阅读说明：本技术 一种双机身串列翼垂直起降布局的飞行器 (Aircraft with double-fuselage tandem wing vertical take-off and landing layout ) 是由 杨小川 付志 肖涵山 王海军 毛仲君 何炬恒 何开锋 姜久龙 于 2020-07-03 设计创作，主要内容包括：本发明专利公开了一种双机身串列翼垂直起降布局的飞行器,具体涉及航空飞行器的技术领域。一种双机身串列翼垂直起降布局的飞行器,包括两个间隔设置的机身,每个机身上均设有发动机,两个机身上共同设有间隔分布的前串列式机翼和后串列式机翼,每个机身上均还对称设有位于前串列式机翼一端的电动倾转旋翼,电动倾转旋翼与发动机之间连接有发电机,发电机与发动机电连接,后串列式机翼上设有位于两个机身之间的第一升力风扇和位于第一升力风扇下方的滑流舵,每个机身上均设有位于后串列式机翼一端的垂尾。采用本发明技术方案克服了现有的飞行器无法在恶劣天气情况下稳定垂直起降的问题,可用于飞行器在极端天气条件下飞行。(The invention discloses an aircraft with a double-fuselage tandem wing vertical take-off and landing layout, and particularly relates to the technical field of aviation aircrafts. The utility model provides an aircraft of double-fuselage tandem wing VTOL overall arrangement, fuselage including two intervals settings, all be equipped with the engine on every fuselage, be equipped with interval distribution's preceding tandem wing and back tandem wing jointly on two fuselages, all still the symmetry is equipped with the electronic rotor that verts that is located preceding tandem wing one end on every fuselage, be connected with the generator between electronic rotor and the engine that verts, the generator is connected with the engine electricity, be equipped with the slipstream rudder that is located first lift fan between two fuselages and is located first lift fan below on the back tandem wing, all be equipped with the vertical fin that is located back tandem wing one end on every fuselage. By adopting the technical scheme of the invention, the problem that the conventional aircraft cannot stably take off and land vertically under the severe weather condition is solved, and the aircraft can fly under the extreme weather condition.)

1. The utility model provides an aircraft of double fuselage tandem wing VTOL overall arrangement which characterized in that: including the fuselage that two intervals set up, every all be equipped with the engine on the fuselage, two be equipped with interval distribution's preceding tandem wing and back tandem wing jointly on the fuselage, the length of preceding tandem wing is less than the length of back tandem wing, every all still the symmetry is equipped with the electronic rotor that verts that is located preceding tandem wing one end on the fuselage, be connected with the generator between electronic rotor and the engine that verts, the generator is connected with the engine electricity, be equipped with the slipstream rudder that is located first lift fan between two fuselages and is located first lift fan below on the back tandem wing, first lift fan is connected with the engine, every all be equipped with the vertical tail that is located back tandem wing one end on the fuselage.

2. The aircraft of claim 1, wherein the aircraft comprises a double-fuselage tandem wing vertical take-off and landing layout: and the rear tandem type wings are symmetrically provided with electric ducted fans outside the fuselage, and the electric ducted fans are electrically connected with the generator.

3. The aircraft of any one of claims 1 or 2, wherein the aircraft comprises a double-fuselage tandem wing vertical take-off and landing layout: the front tandem type wing is a duck wing.

4. The utility model provides an aircraft of double fuselage tandem wing VTOL overall arrangement which characterized in that: including the fuselage that two intervals set up, every all be equipped with the engine on the fuselage, two be equipped with interval distribution's preceding tandem wing and back tandem wing jointly on the fuselage, the length of preceding tandem wing is less than the length of back tandem wing, be connected with the generator between electronic verting rotor and the engine, the generator is connected with the engine electricity, be equipped with the slipstream rudder that is located first lift fan between two fuselages and is located first lift fan below on the back tandem wing, first lift fan is connected with the engine, every all be equipped with the vertical tail that is located back tandem wing one end on the fuselage, every equal symmetry is equipped with electronic verting rotor on the back tandem wing.

5. The aircraft of claim 4, wherein the aircraft comprises: and a second lift fan positioned between the two fuselages is arranged on the front tandem wing, and the second lift fan is connected with the engine.

6. The aircraft of claim 4, wherein the aircraft comprises: and each fuselage is provided with a third lift fan connected with the engine, and each third lift fan is positioned on the fuselage right above the front tandem wing.

Technical Field

The invention relates to the technical field of aviation aircrafts, in particular to an aircraft with a double-fuselage tandem wing vertical take-off and landing layout.

Background

In the field of aviation aircrafts, vertical take-off and landing fixed wing aircrafts have significant military and civil dual-purpose values, and are the key direction for development of all countries of aviation aircrafts. The layout forms of the common vertical take-off and landing aircrafts mainly comprise three types, namely a combined type, a tilting type and a tail-seated type. The existing vertical take-off and landing fixed wing aircraft has the inherent defects of poor wind resistance, insufficient take-off and landing stability, limited load space and the like. For example, in the composite vertical take-off and landing layout, a rotor power design with high hovering efficiency is mostly adopted, and the defects that the rotor has low downwash speed and is easy to vortex ring stall, the rotor disc surface load is greatly changed under the condition of gust, the course control capability is weak and the like are overcome; the tip of a rotor blade adopts a rotor design, so that the rotor blade is easy to enter a vortex ring stall state, and the defects of poor stability, poor wind resistance and the like exist; the tail-sitting type vertical take-off and landing layout has the problems of higher gravity center, poor stability at the take-off and landing moment, weak lateral wind resistance and the like. Therefore, an aircraft capable of stabilizing vertical take-off and landing under severe weather conditions is urgently needed.

Disclosure of Invention

The invention aims to provide an aircraft with a double-fuselage tandem wing vertical take-off and landing layout, so as to solve the problem that the conventional aircraft cannot stably take off and land in severe weather.

In order to achieve the above purpose, one technical solution of the present invention is as follows: the utility model provides an aircraft of double-fuselage tandem wing VTOL overall arrangement, includes the fuselage that two intervals set up, every all be equipped with the engine on the fuselage, two be equipped with interval distribution's preceding tandem wing and back tandem wing jointly on the fuselage, the length of preceding tandem wing is less than the length of back tandem wing, every all on the fuselage still the symmetry is equipped with the electronic rotor that verts that is located preceding tandem wing one end, be connected with the generator between electronic rotor and the engine of verting, the generator is connected with the engine electricity, be equipped with the slipstream rudder that is located first lift fan between two fuselages and is located first lift fan below on the back tandem wing, first lift fan is connected with the engine, every all be equipped with the vertical tail that is located back tandem wing one end on the fuselage.

The principle and the effect of the technical scheme are as follows: the double machine bodies can improve the load space of the whole machine, and large-size goods or equipment can be conveniently carried. The first lift fan can provide power for the vertical direction of the aircraft, and the first lift fan can control the pitching direction; and electronic tilt rotor is located the fuselage of tandem wing one side before, when the aircraft carried out vertical take-off, and electronic tilt rotor can provide the power of VTOL to can also carry out pitch control. The course channel is deflected by a slipstream rudder arranged below the first lift fan to generate course control torque, so that course stability augmentation and operation are realized, and the wind resistance requirement is met; moreover, the aircraft does not need to tilt the aircraft body in vertical take-off and landing, the gravity center is low, the stability in the take-off and landing moment is high, a three-channel stability-increasing control mode is adopted in the hovering state, and the control mode is simple.

Furthermore, electric ducted fans outside the fuselage are symmetrically arranged on the rear tandem type wings, and the electric ducted fans are electrically connected with the generator. By means of the first lift force fan and the electric ducted fan of the wing, the lower wash flow speed is large and is surrounded by the duct, and the problems of blade tip vortex ring stall and the like do not exist.

Furthermore, the front tandem wing is a duck wing. The canard wing is used for generating balance and pitching control moment, so that airplane balancing can be better performed.

The other technical scheme of the invention is as follows: the utility model provides an aircraft of double-fuselage tandem wing VTOL overall arrangement, includes the fuselage that two intervals set up, every all be equipped with the engine on the fuselage, two be equipped with interval distribution's preceding tandem wing and back tandem wing jointly on the fuselage, the length of preceding tandem wing is less than the length of back tandem wing, be connected with the generator between electronic tilt rotor and the engine, the generator is connected with the engine electricity, be equipped with the slipstream rudder that is located first lift fan between two fuselages and is located first lift fan below on the back tandem wing, first lift fan is connected with the engine, every all be equipped with the vertical tail that is located back tandem wing one end on the fuselage, every equal symmetry is equipped with electronic tilt rotor on the back tandem wing.

Furthermore, a second lift fan positioned between the two airframes is arranged on the front tandem type wing, and the second lift fan is connected with the engine.

Furthermore, each fuselage is provided with a third lift fan connected with the engine, and each third lift fan is positioned on the fuselage right above the front tandem wing.

Compared with the prior art, the beneficial effect of this scheme:

1. the wind resistance is strong. The plurality of lift fans and the electric ducted fans have high downwash speed and are surrounded by the ducted ducts, so that the problems of blade tip vortex ring stall and the like do not exist; the electric tilting rotor wing can realize larger torsion angle and high washing speed relative to the rotor wing, and the problem of vortex ring stall is not easy to occur; the course control is carried out by utilizing the slipstream rudder, the efficiency is high, the operating torque is large, and the course wind resistance requirement is met;

2. the hovering efficiency is high. The first lift fan is directly driven by the engine, and has high hovering efficiency, large takeoff weight and large task load;

3. the power arrangement is flexible. According to the scheme, the oil-electricity hybrid power is adopted, the double-generator electric tilting rotor wing is adopted at the front end of the machine head, and the generator dragged by the engine supplies power, so that the complexity of a transmission system is reduced, and the flexibility of arrangement of power, a propulsion device and the whole machine is improved;

4. the payload is large and the load space is abundant. By adopting the design of the double machine bodies, the whole machine loading space can be improved, and large-size goods or equipment can be conveniently carried.

Drawings

FIG. 1 is a plan view of embodiment 1 of the present invention;

FIG. 2 is a top view of embodiment 2 of the present invention;

FIG. 3 is a top view of embodiment 3 of the present invention;

FIG. 4 is a plan view of embodiment 4 of the present invention.

Detailed Description

The present invention will be described in further detail below by way of specific embodiments:

reference numerals in the drawings of the specification include: fuselage 1, preceding tandem wing 2, back tandem wing 3, first lift fan 4, vertical fin 5, electronic rotor 6 that verts, electronic ducted fan 7, duck wing 8, second lift fan 9, third lift fan 10.