CN-122009467-A - Aircraft variant nose cone based on compliant deformation structure

CN122009467ACN 122009467 ACN122009467 ACN 122009467ACN-122009467-A

Abstract

The application belongs to the technical field of aircrafts, and provides an aircraft variant nose cone based on a flexible deformation structure, which comprises a cone head, a deformation structure and an undeformed cabin section, wherein the cone head is arranged on a movable platform in the deformation structure, a static platform in the deformation structure is arranged at the tail end of the undeformed cabin section, the cone head can realize single-degree-of-freedom stretching and two-degree-of-freedom bending movement under the driving of the deformation structure, and the movable platform and the static platform are symmetrically distributed about a middle plane, so that the outer surface of the deformation structure can keep a continuous smooth appearance. The application can realize large-scale controllable deformation of single-degree-of-freedom expansion and two-degree-of-freedom bending, ensures that the outer skin is supported by the constraint of the framework mechanism and the elastic support body in the deformation process, maintains continuous and smooth pneumatic appearance, and effectively improves the pneumatic performance and adaptability of the aircraft in different flight states.

Inventors

TAO JIANGUO
WANG YUE
WU DEZHI
XIAO HONG
YANG GUANG
GUO HONGWEI

Assignees

哈尔滨工业大学

Dates

Publication Date: 20260512
Application Date: 20260407

Claims (10)

1. The aircraft variant nose cone based on the compliant deformation structure is characterized by comprising a cone head, a deformation structure and a non-deformation cabin section, wherein the cone head is arranged on a movable platform in the deformation structure, a static platform in the deformation structure is arranged at the tail end of the non-deformation cabin section, the cone head can realize single-degree-of-freedom stretching and two-degree-of-freedom bending movement under the driving of the deformation structure, and the movable platform and the static platform are symmetrically distributed about a middle plane, so that the outer surface of the deformation structure can keep a continuous smooth appearance.
2. The aircraft variant nose cone based on a compliant deformation structure as claimed in claim 1, wherein the deformation structure comprises an elastic support body and a skeleton mechanism, and two sides of the elastic support body are respectively fixedly connected with a movable platform and a static platform of the skeleton mechanism and are used for supporting the flexible skin and synchronously and smoothly deforming along with the skeleton mechanism.
3. The aircraft variant nose cone based on a compliant deformation structure according to claim 2, wherein the elastic support body is a spiral elastic structure.
4. The aircraft variant nose cone based on a compliant deformation structure according to claim 2, wherein each skeleton mechanism comprises a synchronous component and mechanism modules, each mechanism module is provided with a movable platform and a static platform, two adjacent mechanism modules share one platform, an elastic support body is connected with the movable platform and the static platform, and the synchronous component is connected with the two adjacent mechanism modules and is used for realizing the consistent movement of the two adjacent mechanism modules.
5. The aircraft variant nose cone based on a compliant deformation structure according to claim 3, wherein the mechanism module comprises a static platform, a dynamic platform and at least three branched chains connected between the dynamic platform and the dynamic platform, each branched chain comprises a first connecting rod, a second connecting rod, a third connecting rod and a fourth connecting rod, the first connecting rod is connected with the static platform through a first revolute pair, the second connecting rod is connected with the first connecting rod through a second revolute pair, the third connecting rod is connected with the second connecting rod through a third revolute pair, the fourth connecting rod is connected with the third connecting rod through a fourth revolute pair, and the dynamic platform is connected with the fourth connecting rod through a fifth revolute pair.
6. The aircraft variant nose cone based on a compliant deformation structure according to claim 5, wherein in an initial state in which the static platform is parallel to the moving platform, the axis of the first revolute pair, the axis of the third revolute pair and the axis of the fifth revolute pair are parallel to each other, and the axis of the second revolute pair and the axis of the fourth revolute pair intersect at the axis of the third revolute pair.
7. The aircraft variant nose cone based on the compliant deformation structure according to claim 5, wherein in the same mechanism module, the axes of the second revolute pair, the third revolute pair and the fourth revolute pair of each branched chain intersect at one point, and a plane formed by all the intersection points is a middle plane of the mechanism module, and the moving platform and the static platform of the mechanism module are symmetrically distributed about the middle plane.
8. The aircraft variant nose cone based on the compliant deformation structure according to claim 5, wherein the axis of the first revolute pair is parallel to the plane of the static platform, the axis of the fifth revolute pair is parallel to the plane of the moving platform, and when the moving platform is parallel to the static platform, the axis of the first revolute pair, the axis of the third revolute pair and the axis of the fifth revolute pair are parallel to each other, and when the moving platform generates rotational motion, the axis of the first revolute pair intersects with the axis of the fifth revolute pair.
9. The aircraft variant nose cone based on compliant deformation structure according to claim 5, wherein the synchronization assembly comprises four groups of synchronization mechanisms with the same structure, the single synchronization mechanism comprises a lower synchronization rod, a synchronization slider, a synchronization base and an upper synchronization rod, the lower synchronization rod and the upper synchronization rod are identical in structure, the upper end of the lower synchronization rod is rotationally connected with the synchronization slider, the lower end of the upper synchronization rod is rotationally connected with the synchronization slider, the lower synchronization rod is rotationally connected with a fourth connecting rod of a mechanism module at the rear part of two adjacent mechanism modules, the upper synchronization rod is rotationally connected with a first connecting rod of a mechanism module at the front part of the two adjacent mechanism modules, the synchronization slider is connected with the synchronization base and can linearly move on the synchronization base, and the synchronization base is mounted on the shared platform.
10. The aircraft variant nose cone based on a compliant deformation structure according to claim 5, wherein in an initial state in which the static platform is parallel to the dynamic platform, an acute angle formed by the intersection of the axis of the second revolute pair and the axis of the fourth revolute pair is arranged outwards.

Description

Aircraft variant nose cone based on compliant deformation structure Technical Field The invention belongs to the technical field of aircrafts, relates to an aircraft nose cone, and in particular relates to an aircraft variant nose cone based on a compliant deformation structure. Background The aircraft variant technology can adjust the aerodynamic shape of the aircraft in real time according to different flight states and task requirements, so that the optimal aerodynamic performance is maintained in the whole flight envelope, and the aircraft variant technology is an important direction for the development of future high-speed aircraft and aerospace shuttle aircraft. Currently, related research and applications focus mainly on continuous or discrete deformation of wings, control surfaces, etc. In contrast, intelligent deformation studies on the aircraft precursors are relatively few, and active adjustment of nose cone profile has key effects on reducing aerodynamic drag, improving aerodynamic efficiency, and improving flight stability and maneuverability. The prior design of the variant nose cone is mainly focused on mechanical mechanisms adopted for realizing basic movement functions such as cone expansion and contraction, bending and the like. However, these designs typically only focus on the motion implementation of the drive mechanism itself, and ignore a critical engineering issue of how the skin covering the mechanism deforms over a wide range with a continuous, smooth deformation. Without effective support and control of skin deformation, wrinkles and depressions are inevitably generated on the outer surface of the aircraft, namely stress concentration is generated on the deformed structure, aerodynamic appearance is damaged, local flow separation and resistance surge are caused, and the original purpose of pursuing optimal aerodynamic performance of the variant aircraft is overcome. Disclosure of Invention The invention provides the aircraft variant nose cone based on the compliant deformation structure, which can realize large-scale controllable deformation of single-degree-of-freedom expansion and two-degree-of-freedom bending, ensure that the external skin is maintained to be continuous and smooth in the pneumatic shape under the restraint of the framework mechanism and the support of the elastic support body in the deformation process, and effectively improve the pneumatic performance and adaptability of the aircraft in different flight states. The utility model provides an aircraft variant nose cone based on flexible deformation structure contains conical head, deformation structure and non-deformation cabin section, the conical head is installed in the movable platform in the deformation structure, and quiet platform is installed in the end of non-deformation cabin section in the deformation structure, the conical head can realize the flexible motion of single degree of freedom and two degrees of freedom bending under the drive of deformation structure, movable platform and quiet platform are about the middle plane symmetric distribution for the surface of deformation structure can keep continuous smooth appearance. The deformation structure comprises an elastic support body and a framework mechanism, wherein two sides of the elastic support body are fixedly connected with a movable platform and a static platform of the framework mechanism respectively and are used for supporting the flexible skin and synchronously and smoothly deforming along with the framework mechanism. Further, each framework mechanism comprises a synchronous assembly and mechanism modules, each mechanism module is provided with a movable platform and a static platform, two adjacent mechanism modules share one platform, an elastic support body is connected with the movable platform and the static platform, and the synchronous assembly is connected with the two adjacent mechanism modules and used for achieving the consistent movement of the adjacent mechanism modules. Further, the mechanism module comprises a static platform, a movable platform and at least three branched chains connected between the static platform and the movable platform, wherein each branched chain comprises a first connecting rod, a second connecting rod, a third connecting rod and a fourth connecting rod, the first connecting rod is connected with the static platform through a first revolute pair, the second connecting rod is connected with the first connecting rod through a second revolute pair, the third connecting rod is connected with the second connecting rod through a third revolute pair, the fourth connecting rod is connected with the third connecting rod through a fourth revolute pair, and the movable platform is connected with the fourth connecting rod through a fifth revolute pair. Further, in the initial state that the static platform is parallel to the movable platform, the axis of the first revolute pair, the axis of the third revolute