soft-wing UAV has the ability to deliver large-size and heavy loads, which significantly expands the application range of the soft-wing UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a comparison diagram of the flexible-wing UAV with a large delivery ratio before and after the mission payload is delivered in an embodiment of the present invention.

[0015] Figure 2 1 is a side view of a parafoil according to an embodiment of the present invention.

[0016] Figure 3 Schematic diagram of the pod in an embodiment of the present invention (with the mission payload mounting frame installed).

[0017] Figure 4Schematic diagram of the pod in an embodiment of the present invention (after the mission payload mounting frame is deployed).

[0018] In the figure: 1-parafoil; 2-sling; 3-hanging point after launch; 4-hanging point before launch; 5-connecting rope after launch; 6-connecting rope before launch; 7-connecting point before launch; 8-connecting point after launch; 9-mission payload mounting frame; 10-mission payload; 11-pull rope; 12-pod; 13-latch; 14-connection point. DETAILED DESCRIPTION

[0019] The present invention will be further described below with reference to the accompanying drawings and examples.

[0020] like Figure 1 and Figure 2 As shown, a flexible-wing UAV with a large release ratio is provided with at least two groups of front-to-back connected slings 2 at the lower part of the parafoil 1, each group of slings 2 is provided with a front-to-release suspension point 4 and a rear-to-release suspension point 3, and a pod 12 is provided with a front-to-release connection point 7 and a rear-to-release connection point 8 corresponding to each group of front-to-release suspension points 4 and rear-to-release suspension points 3. The corresponding front-to-release suspension points 4 and the front-to-release connection points 7 are connected by a front-to-release connection rope 6, and the corresponding rear-to-release suspension points 3 and the rear-to-release connection points 8 are connected by a rear-to-release connection rope 5, and the front-to-release connection rope 6 is shorter than the rear-to-release connection rope 5; after the mission payload 10 is released, it can drive the front-to-release connection rope 6 to disconnect from the front-to-release connection point 7.

[0021] Before the mission payload 10 is dropped, since the pre-drop connection rope 6 is shorter than the post-drop connection rope 5, the pre-drop connection rope 6 is straightened and the post-drop connection rope 5 is relaxed, and the parafoil 1 is connected to the pod 12 in sequence through the sling 2, the pre-drop suspension point 4, the pre-drop connection rope 6, and the pre-drop connection point 7. After the mission payload 10 is dropped, since the mission payload 10 drives the pre-drop connection rope 6 to be disconnected from the pre-drop connection point 7, the pre-drop connection rope 6 is relaxed and the post-drop connection rope 5 is straightened, and the parafoil 1 is connected to the pod 12 in sequence through the sling 2, the post-drop suspension point 3, the post-drop connection rope 5, and the post-drop connection point 8; that is, before and after the mission payload 10 is dropped, the suspension point position of the sling 2 and the connection position of the pod 12 are switched, wherein the sling 2 is connected front and back and the total length remains unchanged, so the change of the suspension point position The flight angle of attack of the parafoil 1 can be reduced, so that when the system weight is reduced, the speed of the system in level flight is not greatly reduced. The change in the connection position of the pod 12 can keep the pod 12 hanging point and the center of gravity of the pod 12 in a straight line in the vertical direction, so that the parafoil 1 maintains the best flight state; from the above, it can be seen that the present invention uses the mission payload 10 to release and adjust the flight angle of attack and the position of the pod 12 hanging point, and realizes the synchronous movement of the pod 12 hanging point and the center of gravity of the pod 12 after the mission payload 10 is released, and realizes the reduction of the flight angle of attack after the mission payload 10 is released. Under the condition that the system weight and center of gravity change greatly after the release, the flight speed of the soft-wing UAV is not significantly reduced, and the flight performance is maintained, so that the soft-wing UAV has the ability to release large-size and heavy loads, which significantly expands the application range of the soft-wing UAV.

[0022] like Figure 1 As shown, in this embodiment, the end of the pre-delivery connection rope 6 is sleeved onto the pre-delivery connection point 7 and is limited by a latch 13. The mission payload 10 is connected to the latch 13 via a pull rope 11. After the mission payload 10 is released, the latch 13 is pulled out by pulling the rope 11, and the pre-delivery connection rope 6 is disconnected from the pre-delivery connection point 7. This transmission arrangement has a simple structure and reliable operation.

[0023] like Figure 1 As shown, in this embodiment, the pre-launch suspension point 4 is located behind the post-launch suspension point 3, and the pre-launch connection point 7 is located in front of the post-launch connection point 8. Generally, after launch, the center of gravity of the pod 12 will shift backward, and the parafoil 1 will tilt its head upward to climb. This arrangement can reduce the flight angle of attack of the parafoil 1 and move the suspension point of the pod 12 backward after launch.

[0024] like Figure 2 As shown, in this embodiment, the front hanging point 4 and the rear hanging point 3 are both sewn on the sling 2, and are set according to the optimal flight angle of attack before and after the launch of different mission payloads 10, which is easy to manufacture and adjust.

[0025] like Figure 3 and Figure 4As shown, in this embodiment, each set of slings 2 on the pod 12 corresponds to a number of connection points 14 arranged in a row, which are selected as the pre-delivery connection point 7 and the post-delivery connection point 8 according to the center of gravity position of the pod 12 before and after the delivery of different mission payloads 10. It is suitable for the individual and combined use of various mission payloads 10 and is easy to adjust.

[0026] like Figure 3 and Figure 4 As shown, in this embodiment, the bottom of pod 12 is expanded and open, and mission payload 10 is mounted on mission payload mounting frame 9. Mission payload mounting frame 9 is attached to the bottom of pod 12 via mounting points on all four sides. When mission payload 10 needs to be released, the flight control system releases the mounting points via actuators, and mission payload 10 is released along with mission payload mounting frame 9. Before release, mission payload mounting frame 9 improves the overall rigidity of pod 12. After release, the system load is significantly reduced, and pod 12 can still meet load-bearing requirements. The expanded and open bottom of pod 12 allows mission payload 10 to be released along with mission payload mounting frame 9, which neither hinders the descent of mission payload 10 nor allows for the loading of large mission payloads 10 that exceed the structural width.

[0027] In this embodiment, two sets of front-to-back connected slings 2 are provided on both sides of the lower portion of the parafoil 1, thereby ensuring stable flight while minimizing the rope structure.

[0028] It should be understood that those skilled in the art can make improvements or changes based on the above description, and all such improvements and changes should fall within the scope of protection of the appended claims of the present invention.

Claims

1. A flexible-wing UAV with a large launch ratio, characterized by: The lower part of the parafoil is provided with at least two sets of front-to-back connected slings, each set of slings is provided with a front-drop hanging point and a rear-drop hanging point, and the pod is provided with a front-drop connection point and a rear-drop connection point corresponding to each set of front-drop hanging points and rear-drop hanging points. The corresponding front-drop hanging points are connected to the front-drop connection points by a front-drop connecting rope, and the corresponding rear-drop hanging points are connected to the rear-drop connection points by a rear-drop connecting rope. The front-drop connecting rope is shorter than the rear-drop connecting rope. After the mission payload is dropped, the front-drop connecting rope can be driven to disconnect from the front-drop connection point. The end of the pre-delivery connection rope is sleeved on the pre-delivery connection point and is limited by a pin. The mission payload is connected to the pin by a pull rope. After the mission payload is delivered, the pin is pulled out by pulling the rope, and the pre-delivery connection rope is disconnected from the pre-delivery connection point. The bottom of the pod is expanded and open, and the mission payload is installed on the mission payload mounting frame. The mission payload mounting frame is installed on the bottom of the pod through the mounting points on all sides. When the mission payload needs to be dropped, the flight control system releases the mounting point through the actuator, and the mission payload is dropped together with the mission payload mounting frame.

2. The flexible-wing UAV with a large delivery ratio according to claim 1, characterized in that: Each set of straps on the pod corresponds to several connection points arranged in a row, which are selected as the pre-delivery connection points and post-delivery connection points according to the center of gravity position of the pod before and after the delivery of different mission payloads.

3. The flexible-wing UAV with a large delivery ratio according to claim 1, characterized in that: The front and rear lifting points are sewn onto the slings and are set according to the optimal flight angle of attack before and after the launch of different mission payloads.

4. The flexible-wing UAV with a large delivery ratio according to claim 1, characterized in that: The pre-drop hanging point is located behind the post-drop hanging point, and the pre-drop connection point is located in front of the post-drop connection point.

5. The flexible-wing UAV with a large delivery ratio according to claim 1, characterized in that: There are two sets of front and rear connected straps on both sides of the lower part of the parafoil.

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