CN108791798B

CN108791798B - Aircraft variant nose cone based on 6-SPS space parallel mechanism

Info

Publication number: CN108791798B
Application number: CN201810509284.5A
Authority: CN
Inventors: 阎绍泽; 梁友鉴; 白航
Original assignee: Tsinghua University
Current assignee: Tsinghua University
Priority date: 2018-05-24
Filing date: 2018-05-24
Publication date: 2020-10-09
Anticipated expiration: 2038-05-24
Also published as: CN108791798A

Abstract

The aircraft variant nose cone based on the 6-SPS space parallel mechanism comprises a plurality of conical body sections which are sequentially arranged, the conical body sections are integrally arranged into a conical structure, the outer diameter of the tail part of the previous conical body section is equal to the inner diameter of the head part of the next conical body section, the inner wall of each conical body section is provided with a parallel mechanism for driving two adjacent conical body sections to extend and bend, the parallel mechanisms are arranged on the inner wall of each conical body section at intervals, the parallel mechanisms are not arranged in the first conical body section and the last conical body section, and the end parts of the first conical body section are provided with the cone heads.

Description

Aircraft variant nose cone based on 6-SPS space parallel mechanism

Technical Field

The invention relates to the technical field of aerospace aircrafts, in particular to an aircraft variant nose cone based on a 6-SPS space parallel mechanism.

Background

The aircraft can obtain the optimal aerodynamic configuration under different states by changing the shape of the aircraft during the flight process. While the current research on the variation of the aircraft mainly focuses on the variable wing aircraft, the research on the deformation of the aircraft nose cone is relatively less. The research on the aircraft variant nose cone has important significance for optimizing the aerodynamic characteristics of the aircraft.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention aims to provide the aircraft variant nose cone based on the 6-SPS space parallel mechanism, which can realize the deformation of the aircraft nose cone and has the advantages of compact structure, flexible deformation, high precision, large rigidity, strong bearing capacity, stable dynamic response and the like.

In order to achieve the purpose, the invention adopts the technical scheme that:

aircraft variant nose cone based on 6-SPS space parallel mechanism, including a plurality of cone segments 100 that set gradually, cone segments 100 are whole to be arranged into the toper structure, and the external diameter of preceding cone segment 100 afterbody equals the internal diameter of back cone segment 100 prelude, cone segment 100 inner wall set up drive adjacent two sections cone segments 100 and realize extension and crooked parallel mechanism 200, parallel mechanism 200 interval sets up on cone segment 100 inner wall, first section cone segment 100 and last section cone segment 100 in not set up parallel mechanism 200, first section cone segment 100 tip is provided with conical head 400.

The parallel mechanism 200 comprises a servo cylinder 210 and a spherical hinge 220, one end of the servo cylinder is fixed on the triangular support 120 at the tail part of the previous conical body section 100 through the spherical hinge 220, the other end of the servo cylinder is fixed on the triangular support 120 at the head part of the next conical body section 100 through the spherical hinge 220, the spherical hinges 220 are connected through the servo cylinder 210, and the triangular support 120 is arranged on the mounting platform 110 on the conical body section 100.

The parallel mechanism 200 is composed of six servo cylinders 210 with two ends connected by spherical hinges 220, two ends of each servo cylinder 210 are connected with the spherical hinges 220 by screw threads, and the spherical hinges 220 are fixedly connected on the triangular supports 120 of the mounting platform 110.

When the conical body sections 100 are in the horizontal position, the axes of the conical body sections 100 are overlapped.

The outer conical body section 100 of the parallel mechanism 200 is a flexible skin 300.

The number of the conical body sections 100 is 6, the diameters of the conical body sections are sequentially reduced, the diameters of the tails of the 6 conical body sections 100 are sequentially 1200 mm, 1168 mm, 1004 mm, 850 mm, 546 mm and 372 mm, and the wall thickness of the conical body section 100 is 20 mm.

The invention has the beneficial effects that:

the invention has the advantages of compact structure, flexible deformation, high precision, large rigidity, strong bearing capacity, stable dynamic response and the like.

Six servo cylinders 210 in each group of 6-SPS space parallel mechanisms 200 can keep a determined elongation, have strong bearing capacity and higher precision, and can ensure the stability of the deformed nose cone of the aircraft after deformation.

Drawings

Fig. 1 is a schematic structural diagram of a variant nose cone of an aircraft.

Fig. 2 is an initial state of the aircraft variant nose cone.

FIG. 3 illustrates the extended and flexed positions of the aircraft variant nose cone.

FIG. 4 is a schematic diagram of a 6-SPS space parallel mechanism of the aircraft variant nose cone.

Fig. 5 is a schematic view of the servo cylinder installation of the aircraft morphing nose cone.

FIG. 6 is a schematic view of a triangular support and ball joint of an aircraft morphing nose cone.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

As shown in FIG. 1, an aircraft variant nose cone 1 based on a 6-SPS space parallel mechanism according to an embodiment of the invention comprises a plurality of cone segments 100, two groups of 6-SPS space parallel mechanisms 200, two groups of flexible skins 300 and a cone head 400.

The plurality of conical body segments 100 are arranged along the front-back direction (the front-back direction is shown by an arrow A in fig. 1), and the mounting platform 110 for mounting the 6-SPS space parallel mechanism 200 is arranged at the tail part of the second conical body segment 100, the head part and the tail part of the fourth conical body segment 100 and the head part of the sixth conical body segment 100.

The 6-SPS space parallel mechanism 200 drives the two adjacent conical body sections 100 to realize stretching and bending deformation. In an initial state, the axes of the two conical body sections 100 are overlapped, the servo cylinder 210 is in the original length, and the flexible skin 300 is not deformed; in the process of only realizing the telescopic deformation, the axes of the two conical body sections 100 are overlapped, and the flexible skin 300 deforms to adapt to the deformed nose cone configuration; in the process of simultaneously realizing the stretching and bending deformation, the axes of the two conical body sections 100 are inclined at a certain angle, and the flexible skin 300 is deformed to adapt to the deformed nose cone configuration.

The bit 400 is disposed forward-most of the plurality of cone segments 100.

An aircraft variant nose cone 1 based on a 6-SPS space parallel mechanism according to a specific embodiment of the invention is described below with reference to the accompanying drawings.

As shown in fig. 1, in the initial state, a plurality of taper segments 100 are arranged in the front-rear direction, and the number of taper segments 100 is 6 and the diameters thereof are sequentially reduced. Specifically, the tail diameters of the 6 tapered body segments 100 are 1200 mm, 1168 mm, 1004 mm, 850 mm, 546 mm, 372 mm in this order, and the wall thickness of the tapered body segments 100 is 20 mm.

The third and fifth conic body segments 100 are comprised of a flexible skin 300 and a 6-SPS spatial parallel mechanism 200. The 6-SPS space parallel mechanism 200 in the third section is installed on the installation platforms 110 of the tail part and the head part of the second-section conical body, and the 6-SPS space parallel mechanism 200 in the fifth section is installed on the installation platforms 110 of the tail part and the head part of the sixth-section conical body.

The bit 400 is mounted at the forward end of the first segment cone segment 100.

As shown in fig. 2 and 3, fig. 2 shows an initial state of the aircraft variant nose cone, and fig. 3 shows an extended state and a bent state of the aircraft variant nose cone, when the nose cone is deformed, the plurality of servo cylinders 210 extend to different extents to drive the previous conical body segment 100 to move relative to the next conical body segment. Meanwhile, the deformation of each group of six servo cylinders 210 uniquely determines the telescopic bending deformation degree of the aircraft deformation nose cone 1, and the stability of the aircraft after deformation of the aircraft deformation nose cone 1 can be ensured by maintaining the deformation constant.

As shown in fig. 4 and 5, the 6-SPS space parallel mechanism 200 includes a plurality of servo cylinders 210, a ball joint 220. The servo cylinder 210 is connected with the ball joint 220 through thread fit, and the ball joint 220 is connected with the mounting platform 110 through the triangular support 120. The servo cylinder 210 can be replaced by other driving devices according to different working condition requirements.

As shown in fig. 6, the triangular support 120 is used to connect the ball joint 220 because the triangular support 120 changes the included angle between the servo cylinder 210 and the mounting surface on the mounting platform 110, so that the servo cylinder is always within the allowable movement range of the ball joint 220 in the deformation process.

The working principle of the invention is as follows:

when the aircraft variant nose cone based on the 6-SPS space parallel mechanism is subjected to telescopic deformation, the servo cylinders 210 in the 6-SPS space parallel mechanism 200 are expanded in a constant amplitude manner, so that two adjacent cone body sections 100 are driven to complete telescopic deformation; when the aircraft variant nose cone based on the 6-SPS space parallel mechanism is subjected to extension and bending deformation simultaneously, deformation amounts of the servo cylinders 210 are different, specifically, an upper two servo cylinders 210 (the vertical direction is shown by an arrow B in FIG. 2) are relatively large in extension amount, a middle two servo cylinders 210 are second in extension amount, and a lower two servo cylinders 210 are minimum in extension amount, so that extension and bending movement of the aircraft variant nose cone is realized. The servo cylinder 210 keeps the deformation constant, namely the stability of the corresponding configuration of the aircraft variant nose cone can be maintained.

Claims

1. The aircraft variant nose cone based on the 6-SPS space parallel mechanism is characterized by comprising a plurality of conical body sections (100) which are sequentially arranged, wherein the conical body sections (100) are integrally arranged into a conical structure, the outer diameter of the tail part of the previous conical body section (100) is equal to the inner diameter of the head part of the next conical body section (100), the inner wall of each conical body section (100) is provided with a parallel mechanism (200) for driving the two adjacent conical body sections (100) to realize extension and bending, the parallel mechanisms (200) are arranged on the inner wall of each conical body section (100) at intervals, the parallel mechanisms (200) are not arranged in the first conical body section (100) and the last conical body section (100), and the end part of the first conical body section (100) is provided with a nose cone (400);

the parallel mechanism (200) comprises a servo cylinder (210) and a spherical hinge (220), one end of the servo cylinder is fixed on a triangular support (120) at the tail part of the front section of the conical body section (100) through the spherical hinge (220), the other end of the servo cylinder is fixed on the triangular support (120) at the head part of the rear section of the conical body section (100) through the spherical hinge (220), the spherical hinges (220) are connected through the servo cylinder (210), and the triangular support (120) is arranged on a mounting platform (110) on the conical body section (100).

2. The aircraft morphing nose cone based on the 6-SPS space parallel mechanism according to claim 1, wherein the parallel mechanism (200) is composed of six servo cylinders (210) with two ends connected by spherical hinges (220), two ends of each servo cylinder (210) are connected with the spherical hinges (220) by screw threads, and the spherical hinges (220) are fixedly connected on the triangular support (120) of the mounting platform (110).

3. The 6-SPS space parallel mechanism-based aircraft morphing nose cone of claim 1, wherein axes of the conical body sections (100) are coincident when the conical body sections (100) are in a horizontal position.

4. The 6-SPS space parallel mechanism-based aircraft morphing nose cone of claim 1, wherein the outside conical body segment (100) of the parallel mechanism (200) is a flexible skin (300).

5. The 6-SPS space parallel mechanism-based aircraft variant nose cone of claim 1, wherein the number of the conical body segments (100) is 6, the diameters of the conical body segments are reduced in sequence, the diameters of the tail parts of the 6 conical body segments (100) are 1200 mm, 1168 mm, 1004 mm, 850 mm, 546 mm and 372 mm in sequence, and the wall thickness of the conical body segments 100 is 20 mm.