CN111306996B - Ammunition flight resistance device - Google Patents
Ammunition flight resistance device Download PDFInfo
- Publication number
- CN111306996B CN111306996B CN202010076518.9A CN202010076518A CN111306996B CN 111306996 B CN111306996 B CN 111306996B CN 202010076518 A CN202010076518 A CN 202010076518A CN 111306996 B CN111306996 B CN 111306996B
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- China
- Prior art keywords
- resistance
- locking
- unfolding
- pin
- cabin body
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- 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
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
Abstract
The invention discloses an ammunition flight resistance device, which realizes the initial locking of a resistance piece through an initial locking and unlocking mechanism and the structural matching between the initial locking and unlocking mechanism and the resistance piece, realizes the separation from the resistance piece through the axial movement of the initial locking and unlocking mechanism to realize the unlocking of the resistance piece, keeps the structural integrity of the resistance piece and improves the unfolding synchronism; the expansion limiting of the resistance pieces is realized by adding the expansion locking mechanism, the structure of the resistance device is simplified, and the resistance control of ammunition flying has the characteristics of convenience in operation, high reliability and the like.
Description
Technical Field
The invention belongs to the general technical field of small tactical ammunition structures, and particularly relates to an ammunition flight resistance device.
Background
In order to realize the drop speed control of the guided rocket at different ranges, a bullet speed control device is generally adopted. The working principle is as follows: in the initial stage after the guided rocket is launched, the bullet speed control device is in a closed state, and the good pneumatic appearance of the bullet body is maintained; and after reaching the preset flying height, the missile-borne flying controller gives out a deployment signal of the missile speed control device. After the bullet speed control device is unfolded, the flight resistance coefficient of the guided rocket is obviously increased, and the control of the tail speed of ammunition flight can be effectively realized.
The technical scheme adopted by the common bullet speed control device comprises the following steps: 1) a D-shaped ring resistance mechanism; 2) an "iris" resistance mechanism; 3) paddle type resistance mechanisms, and the like. They each have some drawbacks and limitations: the D-shaped ring resistance mechanism has smaller radial area, the correction capability of the range is limited, and the resistance sheet needs larger centrifugal overload when being unfolded, so the D-shaped ring resistance mechanism is a passive unfolding mechanism; the iris resistance mechanism has complex structural design and high assembly precision requirement, is difficult to ensure the unfolding synchronism and has the risk of ammunition instability in the unfolding process; paddle type resistance mechanism mainly relies on the torsional spring deployment mechanism moment of torsion of its root to realize launching through the release of initiating explosive actuator, every resistance piece, and the mechanism is more complicated to there is the poor problem of resistance piece expansion synchronism.
In summary, a method which can meet the requirement of good unfolding synchronism and has the characteristics of simple structure, convenience in operation, high reliability and the like is lacked in the prior art.
Disclosure of Invention
In view of the above, the invention provides an ammunition flight resistance device, which realizes an ammunition flight resistance device with high unfolding synchronism.
The invention provides an ammunition flight resistance device which comprises an initial locking and unlocking mechanism, an unfolding driving mechanism, an unfolding locking mechanism, a resistance sheet and a cabin body, wherein the initial locking and unlocking mechanism, the unfolding driving mechanism and the unfolding locking mechanism are all arranged in the cabin body; resistance piece set up in the external surface of cabin, resistance piece and the external surface swing joint of cabin:
the initial locking and unlocking mechanism is clamped with the resistance sheet; the initial locking and unlocking mechanism moves along the axial direction of the cabin under the control of a deployment signal, and the resistance sheet is unlocked through the axial movement; the unfolding driving mechanism utilizes spring energy storage to extend outwards of the cabin body, and is matched with the resistance plates to convert the extending movement into the unfolding of the resistance plates; the expansion locking mechanism utilizes spring energy storage to extend outwards of the cabin body, the expansion locking mechanism is matched with the resistance plate, the expansion locking mechanism extends to limit the resistance plate at a set expansion position, and the resistance plate forms resistance to ammunition flying.
Further, the initial locking and unlocking mechanism comprises a pin puller, a pin puller bracket, a clamping ring and a clamping ring pressure spring, the rear end of the pin puller is in sleeve joint clearance fit with the pin puller bracket through a cylindrical surface, and the pin puller bracket is fixed in the cabin body; the front end of the pin puller is fixedly connected with the clamping ring; the clamping ring is clamped with the resistance sheet; the snap ring pressure spring is compressed and sleeved outside the pin puller, and the snap ring pressure spring is connected with the snap ring and the resistance piece in a clamped mode to provide pretightening force.
Further, the device comprises more than two resistance plates, and one end of each resistance plate, which is connected with the cabin, is provided with a conical opening.
Further, the unfolding locking mechanism comprises a locking pin and a pressure spring, the locking pin is preset in a blind hole in the root area of the cabin, and when the resistance plate is unfolded to a set position, the locking pin moves into the conical hole to lock the resistance plate.
Further, the initial locking and unlocking mechanism is driven by a firer to move along the axial direction of the cabin body under the control of the unfolding signal.
Has the beneficial effects that:
according to the invention, the initial locking and unlocking mechanism is adopted, the initial locking of the resistance piece is realized through the structural matching between the initial locking and unlocking mechanism and the resistance piece, the resistance piece is unlocked through the separation of the initial locking and unlocking mechanism and the resistance piece, the structural integrity of the resistance piece is maintained, and the unfolding synchronism is improved; the expansion limiting of the resistance pieces is realized by adding the expansion locking mechanism, the structure of the resistance device is simplified, and the resistance control of ammunition flying has the characteristics of convenience in operation, high reliability and the like.
Drawings
Fig. 1 is a schematic view of a folding structure of an ammunition flight resistance device provided by the invention.
Fig. 2 is a schematic diagram of a 25-degree unfolded state of a resistance sheet of the ammunition flight resistance device provided by the invention.
The device comprises an adapter ring 1, a snap ring 2, a nut 3, a pin puller 4, a snap ring pressure spring 5, a resistance sheet 6, a pin puller support 7, a support 8, a push rod 9, an opening spring 10, a plug cover 11, a buffer spring 12, a rotating shaft 13, a locking pin 14, a cabin body 15 and a locking spring 16.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The ammunition flight resistance device provided by the invention comprises an initial locking and unlocking mechanism, a spreading driving mechanism, a spreading locking mechanism, a resistance plate and a cabin body, as shown in figure 1. The initial locking and unlocking mechanism, the unfolding driving mechanism and the unfolding locking mechanism are all arranged in the cabin body, and the resistance sheet is arranged on the outer surface of the cabin body and movably connected with the outer surface of the cabin body.
Initial locking release mechanism sets up in the cavity at resistance device cabin body middle part, initial locking release mechanism is including pulling out round pin ware 4, pulling out round pin ware support 7, snap ring 2 and snap ring pressure spring 5, the rear end of pulling out round pin ware 4 and pulling out round pin ware support 7 fixed connection, pulling out round pin ware support 7 through screw radial connection on the resistance device cabin body, the front end of pulling out the round pin ware cup joints with 2 face of cylinder of snap ring, and restrict its axial displacement and compress snap ring pressure spring 5 through nut 3, snap ring and resistance piece joint, the compression of snap ring pressure spring cup joints outside pulling out the round pin ware, under snap ring 2 and the joint of pulling out round pin ware support 7 is spacing jointly, provide initial pretightning force to the snap ring with the joint of resistance piece. The snap ring 2 is lapped with the resistance sheet 6 under the elastic action of the snap ring pressure spring 5, and the function of initially locking the resistance sheet is realized. After the guided rocket is launched, at the scheduled time of the trajectory, the flight controller gives an ignition signal of the pin puller 4, and under the action of gunpowder and fuel gas of the pin puller 4, the pin puller 4 overcomes the elasticity of a pressure spring of the snap ring and drives the snap ring to move backwards, so that the pin puller is originally attached to a resistance piece, constrained by the snap ring, on the outer surface of the cabin body of the resistance device, and is released from constraint to realize unlocking.
The number of the resistance plates is 4-8, and the resistance plates are tightly attached to the outer surface of the cabin body 15 of the bullet speed control device under the constraint of the snap ring 2 in the initial flying stage of ammunition.
The unfolding driving mechanism is arranged in the middle of the cabin body 15 and consists of a support 8, a mandril 9, an opening spring 10 and a blocking cover 11. The support 8 is connected circumferentially to the resistance device housing 15 by means of screws. The mandril 9 provided with the opening spring 10 is pressed into the support in advance and is restrained by the blocking cover 11, when the resistance sheet is in a folding state, the opening spring 10 is in a compression state by the limit of the resistance sheet, and the spring force is stored. After the resistance piece is unlocked, the ejector rod 9 provides initial thrust for the expansion of the resistance piece under the action of the elastic force of the expanding spring 10, and the resistance piece is pushed to rotate around the rotating shaft 13. Due to the action of the ejector rod 9, the resistance sheet can overcome the pneumatic resistance to be unfolded under the working condition that the guided rocket has a certain attack angle.
The unfolding locking mechanism is formed by combining a locking pin 14, a locking spring 16 and a buffer spring 12, wherein the locking pin 14 is pre-arranged in a blind hole in the root area of the cabin body of the resistance device. Before the resistance sheet is unfolded in place, the locking spring 16 is in a compressed state by the limit of the resistance sheet and stores the spring force; in the process of unfolding the resistance plate, the buffer spring 12 is attached to the outer surface of the resistance plate and elastically deforms to reduce the impact in the process of unfolding the resistance plate; when the resistance plate is unfolded to the proper position, the locking pin 14 is pushed into the tapered hole at the root of the resistance plate under the action of the locking spring 16 and locked.
Example (b):
referring to fig. 1, in a resistance device based on a pin puller according to a preferred embodiment of the present invention, an adapter ring 1, a snap ring 2, a resistance device cabin 15 and a resistance plate 6 are of an integral structure and are machined and formed from an aluminum alloy 2a 12-T4. The locking and unlocking mechanism is arranged in a cavity structure in the resistance device cabin body 15 and consists of a pin puller 4, a pin puller bracket 7, a clamping ring 2, a clamping ring locking spring 5, a nut 3 and a switching ring 1. At the tail part of the resistance device cabin body 15, the rotating shaft 13 sequentially penetrates through the resistance device cabin body 15 and the round holes on the resistance plates 6, so that the resistance plates 6 are connected with the resistance device cabin body 15. The resistance plate 6 is also connected with the resistance device cabin 15 through a rotating shaft 13. Under the elastic force action of the snap ring pressure spring 5, the two resistance pieces are in lap joint with the snap ring 2 and limited by the snap ring 2, so that the locking function is realized and the two resistance pieces are in a completely folded state. The unfolding mechanism consists of a support 8, a mandril 9, an opening spring 10 and a blocking cover 11. The opening spring 10 and the mandril 9 are arranged in the support 8 in advance and are restrained by the blanking cover 11, so that the opening spring 10 is in a compressed state to store compression force. After the installation, the deployment mechanism is attached to the resistance device cabin 15. The locking buffer mechanism consists of a buffer reed 12, a locking pin 14 and a locking spring 16. Before the resistance plate is installed, the locking spring 16 and the locking pin 14 are arranged in a blind hole in the resistance device cabin body 15, and the buffer spring 12 is matched with the locking pin 14 and fixed on the resistance device cabin body 15 by screws. After the two resistance sheets are installed, the locking spring 16 is in a compressed state by the limit of the resistance sheet to store the compression force.
After receiving the unlocking signal, the thrust generated by the action of the fuel gas in the pin puller 4 overcomes the elasticity of the snap ring pressure spring 5, and drives the snap ring 2 restrained by the nut 3 to move backwards together, so that the locking of the resistance piece is released. And after the ejector rod 9 and the opening spring 10 which are preset in the support 8 are unlocked, the opening spring 10 loses restraint, pressure is released, the ejector rod 9 is pushed to move, and the resistance plate 6 rotates around the rotating shaft 13. The mandril 9 is pushed for 16mm stroke, so that the expansion angle of the resistance plate 6 reaches 25 degrees, and the resistance plate of the resistance device can be initially expanded under the condition of small attack angle flight of the guided rocket, as shown in figure 2.
After the rotation angle of the resistance sheet 6 reaches 25 degrees around the rotating shaft 13, the aerodynamic force becomes the main driving force for unfolding the resistance sheet 6. When resistance piece 6 expanded to 90, the taper hole on the resistance piece 6 moved to the position with the 14 coaxial lines of fitting pin, and locking spring 16 under every resistance piece lost the restraint, and release pressure pushes up fitting pin 14 in the taper type fitting hole of resistance piece root, realizes the locking of resistance piece. Meanwhile, the buffering reed 12 realizes buffering and shock absorption in the process of expanding the resistance sheet, and ensures that the resistance sheet is normally expanded and locked.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. An ammunition flight resistance device is characterized by comprising an initial locking and unlocking mechanism, an unfolding driving mechanism, an unfolding locking mechanism, a resistance sheet and a cabin body, wherein the initial locking and unlocking mechanism, the unfolding driving mechanism and the unfolding locking mechanism are all arranged in the cabin body; resistance piece set up in the external surface of cabin, resistance piece and the external surface swing joint of cabin:
the initial locking and unlocking mechanism is clamped with the resistance sheet; the initial locking and unlocking mechanism moves along the axial direction of the cabin under the control of a deployment signal, and the resistance sheet is unlocked through the axial movement; the unfolding driving mechanism utilizes spring energy storage to extend outwards of the cabin body, and is matched with the resistance plates to convert the extending movement into the unfolding of the resistance plates; the unfolding locking mechanism utilizes spring energy storage to extend outwards of the cabin body, the unfolding locking mechanism is matched with the resistance plate, the extension of the unfolding locking mechanism limits the resistance plate at a set unfolding position, and the resistance plate forms resistance to ammunition flying;
the initial locking and unlocking mechanism comprises a pin puller, a pin puller bracket, a clamping ring and a clamping ring pressure spring, the rear end of the pin puller is in sleeve joint clearance fit with the pin puller bracket through a cylindrical surface, and the pin puller bracket is fixed in the cabin body; the front end of the pin puller is fixedly connected with the clamping ring; the clamping ring is clamped with the resistance sheet; the snap ring pressure spring is compressed and sleeved outside the pin puller and provides pretightening force for clamping the snap ring and the resistance sheet;
the device comprises more than two resistance sheets, wherein one end of each resistance sheet connected with the cabin body is provided with a taper hole; the unfolding locking mechanism comprises a locking pin and a pressure spring, the locking pin is preset in a blind hole in the root area of the cabin body, and when the resistance plate is unfolded to a set position, the locking pin moves into the conical hole to lock the resistance plate;
after receiving the unlocking signal, the thrust generated by the action of the fuel gas in the pin puller overcomes the elasticity of the snap ring pressure spring, drives the snap ring restrained by the nut to move backwards together, and releases the locking of the resistance piece; after the resistance sheet is unlocked, the opening spring loses restraint, releases pressure, pushes the ejector rod to move, and realizes that the resistance sheet rotates around the rotating shaft; the ejector rod is pushed for 16mm stroke, and the spreading angle of the resistance sheet reaches 25 degrees;
after the rotation angle of the resistance sheet around the rotating shaft reaches 25 degrees, the aerodynamic force becomes the main driving force for unfolding the resistance sheet; when the resistance pieces are unfolded to 90 degrees, the taper holes on the resistance pieces move to the positions coaxial with the locking pins, the locking springs below each resistance piece lose restraint, pressure is released, and the locking pins are pushed into the taper holes at the roots of the resistance pieces, so that the resistance pieces are locked;
the resistance pieces are 2.
2. The apparatus of claim 1, wherein the initial locking and unlocking mechanism is actuated by a fire in an axial direction along the cabin under the control of a deployment signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010076518.9A CN111306996B (en) | 2020-01-23 | 2020-01-23 | Ammunition flight resistance device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010076518.9A CN111306996B (en) | 2020-01-23 | 2020-01-23 | Ammunition flight resistance device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111306996A CN111306996A (en) | 2020-06-19 |
| CN111306996B true CN111306996B (en) | 2022-07-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010076518.9A Active CN111306996B (en) | 2020-01-23 | 2020-01-23 | Ammunition flight resistance device |
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| Country | Link |
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| CN (1) | CN111306996B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212268B (en) * | 2021-12-27 | 2023-10-31 | 西安现代控制技术研究所 | Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft |
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|---|---|---|---|---|
| CN201895770U (en) * | 2010-09-29 | 2011-07-13 | 贵州航天控制技术有限公司 | Locking and unlocking mechanism for aircraft airfoil |
| RU2478907C1 (en) * | 2011-12-14 | 2013-04-10 | Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Unfolding wing of two-stage rocket |
| KR101345669B1 (en) * | 2013-09-03 | 2013-12-30 | 국방과학연구소 | Portable guided missile having unfolding device for wing |
| CN107576228A (en) * | 2017-08-15 | 2018-01-12 | 兰州空间技术物理研究所 | A kind of high synchronism rudder face folding and expanding mechanism |
| CN109595997A (en) * | 2019-01-02 | 2019-04-09 | 西安微电子技术研究所 | The synchronization four-way folding wings locking unfolding mechanism and its method of anti high overload impact |
| CN110230955A (en) * | 2019-06-28 | 2019-09-13 | 浙江理工大学 | Retaining mechanism and its expansion locking method is unfolded in submersible folding wings synchronous horizontal |
| CN110481756A (en) * | 2019-08-26 | 2019-11-22 | 北京机电工程研究所 | A kind of folding minute vehicle of the rudder wing |
-
2020
- 2020-01-23 CN CN202010076518.9A patent/CN111306996B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201895770U (en) * | 2010-09-29 | 2011-07-13 | 贵州航天控制技术有限公司 | Locking and unlocking mechanism for aircraft airfoil |
| RU2478907C1 (en) * | 2011-12-14 | 2013-04-10 | Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Unfolding wing of two-stage rocket |
| KR101345669B1 (en) * | 2013-09-03 | 2013-12-30 | 국방과학연구소 | Portable guided missile having unfolding device for wing |
| CN107576228A (en) * | 2017-08-15 | 2018-01-12 | 兰州空间技术物理研究所 | A kind of high synchronism rudder face folding and expanding mechanism |
| CN109595997A (en) * | 2019-01-02 | 2019-04-09 | 西安微电子技术研究所 | The synchronization four-way folding wings locking unfolding mechanism and its method of anti high overload impact |
| CN110230955A (en) * | 2019-06-28 | 2019-09-13 | 浙江理工大学 | Retaining mechanism and its expansion locking method is unfolded in submersible folding wings synchronous horizontal |
| CN110481756A (en) * | 2019-08-26 | 2019-11-22 | 北京机电工程研究所 | A kind of folding minute vehicle of the rudder wing |
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| CN111306996A (en) | 2020-06-19 |
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