Vertical take-off and landing freight flight device based on composite lift system

Abstract

The invention discloses a vertical take-off and landing freight flight device based on a composite lift system. The vertical take-off and landing freight flight device comprises a cargo hold, a connecting rod and a multi-rotor aircraft, the cargo hold comprises a hold body, an upper single sweepback wing and an empennage; wherein the sweepback wing and the empennage play a supporting role when on the ground, one end of the connecting rod is coaxially and fixedly connected with the top end of the cargo hold, and the other end of the connecting rod is connected with the center of the bottom end of the multi-rotor aircraft through the universal hinge. During forward flight, the rotor wings can distribute more power into forward thrust, so that the aim of increasing the voyage or increasing the speed is fulfilled.

Description

Technical Field

[0001] The present invention belongs to the field of aviation flight, and particularly relates to a vertical take-off and landing cargo flight device based on a composite lift system. Background Art

[0002] Multi-rotor aircraft have become an important carrier for urban low-altitude transportation due to their vertical take-off and landing capabilities and flexible maneuvering characteristics. However, existing low-altitude transportation technologies have defects: (1) In the hanging transportation mode, the cargo hold completely serves as a passive load, and its aerodynamic shape has not been optimized, resulting in a reduction in the overall aerodynamic efficiency of the system; (2) The rotor system of a conventional multi-rotor aircraft needs to bear both the lift and propulsion forces of the whole machine, with low energy utilization efficiency, and its economy is difficult to meet the requirements of commercial transportation; (3) The mechanical transmission system of the tilt-rotor configuration is complex, and its reliability is difficult to guarantee. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a vertical take-off and landing cargo flight device based on a composite lift system for the defects involved in the background art.

[0004] The present invention adopts the following technical solutions to solve the above technical problems: A vertical take-off and landing cargo flight device based on a composite lift system, comprising a cargo hold, a connecting rod, and a multi-rotor aircraft; The cargo hold includes a cabin body, a fixed wing, and a tail wing; The cabin body includes a head cabin, a middle cabin, and a tail cabin connected in sequence. Among them, both the head cabin and the tail cabin are hollow cones with one end open, and the middle cabin is a hollow cylinder with both ends open; one end of the middle cabin is coaxially and hermetically fixed to the open end of the head cabin, and the other end is coaxially and hermetically fixed to the open end of the tail cabin, and a hatch that can be opened or closed is provided on the middle cabin; The fixed wing is arranged on the cabin body in a swept-back and high-wing layout, which can enhance the stability in the yaw and roll directions; the tail wing is arranged on the tail cabin to enhance the course stability, and the tail wing can cooperate with the fixed wing to support the cabin body to be vertical on the ground; One end of the connecting rod is coaxially fixed to the top end of the head cabin, and the other end is connected to the center of the bottom end of the multi-rotor aircraft through a universal hinge.

[0005] Compared with the prior art, the present invention adopting the above technical solutions has the following technical effects: 1. Improved power efficiency: Compared with the process of an ordinary multi-rotor unmanned aerial vehicle lifting goods, the present invention can distribute more rotor thrust to the forward flight power direction, resulting in a faster flight speed and a longer flight range.

[0006] 2. Payload Integrated Innovation: The modular cabin structure combines both the aerodynamic shape and the cargo-carrying function, reducing aerodynamic drag compared to traditional lifting methods.

[0007] 3. Enhanced Operational Safety: The universal hinge allows the cargo hold to self-trim, avoiding the risk of load instability caused by sudden changes in flight attitude. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 Schematic diagram of the structure of the present invention.

[0009] In the figure, 1 - multi-rotor, 2 - cabin, 3 - fixed wing, 4 - tail wing, 5 - connecting rod, 6 - universal hinge. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0010] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings: The present invention can be implemented in many different forms and should not be considered limited to the embodiments described herein. On the contrary, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the present invention to those skilled in the art. In the drawings, components are enlarged for clarity.

[0011] It should be understood that although the terms first, second, third, etc. may be used herein to describe various elements, components, and / or parts, these elements, components, and / or parts are not limited by these terms. These terms are only used to distinguish one element, component, and / or part from another. Thus, the first element, component, and / or part discussed below may become the second element, component, or part without departing from the teachings of the present invention.

[0012] As Figure 1 shown, the present invention discloses a vertical takeoff and landing cargo flight device based on a composite lift system, including a cargo hold, a connecting rod, and a multi-rotor aircraft; The cargo hold includes a cabin, a fixed wing, and a tail wing; The cabin includes a head cabin, a middle cabin, and a tail cabin connected in sequence. Among them, both the head cabin and the tail cabin are hollow cones with one end open, and the middle cabin is a hollow cylinder with both ends open; one end of the middle cabin is coaxially and hermetically fixed to the open end of the head cabin, and the other end is coaxially and hermetically fixed to the open end of the tail cabin, and a hatch that can be opened or closed is provided on the middle cabin; The fixed wing is arranged on the cabin in a swept-back, high-wing layout, which can enhance the stability in the yaw and roll directions; the tail wing is arranged on the tail cabin to enhance the heading stability, and the tail wing can cooperate with the fixed wing to support the cabin to be vertical on the ground; One end of the connecting rod is coaxially fixed to the top of the head cabin, and the other end is connected to the center of the bottom of the multi-rotor aircraft through a universal hinge.

[0013] The multi-rotor aircraft includes a multi-rotor UAV that matches the power required by the cargo compartment and a gimbal fixing device.

[0014] No torque is transmitted between the connecting rod and the rotor aircraft. The cargo compartment maintains pitch moment balance under the combined action of the lift of the fixed wing and gravity. The multi-rotor aircraft maintains vertical force balance by the vertical component of the rotor lift.

[0015] The present invention ensures the vertical takeoff and landing advantages of the original multi-rotor UAV and enhances the high-speed flight performance. This device can be divided into three states: 1. Vertical takeoff and landing state: When the pull rod completely bears the mass of the cargo compartment and the cargo compartment is completely suspended below as a heavy object, at this time, the multi-rotor aircraft vertically outputs lift, and operations such as the vertical takeoff and landing of a conventional rotor aircraft can be achieved; 2. Transition state: When the device speed is lower than the cruise speed, the rotor provides forward flight power, the fixed wing begins to provide lift and the pitch moment of the cargo compartment, and the cargo compartment tilts under the influence of aerodynamic force and gravity. At this time, it is a transition state; 3. Horizontal cruise state: When the flight speed is relatively high, the cargo compartment is close to horizontal. The cargo compartment mainly relies on the fixed wing to provide lift. In addition to overcoming its own gravity, almost all the power of the rotor system is used to provide the forward flight power of the entire mechanism. This state is the forward flight state.

[0016] Those skilled in the art of this technology can understand that, unless otherwise defined, all terms used here (including technical terms and scientific terms) have the same meaning as the general understanding of those of ordinary skill in the art to which the present invention belongs. It should also be understood that terms defined in general dictionaries should be understood to have a meaning consistent with the meaning in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as here.

[0017] The specific embodiments described above have further elaborated on the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only the specific embodiments of the present invention and is not used to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A vertical take-off and landing cargo flying device based on a composite lift system, characterized in that: Includes cargo hold, linkage and multirotor; The cargo hold comprises a cabin, fixed wings and a tail wing; The cabin body comprises a head cabin, a middle cabin and a tail cabin connected in sequence, wherein the head cabin and the tail cabin are hollow cones with one end open, and the middle cabin is a hollow cylinder with two ends open; one end of the middle cabin is coaxially and tightly connected to the open end of the head cabin, and the other end is coaxially and tightly connected to the open end of the tail cabin, and the middle cabin is provided with a cabin door that can be opened or closed; The fixed wing is arranged on the cabin in a swept-back, upper-wing layout; the tail wing is arranged on the tail cabin to enhance the heading stability, and the tail wing can cooperate with the fixed wing to support the cabin vertically on the ground; One end of the connecting rod is coaxially fixedly connected to the top of the cargo hold, and the other end is connected to the bottom center of the multi-rotor aircraft through a universal joint.

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