CN213120304U - Fin stabilizer for rifling gun projectile - Google Patents
Fin stabilizer for rifling gun projectile Download PDFInfo
- Publication number
- CN213120304U CN213120304U CN202021450503.6U CN202021450503U CN213120304U CN 213120304 U CN213120304 U CN 213120304U CN 202021450503 U CN202021450503 U CN 202021450503U CN 213120304 U CN213120304 U CN 213120304U
- Authority
- CN
- China
- Prior art keywords
- tail
- wing
- projectile
- seat
- spring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model relates to a line thorax big gun shot fin stabilising arrangement, it includes spring, solid wing ring, tail wing seat and a plurality of fin, wherein: the tail wing seat is sleeved on a tail pipe of the projectile, the end part of the tail wing seat is abutted against the tail part of the projectile, and a plurality of hinged supports are arranged on the tail wing seat; the fixed wing ring is movably sleeved on the tail pipe relative to the tail wing seat; the spring is arranged on the tail pipe, one end of the spring is connected with the wing fixing ring, and the other end of the spring is connected with the tail pipe close to one end of the projectile; one end of each tail wing is hinged with a hinged support of the tail wing seat, and a hook-shaped part is arranged at the bottom of the hinged part of each tail wing; the end face, opposite to the hook-shaped part, of the wing fixing ring is provided with an annular groove capable of containing the hook-shaped part. The utility model facilitates the packaging, transportation and loading of the projectile, improves the service performance, and solves the problem that the empennage expands in the chamber to damage the bore; the size and the structure of each part can be adjusted according to the specific structure of the projectile, and the projectile bullet device is high in flexibility and applicability.
Description
Technical Field
The utility model relates to a shot fin design technical field especially relates to a rifle big gun shot fin stabilising arrangement, is applicable to the rifle big gun of medium-and-large-bore.
Background
At present, a rotary stabilization and tail fin stabilization mode is adopted for a plurality of projectiles, and the method for solving the problem of unfolding of a tail fin in a chamber generally is to design the gravity center of the tail fin at one side close to the axis of the projectile, so that the tail fin is close to the axis of the projectile due to the fact that the overload tail fin can generate a turning moment during launching. Some of the ammunition can also hoop a circle of copper wires on the tail wing to play an auxiliary role, and after the ammunition is taken out of the chamber, the copper wires are sheared by the centrifugal force of the tail wing and then are unfolded. The structural design can not avoid that some fins deviate from the axis under the action of gravity and contact the bore, and the fins can scratch the bore when a projectile moves in the bore, so that the service life of the gun barrel is shortened. In addition, the consistency of the sheared copper wires after the shot is taken out of the chamber cannot be ensured.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a simple structure, reliability are high, the suitability is strong, can carry out the cartridge fin stabilising arrangement of suitable adjustment according to the shot structure of difference.
The utility model provides a technical scheme that its technical problem adopted is: the rifle big gun shot fin stabilising arrangement, including spring, solid wing ring, empennage seat and a plurality of fin, wherein: the tail wing seat is sleeved on a tail pipe of the projectile, the end part of the tail wing seat is abutted against the tail part of the projectile, and a plurality of hinged supports are arranged on the tail wing seat; the fixed wing ring is movably sleeved on the tail pipe relative to the tail wing seat; the spring is arranged on the tail pipe, one end of the spring is connected with the wing fixing ring, and the other end of the spring is connected with the tail pipe close to one end of the projectile; one end of each tail wing is hinged with a hinged support of the tail wing seat, and a hook-shaped part is arranged at the bottom of the hinged part of each tail wing; the end face, opposite to the hook-shaped part, of the wing fixing ring is provided with an annular groove capable of containing the hook-shaped part.
In a preferred embodiment of the present invention, the tail wing seat is a conical cover structure with a neck, the neck is provided with an internal thread, and the hinged support is uniformly distributed on the conical surface of the tail wing seat, and the conical surface is arranged towards the projectile.
In a preferred embodiment of the present invention, the threaded connection between the tail tube of the projectile and the tail wing seat is provided with a shoulder, and the height of the shoulder does not exceed the neck surface of the tail wing seat.
In a preferred embodiment of the present invention, the fin fixing ring is in clearance fit with the neck of the tail fin seat.
In a preferred embodiment of the present invention, the fin is a bevel edge structure for limiting the spreading angle of the fin in the relative outer side of the hinge.
The utility model provides a preferred embodiment of chamber big gun shot fin stabilising arrangement, still be equipped with the radome fairing between shot and the afterbody, the radome fairing is acceptd fin stabilising arrangement, just relative each on the radome fairing the fin is equipped with and dodges the groove.
In a preferred embodiment of the present invention, the tail fin stabilizing device for a rifling gun projectile is further provided with a belt.
Compared with the prior art, the utility model provides a rifling big gun shot fin stabilising arrangement's beneficial effect is: the utility model discloses through add solid wing ring, and increase on the fin and collude the shape portion, and design out the structure of solid wing ring, fin and the elastic coefficient and the length of spring through accurate calculation, utilize the centrifugal force distance of fin and the overload moment that solid wing ring produced, the fin is in the contraction state when realizing the shot in non-launch state and thorax internal motion, is in the expansion state after going out the big gun muzzle, has made things convenient for the shot to pack, transport, loads, has improved the service performance, has effectively solved the fin again and has expanded the problem of damaging the bore in the bore; the device can adjust the size and the structure of each part according to the specific structure of the projectile, and has high flexibility and strong applicability.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained without inventive work, wherein:
fig. 1 is a schematic structural view of a projectile tail fin stabilizing device of a rifling gun provided by the utility model;
FIG. 2 is a force analysis diagram of a single tail wing provided by the present invention;
fig. 3 is a partial enlarged view provided in fig. 1.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example one
Referring to fig. 1 and 3, the cartridge fin stabilizing device 1 of the rifling gun according to the present embodiment includes a spring 101, a wing fixing ring 102, a fin base 103, and a plurality of fins 104, wherein:
the tail wing seat 103 is sleeved on the tail pipe 201 of the projectile 2, the end part of the tail wing seat is abutted against the tail part 202 of the projectile, and a plurality of hinged supports 1030 are arranged on the tail wing seat 103;
the wing fixing ring 102 is movably sleeved on the tail pipe 201 along the axial direction of the tail pipe 201 relative to the tail wing seat 103;
the spring 101 is arranged on the tail pipe 201, one end of the spring 101 is connected with the wing fixing ring 102, the other end of the spring is connected with the tail pipe 201 close to one end of the projectile 2, and the thrust of the wing fixing ring 102 is provided by the spring 101 so that the wing fixing ring has the thrust towards the direction of a tail wing seat;
one end of each tail wing 104 is hinged with a hinged support 1030 of the tail wing seat 103, generally, the tail wing 104 is fixedly mounted on the hinged support 1030 through a pin and can freely rotate around the pin, and a hook 1042 is arranged at the bottom of the hinged position of the tail wing 104;
the end surface of the wing fixing ring 102 opposite to the hook-shaped part 1042 is provided with an annular groove 1020 capable of accommodating the hook-shaped part.
In the specific implementation: the spring, the fixed wing ring and the tail wing seat are sequentially assembled on a tail pipe of the projectile, then the tail wing is connected to the tail wing seat through the pin, the fixed wing ring is pushed along the axis direction of the tail pipe to compress the spring, the length of the hook-shaped part of the tail wing is made to be longer, the tail wing is folded by a hand, the fixed wing ring is released, the annular groove of the fixed wing ring is sleeved on the hook-shaped part of the tail wing, the restraint effect of the tail wing is guaranteed, and the stabilizing device is completely installed.
The shape and the size of the fixed wing ring and the shape and the size of the empennage are matched, designed and processed, so that the empennage cannot interfere with each other when rotating, the fixed wing ring can be designed into a conical shape according to the empennage shown in figure 3, and the annular groove of the fixed wing ring is designed into a conical groove according to the hook-shaped part of the empennage shown in figure 3. Meanwhile, in order to deploy the tail wing to the designed position, the opposite outer side of the tail wing 104 at the hinge joint is provided with a bevel 1040 structure for limiting the deployment angle of the tail wing, and the bevel design is designed according to the deployment angle of the tail wing.
The working principle is as follows: when the projectile is in a non-launching state, the spring is compressed to generate elastic force to push the wing fixing ring to lock the empennage, so that the empennage is prevented from being unfolded; when the projectile is in the in-bore motion state, due to the fact that the powder gas acts to generate overload, the wing fixing ring can generate larger force opposite to the motion direction of the projectile on the tail wing, the tail wing is locked reliably, and the projectile is prevented from unfolding in a bore; when the projectile flies out of the bore, the projectile rotates to generate centrifugal force, the tail wing has the tendency of unfolding around the pin, at the moment, the overload disappears, the constraint force of the fixed wing ring on the tail wing is reduced, the tail wing cannot be locked continuously, and the tail wing can be unfolded smoothly. After the empennage is unfolded in place, the fixed wing ring moves backwards for a certain distance along the axis of the projectile under the push of the spring to clamp the unfolded empennage, so that the stability of the flying state of the fixed wing ring is ensured.
The present embodiment performs stress analysis according to the displacement in the launching process to know that: as shown in fig. 2, during the launching process, the gunpowder gas applies work to the projectile to generate overload, so that the projectile has acceleration along the axis direction of the projectile and angular acceleration rotating around the axis of the projectile, therefore, the force applied to the tail wing is the pressure of the fixed wing ring, the force generated by the spring, the centrifugal force, the pressure of the gunpowder gas to the wing (the force applied to the wing is negligible due to the sealing effect of the belt and the small force area), and other forces are not considered to be influenced slightly. Calculating the formula:
bFL1＝(N+Ft)L2
in the formula: f- -centrifugal force of a single airfoil; n- -pressure generated by the stationary wing ring; b- -number of fins; ft-the force generated by the spring; l is1，L2A moment arm.
When in the bore, the mass and the structural size of the wing fixing ring and the wing and the elastic coefficient and the compression amount of the spring are determined according to the formula, so that bFL1＜(N+Ft)L2The wing pieces can be close to the axis when the projectile is launched; after the shot leaves the chamber, the initial speed of the shot is not high and the windward side of the fixed wing ring is small due to the disappearance of overload, the influence of air resistance on the fixed wing ring can be ignored, and bFL is enabled to be at the moment1＞FtL2And the fins can be unfolded after the projectile leaves the chamber, so that the projectile can stably fly.
The empennage can be guaranteed to be folded towards the ammunition shaft in the bore and unfolded after being taken out of the bore by adjusting the mass of the fixed wing ring, the elastic coefficient of the spring and the mass of the wing pieces in the stabilizing device, so that the problem that the empennage scratches the bore when unfolded in the bore is effectively avoided, and the service life of the gun barrel is prolonged.
Example two
Based on the first embodiment, specifically, the tail vane seat 103 of the present embodiment is a conical cover structure with a neck 1032, the cover structure can reduce the weight of the device and the projectile body, the neck 1032 is provided with an internal thread, the hinge supports 1030 are uniformly distributed on the conical surface of the tail vane seat 103, and the conical surface is arranged toward the projectile.
Preferably, a shoulder 2012 is arranged at the threaded connection part of the tail pipe 201 of the projectile 2 and the tail wing seat 103, the shoulder is arranged to limit the tail wing seat, so that the reliability and firmness of the installation structure of the tail wing seat are enhanced, and the height of the shoulder is not more than the surface of the neck part of the tail wing seat, so that the shoulder does not influence the movement of the wing fixing ring.
The wing securing ring 102 is clearance fitted with the neck 1032 of the tail seat 103.
In the above embodiment, a fairing 203 is further provided between the projectile 2 and the tail 202, the fairing 203 accommodates the tail stabilizer 1, and the fairing 203 is provided with an escape groove 2030 corresponding to each tail.
In the above embodiment, the tail 202 is further provided with a belt 204.
The device ingeniously utilizes overload during projectile launching and centrifugal force during rotation to control the contraction and expansion of the tail wing, and has the characteristics of easiness in processing, simplicity in assembly, reliability in work and strong applicability.
The above only is the embodiment of the present invention, not limiting the scope of the present invention, all the equivalent structures or equivalent processes made by the present specification can be changed, or directly or indirectly applied to other related technical fields, and all the same principles are included in the protection scope of the present invention.
Claims (7)
1. The utility model provides a rifle big gun shot fin stabilising arrangement which characterized in that: including spring, solid wing ring, tail wing seat and a plurality of fin, wherein:
the tail wing seat is sleeved on a tail pipe of the projectile, the end part of the tail wing seat is abutted against the tail part of the projectile, and a plurality of hinged supports are arranged on the tail wing seat;
the fixed wing ring is movably sleeved on the tail pipe relative to the tail wing seat;
the spring is arranged on the tail pipe, one end of the spring is connected with the wing fixing ring, and the other end of the spring is connected with the tail pipe close to one end of the projectile;
one end of each tail wing is hinged with a hinged support of the tail wing seat, and a hook-shaped part is arranged at the bottom of the hinged part of each tail wing;
the end face, opposite to the hook-shaped part, of the wing fixing ring is provided with an annular groove capable of containing the hook-shaped part.
2. The cartridge projectile tail stabilizer of claim 1, wherein: the tail wing seat is a conical cover structure with a neck, the neck of the tail wing seat is provided with internal threads, and the hinged support is uniformly distributed on the conical surface of the tail wing seat, and the conical surface is arranged towards the projectile.
3. The cartridge projectile tail stabilizer of claim 2, wherein: the threaded connection part of the tail pipe of the projectile and the tail wing seat is provided with a shoulder, and the height of the shoulder does not exceed the surface of the neck of the tail wing seat.
4. The cartridge projectile tail stabilizer of claim 2, wherein: the wing fixing ring is in clearance fit with the neck of the tail wing seat.
5. The cartridge projectile tail stabilizer of claim 1, wherein: and the opposite outer side of the tail at the hinged position is provided with a bevel edge structure for limiting the unfolding angle of the tail.
6. The cartridge projectile tail stabilizer of claim 1, wherein: and a fairing is arranged between the projectile and the tail part and accommodates the tail fin stabilizing device, and each tail fin is provided with an avoiding groove relative to the fairing.
7. The cartridge projectile tail stabilizer of claim 1, wherein: the tail part is also provided with a spring band.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021450503.6U CN213120304U (en) | 2020-07-21 | 2020-07-21 | Fin stabilizer for rifling gun projectile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021450503.6U CN213120304U (en) | 2020-07-21 | 2020-07-21 | Fin stabilizer for rifling gun projectile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213120304U true CN213120304U (en) | 2021-05-04 |
Family
ID=75678615
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021450503.6U Active CN213120304U (en) | 2020-07-21 | 2020-07-21 | Fin stabilizer for rifling gun projectile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213120304U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113607003A (en) * | 2021-08-09 | 2021-11-05 | 南京理工大学工程技术研究院有限公司 | Structure for improving opening reliability of tail wing of smoothbore gun |
| CN113607002A (en) * | 2021-08-09 | 2021-11-05 | 南京理工大学工程技术研究院有限公司 | Structure for improving revolving speed of smooth-bore gun projectile |
| RU225333U1 (en) * | 2023-10-19 | 2024-04-16 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | PROJECTILE STABILIZER |
-
2020
- 2020-07-21 CN CN202021450503.6U patent/CN213120304U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113607003A (en) * | 2021-08-09 | 2021-11-05 | 南京理工大学工程技术研究院有限公司 | Structure for improving opening reliability of tail wing of smoothbore gun |
| CN113607002A (en) * | 2021-08-09 | 2021-11-05 | 南京理工大学工程技术研究院有限公司 | Structure for improving revolving speed of smooth-bore gun projectile |
| RU225333U1 (en) * | 2023-10-19 | 2024-04-16 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | PROJECTILE STABILIZER |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN213120304U (en) | Fin stabilizer for rifling gun projectile | |
| AU2002323387B2 (en) | Precision guided extended range artillery projectile tactical base | |
| US8640589B2 (en) | Projectile modification method | |
| EP2165152B1 (en) | Hybrid spin/fin stabilized projectile | |
| US20190368846A1 (en) | Artillery projectile with a piloted phase | |
| US4815682A (en) | Fin-stabilized subcaliber projectile and method of spin tuning | |
| US4869442A (en) | Self-deploying airfoil | |
| AU2002323387A1 (en) | Precision guided extended range artillery projectile tactical base | |
| US4728058A (en) | Airborne body with over-caliber sized guidance mechanism | |
| US11754379B2 (en) | Space saving wing stowage | |
| US4607810A (en) | Passive constraint for aerodynamic surfaces | |
| US6168111B1 (en) | Fold-out fin | |
| US4351503A (en) | Stabilized projectiles | |
| US7004425B2 (en) | Flying body for firing from a tube with over-caliber stabilizers | |
| CN2193180Y (en) | Fire-extinguishing shell and firing apparatus | |
| US4389028A (en) | Flat trajectory projectile | |
| US4523728A (en) | Passive auto-erecting alignment wings for long rod penetrator | |
| US4998994A (en) | Aerodynamically compliant projectile nose | |
| US4901646A (en) | Fin-stabilized subcaliber projectile | |
| KR101931034B1 (en) | Tail fin unit and fastening method thereof for flight stabilized projectile | |
| US10309755B1 (en) | Spin stabilized projectile for smoothbore barrels | |
| US5182419A (en) | Saboted projectile | |
| KR101262696B1 (en) | Protective cover of missile, missile having the same and impact relief method of missile | |
| RU2251068C1 (en) | Mode of increasing range of an artillery shell's flight and a device for its realization | |
| US6769643B2 (en) | Projectile to be fired from a barrel with an over-caliber control surface assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |