CN110579139B - Adjustable torsion spring driven unfolding missile control surface and assembly process - Google Patents
Adjustable torsion spring driven unfolding missile control surface and assembly process Download PDFInfo
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- CN110579139B CN110579139B CN201910829949.5A CN201910829949A CN110579139B CN 110579139 B CN110579139 B CN 110579139B CN 201910829949 A CN201910829949 A CN 201910829949A CN 110579139 B CN110579139 B CN 110579139B
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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
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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Abstract
An adjustable torsion spring driven unfolding missile control surface and an assembly process thereof comprise a base, a control surface, a torsion spring and a pin shaft; the torsion bar hole for adjusting force is added on the end face of the shaft shoulder of the pin shaft, so that the adjustability of torsion of the torsion spring in the assembly process is realized, the consistency of the torsion of the folded torsion spring of the control surface after assembly is ensured, and the problem of scrapping of parts is avoided; meanwhile, the position of a force torsion bar reference hole and the outer side surface of a right baffle plate at the upper part of the base shaft shoulder are processed with assembly reference marks on the end surface of the pin shaft shoulder, so that errors are prevented in the assembly process; after the new structure and the assembly process are adopted, the grouping matching process and the process of re-disassembling and assembling parts of components in the existing assembly process are eliminated, and the one-time assembly success rate is improved, so that the overall assembly efficiency is greatly improved.
Description
Technical Field
The invention relates to a missile flight control surface unfolding mechanism, in particular to an adjustable torsion spring driven guided missile control surface unfolding and an assembly process.
Background
In the process of storage and transportation of missiles, a folding mechanism is required to be adopted for missile control surfaces in order to reduce loading space and improve loading quantity and transportation efficiency, and then the missile control surfaces are unfolded after being launched. At present, most folding mechanisms adopt torsion springs to drive and unfold, and the working principle is as follows: when the control surface is folded for a certain angle, the torsion spring also twists a corresponding angle, and corresponding potential energy is accumulated; when the control surface releases the constraint, potential energy accumulated by the torsion spring is converted into control surface kinetic energy, and the control surface is driven to return to the unfolding position.
In the actual production and assembly process, the movement clearance and friction of the mechanism are different when the parts are assembled because the parts are processed within a certain tolerance range; meanwhile, the torsional springs have certain difference in processing, so that the rigidity of the torsional springs is different; therefore, after the assembly is completed, the torsion generated by the torsion springs is different under the condition that the folding angles of the control surfaces are the same, and the problem of asynchronism exists when the control surfaces are unfolded. When the missile is launched, the problem of unsynchronization of the control surface unfolding can influence the safety of the missile launching.
In order to ensure synchronization when the missile control surface is unfolded, the existing assembly process comprises the following steps: after the missile control surface is assembled, measuring torsion of the torsion spring, and carrying out grouping matching according to a measurement result to ensure that the control surface of the same missile is unfolded and kept synchronous; for the torsion of the torsion spring after assembly exceeding the standard, the control surface assembly cannot be matched for use, the torsion spring is disassembled and assembled again after the parts are replaced, and then the torsion spring is measured and matched and grouped; and (5) scrapping the parts which are finally disassembled and assembled for multiple times and cannot be used. The assembling, grouping matching and re-disassembling processes are complex, the process is complex, and the problems of low efficiency and high cost exist.
Disclosure of Invention
In order to overcome the defects in the background art, the invention discloses an adjustable torsion spring driven unfolding missile control surface and an assembly process thereof, wherein an adjusting force torsion bar hole is added on the end face of a shaft shoulder of a pin shaft, so that the adjustability of torsion of the torsion spring in the assembly process is realized, the consistency of torsion of the torsion spring after the control surface is folded is ensured, and the problem of scrapping of parts is avoided; meanwhile, an assembly reference mark is processed on the position of a force torsion bar reference hole on the end face of the shaft shoulder of the pin shaft and the outer side face of a right baffle plate on the upper part of the shaft shoulder of the base, so that errors in the assembly process are prevented; after the new structure and the assembly process are adopted, the grouping matching process and the process of re-disassembling and assembling parts of components in the existing assembly process are eliminated, and the one-time assembly success rate is improved, so that the overall assembly efficiency is greatly improved.
In order to achieve the aim of the invention, the invention adopts the following technical scheme: an adjustable torsion spring driven unfolding missile control surface and an assembly process thereof comprise a base, a control surface, a torsion spring, a pin shaft, a force torsion bar through hole, a reference hole mark and an installation reference mark; the base is a short round shaft with a shaft shoulder, a ring groove used for being connected and fixed with the missile is formed in the lower portion of the shaft, a control surface mounting groove formed by two baffles is formed in the upper portion of the shaft shoulder, a square through hole is formed in the middle of the left baffle, and a round through hole is formed in the middle of the right baffle; two sides of the root of the control surface are planes, two through holes are formed in the direction perpendicular to the planes at the root, the through hole with the smaller diameter at the upper part is a control surface force torsion bar hole, the through hole with the larger diameter at the lower part is a pin hole, the end face of the root is an arc surface, and the arc of the end face of the root is concentric with the pin hole; the two ends of the torsion spring are extended with force torsion bars; the pin shaft is a step-shaped short shaft, a shaft shoulder, a torsion spring mounting surface, a base round hole mounting surface, a control surface hole mounting surface, a base square hole mounting surface and threads at the leftmost end are sequentially arranged from right to left, and a plurality of through holes for assembling the force torsion bar are uniformly distributed on the end surface of the shaft shoulder along the circumference; the control surface root is arranged in a control surface mounting groove at the upper part of the base shaft shoulder, and the pin shaft is arranged in through holes of two baffles at the upper part of the base shaft shoulder and a pin shaft hole at the root of the control surface, wherein a square hole mounting surface of the pin shaft is matched with a square through hole of a baffle at the left side at the upper part of the base shaft shoulder to prevent the pin shaft from rotating; the torsion spring is arranged on the torsion spring mounting surface of the pin shaft, one end of the torsion spring enables the force torsion bar to be inserted into the force torsion bar hole of the control surface, and the other end of the torsion spring enables the force torsion bar to be inserted into the force torsion bar through hole of the pin shaft; the pin shaft is locked and fixed by a nut through the leftmost thread.
Preferably, the force torsion bar through holes on the end face of the pin shaft shoulder are provided with a plurality of force torsion bar through holes, so that the torque adjusting range of the torsion spring can be increased, the overall weight of the control surface assembly can be reduced, the force torsion bar through holes are uniformly distributed along the circumferential direction of the end face of the pin shaft shoulder, and the force torsion bar reference holes are marked.
Preferably, the mounting reference mark is processed on the outer side surface of the right baffle plate at the upper part of the base shaft shoulder, so that errors in the assembly process are prevented.
Preferably, a blind hole is formed in the middle of the end face of the pin shaft shoulder so as to reduce the overall weight of the control surface assembly.
In the assembly process of the control surface of the unfolding missile driven by the adjustable torsion spring, when the torsion spring is installed, one end of the torsion spring is inserted into a force torsion bar reference hole of a pin shaft, and the other end of the torsion spring is inserted into a force torsion bar hole of the control surface; then folding the control surface to a set angle, measuring the torque of the torsion spring, and installing the nut at the left end of the pin shaft and locking and fixing when the torque of the torsion spring is within a design range; when the torsion of the torsion spring is smaller than the design range, the force torsion bar inserted into the pin shaft rotates anticlockwise according to the measurement result and is inserted into the force torsion bar hole corresponding to the pin shaft; refolding the control surface to a set angle, measuring the torque of the torsion spring, and installing a nut at the left end of the pin shaft and locking and fixing when the torque of the torsion spring is within a design range; when the torsion of the torsion spring is larger than the design range, the force-making torsion bar inserted into the pin shaft is rotated clockwise according to the measurement result and is inserted into the force-making torsion bar hole corresponding to the pin shaft; and refolding the control surface to a set angle, measuring the torque of the torsion spring, and installing the nut at the left end of the pin shaft and locking and fixing when the torque of the torsion spring is within a design range.
The assembly process of the adjustable torsion spring driven unfolding missile rudder surface is specifically described through the following explanation:
s1: the torsion spring is arranged on the torsion spring installation surface of the pin shaft, and one end of the torsion spring is inserted into the force torsion bar reference hole of the pin shaft; the control surface root is arranged in a control surface mounting groove at the upper part of the shaft shoulder of the base, so that the pin shaft hole at the control surface root is ensured to be coaxial with the circular through hole of the baffle at the right side at the upper part of the shaft shoulder; the other end of the torsion spring enables the force torsion bar to be aligned with a force torsion bar hole of the control surface, the force torsion bar reference hole mark of the pin shaft is aligned with the mounting reference mark of the base, then the force torsion bar of the torsion spring is inserted into the force torsion bar hole of the control surface, and the pin shaft is inserted into the pin shaft holes of the base and the control surface, so that the end face of the mounting surface of the pin shaft torsion bar is ensured to be contacted with the outer side face of the right baffle plate at the upper part of the shaft shoulder of the base.
S2: and folding the control surface to a set angle, measuring the torque of the torsion spring, and installing the nut at the left end of the pin shaft and locking and fixing when the torque of the torsion spring is within a design range, so that the assembly is completed.
S3: if the measured torsion moment of the torsion spring is smaller than the design range, the torsion spring and the pin shaft are removed together;
s4: and pulling out the force torsion bar of the torsion spring from the force torsion bar reference hole of the pin shaft, and according to the measurement result, rotating the torsion spring anticlockwise to insert the force torsion bar into the corresponding pin shaft force torsion bar hole.
S5: the other end of the torsion spring is aligned with a force torsion bar hole of the control surface, a force torsion bar reference hole mark of the pin shaft is aligned with a base mounting reference mark, the torsion bar is inserted into the force torsion bar hole of the control surface again, the pin shaft is inserted into pin shaft holes of the base and the control surface, and the contact between the end face of the pin shaft torsion bar mounting surface and the outer side face of the right baffle plate at the upper part of the base shaft shoulder is ensured.
S6: and folding the control surface to a set angle, measuring the torque of the torsion spring, and installing the nut at the left end of the pin shaft and locking and fixing when the torque of the torsion spring is within a design range, so that the assembly is completed.
S7: when the measured torsion moment of the torsion spring is larger than the design range, the torsion spring and the pin shaft are removed together;
s8: and pulling out the force torsion bar of the torsion spring from the force torsion bar reference hole of the pin shaft, and rotating the torsion spring clockwise according to the measurement result to insert the force torsion bar into the corresponding pin shaft force torsion bar hole.
S9: the other end of the torsion spring is aligned with a force torsion bar hole of the control surface, a force torsion bar reference hole mark of the pin shaft is aligned with an installation reference mark of the base, the torsion bar is inserted into the force torsion bar hole of the control surface again, the pin shaft is inserted into pin shaft holes of the base and the control surface, and the contact between the end face of the pin shaft torsion bar installation surface and the outer side face of the right baffle plate at the upper part of the base shaft shoulder is ensured.
S10: and folding the control surface to a set angle, measuring the torque of the torsion spring, and installing the nut at the left end of the pin shaft and locking and fixing when the torque of the torsion spring is within a design range, so that the assembly is completed.
Due to the adoption of the technical scheme, the invention has the following beneficial effects: according to the adjustable torsion spring driven unfolding missile control surface and the assembly process thereof, the torsion bar hole for adjusting is added on the shaft shoulder end face of the pin shaft, so that the adjustability of torsion of the torsion spring in the assembly process is realized, the consistency of the torsion of the folding torsion spring of the control surface after assembly is ensured, and the problem of scrapping of parts is avoided; meanwhile, the position of a force torsion bar reference hole and the outer side surface of a right baffle plate at the upper part of the base shaft shoulder are processed with assembly reference mark marks on the end surface of the pin shaft shoulder, so that errors are prevented in the assembly process; after the new structure and the assembly process are adopted, the grouping matching process and the process of re-disassembling and assembling parts of components in the existing assembly process are eliminated, and the one-time assembly success rate is improved, so that the overall assembly efficiency is greatly improved.
Drawings
FIG. 1 is a schematic view of a control surface structure of a debugged torsion spring driven deployment missile;
FIG. 2 is a schematic side view of a control surface of an adjustable torsion spring driven deployed missile.
In the figure: 1. a base; 2. a control surface; 3. a torsion spring; 4, pin shafts; 5. force torsion bar through hole; 6. marking a reference hole; 7. and (5) installing a reference mark.
Detailed Description
The invention will be explained in more detail by the following examples, the purpose of which is to protect all technical improvements within the scope of the invention.
An adjustable torsion spring driven unfolding missile control surface comprises a base 1, a control surface 2, a torsion spring 3 and a pin shaft 4; the root of the control surface 2 is arranged in a control surface mounting groove of the base 1, and the pin shaft 4 is arranged in pin shaft holes of the base 1 and the control surface 2, wherein a square hole mounting surface of the base of the pin shaft 4 is matched with a square through hole of a baffle plate at the left side of the upper part of a shaft shoulder of the base 1 to prevent the pin shaft from rotating; the torsion spring 3 is arranged on the torsion spring mounting surface of the pin shaft 4, one end of the torsion spring is inserted into a force torsion bar hole of the control surface 2, and the other end of the torsion spring is inserted into a force torsion bar through hole 5 of the pin shaft 4; the pin shaft 4 is locked and fixed by a nut through the leftmost thread.
When the adjustable torsion spring drives the control surface of the unfolding missile to be assembled, the torsion spring 3 is arranged on the torsion spring installation surface of the pin shaft 4, and one end of the torsion spring is inserted into a force torsion bar reference hole of the pin shaft 4; the root of the control surface 2 is arranged in a control surface mounting groove of the base 1, so that a pin shaft hole at the root of the control surface 2 is ensured to be coaxial with a circular through hole in the middle of a baffle plate at the right side of the upper part of the shaft shoulder; the other end of the torsion spring 3 enables the force torsion bar to be aligned with a force torsion bar hole of the control surface 2, a force torsion bar reference hole mark 6 of the pin shaft 4 is aligned with a mounting reference mark 7 of the base, then the torsion spring 3 enables the force torsion bar to be inserted into the force torsion bar hole of the control surface 2, the pin shaft 4 is inserted into pin shaft holes of the base 1 and the control surface 2, and the end face of a torsion spring mounting surface of the pin shaft 4 is ensured to be contacted with the outer side face of a baffle plate on the upper right side of a shaft shoulder of the base 1; and folding the control surface 2 to a set angle, measuring the torque of the torsion spring 3, and installing the nut at the left end of the pin shaft 4 and locking and fixing when the torque of the torsion spring 3 is within a design range, so that the assembly is completed.
When the measured torque of the torsion spring 3 is smaller than the design range, the torsion spring 3 and the pin shaft 4 are removed together; pulling out the force torsion bar of the torsion spring from the pin shaft force torsion bar reference hole, and according to the measurement result, rotating the torsion spring 3 anticlockwise, and inserting the force torsion bar into the corresponding pin shaft 4 force torsion bar through hole 5; aligning the force torsion bar at the other end of the torsion spring 3 with the force torsion bar hole of the control surface 2, aligning the force torsion bar reference hole mark 6 of the pin shaft 4 with the mounting reference mark 7 of the base 1, inserting the force torsion bar of the torsion spring 3 into the force torsion bar hole of the control surface 2 again, inserting the pin shaft 4 into the pin shaft holes of the base 1 and the control surface 2, and ensuring that the end face of the torsion spring mounting surface of the pin shaft 4 contacts with the outer side face of the right baffle at the upper part of the shaft shoulder of the base 1; and folding the control surface 2 to a set angle, measuring the torque of the torsion spring 3, and installing the nut at the left end of the pin shaft 4 and locking and fixing when the torque of the torsion spring 3 is within a design range, so that the assembly is completed.
When the measured torque of the torsion spring 3 is larger than the design range, the torsion spring 3 and the pin shaft 4 are removed together; pulling out the force torsion bar of the torsion spring from the pin shaft force torsion bar reference hole, rotating the torsion spring 3 clockwise according to the measurement result, and inserting the force torsion bar into the corresponding pin shaft 4 force torsion bar through hole 5; aligning the force torsion bar at the other end of the torsion spring 3 with the force torsion bar hole of the control surface 2, aligning the force torsion bar reference hole mark 6 of the pin shaft 4 with the mounting reference mark 7 of the base 1, inserting the force torsion bar of the torsion spring 3 into the force torsion bar hole of the control surface 2 again, inserting the pin shaft 4 into the pin shaft holes of the base 1 and the control surface 2, and ensuring that the end face of the torsion spring mounting surface of the pin shaft 4 contacts with the outer side face of the right baffle at the upper part of the shaft shoulder of the base 1; and folding the control surface 2 to a set angle, measuring the torque of the torsion spring 3, and installing the nut at the left end of the pin shaft 4 and locking and fixing when the torque of the torsion spring 3 is within a design range, so that the assembly is completed.
The invention is not described in detail in the prior art.
Claims (4)
1. An assembly process of an adjustable torsion spring driven unfolding missile rudder surface comprises a base (1), a rudder surface (2), a torsion spring (3), a pin shaft (4), a force torsion bar through hole (5), a reference hole mark (6) and an installation reference mark (7); the base (1) is a short round shaft with a shaft shoulder, a ring groove used for being connected and fixed with the missile is formed in the lower part of the shaft, a control surface mounting groove formed by two baffles is formed in the upper part of the shaft shoulder, a square through hole is formed in the middle of the left baffle, and a round through hole is formed in the middle of the right baffle; two sides of the root of the control surface (2) are planes, two through holes are formed in the direction perpendicular to the planes of the root, the diameter of the upper part of the control surface is smaller than that of the control surface to enable the torsion bar to be in a hole, the diameter of the lower part of the control surface is larger than that of the lower part of the control surface to be in a pin hole, the lower end face of the root is an arc face, and the arc of the lower end face of the root is concentric with the pin hole; force torsion bars extend out of two ends of the torsion spring (3); the pin shaft (4) is a step-shaped short shaft, a shaft shoulder, a torsion spring mounting surface, a base round hole mounting surface, a control surface hole mounting surface, a base square hole mounting surface and threads at the leftmost end are sequentially arranged from right to left, and a plurality of force torsion bar through holes (5) are uniformly distributed along the circumferential direction on the end face of the shaft shoulder; the root of the control surface (2) is arranged in a control surface mounting groove at the upper part of the shaft shoulder of the base (1), and the pin shaft (4) is arranged in a through hole of two baffles at the upper part of the shaft shoulder of the base (1) and a pin shaft hole at the root of the control surface (2), wherein a square hole mounting surface of the base of the pin shaft (4) is matched with a square through hole of a left baffle at the upper part of the shaft shoulder of the base (1); the torsion spring (3) is arranged on a torsion spring mounting surface of the pin shaft (4), one end of the torsion spring is inserted into a force torsion bar hole of the control surface (2), and the other end of the torsion spring is inserted into a force torsion bar through hole (5) of the pin shaft (4); the pin shaft (4) is locked and fixed by a nut through the leftmost thread; the method is characterized in that: the force torsion bar through hole (5) is provided with a reference hole, and the force torsion bar reference hole is provided with a reference hole mark (6); when the torsion spring (3) is installed for the first time, one end of the torsion spring is inserted into a force torsion bar reference hole on the end face of the shaft shoulder of the pin shaft (4), and the other end of the torsion spring is inserted into a force torsion bar hole on the root of the control surface (2); then folding the control surface (2) to a set angle, measuring the torque of the torsion spring (3), and installing a nut at the left end of the pin shaft (4) and locking and fixing when the torque of the torsion spring (3) is within a design range; when the torque of the torsion spring (3) is smaller than the design range, according to the measurement result, the force-making torsion bar of the torsion spring (3) inserted into the shaft shoulder end surface of the pin shaft (4) rotates anticlockwise, then the torsion bar is inserted into a force-making torsion bar hole corresponding to the shaft shoulder end surface of the pin shaft (4), the control surface (2) is refolded to a set angle, the torque of the torsion spring (3) is measured, and when the torque of the torsion spring (3) is within the design range, a left end nut of the pin shaft (4) is installed and locked and fixed; when the torque of the torsion spring (3) is larger than the design range, according to the measurement result, the force-making torsion bar of the torsion spring (3) inserted into the shaft shoulder end face of the pin shaft (4) rotates clockwise, then is inserted into a force-making torsion bar hole corresponding to the shaft shoulder end face of the pin shaft (4), the control surface (2) is refolded to a set angle, the torque of the torsion spring (3) is measured, and when the torque of the torsion spring (3) is in the design range, a left end nut of the pin shaft (4) is installed and locked and fixed.
2. The assembly process of the adjustable torsion spring driven unfolding missile rudder surface according to claim 1, which is characterized in that: the outer side surface of the right baffle plate at the upper part of the shaft shoulder of the base (1) is provided with a mounting reference mark (7).
3. The assembly process of the adjustable torsion spring driven unfolding missile rudder surface according to claim 1, which is characterized in that: a blind hole is formed in the middle of the end face of the shaft shoulder of the pin shaft (4).
4. The assembly process of the adjustable torsion spring driven unfolding missile rudder surface according to claim 1, which is characterized in that: the specific assembly steps are as follows:
s1: the torsion spring (3) is arranged on the torsion spring installation surface of the pin shaft (4), and one end of the torsion spring is inserted into a force torsion bar reference hole of the pin shaft (4); the root of the control surface (2) is arranged in a control surface mounting groove at the upper part of a shaft shoulder of the base (1), so that the pin shaft hole at the root of the control surface (2) is ensured to be coaxial with a circular through hole in the middle of a baffle at the right side at the upper part of the shaft shoulder; the other end of the torsion spring (3) is aligned with a force torsion bar hole of the control surface (2), a reference mark (7) is arranged on the Ji De (1) by the reference hole mark (6) of the pin shaft (4), then the force torsion bar of the torsion spring (3) is inserted into the force torsion bar hole of the control surface (2), the pin shaft (4) is inserted into the pin shaft holes of the base (1) and the control surface (2), and the end surface of the torsion spring mounting surface of the pin shaft (4) is ensured to be contacted with the outer side surface of the baffle plate at the upper part of the shaft shoulder of the base (1);
s2: the control surface (2) is folded to a set angle, the torque of the torsion spring (3) is measured, and when the torque of the torsion spring (3) is within a design range, a nut at the left end of the pin shaft (4) is installed, locked and fixed, and the assembly is completed;
s3: if the measured torque of the torsion spring (3) is smaller than the design range, the torsion spring (3) and the pin shaft (4) are removed together;
s4: pulling out the force torsion bar of the torsion spring (3) from the pin shaft (4) to enable the force torsion bar reference hole, and according to the measurement result, rotating the torsion spring (3) anticlockwise to enable the force torsion bar to be inserted into the force torsion bar hole corresponding to the pin shaft (4);
s5: aligning the other end of the torsion spring (3) with a force torsion bar hole of the control surface (2), mounting a reference mark (7) on the Ji De (1) by using a reference hole mark (6) of the pin shaft (4), inserting the torsion bar of the torsion spring (3) into the force torsion bar hole of the control surface (2), inserting the pin shaft (4) into pin shaft holes of the base (1) and the control surface (2), and ensuring that the end surface of a torsion spring mounting surface of the pin shaft (4) is contacted with the outer side surface of a baffle plate at the upper part of the shaft shoulder of the base (1);
s6: the control surface (2) is folded to a set angle, the torque of the torsion spring (3) is measured, and when the torque of the torsion spring (3) is within a design range, a nut at the left end of the pin shaft (4) is installed, locked and fixed, and the assembly is completed;
s7: when the measured torque of the torsion spring (3) is larger than the design range, the torsion spring (3) and the pin shaft (4) are removed together;
s8: pulling out the force torsion bar of the torsion spring (3) from the pin shaft (4) to enable the force torsion bar reference hole, rotating the torsion spring (3) clockwise according to the measurement result, and inserting the force torsion bar into the force torsion bar hole corresponding to the pin shaft (4);
s9: aligning the other end of the torsion spring (3) with a force torsion bar hole of the control surface (2), mounting a reference mark (7) on the Ji De (1) by using a reference hole mark (6) of the pin shaft (4), inserting the torsion bar of the torsion spring (3) into the force torsion bar hole of the control surface (2), inserting the pin shaft (4) into pin shaft holes of the base (1) and the control surface (2), and ensuring that the end surface of a torsion spring mounting surface of the pin shaft (4) is contacted with the outer side surface of a baffle plate at the upper part of the shaft shoulder of the base (1);
s10: and (3) folding the control surface (2) to a set angle, measuring the torque of the torsion spring (3), and installing the left end nut of the pin shaft (4) and locking and fixing when the torque of the torsion spring (3) is within a design range, so that the assembly is completed.
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| CN105256739A (en) * | 2015-10-09 | 2016-01-20 | 石家庄优创科技股份有限公司 | Torsion spring type electric barrier machine |
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| 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 |
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