CN114593644A - Restraining locking mechanism for limiting deflection and buffeting of plane rudder - Google Patents
Restraining locking mechanism for limiting deflection and buffeting of plane rudder Download PDFInfo
- Publication number
- CN114593644A CN114593644A CN202210089525.1A CN202210089525A CN114593644A CN 114593644 A CN114593644 A CN 114593644A CN 202210089525 A CN202210089525 A CN 202210089525A CN 114593644 A CN114593644 A CN 114593644A
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- CN
- China
- Prior art keywords
- limiting
- plate
- rudder
- unlocking
- fixing plate
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- 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.)
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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
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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
- F42B10/04—Stabilising arrangements using fixed fins
- F42B10/06—Tail fins
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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
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
A restraining and locking mechanism for limiting deflection and buffeting of a planar rudder comprises a limiting plate (1), a fixing plate (2), a shaft pin (3), an unlocking torsion spring (4), a gasket group (6) and a cushion pad (7); the limiting plate (1) and the fixing plate (2) are connected with the unlocking torsion spring (4) through the shaft pin (3), and have a tendency of twisting towards the fixing plate (2) under the action of the unlocking torsion spring (4); the buffer pad (7) is arranged on the limit plate (1) and is used for buffering the buffeting of the plane rudder in a locking state; the gasket group (6) is positioned between the cushion pad (7) and the limiting plate (1) and used for improving the matching degree of the cushion pad (7) and the plane rudder surface; the adjacent part of the limiting plate (1) and the plane rudder is L-shaped, the L-shaped part is inserted into a gap between the plane rudder and the arrow body and abuts against the plane rudder, and the motion of the limiting plate (1) rotating around the shaft pin (3) to the fixing plate (2) is restrained, so that the deflection of the plane rudder is limited, buffeting is inhibited, and the locking function is realized.
Description
Technical Field
The invention relates to a plane rudder inhibition locking mechanism, in particular to an inhibition locking mechanism which is suitable for the deflection and buffeting inhibition functions of a plane rudder on a spacecraft.
Background
The high-altitude launch technology of the carrier rocket uses the airplane to carry the rocket to climb to a certain height and then launch, and the rocket is endowed with certain initial height and speed, so that the high-altitude launch technology is beneficial to reducing the requirement of the rocket on fuel carrying capacity and improving the range of the rocket, and has higher launch flexibility. When the rocket is hung and flies to be launched, the plane rudder on the rocket body bears larger pneumatic load, larger torque is generated on the steering engine, the locking function of the steering engine is disabled, and abnormal deflection towards a specific direction is generated. Meanwhile, due to the complex pneumatic environment during hanging and flying, a rudder system may generate large buffeting, and the functionality, safety and reliability of the equipment are also endangered.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the locking mechanism for restraining the deflection and buffeting of the plane rudder overcomes the defects of the prior art, prevents the plane rudder from generating abnormal deflection in a certain direction in the rocket hanging and flying stage, can restrain the buffeting of the plane rudder, can reduce the torque applied by the rudder body to a plane rudder control mechanism, has lower requirements on the locking performance of a steering engine, is beneficial to improving the launching reliability and reducing the launching cost.
The purpose of the invention is realized by the following technical scheme:
a restraining and locking mechanism for limiting deflection and buffeting of a planar rudder comprises a limiting plate, a fixing plate, a shaft pin, an unlocking torsion spring, a gasket group and a buffer pad;
the limiting plate and the fixing plate are connected with the unlocking torsion spring through a shaft pin, and have a tendency of twisting towards the fixing plate under the action of the unlocking torsion spring; the buffer cushion is arranged on the limiting plate and is used for buffering the buffeting of the plane rudder in a locking state; the gasket group is positioned between the cushion pad and the limiting plate and used for improving the matching degree of the cushion pad and the plane rudder surface; the adjacent parts of the limiting plate and the plane rudder are L-shaped, the L-shaped parts are inserted into a gap between the plane rudder and the arrow body and abut against the plane rudder, and the motion of the limiting plate rotating around the shaft pin to the fixing plate is restrained, so that the deflection of the plane rudder is limited, the buffeting is inhibited, and the locking function is realized.
In an embodiment of the present invention, the gasket set is composed of a plurality of gaskets, and the number of the gaskets is adjustable.
In an embodiment of the present invention, the manner of suppressing unlocking of the locking mechanism is: the plane rudder deflects towards the direction far away from the cushion pad, the contact between the cushion pad and the plane rudder is removed, and the plane rudder is not contacted with the L-shaped part of the limiting plate any more, so that the limiting plate can smoothly rotate around the shaft pin towards the fixing plate under the action of the unlocking torsion spring, and the limitation on the deflection range of the plane rudder is removed.
In one embodiment of the invention, the unlocking device further comprises a torsion spring positioning block arranged on the fixing plate and used for limiting the unlocking torsion spring.
In one embodiment of the invention, the device further comprises an unlocking guide block arranged on the fixing plate, and in the unlocking process, the plane rudder props against the unlocking guide block when deflecting, and pushes the limiting plate to rotate around the shaft pin towards the fixing plate.
In one embodiment of the invention, the plane rudder unlocking device further comprises an unfolding limiting pin arranged on the limiting plate and an unfolding limiting mechanism arranged on the fixing plate, wherein in the unlocking process, after the limiting plate rotates to the fixing plate in a certain range around the shaft pin, the unfolding limiting pin is clamped into the unfolding limiting mechanism, so that the limiting plate is prevented from interfering with the plane rudder after unlocking.
In one embodiment of the invention, the limiting plate is connected with the cushion pad through a bolt and a self-locking nut.
In one embodiment of the invention, the unfolding limiting mechanism comprises an unfolding limiting torsion spring, an unfolding limiting block, a gasket, an unfolding limiting shaft and a limiting support;
the unfolding limit shaft penetrates through the gasket, the unfolding limit block and the unfolding limit torsion spring and is installed on the limit support, and the limit support is installed on the fixing plate.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention limits the movement range of the plane rudder during locking, restrains buffeting, relieves the limitation on the movement range of the plane rudder after unlocking, and has the function of limiting after unlocking to prevent the plane rudder from interfering.
(2) On the basis of meeting the requirements of the geometrical overall dimension and the interface for the structural installation of the tail cabin of the air-jet carrier rocket, the original structural form of the shell section or the plane rudder is not changed, the influence on the aerodynamic performance of the whole rocket is small, and the installation is simpler.
(3) The part of the invention contacting with the control surface has a certain shape adjusting function, so that the cushion pad can be better matched with the plane rudder in the stage of flying.
(4) The invention mainly realizes the locking function by the pressure acting on the L-shaped part of the limiting plate and the torsion of the unlocking torsion spring during locking, has simple and reliable force transmission path, has the redundant unlocking function and the limiting function after unlocking, and has higher reliability.
Drawings
FIG. 1 is a schematic view showing a state in which the lock mechanism is inhibited from being locked
FIG. 2 is a schematic view showing a state in which the lock mechanism is inhibited from being unlocked
FIG. 3 is a schematic view of the assembly of the locking mechanism with rocket body and planar rudder
FIG. 4 is an exploded view of the lock-down mechanism
FIG. 5 is a schematic view of the function of limiting the spread of the locking mechanism
FIG. 6 is a schematic view of the lock function of the lock mechanism
Reference numerals: 1-a limiting plate, 2-a fixing plate, 3-a shaft pin, 4-an unlocking torsion spring, 5-a torsion spring positioning block, 6-a gasket group, 7-a cushion pad, 8-an unfolding limiting mechanism, 9-an unfolding limiting pin, 10-an unlocking guide block, 11-a first self-locking nut, 12-a first bolt, 13-a second bolt, 14-a locking bolt, 15-a second self-locking nut, 16-a third bolt, 81-an unfolding limiting torsion spring, 82-an unfolding limiting block, 83-a gasket, 84-an unfolding limiting shaft and 85-a limiting support.
Detailed Description
To make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
The invention provides a locking mechanism suitable for a plane rudder of a carrier rocket, which restrains the plane rudder from buffeting in a flying stage and prevents the plane rudder from generating abnormal deflection in a specific direction. Before the rocket is ignited and launched, the mechanism is actuated and unlocked, and the limit on the deflection of the plane rudder is removed. In the rocket flying process, the mechanism has a limiting function, and rebounding after unlocking is prevented, so that interference is generated between the mechanism and the plane rudder.
A damper lockout mechanism for limiting planar rudder deflection and buffeting, comprising: the locking device comprises a limiting plate 1, a fixing plate 2, a shaft pin 3, an unlocking torsion spring 4, a torsion spring positioning block 5, a gasket group 6, a cushion pad 7, an expansion limiting mechanism 8, an expansion limiting pin 9, an unlocking guide block 10, a first self-locking nut 11, a first bolt 12, a second bolt 13, a second locking bolt 14, a third self-locking nut 15 and a third bolt 16, and is shown in figures 1-6.
The working principle of the plane rudder inhibition locking mechanism is as follows: in the stage of the carrier rocket hanging, the plane rudder is subjected to pneumatic load and has the tendency of swinging and pressing towards the cushion 7 on the limit plate 1. The limiting plate 1 and the fixing plate 2 are connected with an unlocking torsion spring 4 through a shaft pin 3, and have a tendency of twisting towards the fixing plate 2 under the action of the torsion spring. As shown in fig. 1 and 4, the limiting plate 1 is connected to the cushion pad 7 and the shim group 6 through 3 second bolts 13 and 3 first self-locking nuts 11. The buffer cushion 7 has the function of buffering buffeting of the plane rudder, the gasket group 6 is composed of a plurality of gaskets, and the quantity of the gaskets is adjustable, so that the matching degree of the buffer cushion 7 and the plane rudder surface is improved. The adjacent parts of the limiting plate 1 and the plane rudder adopt an L-shaped design, in a flying stage, the L-shaped part of the limiting plate 1 is inserted into a gap between the plane rudder and the rocket body and abuts against the plane rudder, the motion of the limiting plate 1 rotating to the fixing plate 2 around the shaft pin 3 is restrained, the deflection of the plane rudder is limited, buffeting is inhibited, and the locking function is realized.
Before the carrier rocket is ignited, the plane rudder control system sends out an instruction to deflect the plane rudder in the direction opposite to the deflection direction in the hanging flight stage, namely the direction far away from the cushion pad 7, so that the contact between the cushion pad 7 and the plane rudder is removed, the limiting plate 1 can smoothly rotate towards the fixing plate 2 around the shaft pin 3 under the action of the unlocking torsion spring 4, the limitation on the deflection range of the plane rudder is removed, and the unlocking is realized.
The locking mechanism has a redundant unlocking function, if the limiting plate 1 rotates unsmoothly, the plane rudder deflects towards the direction opposite to the deflection direction in the hanging flight stage, namely the direction far away from the cushion pad 7, and then the plane rudder props against the unlocking guide block 10 to push the limiting plate 1 to rotate around the shaft pin 3 towards the fixing plate 2, so that redundant unlocking is realized.
The locking inhibition mechanism has a limiting function after unlocking. As shown in fig. 5, after the position limiting plate 1 rotates around the shaft pin 3 to the fixing plate 2 within a certain range, the unfolding limiting pin 9 will impact the unfolding limiting block 82, and the unfolding limiting pin 9 will be smoothly pressed between the unfolding limiting block 82 and the fixing plate 2 because the limiting block 82 can rotate around the unfolding limiting shaft 84 under the action of the unfolding limiting torsion spring 81. When the limiting plate moves back to the locking position in the hanging flight stage due to pneumatic and mechanical environmental factors, the unfolding limiting block 82 abuts against the unfolding limiting pin 9 to restrict the movement, so that the limiting plate 1 is prevented from interfering with the planar rudder, and the limiting function after unlocking is realized.
The installation process is as follows:
when the restraint lock mechanism is assembled, the deployment limit shaft 84 is first passed through the spacer 83, the deployment limit block 82, and the deployment limit torsion spring 81 and mounted on the limit support 85 to form the deployment limit mechanism 8. Subsequently, the deployment limiting mechanism 8 is mounted to the fixed plate 2 using the first bolt 12.
The shaft pin 3 is inserted into the mounting hole at one side of the limit plate 1, then the unlocking torsion spring 4 is inserted into the mounting hole at the other side of the limit plate 1, and the locking bolt 14 is inserted into the mounting hole at the head of the shaft pin 3. Subsequently, the unlocking torsion spring 4 is pressed to the position of the fixing plate 2 where the torsion spring positioning block 5 is installed, and the torsion spring positioning block 5 is installed by using the second self-locking nut 15 and the third bolt 16, so that the U-shaped part of the unlocking torsion spring 4 is pressed into the matching part of the torsion spring positioning block 5. At this time, the position-limiting plate 1 should have a tendency to rotate toward the fixing plate 2 along the shaft pin 3, as shown in fig. 1.
The fixing plate 2 is mounted on the rocket body. Adjusting the limiting plate 1 to a locking position in a hanging flight stage, and trial assembling with a plane rudder: inserting the L-shaped part of the limiting plate 1 into a gap between the planar rudder and the arrow body, testing the matching degree of the cushion pad 7 and the control surface, properly adjusting the number of the gaskets of the gasket group 6 to achieve the optimal matching degree between the cushion pad 7 and the control surface, and fixing the cushion pad 7 and the gasket group 6 by using a first self-locking nut 11 and a second bolt 13, as shown in fig. 3, 4 and 6.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are not particularly limited to the specific examples described herein.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (8)
1. A restraining and locking mechanism for restraining deflection and buffeting of a plane rudder is characterized by comprising a limiting plate (1), a fixing plate (2), a shaft pin (3), an unlocking torsion spring (4), a gasket group (6) and a cushion pad (7);
the limiting plate (1) and the fixing plate (2) are connected with the unlocking torsion spring (4) through the shaft pin (3), and have a tendency of twisting towards the fixing plate (2) under the action force of the unlocking torsion spring (4); the buffer pad (7) is arranged on the limit plate (1) and is used for buffering the buffeting of the plane rudder in a locking state; the gasket group (6) is positioned between the cushion pad (7) and the limiting plate (1) and used for improving the matching degree of the cushion pad (7) and the plane rudder surface; the adjacent part of the limiting plate (1) and the plane rudder is L-shaped, the L-shaped part is inserted into a gap between the plane rudder and the arrow body and abuts against the plane rudder, and the motion of the limiting plate (1) rotating around the shaft pin (3) to the fixing plate (2) is restrained, so that the deflection of the plane rudder is limited, buffeting is inhibited, and the locking function is realized.
2. The positive locking mechanism of claim 1, characterized in that the set of shims (6) consists of a number of shims, the number of shims being adjustable.
3. The lock-inhibiting mechanism of claim 1, wherein the lock-inhibiting mechanism is unlocked by: the plane rudder deflects towards the direction far away from the cushion pad (7), the contact between the cushion pad (7) and the plane rudder is relieved, and the plane rudder is not contacted with the L-shaped part of the limiting plate (1) any more, so that the limiting plate (1) can smoothly rotate around the shaft pin (3) towards the fixing plate (2) under the action of the unlocking torsion spring (4), and the limitation on the deflection range of the plane rudder is relieved.
4. The positive locking mechanism of claim 1, further comprising a torsion spring positioning block (5) mounted on the fixed plate (2) for limiting the unlocking torsion spring (4).
5. The lock-restraining mechanism according to claim 3, further comprising an unlocking guide block (10) mounted on the fixing plate (2), wherein during unlocking, the planar rudder will abut against the unlocking guide block (10) when deflecting, and the limiting plate (1) is pushed to rotate around the shaft pin (3) towards the fixing plate (2).
6. The mechanism for restraining locking according to claim 3, further comprising a deployment limiting pin (9) installed on the limiting plate (1) and a deployment limiting mechanism (8) installed on the fixing plate (2), wherein in the unlocking process, after the limiting plate (1) rotates to the fixing plate (2) in a certain range around the shaft pin (3), the deployment limiting pin (9) is clamped into the deployment limiting mechanism (8), and the limiting plate (1) is prevented from interfering with the rudder after unlocking.
7. The restraint locking mechanism according to any one of claims 1 to 6 characterized in that the stopper plate (1) and the cushion pad (7) are connected by a bolt and a self-locking nut.
8. The restraint locking mechanism according to claim 6, wherein the deployment limiting mechanism (8) comprises a deployment limiting torsion spring (81), a deployment limiting block (82), a gasket (83), a deployment limiting shaft (84), a limiting support (85);
the unfolding limiting shaft (84) penetrates through the gasket (83), the unfolding limiting block (82) and the unfolding limiting torsion spring (81) and is installed on the limiting support (85), and the limiting support (85) is installed on the fixing plate (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210089525.1A CN114593644B (en) | 2022-01-25 | 2022-01-25 | Suppression locking mechanism for limiting deflection and buffeting of plane rudder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210089525.1A CN114593644B (en) | 2022-01-25 | 2022-01-25 | Suppression locking mechanism for limiting deflection and buffeting of plane rudder |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114593644A true CN114593644A (en) | 2022-06-07 |
| CN114593644B CN114593644B (en) | 2023-06-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210089525.1A Active CN114593644B (en) | 2022-01-25 | 2022-01-25 | Suppression locking mechanism for limiting deflection and buffeting of plane rudder |
Country Status (1)
| Country | Link |
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| CN (1) | CN114593644B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659798B (en) * | 2008-12-26 | 2012-10-17 | 北京精密机电控制设备研究所 | The integrated electric steering engine of anti high overload |
| CN103644780A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Empennage rapid disassembly structure |
| US20160169642A1 (en) * | 2014-12-11 | 2016-06-16 | Mbda Deutschland Gmbh | Rudder System |
| CN206330490U (en) * | 2016-10-27 | 2017-07-14 | 浙江理工大学 | Guided missile rudder plane controlling mechanism |
| CN206787404U (en) * | 2017-07-06 | 2017-12-22 | 北京宇航系统工程研究所 | A kind of Aero-Space close lid with radially automatic |
| CN110487131A (en) * | 2019-05-30 | 2019-11-22 | 上海宇航系统工程研究所 | A kind of space transportation device grid rudder expansion locking mechanism |
| US20190367155A1 (en) * | 2018-06-01 | 2019-12-05 | Airbus Operations Gmbh | Wing arrangement for an aircraft and aircraft |
| CN210718853U (en) * | 2019-09-03 | 2020-06-09 | 中国空空导弹研究院 | Adjustable torsional spring driven unfolding missile rudder surface |
| CN212889976U (en) * | 2020-03-13 | 2021-04-06 | 浙江国利汽车环保科技有限公司 | Unlocking device for slide rail of automobile seat |
-
2022
- 2022-01-25 CN CN202210089525.1A patent/CN114593644B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659798B (en) * | 2008-12-26 | 2012-10-17 | 北京精密机电控制设备研究所 | The integrated electric steering engine of anti high overload |
| CN103644780A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Empennage rapid disassembly structure |
| US20160169642A1 (en) * | 2014-12-11 | 2016-06-16 | Mbda Deutschland Gmbh | Rudder System |
| CN206330490U (en) * | 2016-10-27 | 2017-07-14 | 浙江理工大学 | Guided missile rudder plane controlling mechanism |
| CN206787404U (en) * | 2017-07-06 | 2017-12-22 | 北京宇航系统工程研究所 | A kind of Aero-Space close lid with radially automatic |
| US20190367155A1 (en) * | 2018-06-01 | 2019-12-05 | Airbus Operations Gmbh | Wing arrangement for an aircraft and aircraft |
| CN110487131A (en) * | 2019-05-30 | 2019-11-22 | 上海宇航系统工程研究所 | A kind of space transportation device grid rudder expansion locking mechanism |
| CN210718853U (en) * | 2019-09-03 | 2020-06-09 | 中国空空导弹研究院 | Adjustable torsional spring driven unfolding missile rudder surface |
| CN212889976U (en) * | 2020-03-13 | 2021-04-06 | 浙江国利汽车环保科技有限公司 | Unlocking device for slide rail of automobile seat |
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| Publication number | Publication date |
|---|---|
| CN114593644B (en) | 2023-06-06 |
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