CN115638695A - Separation mechanism, carrier rocket and separation method thereof - Google Patents
Separation mechanism, carrier rocket and separation method thereof Download PDFInfo
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- CN115638695A CN115638695A CN202211364363.4A CN202211364363A CN115638695A CN 115638695 A CN115638695 A CN 115638695A CN 202211364363 A CN202211364363 A CN 202211364363A CN 115638695 A CN115638695 A CN 115638695A
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- 238000000926 separation method Methods 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 claims abstract description 20
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 210000000707 wrist Anatomy 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 14
- 210000001503 joint Anatomy 0.000 abstract description 9
- 230000008602 contraction Effects 0.000 abstract description 7
- 239000002360 explosive Substances 0.000 description 10
- 230000000977 initiatory effect Effects 0.000 description 10
- 238000002474 experimental method Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 238000012795 verification Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005283 ground state Effects 0.000 description 1
- 238000011007 installation qualification Methods 0.000 description 1
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Abstract
The embodiment of the application provides a separation mechanism, a carrier rocket and a separation method thereof. The separation structure includes: the first actuating cylinder module comprises a first cylinder body and a second cylinder body, wherein the first cylinder body is provided with a first pin hole; the second actuating cylinder module comprises a second cylinder body and a piston pin, and the piston pin comprises a tail part and a head part which penetrates through the first pin hole and extends into the first cylinder body; the pipeline module comprises an air source, a first air inlet pipe and a second air inlet pipe, wherein the first air inlet pipe and the second air inlet pipe are connected with the air source and the second barrel, and the joint of the first air inlet pipe and the second barrel and the joint of the second air inlet pipe and the second barrel are respectively positioned on one side, close to and far away from the first barrel, of the tail portion of the piston pin. According to the embodiment of the application, the separation mechanism is arranged in the stage section, so that the number of butt joint surfaces is reduced, and the integral rigidity of the carrier rocket is improved; the first air inlet pipe and the second air inlet pipe are respectively communicated to control the extension and the contraction of the second actuating cylinder module, so that the first actuating cylinder module is locked and unlocked. The method is safe and environment-friendly, has low testing requirement, can be recycled and reused, and saves cost.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a separating mechanism, a carrier rocket and a separating method thereof.
Background
At present, a carrier rocket mostly adopts a multi-stage structure and is formed by connecting a plurality of cabin sections, and engines at all stages are connected through an interstage structure. During the flight, the sections of the capsule, which have completed the scheduled work of the launch vehicle and are useless in the subsequent flight, are separated by a separation system. The existing large-scale liquid carrier rocket adopts a twice separation method for separation in order to avoid the collision between the jet pipe and the stage section during large-depth separation because the jet pipe of the secondary engine is longer and the length of the whole stage section is longer, and a separation device adopts initiating explosive devices for separation.
The thermal separation of the initiating explosive device can reduce the out-of-control time and the possibility of collision generated by two stages, and ensure the rapid separation of the two stages. However, the existing twice-separation scheme has two abutting surfaces, and the abutting surfaces cause lower overall rigidity of the carrier rocket. The method for separating the initiating explosive devices impacts the rocket body, cannot test and verify the rocket body in a ground state, has strict requirements on installation qualification, operation flow and the like, and can reduce the integral assembly efficiency of the carrier rocket.
In conclusion, the carrier rocket in the related art has the technical problems of multiple butt joint surfaces, lower overall rigidity, higher requirements on installation test verification and lower assembly efficiency.
Disclosure of Invention
The separation mechanism, the carrier rocket and the separation method thereof are provided for overcoming the defects of the existing mode, and are used for solving at least one aspect of the technical problems that the carrier rocket in the related technology has more interfaces, lower overall rigidity, higher requirements for installation, test and verification, lower assembly efficiency and the like.
In a first aspect, an embodiment of the present application provides a separation mechanism, including:
the first actuating cylinder module comprises a hollow first cylinder body, and a first pin hole is formed in the side wall of the first cylinder body;
the second actuating cylinder module comprises a hollow second cylinder body and a piston pin movably connected with the second cylinder body, and the piston pin comprises a tail part positioned on the second cylinder body and a head part penetrating through the first pin hole and extending into the first cylinder body;
the pipeline module comprises an air source, a first air inlet pipe and a second air inlet pipe, wherein the first air inlet pipe and the second air inlet pipe are connected with the air source and the second barrel, the joint of the first air inlet pipe and the second barrel is located on one side, close to the first barrel, of the tail portion of the piston pin, and the joint of the second air inlet pipe and the second barrel is located on one side, far away from the first barrel, of the tail portion of the piston pin.
In some embodiments of the present application, the first ram further includes a connecting pin, a connecting pin push rod, the connecting pin push rod is at least partially located in the first cylinder and slidably connected to the first cylinder, the connecting pin is at least partially located in the first cylinder and fixedly connected to the connecting pin push rod, and a side of the connecting pin facing the second ram has a second pin hole, and the second pin hole is at least partially overlapped with the first pin hole.
In some embodiments of the application, the pipeline module further includes an outlet pipe, two ends of the outlet pipe are respectively communicated with the first cylinder and the second cylinder, a connection position of the outlet pipe and the second cylinder is located on one side, away from the first cylinder, of the tail portion of the piston pin, and a connection position of the outlet pipe and the first cylinder is located on one side, away from the connecting pin, of the connecting pin push rod.
In some embodiments of the application, the pipeline module includes the switching-over valve, and the one end and the air supply intercommunication of switching-over valve, the other end communicate with first intake pipe, second intake pipe respectively to switch on first intake pipe or second intake pipe.
In some embodiments of the present application, the separating mechanism further comprises a locking pin sleeved to the piston pin, the locking pin extending at least partially through the first pin hole into the interior of the first cylinder.
In a second aspect, embodiments of the present application provide a launch vehicle, including: the secondary section is connected with the secondary section, the secondary section comprises a separating mechanism in any one embodiment of the first aspect, a connecting pin in the separating mechanism is fixedly connected with the secondary section, and the separating mechanism is in signal connection with the controller.
In a third aspect, the present application provides a launch vehicle separation method for controlling the launch vehicle separation as in the second aspect, including the following steps:
when the carrier rocket is in the integral motion stage, the second air inlet pipe is driven to be communicated;
when the carrier rocket is in the separation stage, the first air inlet pipe is driven to be communicated.
In some embodiments of the present application, in driving the second intake pipe to conduct, includes:
driving a reversing valve to be in a first gear to block a first air inlet pipe;
in driving the first intake pipe to conduct, the method includes:
and driving the reversing valve to be in a second gear to block the second air inlet pipe.
In some embodiments of the present application, the drive directional valve is in a first gear comprising;
the reversing valve blocks the air outlet pipe;
the drive reversing valve is in a second gear position and comprises:
the reversing valve is led to the air outlet pipe.
In some embodiments of the present application, before driving the second intake pipe to conduct, the method includes: the locking pin is removed.
The beneficial technical effects brought by the technical scheme provided by the embodiment of the application comprise: according to the embodiment of the application, the separating mechanism is arranged in the secondary section, and the first actuator cylinder module in the separating mechanism is connected with the secondary section, so that the number of butt joint surfaces is reduced, and the integral rigidity of the carrier rocket is improved; the second actuator cylinder module is aligned to the pin hole of the first actuator cylinder module, and then the first air inlet pipe and the second air inlet pipe in the pipeline module are respectively communicated to control the extension and the contraction of the second actuator cylinder module, so that the locking state of the first actuator cylinder module is respectively realized at the integral motion stage of the carrier rocket, and the unlocking state of the first actuator cylinder module is realized at the separation stage of the carrier rocket. Compared with an initiating explosive device thermal separation method, interference collision among different sections of a carrier rocket during large-depth separation is avoided, the separation mechanism in the embodiment of the application is safe and environment-friendly by changing the locking state and the unlocking state, the test requirement is low, a test experiment can be carried out on the ground, the separation mechanism can be recycled, and the cost is saved.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of a separation mechanism according to an embodiment of the present disclosure.
In the figure, the position of the upper end of the main shaft,
1-connecting pin, 2-piston pin, 3-second cylinder, 4-air source, 5-first air inlet pipe, 6-air outlet pipe, 7-connecting pin push rod, 8-first cylinder, 9-second air inlet pipe, 10-reversing valve and 11-locking pin.
Detailed Description
Embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the embodiments set forth below in connection with the drawings are exemplary descriptions for explaining technical solutions of the embodiments of the present application, and do not limit the technical solutions of the embodiments of the present application.
As used herein, the singular forms "a", "an", "the" and "the" include plural referents unless the content clearly dictates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of other features, information, data, steps, operations, elements, components, and/or groups thereof, that may be implemented as required by the art. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or wirelessly coupled. The term "and/or" as used herein refers to at least one of the items defined by that term.
To make the objects, technical solutions and advantages of the present application more clear, embodiments of the present application will be described in further detail below with reference to the accompanying drawings.
The research finds that: the existing twice-separation scheme has two butt-joint surfaces, and specifically comprises the following steps: the carrier rocket has the advantages that the carrier rocket is low in overall rigidity due to the fact that the number of the butt joint surfaces between the stage section and the initiating explosive device and the butt joint surfaces between the stage section and the initiating explosive device are large. The method for separating the initiating explosive devices impacts the rocket body, cannot test and verify the rocket body on the ground, has strict requirements on installation quality, operation flow and the like, and can reduce the overall assembly efficiency of the carrier rocket.
Therefore, the carrier rocket in the related technology has the technical problems of multiple butt joint surfaces, lower overall rigidity, higher requirement on installation test verification and lower assembly efficiency.
In view of at least one of the above-mentioned problems in the related art or needs to be improved, the present application provides a detaching mechanism, a launch vehicle, and a detaching method thereof. According to the embodiment of the application, the separating mechanism is arranged in the secondary section, and the first actuator cylinder module in the separating mechanism is connected with the secondary section, so that the number of butt joint surfaces is reduced, and the integral rigidity of the carrier rocket is improved; the second actuator cylinder module is aligned to the pin hole of the first actuator cylinder module, and then the first air inlet pipe 5 and the second air inlet pipe 9 in the pipeline module are respectively communicated to control the extension and the contraction of the second actuator cylinder module, so that the locking state of the first actuator cylinder module is respectively realized at the integral motion stage of the carrier rocket, and the unlocking state of the first actuator cylinder module is realized at the separation stage of the carrier rocket. Compared with an initiating explosive device thermal separation method, interference collision among different sections of a carrier rocket during large-depth separation is avoided, the separation mechanism in the embodiment of the application is safe and environment-friendly by changing the locking state and the unlocking state, the test requirement is low, a test experiment can be carried out on the ground, the separation mechanism can be recycled, and the cost is saved.
The following describes the technical solution of the present application and how to solve the above technical problems in detail by specific embodiments. It should be noted that the following embodiments may be referred to, referred to or combined with each other, and the description of the same terms, similar features, similar implementation steps and the like in different embodiments is not repeated.
In a first aspect, the present application provides a separation mechanism, as shown in fig. 1, fig. 1 is a schematic structural diagram of a separation mechanism provided in the present application.
A separation mechanism comprising:
the first actuating cylinder module comprises a hollow first cylinder 8, and a first pin hole is formed in the side wall of the first cylinder 8;
the second actuating cylinder module comprises a hollow second cylinder body 3 and a piston pin 2 movably connected with the second cylinder body 3, and the piston pin 2 comprises a tail part positioned on the second cylinder body 3 and a head part penetrating through a first pin hole and extending into a first cylinder body 8;
the pipeline module comprises an air source 4, a first air inlet pipe 5 and a second air inlet pipe 9, wherein the first air inlet pipe 5 and the second air inlet pipe 9 are connected with the air source 4 and the second barrel 3, the joint of the first air inlet pipe 5 and the second barrel 3 is located on one side, close to the first barrel 8, of the tail portion of the piston pin 2, and the joint of the second air inlet pipe 9 and the second barrel 3 is located on one side, far away from the first barrel 8, of the tail portion of the piston pin 2.
In this embodiment, the axes of the first ram module and the second ram module are coplanar and staggered. One side of the first actuator cylinder module facing the second actuator cylinder module is at least provided with a first pin hole, and the axis of the second actuator cylinder module passes through the first pin hole.
By taking the carrier rocket to be in the example of the global motion phase, including hollow second barrel 3 and with second barrel 3 swing joint's piston pin 2 in the second pressurized strut module, the junction of first intake pipe 5 and second barrel 3, the junction of second intake pipe 9 and second barrel 3 is located the afterbody of piston pin 2 respectively and is close to, keep away from one side of first barrel 8, block first intake pipe 5, switch on second intake pipe 9, 4 air supplies of air supply, one side of first barrel 8 is kept away from with the afterbody of the leading-in piston pin 2 of air current to second intake pipe 9, be the right side space of second barrel 3 in the picture promptly, the atmospheric pressure increase in the right side space, thrust left is received to the afterbody of piston pin 2. When the piston pin 2 and the second cylinder 3 are displaced relatively, the piston pin 2 moves to the limit of the stroke close to one side of the first cylinder 8, and the second actuating cylinder module is in an extended state, namely the effective length of the second actuating cylinder module parallel to the axis reaches the maximum. At the moment, at least part of the head part of the piston pin 2 penetrates through the first pin hole and extends into the hollow first cylinder 8, the relative motion between the first actuating cylinder module and the second cylinder 3 is limited, the tail part of the piston pin 2 continuously receives leftward thrust along with the continuous air supply of the air source 4, the piston pin 2 is pressed by the thrust, the piston pin 2 is prevented from moving to one side far away from the first cylinder 8, and the head part of the piston pin 2 is prevented from falling off from the first pin hole. Therefore, the locking state of the first actuating cylinder module is completed, the secondary section and the secondary section are fixedly connected and do not move relatively, namely the secondary section and the secondary section are integrally kept in the same movement state.
The carrier rocket is turned into the separation stage after lasting a period of time overall motion stage, is in the separation stage when the carrier rocket, switches on first intake pipe 5, blocks second intake pipe 9, and air supply 4 air feed, first intake pipe 5 are close to one side of first barrel 8 with the afterbody of the leading-in piston pin 2 of air current, and the left side space of first barrel 8 in the picture promptly, the increase of air pressure in the left side space, the afterbody of piston pin 2 receives thrust right. When the piston pin 2 and the second cylinder 3 are displaced relatively, the piston pin 2 moves to the limit of the stroke far away from the first cylinder 8, and the second actuating cylinder module is in a contraction state, namely the effective length of the second actuating cylinder module parallel to the axis reaches the minimum. At this time, the portions of the piston pin 2 are completely separated from the first pin holes, and relative movement can occur between the first cylinder module and the second cylinder 3. Therefore, the unlocking state of the first actuating cylinder module is finished, the second stage and the second stage are not fixed, relative motion occurs between the second stage and the second stage, the second stage is far away from the second stage, the second stage continues to move towards a preset target, and the second stage gradually decelerates relative to the second stage and falls for recovery. The separating mechanism can be recycled, and cost is saved.
In some embodiments of the present application, the first ram module further includes a connecting pin 1, a connecting pin push rod 7, the connecting pin push rod 7 is at least partially located in the first cylinder 8 and slidably connected to the first cylinder 8, the connecting pin 1 is at least partially located in the first cylinder 8 and fixedly connected to the connecting pin 1 push rod 7, and a side of the connecting pin 1 facing the second ram module has a second pin hole, and the second pin hole is at least partially overlapped with the first pin hole.
In this embodiment, the first ram module includes a first cylinder 8, a connecting pin 1, and a connecting pin push rod 7, and both the connecting pin 1 and the connecting pin push rod 7 can move relative to the first cylinder 8, and the relative movement is parallel to the axis of the first cylinder 8. The connecting pin 1 and the connecting pin push rod 7 are fixedly connected and do not move relatively, namely the connecting pin push rod 7 can be pushed and pulled to push and pull the connecting pin 1, and when the connecting pin 1 is separated from the first cylinder 8, the first actuating cylinder module completes unlocking.
In one embodiment, the connecting pin 1 has a second pin hole formed in a side thereof facing the second ram module, the first pin hole and the second pin hole at least partially coincide, and the piston pin 2 of the second ram module extends into the first cylinder 8 through the first pin hole and the second pin hole in sequence. Since the locus of relative movement between the connecting pin 1 and the first barrel 8 is parallel to the axis of the first barrel 8, the axis of the piston pin 2 is staggered with respect to the axis of the first barrel 8. The piston pin 2 locks the connecting pin 1 with the first barrel 8, limiting the relative movement between the connecting pin 1 and the first barrel 8. Since the connecting pin 1 connects the secondary segment and the secondary segment, at this time, the secondary segment and the secondary segment move integrally.
In another embodiment, the connecting pin push rod 7 is provided with a second pin hole on a side facing the second cylinder module, the first pin hole and the second pin hole are at least partially overlapped, and the piston pin 2 in the second cylinder module sequentially passes through the first pin hole and the second pin hole and extends into the first cylinder 8. Since the locus of relative movement between the connecting pin push rod 7 and the first cylinder 8 is parallel to the axis of the first cylinder 8, the axis of the piston pin 2 and the axis of the first cylinder 8 are staggered. The piston pin 2 locks the connecting pin push rod 7 with the first cylinder 8 and limits the relative movement between the connecting pin push rod 7 and the first cylinder 8. Because the connecting pin push rod 7 is fixedly connected with the connecting pin 1, the connecting pin 1 is connected with the secondary section and the secondary section, and at the moment, the secondary section and the secondary section integrally move.
In some embodiments of the present application, the pipeline module further includes an outlet pipe 6, two ends of the outlet pipe 6 are respectively communicated with the first cylinder 8 and the second cylinder 3, a connection point of the outlet pipe 6 and the second cylinder 3 is located on one side of the tail portion of the piston pin 2 away from the first cylinder 8, and a connection point of the outlet pipe 6 and the first cylinder 8 is located on one side of the connecting pin push rod 7 away from the connecting pin 1.
In this embodiment, during the whole motion phase of the launch vehicle, a certain amount of gas is accumulated on the side of the second cylinder 3 away from the first cylinder 8, that is, the air pressure in the space on the right side of the second cylinder 3 is greater than the air pressure in the space on the left side in the figure, so that the piston pin 2 receives the thrust on the left side to complete locking.
When the carrier rocket is shifted to a separation stage from the integral motion stage, in order to realize that the piston pin 2 is subjected to right thrust, the air source 4 can supply air to one side of the second cylinder 3 close to the first cylinder 8, namely, the air is supplied to the left space of the second cylinder 3, and the air can be leaked from the right space of the second cylinder 3. An air outlet pipe 6 is arranged between the right space of the second cylinder 3 and one side of the first cylinder 8 facing the connecting pin push rod 7, the right space of the second cylinder 3 supplies air to one side of the first cylinder 8 facing the connecting pin push rod 7, the air pressure of the lower side space of the first cylinder 8 is larger than that of the upper side space in the drawing, and the connecting pin push rod 7 is pushed upwards. After the piston pin 2 is unlocked, the upward thrust generated by the airflow of the air outlet pipe 6 accelerates the relative movement speed between the connecting pin 1 and the connecting pin push rod 7 and the first cylinder 8, so that the separation speed of the connecting pin 1 and the connecting pin push rod 7 can be accelerated, the secondary section can continue to move along the axis of the first cylinder 8 during separation, and the direction does not deviate.
In some embodiments of the present application, the pipeline module includes a reversing valve 10, one end of the reversing valve 10 is communicated with the air source 4, and the other end of the reversing valve is communicated with the first air inlet pipe 5 and the second air inlet pipe 9 respectively, so as to conduct the first air inlet pipe 5 or the second air inlet pipe 9.
In this embodiment, the pipeline module includes a directional valve 10, the directional valve 10 is in signal connection with the controller, the directional valve 10 includes a plurality of gears, at least one gear can realize conducting the first intake pipe 5 and blocking the second intake pipe 9, and at least another gear can realize blocking the first intake pipe 5 and conducting the second intake pipe 9. The controller controls the reversing valve 10 to switch gears, and the locking state and the unlocking state of the second actuating cylinder module on the first actuating cylinder module are achieved.
In some embodiments of the present application, the separating mechanism further comprises a locking pin 11, the locking pin 11 is sleeved on the piston pin 2, and the locking pin 11 at least partially penetrates through the first pin hole and extends into the interior of the first cylinder 8.
In this embodiment, the locking pin 11 is sleeved on the piston pin 2, the locking pin 11 at least partially penetrates through the first pin hole and extends into the first cylinder 8, and the locking pin 11 locks the first ram module. The locking pin 11 and the piston pin 2 thus form a double safety, improving the reliability of the device.
On the basis of the above embodiments, in different embodiments, the locking pin 11 may also pass through the second pin hole of the connecting pin 1, and the locking pin 11 may also pass through the second pin hole of the connecting pin pushing rod 7.
In a second aspect, embodiments of the present application provide a launch vehicle, including: the secondary section is connected with the secondary section, the secondary section comprises a separating mechanism in any one embodiment of the first aspect, a connecting pin 1 in the separating mechanism is fixedly connected with the secondary section, and the separating mechanism is in signal connection with the controller.
In the embodiment, the separating mechanism is arranged in the stage section, the secondary section is directly connected with the connecting pin 1 in the stage section, and an initiating explosive device is not required to be arranged.
According to the embodiment of the application, the first actuator cylinder module in the separating mechanism is connected with the second-stage section, so that the number of butt joint surfaces is reduced, and the integral rigidity of the carrier rocket is improved; the second actuator cylinder module is aligned to the pin hole of the first actuator cylinder module, and then the first air inlet pipe 5 and the second air inlet pipe 9 in the pipeline module are respectively communicated to control the extension and the contraction of the second actuator cylinder module, so that the locking state of the first actuator cylinder module is respectively realized at the integral motion stage of the carrier rocket, and the unlocking state of the first actuator cylinder module is realized at the separation stage of the carrier rocket.
The separating mechanism in the embodiment of the application is safe and environment-friendly by changing the locking state and the unlocking state, has lower testing requirement, and can carry out testing experiments on the ground.
In a third aspect, the present application provides a launch vehicle separation method for controlling the launch vehicle separation as in the second aspect, including the following steps:
when the carrier rocket is in the integral motion stage, the second air inlet pipe 9 is driven to be communicated;
when the carrier rocket is in the separation stage, the first air inlet pipe 5 is driven to be communicated.
In the embodiment, when the carrier rocket is in the whole motion phase, the second air inlet pipe 9 is communicated, and the first air inlet pipe 5 is at least partially shielded, so that no air flow exists in the first air inlet pipe 5 or the air inlet speed of the first air inlet pipe 5 is smaller than the air inlet speed of the second air inlet pipe 9.
The air pressure in the right space of the second cylinder 3 is larger than that in the left space, and the tail part of the piston pin 2 is pushed leftwards. When the piston pin 2 and the second cylinder 3 are displaced relatively, the piston pin 2 moves to the limit of the stroke close to one side of the first cylinder 8, and the second actuating cylinder module is in an extended state, namely the effective length of the second actuating cylinder module parallel to the axis reaches the maximum. At the moment, at least part of the head part of the piston pin 2 penetrates through the first pin hole and extends into the hollow first cylinder 8, the relative motion between the first actuating cylinder module and the second cylinder 3 is limited, the tail part of the piston pin 2 continuously receives leftward thrust along with the continuous air supply of the air source 4, the piston pin 2 is pressed by the thrust, the piston pin 2 is prevented from moving to one side far away from the first cylinder 8, and the head part of the piston pin 2 is prevented from falling off from the first pin hole. Therefore, the locking state of the first actuating cylinder module is completed, the secondary section and the secondary section are fixedly connected and do not move relatively, namely the secondary section and the secondary section are integrally kept in the same moving state.
And after the carrier rocket is in the separation stage, the first air inlet pipe 5 is communicated, and at least part of the second air inlet pipe 9 is shielded, so that no air flow exists in the second air inlet pipe 9 or the air inlet speed of the second air inlet pipe 9 is smaller than that of the first air inlet pipe 5.
The air supply 4 supplies air, the first air inlet pipe 5 leads the tail of the air flow introduced to the piston pin 2 to be close to one side of the first cylinder 8, namely, the left space of the first cylinder 8 in the drawing, the air pressure in the left space is increased, and the tail of the piston pin 2 is pushed rightwards. When the piston pin 2 and the second cylinder 3 are displaced relatively, the piston pin 2 moves to the limit of the stroke far away from the first cylinder 8, and the second actuating cylinder module is in a contraction state, namely the effective length of the second actuating cylinder module parallel to the axis reaches the minimum. At this time, the portions of the piston pin 2 are completely separated from the first pin holes, and relative movement can occur between the first cylinder module and the second cylinder 3. Therefore, the unlocking state of the first actuating cylinder module is finished, the second stage and the second stage are not fixed, relative motion occurs between the second stage and the second stage, the second stage is far away from the second stage, the second stage continues to move towards a preset target, and the second stage gradually decelerates relative to the second stage and falls for recovery. The separating mechanism can be recycled, and cost is saved.
In some embodiments of the present application, in driving the second intake pipe 9 to conduct, the following are included:
driving the reversing valve 10 to be in a first gear to block the first air inlet pipe 5;
in driving the first intake pipe 5 to conduct, the following are included:
the drive switch valve 10 is in the second gear position to block the second intake pipe 9.
In the present embodiment, the directional valve 10 is in signal connection with the controller, and the directional valve 10 includes a plurality of gears. In order to change the relationship of air pressure in the spaces at the two sides of the tail part of the piston pin 2 more quickly, at least one gear can realize the conduction of the first air inlet pipe 5 and the blockage of the second air inlet pipe 9, and at least another gear can realize the blockage of the first air inlet pipe 5 and the conduction of the second air inlet pipe 9. The controller controls the reversing valve 10 to switch gears, and the locking state and the unlocking state of the second actuating cylinder module on the first actuating cylinder module are achieved.
In some embodiments of the present application, the drive directional valve 10 is in a first gear, including;
the reversing valve 10 blocks the air outlet pipe 6;
the drive switch valve 10 is in the second gear position, and includes:
the reversing valve 10 conducts the air outlet pipe 6.
In the present embodiment, in order to further accelerate the change of the relationship of the air pressure level in the spaces on both sides of the tail portion of the piston pin 2. In the stage of the overall motion of the carrier rocket, when the gas is supplied to one side of the second cylinder 3, which is far away from the first cylinder 8, the gas outlet pipe 6 is blocked, and the gas leakage and pressure relief of the space on the right side of the second cylinder 3 are prevented. In the figure, the air pressure in the right space of the second cylinder 3 is larger than that in the left space, so that the piston pin 2 receives the leftward thrust to complete locking.
When the carrier rocket is shifted to a separation stage from the integral motion stage, in order to realize that the piston pin 2 is subjected to right thrust, the air source 4 can supply air to one side of the second cylinder 3 close to the first cylinder 8, namely, the air is supplied to the left space of the second cylinder 3, and the air can be leaked from the right space of the second cylinder 3. Set up outlet duct 6 between one side towards connecting pin push rod 7 in the right side space of second barrel 3 and first barrel 8, switch on outlet duct 6, the right side space of second barrel 3 is to first barrel 8 air feed towards one side of connecting pin push rod 7, and the downside space atmospheric pressure of first barrel 8 is greater than the upside space in the figure, and connecting pin push rod 7 receives ascending thrust. After the piston pin 2 is unlocked, the speed of relative movement between the connecting pin 1 and the connecting pin push rod 7 and the first cylinder 8 is increased, so that the disengaging speed of the connecting pin 1 and the connecting pin push rod 7 can be increased, the secondary section can be ensured to continue to move along the axis of the first cylinder 8 during separation, and the direction does not deviate.
In some embodiments of the present application, before driving the second intake pipe 9 to conduct, the following are included: the locking pin 11 is removed.
In this embodiment, the locking pin 11 is sleeved on the piston pin 2, the locking pin 11 at least partially penetrates through the first pin hole and extends into the first cylinder 8, and the locking pin 11 locks the first ram module. The locking pin 11 and the piston pin 2 thus form a double safety, improving the reliability of the device.
On the basis of the above embodiments, in different embodiments, the locking pin 11 may also pass through the second pin hole of the connecting pin 1, and the locking pin 11 may also pass through the second pin hole of the connecting pin pushing rod 7.
The locking pins 11 are removed prior to launch of the launch vehicle.
Compared with the prior art, the method and the device have the advantages that the following beneficial effects can be at least realized by applying the embodiment of the application: according to the embodiment of the application, the separating mechanism is arranged in the secondary section, and the first actuator cylinder module in the separating mechanism is connected with the secondary section, so that the number of butt joint surfaces is reduced, and the integral rigidity of the carrier rocket is improved; the second actuator cylinder module is aligned to the pin hole of the first actuator cylinder module, and then a first air inlet pipe 5 and a second air inlet pipe 9 in the pipeline module are respectively communicated to control the extension and contraction of the second actuator cylinder module, so that the locking state of the first actuator cylinder module is respectively realized in the integral motion stage of the carrier rocket and the unlocking state of the first actuator cylinder module is realized in the separation stage of the carrier rocket. Compared with an initiating explosive device thermal separation method, interference collision among different sections of a carrier rocket during large-depth separation is avoided, the separation mechanism in the embodiment of the application is safe and environment-friendly by changing the locking state and the unlocking state, the test requirement is low, a test experiment can be carried out on the ground, the separation mechanism can be recycled, and the cost is saved.
Those of skill in the art will appreciate that the various operations, methods, steps in the processes, acts, or solutions discussed in this application can be interchanged, modified, combined, or eliminated. Further, various operations, methods, steps, measures, schemes in the various processes, methods, procedures that have been discussed in this application may be alternated, modified, rearranged, decomposed, combined, or eliminated. Further, steps, measures, schemes in the prior art having various operations, methods, procedures disclosed in the present application may also be alternated, modified, rearranged, decomposed, combined, or deleted.
In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like are for convenience of description or simplicity of describing the embodiments of the present application based on the exemplary directions or positional relationships shown in the drawings, and do not indicate or imply that the devices or components referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, are not to be construed as limiting the present application.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description herein, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
It should be understood that, although the steps in the flowcharts of the figures are shown in sequence as indicated by the arrows, the order in which the steps are performed is not limited to the sequence indicated by the arrows. In some implementations of the embodiments of the present application, the steps in the various flows may be performed in other sequences as desired, unless explicitly stated otherwise herein. Moreover, some or all of the steps in each flowchart may include multiple sub-steps or multiple stages, depending on the actual implementation scenario. Some or all of the sub-steps or phases may be executed at the same time, or may be executed at different times in a scenario where the execution time is different, and the execution order of the sub-steps or phases may be flexibly configured according to the requirement, which is not limited in this embodiment of the application.
The foregoing is only a part of the embodiments of the present application, and it should be noted that it is within the scope of the embodiments of the present application that other similar implementation means based on the technical idea of the present application can be adopted by those skilled in the art without departing from the technical idea of the present application.
Claims (10)
1. A release mechanism, comprising:
the first actuating cylinder module comprises a hollow first cylinder body, and a first pin hole is formed in the side wall of the first cylinder body;
the second actuating cylinder module comprises a hollow second cylinder body and a piston pin movably connected with the second cylinder body, and the piston pin comprises a tail part positioned on the second cylinder body and a head part penetrating through the first pin hole and extending into the first cylinder body;
the pipeline module comprises an air source, a first air inlet pipe and a second air inlet pipe, wherein the first air inlet pipe and the second air inlet pipe are connected with the air source and the second barrel, the joint of the first air inlet pipe and the second barrel is located on one side, close to the first barrel, of the tail portion of the piston pin, and the joint of the second air inlet pipe and the second barrel is located on one side, far away from the first barrel, of the tail portion of the piston pin.
2. A release mechanism according to claim 1, wherein the first ram further comprises a connecting pin, a connecting pin push rod at least partially disposed within the first cylinder and slidably coupled thereto, and a connecting pin at least partially disposed within the first cylinder and fixedly coupled thereto, wherein a side of the connecting pin facing the second ram has a second pin aperture at least partially coincident with the first pin aperture.
3. The separating mechanism according to claim 2, wherein the pipeline module further comprises an outlet pipe, two ends of the outlet pipe are respectively communicated with the first cylinder and the second cylinder, a connection position of the outlet pipe and the second cylinder is located on a side, away from the first cylinder, of the tail portion of the piston pin, and a connection position of the outlet pipe and the first cylinder is located on a side, away from the connecting pin, of the connecting pin pushing rod.
4. The separating mechanism according to claim 1, wherein the pipeline module comprises a reversing valve, one end of the reversing valve is communicated with the air source, and the other end of the reversing valve is communicated with the first air inlet pipe and the second air inlet pipe respectively so as to conduct the first air inlet pipe or the second air inlet pipe.
5. A release mechanism according to claim 1, further comprising a locking pin sleeved on the wrist pin, the locking pin extending at least partially through the first pin bore into the interior of the first barrel.
6. A launch vehicle comprising a controller, a secondary section and a staging section, said secondary section being connected to said staging section,
the secondary section includes a disconnect mechanism as defined in any one of claims 1-5, a connector pin in the disconnect mechanism being fixedly connected to the secondary section, the disconnect mechanism being in signal communication with the controller.
7. A launch vehicle separation method for controlling the launch vehicle separation as recited in claim 6, comprising the steps of:
when the carrier rocket is in the integral motion stage, driving a second air inlet pipe to be communicated;
and when the carrier rocket is in a separation stage, driving the first air inlet pipe to be communicated.
8. A method of separating as claimed in claim 7, wherein in said driving second inlet conduit conducting, comprising:
driving a reversing valve to be in a first gear to block the first air inlet pipe;
in the drive first intake pipe conduction, the method includes:
and driving the reversing valve to be in a second gear to block the second air inlet pipe.
9. A method of separating according to claim 8, wherein the drive reversing valve is in a first gear comprising;
the reversing valve blocks the air outlet pipe;
the driving the directional valve in a second gear comprising:
the reversing valve is communicated with the air outlet pipe.
10. A method of separating as claimed in claim 7, comprising, prior to opening of the drive second inlet conduit: the locking pin is removed.
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| CN202211364363.4A CN115638695B (en) | 2022-11-02 | 2022-11-02 | Separation mechanism, carrier rocket and separation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211364363.4A CN115638695B (en) | 2022-11-02 | 2022-11-02 | Separation mechanism, carrier rocket and separation method thereof |
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| CN115638695B (en) | 2024-01-09 |
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