Search

CN-122009466-A - Aircraft nose cone based on deformation of connecting rod mechanism

CN122009466ACN 122009466 ACN122009466 ACN 122009466ACN-122009466-A

Abstract

The invention provides an aircraft nose cone based on deformation of a connecting rod mechanism, which comprises three sections of tapered nose cone shells with gradually reduced diameters, a bending mechanism, a telescopic connecting rod mechanism and a locking mechanism which are sequentially arranged, wherein the first section of nose cone shell is connected with a rod piece of the bending mechanism, a group of lower hinge bases are respectively arranged on the first section of nose cone shell and the second section of nose cone shell, a group of upper hinge bases are respectively arranged on the second section of nose cone shell and the third section of nose cone shell, the first section of nose cone shell and the third section of nose cone shell are respectively welded with the lower parts and the upper part of the two groups of telescopic connecting rod mechanisms, the second section of nose cone shell is simultaneously welded with the upper parts and the lower part of the two groups of telescopic connecting rod mechanisms, the locking mechanism is connected to the hinge bases as a driven branched chain, the telescopic connecting rod mechanism and the bending mechanism are driven by a driving assembly, and the nose cone shell is further driven to deform by changing the length and direction of the connecting rod mechanism. The invention can realize stepwise deformation of expansion and integral bending deformation, and has the advantages of large deformation amount, simple driving, locking, integral rigidity improvement and the like.

Inventors

  • GU YONGXIA
  • KE SHIHAO
  • Xing Wenxu
  • HAN JIZE
  • CHEN YUHANG

Assignees

  • 北京工商大学

Dates

Publication Date
20260512
Application Date
20260305

Claims (9)

  1. 1. An aircraft nose cone based on linkage deformation, comprising: Three sections of cone-shaped nose cone shells (100) are sequentially arranged; a bending mechanism (200), the bending mechanism (200) being connected to the first nose cone housing (100); The telescopic link mechanism (300) is provided with two groups, and the two groups of telescopic link mechanisms (300) are respectively connected between the adjacent nose cone shells (100); The locking mechanism (400) is provided with four groups, and the four groups of locking mechanisms (400) are respectively connected between the adjacent nose cone shells (100); Wherein, the first section and the second section of the head cone shell (100) are respectively provided with a group of lower hinge bases (402), and the second section and the third section of the head cone shell (100) are respectively provided with a group of upper hinge bases (401); the first section and the third section of the head cone shell (100) are respectively welded with the lower connecting rod bracket (304) and the upper connecting rod bracket (301) of the two groups of telescopic connecting rod mechanisms (300), and the second section of the head cone shell (100) is simultaneously welded with the upper connecting rod bracket (301) and the lower connecting rod bracket (304) of the two groups of telescopic connecting rod mechanisms (300); The two groups of telescopic link mechanisms (300) and the bending links (205) of the bending mechanism (200) are arranged in the same vertical plane, and other components of the bending mechanism (200) and the telescopic link mechanisms (300) are distributed in a vertical state; the locking mechanism (400) and the telescopic link mechanism (300) are distributed in a parallel state.
  2. 2. The aircraft nose cone based on linkage deformation according to claim 1, wherein the bending mechanism (200) comprises a motor (201), a coupling (202), a rotating shaft (203), a sleeve (204), a bending link (205), a deep groove ball bearing (206) and a bearing seat (207); the motor (201) is connected with the rotating shaft (203) through a coupler (202); The rotating shaft (203) is provided with shaft shoulders with different heights, and the combined sleeve (204) realizes the axial positioning of the bending connecting rod (205); The rotating shaft (203) is milled with a key slot and is connected with the bending connecting rod (205) through a key, so that the circumferential positioning of the bending connecting rod (205) is realized; one end of the rotating shaft (203) is connected with a deep groove ball bearing (206), and the bearing seat (207) is arranged on the aircraft body and bears the radial load of the bending mechanism (200); The bending connecting rod (205) is welded with the first cone housing (100) and transmits the rotary motion to the cone, so that the whole bending motion of the cone is realized.
  3. 3. An aircraft nose cone based on linkage deformation according to claim 1, wherein each set of telescopic linkages (300) comprises an upper linkage mount (301), an i-shaped slider (302), a middle linkage mount (303), a lower linkage mount (304), a long linkage (305), a sliding linkage (306), a middle hinged long linkage (307) and a short linkage (308); The upper connecting rod bracket (301) and the lower connecting rod bracket (304) are respectively welded and fixed with the nose cone shells (100) of different sections; The telescopic link mechanism (300) is symmetrically distributed about the middle link bracket (303); The connecting rod mechanism from the middle connecting rod bracket (303) to the lower connecting rod bracket (304) consists of two layers of rod pieces, including a first layer of rod pieces (310) and a second layer of rod pieces (320); The first-layer rod piece (310) consists of a lower connecting rod bracket (304), a long connecting rod (305), a middle hinged long connecting rod (307) and a short connecting rod (308), wherein the long connecting rod (305) and the middle hinged long connecting rod (307) are respectively hinged with two ends of the lower connecting rod bracket (304), one end of the short connecting rod (308) is hinged with the inside of the middle hinged long connecting rod (307), and the non-hinged end of the short connecting rod is hinged with the non-bracket end of the long connecting rod (305); the second-layer rod piece (320) consists of a middle connecting rod bracket (303), a long connecting rod (305), a middle hinged long connecting rod (307), a sliding connecting rod (306) and an I-shaped sliding block (302), one end of the middle hinged long connecting rod (307) of the second-layer rod piece (320) is hinged with the long connecting rod (305) and the short connecting rod (308) of the first-layer rod piece (310) to form a composite hinge, the long connecting rod (305) of the second-layer rod piece (320) is hinged with the non-bracket end of the middle hinged long connecting rod (307) to form a composite hinge, and the other ends of the long connecting rod (305) and the middle hinged long connecting rod (307) of the second-layer rod piece (320) are respectively hinged with two ends of the middle connecting rod bracket (303); the middle connecting rod bracket (303) is provided with a slide block track, the I-shaped slide block (302) moves in the track, and two ends of the slide block are connected by a cylindrical rod; One end of the sliding connecting rod (306) is provided with a sliding track, a cylindrical rod of the I-shaped sliding block (302) moves in the track, and the middle part of the sliding connecting rod (306) is hinged with the inside of a middle hinged long connecting rod (307) of the second-layer rod piece (320).
  4. 4. The aircraft nose cone based on linkage deformation according to claim 1, wherein each set of locking mechanisms (400) comprises an upper hinge base (401), a lower hinge base (402), a rotating link (403), a locking nut (404), a nut stopper (405) and a locking screw (406); The locking screw (406) is arranged on the upper hinge base (401), and the rotary connecting rod (403) is hinged with the lower hinge base (402) and the locking nut (404); the locking nut (404) is sleeved on the locking screw (406), and nut limiting blocks (405) are arranged at the left end, the right end and the middle position of the locking screw (406) and used for limiting the limiting position of the locking nut (404) on the locking screw (406); the locking mechanism (400) moves as a driven branch following the nose cone housing (100).
  5. 5. An aircraft nose cone based on linkage deformation according to claim 3, wherein the telescopic linkage (300) has two groups, respectively arranged between the first and second nose cone shells (100) and between the second and third nose cone shells (100); the telescopic connecting rod mechanism (300) is arranged between the first section and the second section of the nose cone shell (100), the lower connecting rod bracket (304) of the telescopic connecting rod mechanism is welded on the first section of the nose cone shell (100), and the upper connecting rod bracket (301) is welded on the second section of the nose cone shell (100); The telescopic connecting rod mechanism (300) is arranged between the second section and the third section of the head cone shell (100), the lower connecting rod bracket (304) of the telescopic connecting rod mechanism is welded on the second section of the head cone shell (100), and the upper connecting rod bracket (301) is welded on the third section of the head cone shell (100); the two sets of telescopic link mechanisms (300) are independent of each other.
  6. 6. The aircraft nose cone based on linkage deformation according to claim 4, wherein the locking mechanisms (400) are arranged between the first section and the second section nose cone housing (100) and between the second section and the third section nose cone housing (100), respectively, and two groups of locking mechanisms (400) are arranged between each group of adjacent nose cone housings; The locking mechanism (400) is arranged between the first section and the second section of the nose cone shell (100), the lower hinge base (402) of the locking mechanism is arranged on the first section of the nose cone shell (100), and the upper hinge base (401) is arranged on the second section of the nose cone shell (100); and the locking mechanism (400) is arranged between the second section and the third section of the head cone shell (100), the lower hinge base (402) of the locking mechanism is arranged on the second section of the head cone shell (100), and the upper hinge base (401) is arranged on the third section of the head cone shell (100).
  7. 7. The aircraft nose cone based on linkage deformation of claim 1, wherein the aircraft nose cone is provided with three sets of drive assemblies, comprising: Two groups of linear motors respectively drive the I-shaped sliding blocks (302) of the two groups of telescopic link mechanisms (300) to move; a set of rotating motors, i.e. motors (201) of the bending mechanism (200), driving the bending mechanism (200) in motion; When the rotating speeds and the directions of the two groups of linear motors are equal, the two groups of telescopic link mechanisms (300) synchronously extend or shorten, so that the distance between adjacent nose cone shells (100) is driven to increase or decrease, and the telescopic deformation of the nose cone of the aircraft is realized; When a motor (201) of the bending mechanism (200) drives the rotating shaft (203) to rotate, the bending connecting rod (205) drives the first nose cone shell (100) to rotate, so that the integral bending deformation of the nose cone of the aircraft is realized.
  8. 8. The aircraft nose cone based on linkage deformation according to claim 4, wherein a nut stopper (405) is provided on the locking screw (406); when the nose cone of the aircraft is contracted to the limit position, the locking nut (404) is connected with the nut limiting blocks (405) at the two sides to play a role in limiting the contracted state, and when the external force drive is removed, the locking nut (404) and the locking screw (406) are locked by virtue of thread friction; When the nose cone of the aircraft stretches to the limit position, the locking nut (404) is connected with the middle nut limiting block (405) to play a role in limiting the stretching state, and when the external force drive is removed, the locking nut (404) and the locking screw (406) are locked by virtue of thread friction; when the linear motor applies driving, the locked state is released.
  9. 9. The aircraft nose cone based on linkage deformation according to claim 4, wherein the upper hinge base (401), the lower hinge base (402) and the nose cone housing (100) are fixedly connected through bolts, and the contact surfaces of the upper hinge base (401), the lower hinge base (402) are processed into arc surfaces which are attached to the inside of the housing.

Description

Aircraft nose cone based on deformation of connecting rod mechanism Technical Field The invention belongs to the technical field of aerospace aircrafts, and particularly relates to an aircraft nose cone based on deformation of a connecting rod mechanism. Background The aerospace vehicle is an integrated multifunctional aircraft, has become a research hot spot in the field of military application, and experiences large speed change when traversing a wide airspace and faces a complex pneumatic environment. The nose cone device of the variant aircraft is arranged at the front end of the nose cone device, and the aerodynamic shape of the nose cone of the aircraft is changed, so that the nose cone device has important significance for improving the environmental adaptability of the aerospace aircraft. Most of the currently studied aircraft nose cone deformation mechanisms are connected in parallel with multiple chains in a complex space, a series of errors such as machining errors are accumulated during movement, the mechanism can vibrate, and meanwhile, redundant constraint can be introduced for improving the rigidity performance of the nose cone, so that the dead weight of the aerospace aircraft is increased. Disclosure of Invention The invention aims to provide the aircraft nose cone based on the deformation of the connecting rod mechanism, and the telescopic connecting rod mechanism and the bending mechanism are arranged in series, so that the telescopic and bending deformation of the aircraft nose cone can be realized step by step, and the aircraft nose cone has the advantages of large deformation, simplicity in driving, capability of improving the overall rigidity through the locking mechanism and the like. The invention provides an aircraft nose cone based on linkage deformation, comprising: three sections of cone-shaped nose cone shells are sequentially arranged; the bending mechanism is connected with the first nose cone shell; the telescopic connecting rod mechanisms are provided with two groups and are respectively connected between the adjacent nose cone shells; the locking mechanisms are provided with four groups and are respectively connected between the adjacent nose cone shells; wherein, the first section and the second section of the head cone shell are respectively provided with a group of lower hinge bases, and the second section and the third section of the head cone shell are respectively provided with a group of upper hinge bases; The first section and the third section of head cone shell are respectively welded with the lower connecting rod support and the upper connecting rod support of the two groups of telescopic connecting rod mechanisms, and the second section of head cone shell is simultaneously welded with the upper connecting rod support and the lower connecting rod support of the two groups of telescopic connecting rod mechanisms; the two groups of telescopic link mechanisms and the bending links of the bending mechanism are arranged in the same vertical plane, and other components of the bending mechanism and the telescopic link mechanisms are distributed in a vertical state; the locking mechanism and the telescopic connecting rod mechanism are distributed in a parallel state. Further, the bending mechanism comprises a motor, a coupler, a rotating shaft, a sleeve, a bending connecting rod, a deep groove ball bearing and a bearing seat; The motor is connected with the rotating shaft through a coupler; The rotating shaft is provided with shaft shoulders with different heights, and the axial positioning of the bending connecting rod is realized by combining the sleeve; The rotating shaft is milled with a key slot and is connected with the bending connecting rod through a key, so that the circumferential positioning of the bending connecting rod is realized; one end of the rotating shaft is connected with the deep groove ball bearing, and the bearing seat is arranged on the aircraft body and bears the radial load of the bending mechanism; The bending connecting rod is welded with the first nose cone shell, and transmits the rotary motion to the nose cone, so that the integral bending motion of the nose cone is realized. Further, each group of the telescopic link mechanisms comprises an upper link support, an I-shaped sliding block, a middle link support, a lower link support, a long link, a sliding link, a middle hinged long link and a short link; The upper connecting rod bracket and the lower connecting rod bracket are respectively welded and fixed with the nose cone shells of different sections; the telescopic link mechanisms are symmetrically distributed about the middle link bracket; The connecting rod mechanism from the middle connecting rod support to the lower connecting rod support consists of two layers of rod pieces, and comprises a first layer of rod pieces and a second layer of rod pieces; the first layer rod piece consists of a lower connecting rod bracket, a long connec