Integrated design structure of unmanned aerial vehicle zero-length launching fulcrum and retractable landing gear and application thereof

Abstract

The application relates to the technical field of unmanned aerial vehicle launching, in particular to an integrated design structure of an unmanned aerial vehicle zero-length launching support point and a retractable take-off and landing device and application thereof, which comprises a launching support base, a front launching support assembly, a rear launching support assembly, a rocket booster assembly, a front launching support point structure and a rear launching support point structure; the front launching support assembly, the rear launching support assembly and the rocket booster assembly are arranged on the launching support base; the front launching support point structure is arranged at the bottom of the front fuselage of the unmanned aerial vehicle; and the rear launching support point structure is arranged at the supporting end of the retractable take-off and landing device of the fuselage below the wing of the unmanned aerial vehicle. The unmanned aerial vehicle launching support point structure and the retractable take-off and landing device are connected to form an integrated structure, the transverse interval of the launching support point can be effectively reduced, the structural size and weight of the ground launching support are reduced, the cost of the launching support is reduced, and the passability and transportability are greatly improved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) launch technology, specifically to an integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for UAVs, and its application. Background Technology

[0002] There are various ways to launch and recover drones. Common takeoff methods include rocket-assisted zero-length launch, wheeled landing gear takeoff, and catapult launch. Landing methods include recovery parachute + skid shock absorption device recovery, recovery parachute + airbag shock absorption recovery, and arresting recovery.

[0003] like Figure 9 As shown, UAVs that use rocket-assisted zero-length launch or catapult takeoff typically have 2 to 4 launch points arranged on the fuselage and wings, in conjunction with... Figure 10 The ground launch support shown enables zero-length launch or catapult takeoff. For Figure 9 The image shows a fixed-wing UAV with a rear-mounted propeller. To prevent the rotating propeller or landing gear from colliding with the launch support during takeoff as the UAV detaches from the launch support and flies forward, [further details are needed]. Figure 10 The lateral spacing and height between the launch fulcrum and the ground launch bracket shown in the diagram need to be designed to be relatively large, resulting in a large size and volume of the ground launch bracket. Therefore, how to reduce the lateral spacing between the UAV launch fulcrum to enable the ground launch bracket to meet the requirements of small size and lightweight design is an urgent problem to be solved.

[0004] Therefore, there is a need to provide an integrated design structure for a UAV with a zero-length launch pivot and a retractable take-off and landing device, and its application, to solve the above problems. Summary of the Invention

[0005] This invention provides an integrated design structure and application of a zero-length launch fulcrum and a retractable take-off and landing device for unmanned aerial vehicles (UAVs), in order to solve the problem that the lateral spacing and height of the existing launch fulcrum and ground launch support need to be designed to be relatively large, resulting in a large size of the ground launch support, that is, the ground launch support is difficult to meet the requirements of small size and lightweight design.

[0006] The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV, and its application, adopt the following technical solution, including: The launch base is equipped with a front launch support assembly, a rear launch support assembly, and a rocket booster assembly. The forward launch pivot structure is located at the bottom of the forward fuselage of the UAV; And the rear launch pivot structure, which is the support end of the retractable take-off and landing device of the fuselage located under the wing of the UAV; The front launch support assembly supports the front launch pivot structure at the bottom of the front fuselage; the rocket booster assembly provides boost for the UAV's takeoff; and the rear launch support assembly supports the rear launch pivot structure on the UAV's retractable takeoff and landing device.

[0007] Preferably, the front launch support structure of the front launch bracket assembly and the rear launch support structure of the rear launch bracket assembly constitute a three-point launch support.

[0008] Preferably, the three-point launch fulcrum has one front launch fulcrum structure and two rear launch fulcrum structures; The front launch support assembly includes a front launch support, one end of which is fixed to the launch base and the other end of which is supported on a front launch fulcrum structure set on a frame at the bottom of the front fuselage; the rear launch support assembly includes two rear launch supports symmetrically arranged on both sides of the fuselage, one end of which is fixed to the launch base and the other end of which is supported on a rear launch fulcrum structure on a retractable take-off and landing device.

[0009] Preferably, the three-point launch fulcrum consists of two front launch fulcrum structures and one rear launch fulcrum structure; The forward launch support assembly includes two forward launch supports symmetrically arranged on both sides of the forward fuselage, one end of which is fixed to the launch base and the other end of which is supported on a forward launch fulcrum structure set on a frame at the bottom of the forward fuselage; the rear launch support assembly includes a rear launch support, one end of which is fixed to the launch base and the other end of which is supported on a rear launch fulcrum structure on a retractable take-off and landing device.

[0010] Preferably, the retractable take-off and landing device adopts a chute-type UAV skid retractable mechanism.

[0011] Preferably, the chute-type UAV skid deployment and retrieval mechanism includes: The skid bar has one end hinged to the bottom of the fuselage between the front launch support assembly and the rear launch support assembly, and the other end is provided with a rear launch fulcrum structure, which is slidably connected to the support end of the launch support assembly in the horizontal direction. The skid arm is tilted, with one end connected to the skid bar and the other end used to support the bottom of the fuselage under the wings of the drone. And a shock absorber, one end of which is hinged to the skid arm and the other end of which is hinged to the side of the fuselage.

[0012] Preferably, the support end of the front launch bracket is provided with a pressure tongue, which is used to lock or release the front launch fulcrum structure.

[0013] Preferably, a pressure block is horizontally provided at the support end of the rear launch bracket, and the pressure block is used to limit the vertical movement of the rear bracket point structure.

[0014] The application of an integrated design structure for a zero-length launch fulcrum and a retractable take-off and landing device for unmanned aerial vehicles (UAVs) includes: using the integrated design structure for a zero-length launch fulcrum and a retractable take-off and landing device disclosed in this invention to launch and take off a UAV with a rear-mounted engine and a high-wing, twin-tail configuration, or to launch and take off a UAV with a rear-mounted engine and a rocket-assisted zero-length launch and take-off configuration.

[0015] The beneficial effects of this invention are: 1. By integrating the UAV launch support structure and the retractable takeoff and landing device into a single unit, the support and fixation requirements for the UAV during launch and takeoff can be met, as well as the landing buffer and overload requirements during UAV recovery. The integrated structure can effectively reduce the lateral spacing of the launch support points, thereby reducing the structural size and weight of the ground launch support, reducing the cost of the launch support, and greatly improving maneuverability and transportability.

[0016] 2. The rear launch pivot structure is directly connected to the retractable takeoff and landing device to form an integrated structure, which simplifies the structure. Its positioning accuracy is guaranteed by the positioning accuracy of the takeoff and landing device and the CNC machining accuracy of the metal parts. This avoids the problems of existing technology that places the launch pivot structure on the fuselage or wing, which requires fixing it to the main force transmission structure such as the fuselage longitudinal beam or wing main beam. When the fuselage is closed, tooling is needed to position the launch pivot, which makes the aircraft structure design and assembly more complicated and requires additional positioning tooling.

[0017] 3. Existing technologies place the launch fulcrum structure on the fuselage or wing, which protrudes from the aircraft's surface shape and increases aerodynamic drag. This invention directly connects the rear launch fulcrum structure to the retractable takeoff and landing device to form an integrated structure. After takeoff, the rear launch fulcrum structure folds up and retracts along with the retractable takeoff and landing device, fitting snugly against the sides of the UAV's fuselage, thereby reducing aerodynamic drag during flight and improving the UAV's flight performance. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a front view of an integrated design structure of a zero-length launch fulcrum and a retractable take-off and landing device for a UAV according to the present invention. Figure 2 for Figure 1 A magnified view of a portion of point I in the image; Figure 3 for Figure 1 A magnified view of section II in the image; Figure 4 for Figure 1 The left view; Figure 5 for Figure 4 A magnified view of a portion of point I in the image; Figure 6 for Figure 4 A magnified view of section II in the image; Figure 7 This is a schematic diagram of the rear launch pivot structure retracting onto the UAV with the retractable take-off and landing device in this embodiment. Figure 8 for Figure 7 The left view; Figure 9 This is a schematic diagram of the launch fulcrum of a drone in the prior art. Figure 10 This is a schematic diagram of a drone take-off and landing device in the background art.

[0020] In the diagram: 1. Fuselage; 2. Frame; 3. Center of gravity of the UAV; 4. Wing; 5. Propeller; 6. Front launch pivot structure; 7. Front launch support; 8. Retractable take-off and landing device; 9. Rear launch pivot structure; 10. Rear launch support; 11. Rocket booster; 12. Launch support base; 13. Rocket booster support; 14. Ground; 15. Propeller rotation plane; 16. Cotter pin; 17. Bolt; 18. Nut; 61. Load-bearing angle box; 62. Shaft pin; 71. Pressure tongue; 81. Skid bar; 82. Skid arm; 83. Shock absorber; 101. Pressure block. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] An embodiment of the integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to the present invention, such as... Figure 1 and Figure 4As shown, it includes: a launch support base 12, a front launch support assembly, a rear launch support assembly, a rocket booster assembly, a front launch fulcrum structure 6, and a rear launch fulcrum structure 9. The launch support base 12 is set on the ground 14, and the front launch support assembly, the rear launch support assembly, and the rocket booster assembly are set on the launch support base 12. The front launch fulcrum structure 6 is set at the bottom of the front fuselage of the UAV. The rear launch fulcrum structure 9 is set at the support end of the retractable take-off and landing device 8 of the fuselage below the wing 4 of the UAV. The support end of the front launch support assembly is used to support the front launch fulcrum structure 6 at the bottom of the front fuselage. The rocket booster assembly is used for boosted take-off of the UAV. The rear launch support assembly is used to support the rear launch fulcrum structure 9 on the retractable take-off and landing device 8 of the UAV.

[0023] Specifically, the front launch fulcrum structure 6 of the front launch support assembly and the rear launch fulcrum structure 9 of the rear launch support assembly constitute a three-point launch fulcrum. A first embodiment of the three-point launch fulcrum is as follows... Figure 1 and Figure 4 As shown, in this embodiment, the three-point launch support consists of a front launch support structure 6 and two rear launch support structures 9. The front launch support assembly includes a front launch support 7, one end of which is fixed to the launch support base 12, and the other end of which is supported on the front launch support structure 6 set on a frame 2 at the bottom of the front fuselage. The rear launch support assembly includes two rear launch supports 10 symmetrically arranged on both sides of the fuselage. One end of the rear launch support 10 is fixed to the launch support base 12, and the other end of which is supported on the rear launch support structure 9 on the retractable take-off and landing device 8. The second embodiment of the three-point launch support is that the three-point launch support consists of two front launch support structures 6 and one rear launch support structure 9. The front launch support assembly includes two front launch supports 7 symmetrically arranged on both sides of the front fuselage, one end of which is fixed to the launch support base 12, and the other end of which is supported on the front launch support structure 6 arranged on a frame 2 at the bottom of the front fuselage. The rear launch support assembly includes a rear launch support 10, one end of which is fixed to the launch support base 12, and the other end of which is supported on the rear launch support structure 9 on the retractable take-off and landing device 8.

[0024] It should be noted that in this embodiment, the front launch fulcrum structure 6 is located in front of the center of gravity 3 of the UAV, and the rear launch fulcrum structure 9 is located behind the center of gravity 3 of the UAV. The launch fulcrum structure 6 and the rear launch fulcrum structure 9 together provide balance support for the UAV. At this time, the rocket booster 11 and the rocket booster bracket 13 do not bear the weight of the UAV.

[0025] Specifically, the retractable take-off and landing device 8 adopts a chute-type UAV skid retractable mechanism; in this embodiment, the retractable take-off and landing device 8 adopts the patent number CN 106394882. Name B is a chute-type UAV skid deployment and take-off mechanism. Specifically, the chute-type UAV skid deployment and take-off mechanism includes: a skid rod 81, an inclined skid support arm 82, and a shock absorber 83. One end of the skid rod 81 is hinged to the bottom of the fuselage between the front launch support assembly and the rear launch support assembly. The other end of the skid rod 81 is provided with a rear launch fulcrum structure 9, which slides horizontally to the support end of the launch support assembly. One end of the skid support arm 82 is connected to the skid rod 81, and the other end of the skid support arm 82 supports the bottom of the fuselage below the UAV's wing 4. One end of the shock absorber 83 is hinged to the skid support arm 82, and the other end of the skid support arm 82 is hinged to the side of the fuselage. The retractable take-off and landing device 8 can also adopt a wheeled landing gear, which consists of a front landing gear and a main landing gear. The main landing gear adopts a fixed or retractable inclined support arm form, and the rear launch fulcrum structure 9 can be fixed to the outer side of the main landing gear inclined support arm.

[0026] like Figure 2 As shown, the support end of the front launch bracket 7 is provided with a pressure tongue 71, which is used to lock or release the front launch fulcrum structure 6, such as... Figure 5 As shown, the front launch support structure 6 includes a load-bearing corner box 61 and a pivot pin 62, as... Figure 5 As shown, the load-bearing angle box 61 is an I-shaped structure with two lugs. The load-bearing angle box 61 is fixed to the frame 2 of the UAV by bolts 17 and nuts 18. The shaft pin 62 passes through the hole on the lug of the load-bearing angle box 61 and is fixed at one end by a cotter pin 16. Alternatively, an external thread can be designed at the end of the shaft pin 62, and the shaft pin 62 can be fixed to the load-bearing angle box 61 by a nut. The shaft pin 62 can be locked by the pressure tongue 71 of the front launch bracket 7. Specifically, the front launch bracket 7 and its pressure tongue 71 are existing technologies, and the structure in patent CN201907656U can be adopted. This embodiment will not be described in detail. Specifically, when the UAV is launched, the front launch bracket 7 can tilt forward around the lower pivot, and the pressure tongue 71 automatically lifts up, releasing the pin 61 of the front launch fulcrum structure 6, thereby releasing the front launch fulcrum structure 6. The front launch fulcrum structure 6 in this embodiment can also adopt an inverted "T" shaped structure. The front launch bracket 7 adopts a sliding groove design to achieve a matching connection between the "T" shaped structure and the sliding groove.

[0027] Specifically, a pressure block 101 is horizontally provided at the support end of the rear launch bracket 10. The pressure block 101 is used for vertical limiting of the rear launch fulcrum structure 9. In this embodiment, as shown... Figure 3 and 6As shown, the rear launch fulcrum structure 9 is fixed to the skid arm 82 of the retractable take-off and landing device 8 by bolts 17 and nuts 18. The extended part has a cylindrical cross section, or a square cross section. The bottom has a U-shaped or planar shape. The rear launch fulcrum structure 9 slides in contact with the support end of the rear launch bracket 10 and is vertically limited by the pressure block 101.

[0028] Specifically, the rocket booster assembly includes: a rocket booster bracket 13 and a rocket booster 11 mounted on the rocket booster bracket 13, with the output end of the rocket booster 11 acting on the tail of the UAV.

[0029] The application of an integrated design structure for a zero-length launch fulcrum and a retractable take-off and landing device for unmanned aerial vehicles (UAVs) includes: using the integrated design structure for a zero-length launch fulcrum and a retractable take-off and landing device disclosed in this invention to launch and take off a UAV with a rear-mounted engine and a high-wing, twin-tail configuration, or to launch and take off a UAV with a rear-mounted engine and a rocket-assisted zero-length launch and take-off configuration.

[0030] Specific working principle like Figure 1 As shown, the retractable take-off and landing device 8 is in the lowered state; the UAV is placed on the front launch support 7 and rear launch support 10 of the integrated design structure of this invention. At this time, the pin 62 of the front launch fulcrum structure 6 of the UAV is locked by the pressure tongue 71 of the front launch support 7, and the rear launch fulcrum structure 9 is vertically limited and locked by the pressure block 101 of the rear launch support 10 to prevent the UAV from moving forward under the thrust of the propeller 5 after the engine is started and causing danger; the rocket booster 11 is installed and the ignition cable is laid; after the rocket booster 11 is working, the UAV moves forward, the front launch support 7 collapses, the pressure tongue 71 automatically lifts to release the front launch fulcrum structure 6, and at the same time, the rear launch fulcrum structure 9 slides on the rear launch support 10 until the rear launch fulcrum structure 9 slides past the length of the pressure block 101, and then releases from the limitation of the pressure block 101. Theoretically, the front launch fulcrum structure 6 and the rear launch fulcrum structure 9 are released simultaneously, and the UAV launches and takes off; after reaching the predetermined flight altitude, as Figure 7 and Figure 8 As shown, the rear launch fulcrum structure 9 retracts with the retractable take-off and landing device 8 and attaches to both sides of the fuselage; before the UAV is recovered and touches the ground, the rear launch fulcrum 9 is lowered with the retractable take-off and landing device 8 to achieve grounding buffering, shock absorption and energy absorption of the UAV.

[0031] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An integrated design structure for a zero-length launch pivot and a retractable take-off and landing device for unmanned aerial vehicles (UAVs), characterized in that, include: The launch support base (12) is provided with a front launch support assembly, a rear launch support assembly and a rocket booster assembly. The front launch pivot structure (6) is located at the bottom of the front fuselage of the UAV; And the rear launch pivot structure (9), which is located at the support end of the retractable take-off and landing device (8) of the fuselage below the wing (4) of the UAV; Among them, the support end of the front launch bracket assembly is used to support the front launch fulcrum structure (6) at the bottom of the front fuselage; the rocket booster assembly is used for the boosted take-off of the UAV; and the rear launch bracket assembly is used to support the rear launch fulcrum structure (9) on the retractable take-off and landing device (8) of the UAV.

2. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 1, characterized in that, The front launch support structure (6) of the front launch bracket assembly and the rear launch support structure (9) of the rear launch bracket assembly constitute a three-point launch support.

3. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 2, characterized in that, The three-point launch fulcrum consists of a front launch fulcrum structure (6) and two rear launch fulcrum structures (9). The front launch support assembly includes a front launch support (7), one end of which is fixed on the launch support base (12), and the other end of which is supported on the front launch fulcrum structure (6) set on a frame (2) at the bottom of the front fuselage; the rear launch support assembly includes two rear launch supports (10) symmetrically arranged on both sides of the fuselage, one end of which is fixed on the launch support base (12), and the other end of which is supported on the rear launch fulcrum structure (9) on the retractable take-off and landing device (8).

4. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 2, characterized in that, The three-point launch fulcrum consists of two front launch fulcrum structures (6) and one rear launch fulcrum structure (9). The front launch support assembly includes two front launch supports (7) symmetrically arranged on both sides of the front fuselage, one end of which is fixed on the launch support base (12) and the other end of which is supported on the front launch fulcrum structure (6) set on a frame (2) at the bottom of the front fuselage; the rear launch support assembly includes a rear launch support (10), one end of which is fixed on the launch support base (12) and the other end of which is supported on the rear launch fulcrum structure (9) on the retractable take-off and landing device (8).

5. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 4, characterized in that, The take-off and landing device (8) adopts a chute-type UAV skid take-off and landing mechanism.

6. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 5, characterized in that, The chute-type drone skid launch and recovery mechanism includes: A skid bar (81) has one end hinged to the bottom of the fuselage between the front launch support assembly and the rear launch support assembly, and the other end is provided with a rear launch fulcrum structure (9). The rear launch fulcrum structure (9) is slidably connected to the support end of the launch support assembly in the horizontal direction. The skid arm (82) is tilted, with one end connected to the skid bar (81) and the other end used to support the bottom of the fuselage below the wing (4) of the UAV. And a shock absorber (83), one end of which is hinged to the skid arm (82) and the other end of which is hinged to the side of the fuselage.

7. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 4, characterized in that, The front launch bracket (7) is provided with a pressure tongue (71) at its support end. The pressure tongue (71) is used to lock or release the front launch fulcrum structure (6).

8. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 4, characterized in that, A pressure block (101) is horizontally provided at the support end of the rear launch bracket (10), and the pressure block (101) is used for the vertical limitation of the rear launch support structure (9).

9. The integrated design structure of a zero-length launch pivot and a retractable take-off and landing device for a UAV according to claim 4, characterized in that, The rocket booster assembly includes a rocket booster bracket (13) and a rocket booster (11) mounted on the rocket booster bracket (13), the output of which acts on the tail of the UAV.

10. The application of an integrated design structure for a zero-length launch pivot and a retractable take-off and landing device for unmanned aerial vehicles (UAVs), characterized in that, include: The launch and takeoff of a UAV with a rear-mounted engine and a high-wing, twin-tail configuration is carried out using the integrated design structure of the zero-length launch fulcrum and retractable takeoff and landing device as described in any one of claims 1-9, or the launch and takeoff of a UAV with a rear-mounted engine and a rocket-assisted zero-length launch and takeoff configuration.

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