CN111086656A - Combined adjustable grid rudder unfolding and locking mechanism - Google Patents
Combined adjustable grid rudder unfolding and locking mechanism Download PDFInfo
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- CN111086656A CN111086656A CN201911248422.XA CN201911248422A CN111086656A CN 111086656 A CN111086656 A CN 111086656A CN 201911248422 A CN201911248422 A CN 201911248422A CN 111086656 A CN111086656 A CN 111086656A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
Abstract
A combined adjustable grid rudder unfolding and locking mechanism comprises a grid rudder, a rudder disc, a locking block, a locking device, a torsion piece device, a left unfolding shaft and a right unfolding shaft. The torsion piece device is composed of a torsion piece retainer, torsion pieces, cushion blocks and bolts, and the torsion piece groups made of different materials and quantities can provide unfolding moments of different sizes for the grid rudder to unfold. The locking device comprises a retainer, a guide rail, a spring pin, a spring, a cover plate and the like, wherein the spring pin moves in the retainer, the T-shaped guide rail limits the rolling of the spring pin in the retainer and plays a role in guiding, one end of the spring is inserted into a cylindrical hole at the tail end of the spring pin, and the other end of the spring is sleeved on a guide cylinder on the cover plate, so that the spring can be kept from being bent and unstable. The invention realizes the preset function through the combination of a plurality of parts, and achieves the purpose of adjusting the product performance of the mechanism through the replacement and the quantity change of key parts so as to adapt to the requirements of different use environments.
Description
Technical Field
The invention relates to a combined adjustable grid rudder unfolding and locking mechanism, and belongs to the technical field of air rudder unfolding and locking mechanisms.
Background
With the development of launch vehicle technology, the need to establish low cost space entry capability is ever stronger. With the economic development and the improvement of population density in China, the requirements for reducing the area of the debris falling area of the carrier rocket, avoiding or reducing the workload of ground personnel evacuation and protecting the life and property safety of people are more and more strong, and the reuse rocket technology and the carrier rocket sublevel falling area control technology need to be developed. In the control technology of the falling area of the repeatedly used rocket and carrier rocket substage, after the rocket substage or the booster enters the atmosphere again, a grid rudder pneumatic control mechanism is needed to control the posture of the rocket body.
The grid rudder installed on the rocket stage section is tightly attached to the surface of the rocket body in a folding state in the launching and rising section of the rocket, the grid rudder is unfolded and locked with a rudder disk after the stage separation, and the grid rudder rotates under the action of a servo actuator and a transmission mechanism when the later sub-stage enters the atmosphere again according to a control instruction to generate pneumatic control for rolling, pitching and yawing so as to realize the accurate landing of the rocket.
The grid rudder is convenient to fold, good in lift characteristic in a large attack angle/wide Mach number range, high in structural rigidity and the like, is suitable for being applied to a reusable rocket, needs to complete unfolding, locking, rotating and other actions after interstage separation, and is subjected to severe aerodynamic force and aerodynamic heat load environments in a reentry section, so that a grid steering mechanism system is required to reliably complete preset actions such as unfolding, locking and the like, can adapt to different separation conditions/rocket body posture influences, and can stably work in a severe thermal environment.
After the carrier rocket is separated from the stages, the rocket stage with the grid rudder continues to move by means of inertia, the posture is greatly changed, the grid rudder is unfolded by using a servo mechanism, the method has the advantages of controllable process and strong load environment adaptability, but an independent servo steering engine, a servo controller, a power supply, an auxiliary structure, a mechanism and the like need to be added, the cost is high, the weight is heavy, and the influence on other equipment is easily caused due to the addition of complex electromechanical products. The grid rudder is unfolded by means of centrifugal force, the structure is simple, the process is uncontrollable, the grid rudder is easily unfolded in place at an overlarge speed, and the arrow body structure is subjected to overhigh impact and even damaged. The grid rudders are driven to unfold by using elastic elements such as torsion springs, the driving force is small, and the unfolding synchronism of the grid rudders is difficult to ensure.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and a combined adjustable grid rudder unfolding and locking mechanism is provided, so that the grid rudder can reliably complete preset actions such as unfolding and locking, can adapt to different separation conditions/arrow body posture influences, and can stably work in a severe thermal environment.
The technical solution of the invention is as follows:
a combined adjustable grid rudder unfolding and locking mechanism comprises a grid rudder, a rudder disc, a locking block, a locking device, a torsion piece device, a left unfolding shaft and a right unfolding shaft;
two lugs at the upper end of the grid rudder are provided with shaft holes and are arranged on the rudder disc through a left unfolding shaft and a right unfolding shaft;
the grid rudder comprises a grid rudder, a grid rudder lug, a left unfolding shaft, a right unfolding shaft, a grid rudder and a grid rudder, wherein the grid rudder is provided with a grid plate, the grid;
the grid rudder is provided with a grid rudder unfolding shaft hole, a grid rudder unfolding shaft hole and a torsion sheet device, wherein the grid rudder unfolding shaft hole is provided with a right unfolding shaft, the right unfolding shaft hole is provided with a right unfolding shaft, and the right unfolding shaft hole is provided with a right unfolding shaft;
under the drive of the torsion piece device, the grid rudder is unfolded from a folding position, when the grid rudder is unfolded in place, the locking block on the grid rudder is contacted with the rudder disc and matched with the locking device to lock the grid rudder and the rudder disc, and the locked rudder disc and the grid rudder are rotated under the action of the servo steering engine and the transmission mechanism.
Furthermore, the locking device is a cuboid assembly and comprises a spring pin, a retainer, a guide rail, a spring and a cover plate;
the spring pin is in a stepped cylinder shape, the small diameter section is provided with an inclined plane, a cylinder hole is formed in the large diameter section along the axis, and a strip-shaped groove is formed in the side face of the large diameter section along a bus; the retainer is a cuboid and is detachably mounted on the surface of the rudder plate, a mounting hole of the spring pin is formed in the retainer and used for stretching the spring pin, and a strip-shaped groove is formed in the retainer and used for mounting a guide rail; the guide rail is a T-shaped part, is downwards inserted into the strip-shaped groove and is matched with the strip-shaped groove of the spring pin to limit the rotation of the spring pin, so that the guide rail plays a role in guiding the spring pin and can enable the inclined surface of the spring pin to always face the locking block; the cover plate is of a flat plate structure with a guide cylinder, one end of the spring is inserted into the cylindrical hole of the spring pin along the axis, and the other end of the spring is sleeved on the guide cylinder of the cover plate.
Furthermore, the torsion piece device is a slender assembly and comprises a torsion piece, a torsion piece retainer, a screw and a cushion block;
connecting holes are formed at two ends of the torsion piece; a plurality of twisting sheets are stacked for use and are connected with the twisting sheet retainer through the matching of screws and cushion blocks; the twisted piece retainer is cylindrical, and one end of the twisted piece retainer is provided with a square groove for placing the twisted piece and the cushion block.
Furthermore, the torsion sheet is a strip-shaped sheet-shaped part made of alloy spring steel materials, and 5-20 pieces are stacked in groups for use.
Furthermore, the thickness and the stacking number of the single pieces of the torsion pieces are matched with the thickness of the cushion blocks, and the total thickness is smaller than or equal to the thickness of the square groove of the torsion piece retainer.
Furthermore, the maximum torsion angle of the torsion piece device is 90 degrees + the pre-torsion angle, and the pre-torsion angle is adjustable.
Furthermore, the steering wheel rotating shaft is of a circular truncated cone-shaped structure.
Further, the surfaces of the left unfolding shaft and the right unfolding shaft extending into the steering wheel part are provided with MoS2Coating, MoS on the inclined surface of spring pin2And (4) coating.
Furthermore, the right unfolding shaft comprises a cylindrical section, a flange plate and a hexagonal head which are sequentially connected, and a small plane structure is cut at the edge of the flange plate.
Furthermore, only if the right unfolding shaft is rotated anticlockwise by a pre-twisting angle to enable the edge small plane structure to be parallel to the upper surface of the grid rudder support lug, the right unfolding shaft and the grid rudder can be fixed by using a screw, otherwise, the mounting hole in the right unfolding shaft cannot be aligned with the threaded hole in the grid rudder.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the requirements of unfolding and locking of the grid rudder under different use environments, the invention designs the elastic element for driving the grid rudder to unfold, the installation mode of the elastic element, the locking pin device and the like according to a combined and adjustable design concept. The manufacturing complexity of a single part is reduced, the performance of the mechanism product is adjusted through replacement and quantity change of key parts, and the realization of the function of the mechanism is maintained under the condition that individual parts are damaged through a part replacement mode.
(2) The manufacturing complexity of a single part is reduced, and a predetermined function is realized through the combination of a plurality of parts; the purpose of adjusting the product performance of the mechanism is achieved through replacement and quantity change of key parts, so that the requirements of different use environments are met.
(3) The mechanical property of the locking pin device can be changed by replacing small-sized parts with different specifications and sizes.
(4) Under the condition that individual parts are damaged or out of tolerance and the like, the function of the mechanism is kept to be realized by replacing the parts, and the time and economic loss caused by the integral failure or integral replacement of the mechanism is avoided.
(5) The right unfolding shaft is designed to be error-proof, and only when the right unfolding shaft rotates anticlockwise by a pre-twisting angle to enable the edge small plane of the right unfolding shaft to be parallel to the upper surface of the grid rudder support lug can the right unfolding shaft be fixed with the grid rudder by using a screw, otherwise, the mounting hole in the right unfolding shaft cannot be aligned with the threaded hole in the grid rudder.
Drawings
FIG. 1 is a schematic view of a combination adjustable grid rudder deployment locking mechanism;
fig. 2 is a schematic view of a torsion sheet apparatus;
FIG. 3 is one of the schematic views of the locking device;
FIG. 4 is a second schematic view of the locking device;
fig. 5 is a schematic view of the right deployment axis.
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
In order to adapt to the aerodynamic thermal environment in the reentry process, the grid rudder is generally made of titanium alloy materials, and the titanium alloy grid rudder with larger self weight needs to be unfolded under the action of an elastic element after an explosion bolt connecting the grid rudder and a rocket body is unlocked. Because the titanium alloy grid rudder has larger self weight and larger rotational inertia, the elastic element is required to provide larger unfolding moment, and a certain moment can be still kept at the position where the grid rudder is unfolded in place, so that the rebounding and the unlocking are avoided.
As shown in fig. 1, the invention provides a combined adjustable grid rudder unfolding and locking mechanism, which comprises a grid rudder 1, a rudder disc 2, a locking block 3, a locking device 4, a torsion piece device 5, a left unfolding shaft 6 and a right unfolding shaft 7;
two lugs at the upper end of the grid rudder 1 are provided with shaft holes and are arranged on the rudder disc 2 through a left unfolding shaft 6 and a right unfolding shaft 7;
the left unfolding shaft 6 and the right unfolding shaft 7 are both multi-step cylinders, the steering wheel 2 is provided with two axes of an unfolding shaft and a rotating shaft which are perpendicular to each other, shaft holes in the middle of two lugs of the grid rudder 1 are coaxial with the shaft holes of the unfolding shaft of the steering wheel 2 and the axes of the left unfolding shaft 6 and the right unfolding shaft 7, the left unfolding shaft 6 and the right unfolding shaft 7 penetrate into the lug shaft holes of the grid rudder 1 and the shaft holes of the unfolding shaft of the steering wheel 2 from the left side and the right side respectively, and the left unfolding shaft 6 and the right unfolding shaft 7 are connected with the grid rudder 1 through screws;
the twisted sheet device 5 is arranged in the shaft hole of the unfolding shaft of the rudder disc 2, one end of the twisted sheet device 5 is connected with the rudder disc 2 through a screw, the other end of the twisted sheet device 5 is connected with the right unfolding shaft 7 through a screw, and a pre-twisting angle is arranged, namely when the grid rudder is unfolded in place, the twisted sheet device 5 still applies a moment effect generated by twisting the pre-twisting angle to the grid rudder, and the pre-twisting moment can be changed by adjusting the pre-twisting angle;
under the drive of a torsion sheet device 5, the grid rudder 1 is unfolded from a folding position, when the grid rudder 1 is unfolded in place, a locking block 3 on the grid rudder 1 is in contact with a rudder disc 2 and is matched with a locking device 4 to complete the locking of the grid rudder 1 and the rudder disc 2, and the locked rudder disc 2 and the grid rudder 1 rotate under the action of a servo steering engine and a transmission mechanism.
The twisted piece is a strip-shaped sheet part made of alloy spring steel materials, when two ends of the twisted piece are twisted, the twisted piece is twisted and deformed to generate elastic potential energy, one end of each end of the twisted piece is connected to the rudder disk, and the other end of each end of the twisted piece is connected to the grid rudder, so that a moment for driving the grid rudder to unfold can be formed between the grid rudder and the rudder shaft. The torque generated on the single torsion piece depends on the elastic modulus, strength, thickness, width, length and torsion angle of the torsion piece, and the number of the torsion pieces is increased or decreased in a superposition mode, so that the torque value is adjusted. The torsion piece device is shown in figure 2 and comprises a torsion piece retainer, torsion pieces, cushion blocks and bolts, and the torsion piece groups made of different materials and quantities can provide unfolding moments with different sizes for the grid rudder to unfold.
Specifically, the torsion piece device 5 is an elongated component, and comprises a torsion piece 51, a torsion piece holder 52, a screw 53 and a cushion block 54;
connecting holes are formed at two ends of the torsion piece 51; a plurality of twisting sheets 51 are stacked for use and are connected with a twisting sheet retainer 52 through screws 53 matched with cushion blocks 54; the torsion piece holder 52 is cylindrical, and one end of the torsion piece holder is provided with a square groove for placing the torsion piece 51 and the cushion block 54.
Preferably, the torsion piece 51 is an elongated sheet-shaped part made of alloy spring steel material, and 5-20 pieces are stacked in groups for use.
Preferably, the thickness of the single piece of the torsion piece 51, the stacking number and the thickness of the cushion block 54 are matched, and the total thickness is less than or equal to the thickness of the square groove of the torsion piece holder 52.
Preferably, the maximum torsion angle of the torsion piece device 5 is 90 ° + a pre-torsion angle, and the pre-torsion angle is adjustable.
The torsion piece device is installed in the sequence that the torsion piece retainer, the torsion piece and the cushion block on one side are connected through the bolt, and then the other retainer and the cushion block are connected. The torsion piece retainer can be matched with torsion pieces of different materials, specifications and quantities by matching with different cushion blocks, thereby achieving the purpose of adjusting the unfolding moment.
One end of the installed torsion piece device is connected with the rudder disc, the other end of the installed torsion piece device is connected with the grid rudder, and a pre-twisting angle is set, namely when the grid rudder is unfolded in place, the torsion piece group still exerts a moment effect generated by twisting the pre-twisting angle on the grid rudder, and the pre-twisting moment can be changed by adjusting the pre-twisting angle.
The installation sequence of the twisted sheet device, the rudder disc and the grid rudder is that the grid rudder shaft hole and the rudder disc unfolding shaft hole are coaxial, then a left unfolding shaft is installed, then the twisted sheet device is placed into the rudder disc from the other side, a twisted sheet retainer and the rudder disc are fixed through screws, a right unfolding shaft is inserted into the rudder disc, the right unfolding shaft and the twisted sheet retainer are connected through screws, then the right unfolding shaft is rotated counterclockwise by a pre-twisting angle to enable the edge facet of the right unfolding shaft to be parallel to the upper surface of a grid rudder lug, and finally the right unfolding shaft and the grid rudder are fixed through screws.
Under the drive of torque of the torsion piece, the grid rudder is unfolded from a folding position, a locking block on the grid rudder is contacted with a rudder disc when the grid rudder is unfolded in place, locking pins on the rudder disc are inserted into pin holes in the locking block from two sides to lock the grid rudder and the rudder disc, and the rudder disc and the grid rudder rotate under the action of a servo steering engine and a transmission mechanism after being locked.
The rudder disc is integrally machined, has the characteristics of large volume, complex appearance and complex machining, is designed for reducing the manufacturing complexity of a single part, realizes a preset function through the combination of a plurality of parts, can change the size and the performance of a product through the replacement of key parts, and can maintain the realization of the function of a mechanism under the condition that individual parts are damaged through a part replacing mode. The rotating shaft of the rudder disk 2 is in a round platform-shaped structure.
As shown in fig. 3 and 4, the locking device 4 is a rectangular parallelepiped component including a spring pin 41, a holder 42, a guide rail 43, a spring 44, and a cover plate 45;
the spring pin 41 is in a stepped cylinder shape, the small diameter section is provided with an inclined plane, a cylinder hole is formed in the large diameter section along the axis, and a strip-shaped groove is formed in the side face of the large diameter section along a bus; the retainer 42 is a cuboid and is detachably mounted on the surface of the rudder stock, a mounting hole of the spring pin 41 is formed in the retainer 42 and used for stretching the spring pin, and a strip-shaped groove is formed in the retainer 42 and used for mounting the guide rail 43; the guide rail 43 is a T-shaped part, is inserted downwards into the strip-shaped groove and is matched with the strip-shaped groove of the spring pin 41 to limit the rotation of the spring pin 41, so that the spring pin 41 is guided, and the inclined surface of the spring pin 41 can always face the locking block 3; the cover plate 45 is a flat plate structure with a guide cylinder, one end of the spring 44 is inserted into the cylindrical hole of the spring pin 41 along the axis, and the other end is sleeved on the guide cylinder of the cover plate 45.
The spring pins are not mounted directly on the rudder stock, but are combined with the rudder stock from the retainer and the guide rail. The square spaces for installing the retainer and the guide rail are reserved in the two protruding areas on the surface of the rudder plate, the retainer with the outer square and the inner circle is combined with the rudder plate and plays a role in guiding the spring pin, and the movement of the spring pin in the retainer is guaranteed. After the T-shaped guide rail is installed, the T-shaped guide rail is matched with the groove on the spring pin, so that the rolling of the spring pin in the retainer can be limited, a guiding effect is achieved, and the inclined surface of the spring pin can always face the locking block. One end of the spring is inserted into the cylindrical hole at the tail end of the spring pin, and the other end of the spring is sleeved on the guide cylinder on the cover plate, so that the spring is prevented from being bent and unstable. Aiming at different requirements, the strength, rigidity, compression force and other properties of the locking pin device can be changed by replacing spring pins, retainers, guide rails, springs and other small parts with lower complexity in different specifications and sizes under the condition of not changing the most complicated part of the rudder stock body, the locking pin device can be matched with the locking block at different clearance values, and the locking pin device can be quickly replaced under the condition of damaging individual parts and can maintain the function of the mechanism.
The locking device is installed in sequence, the retainer is firstly placed in a square groove of a protruding area of the rudder plate, then the T-shaped guide rail is installed from top to bottom, the T-shaped guide rail is inserted into a groove of the retainer, and the guide rail is fixed by a screw; then the spring pin is put into the cylindrical hole of the retainer, the strip-shaped groove of the spring pin is upwards matched with the guide rail, and the inclined plane of the spring pin is kept outwards; one end of the spring is inserted into a cylindrical hole at the tail end of the spring pin, the other end of the spring is sleeved on a guide cylinder on the cover plate, the cover plate is pressed into the protruding area of the rudder plate, and the cover plate is fixed in the protruding area of the rudder plate through screws.
The surfaces of the parts of the left unfolding shaft 6 and the right unfolding shaft 7 extending into the rudder plate 2 are provided with MoS2Coating, MoS on the inclined plane of the spring pin 412And (4) coating.
As shown in fig. 5, the right unfolding shaft 7 comprises a cylindrical section, a flange plate and a hexagonal head which are connected in sequence, and a facet structure is cut at the edge of the flange plate. The right unfolding shaft 7 is designed to be error-proof in the invention. Only if the right unfolding shaft 7 is rotated anticlockwise by a pre-twisting angle to enable the edge small plane structure to be parallel to the upper surface of the grid rudder support lug, the right unfolding shaft 7 and the grid rudder 1 can be fixed by using a screw, otherwise, a mounting hole in the right unfolding shaft 7 cannot be aligned with a threaded hole in the grid rudder 1.
Through experimental verification of ground static force experiments, ground unfolding locking experiments, ground transfer characteristic experiments and the like, the invention can meet the requirements of functions and performance, the reasonability and the reliability of the design of the CZ-2C Y37 rocket are verified through launching, the four sets of grid rudders are all reliably and synchronously unfolded and locked, the test of a complex force and heat environment is carried out in the reentry and return processes of a rocket level, and the drop point precision of reentry and return of the rocket level is greatly improved.
Those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The utility model provides a grid rudder deployment locking mechanical system with adjustable combination which characterized in that: the grid rudder comprises a grid rudder (1), a rudder disc (2), a locking block (3), a locking device (4), a torsion piece device (5), a left unfolding shaft (6) and a right unfolding shaft (7);
shaft holes are formed in two lugs at the upper end of the grid rudder (1), and the grid rudder is installed on the rudder disc (2) through a left unfolding shaft (6) and a right unfolding shaft (7);
the grid rudder comprises a grid rudder (1), a left unfolding shaft (6), a right unfolding shaft (7), a grid rudder (1), a grid rudder and a steering wheel, wherein the grid rudder;
the twisted sheet device (5) is arranged in a shaft hole of a unfolding shaft of the rudder disc (2), one end of the twisted sheet device (5) is connected with the rudder disc (2) through a screw, the other end of the twisted sheet device is connected with the right unfolding shaft (7) through a screw, and a pre-twisting angle is arranged, namely when the grid rudder is unfolded in place, the twisted sheet device (5) still applies a moment effect generated by twisting the pre-twisting angle to the grid rudder, and the pre-twisting moment can be changed by adjusting the pre-twisting angle;
under the drive of the torsion sheet device (5), the grid rudder (1) is unfolded from a folding position, when the grid rudder (1) is unfolded in place, the locking block (3) on the grid rudder (1) is in contact with the rudder disc (2) and is matched with the locking device (4) to lock the grid rudder (1) and the rudder disc (2), and the locked rudder disc (2) and the grid rudder (1) are rotated under the action of the servo steering engine and the transmission mechanism.
2. The combination adjustable grid rudder deployment locking mechanism of claim 1, wherein: the locking device (4) is a cuboid assembly and comprises a spring pin (41), a retainer (42), a guide rail (43), a spring (44) and a cover plate (45);
the spring pin (41) is in a stepped cylinder shape, the small diameter section is provided with an inclined plane, a cylinder hole is formed in the large diameter section along the axis, and a strip-shaped groove is formed in the side face of the large diameter section along a bus; the retainer (42) is a cuboid and is detachably mounted on the surface of the rudder stock, a mounting hole of a spring pin (41) is formed in the retainer for stretching the spring pin, and a strip-shaped groove is formed in the retainer (42) and used for mounting a guide rail (43); the guide rail (43) is a T-shaped part, is downwards inserted into the strip-shaped groove of the retainer (42) and is matched with the strip-shaped groove of the spring pin (41) to limit the rotation of the spring pin (41), plays a role in guiding the spring pin (41), and can enable the inclined surface of the spring pin (41) to face the locking block (3) all the time; the cover plate (45) is of a flat plate structure with a guide cylinder, one end of a spring (44) is inserted into a cylindrical hole of the spring pin (41) along the axis, and the other end of the spring is sleeved on the guide cylinder of the cover plate (45).
3. The combination adjustable grid rudder deployment locking mechanism of claim 1, wherein: the torsion piece device (5) is a slender assembly and comprises a torsion piece (51), a torsion piece retainer (52), a screw (53) and a cushion block (54);
connecting holes are formed at two ends of the torsion piece (51); a plurality of torsion pieces (51) are stacked for use and are connected with a torsion piece retainer (52) through screws (53) matched with cushion blocks (54); the torsion piece retainer (52) is cylindrical, and one end of the torsion piece retainer is provided with a square groove used for placing the torsion piece (51) and the cushion block (54).
4. The combined adjustable grid rudder deployment locking mechanism is characterized in that the torsion pieces (51) are strip-shaped sheet-like parts made of alloy spring steel materials, and 5-20 pieces are stacked in groups for use.
5. The combined adjustable grid rudder deployment locking mechanism is characterized in that the thickness of the single piece of the torsion piece (51) and the stacking quantity of the torsion piece are matched with the thickness of the cushion block (54), and the total thickness is smaller than or equal to the thickness of the square groove of the torsion piece retainer (52).
6. The combined adjustable grid rudder deployment locking mechanism according to claim 4, characterized in that the maximum twist angle of the torsion sheet device (5) is 90 ° + pretwist angle, which is adjustable.
7. The combined adjustable grid rudder deployment locking mechanism according to claim 1, characterized in that the rudder disk (2) rotating shaft is of a truncated cone structure.
8. The combined adjustable grid rudder deployment locking mechanism is characterized in that the surface of the part of the left deployment shaft (6) and the right deployment shaft (7) extending into the rudder disk (2) is provided with MoS2Coating, the inclined surface of the spring pin (41) is provided with MoS2 coating.
9. The combined adjustable grid rudder deployment locking mechanism is characterized in that the right deployment shaft (7) comprises a cylindrical section, a flange plate and a hexagonal head which are connected in sequence, and a small plane structure is cut at the edge of the flange plate.
10. The combined adjustable grid rudder deployment locking mechanism according to claim 9, characterized in that the right deployment shaft (7) can be fixed to the grid rudder (1) by using screws only if the right deployment shaft (7) is rotated counterclockwise by a pre-twist angle to keep the edge facet structure parallel to the upper surface of the grid rudder lug, otherwise the mounting holes on the right deployment shaft (7) are not aligned with the threaded holes on the grid rudder lug.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911248422.XA CN111086656B (en) | 2019-12-09 | 2019-12-09 | Combined adjustable grid rudder unfolding and locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911248422.XA CN111086656B (en) | 2019-12-09 | 2019-12-09 | Combined adjustable grid rudder unfolding and locking mechanism |
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| Publication Number | Publication Date |
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| CN111086656A true CN111086656A (en) | 2020-05-01 |
| CN111086656B CN111086656B (en) | 2021-07-13 |
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| CN201911248422.XA Active CN111086656B (en) | 2019-12-09 | 2019-12-09 | Combined adjustable grid rudder unfolding and locking mechanism |
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| CN (1) | CN111086656B (en) |
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| CN114264215A (en) * | 2021-12-24 | 2022-04-01 | 北京新风航天装备有限公司 | Torsion element loading aging residual deformation angle online detection device and method |
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| 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 |
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