CN210455235U

CN210455235U - Small-sized double-shaft hidden blade jet manned aircraft

Info

Publication number: CN210455235U
Application number: CN201921259664.4U
Authority: CN
Inventors: 张季任; 周浩
Original assignee: Nantong Tianrui Electronic Technology Co Ltd
Current assignee: Nantong Tianrui Electronic Technology Co Ltd
Priority date: 2019-08-06
Filing date: 2019-08-06
Publication date: 2020-05-05
Anticipated expiration: 2029-08-06

Abstract

The utility model discloses a blade jet manned aircraft is hidden to small-size biax relates to aircraft technical field, has solved current biax aircraft and has mostly been large-scale turbine oar engine biax cargo airplane, because of the huge of its paddle, leads to unstable flight gesture to turbine oar engine's efficiency is far less than turbofan engine's problem. The air jet engine comprises an engine body, wherein a plurality of miniature turbofan engines are arranged in the engine body, a plurality of air jet rings are connected to the turbofan engines, air ring air inlets communicated with air outlets of the turbofan engines are formed in the outer peripheral surfaces of the air jet rings, a circle of air flow pipeline arranged along the circumferential direction of the air jet rings is formed in the inner portions of the air jet rings, the air ring air inlets are communicated with the air flow pipeline, a circle of air outlets communicated with the air flow pipeline are formed in the inner peripheral surfaces of the air jet rings, and openings of the. The effect of providing larger thrust and more flexible attitude conversion capability of the aircraft under the environment with low consumption is achieved, and better flight stability is brought.

Description

Small-sized double-shaft hidden blade jet manned aircraft

Technical Field

The utility model relates to an aircraft technical field, in particular to jet manned aircraft of blade is hidden to small-size biax.

Background

Current biax aircraft is mostly large-scale turbine oar engine biax cargo airplane, and main application provides lift in the aspect of military transportation, and current biax manned aircraft leans on two turbine oar engines to drive large-scale paddle, because of the huge of its paddle, can produce resonance scheduling problem, can lead to unstable flight gesture indirectly to turbine oar engine's efficiency is far less than turbofan engine. The attitude adjustment of the turbine-paddle biaxial aircraft needs to depend on adjusting the thrust directions of two engines, so that the thrust direction of the turbine-paddle biaxial aircraft can be changed by inertia caused by high-speed rotation of the turbine paddle through relatively large torsion.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a blade jet manned aircraft is hidden to small-size biax, it can utilize the vortex to smuggle the phenomenon (inclusion) principle secretly, increases turbofan engine's thrust 10-15 times, provides bigger thrust and more nimble aircraft gesture conversion ability under the environment that consumes slowly to replace the high energy consumption of current turbine oar engine, it is low efficient, bring better flight stability.

The above technical purpose of the present invention can be achieved by the following technical solutions:

the utility model provides a jet-propelled manned aircraft of blade is hidden to small-size biax, includes the fuselage, be equipped with a plurality of miniature turbofan engines in the fuselage, last a plurality of jet rings that are connected with of turbofan engine, the gaseous ring air inlet that is linked together with turbofan engine's gas vent is seted up on the jet ring outer peripheral face, the round airflow channel who sets up along its circumference is seted up to the jet ring inside, and the gaseous ring air inlet is linked together with the airflow channel, sets up the air outlet that round and airflow channel are linked together on the jet ring internal peripheral face, the air outlet opening sets up downwards.

Further, the jet ring is symmetrically disposed about the fuselage.

Furthermore, the tail part of the fuselage is provided with a rear vertical tail wing.

Furthermore, the outer side of the air inlet of the air ring is connected with a butt-joint ring, and the butt-joint ring is fixedly connected with the exhaust port of the turbofan engine through a plurality of bolts.

Further, the diameter of the inner circumferential surface of the lower portion of the gas injection ring is decreased downward.

Furthermore, a circle of bent edge is arranged at the top of the side wall right below the air outlet and is positioned inside the airflow pipeline.

Further, the distance between the top of the gas flow duct and the bent edge decreases with decreasing diameter.

To sum up, the utility model discloses following beneficial effect has:

by utilizing the principle that when a beam of air flows passes through at a high speed by using the vortex Entrainment phenomenon (Entrainment), because of different air flow speeds, the air flow generates friction with the air around the air flow, so that the air around the air flow is driven to move towards the same direction, one or two miniature turbofan engines are used for providing power, high-speed air is sprayed out through a diversion pipeline and passes through a Jet ring (Jet Loop) to generate thrust, and because the Jet ring does not have a paddle rotating at a high speed when generating the thrust, the thrust direction of the Jet ring can be changed only by low directional torque.

Compared with the existing military double-shaft aircraft, the aircraft has higher thrust and lower oil consumption, and the airflow thrust can be increased by 10-15 times under the original thrust by utilizing the vortex entrainment principle. And this design will reduce the large inertia that would otherwise be brought about by the size of the turbine blades. Stable power can be provided in flight and better maneuverability can be achieved.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic view of the overall structure of FIG. 1 from another perspective;

FIG. 3 is a schematic cross-sectional view of a portion of the jet ring;

FIG. 4 is an exploded view of the structure between the jet ring and the micro turbofan engine.

In the figure, 1, a fuselage; 11. an engine compartment; 12. an oil tank; 13. a vertical tail; 2. a turbofan engine; 3. an air injection ring; 31. an air ring inlet; 32. an air flow conduit; 33. an air outlet; 34. a docking ring; 35. and (5) bending the edges.

Detailed Description

The following description will be further described with reference to the accompanying drawings, which are not intended to limit the present invention.

A small-sized double-shaft hidden blade jet manned aircraft comprises an aircraft body 1, wherein an engine cabin 11 and an oil tank 12 are arranged in the aircraft body 1, two miniature turbofan engines 2 (refer to fig. 4) are fixed in the engine cabin 11, the turbofan engines 2 are connected with an air injection ring 3, and the two air injection rings 3 are symmetrically arranged relative to the aircraft body 1; the tail part of the machine body 1 is provided with a rear vertical tail wing 13.

As shown in fig. 3 and 4, an air ring air inlet 31 communicated with an air outlet of the turbofan 2 is formed on the outer circumferential surface of the air injection ring 3, a circle of air flow pipelines 32 arranged along the circumferential direction are formed inside the air injection ring 3, the air ring air inlet 31 is communicated with the air flow pipelines 32, a circle of air outlets 33 communicated with the air flow pipelines 32 are formed on the inner circumferential surface of the air injection ring 3, and openings of the air outlets 33 are inclined downwards towards the axis of the air injection ring 3.

As shown in fig. 4, the outer side of the air ring inlet 31 is integrally connected with a docking ring 34, and the docking ring 34 is fixedly connected with the exhaust port of the turbofan engine 2 through a plurality of bolts uniformly distributed.

As shown in fig. 3, a circle of bent edge 35 is disposed at the top of the sidewall right below the air outlet 33, the cross section of the bent edge 35 is arc-shaped and is located inside the air flow duct 32, and the distance between the top of the air flow duct 32 and the bent edge 35 decreases with the decrease of the diameter; the diameter of the inner circumferential surface of the lower half portion of the gas injection ring 3 decreases downward, and the diameter of the inner circumferential surface of the upper half portion of the gas injection ring 3 below the bent edge 35 is equal.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and those skilled in the art can make various modifications or equivalent substitutions within the spirit and scope of the present invention, and such modifications or equivalent substitutions should also be considered as falling within the scope of the present invention.

Claims

1. The utility model provides a blade jet manned aircraft is hidden to small-size biax which characterized in that: including fuselage (1), be equipped with a plurality of miniature turbofan engine (2) in fuselage (1), be connected with a plurality of gas injection rings (3) on turbofan engine (2), set up gas ring air inlet (31) that are linked together with turbofan engine's (2) gas vent on gas injection ring (3) outer peripheral face, gas injection ring (3) inside is seted up round air flow pipeline (32) that set up along its circumference, and gas ring air inlet (31) are linked together with air flow pipeline (32), set up round air outlet (33) that are linked together with air flow pipeline (32) on gas injection ring (3) inner peripheral face, air outlet (33) opening sets up downwards.

2. The small, dual-axis, hidden-blade, jet manned vehicle of claim 1, wherein: the air injection ring (3) is symmetrically arranged relative to the machine body (1).

3. The small two-axis hidden-blade jet manned vehicle of claim 1 or 2, characterized in that: the tail part of the machine body (1) is provided with a rear vertical tail wing (13).

4. The small, dual-axis, hidden-blade, jet manned vehicle of claim 3, wherein: the outer side of the air ring air inlet (31) is connected with a butt joint ring (34), and the butt joint ring (34) is fixedly connected with an air outlet of the turbofan engine (2) through a plurality of bolts.

5. The small, dual-axis, hidden-blade, jet manned vehicle of claim 1, wherein: the diameter of the inner circumferential surface of the lower part of the gas injection ring (3) is decreased downwards.

6. The small two-axis hidden-blade jet manned vehicle of claim 1 or 5, characterized in that: and a circle of bent edge (35) is arranged at the top of the side wall right below the air outlet (33), and the bent edge (35) is positioned inside the airflow pipeline (32).

7. The small, dual-axis, hidden-blade, jet manned vehicle of claim 6, wherein: the distance between the top of the airflow duct (32) and the bent edge (35) decreases with the decrease of the diameter.