JP2016210333A - Payload emergency escape system for rocket - Google Patents

Abstract

PROBLEM TO BE SOLVED: To enable protection and recovery of a payload, by solving the problem in which, in a conventional system, as the entire rocket is destroyed, the payload is also destroyed, and it is impossible to recover and reuse them.SOLUTION: A rocket R includes: a first stage R1; a stage PS for mounting for holding a payload PL; and a fairing F. A payload emergency escape system includes: a rocket for separation for imparting propulsion power in an axial direction for separating from the first stage R1 to the stage PS for mounting; emergency escape means for separating between the stage PS for mounting and the first stage R1 based on reception of a destruction command of the first stage R1, and for executing separation of the stage PS for mounting by the rocket for separation; and deceleration and descent means for allowing the stage PS for mounting to decelerate and descend. When performing the destruction of the first stage R1 after launch, the payload PL can be separated quickly from the first stage R1, and protection and recovery of the payload PL can be achieved.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a rocket payload emergency escape system used when an abnormality occurs after launch in a rocket carrying a payload such as an artificial satellite.

  Conventionally, as a rocket system used when an abnormality occurs after launch, for example, there is one described in Patent Document 1 under the name of a solid fuel launch vehicle destruction system and method. The system described in Patent Document 1 avoids an influence on the ground by destroying the entire vehicle when an abnormality occurs after the vehicle is launched and it is determined that if the flight is continued, there is a danger to the ground. This system is equipped with a motor case pressurizing means and explosive means, and after launching the vehicle, the pressurizing means and explosive means are activated by a breakdown signal from the ground to break the propellant and motor case into small pieces. It has become.

Japanese National Patent Publication No. 10-511174

  However, in the conventional system as described above, the entire rocket is destroyed, so it is natural that payloads such as onboard artificial satellites are also destroyed, and they can be recovered and reused. There was a problem that it was impossible, and it was a problem to solve such a problem.

  The present invention has been made paying attention to the above-mentioned conventional problems, and when a rocket is destroyed due to the occurrence of an abnormality after launch, it is possible to detach the mounted payload and quickly move it to a safe airspace. It is an object of the present invention to provide a rocket payload emergency escape system capable of protecting and recovering a payload.

  A rocket emergency escape system according to the present invention includes a first stage which is a lowermost stage, a mounting stage which holds a payload in the uppermost stage, and a fairing which covers the payload on the mounting stage. And a separation rocket that imparts a propulsion force that separates from the first stage to the mounting stage equipped with a fairing in the axial direction, and between the mounting stage and the first stage based on reception of the first stage destruction command And an emergency escape means for detaching the mounting stage by the detaching rocket, and a deceleration lowering means for decelerating and lowering the mounting stage detached from the first stage. It is a means to solve the problem.

  The rocket payload emergency escape system according to the present invention protects and recovers the payload when the rocket after launch is broken and the rocket is destroyed to avoid impact on the ground. . In addition, since a situation that destroys the rocket after launch occurs mainly in the atmosphere, it is necessary to promptly take place before the rocket deviates significantly from the normal orbit. Thus, the rocket payload emergency escape system according to the present invention operates in accordance with the first stage destruction command used for launch.

  The first stage of the rocket generally refers to the lowermost stage part of a multistage rocket in which a plurality of stage parts including a propulsion device are combined. However, the payload emergency escape system according to the present invention has a stage part. Since it is applicable regardless of the number, the step including the propulsion device that is used first when launching from the ground is defined as the first step that is the lowest step. Therefore, the first stage in the configuration of the present invention described above is a lower stage in the case of a rocket composed of a lower stage including a propulsion device and an upper stage including a payload for mounting, and in the case of a multistage rocket. Is the bottom step. In addition, the separation rocket can use an existing rocket (a rocket other than the first stage) having sufficient propulsive force for separation, as providing the propulsive force in the axial direction.

  In the rocket payload emergency escape system according to the present invention, the emergency escape means separates between the stage for mounting and the first stage based on the reception of the first stage destruction command, and the propulsive force is generated by the release rocket. The mounting stage provided with the fairing and payload is detached from the first stage and moved positively and promptly. Thereafter, a predetermined destruction process is performed in the first stage. Further, the mounting stage having the fairing and the payload is slowly lowered by the deceleration lowering means and collected.

  Thus, according to the rocket payload emergency escape system according to the present invention, in the rocket loaded with a payload such as an artificial satellite, when the first stage is destroyed due to an abnormality after launch, It is possible to move away from the stage and move to a safe airspace positively and quickly, and the payload can be protected and recovered.

It is the side view (A) of the rocket explaining 1st Embodiment of the payload emergency escape system of the rocket concerning this invention, and the side view (B) which shows the state in emergency. It is a flowchart explaining the operation | movement at the time of normal and emergency of 1st Embodiment. It is explanatory drawing which shows the process in emergency of 1st Embodiment. It is the side view (A) of the rocket explaining 2nd Embodiment of the payload emergency escape system of the rocket concerning this invention, and each side view (B) (C) which shows the state in emergency in order. It is a flowchart explaining the operation | movement at the time of normal and emergency of 2nd Embodiment. A side view (A) of a rocket for explaining a third embodiment of a payload emergency escape system for a rocket according to the present invention, a side view (B) showing fairing separation in a normal state, and a side view showing an emergency state ( C). It is a flowchart explaining the operation | movement at the time of normal and emergency of 3rd Embodiment.

1-3 is a figure explaining 1st Embodiment of the payload emergency escape system of the rocket concerning this invention.
The rocket R shown in FIG. 1A includes a first stage R1 that is the lowest stage, a second stage R2 that is the upper stage, a mounting stage PS that holds a payload PL such as an artificial satellite in the uppermost stage, And a fairing F covering the payload PL on the stage PS.

  The first stage R1 and the second stage R2 mainly include a propulsion device such as a rocket motor using a solid propellant and a rocket engine using a liquid fuel and an oxidant. It is detachably coupled by the device B1. For the interstage separator B1, an apparatus using known devices such as a separation band, a bolt cutter, a separation nut, and a linear pyrotechnic can be applied. The same applies to other interstage separators described below. It is.

  The mounting stage PS includes a holding mechanism and a separation mechanism for the payload PL, and a propulsion mechanism such as a rocket or a thruster. The second stage R2 is a lower stage by the second interstage separator B2. It is separable.

  The fairing F protects the payload PL from aerodynamic heating or the like in the atmosphere, and is detachably coupled to the mounting stage PS by a third interstage separation device B3. Released. Further, the head of the fairing F accommodates a deceleration lowering means for decelerating and lowering the mounting stage PS after being detached.

  The deceleration descent means of this embodiment is a parachute PC (see FIG. 3), and the size and number are set according to the total weight of the payload PL, fairing F and mounting stage PS, and the parachute PC is pulled out. It consists of an auxiliary parachute for releasing and developing, an auxiliary parachute discharge device, and the like. As this deceleration descent means, in addition to the parachute PC, a parafoil (paraglider) having a glide function, a deployable wing and the like may be used, and these may be used in combination.

  The above-mentioned payload emergency escape system in the rocket R includes a detachment rocket that applies a propulsive force that detaches from the first stage R1 to the mounting stage PS having the payload PL and the fairing F in the axial direction, and the first stage R1. The emergency escape means (E) for separating the mounting stage PS and the first stage R1 based on reception of the destruction command and executing the separation of the mounting stage by the separation rocket, and the first stage R1 And a deceleration lowering means (PC) for decelerating and lowering the mounting stage.

  In the payload emergency escape system of this embodiment, a second stage R2 rocket provided between the first stage R1 and the mounting stage PS is used as a separation rocket that imparts propulsive force in the axial direction. The emergency escape means (E) includes a first interstage separation device B1 as an interstage separation device that detachably couples the mounting stage PS and the lower stage portion thereof, and a separation rocket (second stage R2). Rocket) ignition means.

  Next, the normal operation of the rocket R having the above configuration and the emergency operation of the payload emergency escape system will be described with reference to FIGS. Note that the flowchart shown in FIG. 2 explains the basic operation of the rocket R, and does not show the detailed processing flow of each control system actually used.

  The rocket R is launched by the ignition of the first stage R1 in step S1 in FIG. 2, and it is determined whether or not a destruction command is input in step ES. Normally, the destruction command is not input (NO), so step S2 In step S3, the first stage R1 and the second stage R2 are separated by the first interstage separator B1 in step S3.

  Subsequently, the rocket R ignites the second stage R2 in step S4. After the operation of the second stage R2 is completed in step S5, the rocket R is mounted on the second stage R2 by the second interstage separator B2 as necessary. The stage for use PS is separated, and the stage for mounting PS and the fairing F are opened by the third interstage separator B3 in step S6. The opening of the fairing F is performed outside the atmosphere. As a result, the payload PL is exposed to outer space, and after the posture and trajectory are adjusted by the mounting stage PS, the payload PL is separated from the mounting stage PS.

  Next, if it is determined that an abnormality has occurred in the rocket R after launch and there is a possibility that it will affect the ground if it continues to fly, it will be destroyed from the ground station LS to the rocket R as shown in FIG. A command is sent. As a result, the rocket R determines that a destruction command has been input (YES) in step ES in FIG. 2, and proceeds to steps S7 to S12 of the emergency escape means E, that is, emergency operation of the payload emergency escape system. To do.

  In step S7, the emergency escape means E stops the combustion of the first stage R1 if possible, and separates the first stage R1 and the second stage R2 by the first interstage separator B1. Next, in step S8, the rocket of the second stage R2 is ignited. As shown in FIGS. 1B and 3, in step S9, the mounting stage PS having the payload PL and the fairing F together with the second stage R2. Is removed from the first stage R1, and the mounting stage PS is quickly moved to a safe airspace. Thereafter, the destruction process (see FIG. 3) of the first stage R1 is performed.

  Next, the emergency escape means E separates the second stage R2 and the mounting stage PS by the second interstage separator B2 in step S11 after the operation of the second stage R2 rocket is completed in step S10. In step S12, the parachute (see FIG. 3) is released. Various mechanisms can be used for the release of the parachute PC. For example, a head part of the fairing F is provided with a storage part for the parachute PC including the auxiliary parachute and a lid for opening the storage part. A mechanism for releasing the auxiliary chute or the parachute PC from the accommodating portion with the lid opened and opening the umbrella can be employed.

  The separation of the second stage R2 and the mounting stage PS (S11) may be performed sufficiently away from the first stage R1 separated in step S7. If possible, the second stage R2 and the mounting stage PS may be separated before the step S10. It may be performed after the rocket combustion is stopped. Further, the second stage R2 after separation may be destroyed as shown in FIG. As a result, the payload PL slowly descends and soft-lands (or lands), and then is recovered.

  Thus, according to the payload emergency escape system of the rocket R of the above embodiment, when the first stage R1 is destroyed due to the occurrence of an abnormality after launch in the rocket R equipped with a payload PL such as an artificial satellite, the detachment is performed. The second stage R2 rocket, which is a rocket for use, allows the loaded payload PL to be removed from the first stage R1 and moved actively and quickly to a safe airspace. Protection and recovery of the payload PL It can be performed. In addition, as the separation rocket, an existing second stage R2 rocket having sufficient propulsive force for separation and movement can be used as one that imparts propulsive force in the axial direction.

  In addition, the above-described payload emergency escape system can reuse the collected payload PL, which can contribute to a reduction in production costs of the entire rocket. In addition to the original function of protecting the payload PL from aerodynamic heating, the fairing F protects the payload PL when the first stage R1 is destroyed, and protects the payload PL until it is recovered on the ground. It will be possible.

  Furthermore, the above-mentioned payload emergency escape system uses a second stage R2 rocket as a separation rocket that imparts propulsive force in the direction of the axis, and includes a mounting stage PS and a first stage R1 that is a lower stage thereof. The emergency escape means E provided with the 1st interstage separator B1 to couple | bond together and the ignition means of the rocket of 2nd stage R2 is employ | adopted. As a result, the payload emergency escape system can use the existing second stage R2 rocket and ignition means and the first interstage separator B1 for emergency use, thereby reducing the complexity and weight of the rocket structure. It is possible to suppress the manufacturing cost and realize further reduction of the manufacturing cost. Since the second stage R2 is originally an upper stage propulsion device including the mounting stage PS, it has sufficient propulsive force, and the mounting stage PS can be quickly moved from the first stage R1 where an abnormality has occurred. Can be separated.

  In the above embodiment, FIG. 2 illustrates the basic operation of the rocket R. Therefore, the determination step ES determines whether or not a rocket R destruction command is input, and the payload is based on the destruction command input. The emergency escape system shall be activated. However, since the basic operation of the payload emergency escape system does not directly include the destruction of the rocket, the determination step ES may be a determination as to whether or not an activation command is input to the emergency escape means E.

  4 and 5 are diagrams for explaining a second embodiment of the rocket payload emergency escape system according to the present invention, and FIGS. 6 and 7 show the first embodiment of the rocket payload emergency escape system according to the present invention. It is a figure explaining 3 embodiment. In the following embodiments, the same components as those in the first embodiment are denoted by the same reference numerals, and detailed description thereof is omitted.

  The rocket R shown in FIG. 4A includes a first stage R1 that is the lowest stage, a second stage R2 that is the upper stage, and a mounting stage PS that holds a payload PL such as an artificial satellite in the uppermost stage, And a fairing F that covers the payload PL on the mounting stage PS. In addition, the rocket R includes a plurality of booster rockets BR including a rocket motor loaded with a solid propellant in the first stage R1.

  The above-mentioned payload emergency escape system in the rocket R includes a detachment rocket that applies a propulsive force that detaches from the first stage R1 to the mounting stage PS having the payload PL and the fairing F in the axial direction, and the first stage R1. The emergency escape means (E) for separating the mounting stage PS and the first stage R1 based on reception of the destruction command and executing the separation of the mounting stage by the separation rocket, and the first stage R1 And a decelerating / lowering means (see FIG. 3) for decelerating and lowering the mounting stage PS.

  In the payload emergency escape system of this embodiment, a booster rocket BR provided in the first stage R1 is used as a separation rocket that imparts propulsive force in the axial direction. The emergency escape means (E) moves the booster release device 11 for releasing the restraint of the booster rocket BR from the first stage R1 and the released booster rocket BR from the first stage R1 to the mounting stage PS. And a second interstage separation device B2 that detachably couples the mounting stage PS and the second stage R2 that is the lower stage thereof.

  The booster releasing device 11 transmits the propulsive force of the booster rocket BR to the first stage R1 side and can release the restraint on the first stage R1 while maintaining the engagement with the booster guide 12. is there. The booster releasing device 11 also has a function of releasing the engagement with the booster guide 12 and completely separating it from the rocket body. The booster guides 12 are individually provided for the booster rocket BR, arranged linearly from the side surface of the first stage R1 to the side surface of the mounting stage PS, and can be separated at each interstage.

  The rocket R having the above-described configuration is launched by ignition of the first stage R1 and the booster rocket BR in step S21 in FIG. 5, and it is determined whether or not a destruction command is input in step ES. Since it is not input (NO), after the operation of the first stage R1 and the booster rocket BR is finished in step S22, the first stage R1 and the second stage R2 are separated by the first interstage separator B1 in step S23.

  Subsequently, the rocket R performs ignition of the second stage R2 in step S24, and after the operation of the second stage R2 is completed in step S25, the second stage R2 and the second stage R2 are connected as necessary. The mounting stage PS is separated, and the fairing F is opened by the third interstage separator B3 in step S26. The subsequent steps are the same as in the first embodiment.

  Next, when an abnormality occurs in the rocket R after launch and a destruction command is transmitted from the ground station (LS) to the rocket R, the destruction command is input in step ES in FIG. 5 (YES). The process proceeds to steps S27 to S32 of the emergency escape means E.

  When the emergency escape means E releases the restraint of the booster rocket BR with respect to the first stage R1 by the booster release device 11 in step S27, as shown in FIG. It moves along the booster guide 12 and is positioned on the side of the mounting stage PS.

  Thereafter, the emergency escape means E separates the second stage R2 and the mounting stage PS by the second interstage separator B2 in step S29, and, as shown in FIG. 4C, the booster rocket BR in step S30. With this propulsive force, the mounting stage PS having the payload PL and the fairing F is separated from the second stage R2, and the mounting stage PS is quickly moved to a safe air space.

  Then, the emergency escape means E separates the booster rocket BR from the mounting stage PS in step S31 and releases the parachute (see FIG. 3) in step S32. As a result, the payload PL is slowly lowered and soft landing (or landing) is collected. The separated booster rocket BR may be destroyed.

  As described above, according to the payload emergency escape system for the rocket R, as in the first embodiment, when the first stage R1 is destroyed due to the occurrence of an abnormality after launch, the booster rocket BR as a release rocket is used. Thus, it is possible to remove the mounted payload PL from the first stage R1 and move it positively and quickly to a safe air space, and the payload PL can be protected and recovered, and the payload PL can be recovered. It can also be used.

  The above-mentioned payload emergency escape system uses a booster rocket BR as a separation rocket that imparts propulsive force in the direction of the axis, and includes a booster release device 11, a booster guide 12, and a second interstage separator B2. The emergency escape means E provided with is adopted. As a result, the payload emergency escape system can use the existing booster rocket BR and the second interstage separator B2 for emergency use. Further reductions in costs can be realized. Further, since the booster rocket BR is originally a propulsion device used at the time of launch, the booster rocket BR has a sufficient propulsive force and can quickly separate the mounting stage PS from the first stage R1 where an abnormality has occurred.

  The rocket R shown in FIG. 6A includes a first stage R1 which is the lowest stage, a second stage R2 which is the upper stage, a mounting stage PS which holds a payload PL such as an artificial satellite in the uppermost stage, And a fairing F covering the payload PL on the stage PS.

  The fairing F of this embodiment includes a detaching rocket VR for detaching the fairing F from the mounting stage PS at the head. The rocket VR for leaving the fairing F is, for example, a rocket motor loaded with a solid propellant and includes ignition means including an igniter and is directed obliquely downward so that the fuel gas does not directly hit the fairing F. A plurality of nozzles are provided, thereby applying a propulsive force in the direction of the axis.

  In the configuration provided with the above-described separation rocket VR, the third interstage separation mechanism B3 can be simplified and the fairing F can be moved quickly. The third interstage separation mechanism B3 includes a means for detachably coupling the mounting stage PS and the fairing F when the fairing F is normally opened as in the first and second embodiments. And means for imparting separation force to the fairing F after separation. On the other hand, in the configuration provided with the separation rocket VR, the structure of the third interstage separation mechanism B3 can be simplified and reduced in weight because the means for applying the separation force becomes unnecessary. Further, the separation fairing F can be quickly separated from the mounting stage PS by the separation rocket VR. Moreover, the third interstage separation mechanism B3 plays a role of fixing and maintaining the fairing F that serves as a protector of the payload PL in the mounting stage PS in an emergency, and such a function is common in each embodiment. It is.

  The above-described payload emergency escape system for the rocket R is based on the receiving stage PS that receives at least the detaching rocket that gives the propulsion force to detach from the first stage R1 to the mounting stage PS and the destruction stage PS of the first stage R1. Emergency exit means (E) that separates the mounting stage PS from the first stage R1 and decelerates and lowers the mounting stage PS separated from the first stage R1. (See FIG. 3).

  In the payload emergency escape system of this embodiment, a separation rocket VR for separating the fairing F from the mounting stage PS is used as a separation rocket that imparts propulsive force in the axial direction. The emergency escape means (E) includes a second interstage separator B2 as an interstage separator that detachably connects the mounting stage PS and its lower stage part, and an ignition means for the separation rocket VR. It is included.

  The rocket R having the above configuration is launched by the ignition of the first stage R1 in step S41 in FIG. 7, and it is determined whether or not a destruction command is input in step ES. Therefore, after the operation of the first stage R1 is completed in step S42, the first stage R1 and the second stage R2 are separated by the first interstage separator B1 in step S43.

  Subsequently, the rocket R performs ignition of the second stage R2 in step S44, and after the operation of the second stage R2 is completed in step S45, the second stage R2 is mounted with the second stage R2 as necessary. The mounting stage PS is separated, and in step S46, the mounting stage PS and the fairing F are separated by the third interstage separator B3.

  Then, in step S47, the rocket R opens the fairing F by ignition of the separation rocket VR, as shown in FIG. 6B. In other words, in this embodiment, the fairing F is detached from the mounting stage PS and released in a decapitation manner by the separation rocket VR. The subsequent steps are the same as in the first embodiment.

  Next, when an abnormality occurs in the rocket R after launch and a destruction command is transmitted from the ground station (LS) to the rocket R, the destruction command is input in step ES in FIG. 7 (YES). The process proceeds to steps S48 to S53 of the emergency escape means E.

  In step S48, the emergency escape means E stops the combustion of the first stage R1 if possible, and separates the second stage R2 and the mounting stage PS by the second interstage separator B2. In step S49, the separation rocket VR is ignited. As shown in FIG. 6C, in step S50, the mounting stage PS including the payload PL and the fairing F is separated from the second stage R2. The stage for mounting PS is moved to a safe airspace. Thereafter, destruction processing (see FIG. 3) is performed on the first stage R1 and the second stage R2.

  Next, the emergency escape means E separates the release rocket VR in step S52 after the operation of the release rocket VR in step S51, and releases a parachute (see FIG. 3) as deceleration decelerating means in step S53. As a result, the payload PL is slowly lowered and soft landing (or landing) is collected.

  Thus, according to the payload emergency escape system for the rocket R, as in the first embodiment, the propulsive force is applied in the axial direction when the first stage R1 is destroyed due to the occurrence of an abnormality after launch. The separation rocket VR of the fairing F as the separation rocket enables the loaded payload PL to be detached from the first stage R1 and actively and quickly moved to a safe air space, thereby protecting the payload PL. In addition, the payload PL can be reused.

  In addition, the payload emergency escape system described above uses the separation rocket VR of the fairing F as a separation rocket that imparts propulsive force in the axial direction, and the loading stage PS and the second stage R2 that is the lower stage thereof. The emergency escape means E provided with the second interstage separator B2 that couples to and the ignition means of the detachment rocket VR is employed. As a result, the payload emergency escape system can use the existing separation rocket VR and ignition means and the second interstage separator B2 for emergency use, thereby suppressing the complexity and weight increase of the rocket structure. It is possible to achieve a further reduction in production costs.

  The rocket payload emergency escape system according to the present invention is not limited to the above-described embodiment, and the configuration can be changed as appropriate without departing from the gist of the present invention. In addition to the above embodiments, applicable rockets include a rocket that does not have a second stage, and a multi-stage rocket equipped with a plurality of stages that can be separated between the first stage and the mounting stage. Also good.

  Furthermore, in the above first to third embodiments, the configuration using the second stage R2 rocket, the booster rocket BR, and the fairing F separation rocket VR as the separation rocket is exemplified. It is also possible to provide a dedicated release rocket on the mounting stage PS. In this case, the dedicated detaching rocket may be used in both normal and emergency situations, and may be used only in emergency situations, as the stage for dismounting the mounting stage PS from its lower stage. .

B1 First interstage separator (emergency escape means)
B2 Second interstage separator (emergency escape means)
BR booster rocket (release rocket)
E Emergency escape means F Fairing PC Parachute (Deceleration and descent means)
PL payload PS stage for loading R rocket R1 first stage R2 second stage (release rocket)
VR release rocket 11 booster release device (emergency escape means)
12 Booster guide (emergency escape means)

Claims (4)

In a rocket including a first stage that is the lowest stage, a mounting stage that holds a payload in the uppermost stage, and a fairing that covers the payload on the mounting stage,
A detaching rocket that imparts a propulsive force that departs from the first stage to the mounting stage having a payload and a fairing;
Emergency escape means for separating the mounting stage and the first stage based on the reception of the first stage destruction command and executing the release of the mounting stage by the release rocket;
A rocket payload emergency escape system, comprising: a decelerating / lowering means for decelerating and lowering the mounting stage detached from the first stage.   The separation rocket is a second stage rocket provided between the first stage and the mounting stage, and the emergency escape means is connected between the first stage and the second stage in a separable manner. The rocket payload emergency escape system according to claim 1, comprising a separation device and ignition means for the detaching rocket. The release rocket is a booster rocket provided in the first stage,
The emergency escape means includes a booster release device for releasing the restraint of the booster rocket from the first stage, a booster guide for moving the released booster rocket from the first stage to the stage for mounting, the stage for mounting and the lower stage thereof The rocket payload emergency escape system according to claim 1, further comprising an interstage separation device that detachably couples the components to each other. The release rocket is a release rocket for releasing the fairing from the mounting stage,
2. The rocket payload emergency according to claim 1, wherein the emergency escape means includes an interstage separation device that detachably couples the mounting stage and a lower stage portion thereof, and ignition means for the separation rocket. Escape system.

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