CN115014132A - Controllable unfolding mechanism for target missile rudder piece and target missile provided with same - Google Patents
Controllable unfolding mechanism for target missile rudder piece and target missile provided with same Download PDFInfo
- Publication number
- CN115014132A CN115014132A CN202210195207.3A CN202210195207A CN115014132A CN 115014132 A CN115014132 A CN 115014132A CN 202210195207 A CN202210195207 A CN 202210195207A CN 115014132 A CN115014132 A CN 115014132A
- Authority
- CN
- China
- Prior art keywords
- rudder
- unfolding
- locker
- sheet
- controllable
- 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.)
- Pending
Links
Images
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention discloses a controllable unfolding mechanism of a target missile rudder piece, and belongs to the field of missile attitude control. The unfolding mechanism arranged in the steering engine cabin section comprises an electric actuating mechanism, a control circuit and a torsion spring unfolding mechanism unit; the electric actuating mechanism comprises a rudder blade locker, a rudder blade locking screw, a ball screw reducer, a direct current motor, a motor fixing base and an encoder; the rudder sheet locker is provided with a rudder sheet locker clamping groove, and the rudder sheet is embedded into the rudder sheet locker clamping groove when being folded; when the target projectile launches the barrel, the control circuit receives an instruction, the direct current motor drives the nut of the ball screw reducer to do linear motion, and then the rudder sheet locker is driven to do linear motion, so that the position of the rudder sheet and the position of the clamping groove of the rudder sheet locker are relieved, and the rudder sheet can be controllably unfolded under the action of the torsion spring. The rudder piece unfolding mechanism is simple in structure and quick in response, can accurately control the unfolding time of the rudder piece, and facilitates test circulation when the unfolding reliability of the folded rudder piece is tested.
Description
Technical Field
The invention belongs to the field of missile attitude control, and particularly relates to a controllable unfolding mechanism for a target missile folding rudder piece.
Background
With the development of missile technology and launching technology, higher requirements are put forward on the functions of small missiles with local lethality.
The small missile has different shapes and functions according to different application environments and application requirements, wherein the small missile with the folded rudder sheet is more applied. In most cases, the target missile of the folded rudder sheet is shot out of the bin in the launch canister (box), and the rudder sheet is generally folded inside the missile body in order to reduce the size, volume and weight of the launch canister (box). The rudder piece folding-unfolding principle of the small missile is as follows: the missile is placed in a launching barrel (box) before launching, a rudder sheet is hinged with a shell of the missile, a torsion spring is arranged between the rudder sheet and the shell of the missile, the missile is placed in the launching barrel (box), the rudder sheet starts to be folded under the action of the launching barrel wall, the torsion spring starts to store energy, the rudder sheet is completely folded when the torsion spring stores energy to the maximum extent, and the rudder sheet is limited by the launching barrel wall of the rudder sheet at the moment; after the missile is launched, the rudder sheet loses the limit of the launching cylinder wall, and is unfolded under the action of the torsion spring, and the completely unfolded state of the rudder sheet is realized when the torsion spring completely releases energy. According to the traditional rudder piece unfolding mode, when the rudder piece leaves the launching tube, the rudder piece starts to unfold, and the unfolding time cannot be accurately controlled. In order to ensure the unfolding reliability of the folded rudder sheet, a conventional rudder sheet folding-unfolding cyclic test is required.
Along with the improvement of the requirement on the initial launching speed of the missile, the requirement on delayed unfolding of the folded rudder piece of the small missile is brought, the folded rudder piece cannot be unfolded when the missile with the delayed unfolding function leaves the launching tube, and then the missile is unfolded when an unfolding instruction is received, so that the initial speed of the missile is prevented from being lost. The prior art is realized mainly through spring mechanism after the initiating explosive device mode unblock, like patent CN 108871103A/a time delay deployment mechanism of folding rudder piece of small-size guided missile, its deployment mechanism structure is complicated low reliability, and its drive assembly is the initiating explosive device, need load the initiating explosive device repeatedly when carrying out the cycle test, and test efficiency is lower, and safe cost and test cost all spend quite a lot.
Disclosure of Invention
Aiming at the defects or the improvement requirements of the prior art, the invention provides a controllable unfolding mechanism of a target projectile rudder piece and a target projectile provided with the controllable unfolding mechanism. The invention mainly solves the problems that controllable unfolding of the rudder sheet is realized under the driving of a motor, the unfolding time is accurate and controllable, and the test is convenient to be circularly carried out when the unfolding reliability of the folded rudder sheet is tested.
In order to achieve the purpose, the invention aims to provide a controllable unfolding mechanism for rudder pieces of a target projectile, which is arranged in a steering engine cabin section of the target projectile and is used for locking and controllably unfolding four rudder pieces, wherein the controllable unfolding mechanism is arranged in the center of the steering engine cabin section and comprises an electric actuating mechanism, a control circuit and a torsion spring unfolding mechanism unit;
the electric actuating mechanism comprises a rudder blade locker, a rudder blade locking screw, a ball screw reducer, a direct current motor, a motor fixing base and an encoder; the torsion spring unfolding mechanism unit comprises a folding shaft, a control surface pin and a torsion spring; the four rudder pieces, the electric actuating mechanism, the control circuit and the torsion spring unfolding mechanism unit are all arranged on the body in the steering engine cabin section;
the rudder sheet locker is provided with a rudder sheet locker clamping groove, and the rudder sheet is embedded into the rudder sheet locker clamping groove to be in a locking state when being folded; the rudder sheet locker is fixedly connected with the ball screw reducer through a rudder sheet locking screw, and the ball screw reducer drives the rudder sheet locker to move linearly along the axis of the cabin section, so that the rudder sheet is separated from the limit of the rudder sheet locker clamping groove, and the rudder sheet is unlocked and unfolded.
Preferably, the target projectile rudder piece is restrained by the rudder piece locker to be in a folding locking state before launching, and a torsion spring in the torsion spring unfolding mechanism is in a torsional energy storage state.
As a further preference, the four rudder pieces are embedded into the rudder sheet locker clamping grooves and are arranged at intervals of 90 degrees.
Preferably, the rudder blade locker and a screw of the ball screw reducer rotate coaxially to drive a nut of the ball screw reducer to move linearly.
Preferably, the direct current motor is positioned below the ball screw speed reducer and is axially and radially fixed on the motor fixing base through a support and a locking screw; the rudder sheet locker, the direct current motor and an output shaft of the ball screw reducer are coaxial.
Preferably, the encoder is mounted at the tail of the dc motor, and is integrated with the motor, and is configured to detect a rotation angle of the dc motor shaft and feed back the rotation angle to the control circuit to control the rotation angle of the dc motor shaft.
Preferably, the control circuit is provided with a cover plate protection device, and holes are reserved in the cover plate and used for connecting the outgoing lines of the direct current motor and the encoder to the control circuit.
Preferably, the unfolding time of the target missile rudder piece is accurately controllable, and the error of the unfolding time of the rudder piece from the time when the target missile control system sends out a rudder piece unfolding instruction to the time when the rudder piece starts to unfold can be controlled within 10%.
A target projectile is provided with the controllable target projectile rudder piece unfolding mechanism.
Compared with the prior art, the controllable unfolding mechanism for the target missile rudder piece has the following advantages or beneficial effects:
(1) the controllable unfolding mechanism of the target missile rudder piece has the advantages of simple structure, quick response and high reliability, and can fully meet the working requirement of folding the rudder piece.
(2) After the target projectile containing the folded rudder sheet is launched out of the cabin, the rudder sheet locker can be driven by an electric mechanism to rotate around the central shaft of the cabin section of the steering engine to realize the controllable unfolding of the folded rudder sheet, and the unfolding time is accurate and controllable.
(3) The invention mainly solves the problems that the unfolding time of the rudder can be accurately controlled, and the test circulation is convenient to carry out when the unfolding reliability of the folded rudder is tested.
Drawings
FIG. 1 is a schematic cross-sectional view of a controllable deployment mechanism of a target missile rudder sheet in the invention;
FIG. 2 is a schematic perspective view of the rudder blade locker of the present invention;
FIG. 3 is a top view of the controllable deployment mechanism of the projectile rudder in the present invention;
FIG. 4 is a schematic sectional view showing the structure of the torsion spring unwinding mechanism unit according to the present invention;
in the figure, 1-a steering engine cabin section, 2-a rudder sheet, 3-a rudder sheet locker, 4-a rudder sheet locking screw, 5-a ball screw reducer, 6-a direct current motor, 7-a motor fixing base, 8-an encoder, 9-a torsion spring, 10-a rudder surface pin, 11-a folding shaft, 12-a body, 13-a control circuit, 14-a cover plate, 15-an outgoing line through hole, 16-a support, 17-a locking screw and 31-a rudder sheet locker clamping groove.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and operate, and thus should not be construed as limiting the present invention.
As shown in figure 1, a controllable unfolding mechanism of the target missile rudder piece is arranged in a steering engine cabin section (1) and is used for locking and controllably unfolding four rudder pieces (2). The controllable unfolding mechanism is arranged in the center of the steering engine cabin section (1) and comprises an electric actuating mechanism, a control circuit (13) and a torsion spring unfolding mechanism unit.
The four rudder blades (2), the electric actuating mechanism and control circuit (13) and the torsion spring unfolding mechanism unit are all arranged on the body (12) in the steering engine cabin section (1). The electric actuating mechanism comprises a rudder blade locker (3), a rudder blade locking screw (4), a ball screw reducer (5), a direct current motor (6), a motor fixing base (7) and an encoder (8).
As shown in figure 1, the direct current motor (6) is positioned below the ball screw speed reducer (5), and is axially and radially fixed on the motor fixing base (7) through a support (16) and a locking screw (17), and the rudder sheet locker (3), the direct current motor (6) and an output shaft of the ball screw speed reducer (5) are coaxial. The ball screw reducer (5) is the most mechanically used transmission element, and consists of a screw rod, a nut, a steel ball, a preforming piece, a reverser and a dust remover, and has the function of converting rotary motion into linear motion. The direct current motor (6) drives a screw rod of the ball screw speed reducer (5) to rotate after the control circuit (13) is electrified, so that a nut of the ball screw speed reducer (5) is driven to linearly move along the central shaft of the steering engine cabin section (1).
As shown in fig. 1, the encoder (8) is installed at the tail of the dc motor (6), and is designed integrally with the motor, and is used for detecting the rotation angle of the motor shaft and feeding back the rotation angle to the control circuit (13) to control the rotation angle of the shaft of the dc motor (6). In fig. 1, a cover plate (14) is arranged on the control circuit (13) for physical protection and plays a role in heat dissipation of the power device. Holes are reserved on the cover plate (14) and used for connecting the outgoing lines of the direct current motor (6) and the encoder (8) to the control circuit (13).
As shown in the schematic perspective view of the rudder blade locker (3) in fig. 2, rudder blade locker slots (31) are formed in the rudder blade locker (3), and the four rudder blades (2) are inserted into the rudder blade locker slots (31) and are in a locked state when being folded. Direct current motor (6) drive ball screw reduction gear (5) nut carries out linear motion, and then makes rudder blade locker (3) prolong steering wheel cabin section (1) center pin linear motion about 10mm, when rudder blade locker (3) linear motion about 5mm, rudder blade (2) break away from the spacing of rudder blade locker draw-in groove (31), makes rudder blade (2) be in the unblock state, and rudder blade (2) expand rapidly under the effect of torsional spring (9).
As shown in figure 3, the included angle between the four rudder blades (2) is set to be 90 degrees, the direct current motor (6) and the ball screw speed reducer (5) are axially and radially fixed on the motor fixing base (7) through the locking screw (17), and the motor fixing base (7) is fixed on the body (12) below through the locking screw (17).
The torsion spring deployment mechanism unit shown in fig. 4 includes a folding shaft (11), a control surface pin (10), and a torsion spring (9). Before unfolding, the rudder blade (2) is in a folded state under the restraint of the rudder blade locker (3), and at the moment, the torsion spring (9) is in a torsion energy storage state; when an unlocking instruction is received, namely the rudder sheet locker (3) releases the position limitation of the clamping groove, the folding shaft (11) rapidly pushes the rudder sheet (2) to rotate and unfold around the rudder surface pin (10) under the action of the torsion spring (9).
The working process of the controllable unfolding mechanism for the target projectile rudder sheet comprises the following steps:
firstly, a target projectile needs to be installed in a launching tube, an internal battery can be activated before launching, a control system is powered on, and the rudder piece (2) is in a folding and locking state at the moment. When a target projectile launches a barrel, a control system sends a deployment signal to a controllable deployment unit under the condition that the rudder piece can be safely deployed, after a control circuit (13) of the controllable deployment unit receives an instruction, a direct current motor (6) is driven to drive a lead screw of a ball screw speed reducer (5) to rotate, so that a nut of the ball screw speed reducer (5) is driven to linearly move, the rudder piece locker (3) linearly moves about 10mm along a central shaft of a rudder cabin section (1), when the rudder piece locker (3) linearly moves about 5mm, the rudder piece (2) is separated from the limit of a rudder piece locker clamping groove (31), the rudder piece (2) is in an unlocking state, and the folding shaft (11) rapidly pushes the rudder piece (2) to rotate and deploy around a rudder face pin (10) under the action of a torsion spring (9).
According to the design parameters of the controllable unfolding unit, the unfolding instruction of the rudder blade (2) is sent from the target missile control system to the unfolding of the rudder blade (2), the time is about 300ms, the complete unfolding time of the rudder blade (2) is about 100ms under the action of the torsion spring (9), and the total time is about 400 ms. The pneumatic controllable unfolding mechanism of the target missile rudder sheet can ensure the accurate unfolding time of the rudder sheet (2), and comprises the steps of sending an unfolding instruction of the rudder sheet (2) from a control system, starting unfolding the rudder sheet (2), and finishing unfolding the rudder sheet (2), wherein all the time is controllable, the error of the unfolding time can be controlled within 10 percent, the error does not exceed 20ms, and the requirement on the consistency of the control system can be met.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made without departing from the spirit and scope of the invention.
Claims (9)
1. A controllable unfolding mechanism for rudder pieces of a target projectile is arranged in a steering engine cabin section of the target projectile and is used for locking and controllably unfolding four rudder pieces, and is characterized in that the controllable unfolding mechanism is arranged in the center of the steering engine cabin section and comprises an electric actuating mechanism, a control circuit and a torsion spring unfolding mechanism unit;
the electric actuating mechanism comprises a rudder blade locker, a rudder blade locking screw, a ball screw reducer, a direct current motor, a motor fixing base and an encoder; the torsion spring unfolding mechanism unit comprises a folding shaft, a control surface pin and a torsion spring; the four rudder pieces, the electric actuating mechanism, the control circuit and the torsion spring unfolding mechanism unit are all arranged on the body in the steering engine cabin section;
the rudder sheet locker is provided with a rudder sheet locker clamping groove, and the rudder sheet is embedded into the rudder sheet locker clamping groove to be in a locking state when being folded; the rudder sheet locker is fixedly connected with the ball screw reducer through a rudder sheet locking screw, and the ball screw reducer drives the rudder sheet locker to move linearly along the axis of the cabin section, so that the rudder sheet is separated from the limit of the rudder sheet locker clamping groove, and the rudder sheet is unlocked and unfolded.
2. The controllable target projectile rudder piece unfolding mechanism according to claim 1, wherein the target projectile rudder piece is restrained by a rudder piece locker to be in a folding locking state before launching, and a torsion spring in the torsion spring unfolding mechanism is in a torsional energy storage state.
3. The controllable unfolding mechanism of target missile rudder sheet according to claim 1, wherein the four rudder sheets are embedded into the rudder sheet locker clamping grooves and are arranged at intervals of 90 degrees.
4. The controllable unfolding mechanism of target missile rudder piece as claimed in claim 1, wherein the rudder piece locker and the screw of the ball screw reducer rotate coaxially to drive the nut of the ball screw reducer to move linearly.
5. The controllable unfolding mechanism of the target projectile rudder blade as claimed in claim 1, wherein the direct current motor is positioned below the ball screw reducer and axially and radially fixed on the motor fixing base through a support and a locking screw; the rudder sheet locker, the direct current motor and an output shaft of the ball screw reducer are coaxial.
6. The controllable unfolding mechanism for a target missile rudder sheet as claimed in claim 1, wherein the encoder is installed at the tail part of the direct current motor and is integrated with the motor for detecting the rotation angle of the direct current motor shaft and feeding back to the control circuit for controlling the rotation angle of the direct current motor shaft.
7. The controllable unfolding mechanism of target missile rudder piece as claimed in claim 1, wherein the control circuit is protected by a cover plate, and holes are reserved on the cover plate and used for connecting outgoing lines of a direct current motor and an encoder to the control circuit.
8. The controllable unfolding mechanism of the target missile rudder piece according to claim 1, wherein the unfolding time of the target missile rudder piece is accurately controllable, and the error of the unfolding time of the rudder piece from the launching of the target missile control system to the beginning of the unfolding of the rudder piece can be controlled within 10%.
9. A projectile having mounted thereon a controllable deployment mechanism for a projectile rudder according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210195207.3A CN115014132A (en) | 2022-03-01 | 2022-03-01 | Controllable unfolding mechanism for target missile rudder piece and target missile provided with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210195207.3A CN115014132A (en) | 2022-03-01 | 2022-03-01 | Controllable unfolding mechanism for target missile rudder piece and target missile provided with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115014132A true CN115014132A (en) | 2022-09-06 |
Family
ID=83066670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210195207.3A Pending CN115014132A (en) | 2022-03-01 | 2022-03-01 | Controllable unfolding mechanism for target missile rudder piece and target missile provided with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115014132A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115451757A (en) * | 2022-09-13 | 2022-12-09 | 北京航星传动科技有限公司 | Grid rudder folding and unfolding actuating mechanism and servo system thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0184704A1 (en) * | 1984-11-24 | 1986-06-18 | DORNIER SYSTEM GmbH | Rudder actuator |
| EP0499907A2 (en) * | 1991-02-20 | 1992-08-26 | DIEHL GMBH & CO. | Projectile having deployable fins |
| CN108871103A (en) * | 2018-06-14 | 2018-11-23 | 湖北三江航天红峰控制有限公司 | A kind of miniature missile folds the delay unfolding mechanism of rudder piece |
| 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 |
-
2022
- 2022-03-01 CN CN202210195207.3A patent/CN115014132A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0184704A1 (en) * | 1984-11-24 | 1986-06-18 | DORNIER SYSTEM GmbH | Rudder actuator |
| EP0499907A2 (en) * | 1991-02-20 | 1992-08-26 | DIEHL GMBH & CO. | Projectile having deployable fins |
| CN108871103A (en) * | 2018-06-14 | 2018-11-23 | 湖北三江航天红峰控制有限公司 | A kind of miniature missile folds the delay unfolding mechanism of rudder piece |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115451757A (en) * | 2022-09-13 | 2022-12-09 | 北京航星传动科技有限公司 | Grid rudder folding and unfolding actuating mechanism and servo system thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114963883A (en) | Electric controllable unfolding mechanism for target projectile rudder piece and target projectile with same | |
| US7475846B2 (en) | Fin retention and deployment mechanism | |
| US6880780B1 (en) | Cover ejection and fin deployment system for a gun-launched projectile | |
| US7642492B2 (en) | Single-axis fin deployment system | |
| EP0622604B1 (en) | Rotationally mounted flexible band wing | |
| WO2002032762A3 (en) | Artillery launched flyer assembly | |
| US6446906B1 (en) | Fin and cover release system | |
| GB2246330A (en) | A mechanism for unlocking and swinging-out the control fins of a projectile. | |
| CN115014132A (en) | Controllable unfolding mechanism for target missile rudder piece and target missile provided with same | |
| CN102363444B (en) | Transverse folding mechanism for empennage | |
| CN109539902B (en) | Electric-drive folding wing system with large aspect ratio | |
| WO2020174448A1 (en) | Wing deployment and locking system | |
| US8878110B2 (en) | Projectile that includes propulsion system and launch motor on opposing sides of payload and method | |
| CN104713426A (en) | Slide wedge block type transverse foldable wing surface | |
| CN118004464A (en) | Can launch folding unmanned aerial vehicle and horn auto-lock and storage method thereof | |
| US7434762B2 (en) | Retractable thrust vector control vane system and method | |
| CN113008086A (en) | Dimensional folding structure of grid wing | |
| CN114963884A (en) | Pneumatic controllable unfolding mechanism for target projectile rudder piece and target projectile with pneumatic controllable unfolding mechanism | |
| US3515360A (en) | Pivot system for folding control surfaces | |
| US5085381A (en) | Deployable aerodynamic aerosurface | |
| US7100865B2 (en) | Method and apparatus for stowing and deploying control surfaces of a guided air vehicle | |
| CN115962685B (en) | Folding control surface locking and unfolding mechanism and guided projectile with same | |
| CN113218242B (en) | Universal vertical transmitting and turning device | |
| CN117585215B (en) | Folding wing of small unmanned aerial vehicle expands and locking mechanism and unmanned aerial vehicle | |
| JPH05296700A (en) | Power supply device for missile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |