A device for vertical takeoff of aircraft-type unmanned aerial vehicles

Abstract

The invention relates to unmanned aerial vehicles (UAVs), specifically to systems for taking off from fixed-wing aircraft. The system for vertical takeoff of fixed-wing aircraft comprises a launch platform containing at least two fixed-wing aircraft, a platform with a vertically mounted telescopic arm. A coupling is secured to the arm, capable of rotational and translational movement, and is connected to connecting links equipped with quick-release grips that interact with mating fastening units located on the UAV, capable of engaging and disengaging upon reaching a predetermined rotational speed. A locking device, implemented as a spring-loaded stop, is also secured to the upper end of the telescopic arm.The takeoff device enables the simultaneous launch of large numbers of fixed-wing UAVs from unprepared, limited-size sites, significantly reducing the time required to prepare and launch UAVs and improving safety at all stages of the launch. 3 s.p. f-ly, 5 ill.

Description

[0001] Technical field

[0002] The utility model relates to unmanned aerial vehicles (UAVs), namely to aircraft-type UAV takeoff systems.

[0003] Aircraft-type UAVs are widely used for both military (reconnaissance of enemy locations, delivery of ammunition to engage targets) and civilian (particularly as a means of transporting people and cargo) purposes. In both cases, UAVs are often used in areas without designated runways, such as in wooded areas or urban areas. Therefore, the task of quickly and safely taking off UAVs is a pressing issue.

[0004] State of the art

[0005] A US patent, "Rotating Launcher for a Remotely Controlled Aircraft," discloses a method and apparatus for launching a remotely controlled aircraft (Patent No. US 3989206 A, https: / / patentscope.wipo.int / search / ). The aircraft rotates around a fixed pivot point until a predetermined speed is reached, after which it is released from the launcher. The aircraft is attached to one end of a rotating lever, with the imbalance on the lever compensated for by a counterweight attached to the opposite end. The counterweight is removed from the lever simultaneously with the aircraft to prevent damage to the aircraft's structure caused by rotation in an unbalanced state. The lever is mounted vertically so that it rotates in a plane inclined at an angle to the local gravitational field of the spaceport.The support structure for the manipulator can be made stationary or can be attached to a mobile vehicle for ground transportation.

[0006] The disadvantage of this technical solution is the need to use a counterweight, which significantly complicates the design and can also lead to the creation of an emergency situation when the counterweight is separated due to the uncertainty of its movement after separation from the pivot arm.

[0007] The “Unmanned Aircraft Complex” (RF Patent No. 2403182, https: / / new.fips.ru / registers-doc-view / fips.servlet) is known, which discloses a method for launching a UAV and a launch device for its implementation.

[0008] The unmanned aerial system (UAS) without an airfield base comprises an unmanned aerial vehicle (UAV) and a launch ground station containing a mobile platform and a power plant and flight control unit. The UAV is designed as a dual-wing console with propulsion units mounted on rotating consoles. The consoles are capable of rotating 180° relative to the longitudinal axis of the wing around the payload body. A transmission shaft connected to a gearbox and a launch device mounted vertically on the launch ground station platform are supported by three supports.

[0009] The launch device contains means for transmitting rotation from the transmission shaft to the UAV, as well as means for locking and unlocking it at a predetermined transmission shaft speed. The launch device's supports are telescopic and independently adjustable in length by the control unit for pre-flight correction of the UAV's spatial orientation.

[0010] The objective of the known technical solution is to increase the efficiency of the unmanned aerial vehicle, expand the controlled area, its range and the duration of its operation by using an external energy source (installed on a mobile platform) to accumulate kinetic energy and ensure the “jump takeoff” of the unmanned aerial vehicle to a given altitude and its transition to airplane mode.

[0011] A disadvantage of this analogue is the need to rotate the wing panels and perform maneuvers when transitioning from takeoff mode to horizontal flight, which can lead to instability of the aircraft when the thrust vector direction changes. Furthermore, this technical solution does not allow for the launch of large UAVs.

[0012] The closest thing to a utility model is the "Aviation System" known from patent No. RU 2049701 C1 (https: / / www1.fips.ru / registers-doc-view / fips_servlet). The purpose of the invention is to simplify the design while ensuring vertical takeoff. The system consists of several aircraft with high-aspect-ratio wing panels and a connecting means, designed as a fastening device that connects the ends of the wing panels. The aircraft are oriented for circular motion in one direction. The fastening means holds the moving aircraft when the engines are turned on, and after the system reaches the required altitude, it releases, releasing the aircraft for further flight.

[0013] The mounting device contains a means for descending to the ground after undocking, such as a parachute.

[0014] A drawback of the chosen prototype is the need for a parachute-like means of lowering the mounting device to the ground, which is associated with the uncertainty of its landing location in strong winds, wooded areas, or densely populated areas. Furthermore, the choice of aircraft with high-aspect-ratio wings necessitates the use of a large takeoff area for such a system. When using small UAVs with low-aspect-ratio wings, takeoff can take a considerable amount of time due to the small radius of the connected aircraft's rotational trajectory and will require a significant increase in thrust from their cruise engines.

[0015] The technical problem that the utility model is aimed at solving is the elimination of the shortcomings inherent in known technical solutions, in particular the ability to launch UAVs from unprepared small sites, as well as the use of a device for the rapid launch of UAVs in combat and emergency situations, for example, during fires, where the speed of decision-making is crucial.

[0016] Disclosure of the essence of the utility model

[0017] The technical result that the launch device is aimed at achieving is to increase safety at all stages of launch.

[0018] This technical result is achieved in that the device for performing a vertical takeoff of an aircraft-type UAV contains a launch device including a connecting means for two UAVs, made with the possibility of interaction with the consoles of the wings of the aircraft-type UAV, equipped with a means for descending to the ground, a platform with a vertically mounted telescopic rod on it, on which a coupling is secured with the possibility of rotational and translational movement, connected to connecting links equipped with quick-release grips interacting with the mating attachment units of the UAV with the possibility of engagement and disengagement upon reaching a predetermined rotation speed, as well as a locking device secured to the upper end of the telescopic rod, made in the form of a spring-loaded stop.

[0019] In a preferred embodiment of the proposed device, the connecting links are made telescopic.

[0020] In addition, the connecting links are made in the form of telescopic rods of varying length depending on the rotation speed of the starting system.

[0021] Brief description of drawings

[0022] The essence of the proposed device is explained by the following description and the attached graphic materials, which show:

[0023] Fig. 1 - general view of the launch pad, diagram of the acting forces and in the acceleration mode of two UAVs;

[0024] Fig. 2 - top view of the vertical takeoff system of two UAVs in acceleration mode;

[0025] Fig. 3 - diagram of the acceleration of two UAVs and their takeoff in a spiral until the moment of separation from the connecting link;

[0026] Fig. 4 - top view of the vertical takeoff system of two UAVs at the moment of disengagement in takeoff mode;

[0027] in Fig. 5 - calculated dependence of the influence of the length of the connecting link on the time of separation of the UAV from the connecting link;

[0028] where 1 - Platform;

[0029] 2 - Barbell;

[0030] 3 - Locking device;

[0031] 4 - Coupling;

[0032] 5 - Connecting link;

[0033] 6 - UAV 1;

[0034] 7 - UAV 2;

[0035] 8 - Rudders;

[0036] 9 - Elevators.

[0037] The device (Fig. 1) includes a platform 1, a vertical telescopic rod 2 with a fixed locking device 3 and a coupling 4 secured thereto, connecting links 5 configured to interact with the wing consoles of at least two aircraft-type UAVs 6 and 7, equipped with engines. The UAVs are connected by means of connecting links 5 equipped with quick-release grips interacting with mating fastening units located on the UAV for connection and uncoupling. The UAVs are oriented for movement in a circle in one direction, i.e. the thrust vectors P1 and P2 of their engines are directed in opposite directions so that a torque of one direction is created during operation. UAVs docked in this manner must be close in mass. In addition, the UAVs have rudders 8 and elevators 9.The coupling 4 with the connecting links 5 is equipped with a means for lowering, made in the form of a self-braking device, for example, a wedge brake, a worm gear, a screw-nut pair, or a hydraulic or aerodynamic retarder.

[0038] Implementation of a utility model

[0039] Takeoff consists of the following stages:

[0040] Stage 1 - a circular takeoff run of two rigidly connected UAVs;

[0041] Stage 2 - spiral takeoff of two rigidly connected UAVs;

[0042] Stage 3 - UAV disengagement and further separate flight.

[0043] The system carries out the takeoff of the UAV as follows.

[0044] Stage 1

[0045] Circular Acceleration

[0046] After starting the engines, the unmanned aerial vehicles take off around the rotation axis to takeoff speed. At the first stage, we have a flat rotation of the system of three interconnected bodies: UAV1, UAV2, and connecting link 5 (Figs. 1, 2),

[0047] where - thrust force of UAV1 and UAV2 respectively;

[0048] - reaction force of the support of UAV1 and UAV2;

[0049] - the force of interaction between the UAV1 and the connecting link;

[0050] - the force of interaction between the UAV2 and the connecting link;

[0051] - the reaction force of the UAV1 support from the connecting link;

[0052] - the reaction force of the UAV2 support from the connecting link;

[0053] m - UAV mass.

[0054] In this case, elevators 9 are located in the plane of the wing, and rudders 7 and 8 are turned to the outside in relation to the center of rotation to reduce the aerodynamic force and prevent premature separation of the aircraft.

[0055] Stage 2

[0056] Spiral Takeoff

[0057] After reaching takeoff speed, the elevators, on command from the operator, are smoothly moved to the takeoff position (at an angle to the wing plane), and the UAV takes off in a spiral upward, continuing to move around their common axis of rotation (Fig. 3).

[0058] The telescopic rod extends upward until it reaches a safe height, i.e. a height at which the UAV cannot collide with surrounding objects, and rests against the locking device.

[0059] After the UAV has reached a safe altitude, a command is given from the ground to increase the flight speed and the aircraft, under the influence of centrifugal forces, disengage and fly apart in different directions (Fig. 4), and the means for connecting and disconnecting smoothly descends along the rod onto the platform.

[0060] To determine the takeoff time (ttakeoff=t2+tk), a calculation was carried out for different values ​​of the length of the connecting links for a UAV mass of m=130 kg.

[0061] The system of equations (1.1) for determining the coordinates of the UAV during acceleration on the ground has the form:

[0062]

[0063] where t ∈ [t0; t2], t2 is the time the UAV takes off from the ground.

[0064] Lifting force generation condition:

[0065]

[0066] or

[0067]

[0068] The law of change in the flight altitude of a UAV when moving in an ascending spiral has a linear dependence of the form:

[0069]

[0070] where t k - UAV disengagement time.

[0071] Calculation results showed that takeoff time depends significantly on the size of the connecting link (Fig. 5). The preferred range is 1-5 meters.

[0072] Using the proposed "jump takeoff" device to launch UAVs allows for launches from unprepared, limited-size sites, significantly reducing the time required to prepare and launch UAVs, and improving safety at all stages of the launch. The proposed system enables the simultaneous launch of multiple fixed-wing UAVs, including large ones.

Claims

1. A device for performing a vertical takeoff of unmanned aerial vehicles of an aircraft type, comprising a launch device including a connecting means for two UAVs, made with the possibility of interaction with the consoles of the UAV wings, equipped with a means for descending to the ground, a platform with a rod installed vertically on it, characterized in that the connecting means is made in the form of a coupling placed on a telescopic vertical rod with the possibility of rotational and translational movement, connected with connecting links made with the possibility of interaction with the UAV fastening units with the possibility of their engagement and disengagement, wherein a locking device made in the form of a spring-loaded stop is secured to the upper end of the telescopic rod.

2. The device according to paragraph 1, characterized in that the connecting links of the starting device are made telescopic.

3. The device according to paragraph 1, characterized in that the length of the connecting link is selected in the range of 1-5 meters.

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