CN109539902B - Electric-drive folding wing system with large aspect ratio - Google Patents
Electric-drive folding wing system with large aspect ratio Download PDFInfo
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- CN109539902B CN109539902B CN201811594834.4A CN201811594834A CN109539902B CN 109539902 B CN109539902 B CN 109539902B CN 201811594834 A CN201811594834 A CN 201811594834A CN 109539902 B CN109539902 B CN 109539902B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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Abstract
The invention discloses an electric-drive folding wing system with a large aspect ratio, which comprises a belt wheel support, a servo motor, a synchronous belt, a belt wheel shaft system, a universal coupling, a clutch shaft system, a missile wing shaft system, an axial compression spring, a missile wing rotating shaft mounting seat, a missile wing, a locking pin assembly and a cabin body. The missile wings are in a furled folded state in an initial state, after an unfolding instruction is sent, the unfolding functions of the four groups of missile wings are realized under the drive of the servo motor, and the locking of the unfolding states of the missile wings is realized through the locking pin assembly. The electrically-driven folding wing system with the large aspect ratio overcomes the defects of the prior art, has a parameterized design process, can be quickly transplanted according to the requirements of different weapon systems, has the characteristics of simple mechanism, reliable function, small outer envelope size of a folded state, good pneumatic appearance in an unfolded state, small occupied space of a cabin body by the mechanism, smooth working process, no impact and the like, and can be used as a folding wing component with the large aspect ratio for airborne, ground and water surface barrel type missile launching.
Description
Technical Field
The invention relates to a novel electric-drive folding wing system with a large aspect ratio, in particular to a folding missile wing mechanism which effectively reduces storage space and greatly increases weapon range, and can be applied to various airborne, ground and water surface cylinder type launched missiles adopting large aspect ratio missile wing layout, and aircrafts such as similar pneumatic appearance flyers, unmanned planes and the like.
Background
In order to meet the combat requirements of the modern war on hitting outside a defense area and low collateral damage, the range requirement of the flight missile is continuously improved, and meanwhile, the weapon has a structural shape which is as compact as possible when being hung on a carrier or being launched on the ground or on the water surface. The requirements of long range and small volume make the battle weapons more and more adopt the layout form of folding wings.
Conventional folding wing systems typically take the form of both transverse and longitudinal folds. The outer envelope size of the transverse folding mode is influenced by the span length of the missile wing, and the transverse folding mode is not suitable for large-aspect-ratio pneumatic layout. The structural arrangement of the currently generally adopted longitudinal folding mode is greatly influenced by the chord length of the missile wing, a longitudinal straight-shaped groove formed on the cabin body or a mounting seat outside the cabin body can greatly influence the structural strength and the pneumatic appearance, and the missile wing which is taken in the cabin body also greatly extrudes the internal space of the cabin body. There is therefore a need to develop a folding wing system suitable for high aspect ratio.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the high-aspect-ratio electrically-driven folding wing system capable of being unfolded outside the cabin is provided, the mechanism is simple in composition and reliable in function, the influence of the folding mechanism on the aspects of full-missile outer envelope size, pneumatic appearance and the like is effectively reduced, and the requirements of simultaneous unfolding motion and locking of multiple groups of missile wings in a small space are met.
The technical scheme of the invention is as follows: an electric drive folding wing system with a large aspect ratio comprises a belt wheel support 1, a servo motor 2, a synchronous belt 3, a belt wheel shafting 4, a universal coupling 5, a clutch shafting 6, a missile wing shafting 7, an axial compression spring 8, a missile wing rotating shaft mounting seat 9, a missile wing 10, a locking pin assembly 11 and a cabin body 12;
the belt wheel bracket 1 is fixed on the cabin body 12, and the output shaft of the servo motor 2 is fixedly connected with a group of belt wheel shaft systems 4 and can drive the group of belt wheel shaft systems 4 to rotate;
a plurality of groups of belt wheel shaft systems 4 are all arranged on the belt wheel support 1 and can respectively rotate on the belt wheel support 1, and synchronous belts 3 are respectively meshed with the plurality of groups of belt wheel shaft systems 4;
the clutch shafting 6 and the missile wing shafting 7 are arranged on the missile wing rotating shaft mounting seat 9 and can respectively rotate on the missile wing rotating shaft mounting seat 9, the clutch shafting 6 and the missile wing shafting 7 are mutually meshed, and an axial compression spring 8 is arranged between the missile wing shafting 7 and the missile wing rotating shaft mounting seat 9;
one end of the universal coupling 5 is fixedly connected with the belt wheel shaft system 4, and the other end of the universal coupling is fixedly connected with the clutch shaft system 6;
the missile wing rotating shaft mounting seat 9 is fixed on the cabin body 12, and the missile wing 10 is fixedly connected with the missile wing shafting 7; the missile wing 10 is driven to be in a folded state to an unfolded state along with the rotation of the missile wing shafting 7;
the locking pin assembly 11 is installed on the missile wing rotating shaft installation seat 9, and after the missile wing 10 is unfolded to the proper position, the locking pin assembly 11 is matched with the missile wing shafting 7 to lock the missile wing 10 at the unfolded position.
The belt wheel shafting 4 comprises a synchronous belt wheel shaft 13, a synchronous belt wheel 14, a first bearing 15-1, a first bearing inner ring baffle ring 16-1, a first bearing outer ring baffle cover 17-1, a first shaft end baffle cover 18-1 and a belt wheel baffle ring 19;
inner rings of a synchronous pulley 14 and a bearing 15 are fixed on a synchronous pulley shaft 13, an outer ring of the bearing 15 is fixed on a pulley bracket 1 by a bearing outer ring baffle cover 17, pulley baffle rings 19 are arranged at two sides of the synchronous pulley 14, a pair of pulley baffle rings 19 are used for preventing a synchronous belt 3 from falling off from the synchronous pulley 14, a first bearing inner baffle ring 16-1 is positioned between a first bearing 15-1 and a first shaft end baffle cover 18-1 and is used for fixing the synchronous pulley shaft 13 by pressing the first shaft end baffle cover 18-1 at one end of the synchronous pulley shaft 13.
The clutch shafting 6 comprises: the clutch gear shaft 20, the first clutch gear 21-1, the adjusting gasket 22, the second bearing 15-2, the second bearing inner ring baffle ring 16-2, the second bearing outer ring baffle cover 17-2 and the second bearing end baffle cover 18-2, wherein the adjusting gasket 22 is used for eliminating the assembly clearance between the universal coupling 5 and the clutch shaft system 6; the outer ring of the second bearing 15-2 is fixed on the rotating shaft mounting base 9 with the elastic wings by the second bearing outer ring baffle cover 17-2, the second bearing inner baffle ring 16-2 is positioned between the second bearing 15-2 and the second shaft end baffle cover 18-2, and the second shaft end baffle cover 18-2 at one end of the clutch gear shaft 20 is pressed tightly to fix the clutch gear shaft 20;
the missile wing shafting 7 comprises: the missile wing rotating shaft 23, the second clutch gear 21-2 and the missile wing rotating shaft blocking cover 24 are arranged, the second clutch gear 21-2 is fixed at the non-inclined end of the missile wing rotating shaft 23 by the missile wing rotating shaft blocking cover 24, the second clutch gear 21-2 is meshed with the clutch shaft system 6, the rotation of the missile wing rotating shaft 23 along with the rotation of the clutch shaft system 6 is realized, and the missile wing rotating shaft 23 is provided with a protruding shaft key and a locking hole for limiting and locking the missile wing rotating shaft 23 in the unfolding process of the missile wing; the missile wing 10 consists of a wing handle 27 and a missile wing body 28, the missile wing 10 is installed at one end of the inclined plane of the missile wing rotating shaft 23, and the wing handle 27 is used for fixing the missile wing body 28 on the missile wing rotating shaft 23.
When the belt wheel shafting 4 rotates under the driving of the servo motor 2 or the synchronous belt 3, the clutch shafting 6 is driven to rotate simultaneously by the universal coupling 5, and the clutch shafting 6 drives the missile wing shafting 7 to rotate simultaneously by a pair of clutch gears, namely a first clutch gear 21-1 and a second clutch gear 21-2.
The missile wing rotating shaft mounting seat 9 comprises a base 25 and a rotating shaft support 26, wherein the base 25 is fixed on the cabin body 12, the rotating shaft support 26 is fixed on the base 25, the rotating shaft support 26 is provided with a shaft hole, and the shaft hole is obtained from the Euler angle transformation matrix from the folding posture to the unfolding posture of the missile wing 10 relative to the direction of the cabin body 12, and the preferred results are as follows: the coordinate transformation matrix of the missile wing 10 from the folded state to the unfolded state is
The direction of the missile wing rotating shaft (23) is preferably as follows:
this is the direction vector of the shaft hole of the rotating shaft bracket 26 relative to the cabin body 12.
The missile wing rotating shaft 23 is installed in a shaft hole of the rotating shaft support 26, the axial compression spring 8 is installed between the clutch gear 21 of the missile wing shafting 7 and the rotating shaft support 26, the axial compression spring 8 is in a compression state, a shaft key is arranged on the side wall of the missile wing rotating shaft 23, a shaft key sliding surface is arranged on one side of the shaft hole of the rotating shaft support 26, and the shaft key of the missile wing rotating shaft 23 is tightly attached to the shaft key sliding surface of the rotating shaft support 26 under the action of the axial compression spring 8.
When the missile wing shafting 7 rotates under the driving of the servo motor 2, the shaft key on the missile wing rotating shaft 23 is attached to the shaft key sliding surface of the rotating shaft bracket 26 to rotate, the inner wall of the shaft hole of the rotating shaft bracket 26 is provided with a guide groove, the junction of the guide groove and the shaft key sliding surface is provided with a slope, when the contact surface of the shaft key on the missile wing rotating shaft 23 and the rotating shaft bracket 26 is transited from the shaft key sliding surface to the slope, the missile wing shafting 7 starts to move along the axial direction of the missile wing rotating shaft 23 under the action of the axial compression spring 8, since the length component of the slope in the axial direction is larger than the thickness of the second clutch gear 21-2, therefore, the second clutch gear 21-2 of the missile wing shafting 7 is separated from the first clutch gear 21-1 of the clutch shafting 6, and the shaft key on the missile wing rotating shaft 23 finally slides into the bottom of the guide groove of the rotating shaft bracket 26 and is locked in the final position by the locking pin assembly 11.
Due to machining and assembling errors, multiple groups of missile wing folding mechanisms cannot be unfolded in place simultaneously in actual movement, and the arrangement of the slopes on the rotating shaft support 26 ensures that each group of missile wing shafting 7 which is unfolded in place is separated from the transmission mechanism before the rotation is stopped, so that the movement of other groups of missile wing shafting 7 cannot be influenced due to the stop of the rotation.
The arrangement of the guide groove enables the missile wing 10 to keep a certain distance from the cabin body 12 in the rotating process, and the missile wing 10 slides into the final position after rotating to the position, so that the missile wing 10 is prevented from interfering with the cabin body 12.
Further, the locking pin assembly 11 includes: a locking pin 29, a locking pin spring 30, a locking pin seat 31, a pin pulling rod 32;
the missile wing rotating shaft 23 is provided with a locking hole; the locking pin spring 30 and the locking pin 29 are arranged in an inner cavity of a locking pin seat 31, the locking pin seat 31 is arranged on the rotating shaft bracket 26, and the pin pulling rod 32 penetrates through the inner cavity of the locking pin seat 31 to be connected with the locking pin 29;
the tail end of the locking pin 29 is propped against the surface of the missile wing rotating shaft 23 under the thrust action of the locking pin spring 30 in an initial folding state, when the missile wing rotating shaft 23 moves in place, a locking hole in the missile wing rotating shaft 23 is aligned with the locking pin assembly 11, and the locking pin 29 is propped into the locking hole in the missile wing rotating shaft 23 under the thrust action of the locking pin spring 30, so that the tail locking of the missile wing rotating shaft 23 is realized;
the locking pin 29 is pulled out of the locking hole by the pin pulling rod 32, so that the missile wing rotating shaft 23 is unlocked, and the missile wing 10 is folded again.
Compared with the prior art, the invention has the technical effects that:
(1) according to the missile wing rotating shaft, a certain space vector is selected as the rotating shaft direction of the missile wing, the posture of the missile wing from a folded state to an unfolded state is changed, and the problem of interference between the root of the missile wing and a cabin body in the rotating process is solved by arranging the shaft key and the translation pair of the wire guide groove.
(2) The folding mechanisms are all arranged in the cabin body, the rotating shafts of the mechanisms are directly connected with the wing roots of the missile wings, and the cabin body is not provided with any open groove or hole, so that the unfolded missile has a good pneumatic appearance, and the folding mechanisms almost have no influence on the pneumatic appearance; the unfolding motion of the missile wings is completely carried out outside the cabin body, so that the internal space of the cabin body is not occupied, and the utilization rate of the space in the missile body is greatly improved;
(3) the synchronous unfolding of four groups of missile wings is realized through the servo motor, the synchronous belt and the gear mechanism, the translation of the rotating shaft of the missile wings is realized through the axial compression spring, the mechanism is simple and easy to process and assemble, the whole mechanism is smooth and stable in motion process, high in reliability and reusable, the servo motor can feed back the motion state of the mechanism in real time, and the starting and controlling time of the missile after the missile wings are unfolded can be greatly advanced.
(4) According to the invention, the separation of each group of the missile wing shafting which is unfolded in place from the folding mechanism is realized through the arrangement of the slope and the guide groove on the rotating shaft support, the stable and continuous unfolding process of four groups of missile wings is ensured, and the influence of the unfolded missile wing shafting in place on the rotation of the missile wing shafting which is not unfolded in place is avoided.
(5) The invention adopts a double limiting locking mode of the shaft key, the guide groove and the locking pin and the locking hole, so that the missile wing has better positioning precision and bearing performance after being unfolded.
Description of the drawings:
FIG. 1 is an assembled view of the present invention in a collapsed condition;
FIG. 2 a is a front view of the missile wing in the unfolded state, and b is a side view of the single group of missile wings in the unfolded state;
FIG. 3 is an exploded view of the pulley shafting and associated components of the present invention;
FIG. 4 is a cross-sectional view of the structure of the pulley shafting and associated components of the present invention;
FIG. 5 is an exploded view of the clutch shaft system and related components of the present invention;
FIG. 6 is a cross-sectional view of the clutch shafting and associated components according to the present invention;
FIG. 7 is an exploded view of the missile wing shafting and associated components of the present invention;
FIG. 8 a is a schematic view of the shape of the rotor shaft of the missile wing according to the invention;
fig. 8 b is a schematic view of the shape of the spindle bracket according to the present invention;
FIG. 9 a is a schematic view of the missile wing attitude in the deployed state of the invention;
fig. 9 b is a schematic view of the folded missile wing attitude of the invention;
FIG. 10 is an exploded view of the locking pin assembly of the present invention;
FIG. 11 is a structural cross-sectional view of the locking pin assembly of the present invention;
FIG. 12 is an effect view of the folded state of the present invention;
FIG. 13 is a diagram illustrating the effect of the unfolded state of the present invention;
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
The invention discloses an electric-drive folding wing system with a large aspect ratio, which comprises a belt wheel support, a servo motor, a synchronous belt, a belt wheel shaft system, a universal coupling, a clutch shaft system, a missile wing shaft system, an axial compression spring, a missile wing rotating shaft mounting seat, a missile wing, a locking pin assembly and a cabin body. The missile wings are in a furled folded state in an initial state, after an unfolding instruction is sent, the unfolding functions of the four groups of missile wings are realized under the drive of the servo motor, and the locking of the unfolding states of the missile wings is realized through the locking pin assembly. The electrically-driven folding wing system with the large aspect ratio overcomes the defects of the prior art, has a parameterized design process, can be quickly transplanted according to the requirements of different weapon systems, has the characteristics of simple mechanism, reliable function, small outer envelope size of a folded state, good pneumatic appearance in an unfolded state, small occupied space of a cabin body by the mechanism, smooth working process, no impact and the like, and can be used as a folding wing component with the large aspect ratio for airborne, ground and water surface barrel type missile launching.
The electrically-driven folding wing system with the large aspect ratio overcomes the defects of the prior art, has a parameterized design process, can be quickly transplanted according to the requirements of different weapon systems, has the characteristics of simple mechanism, reliable function, small outer envelope size of a folded state, good pneumatic appearance in an unfolded state, small occupied space of a cabin body by the mechanism, smooth working process, no impact and the like, and can be used as a folding wing component with the large aspect ratio for airborne, ground and water surface barrel type missile launching.
The invention relates to an electrically-driven folding wing system with a large aspect ratio, which comprises a belt wheel support 1, a servo motor 2, a synchronous belt 3, a belt wheel shafting 4, a universal coupling 5, a clutch shafting 6, a missile wing shafting 7, an axial compression spring 8, a missile wing rotating shaft mounting seat 9, a missile wing 10, a locking pin assembly 11 and a cabin body 12;
the belt wheel bracket 1 is fixed on the cabin body 12, and the output shaft of the servo motor 2 is fixedly connected with a group of belt wheel shaft systems 4 and can drive the group of belt wheel shaft systems 4 to rotate;
a plurality of groups of belt wheel shaft systems 4 are all arranged on the belt wheel support 1 and can respectively rotate on the belt wheel support 1, and synchronous belts 3 are respectively meshed with the plurality of groups of belt wheel shaft systems 4;
the clutch shafting 6 and the missile wing shafting 7 are arranged on the missile wing rotating shaft mounting seat 9 and can respectively rotate on the missile wing rotating shaft mounting seat 9, the clutch shafting 6 and the missile wing shafting 7 are mutually meshed, and an axial compression spring 8 is arranged between the missile wing shafting 7 and the missile wing rotating shaft mounting seat 9;
one end of the universal coupling 5 is fixedly connected with the belt wheel shaft system 4, and the other end of the universal coupling is fixedly connected with the clutch shaft system 6;
the missile wing rotating shaft mounting seat 9 is fixed on the cabin body 12, and the missile wing 10 is fixedly connected with the missile wing shafting 7; the missile wing 10 is driven to be in a folded state to an unfolded state along with the rotation of the missile wing shafting 7;
the last locking assembly 11 is installed on the missile wing rotating shaft installation seat 9, and after the missile wing 10 is unfolded in place, the last locking assembly 11 is matched with the missile wing shafting 7 to lock the missile wing 10 at the unfolded position.
As shown in figures 1 and 2 a and b, the invention provides an electrically-driven folding wing system with a large aspect ratio, which provides pneumatic lift for missile flight in a missile wing unfolding state and has smaller volume in a folding state so as to realize airborne, ground and water surface barrel type launching. The invention comprises a belt wheel bracket 1, a servo motor 2, a synchronous belt 3, a belt wheel shaft system 4, a universal coupling 5, a clutch shaft system 6, a missile wing shaft system 7, an axial compression spring 8, a missile wing rotating shaft mounting seat 9, a missile wing 10, a locking pin assembly 11 and a cabin body 12.
The belt wheel support 1 is fixed on the cabin body 12 and used for mounting the servo motor 2, the synchronous belt 3 is used for guaranteeing synchronism of the belt wheel shaft system 4, the belt wheel shaft system 4 is connected with the clutch shaft system 6 through the universal shaft connector 5, and the axial compression spring 8 is compressed between the second clutch gear 21-2 and the rotating shaft support, so that the axial compression spring stores outward elastic energy. The missile wing 10 comprises a wing handle 27 and a missile wing body 28, wherein the missile wing body 28 is fixedly connected with the missile wing rotating shaft 23 through the wing handle 27.
As shown in fig. 3 and 4, the pulley shafting 4 comprises a synchronous pulley shaft 13, a synchronous pulley 14, a first bearing 15-1, a first bearing inner ring retaining ring 16-1, a first bearing outer ring retaining cover 17-1, a first shaft end retaining cover 18-1 and a pulley retaining ring 19. The inner ring of the first bearing 15-1 is pressed and fixed on the synchronous pulley shaft 13 by the first bearing inner ring retaining ring 16-1. The universal joint 5 is fixed at one end of the synchronous pulley shaft 13 and fixes the synchronous pulley 14 on the synchronous pulley shaft 13, and the pair of pulley retainer rings 19 are positioned at two sides of the synchronous pulley 14 and used for preventing the synchronous belt 3 from falling off from the synchronous pulley 14. The outer ring of the first bearing 15-1 is fixed on the belt wheel support 2 by the first bearing outer ring baffle cover 17-1, the belt wheel support 1 is fixed on the cabin body 12, and the output shaft of the servo motor 2 is fixedly connected with a group of belt wheel shaft systems 4 and can drive the group of belt wheel shaft systems 4 to rotate. The other three groups of belt wheel shaft systems 4 are also arranged on the belt wheel support 1 and can rotate on the belt wheel support 1 respectively, the synchronous belts 3 are meshed with the gears of the four groups of belt wheel shaft systems 4 respectively, and when the servo motor 2 drives one group of belt wheel shaft systems 4 to rotate, the other three groups of belt wheel shaft systems 4 also rotate synchronously.
As shown in fig. 5 and 6, the clutch shafting 6 includes a clutch gear shaft 20, a first clutch gear 21-1, an adjusting shim 22, a second bearing 15-2, a second bearing inner ring retainer ring 16-2, a second bearing outer ring retainer cover 17-2, and a second bearing end retainer cover 18-2. The universal joint 5 is fixed to one end of the clutch gear shaft 20 and fixes the first clutch gear 21-1 to the clutch gear shaft 20. An adjusting gasket 22 is arranged between the first clutch gear 21-1 and the universal coupling 5 and used for eliminating a mounting gap caused by machining and assembling errors between the universal coupling 5 and the clutch shaft system 6. When the belt wheel shafting 4 starts to rotate, the clutch shafting 6 is driven to synchronously rotate through the universal coupling 5.
As shown in fig. 7, the missile wing shafting 7 includes a missile wing rotating shaft 23, a second clutch gear 21-2, and a missile wing rotating shaft blocking cover 24, and the missile wing rotating shaft mounting seat 9 includes a base 25 and a rotating shaft support 26. The base 25 is fixed to the cabin 12, and the pivot bracket 26 is fixed to the base 25. The missile wing rotating shaft 23 is arranged in the shaft hole of the rotating shaft bracket 26, the missile wing 10 is arranged at one end of the missile wing rotating shaft 23, and the second clutch gear 21-2 is fixed at the other end of the missile wing rotating shaft 23 by the missile wing rotating shaft blocking cover 24. In the folded state of the missile wing, the second clutch gear 21-2 of the missile wing shafting 7 is meshed with the first clutch gear 21-1 of the clutch shafting 6. When the clutch shafting 6 starts to rotate, the missile wing shafting 7 is driven to synchronously rotate by the pair of clutch gears 21-1 and 21-2. An axial compression spring 8 is arranged between the clutch gear on the missile wing shafting 7 and the rotating shaft support 26, and the axial compression spring 8 is in a compression state.
As shown in a and b of fig. 8, the missile wing rotating shaft 23 is provided with a shaft key and a locking hole, the rotating shaft bracket 26 is provided with a shaft hole, a guide groove along the axial direction is formed at a specific position on the side surface of the shaft hole, the surface of the rotating shaft bracket 26 contacting with the shaft key of the missile wing rotating shaft 23 is a shaft key sliding surface, and a transitional slope is formed between the shaft key sliding surface and the guide groove. In the folded state, the missile wing rotating shaft 23 is pressed on the rotating shaft support 26 by the axial compression spring 8, and the shaft key of the missile wing rotating shaft 23 is tightly attached to the shaft key sliding surface of the rotating shaft support 26.
As shown in fig. 9 a and b, the y-axis of the coordinate system is the axial direction of the nacelle, and the x-axis and z-axis are the lateral direction and the normal direction of the nacelle 12, respectively. When the missile wing 10 is in an unfolding state, the sweepback angle is delta, namely, the included angle between the front edge of the missile wing 10 and the y axis is delta, and the wing surface of the missile wing 10 is superposed with the yoz surface. When the missile wing 10 is folded, the front edge of the missile wing is parallel to the y axis, and the wing surface of the missile wing 10 is parallel to the xoy plane. The coordinate transformation matrix of the missile wing 10 from the folded state to the unfolded state is preferably
The preferred direction of the missile wing rotating shaft (23) is as follows:
this is the direction vector of the shaft hole of the rotating shaft bracket 26 relative to the cabin body 12.
As shown in fig. 10 and 11, the locking pin assembly 11 includes a locking pin 29, a locking pin spring 30, a locking pin holder 31, and a pin pulling rod 32. The locking pin spring 30 and the locking pin 29 are installed in an inner cavity of a locking pin holder 31, the locking pin holder 31 is installed at a specific position on the rotation shaft bracket 26, and the pin pulling rod 32 passes through the inner cavity of the locking pin holder 31 to be connected with the locking pin 29. In the folded state, the end of the locking pin 29 is pressed against the surface of the missile wing rotating shaft 23 by the pushing force of the locking pin spring 30.
FIG. 12 shows the effect of the folded state of the present invention; FIG. 13 is a diagram showing the effect of the expanded state of the present invention.
The preferred working process of the invention is as follows:
in the initial state: the missile is stored in the launching tube, and the missile wings 10 are folded to be in the initial position. The servo motor 2 is in a band-type brake locking state, and four groups of elastic wing folding mechanisms are locked through motor shafts. The missile wing rotating shaft 23 is located at the initial position on the rotating shaft bracket 26, and under the action of the axial compression spring 8, the shaft key of the missile wing rotating shaft 23 is pressed against the plane of the rotating shaft bracket 26. The locking pin 29 is pressed against the surface of the missile wing rotating shaft 23 by the locking pin spring 30.
The unfolding process of the missile wing: when the missile flies to a certain moment or a certain position on the trajectory, the missile-mounted computer sends out a missile wing unfolding instruction, and the servo motor 2 starts to rotate. One group of belt wheel shaft systems 4 fixedly connected with the servo motor 2 rotates under the driving of the servo motor 2, and the other three groups of belt wheel shaft systems 4 are driven to rotate simultaneously through the synchronous belt 3. The belt wheel shafting 4 drives the clutch shafting 6 to rotate through the universal coupling 5. The clutch shafting 6 drives the missile wing shafting 7 to rotate through a pair of clutch gears 21-1 and 21-2. When the missile wing shafting 7 rotates by a certain angle, the shaft key of the missile wing rotating shaft 23 slides to the slope from the shaft key sliding surface of the rotating shaft support 26, and at this time, the missile wing shafting 7 starts to do axial motion besides rotating. When the shaft key slides to a certain position on the slope, the axial movement distance of the missile wing shafting 7 exceeds the thickness of the first clutch gear 21-1, and then the second clutch gear 21-2 of the missile wing shafting 7 is separated from the first clutch gear 21-1 of the clutch shafting 6. Under the action of the axial compression spring 8, the shaft key continues to slide along the slope and finally falls into the guide groove of the rotating shaft bracket 26 and slides to the bottom of the guide groove, and the unfolding movement of the missile wing 10 is completed. Because of unavoidable processing and installation errors, the four groups of missile wing folding mechanisms cannot be unfolded in place at the same time, so that the servo motor 2 drives the four groups of belt wheel shafting 4 to rotate by an angle larger than the theoretical angle required by unfolding the missile wings 10, and the four groups of missile wings 10 are ensured to be unfolded to the final position and locked.
The last locking state: in the unfolding process of the missile wing 10, the locking pin 29 is pressed against the surface of the missile wing rotating shaft 23 under the thrust of the locking pin spring 30, after the missile wing rotating shaft 23 rotates and slides in place, the locking hole in the missile wing rotating shaft 23 is aligned with the installation position of the locking pin assembly 11, and the locking pin 29 is pressed into the locking hole in the rotating shaft 23 under the thrust of the locking pin spring 30, so that the final locking of the rotating shaft 23 is realized.
While the invention has been described with reference to specific preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (7)
1. The utility model provides an electrically drive folding wing system of big aspect ratio which characterized in that: the missile wing device comprises a belt wheel support (1), a servo motor (2), a synchronous belt (3), a belt wheel shaft system (4), a universal coupling (5), a clutch shaft system (6), a missile wing shaft system (7), an axial compression spring (8), a missile wing rotating shaft mounting seat (9), a missile wing (10), a locking pin assembly (11) and a cabin body (12);
the belt wheel bracket (1) is fixed on the cabin body (12), and an output shaft of the servo motor (2) is fixedly connected with a group of belt wheel shafting (4) and can drive the group of belt wheel shafting (4) to rotate;
the multiple groups of belt wheel shafting (4) are all arranged on the belt wheel bracket (1) and can respectively rotate on the belt wheel bracket (1), and the synchronous belts (3) are respectively meshed with the multiple groups of belt wheel shafting (4);
the clutch shafting (6) and the missile wing shafting (7) are arranged on the missile wing rotating shaft mounting seat (9) and can respectively rotate on the missile wing rotating shaft mounting seat (9), the clutch shafting (6) and the missile wing shafting (7) are mutually meshed, and an axial compression spring (8) is arranged between the missile wing shafting (7) and the missile wing rotating shaft mounting seat (9);
one end of the universal coupling (5) is fixedly connected with the belt wheel shaft system (4), and the other end of the universal coupling is fixedly connected with the clutch shaft system (6);
the missile wing rotating shaft mounting seat (9) is fixed on the cabin body (12), and the missile wing (10) is fixedly connected with the missile wing shafting (7); the missile wing shaft system (7) rotates to drive the missile wing (10) to be in a folded state or an unfolded state;
the locking pin assembly (11) is arranged on the missile wing rotating shaft mounting seat (9), and when the missile wing (10) is unfolded in place, the locking pin assembly (11) is matched with the missile wing shafting (7) to lock the missile wing (10) at the unfolded position;
the belt wheel shafting (4) comprises a synchronous belt wheel shaft (13), a synchronous belt wheel (14), a first bearing (15-1), a first bearing inner ring baffle ring (16-1), a first bearing outer ring baffle cover (17-1), a first shaft end baffle cover (18-1) and a belt wheel baffle ring (19);
inner rings of a synchronous pulley (14) and a bearing (15) are fixed on a synchronous pulley shaft (13), an outer ring of the bearing (15) is fixed on a pulley bracket (1) by a bearing outer ring baffle cover (17), pulley baffle rings (19) are arranged at two sides of the synchronous pulley (14), a pair of pulley baffle rings (19) are used for preventing a synchronous belt (3) from falling off from the synchronous pulley (14), a first bearing inner ring baffle ring (16-1) is positioned between a first bearing (15-1) and a first shaft end baffle cover (18-1), and the first shaft end baffle cover (18-1) at one end of the synchronous pulley shaft (13) is pressed tightly to fix the synchronous pulley shaft (13);
the clutch shafting (6) comprises: the clutch gear shaft (20), the first clutch gear (21-1), the adjusting gasket (22), the second bearing (15-2), the second bearing inner ring baffle ring (16-2), the second bearing outer ring baffle cover (17-2) and the second shaft end baffle cover (18-2), wherein the adjusting gasket (22) is used for eliminating the assembly clearance between the universal coupling (5) and the clutch shaft system (6); the outer ring of the second bearing (15-2) is fixed on the rotating shaft mounting seat (9) with the elastic wing by a second bearing outer ring baffle cover (17-2), and a second bearing inner ring baffle ring (16-2) is positioned between the second bearing (15-2) and a second shaft end baffle cover (18-2) and is used for fixing the clutch gear shaft (20) by pressing the second shaft end baffle cover (18-2) at one end of the clutch gear shaft (20);
the missile wing shafting (7) comprises: the missile wing rotating shaft locking device comprises a missile wing rotating shaft (23), a second clutch gear (21-2) and a missile wing rotating shaft blocking cover (24), wherein the second clutch gear (21-2) is fixed at one end, which is not an inclined plane, of the missile wing rotating shaft (23) by the missile wing rotating shaft blocking cover (24), the second clutch gear (21-2) is meshed with a clutch shaft system (6), so that the missile wing rotating shaft (23) rotates along with the rotation of the clutch shaft system (6), and the missile wing rotating shaft (23) is provided with a protruding shaft key and a locking hole for limiting and locking the missile wing rotating shaft (23) in the missile wing unfolding process; the missile wing (10) consists of a wing handle (27) and a missile wing body (28), the missile wing (10) is installed at one end of the inclined plane of the missile wing rotating shaft (23), and the wing handle (27) is used for fixing the missile wing body (28) on the missile wing rotating shaft (23).
2. The high aspect ratio electrically driven folding wing system according to claim 1, characterized in that: when the belt wheel shafting (4) rotates under the drive of the servo motor (2) or the synchronous belt (3), the clutch shafting (6) is driven to rotate simultaneously through the universal coupling (5), and the missile wing shafting (7) is driven to rotate simultaneously by the clutch shafting (6) through a pair of clutch gears, namely the first clutch gear (21-1) and the second clutch gear (21-2).
3. The high aspect ratio electrically driven folding wing system according to claim 1, characterized in that: missile wing pivot mount pad (9) is including base (25) and pivot support (26), and base (25) are fixed on cabin body (12), and pivot support (26) are fixed on base (25).
4. The high aspect ratio electrically driven folding wing system according to claim 1, characterized in that: the missile wing rotating shaft (23) is installed in a shaft hole of the rotating shaft support (26), an axial compression spring (8) is installed between a clutch gear (21) of a missile wing shafting (7) and the rotating shaft support (26), the axial compression spring (8) is in a compression state, a shaft key is arranged on the side wall of the missile wing rotating shaft (23), a shaft key sliding surface is arranged on one side of the shaft hole of the rotating shaft support (26), and the shaft key of the missile wing rotating shaft (23) is tightly attached to the shaft key sliding surface of the rotating shaft support (26) under the action of the axial compression spring (8).
5. The high aspect ratio electrically driven folding wing system according to claim 1, characterized in that: when the missile wing shafting (7) is driven by the servo motor (2) to rotate, an axial key on the missile wing rotating shaft (23) is attached to an axial key sliding surface of a rotating shaft support (26) to rotate, a guide groove is arranged on the inner wall of a shaft hole of the rotating shaft support (26), a slope is arranged at the junction of the guide groove and the axial key sliding surface, when the contact surface between the axial key on the missile wing rotating shaft (23) and the rotating shaft support (26) is transited from the axial key sliding surface to the slope, the missile wing shafting (7) starts to move along the axial direction of the missile wing rotating shaft (23) under the action of an axial compression spring (8), and as the length component of the slope in the axial direction is greater than the thickness of a second clutch gear (21-2), the second clutch gear (21-2) of the missile wing shafting (7) is separated from the contact with a first clutch gear (21-1) of a clutch shafting (6), and the axial key on the missile wing rotating shaft (23) finally slides into the bottom of the, and locked in the final position by the locking pin assembly (11).
6. The high aspect ratio electrically driven folding wing system according to claim 1, characterized in that: due to machining and assembling errors, multiple groups of missile wing folding mechanisms cannot be unfolded in place simultaneously in actual movement, and the arrangement of the slopes on the rotating shaft support (26) ensures that each group of missile wing shafting (7) which is unfolded in place is separated from the transmission mechanism before stopping rotation, so that the movement of other groups of missile wing shafting (7) cannot be influenced due to the stop of rotation of the missile wing shafting.
7. The high aspect ratio electrically driven folding wing system according to claim 1, characterized in that: the arrangement of the guide groove enables the missile wing (10) to keep a certain distance with the cabin body (12) in the rotating process, and the missile wing slides into the final position after rotating to the position, so that the missile wing (10) is prevented from interfering with the cabin body (12).
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| CN201811594834.4A CN109539902B (en) | 2018-12-25 | 2018-12-25 | Electric-drive folding wing system with large aspect ratio |
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| CN201811594834.4A CN109539902B (en) | 2018-12-25 | 2018-12-25 | Electric-drive folding wing system with large aspect ratio |
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| CN111707146B (en) * | 2020-06-12 | 2022-11-25 | 湖北三江航天万峰科技发展有限公司 | Folding positioning device and method for limiting folding wing by folding positioning device |
| CN114537640B (en) * | 2022-02-15 | 2023-08-25 | 中天长光(青岛)装备科技有限公司 | Double-freedom-degree folding wing mechanism |
| CN115046431B (en) * | 2022-06-07 | 2024-05-28 | 湖南航天机电设备与特种材料研究所 | Aircraft wing surface folding and unfolding device and patrol missile adopting same |
| CN117172077B (en) * | 2023-10-27 | 2024-02-20 | 西安现代控制技术研究所 | Non-ablative transverse folding tail rudder structure of supersonic missile and design method thereof |
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| US6739548B1 (en) * | 2003-04-21 | 2004-05-25 | The United States Of America As Represented By The Secretary Of The Army | Fin lock system |
| CN203949574U (en) * | 2014-06-30 | 2014-11-19 | 中国航天时代电子公司 | A kind of Deployment and locking device of folding rudder face |
| CN105157485B (en) * | 2015-08-04 | 2017-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding aerofoil retaining mechanism |
| CN106347632B (en) * | 2016-10-26 | 2018-10-26 | 中国科学院长春光学精密机械与物理研究所 | A kind of expansion retaining mechanism |
| CN207454534U (en) * | 2017-11-08 | 2018-06-05 | 江西洪都航空工业集团有限责任公司 | A kind of retaining mechanism in place |
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