阅读说明：本技术 一种刚柔一体结构飞艇尾锥 (Rigid-flexible integrated airship tail cone ) 是由 陈务军 胡建辉 高成军 徐建东 杨钧 于 2020-07-10 设计创作，主要内容包括：本发明公开了一种刚柔一体结构飞艇尾锥,涉及浮空飞行器结构技术领域,包括内尾锥、外尾锥和囊体,其中,所述内尾锥由主承力环、斜支撑、径向支撑和节点连接而成倒圆锥形空间结构,所述外尾锥由纵撑杆、端承力环、加劲环和所述节点连接而成圆锥形空间结构,所述囊体为飞艇主气囊,由多个幅片热合焊接而成,飞艇内部刚柔一体结构与所述囊体通过所述内尾锥相连。本发明构造简单、集成方便、受力合理,实现了飞艇尾锥与刚柔一体结构的完整统一,具有重量轻、整体纵向和横向刚度大的优点,使飞艇尾部结构更便于设置矢量推力航向保持机构,从而承受纵向推力及俯仰和侧向控制力。(The invention discloses an airship tail cone with a rigid-flexible integrated structure, which relates to the technical field of floating aircraft structures and comprises an inner tail cone, an outer tail cone and an envelope, wherein the inner tail cone is of an inverted cone-shaped space structure formed by connecting main bearing rings, inclined supports, radial supports and nodes, the outer tail cone is of a cone-shaped space structure formed by connecting longitudinal support rods, end bearing rings, stiffening rings and the nodes, the envelope is an airship main envelope formed by heat-seal welding of a plurality of webs, and the rigid-flexible integrated structure in the airship is connected with the envelope through the inner tail cone. The airship tail structure is simple in structure, convenient to integrate and reasonable in stress, realizes the complete and unified structure of the airship tail cone and the rigid-flexible integrated structure, has the advantages of light weight and high overall longitudinal and transverse rigidity, and enables the airship tail structure to be more convenient to arrange the vector thrust course retaining mechanism so as to bear longitudinal thrust, pitching and lateral control forces.)

1. The utility model provides a just gentle integrative structure airship tail cone which characterized in that, includes interior tail cone, outer tail cone and utricule, wherein, interior tail cone is by main load ring, bearing diagonal, radial support and nodal connection form the inverted cone spatial structure, outer tail cone by indulge vaulting pole, end bearing ring, stiffening ring and the nodal connection forms the conical spatial structure, the utricule is airship main airbag, the inside just gentle integrative structure of airship with the utricule passes through interior tail cone links to each other.

2. The rigid-flexible integral airship tail cone of claim 1, wherein the inner tail cone and the outer tail cone are connected through the nodes, and the nodes are uniformly arranged on the main bearing ring.

3. The rigid-flexible integral structural airship tail cone of claim 2, wherein in the inner tail cone, the radial struts and the diagonal struts are connected with the main bearing ring through the nodes, the diagonal struts are arranged on the main bearing ring along every 120 degrees, the diagonal struts are connected with the main bearing ring and the inner equilateral triangular truss chords through the nodes, the radial struts are connected with the main bearing ring along every 120 degrees in a radial direction through the nodes, and the radial struts are connected with the rigid-flexible integral structure inside the airship.

4. The rigid-flexible integral structural airship tail cone of claim 3, wherein the diagonal braces comprise primary diagonal braces and secondary diagonal braces, the primary diagonal braces are arranged every 120 degrees along the primary bearing ring, and the secondary diagonal braces are arranged in a V shape on two sides of the primary diagonal braces.

5. The rigid-flexible integral airship tail cone of claim 4, wherein the diagonal braces and the internal regular triangle truss chords are connected by three-limb pipe through joints, main pipes of the three-limb pipe through joints are connected with the internal regular triangle truss chord main structure, and the three-limb pipes are respectively connected with the main diagonal braces and the secondary diagonal braces in a nested, gluing and curing manner.

6. The airship tail cone with a rigid-flexible integrated structure as claimed in claim 1, wherein in the outer tail cone, the longitudinal support rods are uniformly arranged in a circumferential direction and are spaced by 60 degrees, the longitudinal support rods are connected with the inner tail cone through the nodes, the longitudinal support rods are connected with the stiffening rings and the end bearing rings, and the end bearing rings are connected with an airship tail propelling mechanism.

7. The airship tail cone of rigid-flexible integrated structure as defined in claim 1, wherein the nodes are all formed by solidification and solidification, and the nodes are made of light alloy or composite material.

8. The rigid-flexible integral structure airship tail cone of claim 1, wherein the nodes connecting the diagonal braces and the main bearing ring are paired mating cross-shaped flange connection nodes.

9. The rigid-flexible integral structural airship tail cone of claim 1, wherein the outer tail cone is externally covered by a lightweight tension skin fairing.

10. The rigid-flexible airship tail cone of claim 1, wherein the envelope is formed by heat welding a plurality of webs, the webs being of a high strength lightweight multifunctional laminated film material.

Technical Field

The invention relates to the technical field of floating aircrafts, in particular to a tail cone of an airship with a rigid-flexible integrated structure.

Background

The airship is lighter than an air (LTA) aircraft, has low energy consumption and environmental friendliness, and once has gained great success in the field of aeronautics and technologies, the airship is active in each stage of human aviation development with its unique advantages, and in the 20 th century and the 80 th era, the novel airship has gained a long-term development along with the innovation of novel high-performance composite materials, solar energy and energy storage battery technologies, computer communication electronic technologies and the like.

Airships are often classified into hard airships, soft airships, and semi-hard airships according to a structural system. The hard airship is a Zeppelin typical system, the interior of the hard airship adopts a double-layer cylindrical grid structure form, the integral rigidity is large, the size is large, and the length of the hard airship reaches about 250 m; the soft airship is only provided with the air bag body, the overall structure is light, the rigidity is small, the controllability is poor, generally, the small airship adopts a soft structure, and the maximum length of the airship reaches 120 m; the semi-hard airship is designed into a structure system with high rigidity or high efficiency and light weight in the bearing part of the airship, so as to realize the overall light weight and reasonable stress. The main field of the innovation of the novel configuration airship is structural system innovation.

The airship tail cone is an important component in an airship structure, mainly bears pneumatic load and tail vector thrust, and has the functions of course control and the like. The tail of the blimp is difficult to be provided with a vector thrust course control mechanism. In the redundant structure of crossing of hard formula dirigible, the utricule is only partially sealed, and the tail cone is similar to the aircraft nose, can effectively pass power, but weight is great.

The patent of "rigid structure system of large airship" (cn201521080600.x) proposes an airship with rigid structure system, which comprises a prestressed structure system and a flexible outer capsule structure, wherein the prestressed structure system is composed of a central core shaft, prestressed stiffening rings and longitudinal connecting rods. However, this patent does not teach a tailcone and innovative tailcone design.

The inventor of the old military and the subsidiary power, and the like, "a large-scale semi-rigid structure airship" (CN201910275705.7), which adopts a structure that an integral keel and a pre-tension bag body of a tension-compression self-balancing system are integrated to cooperatively bear force, has the characteristics of integral shape preservation under the zero pressure of the bag body, integral rigidity under the low pressure and high bearing capacity, but does not provide the design of a tail cone and an innovative tail cone.

'A stratospheric airship with large-scale rigid-flexible integrated structure'

(CN201910958705.7) proposes a large scale rigid-flexible integral structure stratospheric airship, which comprises an outer capsule supported by a tensioned integral main keel, and a plurality of sealed inner capsules inside the outer capsule, but the patent does not give a tail cone and an innovative tail cone design.

Therefore, technical personnel in the field are dedicated to develop a rigid-flexible integrated airship tail cone which is simple in structure, convenient to integrate and reasonable in stress, the integrity and the unification of the rigid-flexible integrated airship tail cone and the rigid-flexible integrated structure are achieved, and the rigid-flexible integrated airship tail cone has the advantages of light weight and high overall longitudinal and transverse rigidity, so that a vector thrust course keeping mechanism can be conveniently arranged on the tail structure of the airship, and longitudinal thrust, pitching and lateral control forces can be borne.

Disclosure of Invention

In view of the above-mentioned defects of the prior art, the present invention is to provide an airship tail cone with a rigid-flexible integrated structure, which is light in weight and has high overall longitudinal and transverse rigidity, so that the airship tail structure is convenient to be provided with a vector thrust course maintaining mechanism to bear longitudinal thrust, pitch and lateral control forces.

In order to achieve the purpose, the airship tail cone with the rigid-flexible integrated structure is characterized by comprising an inner tail cone, an outer tail cone and an envelope, wherein the inner tail cone is of an inverted cone-shaped space structure formed by connecting main bearing rings, inclined supports, radial supports and nodes, the outer tail cone is of a cone-shaped space structure formed by connecting longitudinal support rods, end bearing rings, stiffening rings and the nodes, the envelope is a main airship envelope, and the rigid-flexible integrated structure in the airship is connected with the envelope through the inner tail cone.

Furthermore, the inner tail cone is connected with the outer tail cone through the nodes, and the nodes are uniformly arranged on the main bearing ring.

Further, in the inner tail cone, the radial support and the inclined support are connected with the main bearing ring through the node, the inclined support is arranged on the main bearing ring along every 120 degrees, the inclined support is connected with the main bearing ring and the inner regular triangle truss chord member through the node, the radial support is radially connected with the main bearing ring along every 120 degrees through the node, and the radial support is connected with the rigid-flexible integrated structure in the airship.

Furthermore, the inclined strut comprises a main inclined strut and a secondary inclined strut, the main inclined strut is arranged along the main force bearing ring at every 120 degrees, and the secondary inclined strut is arranged on two sides of the main inclined strut in a V shape.

Furthermore, a three-limb pipe intersecting joint is connected with the inclined support and the internal regular triangle truss chord member, a main pipe of the three-limb pipe intersecting joint is connected with the internal regular triangle truss chord member main structure, and the three-limb pipe is respectively nested, glued, cured and connected with the main inclined support and the secondary inclined support.

Further, in the outer tail cone of telling, indulge the vaulting pole and evenly set up along the hoop, the interval 60 degrees, indulge the vaulting pole pass through the node with interior tail cone is connected, indulge the vaulting pole with stiffening ring with the end bearing ring links to each other, the end bearing ring links to each other with airship tail propulsion mechanism.

Furthermore, all the nodes are solidified, solidified and formed, and the nodes are made of light alloy or composite materials.

Furthermore, the nodes for connecting the inclined supports and the main bearing ring are paired matched cross-shaped flange connection nodes.

Further, the outer tail cone is externally covered with a lightweight tension skin fairing.

Further, the bag body is formed by heat welding a plurality of webs, and the webs are made of high-strength light-weight multifunctional laminated film materials.

Compared with the prior art, the invention at least has the following beneficial technical effects:

the airship tail cone with the rigid-flexible integrated structure has the advantages of light weight and large overall longitudinal and transverse rigidity, and the tail structure of the airship is convenient to arrange a vector thrust course retaining mechanism so as to bear longitudinal thrust, pitching and lateral control forces.

The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, the features and the effects of the present invention.

Drawings

FIG. 1 is a side view of a rigid-flexible one-piece airship tail cone according to a preferred embodiment of the invention;

FIG. 2 is a perspective view of a rigid-flexible one-piece airship tail cone of a preferred embodiment of the invention;

FIG. 3 is a perspective view of the inner tail cone of the airship tail cone of a rigid-flexible unitary structure in accordance with a preferred embodiment of the invention;

FIG. 4 is a front elevation view of an inner tail cone of a rigid-flexible unitary structure airship tail cone according to a preferred embodiment of the invention;

FIG. 5 is a side view of the inner tail cone of the airship tail cone of a rigid-flexible unitary structure in accordance with a preferred embodiment of the invention;

FIG. 6 is a perspective view of the outboard tail cone of the rigid-flexible unitary structure airship tail cone of a preferred embodiment of the invention.

Wherein, 1-inner tail cone, 2-outer tail cone, 3-capsule, 101-main bearing ring, 102-inclined strut, 10201-main inclined strut, 10202-secondary inclined strut, 103-radial strut, 104-node, 10401-node, 10402-node, 10403-node, 10404-node, 10405-node, 10406-node, 201-longitudinal strut, 202-end bearing ring, 203-stiffening ring, 204-node, 20401-node, 20402-node, 20403-node.

Detailed Description

The technical contents of the preferred embodiments of the present invention will be more clearly and easily understood by referring to the drawings attached to the specification. The present invention may be embodied in many different forms of embodiments and the scope of the invention is not limited to the embodiments set forth herein.

In the drawings, structurally identical elements are represented by like reference numerals, and structurally or functionally similar elements are represented by like reference numerals throughout the several views. The size and thickness of each component shown in the drawings are arbitrarily illustrated, and the present invention is not limited to the size and thickness of each component. The thickness of the components may be exaggerated where appropriate in the figures to improve clarity.

As shown in fig. 1, the side view of the airship tail cone with a rigid-flexible integrated structure of the preferred embodiment of the invention comprises an inner tail cone 1, an outer tail cone 2 and a capsule 3. Interior tail cone 1 is connected airship utricule 3, and outer tail cone 2 is connected airship utricule 3 to interior tail cone 1 is connected, and three geometric configuration matches, and effective transmission tail pushes away load to the interior rigid and soft body structure.

As shown in fig. 2, the rigid-flexible integrated airship tail cone perspective view of one preferred embodiment of the invention comprises an inner tail cone 1 and an outer tail cone 2.

As shown in fig. 3, a perspective view of the inner tail cone of the airship tail cone of a rigid-flexible integrated structure according to a preferred embodiment of the invention; as shown in fig. 4, a front view of an inner tail cone of a rigid-flexible integrated airship tail cone according to a preferred embodiment of the invention; as shown in fig. 5, in a side view of an inner tail cone of a rigid-flexible integrated structure airship tail cone according to a preferred embodiment of the present invention, the inner tail cone 1 includes a main force-bearing ring 101, an oblique brace 102, a radial brace 103 and a node 104 connected to form an inverted cone-shaped spatial structure, and the inner tail cone 1 is symmetrical every 120 degrees and connects an inner rigid-flexible integrated structure and an airship envelope 3. The inner tail cone 1 and the rigid-flexible integrated structure are organically unified, the high-efficiency space triangular geometry required by geometric stability and the minimum number of components are achieved, light weight and high rigidity are achieved, and the manufacturing integration is simple and convenient.

The main bearing ring 101 is divided into two semicircles and is formed by nesting, connecting and curing in a node 10401; the main bearing ring 101 is symmetrically connected with radial supports 103 and inclined supports 102 at every 120 degrees, and nodes 10402 are uniformly arranged to connect with the longitudinal pull rods; the inclined strut 102 is arranged at every 120 degrees along the main bearing ring 101, the main inclined strut 10201 is arranged at every 120 degrees along the main bearing ring, the V-shaped structures at two sides are secondary inclined struts 10202, the main inclined strut 10201 is connected with the main bearing ring 101 through a node 10403, the main inclined strut 10201 is connected with an internal regular triangle truss chord through a node 10404, the secondary inclined strut 10202 is connected with the main bearing ring 101 through a node 10405, the secondary inclined strut 10202 is connected with the internal regular triangle truss chord through a node 10404, the radial strut 103 is radially connected with the main bearing ring 101 through a node 10403 at every 120 degrees, and the radial strut 103 is connected with the internal rigid-flexible integrated structure through a node 10406. The nodes are all solidified and solidified, and light alloy or composite materials can be adopted to keep the connection rigidity.

The size of the nested part in the node 10401 is closely matched with that of the main bearing ring 101, and the nested length meets the requirements of bending rigidity and emphasis. The number of the nodes 10402 is n, not less than 6, even, and is uniformly arranged along the main bearing ring 101 and is symmetrical about a coordinate axis; the node 10402 is sleeved on the main bearing ring 101, and is solidified and formed by normal temperature solidified glue after being positioned according to the design. 3 nodes 10403 are uniformly arranged along the main bearing ring 101 at an interval angle of 120 degrees and are connected with the main inclined supports 10201 and the radial supports 103; the node 10403 is sleeved on the main bearing ring 101, and is solidified and formed by normal temperature solidified glue after being positioned according to the design; the node 10403 is a pair of cross flange connection nodes, and connects the main bearing ring 101 and the main inclined support 10201 rod end in pair. Node 10404 is the three limbs pipe looks through joint, and the main pipe is connected inside main structure, and three limbs pipe nestification cementing solidification connects main bearing diagonal 10201 and secondary bearing diagonal 10202 respectively. 3 nodes 10405 are uniformly arranged along the main bearing ring 101 at an interval angle of 120 degrees, and are connected with V-shaped secondary inclined supports 10202 at an interval of 60 degrees with the nodes 10403; the node 10405 is sleeved on the main bearing ring 101, and is solidified and formed by normal temperature solidified glue after being positioned according to the design; the node 10405 is a pair of cross flange connection nodes, and the main bearing ring 101 and the rod ends of the V-shaped secondary inclined supports 10202 are connected in pair in a set; the nodes 10405 and 10403 are matched in pairs, and the nodes 10405 can effectively solve the assembly geometric interference between the main bearing ring 101 and the inclined support 102 and ensure rigid connection.

The main bearing ring 101, the diagonal braces 102 and the radial braces 103 are preferably high-strength light CFRP composite thin-wall circular tubes which are rolled by prepreg and cured at high temperature;

the node 104 is preferably made of light high-strength alloy, titanium alloy or magnesium-lithium-aluminum alloy by precision machining; or adopting composite materials, and integrally forming through three-dimensional layering or three-dimensional weaving of prepreg and high-temperature curing;

as shown in fig. 6, the perspective view of the outer tail cone of the airship tail cone with a rigid-flexible integrated structure according to a preferred embodiment of the invention comprises a longitudinal support rod 201, an end bearing ring 202, a stiffening ring 203 and a node 204 which are connected to form an inverted cone-shaped space structure, wherein the outer tail cone 2 is connected with an airship capsule 3 and is simultaneously connected with an inner tail cone 1 and a tail propulsion mechanism. The outer tail cone 2 has the efficient space triangular geometry required by geometric stability and the least number of components, realizes light weight and high rigidity, and is simple and convenient to manufacture and integrate.

Vertical stay 201 is connected with node 1403 and node 1405 of interior tail cone 1 through node 20401, and vertical stay 201 evenly sets up along the hoop, the interval 60 degrees. The outside of the inverted conical space structure can be covered with a lightweight tension skin for rectification, so that local vortex air resistance caused by tail propulsion is reduced. The stiffening ring 203 is arc-shaped, has equal arc length of 6 sections, and is connected with the longitudinal stay 201 through a node 20402. The stiffening ring 203 is a light high-strength composite material, and can be an L-shaped or round pipe. The end bearing ring 202 is a circular bearing platform, is connected with the longitudinal support rod 201 through a node 20403, and is connected with the tail propulsion mechanism through a special interface. The longitudinal support rod 201 is a CFRP thin-wall circular tube, and the end bearing ring 202 and the node 204 are of light composite materials or light alloy structures. After the inner tail cone 1 and the airship capsule 3 are integrated, the outer tail cone 2 is integrally assembled and connected with the inner tail cone 1 after being integrally integrated.

The size, material selection and performance parameters of the structural system can be determined by parameter design analysis aiming at the overall design target and technical index of the airship.

The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.