A general-purpose small aircraft thrust vector mechanism convenient to disassemble and assemble

Abstract

The application discloses a small aircraft thrust vector mechanism, comprising a rudder, a crank, a connecting rod, a vector nozzle and a suspension support; the rudder is fixedly installed outside an engine; the rudder is connected to the vector nozzle through the crank and the connecting rod in sequence; the suspension support comprises a ring part and a supporting leg extending from the ring part, the ring part is fixedly installed on the bottom end face of the engine, the supporting leg is used for connecting the vector nozzle, a connecting point of the supporting leg and the suspension vector nozzle is recorded as a suspension point, and the vector nozzle swings around the suspension point under the driving of the rudder. The application realizes the control of the flight direction, can realize the swing of the engine thrust vector within ±20 degrees, occupies a small space for mechanism operation, has high transmission efficiency, and is suitable for small aircraft products with limited internal space.

Description

TECHNICAL FIELD

[0001] The present application relates to a universal small aircraft thrust vector mechanism convenient to disassemble, in particular to a vector thrust mechanism suitable for small turbojet engines, mainly used for thrust direction control of small aircraft such as single soldier aircraft and unmanned aerial vehicles, and belongs to the technical field of thrust vector mechanisms. BACKGROUND

[0002] In recent years, single-person aircraft technology has become increasingly mature, with the characteristics of small target, fast response, strong maneuverability, and strong environmental adaptability, which has obvious advantages over traditional land, water, and air transport equipment in terms of ultra-short-range rapid delivery across complex land and sea areas. As the power system of single-person aircraft, the variable thrust turbojet engine is the core component of the entire system.

[0003] Current aircraft engine thrust vector control methods mainly use swing-jet engines and three-degree-of-freedom turbulence tubes. The above-mentioned engine thrust vector system is mainly aimed at large turbojet engines, and the mechanism is complex and occupies a large space. For two-degree-of-freedom engines of small turbojet engines, it is necessary to jointly develop engines, which is difficult to achieve compatibility with various small turbojet engines. The mechanism is large in size, the system is complex, the maintenance cost is high, and it is difficult to meet the compact design requirements of small portable flight boards in terms of weight and size. SUMMARY

[0004] The purpose of the present application is to overcome the above-mentioned defects, and to provide a universal small aircraft thrust vector mechanism convenient to disassemble, which overcomes the technical problems of large size and complex system of the existing thrust vector mechanism. The present application realizes the control of flight direction, the mechanism occupies a small space for actuation, has high transmission efficiency, and is compatible with various small turbojet engines, suitable for small aircraft products with limited internal space.

[0005] To achieve the above-mentioned application purpose, the present application provides the following technical scheme:

[0006] A universal small aircraft thrust vector mechanism convenient to disassemble, comprising a rudder, a crank, a connecting rod, a vector nozzle, and a suspension bracket;

[0007] The rudder is fixedly installed on the outside of the engine;

[0008] The rudder is connected to the vector nozzle in sequence through the crank and the connecting rod;

[0009] The suspension bracket comprises a ring-shaped part and a leg extending from the ring-shaped part, the ring-shaped part is fixedly installed on the bottom end face of the engine, and the leg is used to connect the vector nozzle. The connection point of the leg and the suspension vector nozzle is called the suspension point, and the vector nozzle swings around the suspension point under the drive of the rudder.

[0010] Furthermore, the annular part of the suspension bracket is formed by two arc-shaped structures overlapping in a circumferential direction;

[0011] Each segment of the curved structure extends out a support leg;

[0012] The two support legs are arranged symmetrically along the ring-shaped section.

[0013] Furthermore, the vector nozzle has a streamlined structure with an inward-curving nozzle opening.

[0014] Furthermore, the suspension bracket also includes stud roller bearings;

[0015] The stud roller bearing is installed at the suspension point of the vector nozzle;

[0016] The support leg is provided with a lug hole, the outer ring of the stud roller bearing is installed in the lug hole, the outer ring of the stud roller bearing fits against the wall of the lug hole, and the inner ring stud of the stud roller bearing is connected to the suspension bracket by a self-locking nut.

[0017] Furthermore, the suspension bracket and engine nozzle are fixedly installed on the engine nozzle interface provided on the bottom end face of the engine, and the vector nozzle is sleeved on the outside of the lower end of the engine nozzle.

[0018] Furthermore, the servo is fixedly mounted to the outside of the engine via a servo bracket;

[0019] The upper and lower ends of the servo bracket are fixed to the outside of the engine using engine clamps and auxiliary clamps, respectively.

[0020] The engine clamp is installed in the groove on the outer surface of the engine.

[0021] Furthermore, the crankshaft and servo output shaft are connected by flange, keyway, or pin.

[0022] Furthermore, the connecting rod is connected to the crank and the vector nozzle via a rotating shaft;

[0023] A spherical bearing is installed at the pivot point used to connect the connecting rod and the vector nozzle.

[0024] Furthermore, the suspension bracket, vector nozzle, and spherical bearing are made of titanium alloy or high-temperature alloy, wherein the high-temperature alloy is an alloy with an operating temperature of 500°C or higher.

[0025] The crank and connecting rod are made of stainless steel.

[0026] Furthermore, when the servo rotates within a range of ±30°, the vector nozzle oscillates within a range of ±20°.

[0027] Compared with the prior art, the present invention has the following advantages:

[0028] (1) The application creatively provides a general-purpose small aircraft thrust vector mechanism which is convenient to disassemble and assemble, and provides the vertical take-off and landing single aircraft with the vector thrust for the first time in China, and realizes the control of the flight direction;

[0029] (2) The application can realize the swing of the engine thrust vector within ±20°, and effectively improves the control precision and control efficiency;

[0030] (3) The weight of the small aircraft thrust vector mechanism is only 1-1.2 kg, the structure is compact, the mechanism occupies a small space for doing action, the transmission efficiency is high, and the small aircraft product with limited internal space is suitable. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 It is a schematic diagram of the transmission theory of the thrust vector mechanism of the application;

[0032] Figure 2 (a), (b) and (c) are different swing schematic diagrams of the vector nozzle of the application;

[0033] Figure 3 It is a schematic diagram of the suspension bracket of the application;

[0034] Figure 4 It is a schematic diagram of the crank of the application,

[0035] Figure 5 It is a schematic diagram of the vector nozzle of the application;

[0036] Figure 6 It is a schematic diagram of the connecting rod of the application;

[0037] Figure 7 It is a schematic diagram of the overall thrust vector mechanism of the application;

[0038] Figure 8 It is a schematic diagram of the thrust vector mechanism of the application installed on the engine;

[0039] Figure 9 It is a schematic diagram of the slide plate honeycomb frame of the aircraft of the application;

[0040] Figure 10 It is a bottom view of the aircraft of the application after the thrust vector mechanism is installed on the aircraft;

[0041] In the figure, 1 is a rudder, 2 is a crank, 3 is a connecting rod, 4 is a vector nozzle, 5 is an auxiliary band, 6 is a suspension point, 7 is a rudder support, 8 is a third supporting ear of an engine clamp, 9 is a rotating shaft, 10 is a joint bearing, 11 is a second supporting ear of an engine clamp, 12 is an auxiliary band, 13 is a first supporting ear of an engine clamp, and 14 is a stud roller bearing. DETAILED DESCRIPTION

[0042] The features and advantages of the present application will become more apparent from the detailed description set forth below.

[0043] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Unless specifically indicated otherwise, the description herein is not intended to be construed as a description of prior art.

[0044] The flying skateboard mainly aims to realize single-person short-time flight, and can realize single-person independent vertical take-off and low-altitude short-distance flight by virtue of the small and portable characteristics. As the main power source, five turbojet engines are installed at the center of the aircraft in an X-shaped layout. In order to realize direction and stability control during flight, in addition to the central engine, the four engines around are all installed with a vector nozzle mechanism to realize thrust direction adjustment.

[0045] The present application mainly solves the problem of thrust direction control of small aeroengines, adopts a general standard interface, and is compatible with most small turbojet engines at home and abroad. By adding a vector nozzle mechanism, the single-direction thrust of the turbojet engine is converted into a thrust that can be changed in direction within a one-dimensional plane at a small angle according to the control requirements. The mechanism needs to work for a long time in high temperature, has high transmission reliability, can work independently without the aid of other systems, and has small thrust loss. The mechanism has simple functions, compact structure and light weight.

[0046] The present application adopts the scheme of adding a rudder and a vector nozzle mechanism at the end of the nozzle of the turbojet engine, and fixes the rudder to the side of the engine by means of the original general installation interface (i.e. the groove provided on the outer surface of the engine) and the original nozzle interface (i.e. the engine nozzle interface provided on the bottom end surface of the engine), and converts the output rotational angular displacement of the rudder into the rotational angular displacement of the vector nozzle through a crank and connecting rod mechanism. The vector nozzle is designed according to the flow field of the engine and the swing angle requirement, and the material is selected from high-temperature alloy or titanium alloy. The connecting rod, rocker arm and other vector mechanisms are generally made of stainless steel.

[0047] Specifically, as shown in Figure 7 and Figure 8 , the small aircraft thrust vector mechanism of the present application comprises a rudder 1, a crank 2, a connecting rod 3, a vector nozzle 4 and a suspension bracket, which is driven by the rudder 1 to ensure that the vector nozzle 4 swings within a range of 20°. In order to adapt to the selection of the rudder and ensure the corresponding speed of the rudder, the transmission scheme of the mechanism considers the swing angle range of the control rudder output. At the same time, in the mechanism scheme, the engine is arranged at a position away from the high-temperature gas flow of the engine nozzle, and the motion envelope range of the control mechanism is controlled, thereby saving the space of the flying skateboard.

[0048] After multiple optimizations, as shown in Figure 1 and Figure 2 , the small aircraft thrust vector mechanism of the present application comprises a rudder 1, a crank 2, a connecting rod 3, a vector nozzle 4 and a suspension bracket, which is driven by the rudder 1 to ensure that the vector nozzle 4 swings within a range of 20°. In order to adapt to the selection of the rudder and ensure the corresponding speed of the rudder, the transmission scheme of the mechanism considers the swing angle range of the control rudder output. At the same time, in the mechanism scheme, the engine is arranged at a position away from the high-temperature gas flow of the engine nozzle, and the motion envelope range of the control mechanism is controlled, thereby saving the space of the flying skateboard.In a typical scheme: the vector nozzle axis is 60mm, the crank length is 40mm, and the connecting rod length is 119.2mm. When the vector nozzle rotates at -20°, 0°, and +20°, the corresponding positions of the rudder are -31°, 0°, and +26.2°.

[0049] As Figure 3 The suspension bracket is made of high-temperature alloy and is divided into left and right sections. The two sections are circumferentially overlapped and are fixed to the bottom end surface of the engine by screws provided on the engine nozzle. The two sections of the bracket extend out with feet for suspending the vector nozzle 4. The sectional design of the suspension bracket is compatible with various sizes of engine tail nozzles. Meanwhile, the vector nozzle can be directly installed or removed without damaging the engine body, so that the state switching of the finished engine can be realized. The vector mechanism can be added to the vector engine, or the vector mechanism can be removed to become a normal engine. The engine manufacturer does not need to customize or modify the engine. This design makes the state switching of the vector thrust more convenient.

[0050] The vector nozzle 4 has a streamlined design and a converging nozzle. The nozzle can freely swing around the suspension point. The flow field analysis simulation of the nozzle flow passage shows that the thrust loss is less than 15%. Two suspension points 6 are symmetrically arranged, and a roller bearing 14 is installed on the suspension points. The roller bearing is a key structure for the rotation of the nozzle. It has a small size and a short axial length, which can ensure the installation accuracy of the nozzle and reduce the friction of the nozzle rotation. The outer ring of the roller bearing is installed in the ears on both sides of the vector nozzle 4. The outer ring is attached to the ears, and the inner ring studs are connected to the suspension bracket through self-locking nuts. The bearing is installed at the suspension point 6 of the vector nozzle, and the stud end penetrates through the ear hole of the suspension bracket and is locked by a self-locking nut.

[0051] The vector nozzle 4 is made of high-temperature alloy material. When the engine is used for a short or long time or in a small thrust state, titanium alloy TA15 material can also be used. The nozzle body is machined after 3D printing. For mass production, sheet metal welding can also be considered. During manufacturing, attention should be paid to the deformation of the thin-walled nozzle.

[0052] The rudder 1 is connected to the engine through a rudder bracket 7. The rudder bracket 7 is clamped and fixed by the third ear 8 of the engine clamp 12. The bottom is locked and fixed by the auxiliary clamp 5. The engine clamp 12 is provided with a third ear 8 of the engine clamp, a second ear 11 of the engine clamp, and a first ear 13 of the engine clamp. The upper plane of the ears is the mounting interface of the aircraft thrust vector mechanism and the aircraft. Specifically, there are five engines. The central engine is connected to the slide body honeycomb frame through four horizontal ears. The surrounding four vector engines are connected to the slide honeycomb frame in the aircraft through three horizontal ears, i.e. the third ear 8 of the engine clamp, the second ear 11 of the engine clamp, and the first ear 13 of the engine clamp. Figure 9 and Figure 10The steering engine output angle is transmitted to the vector nozzle 4 through the crank 2 and the connecting rod 3. The interface between the crank 2 and the steering engine 1 adopts a flange connection, and can also be adjusted to a key groove, pin and other connection forms according to the output shaft form of the steering engine 1.

[0053] The steering engine support 7 is connected with the engine through the engine clamp 12 and the auxiliary band 5, and can be fixed through the two clamps. The engine clamp 12 is directly buckled in the annular groove of the engine, and is clamped by tightening the screw on the lug. The annular groove of the engine is actually a general interface possessed by all small turbojet engines, so the mechanism of the application can adapt to most engines on the market, and does not need to customize a special interface for the engine.

[0054] As Figure 4 , Figure 5 , Figure 6 The connecting rod 3, the crank 2 and the connecting rod 3 and the vector nozzle 4 are all connected through the rotating shaft 9. In order to eliminate installation deviation and reduce the friction force of the moving parts of the mechanism, the joint bearing 10 is installed at the rotating shaft of the connecting rod 3 and the vector nozzle 4.

[0055] In the mechanism, the working temperature of the stud roller bearing of the suspension support, the auxiliary band, the vector nozzle, the joint bearing and the suspension point is above 500 DEG C, and high-temperature-resistant materials such as titanium alloy or high-temperature alloy should be used. The long-time working temperature of the remaining parts does not exceed 200 DEG C, and stainless steel or light metal materials can be used.

[0056] In order to make the portable flight skateboard have good flight stability and maneuverability, four micro turbojet engines are additionally provided with thrust vector nozzles, and the turbojet engine at the center position is not provided with a vector nozzle. The vector nozzle is designed in a high-temperature state, and involves temperature field simulation, mechanism dynamic characteristic analysis and other problems.

[0057] The application has been described in detail in combination with specific embodiments and exemplary examples, but these descriptions cannot be understood as limitations of the application. Those skilled in the art understand that the technical solutions and embodiments of the application can be variously replaced, modified or improved without departing from the spirit and scope of the application, and these all fall within the scope of the application. The protection scope of the application is subject to the appended claims.

[0058] The contents not described in detail in the specification of the application are the known technology of those skilled in the art.

Claims

1. A general-purpose small aircraft thrust vectoring mechanism that is easy to disassemble, characterized by, The application relates to a rudder mechanism (1), a crank (2), a connecting rod (3), a vector nozzle (4) and a suspension support. The rudder mechanism (1) is fixedly installed on the outer side of an engine. The rudder mechanism (1) is connected to the vector nozzle (4) through the crank (2) and the connecting rod (3) in sequence. The suspension support comprises a ring-shaped part and a supporting leg extending from the ring-shaped part, the ring-shaped part is fixedly installed on the bottom end surface of the engine, the supporting leg is used for connecting the vector nozzle (4), the connecting point of the supporting leg and the vector nozzle (4) is recorded as a suspension point, and the vector nozzle (4) swings around the suspension point under the driving of the rudder mechanism (1). The ring-shaped part of the suspension support is formed by two arc-shaped structures which are ring-coupled. Each arc-shaped structure extends one supporting leg, and the two supporting legs are symmetrically arranged along the ring-shaped part. The vector nozzle (4) is of a streamline structure and has a converging nozzle. The suspension support further comprises a stud roller bearing, the stud roller bearing is installed at the suspension point of the vector nozzle (4), the supporting leg is provided with a lug hole, the outer ring of the stud roller bearing is installed in the lug hole, the outer ring of the stud roller bearing is attached to the wall of the lug hole, and the inner ring stud of the stud roller bearing is connected with the suspension support through a self-locking nut. The suspension support and the engine nozzle are fixedly installed on the engine nozzle interface arranged on the bottom end surface of the engine, and the vector nozzle (4) is sleeved on the outer portion of the lower end of the engine nozzle. The rudder mechanism (1) is fixedly installed on the outer side of the engine through a rudder mechanism support (7), the upper end and the lower end of the rudder mechanism support (7) are fixed to the outer side of the engine by using an engine clamp (12) and an auxiliary clamp (5) respectively, and the engine clamp (12) is installed in the groove arranged on the outer surface of the engine. The crank (2) and the output shaft of the rudder mechanism (1) are connected through flange connection, key groove connection or pin connection.

2. The universal small aircraft thrust vector mechanism of easy assembly and disassembly according to claim 1, characterized in that, The connecting rod (3) and the crank (2) and the connecting rod (3) and the vector nozzle (4) are connected through a rotating shaft.

3. The universal small aircraft thrust vector mechanism of easy assembly and disassembly according to claim 1, characterized in that, The rotating shaft for connecting the connecting rod (3) and the vector nozzle (4) is provided with a joint bearing. The suspension support, the vector nozzle (4) and the joint bearing are made of titanium alloy or high-temperature alloy, and the high-temperature alloy is an alloy with a working temperature of 500 DEG C or above.

4. The universal small aircraft thrust vector mechanism of easy assembly and disassembly according to claim 3, characterized in that, The crank (2) and the connecting rod (3) are made of stainless steel. When the rudder mechanism (1) rotates within the range of +30 DEG, the vector nozzle (4) swings within the range of +20 DEG.

5. The universal small aircraft thrust vector mechanism of easy assembly and disassembly according to claim 1, characterized in that, ​

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