CN109625242B - Wing mechanism, emitter and method for shortening axial length of emitter - Google Patents
Wing mechanism, emitter and method for shortening axial length of emitter Download PDFInfo
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- CN109625242B CN109625242B CN201811448978.9A CN201811448978A CN109625242B CN 109625242 B CN109625242 B CN 109625242B CN 201811448978 A CN201811448978 A CN 201811448978A CN 109625242 B CN109625242 B CN 109625242B
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 230000004323 axial length Effects 0.000 title claims abstract description 12
- 238000004904 shortening Methods 0.000 title abstract description 8
- 230000000903 blocking effect Effects 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 description 3
- 238000010304 firing Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
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- 230000007123 defense Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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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 a wing mechanism, an emitter and a method for shortening the axial length of the emitter, wherein the wing mechanism comprises a support assembly, a right plate and a left plate, one sides of the right plate and the left plate, which are far away from corresponding wing roots, are respectively and rotatably connected with the upper surface of the support assembly, a sliding plate is arranged at the bottom of the support assembly in a sliding manner, a sliding groove is arranged on the sliding plate, and the sliding groove comprises a positioning section, a steering section, an inclined pushing section and a limiting section; the number of the sliding grooves is two, and the sliding grooves are symmetrical along the sliding direction of the supporting component; guide shafts are arranged on the lower surfaces of the right plate and the left plate and close to one side of the corresponding wing root, and the bottom ends of the guide shafts are respectively inserted into one sliding groove; when the right wing and the left wing are unfolded, the bottom end of the guide shaft is positioned in the positioning section and tangent to the groove wall on one side of the positioning section, which is close to the tail, and the two groove walls which are parallel to the moving direction of the supporting component. The invention shortens the whole length of the wing mechanism, thereby adopting a shorter launching tube and improving the convenience of a user in using the invention.
Description
Technical Field
The invention relates to the field of aviation, in particular to a wing mechanism, a launcher and a method for shortening the axial length of the launcher.
Background
Aviation is a complex and strategically significant human activity. Aviation refers to the flight activities of an aircraft in the earth's atmosphere (air space) and numerous fields related thereto such as scientific education, industrial manufacturing, public transportation, aviation sports, national defense military, government management, and the like. Aeronautical activities can be subdivided into a number of independent industries and fields by the use of aeronautical spaces and aircraft (aircraft), typically such as the aeronautical manufacturing industry, civil aviation industry, etc.
An aircraft is an instrumental flyer manufactured by a human being, capable of flying off the ground, flying in space, and flying in an intra-or extra-atmospheric space (space) controlled by the human being. Wings are one of the important components of an aircraft, mounted on the fuselage, and the primary function of the wings is to generate lift.
When launching an aircraft, such as a missile, the wings of the aircraft need to be gathered and then loaded into a launch canister. Therefore, the length of the launching tube is required to be matched with the whole length of the aircraft wings after being folded, and the length of the launching tube is longer because the wing length of the aircraft is not adjustable, so that the carrying and carrying are not facilitated.
Disclosure of Invention
The invention aims at: the wing mechanism, the emitter and the method for shortening the axial length of the emitter are provided, and the problems that the length of the emitting cylinder is long and carrying are not facilitated due to the fact that the wing length of an aircraft is not adjustable are solved. Therefore, the wing mechanism designed by the invention can move along the flying direction in the wing folding process, so that the whole length of the folding mechanism is shortened, a shorter launching tube can be adopted, and the convenience of a user is improved.
The technical scheme adopted by the invention is as follows:
the wing mechanism comprises a supporting component, a right plate connected with a right wing root and a left plate connected with a left wing root, wherein one sides of the right plate and the left plate, which are far away from the corresponding wing root, are rotationally connected with the upper surface of the supporting component, a sliding plate is slidably arranged at the bottom of the supporting component, the sliding direction of the supporting component on the sliding plate is parallel to the flight direction of the wing, a sliding groove is formed in one side of the sliding plate, which is positioned in the moving direction of the supporting component, the sliding groove comprises a positioning section, a steering section, an oblique pushing section and a limiting section which are communicated in sequence in an arc manner and have consistent width dimensions, the extending direction of the positioning section is parallel to the sliding direction of the supporting component, one side of the positioning section, which is far away from the tail, is communicated with one end, close to the tail, of the steering section, the other end of the steering section extends towards the nose and is far away from one side of the moving direction of the supporting component, and is communicated with one end, close to the tail, of the oblique pushing section, the other end of the oblique pushing section extends towards the nose and is close to one end, close to the tail, of the moving direction of the supporting component, and the limiting section is parallel to the sliding direction of the supporting component.
The number of the sliding grooves is two, and the sliding grooves are symmetrical along the sliding direction of the supporting component;
guide shafts are arranged on the lower surfaces of the right plate and the left plate and close to one side of the corresponding wing root, and the bottom ends of the guide shafts are respectively inserted into one sliding groove; when the right wing and the left wing are unfolded, the bottom end of the guide shaft is positioned in the positioning section and tangent to the groove wall on one side of the positioning section, which is close to the tail, and the groove walls parallel to the moving direction of the support component, and meanwhile, the support component moves to the position closest to the tail on the sliding path, wherein the position is the limit position, namely, the support component cannot move continuously towards the tail.
The right wing and the left wing are collectively referred to as wings.
In the initial state, the right wing and the left wing are in an unfolding state, and the bottom end of the guide shaft is positioned in the positioning section; when the wing needs to be folded and moved relative to the initial position, the following folding and moving steps are carried out:
pushing the right wing and the left wing to enable the guide shaft to enter the steering section along the arc connecting section between the positioning section and the steering section;
secondly, continuing to push the wing to the flight direction of the wing, and rotating the wing around a certain point between the supporting component and the wing in the process that the guide shaft moves along the groove wall of the section in the steering section, so that the forward distance of the supporting component along the flight direction of the wing is greater than the forward distance of the guide shaft, and the two wings are gradually closed in the tail direction;
step three, continuing to push the wing to the flight direction of the wing so that the guide shaft enters the oblique pushing section along the arc connecting section between the steering section and the oblique pushing section;
and fourthly, continuing to push the wings to the flight direction of the wings, wherein the guide shaft rotates around a certain point between the support component and the wings in the process of moving along the groove wall of the inclined pushing section until the two wings overlap and enter the limiting section at the same time, and at the moment, the wings are folded at one end far away from the flight direction.
Through the steps, the folding of the wing and the movement of the wing along the flying direction are completed, so that the whole length of the wing mechanism is shortened, a shorter launching tube can be adopted, and the convenience of a user in using the wing mechanism is improved.
Further, a strip-shaped through hole is formed in the sliding plate, and the long side of the cross section of the strip-shaped through hole is parallel to the flight direction of the wing;
the support assembly comprises a base assembly and a hinge shaft which are sequentially connected, the base assembly comprises a bottom plate, a positioning plate and a plurality of screws, the bottom plate and the positioning plate are parallel to the sliding plate and are respectively positioned below and above the sliding plate, one end of the hinge shaft is connected with the bottom plate, and the other end of the hinge shaft sequentially penetrates through the strip-shaped through hole and the positioning plate and then is sequentially connected with the right plate and the left plate in a rotating manner; the screw all is arranged in the bar-shaped through hole, a plurality of screw divide into two sets of, and the slip direction symmetry of supporting component is followed to two sets of screws, and the screw in every group distributes along the slip direction of supporting component, and the pole portion end of screw passes behind the locating plate with bottom plate threaded connection, all cup jointed contact bearing on the screw in the position between bottom plate and the locating plate, keep away from the articulated shaft and be close to one side and the pore wall contact of bar-shaped through hole pore wall on the contact bearing.
In the process of moving the support component along the flying direction, the contact bearing is contacted with the hole wall where the long side is positioned in the cross section of the strip-shaped through hole, so that the linearity of the moving track of the support component is ensured, meanwhile, the friction force between the support component and the sliding plate is reduced, and the friction loss is reduced, so that the support component is pushed more labor-saving and faster.
When the right wing and the left wing are unfolded, the screws far away from the flying direction in each group of screws are contacted with the hole wall far away from the flying direction on the strip-shaped through hole.
Further, the device also comprises a hook-shaped cylindrical helical compression spring, a right through hole matched with the hinge shaft is formed in the right plate, a right annular groove coaxial with the right through hole is formed in the upper surface of the right plate, a right clamping groove communicated with the right annular groove is formed in one side, close to the right wing, of the upper surface of the right plate, and the right plate is sleeved on the hinge shaft through the right through hole;
the left plate is provided with a left through hole matched with the hinge shaft, the lower surface of the left plate is provided with a left annular groove coaxial with the left through hole, one side, close to the left wing, of the lower surface of the left plate is provided with a left clamping groove communicated with the left annular groove, and the left plate is sleeved on the hinge shaft through the left through hole and is positioned above the right plate;
the bottom of the spring is inserted into the right annular groove, the hook component at the bottom of the spring is positioned in the right clamping groove, the top of the spring is inserted into the left annular groove, the hook component at the top of the spring is positioned in the left clamping groove, and when the right wing and the left wing are in an unfolded flying state, the spring is in a original state.
In the process of folding the wings and moving relative to the initial position, as each wing rotates, the hook parts at the two ends of the spring rotate along with the two wings respectively, so that the spring is in a stretched state. When the wings are positioned in the launching cylinder after being folded, the wings are restrained by the cylinder wall and cannot stretch, so that the folded state is maintained; after firing, the wing is separated from the constraint of the cylinder wall, and under the action of the restoring force of a pusher and a spring: the supporting component is pushed away from the flight direction by the pusher, so that the guide shaft moves from the limiting section to the inclined pushing section, then the supporting component moves reversely along the flight direction under the action of the resultant force of the pusher and the spring, the wing is gradually unfolded, and meanwhile, the guide shaft sequentially passes through the inclined pushing section and the steering section and then enters the positioning section, at the moment, the wing completes unfolding action, and a stable unfolding state is maintained under the action of the spring and the positioning section.
The pusher can adopt a telescopic pneumatic rod, the free end of the piston rod of the telescopic pneumatic rod is contacted with or connected with the supporting component, and the pusher is fixed on the emitter provided with the invention.
Compared with the hinge structure between the existing wing and the supporting component, the hinge structure is simple in structure, and folding, moving and unfolding actions of the wing can be achieved only through the springs and the sliding grooves.
The emitter comprises an emitter body with a wing mechanism, wherein the wing mechanism is the wing mechanism, and the bottom of the sliding plate is fixed on an emitter body shell.
According to the emitter, on the basis of completing the folding of the wings of the emitter body, the wings can be moved along the flying direction, so that the whole length of the emitter is shortened, a shorter emitting barrel can be adopted, and the convenience of a user in using the emitter is improved.
A method of reducing the axial length of an emitter comprising the steps of:
pushing the right wing and the left wing to enable the guide shaft to enter the steering section along the arc connecting section between the positioning section and the steering section;
secondly, continuing to push the wing to the flying direction of the emitter body, wherein the guide shaft rotates around a certain point between the support component and the wing in the process of moving along the groove wall of the section in the steering section, so that the forward distance of the support component along the flying direction of the wing is greater than the forward distance of the guide shaft, and the two wings are gradually closed in the tail direction;
step three, continuing to push the wing to the flight direction of the emitter body so that the guide shaft enters the inclined pushing section along the arc connecting section between the steering section and the inclined pushing section;
and fourthly, continuing to push the wings to the flight direction of the emitter body, wherein the guide shaft rotates around a certain point between the support assembly and the wings in the process of moving along the groove wall of the section in the inclined pushing section until the two wings overlap and enter the limiting section at the same time, and the wings are folded at the tail of the aircraft.
Through the steps, the folding of the wing and the movement of the wing along the flying direction are completed, so that the axial length of the emitter body of the folded wing is shortened, a shorter emitting barrel can be adopted, and the convenience of a user in using the invention is improved
Due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. according to the wing mechanism, the emitter and the method for shortening the axial length of the emitter, the folding of the wings and the movement of the wings along the flight direction are completed, so that the whole length of the wing mechanism is shortened, a shorter emitting cylinder can be adopted, and the convenience of a user in using the wing mechanism is improved;
2. the wing mechanism, the emitter and the method for shortening the axial length of the emitter are simple in hinge structure between the wing and the supporting component, and folding, moving and unfolding actions of the wing can be realized only by the springs and the sliding grooves;
3. the wing mechanism, the emitter and the method for shortening the axial length of the wing mechanism are inconvenient to transport and inconvenient to assemble when the wing is integrally arranged because the wing is relatively long; the device is split into multiple sections, so that the convenience of transportation and assembly is improved, and the later maintenance cost is reduced.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
FIG. 1 is a schematic structural view of a wing mechanism;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is an exploded view of the wing mechanism;
FIG. 4 is a cross-sectional view of the support assembly;
FIG. 5 is a top view of the skateboard;
FIG. 6 is a schematic view of the structure of the chute;
FIG. 7 is a cross-sectional view of the wing mechanism from below;
FIG. 8 is a schematic view of the guide shaft moving to the steering section;
FIG. 9 is a cross-sectional view from below of FIG. 8;
FIG. 10 is a schematic view of the guide shaft moving to the tilt segment;
FIG. 11 is a cross-sectional view from below of FIG. 10;
FIG. 12 is a schematic view of the guide shaft moving to the stop segment;
FIG. 13 is a cross-sectional view from below of FIG. 12;
FIG. 14 is an exploded view of a wing;
fig. 15 is a schematic structural view of an emitter.
The reference numerals in the drawings indicate:
the device comprises a 1-right wing, a 2-right plate, a 3-left wing, a 4-left plate, a 5-sliding plate, a 6-sliding groove, a 7-positioning section, a 8-steering section, a 9-oblique pushing section, a 10-limiting section, a 11-guiding shaft, a 12-hinging shaft, a 13-bottom plate, a 14-positioning plate, a 15-screw, a 16-contact bearing, a 17-strip-shaped through hole, a 18-right through hole, a 19-left through hole, a 20-right annular groove, a 21-left annular groove, a 22-right clamping groove, a 23-left clamping groove, a 24-spring, a 25-baffle shaft, a 26-arc surface, a 27-flange plate, a 28-middle flange plate, a 29-end flange plate, a 30-clamping block, a 32-mounting through hole, a 33-baffle plate, a 34-connecting cylinder, a 35-matching bearing and a 36-hook component.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
The present invention will be described in detail with reference to fig. 1 to 15.
Example 1
As shown in fig. 1-15, the wing mechanism of the invention comprises a supporting component, a right plate 2 connected with a wing root of a right wing 1 and a left plate 4 connected with a wing root of a left wing 3, wherein one sides of the right plate 2 and the left plate 4, which are far away from the corresponding wing root, are respectively connected with the upper surface of the supporting component in a rotating way, a sliding plate 5 is slidably arranged at the bottom of the supporting component, the sliding direction of the supporting component on the sliding plate 5 is parallel to the flying direction of the wing, a sliding groove 6 is arranged on one side of the sliding plate 5, which is positioned in the moving direction of the supporting component, the sliding groove 6 comprises a positioning section 7, a steering section 8, an inclined pushing section 9 and a limiting section 10 which are sequentially communicated in an arc way and have the same width dimension, the extending direction of the positioning section 7 is parallel to the sliding direction of the supporting component, one side of the steering section 8, which is far away from the tail, is communicated with one end of the steering section 8, which is close to the tail, the other end of the inclined pushing section 8 extends towards the nose and is far away from the moving direction of the supporting component, and is communicated with one end of the inclined pushing section 9, which is close to the tail, the end of the supporting section 9, and the other end is communicated with the end, which is close to the end of the nose, and the limiting section 10, which is connected with the extending direction of the end in parallel with the extending direction of the direction;
the number of the sliding grooves 6 is two, and the sliding grooves are symmetrical along the sliding direction of the supporting component;
guide shafts 11 are arranged on the lower surfaces of the right plate 2 and the left plate 4 at the sides close to the corresponding wing roots, and the bottom ends of the guide shafts 11 are respectively inserted into one sliding groove 6; when the right wing 1 and the left wing 3 are unfolded, the bottom end of the guide shaft 11 is positioned in the positioning section 7 and tangent to the groove wall on one side of the positioning section 7 close to the tail and the two groove walls parallel to the moving direction of the support component, and meanwhile, the support component moves to the position closest to the tail on the sliding path, wherein the position is the limit position, namely, the support component cannot move towards the tail continuously.
The right wing 1 and the left wing 3 are collectively referred to as wings.
In the initial state, as shown in fig. 1 and 7, the right wing 1 and the left wing 3 are in an unfolded state, the bottom end of the guide shaft 11 is located in the positioning section 7, and when flying, the front edge of the wing receives wind resistance F1, and at this time, the left wing rotates around two hinge points (i.e., the left hinge point and the middle hinge point), and the right wing also rotates around two hinge points (i.e., the right hinge point and the middle hinge point). After the left wing and the right wing are opened in place, the connecting angle between the three hinge points is 90 degrees, namely, the connecting line between the center point of the left hinge point and the center position of the middle hinge point and the connecting line between the center point of the right hinge point and the center position of the middle hinge point form a 90-degree connecting angle, and the guide shaft 11 is tangent with the groove wall on the positioning section 7, which is close to the tail side, and the two groove walls parallel to the moving direction of the supporting component, and is in a limiting state, and the guide shaft 11 only moves to one side in the flying direction; at the same time, the support assembly moves on the sliding path to a position closest to the tail, which is a limit position, and the support assembly can only move in the flying direction. Therefore, when the right wing receives wind resistance F1, the wind resistance F1 is opposite to the movable direction of the guide shaft 11 and the supporting component, as the middle hinge point can only slide along the axial direction, the force F2 applied to the right wing by the middle hinge point is vertical to the axial direction, the right hinge point can only move forwards at the tail end of the chute, the force applied to the right wing by the right hinge point is F3 in the vertical direction and F4 in the horizontal direction, at the moment, F1 and F3 are balanced, F2 and F4 are balanced, the right front wing is in a stress balance state, and the position is fixed. Similarly, the left wing keeps unchanged in position when being windward, and the two wings are in a locking state after being unfolded in place. When the wing is folded by unlocking, the wing rotating shaft at the left hinge point and the right hinge point is required to be pushed to move forwards.
When the wing needs to be folded and moved relative to the initial position, the following folding and moving steps are carried out:
step one, pushing the right wing 1 and the left wing 3 to enable the guide shaft 11 to enter the steering section 8 along the arc connecting section between the positioning section 7 and the steering section 8, as shown in fig. 8 and 9;
step two, continuing to push the wing to the flight direction of the wing, and rotating the wing around a certain point between the supporting component and the wing in the process that the guide shaft 11 moves along the groove wall of the section in the steering section 8, so that the forward distance of the supporting component along the flight direction of the wing is greater than the forward distance of the guide shaft 11, and the two wings are gradually closed in the tail direction, as shown in fig. 10 and 11;
step three, continuing to push the wing to the flight direction of the wing so that the guide shaft 11 enters the inclined pushing section 9 along the arc connecting section between the steering section 8 and the inclined pushing section 9, as shown in fig. 10 and 11;
and step four, continuing to push the wings in the flight direction of the wings, and rotating the wings around a certain point between the supporting component and the wings in the process that the guide shaft 11 moves along the groove wall of the inclined pushing section 9 until the two wings are overlapped and enter the limiting section 10 at the same time, as shown in fig. 12 and 13.
The folding of the wing and the movement of the wing along the flying direction are completed through the invention, so that the whole length of the wing mechanism is shortened, a shorter launching tube can be adopted, and the convenience of a user in using the invention is improved.
Example 2
The present embodiment is described with respect to a sliding connection between the support assembly and the slide 5.
As shown in fig. 1-7, in the wing mechanism of the present invention, a strip-shaped through hole 17 is provided on the sliding plate 5, and the long side in the cross section of the strip-shaped through hole 17 is parallel to the flight direction of the wing;
the support assembly comprises a base assembly and a hinge shaft 12 which are sequentially connected, the base assembly comprises a bottom plate 13, a positioning plate 14 and a plurality of screws 15, the bottom plate 13 and the positioning plate 14 are parallel to the sliding plate 5 and are respectively positioned below and above the sliding plate 5, one end of the hinge shaft 12 is connected with the bottom plate 13, and the other end of the hinge shaft 12 sequentially passes through a strip-shaped through hole 17 and the positioning plate 14 and then is sequentially connected with the right plate 2 and the left plate 4 in a rotating manner; the screws 15 are all located in the strip-shaped through holes 17, the screws 15 are divided into two groups, the two groups of screws are symmetrical along the sliding direction of the supporting component, the screws in each group are distributed along the sliding direction of the supporting component, the tail ends of the rod parts of the screws 15 penetrate through the positioning plates 14 and are connected with the bottom plate 13 in a threaded mode, contact bearings 16 are sleeved on the parts, located between the bottom plate 13 and the positioning plates 14, of the screws 15, and one sides, far away from the hinge shaft 12, of the contact bearings 16 and close to the walls of the strip-shaped through holes 17 are in contact with the walls of the holes.
The hinge shaft 12 is a middle hinge point. When the right wing 1 and the left wing 3 are unfolded, the screw 15 far away from the flying direction in the supporting component is contacted with the hole wall far away from the flying direction on the strip-shaped through hole 17, and the position where the supporting component is located is a limit position, namely the supporting component cannot move towards the tail.
Preferably, the screws 15 are four.
In the process of moving the support assembly along the flight direction, the contact bearing 16 is in contact with the hole wall where the long side is located in the cross section of the strip-shaped through hole 17, so that the linearity of the movement track of the support assembly is ensured, meanwhile, the friction force between the support assembly and the sliding plate 5 is reduced, and the friction loss is reduced, so that the support assembly is pushed more labor-saving and faster.
Example 3
The present embodiment is illustrative of the articulation between the support assembly and the wing.
As shown in fig. 1-7, the wing mechanism of the invention further comprises a hook-shaped cylindrical helical compression spring, a right through hole 18 matched with the hinge shaft 12 is arranged on the right plate 2, a right annular groove 20 coaxial with the right through hole 18 is arranged on the upper surface of the right plate 2, a right clamping groove 22 communicated with the right annular groove 20 is arranged on one side, close to the right wing 1, of the upper surface of the right plate 2, and the right plate 2 is sleeved on the hinge shaft 12 through the right through hole 18;
a left through hole 19 matched with the hinge shaft 12 is formed in the left plate 4, a left annular groove 21 coaxial with the left through hole 19 is formed in the lower surface of the left plate 4, a left clamping groove 23 communicated with the left annular groove 21 is formed in one side, close to the left wing 3, of the lower surface of the left plate 4, and the left plate 4 is sleeved on the hinge shaft 12 through the left through hole 19 and is positioned above the right plate 2;
the bottom of the spring 24 is inserted into the right annular groove 20, the hook component at the bottom of the spring is positioned in the right clamping groove 22, the top of the spring 24 is inserted into the left annular groove 21, the hook component at the top of the spring is positioned in the left clamping groove 23, and when the right wing 1 and the left wing 3 are in the unfolded flying state, the spring 24 is in the original state.
During the process of folding the wings and moving relative to the initial position, as each wing rotates, the hook members at the two ends of the spring 24 rotate with the two wings, respectively, so that the spring 24 is in a stretched state. When the wings are positioned in the launching cylinder after being folded, the wings are restrained by the cylinder wall and cannot stretch, so that the folded state is maintained; after firing, the wings are released from the constraint of the barrel wall and under the restoring force of a pusher and spring 24: the supporting component is pushed away from the flight direction by the pusher, so that the guide shaft 11 moves from the limit section 10 to the inclined pushing section 9, then the supporting component moves reversely along the flight direction under the action of the resultant force of the pusher and the spring 24, the wing is gradually unfolded, meanwhile, the guide shaft sequentially passes through the inclined pushing section 9 and the steering section 8 and then enters the positioning section 7 along the groove wall of the chute 6, at the moment, the wing completes unfolding action, and the stable unfolding state is maintained under the action of the spring 24 and the positioning section 7.
The pusher can adopt a telescopic pneumatic rod, the free end of the piston rod of the telescopic pneumatic rod is contacted with or connected with the supporting component, and the pusher is fixed on the emitter provided with the invention.
Compared with the hinge structure between the existing wing and the supporting component, the hinge structure is simple in structure, and folding, moving and unfolding actions of the wing can be achieved only through the springs and the sliding grooves 6.
Further, a blocking shaft 25 with an axis perpendicular to the sliding plate 5 is arranged on one side, close to the nose, of the upper surface of the right plate 2, an arc surface 26 is concaved inwards on one side, close to the right wing 1, of the left plate 4, and when the right wing 1 and the left wing 3 are in an unfolded flying state, the blocking shaft 25 is inscribed in the arc surface 26.
Further, the side of the right plate 2 far from the right wing 1 is a convex arc-shaped side wall, and the side wall is coaxial with the right through hole 18; the side of the left plate 4 far away from the left wing 3 is an outwards convex arc-shaped side wall, and the side wall is coaxial with the left through hole 19.
Further, a mounting through hole 32 with an axis coincident with the axis of the hinge shaft 12 is provided on the hinge shaft 12, a baffle 33 is provided on the top of the hinge shaft 12, a connecting cylinder 34 is provided on the lower surface of the baffle 33, and one end of the connecting cylinder 34 far from the baffle 33 is inserted into the central hole of the connecting cylinder 34 and connected with the hole wall.
And matching bearings are arranged between the matching surfaces of the left plate 4, the right plate 2 and the hinge shaft 12, so that the matching precision between the left plate 4, the right plate 2 and the hinge shaft 12 is improved, the friction loss in the rotation of the wing is reduced, and the generation of gaps is prevented.
Example 4
In this embodiment, the chute 6 is described.
As shown in fig. 1-7, an airfoil mechanism according to the present invention comprises an angle α formed between the extending direction of the turning section 8 and the moving direction of the supporting component, 30 ° < α <80 °, and an angle β formed between the extending direction of the oblique pushing section 9 and the extending direction of the turning section 8, 95 ° < β <160 °, preferably, α is 40 °, and β is 110 °.
Example 5
The embodiment is to explain the wing.
As shown in fig. 14, in the wing mechanism of the present invention, the right wing 1 and the left wing 3 are collectively called as wings, the wings include a root wing plate 27, a middle wing plate 28 and an end wing plate 29 which are sequentially clamped, one end of the root wing plate 27 far from the wing root and one end of the end wing plate 29 close to the wing root are both provided with clamping blocks 30, two ends of the middle wing plate 28 are both provided with clamping grooves 31, and the clamping grooves 31 are respectively matched with one clamping block 30.
Because the wing is relatively long, when the wing is integrally arranged, the wing is not only inconvenient to transport, but also inconvenient to assemble; the device is split into multiple sections, so that the convenience of transportation and assembly is improved, and the later maintenance cost is reduced.
Example 6
As shown in fig. 15, a projectile includes a projectile body 37 having a wing mechanism as described above, and the bottom of the slide 5 is fixed to the casing of the projectile body 37.
According to the emitter, the folding of the wing and the movement of the wing along the flying direction are completed, so that the whole length of the emitter is shortened, a shorter emitting barrel can be adopted, and the convenience of a user in using the emitter is improved.
Example 7
The present embodiment is described for fixing the slide plate 5.
As shown in fig. 1-13 and 15, the sliding plate 5 is fixed on the housing by fastening screws, both sides of the upper surface of the sliding plate 5 are milled with open grooves 38, the bottoms of the open grooves 38 are provided with a plurality of connecting through holes 39, and the fastening screws respectively pass through one connecting through hole 39 and are in threaded connection with the housing.
In the invention, the left and right refer to the left and right of the wing in the flying process, and the upper and lower are relative to the illustration and the upper and lower of the wing in the normal flying state.
Two connecting through holes 39 are formed in each open groove 38, and the fastening screw may be an inner hexagonal screw, an outer hexagonal screw, a countersunk screw, or the like. The slide plate 5 is made of a lightweight steel plate.
Example 8
A method of reducing the axial length of an emitter comprising the steps of:
step one, pushing the right wing 1 and the left wing 3 to enable the guide shaft 11 to enter the steering section 8 along the arc connecting section between the positioning section 7 and the steering section 8, as shown in fig. 8 and 9;
step two, continuing to push the wing to the flying direction of the emitter body 37, and rotating the wing around a certain point between the supporting component and the wing in the process that the guide shaft 11 moves along the groove wall of the turning section 8, so that the forward distance of the supporting component along the flying direction of the wing is greater than the forward distance of the guide shaft 11, and the two wings are gradually closed in the tail direction, as shown in fig. 10 and 11;
step three, continuing to push the wing to the flying direction of the emitter body so that the guide shaft 11 enters the inclined pushing section 9 along the arc connecting section between the steering section 8 and the inclined pushing section 9, as shown in fig. 10 and 11;
and fourthly, continuing to push the wings to the flight direction of the emitter body, and rotating the wings around a certain point between the supporting component and the wings in the process that the guide shaft 11 moves along the groove wall of the inclined pushing section 9 until the two wings are overlapped and enter the limiting section 10 at the same time, wherein the wings are folded at the tail of the aircraft as shown in fig. 12 and 13.
Through the steps, the folding of the wing and the movement of the wing along the flying direction are completed, so that the length dimension of the emitter body in the axial direction after the wing is folded is shortened, a shorter emitting barrel can be adopted, and the convenience of a user in using the invention is improved.
In the invention, the structural arrangement of the left plate and the right plate can be mutually exchanged, and the operation sequence of the left wing and the right wing is exchanged in the folding and moving steps.
The above description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that are not creatively contemplated by those skilled in the art within the technical scope of the present invention should be included in the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope defined by the claims.
Claims (8)
1. The utility model provides a wing mechanism, includes supporting component, connects right side board (2) of right wing (1) wing root and connects left board (4) of left wing (3) wing root, keep away from on right side board (2) and the left board (4) and all rotate with supporting component's upper surface and be connected, its characterized in that: the bottom of the supporting component is provided with a sliding plate (5) in a sliding manner, the sliding direction of the supporting component on the sliding plate (5) is parallel to the flight direction of the wing, one side of the sliding plate (5) which is positioned in the moving direction of the supporting component is provided with a sliding groove (6), the sliding groove (6) comprises a positioning section (7), a steering section (8), an inclined pushing section (9) and a limiting section (10) which are communicated in sequence in an arc manner and have consistent width sizes, the extending direction of the positioning section (7) is parallel to the sliding direction of the supporting component, one side of the positioning section (7) which is far away from the tail is communicated with one end of the steering section (8) which is close to the tail, the other end of the steering section (8) extends to one end of the inclined pushing section (9) which is close to the tail, the other end of the inclined pushing section (9) extends to one end of the head which is close to the moving direction of the supporting component, the extending direction of the limiting section (10) is communicated with one end of the inclined pushing section which is close to the tail, and the extending direction of the limiting section (10) is parallel to the sliding direction of the supporting component; the number of the sliding grooves (6) is two, and the sliding grooves are symmetrical along the sliding direction of the supporting component; guide shafts (11) are arranged on the lower surfaces of the right plate (2) and the left plate (4) and close to one side of the corresponding wing root, and the bottom ends of the guide shafts (11) are respectively inserted into one sliding groove (6); when the right wing (1) and the left wing (3) are unfolded, the bottom end of the guide shaft (11) is positioned in the positioning section (7) and tangent to the groove wall on one side of the positioning section (7) close to the tail and two groove walls parallel to the moving direction of the support component, and meanwhile, the support component moves to a position closest to the tail on a sliding path, wherein the position is an extreme position;
a strip-shaped through hole (17) is formed in the sliding plate (5), and the long side of the cross section of the strip-shaped through hole (17) is parallel to the flight direction of the wing; the support assembly comprises a base assembly and a hinge shaft (12) which are sequentially connected, the base assembly comprises a bottom plate (13), a positioning plate (14) and a plurality of screws (15), the bottom plate (13) and the positioning plate (14) are parallel to the sliding plate (5) and are respectively positioned below and above the sliding plate (5), one end of the hinge shaft (12) is connected with the bottom plate (13), and the other end of the hinge shaft (12) sequentially passes through the strip-shaped through hole (17) and the positioning plate (14) and then is sequentially connected with the right plate (2) and the left plate (4) in a rotating manner; the screws (15) are all positioned in the strip-shaped through holes (17), the plurality of screws (15) are divided into two groups, the two groups of screws are symmetrical along the sliding direction of the supporting component, the screws in each group are distributed along the sliding direction of the supporting component, the tail ends of the rod parts of the screws (15) penetrate through the positioning plates (14) and are in threaded connection with the bottom plates (13), contact bearings (16) are sleeved on the parts, positioned between the bottom plates (13) and the positioning plates (14), of the screws (15), and one sides, far away from the hinge shafts (12), of the contact bearings (16) and close to the hole walls of the strip-shaped through holes (17) are in contact with the hole walls; when the right wing (1) and the left wing (3) are unfolded, the screws (15) far away from the flying direction in each group of screws are contacted with the hole wall far away from the flying direction on the strip-shaped through hole (17);
an included angle alpha is formed between the extending direction of the steering section (8) and the moving direction of the supporting component, 30 degrees < alpha <80 degrees, and an included angle beta is formed between the extending direction of the inclined pushing section (9) and the extending direction of the steering section (8), 95 degrees < beta <160 degrees.
2. A wing mechanism as claimed in claim 1, wherein: the novel hinge comprises a hinge shaft (12), and is characterized by further comprising a hook-shaped cylindrical helical compression spring, wherein a right through hole (18) matched with the hinge shaft (12) is formed in the right plate (2), a right annular groove (20) coaxial with the right through hole (18) is formed in the upper surface of the right plate (2), a right clamping groove (22) communicated with the right annular groove (20) is formed in the upper surface of the right plate (2), and the right plate (2) is sleeved on the hinge shaft (12) through the right through hole (18); a left through hole (19) matched with the hinge shaft (12) is formed in the left plate (4), a left annular groove (21) coaxial with the left through hole (19) is formed in the lower surface of the left plate (4), a left clamping groove (23) communicated with the left annular groove (21) is formed in the lower surface of the left plate (4), and the left plate (4) is sleeved on the hinge shaft (12) through the left through hole (19) and is positioned above the right plate (2); the bottom of the spring (24) is inserted into the right annular groove (20), the hook part at the bottom of the spring is positioned in the right clamping groove (22), the top of the spring (24) is inserted into the left annular groove (21), the hook part at the top of the spring is positioned in the left clamping groove (23), and when the right wing (1) and the left wing (3) are in an unfolded flying state, the spring (24) is in a normal state.
3. A wing mechanism as claimed in claim 2, wherein: a blocking shaft (25) with an axis perpendicular to the sliding plate (5) is arranged on one side, close to the nose, of the upper surface of the right plate (2), an arc surface (26) is concaved inwards on one side, close to the right wing (1), of the left plate (4), and when the right wing (1) and the left wing (3) are in an unfolded flying state, the blocking shaft (25) is inscribed in the arc surface (26).
4. A wing mechanism according to any one of claims 2 to 3, wherein: the hinge is characterized in that an installation through hole (32) with the axis coincident with the axis of the hinge (12) is formed in the hinge (12), a baffle (33) is arranged at the top of the hinge (12), a connecting cylinder (34) is arranged on the lower surface of the baffle (33), and one end, far away from the baffle (33), of the connecting cylinder (34) is inserted into a central hole of the connecting cylinder (34) and is connected with a hole wall.
5. A wing mechanism according to any one of claims 1 to 3, wherein: the wing comprises a root wing plate (27), an intermediate wing plate (28) and an end wing plate (29) which are sequentially clamped, wherein clamping blocks (30) are arranged at one end, far away from a wing root, of the root wing plate (27) and one end, close to the wing root, of the end wing plate (29), clamping grooves (31) are formed in two ends of the intermediate wing plate (28), and the clamping grooves (31) are matched with one clamping block (30) respectively.
6. A projectile comprising a projectile body (37) having a wing mechanism, characterized in that: the wing mechanism is as claimed in any one of claims 1 to 5, the bottom of the slide plate (5) being fixed to the outer shell of the emitter body (37).
7. An emitter according to claim 6, wherein: the sliding plate (5) is fixed on the shell through fastening screws, open grooves (38) are milled on two sides of the upper surface of the sliding plate (5), a plurality of connecting through holes (39) are formed in the bottoms of the open grooves (38), and the fastening screws respectively penetrate through one connecting through hole (39) and are in threaded connection with the shell.
8. A method of reducing the axial length of an emitter, comprising: comprising an emitter according to any of claims 6-7, comprising the steps of:
pushing the right wing (1) and the left wing (3) to enable the guide shaft (11) to enter the steering section (8) along the arc connecting section between the positioning section (7) and the steering section (8);
secondly, continuing to push the wing to the flying direction of the emitter body (37), and rotating the wing around a certain point between the supporting component and the wing in the process that the guide shaft (11) moves along the groove wall of the steering section (8) so as to enable the distance of the supporting component moving forward along the flying direction of the wing to be larger than the distance of the guide shaft (11), thereby gradually closing the two wings in the tail direction;
step three, continuing to push the wing to the flying direction of the emitter body so that the guide shaft (11) enters the inclined pushing section (9) along the arc connecting section between the steering section (8) and the inclined pushing section (9);
and fourthly, continuing to push the wings to the flight direction of the emitter body, and rotating the wings around a certain point between the supporting component and the wings in the process that the guide shaft (11) moves along the groove wall of the inclined pushing section (9) until the two wings overlap and enter the limiting section (10) at the same time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811448978.9A CN109625242B (en) | 2018-11-28 | 2018-11-28 | Wing mechanism, emitter and method for shortening axial length of emitter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811448978.9A CN109625242B (en) | 2018-11-28 | 2018-11-28 | Wing mechanism, emitter and method for shortening axial length of emitter |
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| CN109625242A CN109625242A (en) | 2019-04-16 |
| CN109625242B true CN109625242B (en) | 2024-02-06 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112665467B (en) * | 2020-12-23 | 2022-04-12 | 北京航天飞腾装备技术有限责任公司 | Novel variable sweepback wing mechanism |
| CN114275144B (en) * | 2021-12-30 | 2022-11-11 | 哈尔滨工业大学 | Mechanical linkage device for wing unfolding time sequence control |
| CN114872881B (en) * | 2022-07-08 | 2022-09-20 | 西安羚控电子科技有限公司 | Large-stroke telescopic wing and unmanned aerial vehicle |
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| CN109625242A (en) | 2019-04-16 |
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