CN206273678U - The unmanned plane that a kind of variable empennage is controlled with folded wing - Google Patents

Abstract

The utility model discloses a kind of variable empennage and the unmanned plane of folded wing control, mainly including fuselage, inboard wing, outside wing and empennage；It is characterized in that：The contour structures of aircraft variable empennage for Flying-wing adds, the flat thin, curved surface of profile is smooth and smooth, and the wing is arranged on fuselage the right and left, is symmetrical folding wing, is divided into inboard wing and outside wing, and outside wing is foldable；The empennage is arranged on afterbody the right and left, and empennage is variable empennage, and empennage rudder face is provided with empennage.The utility model has the advantages that：The wing is folded form wing, by wing-folding when parking, so as to improve the utilization rate in space；The empennage is varistructure, and empennage is transformed into " V " tail or horizontal tail by transmission device, is that unmanned plane improves good mobility and Stealth Fighter.

Description

A UAV controlled by variable tail and folding wings

technical field

The utility model relates to an aircraft, in particular to an unmanned aerial vehicle controlled by a variable tail and folding wings, and belongs to the field of innovative design of aircraft.

Background technique

With the advancement of modern science and technology, the aerospace industry has attracted more and more attention from people. Especially in recent years, with the popularization of aviation knowledge in my country, various companies in the drone industry have sprung up like mushrooms. UAV, also known as unmanned aerial vehicle, has the characteristics of unmanned flight, low operation requirements, sensitive response, and easy to carry. Because it can be equipped with a variety of different sensing devices, it can realize real-time image transmission and unmanned area detection functions. The drone industry has formed an extensive business chain, and its scope of use includes military, civilian and scientific research fields. It is manifested in enemy reconnaissance, border patrol, public security and anti-terrorism, earthquake relief, power communication, agriculture, ocean, meteorology, photography and other fields.

UAVs are generally divided into three types: fixed-wing, flapping-wing and rotary-wing. At present, the most widely used UAV is undoubtedly the rotor UAV, especially the quadrotor UAV. However, the gyroplane also has many shortcomings. Due to the defects of its own structure and layout, the effective weight and flight speed are limited, and batteries are generally used as power, so the battery life is insufficient. Compared with rotary-wing UAVs, fixed-wing UAVs have many advantages, such as carrying more airborne equipment, fast flight speed, and strong maneuverability. strike in time.

The Chinese patent authorization publication number is CN 102530238 A, which discloses a drone with variable wing sweep angle and spread length. Although the variable length structure can be used to realize the length change by means of gears and racks, the weight of the structure is relatively large, and in the process of changing the wingspan, a large power is required through the transmission of the input shaft and the gear.

Contents of the invention

The purpose of this utility model is to solve the above problems, and propose a UAV controlled by a variable tail and a folding wing. The structure of the mechanism for controlling the folding of the wing and the change of the tail on the UAV is simple, the occupied volume is small, and the overall weight is light. . The UAV can change the tail during the flight according to the flight mission, which improves the efficiency and has good stability.

The realization technical scheme of the present utility model is as follows: a kind of unmanned aerial vehicle controlled by variable empennage and folding wing, mainly comprises fuselage, inner side wing, outer side wing and empennage; The shape structure of the variable tail is characterized in that: the layout of the flying wing plus the variable tail, the shape is flat and thin, and the curved surface is smooth and smooth. The wings are arranged on the left and right sides of the fuselage. wing and the outer wing, the outer wing is foldable; the empennage is arranged on the left and right sides of the tail end of the fuselage, the empennage is a variable empennage, and an empennage rudder surface is arranged on the empennage.

When the utility model is in flight state, the empennage can be in a horizontal state, and the empennage can also be transformed into a "V" type symmetrical slope to increase the stability of the vertical plane.

A folding structure is provided between the outer wing and the inner wing of the utility model, and the folding structure is composed of a rocker arm, a fixed seat, a cylindrical sliding block, a threaded rod, a motor and a rotating shaft; the motor is connected to the threaded rod, and the threaded rod Connect the cylindrical sliding block, the cylindrical sliding block is connected with the rocker arm, the rocking arm is arranged on the fixed seat through the rotating shaft, and the external clamp of the cylindrical sliding block is on the fixed seat. The folding process between the outer wing and the inner wing is as follows: the motor drives the screw to rotate so that the cylindrical sliding block pushes the rocker arm to rotate around the rotating shaft to achieve the folding and unfolding of the wings.

According to the utility model, a push rod is arranged at the rear end of the fuselage, and a built-in rod and an outer sleeve are respectively arranged on the left and right tail fins. The outer sleeve and the built-in rod form a telescopic sleeve, and the telescopic sleeve passes through The built-in rod is connected to the push rod, and the empennage changes from a horizontal state to a V shape: the push rod can move up and down so that the outer sleeve is selected around the built-in rod, thereby realizing the transformation of the empennage from a horizontal state to a V shape.

The utility model has the advantages that: the wing is a folding wing, and the wing is folded when parked, thereby improving the utilization rate of space; the tail is a variable structure, and the tail is transformed into a "V" tail Or the flat tail, which improves the maneuverability and stealth performance of the UAV.

Description of drawings

Fig. 1 is a schematic diagram of the overall structure of the utility model UAV in flight state.

Fig. 2 is an overall schematic diagram of the utility model UAV in a folded state of wings.

Fig. 3 is a front view of the "V" state of the UAV of the utility model in flight.

Fig. 4 is the left view of the "V" state when the UAV of the utility model is flying.

Figure 5 is a state diagram of the flat tail of the utility model UAV during flight.

Fig. 6 is a schematic diagram of the mechanism for controlling the folding of the wings of the UAV of the utility model.

Fig. 7 is a schematic diagram of the mechanism for controlling the folding of the wings of the UAV of the utility model without including the internal mechanism of the fixing seat.

Fig. 8 is a schematic diagram of the mechanism for controlling the tail of the utility model UAV to change from a horizontal state to a V shape.

The names of the marks in the figure are: 1-fuselage, 2-inner wing, 3-outer wing, 4-tail, 5-tail rudder surface, 6-rocker arm, 7-fixing seat, 8-cylindrical sliding block , 9-threaded rod, 10-motor, 11-rotating shaft, 12-push rod, 13-built-in rod, 14-outer sleeve.

detailed description

Below in conjunction with accompanying drawing, the utility model is further described.

As shown in Figure 1-5, a UAV controlled by a variable tail and folding wings mainly includes a fuselage 1, an inner wing 2, an outer wing 3 and an empennage 4; The shape structure of the wing layout plus the variable tail is characterized in that: the flying wing plus the variable tail layout, the shape is flat and thin, the curved surface is smooth and smooth, and the wings are arranged on the left and right sides of the fuselage 1, which are left and right symmetrical foldable wings , divided into inner wing 2 and outer wing 3, the outer wing 3 is foldable; the empennage 4 is arranged on the left and right sides of the tail end of the fuselage 1, the empennage 4 is a variable empennage, and an empennage rudder surface 5 is arranged on the empennage .

As shown in Figures 6-8, a folding structure (drive device) is provided between the outer wing 2 and the inner wing 3 of the utility model, and the folding structure consists of a rocker arm 6, a fixed seat 7, a cylindrical sliding block 8, The threaded rod 9, the motor 10 and the rotating shaft 11 are composed; the motor 10 is connected with the threaded rod 9, the threaded rod 9 is connected with the cylindrical sliding block 8, and the cylindrical sliding block 8 is connected with the rocker arm 6, and the rocker arm 6 is arranged on the fixed seat 7 through the rotating shaft 11 , the cylindrical sliding block 8 is externally clamped on the fixing seat 7 . The folding process between the outer wing 2 and the inner wing 3 is as follows: the motor drives the screw to rotate so that the cylindrical sliding block pushes the rocker arm to rotate around the rotation axis to achieve the folding and unfolding of the wings.

According to the utility model, a push rod 12 is provided at the tail end of the fuselage, and a built-in rod 13 and an outer sleeve 14 are respectively arranged on the left and right empennages, and the outer sleeve 14 and the built-in rod 13 form a telescopic sleeve. The telescopic sleeve is connected to the push rod 12 through the built-in rod 13, and the empennage changes from a horizontal state to a V shape: the push rod can move up and down so that the outer sleeve is selected around the built-in rod, thereby realizing the transformation of the empennage from a horizontal state to a V shape.

As shown in Figure 6, the wings of the aircraft are in a folded state when the aircraft is stationary on the ground, and when the flight takes off, the wings are opened by the driving device. When the aircraft is in flight, if there is an emergency, the tail can also be turned into a "V" shape through the drive device (Figure 8) to improve the maneuverability of the aircraft.

The power unit (propeller type engine) of the utility model UAV can be installed on the front part of the fuselage (head), and can also be installed on the rear part of the fuselage, and the rear part of the fuselage can also be replaced with a jet engine. The interior of the fuselage 1 has a large space, which can be loaded with various equipment for reconnaissance, transmission, and control.

The specific working process of the utility model unmanned aerial vehicle is supplemented with examples below:

When the drone is static, the outer wings are in a folded state, as shown in Figure 2. At this time, the placement of the drone can save space and improve space utilization.

The basic principles, main features and advantages of the present utility model have been shown and described above. Those skilled in the industry should understand that the utility model is not limited by the above-mentioned embodiments. The above-mentioned embodiments and descriptions are only the principles of the utility model. Without departing from the spirit and scope of the utility model, the utility model There will also be various changes, and these changes and improvements all fall within the scope of protection claimed by the utility model. The scope of protection required by the utility model is defined by the appended claims and their equivalents.

Claims (4)

1. An unmanned aerial vehicle controlled by a variable empennage and a folding wing, mainly comprising a fuselage, an inner wing, an outer wing and an empennage; it is characterized in that: the fuselage and the wings add the shape of a flying wing layout and a variable empennage Structure, the wing is arranged on the left and right sides of the fuselage, is a symmetrical foldable wing, divided into inner wing and outer wing, and the outer wing is foldable; the empennage is arranged on the left and right sides of the tail end of the fuselage, For variable empennage, empennage rudder surface is provided with on empennage. 2. The unmanned aerial vehicle controlled by a kind of variable empennage and folding wing according to claim 1, is characterized in that: empennage can be in horizontal state, also can empennage be transformed into " V " type symmetrical slope. 3. The unmanned aerial vehicle controlled by a kind of variable empennage and folding wing according to claim 1, it is characterized in that: a folding structure is provided between the outer wing and the inner wing, and the folding structure is controlled by a rocking arm. , a fixed seat, a cylindrical sliding block, a threaded rod, a motor and a rotating shaft; The sliding block is externally clamped on the fixing seat. 4. The UAV controlled by a variable tail and folding wings according to claim 1, characterized in that: a push rod is provided at the rear end of the fuselage, and a built-in rod is respectively provided on the left and right tails and the outer sleeve, the outer sleeve and the built-in rod form a telescopic sleeve, and the telescopic sleeve is connected to the push rod through the built-in rod.