CN111003172B

CN111003172B - Jet type vertical lifting pneumatic system

Info

Publication number: CN111003172B
Application number: CN201811168650.1A
Authority: CN
Inventors: 苏郁夫
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-10-08
Filing date: 2018-10-08
Publication date: 2021-07-27
Anticipated expiration: 2038-10-08
Also published as: CN111003172A

Abstract

The invention relates to a jet-propelled vertical lifting pneumatic system, which comprises a machine body with an upper cabin cover and a lower cabin cover, an engine and two power components arranged on a left wing and a right wing respectively.

Description

Jet type vertical lifting pneumatic system

Technical Field

The invention relates to a jet-propelled vertical lifting pneumatic system, in particular to a jet-propelled vertical lifting pneumatic system applied to a flying carrier.

Background

Generally, a flight vehicle is roughly classified into a fixed wing aircraft and a rotor wing aircraft (such as a helicopter or a gyroplane) according to the difference between the flight principle and the flight function, the fixed wing aircraft mainly uses a power device to provide forward thrust, and generates lift force by using the air pressure difference and the air flow impact effect generated when air flows over the upper part and the lower part of a wing, so that the flight speed is high, the carrying capacity is large, and the flight efficiency is high, but the fixed wing aircraft needs a runway to provide take-off and landing, so the take-off and landing site has limitations. The rotor helicopter drives the rotor to rotate by means of the engine to generate ascending power, so that the rotor helicopter can vertically lift in a small-area field and can fly at low altitude and low speed, but the helicopter has short range and low speed and is greatly influenced by weather. In addition, the gyroplane generates lift force by rotating the rotor wing through the forward relative airflow, so that the take-off and landing distance is short, the gyroplane can fly at low speed and low altitude, and the flying speed and the flying efficiency of the gyroplane are far lower than those of a fixed-wing aircraft.

In recent years, vertical lift aircrafts combining the characteristics of a fixed wing Aircraft and a rotary wing Aircraft have been gradually developed, wherein a tilt rotor Aircraft (Tiltrotor Aircraft) is a more common form, and a fuselage and a wing of the tilt rotor Aircraft are basically similar to an Aircraft, but propellers are arranged at two ends of the wing, so that when the propellers are started to rotate from a horizontal state to a vertical state, the tilt rotor Aircraft can vertically take off and land or hover like a helicopter, and when the tilt rotor Aircraft is about to fly, the propellers are in the horizontal state to provide forward thrust for the Aircraft, and further the tilt rotor Aircraft can fly like a fixed wing Aircraft.

For background of the related art, please refer to U.S. Pat. No. 09868523B2, which discloses a vertical take-off and landing (VTOL) fixed-wing aircraft, wherein an airflow plenum chamber including a compressor housing extends between a plurality of air inlets and air outlets, a centrifugal compressor assembly is disposed in the compressor housing, the centrifugal compressor assembly includes an upper impeller and a lower impeller, and the upper impeller and the lower impeller rotate in opposite directions around a substantially vertical compressor axis, such that the upper impeller and the lower impeller can respectively suck air at upper and lower ends and discharge the air from the air outlets, and a thrust-enhancing tube is disposed at each air outlet, such that the fixed-wing aircraft can vertically take off and land when the thrust-enhancing tube pivots downward, or the thrust-enhancing tube pivots rearward to enable the fixed-wing aircraft to fly forward when the air inlets are closed.

Disclosure of Invention

In view of the fact that fixed wing aircraft and rotor aircraft are each missing coins. Therefore, the invention aims to achieve the purpose of vertical lifting of the flying carrier by means of the power components by respectively arranging the power components on the two wings of the aircraft body and enabling the two power components and the engine to form a three-point balance state.

To achieve the above objects, the present invention provides a jet-propelled vertical lift pneumatic system, comprising:

the aircraft comprises an aircraft body, a front end of the aircraft body, a rear end of the aircraft body, a left wing, a right wing, an upper cabin cover and a lower cabin cover, wherein the aircraft body forms a longitudinal axial aircraft body, the left wing and the right wing are symmetrically connected on two sides of the aircraft body in the transverse axial direction;

the engine is arranged in the machine body and corresponds to the positions of the upper hatch cover and the lower hatch cover, and is driven to pivot through at least one first servo motor; and

two power components, which are respectively combined with the left wing and the right wing to make the engine and the two power components form an isosceles triangle configuration, and the power components comprise a pipe body with a tail cover and a driving device, a slide rail is arranged in the pipe body, a servo seat with a screw motor is sleeved on the slide rail, the servo seat is connected with the driving device so as to drive the servo seat to move on the slide rail by virtue of the driving device, the servo seat is pivoted with a corner seat, a first connecting rod group is assembled between a driving shaft of the screw motor and the corner seat so as to drive the connecting rod group to pivot the corner seat, a motor seat with a second servo motor is pivoted on the corner seat, the second servo motor is used for driving the motor seat to pivot, and a propeller motor is arranged at one end of the motor seat, which is not pivoted with the first connecting rod group, the driving shaft of the propeller motor is coupled with a propeller assembly so as to drive the propeller assembly to unfold and rotate the hinge thereof by virtue of the propeller motor.

In the jet-type vertical lifting pneumatic system, a second connecting rod group is arranged between the first servo motor and the engine, so that the first servo motor drives the second connecting rod group to pivot the engine.

The jet-propelled vertical lifting pneumatic system is characterized in that the engine is an engine.

The jet-propelled vertical lifting pneumatic system is characterized in that the engine is a wind guide fan propeller.

The jet-propelled vertical lifting pneumatic system is characterized in that a third servo motor is arranged on the tube body, and a driving shaft of the third servo motor is connected with the tail cover through a third connecting rod group, so that the third servo motor drives the third connecting rod group to enable the tail cover to be pivoted on the tube body for opening.

The jet-propelled vertical lifting pneumatic system is characterized in that a tail fin is arranged on the tube body, and an accommodating space for accommodating the third servo motor is formed in the tail fin.

The jet-propelled vertical lifting pneumatic system is characterized in that the pivoting angle of the corner seat is 90 degrees.

The jet-type vertical lifting pneumatic system is characterized in that the motor seat pivots by +/-30 degrees by taking a driving shaft of the second servo motor as a center.

The driving device comprises a further motor, two belt wheels and a belt sleeved on the two belt wheels, a gap is formed in the pipe body, and a connecting piece penetrating through the gap is fixedly arranged between the servo seat and the belt, so that when the stepping motor drives one of the belt wheels to rotate, the belt drives the servo seat to move on the slide rail.

The jet-propelled vertical lifting pneumatic system is characterized in that a nozzle assembly is arranged at the tail end of the machine body.

Based on the above, when the engine is pivoted by the two power assemblies in three-point balance with the engine to be in a lifting or falling state, the propeller assembly can be pushed out of the pipe body by the two power assemblies and pivoted to be perpendicular to the machine body, so that the machine body can be in a balance state when being vertically lifted or fallen by adjusting the deflection angle or the rotating speed of the propeller assembly, and the purpose of vertical lifting is achieved. When the engine body is vertically lifted off and suspended, the engine pivots 45 degrees to generate speed by means of jet component force propulsion, at the moment, the wings gradually generate buoyancy, and after a certain idling speed is generated, the two power assemblies start to be retracted into the pipe fitting to complete the process of rotating from vertical to horizontal, and stall is avoided.

Drawings

Fig. 1 is a perspective view of the present invention.

Fig. 2 is an exploded perspective view of the present invention.

Fig. 3 is an exploded perspective view of the power assembly of the present invention.

Fig. 4 is a schematic view of the present invention for opening the upper and lower hatch covers.

Fig. 5-7 are schematic views of the operation of the power assembly of the present invention.

Fig. 8-11 are schematic views of the takeoff of the present invention.

Description of reference numerals: (invention) 1-body; 11-a fuselage; 12-left wing; 13-right wing; 14-upper hatch cover; 15-lower hatch cover; 2-an engine; 21-a second linkage; 22-a first servomotor; 3-a power assembly; 31-a tube body; 310-tail cap; 311-tail fin; 312-a third servomotor; 313-a third linkage; 314-a slide rail; 315-gap; 32-a servo seat; 321-a screw motor; 322-a first set of links; 323-a link; 33-a drive device; 331-a stepper motor; 332-a pulley; 333-a belt; 34-a corner seat; 35-a motor seat; 351-a second servomotor; 36-a propeller motor; 361-a propeller assembly; 362-hinge; 4-nozzle assembly.

Detailed Description

To understand the techniques, means and functions of the present invention, a preferred embodiment will be described in detail with reference to the accompanying drawings, wherein:

first, referring to fig. 1-2, the jet-type vertical lift pneumatic system of the present invention includes a machine body 1, an engine 2, two power assemblies 3, and a nozzle assembly 4. The aircraft body 1 forms a longitudinal axial fuselage 11, two sides of the fuselage 11 are connected with a left wing 12 and a right wing 13 which are symmetrical in a transverse axial direction, and an upper hatch cover 14 and a lower hatch cover 15 are arranged at the front end of the fuselage 11; the engine 2 is an engine or a fan propeller, is disposed inside the fuselage 11 at a position corresponding to the upper deck lid 14 and the lower deck lid 15, and is connected to the first servo motor 22 through a second linkage 21, so that the first servo motor 22 drives the second linkage 21 to pivot the engine 2; the two power assemblies 3 are respectively combined with the left wing 12 and the right wing 13, so that the engine 2 and the two power assemblies 3 form an isosceles triangle configuration.

The power assembly 3 includes a tube 31 having a tail cap 310 and a driving device 33 (refer to fig. 3), a tail fin 311 is disposed on the tube 31, a third servo motor 312 is disposed in the accommodating space of the tail fin 311, and a driving shaft of the third servo motor 312 is connected to the tail cap 310 through a third connecting rod group 313, so that the third servo motor 312 drives the third connecting rod group 313 to pivot and open the tail cap 310 on the tube 31. The sliding rail 314 is disposed in the tube 31, the sliding rail 314 is sleeved with the servo seat 32 having the screw motor 321, and the servo seat 32 is connected to the driving device 33, wherein the driving device 33 includes a stepping motor 331, two pulleys 332, and a belt 333 sleeved on the two pulleys 332, a gap 315 is formed in the tube 31, and a connecting member 323 passing through the gap 315 is fixedly disposed between the servo seat 32 and the belt 333, so that when the stepping motor 331 drives one of the pulleys 332 to rotate, the belt 333 drives the servo seat 32 to move on the sliding rail 314. The servo seat 32 is pivotally connected to the rotation angle seat 34, and is assembled by a first connecting rod group 322 between the driving shaft of the screw motor 321 and the rotation angle seat 34, so that the screw motor 321 drives the first connecting rod group 322 to pivot the rotation angle seat 3490 °, the motor seat 35 with the second servo motor 351 is pivotally connected to the rotation angle seat 34, the second servo motor 351 is used to drive the motor seat 35 to pivot within a range of ± 30 ° centering on the driving shaft of the second servo motor 351, and a propeller motor 36 is disposed at one end of the motor seat 35 not pivotally connected to the first connecting rod group 322, the driving shaft of the propeller motor 36 is pivotally connected to a propeller assembly 361, so that the propeller assembly 361 is driven by the propeller motor 36 to unfold and rotate the hinge 362. And the nozzle assembly 4 is arranged at the tail end of the machine body 1.

Next, referring to fig. 4, the following paragraphs will be described with the body 1 lifted as an example. When the machine body 1 is about to be lifted, the upper deck lid 14 and the lower deck lid 15 are opened respectively, and the first servo motor 22 drives the second linkage 21 to pivot the engine 2, which is originally parallel to the machine body 11, by 90 degrees to be perpendicular to the machine body 11, at this time, the third servo motor 312 of the two power assemblies 3 drives the third linkage 313 to open the tail lid 310 (as shown in fig. 5), at the same time, the stepping motor 331 rotates the pulley 332 and drives the belt 333 to rotate (as shown by the arrow in fig. 5), so that the connecting member 323 fixed on the belt 333 moves along the gap 315 along with the belt 333, the servo seat 32 is pushed out of the tube 31 by the slide rail 314 (as shown in fig. 6), and the screw motor 321 is driven to make the first link set 322 push the corner seat 34 to pivot by 90 ° (see fig. 7), and the motor seat 35 is synchronously pivoted to make the propeller assembly 361 to be vertical, next, the propeller assembly 361 is driven by the propeller motor 36 to unfold and rotate the flap 362 (as shown in fig. 8).

Referring to fig. 9, when the body 1 is axially low at the right side and high at the left side according to X, the propeller motor 36 (not shown) of the power assembly 3 disposed on the right wing 13 is driven to increase the rotation speed, so that the body 1 is balanced left and right; when the machine body 1 presents a machine head with a low machine head and a high machine tail by taking Y as an axial direction, the propeller motors 36 of the power assemblies 3 arranged on the left wing 12 and the right wing 13 are driven to reduce the rotating speed, so that the machine body 1 is balanced front and back; when the machine body 1 deflects towards the right direction (please refer to fig. 10) with the Z as the axial direction, the second servo motor 351 of the power assembly 3 disposed on the left wing 12 drives the motor base 35 to deflect the propeller assembly 361 towards the machine head direction, and the second servo motor 351 of the power assembly 3 disposed on the right wing 13 drives the motor base 35 to deflect the propeller assembly 361 towards the machine tail direction, so that the machine body 1 deflects towards the left direction to guide the positive direction.

When the machine body 1 is lifted vertically, the engine 2 pushes the second linkage 21 by the first servo motor 22 to pivot the engine 2 to 45 ° (as shown in fig. 11), so that the machine body 1 is pushed forward, then, the engine 2 is pivoted to 0 ° (i.e. parallel to the flight status of the machine body 11), the upper and

lower hatches

14 and 15 are closed, at the same time, the propeller motors 36 of the two power assemblies 3 disposed on the left and

right wings

12 and 13 are stopped to operate, so that the hinges 362 are folded, the corner seats 34 are pivoted back to a position parallel to the tube 31, the servo seats 32 are pulled back into the tube 31 by the driving device 33, and the tail cover 310 is closed by the third servo motor 312 (please review fig. 3) driving the third linkage 313.

Thus, through the three axes formed by the engine 2 and the two power assemblies 3 arranged on the left wing 12 and the right wing 13, the thrust generated by the engine 2 can be matched with the operation or deflection of the propeller assemblies 361 of the two power assemblies 3, so as to adjust the vertical rising or falling of the machine body 1 in a balanced state, simplify the structure and parts of the whole machine body 1, reduce the weight of the machine body 1 and improve the stability of the flight.

The foregoing description is intended to be illustrative rather than limiting, and it will be appreciated by those skilled in the art that many modifications, variations or equivalents may be made without departing from the spirit and scope of the invention as defined in the appended claims.

Claims

1. An air-jet type vertical lifting pneumatic system is characterized by comprising:

two power components, which are respectively combined with the left wing and the right wing to make the engine and the two power components form an isosceles triangle configuration, and the power components comprise a pipe body with a tail cover and a driving device, a slide rail is arranged in the pipe body, a servo seat with a screw motor is sleeved on the slide rail, the servo seat is connected with the driving device so as to drive the servo seat to move on the slide rail by virtue of the driving device, the servo seat is pivoted with a corner seat, a first connecting rod group is assembled between a driving shaft of the screw motor and the corner seat so as to drive the connecting rod group to pivot the corner seat, a motor seat with a second servo motor is pivoted on the corner seat, the second servo motor is used for driving the motor seat to pivot, and a propeller motor is arranged at one end of the motor seat, which is not pivoted with the first connecting rod group, a propeller assembly is coupled to a driving shaft of the propeller motor so that the propeller assembly is driven by the propeller motor to unfold and rotate the blades of the propeller assembly;

the tube body is provided with a third servo motor, and a driving shaft of the third servo motor is connected with the tail cover through a third connecting rod group, so that the third connecting rod group is driven by the third servo motor to enable the tail cover to be pivoted on the tube body for opening; the tube body is provided with a tail fin, and an accommodating space for accommodating the third servo motor is formed in the tail fin.

2. The jet-type vertical lift pneumatic system of claim 1, wherein a second linkage is disposed between the first servomotor and the engine, such that the first servomotor drives the second linkage to pivot the engine.

3. The jet-type vertical lift pneumatic system of claim 1, wherein the engine is an engine.

4. The jet-type vertical lift pneumatic system of claim 1, wherein the engine is a fan propeller.

5. The jet-type vertical lift pneumatic system of claim 1, wherein the pivot angle of the corner block is 90 °.

6. The jet-type vertical lift pneumatic system of claim 1, wherein the motor base pivots within a range of ± 30 ° about the drive shaft of the second servomotor.

7. The jet-type pneumatic system for vertical lifting of claim 1, wherein the driving device comprises a further motor, two pulleys and a belt sleeved on the two pulleys, and a gap is formed in the tube, and a connecting member passing through the gap is fixedly disposed between the servo seat and the belt, so that when the stepping motor drives one of the pulleys to rotate, the belt drives the servo seat to move on the slide rail.

8. The jet-type vertical lift pneumatic system of claim 1, wherein a nozzle assembly is provided at the aft end of the body.