Vertical take-off and landing multi-rotor unmanned aerial vehicle capable of rapidly switching modes on ground

Abstract

The utility model belongs to the field of unmanned aerial vehicles, and relates to a vertical take-off and landing multi-rotor unmanned aerial vehicle capable of rapidly switching modes on the ground. The unmanned aerial vehicle comprises a core cabin, a lift motor support, a skid undercarriage, a multi-rotor head fairing and a composite wing configuration assembly. The lift motor bracket is mounted at the upper part of the core cabin, and the skid undercarriage is mounted at the lower part of the core cabin, so that a basic structure of the multi-rotor-wing and composite-wing-wing aircraft is formed; when the multi-rotor aircraft head fairing is mounted at the head of the core cabin, a multi-rotor structure is formed; when the composite wing configuration assembly is mounted on the base structure, a composite wing configuration is formed.

Description

TECHNICAL FIELD

[0001] The utility model belongs to unmanned plane field relates to a ground fast switching mode's vertical take-off and landing multicopter unmanned plane. BACKGROUND

[0002] Electric vertical take-off and landing aircraft generally have three mainstream layouts:

[0003] Multi-rotor: 4-8 groups of propellers are evenly arranged on the periphery of the aircraft body, and the lift and control force are provided by controlling the rotation speed of each propeller;

[0004] Tilt-rotor: the fuselage, wings and tail of the conventional aircraft are provided, but the propeller capable of vertical take-off is increased, the propeller thrust axis can be rotated to change the direction of the thrust, and vertical take-off and horizontal flight are realized;

[0005] Compound wing: the fuselage, wings and tail of the conventional aircraft are provided, but the propeller capable of vertical take-off is increased, the propeller works when vertical take-off, stops when horizontal flight, and the special horizontal propeller provides thrust to realize vertical take-off and horizontal flight.

[0006] Among them, the multi-rotor aircraft has the smallest size, the highest hovering control precision and the strongest wind resistance under the same take-off weight because it has no wings, and is suitable for city internal street patrol, aerial photography and other work; but at the same time, the flight time of the multi-rotor aircraft is the shortest because there is no wing to generate additional lift.

[0007] In the current city patrol, road condition monitoring, forest fire prevention, power line patrol and other use scenarios, various aircraft with different characteristics are often required to perform different tasks, so at least two aircrafts need to be carried each time, and are replaced in different working conditions, which also means that in addition to the aircraft body, different ground equipment, different batteries and maintenance equipment need to be carried, causing too many repetitive equipment to be carried each time to perform tasks, which has a serious impact on work efficiency and utilization rate. UTILITY MODEL CONTENT

[0008] The utility model aims to design an aircraft which can realize the switching of two or more flight layouts by replacing different modules, so as to greatly improve the utilization rate of the aircraft in different environments, expand the use range and save costs.

[0009] TECHNICAL SCHEME

[0010] The utility model provides a kind of vertical take-off and landing multicopter unmanned plane of ground fast switching mode, comprising: core cabin, lift motor support, skid undercarriage, multi-rotor aircraft head fairing, compound wing configuration component;

[0011] The lift motor support is installed on the upper part of the core cabin, and the skid landing gear is installed on the lower part of the core cabin, forming a basic structure of the multi-rotor configuration and the compound wing configuration aircraft;

[0012] When the multi-rotor head fairing is installed on the head of the core cabin, the multi-rotor configuration is formed;

[0013] When the compound wing configuration assembly is installed on the basic structure, the compound wing configuration is formed.

[0014] Further, the compound wing configuration assembly comprises a propulsion motor cabin, a main wing, a tail beam, and a V-shaped tail wing.

[0015] The propulsion motor cabin is installed on the head of the core cabin; the main wing is installed on the lift motor support; and the tail beam and the V-shaped tail wing are installed on the tail of the core cabin.

[0016] Further, the motor cabin is fixed to the head of the core cabin through the propulsion motor cabin latch.

[0017] Further, the main wing is installed on the lift motor support through the main wing quick-release screw.

[0018] Further, the tail beam is installed on the tail of the core cabin through the tail beam screw clamp.

[0019] Further, when the multi-rotor configuration unmanned aerial vehicle and the compound wing configuration unmanned aerial vehicle are switched, the center of gravity of the unmanned aerial vehicle remains unchanged.

[0020] Advantages:

[0021] The application provides a kind of aircraft for realizing quick switching between multi-rotor configuration and compound wing configuration by quick-release mechanism, which can be used for city point suspension or short distance flight in multi-rotor mode, and can be used for long distance flight in compound wing mode. The two configurations are switched quickly, and can be quickly switched and deployed according to actual needs.

[0022] The application uses modularization to change the configuration of the aircraft for the first time on the unmanned vertical take-off and landing aircraft; the weight and gravity distribution of the modules before and after the change remains unchanged, avoiding additional weight of the aircraft; the key components of the two different configurations of the aircraft are shared, reducing the input cost and increasing the efficiency of the aircraft. DETAILED DESCRIPTION

[0023] Figure 1 It is an exploded view of a ground quick switching mode vertical take-off multi-rotor unmanned aerial vehicle;

[0024] Figure 2 It is an exploded view of a basic structure;

[0025] Figure 3 It is a completed assembly view of a multi-rotor configuration unmanned aerial vehicle;

[0026] Figure 4 An exploded view of a compound-wing configuration UAV;

[0027] Figure 5 A diagram showing the completed assembly of a compound wing configuration UAV. Detailed Implementation

[0028] This invention provides a vertical takeoff and landing multi-rotor unmanned aerial vehicle (UAV) with rapid ground mode switching, such as... Figure 1 As shown, it includes: core module 1; lift motor bracket 2; skid landing gear 3; multirotor nose fairing 4; propulsion motor nacelle 5; main wing 6; tail boom 7; V-tail 8; propulsion motor nacelle pin 9; main wing quick-release screw 10; and tail boom spiral clamp 11.

[0029] The lift motor support is installed on the upper part of the core module, and the skid landing gear is installed on the lower part of the core module, forming the basic structure of multi-rotor and compound wing configuration aircraft. Figure 2 As shown;

[0030] When a multi-rotor nose fairing is installed at the head of the core module, a multi-rotor configuration is formed as follows: Figure 3 As shown;

[0031] When compound airfoil components are installed on the base structure, a compound airfoil configuration is formed, such as... Figures 4-5 As shown; the compound wing configuration components include the main wing 6, tail boom 7, V-tail 8, propulsion motor nacelle pin 9, main wing quick-release screw 10, and tail boom spiral clamp 11.

[0032] The aircraft operates by combining different modules on the ground to create two aircraft with different flight characteristics. The core module 1, lift motor support 2, and skid landing gear 3 are mandatory components, forming the basic structure of the aircraft. The multi-rotor nose fairing 4 is fixed to the front of the core module 1 using bayonets, forming the multi-rotor aircraft configuration. At this configuration, the aircraft possesses vertical takeoff, hovering, and attitude flight capabilities, and can carry a certain payload to perform missions.

[0033] The nose fairing 4 of the multi-rotor configuration is removed and replaced with a propulsion motor nacelle 5, secured with propulsion motor nacelle pins 9; the main wing 6 is mounted above the lift motor bracket and secured with quick-release screws 10; the tail boom 7 and V-tail 8 are located at the rear of the core compartment 1 and secured with tail boom spiral clamps 11. This quickly switches to a compound wing configuration. The propulsion motor nacelle 5 and V-tail 8 are located aft and forward of the aircraft's heading, ensuring no change in the overall center of gravity; the main wing 6 and V-tail 8 have controllable surfaces that provide control during level flight. The compound wing configuration allows for a longer flight range while retaining vertical takeoff and landing capabilities, giving it an advantage in long-range missions.

[0034] Example 1

[0035] 1) Aircraft before performing the task, determine the characteristics of the task and select the appropriate configuration: short distance, large load, large wind environment, etc. Select multi-rotor configuration, long distance, long time flight Select composite wing configuration;

[0036] 2) Select the appropriate module according to the drawing: multi-rotor configuration uses core cabin 1, lift motor support 2, skid landing gear 3, multi-rotor head fairing 4; Composite wing configuration uses core cabin 1, lift motor support 2, skid landing gear 3, propulsion motor cabin 5, main wing 6, tail beam 7, V-tail 8;

[0037] 3) Combine the modules into an aircraft and perform a power-on test; After testing without error, perform the flight task.

Claims

1. A vertical take-off and landing multi-copter drone in ground fast handover mode, characterized in that, Comprise: Core cabin, lift motor bracket, skid landing gear, multi-rotor head fairing, compound wing configuration assembly; The lift motor bracket is installed on the upper part of the core cabin, and the skid landing gear is installed on the lower part of the core cabin, forming the basic structure of the multi-rotor configuration and the compound wing configuration aircraft; When the multi-rotor head fairing is installed on the head of the core cabin, the multi-rotor configuration is formed; When the compound wing configuration assembly is installed on the basic structure, the compound wing configuration is formed.

2. The drone of claim 1, wherein, The compound wing configuration assembly comprises a propulsion motor cabin, a main wing, a tail beam and a V-tail. The propulsion motor cabin is installed on the head of the core cabin; the main wing is installed on the lift motor bracket; and the tail beam and the V-tail are installed on the tail of the core cabin.

3. The drone of claim 2, wherein, The motor cabin is fixed to the head of the core cabin by a propulsion motor cabin latch.

4. The drone of claim 2, wherein, The main wing is installed on the lift motor bracket by main wing quick-release screws.

5. The drone of claim 2, wherein, The tail beam is installed on the tail of the core cabin by a tail beam screw clamp.

6. The drone of claim 1, wherein, When the multi-rotor configuration unmanned aerial vehicle and the compound wing configuration unmanned aerial vehicle are switched, the center of gravity of the unmanned aerial vehicle remains unchanged.

Images