A redundant unlocking sleeve structure based on a double pin extractor

Abstract

The present invention relates to a redundant unlocking sleeve structure based on a double pin puller, belonging to the technical field of deployment and retraction drive; it includes two pin pullers, a sleeve and a suspension point connection seat; wherein, the suspension point connection seat is a U-shaped structure with an opening vertically upward; the sleeve is axially horizontally arranged in the inner cavity of the suspension point connection seat; the two pin pullers are symmetrically arranged on both sides of the suspension point connection seat; the head end of the pin puller is provided with a piston that can expand and contract in the horizontal direction; through holes are arranged at corresponding positions on both side walls of the suspension point connection seat, so that the pistons of the two pin pullers extend into the inner cavity of the suspension point connection seat from the through holes on both side walls of the suspension point connection seat, and the sleeve is limited by the two pistons; the sleeve serves as the suspension point of the external deceleration parachute, connecting the external deceleration parachute and the external spacecraft; the present invention designs a simplified, feasible and highly reliable redundant unlocking sleeve structure based on a double pin puller. On this basis, it can be evolved and improved according to actual interface requirements, which can greatly reduce the number of size iterations and improve the design efficiency.

Description

Technical Field

[0001] The present invention belongs to the technical field of deployment and retraction drive, and relates to a redundant unlocking sleeve structure based on a double pin puller. Background Art

[0002] During the process of a spacecraft entering, decelerating, and landing, a parachute is required to decelerate for a safe landing. When single-stage deceleration cannot meet the mission requirements, a multi-stage parachute deceleration scheme needs to be adopted. As an essential component in the multi-stage parachute deceleration scheme, one of the main working characteristics of the deceleration parachute is to unlock and separate after pulling out the main parachute. Therefore, relatively high reliability requirements are imposed on the reliability of the pyrotechnic device and the reliability of the sling separation process. When the pyrotechnic device fails to ignite successfully or the sling fails to unlock and separate due to certain factors after ignition, the deceleration parachute will not be able to separate from the spacecraft, and thus will not be able to pull out the main parachute pack, and the main parachute cannot be opened.

[0003] To improve the reliability of the sling separation of the deceleration parachute, existing patents have mentioned using a combination of two identical parachute release devices and sleeves to enhance the reliability of sling separation. However, the overall structure of this patent is complex, specific components are selected, and the key dimensions of each component and their constraint relationships are not clearly defined. When selecting, the dimensions of each component need to be iterated multiple times, which greatly reduces the design efficiency. Summary of the Invention

[0004] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, a redundant unlocking sleeve structure based on a double pin puller is proposed, and a simplified and feasible high-reliability double pin puller redundant unlocking sleeve structure is designed. On this basis, it can be evolved and improved according to actual interface requirements, which can significantly reduce the number of size iterations and improve the design efficiency.

[0005] The technical solution adopted by the present invention to solve the problem is:

[0006] A redundant unlocking sleeve structure based on a double pin puller includes two pin pullers, a sleeve, and a sling connection seat; wherein, the sling connection seat is a U-shaped structure with an opening vertically upward; the sleeve is axially horizontally arranged in the inner cavity of the sling connection seat; the two pin pullers are symmetrically arranged on both sides of the sling connection seat; a piston that expands and contracts in the horizontal direction is provided at the head end of the pin puller; through holes are provided at corresponding positions on both side walls of the sling connection seat, so that the pistons of the two pin pullers extend into the inner cavity of the sling connection seat from the through holes on both side walls of the sling connection seat, and the sleeve is limited by the two pistons; the sleeve serves as the sling of the external deceleration parachute and connects the external deceleration parachute to the external spacecraft.

[0007] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, the sleeve is a cylindrical structure axially horizontally placed; grooves are provided at both axial end faces of the sleeve; the pistons of the two pin pullers are embedded into the two grooves of the sleeve from both sides to realize the limitation of the sleeve.

[0008] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, the pin puller includes a piston, a body, and a mounting seat; wherein, the body is placed opposite to the suspension point connecting seat, the mounting seat is arranged on one side of the body, and the mounting seat corresponds to the through hole on the side wall of the suspension point connecting seat; the piston is coaxially installed in the mounting seat; the piston is axially translated to extend or retract into the mounting seat.

[0009] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, during assembly, the mounting seat extends into the through hole on the side wall of the suspension point connecting seat, and the thickness of the mounting seat is the same as the thickness of the side wall of the suspension point connecting seat.

[0010] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, the working process of the unlocking sleeve structure is as follows:

[0011] When both 2 pin pullers are working properly, when receiving the unlocking ignition command transmitted from the outside, the pistons of the 2 pin pullers are simultaneously translated and retracted into the corresponding mounting seats, the sleeve loses its restraint, and disengages from the open end of the suspension point connecting seat, realizing the separation of the external deceleration parachute from the external spacecraft;

[0012] When 1 pin puller is working properly and the other pin puller fails, when receiving the unlocking ignition command transmitted from the outside, the piston of the normally working pin puller is translated and retracted into the corresponding mounting seat, the sleeve loses the restraint on one side, and disengages from the open end of the suspension point connecting seat in a translational or flipping manner, realizing the separation of the external deceleration parachute from the external spacecraft.

[0013] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, set the axial length of the piston of the left pin puller as a11, the axial length of the mounting seat as a21, and the piston diameter as a31; set the axial length of the piston of the right pin puller as a12, the axial length of the mounting seat as a22, and the piston diameter as a32; set the axial length of the sleeve as b1, the outer diameter of the sleeve as b2, the inner diameter of the left groove of the sleeve as b31, the inner diameter of the right groove of the sleeve as b32, the axial mating length between the left groove of the sleeve and the left pin puller as b41, the axial mating length between the right groove of the sleeve and the right pin puller as b42, the outer fillet radius of the edge of the sleeve end face as b5; the distance between the suspension point connecting seats is c1, the wall thickness of the left side of the suspension point connecting seat is c21, and the wall thickness of the left side of the suspension point connecting seat is c22;

[0014] After the redundant unlocking sleeve structure is assembled, when no unlocking ignition command is received, the dimensional conditions that the sleeve does not disengage should satisfy:

[0015]

[0016] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, when both 2 pin pullers are working properly and receive an unlocking ignition instruction transmitted from the outside, the dimensional condition that the pistons of the 2 pin pullers should simultaneously translate and retract into the corresponding mounting seats is:

[0017] b1 < c1 - (c21 - a21) - (c22 - a22).

[0018] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, when 1 pin puller is working properly and the other 1 pin puller fails, and after receiving an unlocking ignition instruction transmitted from the outside, the dimensional condition that the sleeve should be disengaged from the open end of the suspension point connecting seat in a translational motion manner is:

[0019] b1 < c1 - (c21 - a21) - (a12 + a22 - c22)

[0020] b1 < c1 - (c22 - a22) - (a11 + a21 - c21).

[0021] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, when 1 pin puller is working properly and the other 1 pin puller fails, and after receiving an unlocking ignition instruction transmitted from the outside, the sleeve cannot be disengaged in a translational motion. Under the action of the external deceleration parachute pulling force, the sleeve is disengaged from the open end of the suspension point connecting seat in a flipping manner.

[0022] In the above-mentioned redundant unlocking sleeve structure based on a double pin puller, assuming that the farthest length from the lower edge of the groove of the sleeve pointing to the failed pin puller to the bottom end of the sleeve pointing to the side wall of the suspension point connecting seat is l, the calculation formula of l is:

[0023]

[0024] In the formula, i is the serial number of the pin puller, i = 1, 2;

[0025] The dimensional condition that the sleeve should be disengaged from the open end of the suspension point connecting seat in a flipping manner is:

[0026]

[0027] The beneficial effects of the present invention compared with the prior art are:

[0028] (1) The present invention provides a design form and design method for a deceleration parachute suspension point unlocking and separating structure with double redundancy and high reliability. By clarifying the working forms of each component, the high reliability of the deceleration parachute suspension point separation is improved;

[0029] (2) By refining the basic structural characteristics of each component, the present invention can be evolved and improved on the basis of retaining the basic structural characteristics according to requirements, so as to obtain an unlocking structure that meets both functional requirements and interface requirements;

[0030] (3) By identifying the key dimensions and establishing the constraint relationships between dimensions, the present invention can reduce the time wasted in selecting non-critical dimensions during design, reduce the number of iterations, and improve design efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 is an overall schematic diagram of the redundant unlocking sleeve structure of the present invention;

[0032] Figure 2 is a schematic diagram of the pin extractor structure of the present invention;

[0033] Figure 3 is a schematic diagram of the sleeve of the present invention;

[0034] Figure 4 is a schematic diagram of the suspension point connection seat of the present invention;

[0035] Figure 5 is a schematic diagram of the dimensions of two pin extractors of the present invention;

[0036] Figure 6 is a schematic diagram of the dimensions of the sleeve of the present invention;

[0037] Figure 7 is a schematic diagram of the dimensions of the suspension point connection seat of the present invention;

[0038] Figure 8 is a schematic diagram of the translational detachment of the sleeve of the present invention;

[0039] Figure 9 is a schematic diagram of the flipping detachment of the sleeve of the present invention;

[0040] Figure 10 is a schematic diagram of the farthest length l of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0041] The present invention will be further described below in conjunction with embodiments.

[0042] The present invention provides a redundant unlocking sleeve structure based on a double pin extractor. By clarifying the working forms of each component, refining the necessary structural characteristics of each component, identifying the key dimensions of each component, and establishing the constraint relationships between the key dimensions, a simplified and feasible basic structure of the double pin extractor redundant unlocking sleeve is obtained. On this basis, it can be evolved and improved according to actual interface requirements. When using this method for design, the number of dimension iterations can be significantly reduced, and the design efficiency can be improved.

[0043] The redundant unlocking sleeve structure based on a double pin extractor, as Figure 1 shown, specifically includes two pin extractors 1, a sleeve 2, and a suspension point connection seat 3; wherein, the suspension point connection seat 3 is a U-shaped structure with an opening vertically upward, as Figure 4As shown in the figure, the sleeve 2 is axially horizontally arranged in the inner cavity of the suspension point connecting seat 3; two pin pullers 1 are symmetrically arranged on both sides of the suspension point connecting seat 3; a piston 4 that telescopically moves horizontally is arranged at the head end of the pin puller 1; through holes are arranged at corresponding positions on both side walls of the suspension point connecting seat 3, enabling the pistons 4 of the two pin pullers 1 to extend into the inner cavity of the suspension point connecting seat 3 from the through holes on both side walls of the suspension point connecting seat 3, and the sleeve 2 is limited by the two pistons 4; the sleeve 2 serves as the suspension point of the external deceleration parachute, connecting the external deceleration parachute and the external spacecraft.

[0044] As Figure 3 shown, the sleeve 2 is a cylindrical structure placed axially horizontally; grooves are arranged at both axial end faces of the sleeve 2; the pistons 4 of the two pin pullers 1 are inserted into the two grooves of the sleeve 2 from both sides, realizing the limitation of the sleeve 2.

[0045] As Figure 2 shown, the pin puller 1 includes a piston 4, a body 5, and a mounting seat 6; among them, the body 5 is placed facing the suspension point connecting seat 3, the mounting seat 6 is arranged on one side of the body 5, and the mounting seat 6 corresponds to the through hole on the side wall of the suspension point connecting seat 3; the piston 4 is coaxially installed in the mounting seat 6; the piston 4 can translate axially to extend or retract into the mounting seat 6.

[0046] During assembly, the mounting seat 6 extends into the through hole on the side wall of the suspension point connecting seat 3, and the thickness of the mounting seat 6 is the same as the thickness of the side wall of the suspension point connecting seat 3.

[0047] The working process of the unlocking sleeve structure is as follows:

[0048] When both of the two pin pullers 1 are working properly, when receiving the unlocking ignition command from the outside, the pistons 4 of the two pin pullers 1 simultaneously translate and retract into the corresponding mounting seats 6, the sleeve 2 loses its restraint, and disengages from the open end of the suspension point connecting seat 3, realizing the separation of the external deceleration parachute and the external spacecraft;

[0049] When one of the two pin pullers 1 is working properly and the other is malfunctioning, when receiving the unlocking ignition command from the outside, the piston 4 of the properly working pin puller 1 translates and retracts into the corresponding mounting seat 6, the sleeve 2 loses the restraint on one side, and disengages from the open end of the suspension point connecting seat 3 in a translational or flipping manner, realizing the separation of the external deceleration parachute and the external spacecraft, as Figure 8 、 Figure 9 shown.

[0050] For the suspension point connecting seat 3 with two pin pullers 1 with pistons 4 that can contract inwardly installed thereon and the sleeve 2 installed on the pistons, when any one of the pistons 4 contracts inwardly after receiving the ignition command, the sleeve 2 can be disengaged from the restraint, realizing the separation of the deceleration parachute.

[0051] As Figure 5 、 Figure 6 、 Figure 7As shown in the figure, set the axial length of the piston 4 of the left pin puller 1 as a11, the axial length of the mounting seat 6 as a21, and the diameter of the piston 4 as a31; set the axial length of the piston 4 of the right pin puller 1 as a12, the axial length of the mounting seat 6 as a22, and the diameter of the piston 4 as a32; set the axial length of the sleeve 2 as b1, the outer diameter of the sleeve 2 as b2, the inner diameter of the left groove of the sleeve 2 as b31, the inner diameter of the right groove of the sleeve 2 as b32, the axial mating length of the left groove of the sleeve 2 and the left pin puller 1 as b41, the axial mating length of the right groove of the sleeve 2 and the right pin puller 1 as b42, and the outer fillet radius of the end face edge of the sleeve 2 as b5; the distance between the suspension point connecting seats 3 is c1, the wall thickness of the left side of the suspension point connecting seat 3 is c21, and the wall thickness of the left side of the suspension point connecting seat 3 is c22; the specific dimensions are shown in Table 1.

[0052] Table 1

[0053]

[0054]

[0055] After the redundant unlocking sleeve structure is assembled and the unlocking ignition instruction is not received, the dimensional conditions that the sleeve 2 does not disengage should satisfy are:

[0056]

[0057] When both 2 pin pullers 1 are working properly and receive the unlocking ignition instruction transmitted from the outside, the dimensional conditions that the pistons 4 of the 2 pin pullers 1 translate and retract into the corresponding mounting seats 6 simultaneously should satisfy are:

[0058] b1 < c1 - (c21 - a21) - (c22 - a22).

[0059] When 1 pin puller 1 is working properly and the other pin puller 1 fails, after receiving the unlocking ignition instruction transmitted from the outside, as Figure 8 shown, the dimensional conditions that the sleeve 2 disengages from the open end of the suspension point connecting seat 3 by translational motion should satisfy are:

[0060] b1 < c1 - (c21 - a21) - (a12 + a22 - c22)

[0061] b1 < c1 - (c22 - a22) - (a11 + a21 - c21).

[0062] When 1 pin puller 1 is working properly and the other pin puller 1 fails, after receiving the unlocking ignition instruction transmitted from the outside, the sleeve 2 cannot disengage by translational motion. As Figure 9 shown, under the action of the external deceleration parachute tension, the sleeve 2 disengages from the open end of the suspension point connecting seat 3 by flipping motion.

[0063] As Figure 10As shown in the figure, the maximum length from the lower edge of the groove of the setting sleeve 2 pointing to the failure pull pin 1 to the bottom end of the sleeve 2 pointing to the side wall of the suspension point connecting seat 3 is set as l, and the calculation formula of l is:

[0064]

[0065] In the formula, i is the serial number of the pull pin 1, and i = 1, 2;

[0066] The dimensional conditions that the sleeve 2 should meet when it is disengaged from the open end of the suspension point connecting seat 3 in a flipping manner are:

[0067]

[0068] The suspension point connecting seat 3 is the installation platform for the pull pin 1, and it can actually be a frame or a parachute bay. The basic structural feature is that the installation surfaces of the two pull pins 1 are parallel and have a certain distance.

[0069] The key dimensions are the dimensions at which each component mates during combination.

[0070] The constraint relationship of the key dimensions refers to the constraint principle that should be followed when selecting the key dimensions of each component in order to achieve the redundant separation of this structural form, so that the sleeve can be detached as long as any one pull pin works.

[0071] The assembly process is as follows: Install one pull pin 1 on the suspension point connecting seat 3 according to the reserved interface. At this time, place the sleeve 2 at the piston 4 of the pull pin 1, install the other pull pin 1 on the suspension point connecting seat 3, and dock the interfaces of the suspension point connecting seat 3 and the sleeve 2, and complete the assembly based on this sequence.

[0072] The present invention provides a design form and design method for a double-redundancy and high-reliability deceleration parachute suspension point unlocking and separating structure. By clarifying the working forms of each component, the high reliability of the deceleration parachute suspension point separation is improved; secondly, by refining the basic structural features of each component, it is possible to evolve and improve on the basis of retaining the basic structural features according to requirements, so as to obtain an unlocking structure that meets both functional requirements and interface requirements; by identifying the key dimensions and establishing the constraint relationship between the dimensions, it is possible to reduce the time wasted in selecting non-critical dimensions during design and reduce the number of iterations, thereby improving the design efficiency.

[0073] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and decorations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention all fall within the protection scope of the technical solution of the present invention.

Claims

1. A redundant unlocking sleeve structure based on a double pin extractor, characterized in that: The invention comprises two pin pullers (1), a sleeve (2) and a suspension point connection seat (3); wherein the suspension point connection seat (3) is a U-shaped structure with an opening placed vertically upward; the sleeve (2) is axially and horizontally arranged in the inner cavity of the suspension point connection seat (3); the two pin pullers (1) are symmetrically arranged on both sides of the suspension point connection seat (3); a piston (4) which can be extended and retracted in the horizontal direction is arranged at the head end of the pin puller (1); through holes are arranged at corresponding positions on the two side walls of the suspension point connection seat (3) so that the pistons (4) of the two pin pullers (1) can extend into the inner cavity of the suspension point connection seat (3) from the through holes on the two side walls of the suspension point connection seat (3), and the sleeve (2) can be limited by the two pistons (4); the sleeve (2) serves as the suspension point of the external deceleration parachute and connects the external deceleration parachute with the external spacecraft; The working process of the unlocking sleeve structure is: When the two pin pullers (1) are working normally, upon receiving an unlocking and ignition command from the outside, the pistons (4) of the two pin pullers (1) simultaneously translate and retract into the corresponding mounting seats (6), and the sleeve (2) loses its restraint and detaches from the open end of the suspension point connection seat (3), thereby realizing the separation of the external deceleration parachute from the external spacecraft; When one pin puller (1) works normally and the other pin puller (1) fails, when an unlocking and ignition command from the outside is received, the piston (4) of the normally working pin puller (1) moves horizontally and retracts into the corresponding mounting seat (6), and the sleeve (2) loses the constraint on one side and is separated from the open end of the suspension point connection seat (3) by a translational motion or a flipping motion, thereby realizing the separation of the external deceleration parachute from the external spacecraft; The axial length of the piston (4) of the left pin puller (1) is set to a11, the axial length of the mounting seat (6) is set to a21, and the diameter of the piston (4) is set to a31; the axial length of the piston (4) of the right pin puller (1) is set to a12, the axial length of the mounting seat (6) is set to a22, and the diameter of the piston (4) is set to a32; the axial length of the sleeve (2) is set to b1, the outer diameter of the sleeve (2) is set to b2, the inner diameter of the left groove of the sleeve (2) is set to b31, the inner diameter of the right groove of the sleeve (2) is set to b32, the axial matching length between the left groove of the sleeve (2) and the left pin puller (1) is set to b41, the axial matching length between the right groove of the sleeve (2) and the right pin puller (1) is set to b42, and the outer fillet radius of the end face edge of the sleeve (2) is set to b5; the spacing of the hanging point connection seat (3) is set to c1, the left wall thickness of the hanging point connection seat (3) is set to c21, and the left wall thickness of the hanging point connection seat (3) is set to c22; After the redundant unlocking sleeve structure is assembled, if no unlocking ignition command is received, the dimensional conditions that the sleeve (2) should meet for not disengaging are: The two pin pullers (1) are both working normally. After receiving the unlocking ignition command from the outside, the pistons (4) of the two pin pullers (1) are simultaneously translated and retracted into the corresponding mounting seats (6). The dimensional conditions to be met are: b1<c1-(c21-a21)-(c22-a22) One pin puller (1) works normally, and the other pin puller (1) fails. After receiving the unlocking ignition command from the outside, the sleeve (2) is separated from the open end of the suspension point connection seat (3) in a translational manner. The dimensional conditions that should be met are: b1 < c1 - (c21 - a21) - (a12 + a22 - c22) b1 < c1 - (c22 - a22) - (a11 + a21 - c21).

2. The redundant unlocking sleeve structure based on a double pin extractor according to claim 1, characterized in that: The sleeve (2) is a cylindrical structure horizontally placed axially; grooves are provided on both axial end faces of the sleeve (2); the pistons (4) of the two pull pin devices (1) are inserted into the two grooves of the sleeve (2) from both sides to limit the sleeve (2).

3. The redundant unlocking sleeve structure based on a double pin extractor according to claim 1, characterized in that: The pull pin device (1) includes a piston (4), a body (5) and a mounting seat (6); wherein, the body (5) is placed opposite to the suspension point connecting seat (3), the mounting seat (6) is arranged on one side of the body (5), and the mounting seat (6) corresponds to the through hole on the side wall of the suspension point connecting seat (3); the piston (4) is coaxially installed in the mounting seat (6); the piston (4) is translated axially to extend or retract into the mounting seat (6).

4. The redundant unlocking sleeve structure based on a double pin extractor according to claim 3, characterized in that: During assembly, the mounting seat (6) extends into the through hole on the side wall of the suspension point connecting seat (3), and the thickness of the mounting seat (6) is the same as the thickness of the side wall of the suspension point connecting seat (3).

5. The redundant unlocking sleeve structure based on a double pin extractor according to claim 4, characterized in that: When one pull pin device (1) works normally and the other pull pin device (1) fails, after receiving the unlocking ignition instruction from the outside, the sleeve (2) cannot translate and disengage. Under the action of the external deceleration parachute tension, the sleeve (2) disengages from the open end of the suspension point connecting seat (3) by means of flipping.

6. The redundant unlocking sleeve structure based on a double pin extractor according to claim 5, characterized in that: Set the maximum length from the lower edge of the groove of the sleeve (2) pointing to the failed pull pin device (1) to the bottom end of the sleeve (2) pointing to the side wall of the suspension point connecting seat (3) as l, and the calculation formula of l is: In the formula, i is the serial number of the pull pin device (1), i = 1, 2; The dimensional conditions that the sleeve (2) should meet when disengaging from the open end of the suspension point connecting seat (3) by means of flipping are:

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