CN113879569A - Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system - Google Patents
Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system Download PDFInfo
- Publication number
- CN113879569A CN113879569A CN202111176589.7A CN202111176589A CN113879569A CN 113879569 A CN113879569 A CN 113879569A CN 202111176589 A CN202111176589 A CN 202111176589A CN 113879569 A CN113879569 A CN 113879569A
- Authority
- CN
- China
- Prior art keywords
- connecting rod
- satellite
- locking
- separation
- rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 126
- 230000009471 action Effects 0.000 claims abstract description 20
- 238000007906 compression Methods 0.000 claims description 36
- 230000006835 compression Effects 0.000 claims description 35
- 230000000694 effects Effects 0.000 claims description 2
- 239000013585 weight reducing agent Substances 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 10
- 108091092878 Microsatellite Proteins 0.000 description 7
- 238000000034 method Methods 0.000 description 5
- 238000004891 communication Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The application discloses satellite and rocket separator and satellite and rocket separation system, through setting up connecting rod, locking lever and ejection subassembly, the surface of locking lever is provided with the locking separation hole, during the installation, is fixed in the satellite with the first end of connecting rod on, the adapter is passed to the second end of connecting rod, and the locking lever passes through the locking separation hole cover is located the second end of connecting rod and is held and offset with the adapter. When the separation action is carried out, the locking rod moves for a certain distance, and the locking separation hole is driven to move, the unlocking of the connecting rod and the locking rod is realized, the second end of the connecting rod penetrates through the locking separation hole under the driving of the ejection assembly, the separation of the connecting rod from the locking rod is realized, finally, the separation of a satellite and an arrow is realized, the arrangement of the device is realized, the unlocking and the separation action of the satellite are both acted on the same position, the assembly space of a satellite installation surface is effectively saved, the moving direction of the locking rod is perpendicular to the moving direction of the connecting rod or not on the same straight line, and the influence on the connecting rod when the locking rod moves can be effectively avoided.
Description
Technical Field
The application belongs to the technical field of satellite and arrow separation equipment, and particularly relates to a low-impact unlocking satellite and arrow separation device and a satellite and arrow separation system.
Background
With the development of launch vehicle technology, the need to establish low cost space entry capability is becoming stronger. The one-rocket multi-satellite system is a direct and effective method, and multiple satellites are placed in a limited rocket payload envelope space as much as possible, so that a rocket can send the multiple satellites into space, the carrying capacity can be obviously improved, and the launching cost can be reduced.
Generally, a satellite is connected with a rocket body through an adapter device, the adapter device has an unlocking ejection function, when the rocket reaches a specified orbital height, the satellite is in a weightless state, the satellite is unlocked with the adapter connecting device, the adapter ejection device ejects the satellite, and separation of the satellite and the rocket is realized.
At present, a miniaturized spacecraft represented by a microsatellite has become an important development trend in the aerospace field. The microsatellite has higher requirements on separation impact, the existing satellite and rocket are generally connected and separated through the explosion bolt, but the explosion bolt connection mode is difficult to adapt to the requirement on the microsatellite separation impact due to overlarge separation impulse, the unlocking and separating process of the existing satellite and rocket separating device occupies larger space, the assembly space of the satellite is increased to a certain extent, and the effective load capacity of the satellite is reduced.
Disclosure of Invention
The technical problem that the effective load of a satellite is reduced due to the fact that space occupied by the unlocking and separating processes of the existing satellite and rocket separating device is large at least can be solved to a certain extent. Therefore, the application provides a low-impact unlocking satellite-rocket separation device and a satellite-rocket separation system.
The low impact unblock star-arrow separator that this application embodiment provided includes:
a link having opposite first and second ends, the first end of the link being secured to the satellite and the second end of the link passing through the adapter;
the surface of the lock rod is provided with a locking separation hole, and the lock rod is sleeved at the second end of the connecting rod through the locking separation hole and is clamped with the connecting rod;
the ejection assembly is connected with the connecting rod, the locking rod moves for a certain distance and is separated from the clamping connection with the connecting rod, and the connecting rod penetrates through the locking separation hole towards the satellite under the action of the ejection assembly.
In some embodiments, the ejection assembly comprises:
the fixing sleeve is fixed on the adapter, and the connecting rod penetrates through the fixing sleeve and is in sliding connection with the fixing sleeve;
the surface of the connecting rod is provided with a butting protrusion, the compression spring is positioned in the fixed sleeve and sleeved on the surface of the connecting rod, the upper end of the compression spring is abutted against the butting protrusion, and the lower end of the compression spring is abutted against the adapter.
In some embodiments, the ejection assembly further comprises a retaining nut threadably coupled to the second end of the link, and the locking rod is positioned between the retaining nut and the compression spring.
In some embodiments, a surface of the connecting rod is provided with a shoulder, and the locking rod is located between the shoulder and the fixing nut.
In some embodiments, the abutting protrusion extends to an end surface of the link in a direction away from the compression spring, and one end of the abutting protrusion away from the compression spring is provided with a first radial extending protrusion, and the first radial extending protrusion is fixed on the satellite.
In some embodiments, the end face of the connecting rod is opened with a weight-reducing groove extending toward the inside of the connecting rod.
In some embodiments, the locking disengagement aperture comprises:
the lock rod is sleeved on the surface of the connecting rod through the lock hole, and the second end of the connecting rod is abutted against the surface of the lock rod;
the separation hole, the separation hole with the lockhole intercommunication, the lockhole with be provided with the confession between the separation hole the intercommunication mouth that the connecting rod passed, the pulling the locking lever makes the connecting rod passes the intercommunication mouth and enters into when the separation hole, the connecting rod is in pop out towards the direction of satellite under the effect of ejection subassembly the separation hole.
In some embodiments, the inner wall of the lock hole is in a circular arc structure, and the connecting rod is attached to the inner wall of the lock hole, which is far away from the separation hole.
In some embodiments, the driver is a pin driver fixed to an end of the lock rod by a pin shaft and configured to drive the lock rod to move in a direction perpendicular to the connecting rod.
The embodiment of the application has at least the following beneficial effects: this satellite and rocket separator is through setting up connecting rod, locking lever and ejection subassembly, and the surface of locking lever is provided with the locking separation hole, during the installation, is fixed in the satellite with the first end of connecting rod, and the adapter is passed to the second end of connecting rod, and the locking lever is located the second end of connecting rod and is held against with the adapter through locking separation hole cover. When the separation action is carried out, the lock rod moves for a certain distance and drives the locking separation hole to move, so that the end part of the connecting rod can pass through the locking separation hole to realize the unlocking of the connecting rod and the lock rod, at the moment, the second end of the connecting rod passes through the locking separation hole under the driving of the ejection assembly to realize the separation of the connecting rod and the lock rod, and finally, the connecting rod and the satellite move towards the direction far away from the adapter under the action of the ejection assembly to realize the separation of the satellite and the arrow, by the arrangement of the device, the unlocking and separating actions of the satellite act on the same position, the assembly space of the satellite mounting surface is effectively saved, the effective load capacity of the satellite is increased, and the moving direction of the lock rod is vertical to the moving direction of the connecting rod or not on the same straight line, the influence on the connecting rod when the locking rod moves can be effectively avoided, so that the driving force of the ejection assembly can meet the emission requirement of the microsatellite.
The satellite and arrow separating system that this application embodiment provided includes satellite and arrow separator, still include:
a satellite secured to a first end of the link;
the adapter, the adapter is located all sides of satellite, the second end of connecting rod passes the adapter, the jettison device is fixed in on the adapter, locking lever and adapter sliding connection.
The embodiment of the application has at least the following beneficial effects: the satellite and rocket separation device is provided with the connecting rod, the locking rod and the ejection assembly, the locking separation hole is formed in the surface of the locking rod, during installation, the first end of the connecting rod is fixed on a satellite, the second end of the connecting rod penetrates through the adapter, and the locking rod is sleeved at the second end of the connecting rod through the locking separation hole and abuts against the adapter. When the separation action is carried out, the lock rod moves for a certain distance and drives the locking separation hole to move, so that the end part of the connecting rod can pass through the locking separation hole to realize the unlocking of the connecting rod and the lock rod, at the moment, the second end of the connecting rod passes through the locking separation hole under the driving of the ejection assembly to realize the separation of the connecting rod and the lock rod, and finally, the connecting rod and the satellite move towards the direction far away from the adapter under the action of the ejection assembly to realize the separation of the satellite and the arrow, by the arrangement of the device, the unlocking and separating actions of the satellite act on the same position, the assembly space of the satellite mounting surface is effectively saved, the effective load capacity of the satellite is increased, and the moving direction of the lock rod is vertical to the moving direction of the connecting rod or not on the same straight line, the influence on the connecting rod when the locking rod moves can be effectively avoided, so that the driving force of the ejection assembly can meet the emission requirement of the microsatellite.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 shows a schematic structural diagram of a satellite-rocket separation system according to an embodiment of the application;
fig. 2 shows a partial enlarged view at a in fig. 1;
FIG. 3 shows a cross-sectional view along A-A of FIG. 1;
fig. 4 shows a partial enlarged view at a in fig. 3.
Reference numerals:
10-connecting rod 11-abutting projection 12-shaft shoulder
13-first radially extending projection 14-lightening slot 15-bolt
20-locking rod 21-locking separation hole 30-ejection assembly
31-fixed sleeve 32-compression spring 33-fixed nut
34-spacer 40-driver 41-pin puller
42-pin shaft 50-satellite-rocket separation device 60-satellite
70-adapter 211-lock hole 212-separation hole
213-communication port 311-second radially extending projection.
Detailed Description
The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Moreover, the present application may repeat reference numerals and/or letters in the various examples, such repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. In addition, examples of various specific processes and materials are provided herein, but one of ordinary skill in the art may recognize applications of other processes and/or use of other materials.
The application is described below with reference to specific embodiments in conjunction with the following drawings: the low-impact unlocking satellite-rocket separation device provided by the embodiment of the application is shown in fig. 3-4 and comprises:
a link 10, the link 10 having opposite first and second ends, the first end of the link 10 being fixed to the satellite 60, the second end of the link 10 passing through the adapter 70;
the surface of the lock rod 20 is provided with a locking separation hole 21, and the lock rod 20 is sleeved at the second end of the connecting rod 10 through the locking separation hole 21 and is clamped with the connecting rod 10;
the ejection assembly 30 is connected with the connecting rod 10, after the locking rod 20 moves for a certain distance and is disengaged from the connecting rod 10, the connecting rod 10 passes through the locking separation hole 21 towards the satellite 60 under the action of the ejection assembly. First end of the link 10 links the second end of the link 10.
Specifically, the satellite and rocket separation device is provided with a connecting rod 10, a locking rod 20 and an ejection assembly 30, wherein a locking separation hole 21 is formed in the surface of the locking rod 20, when the satellite and rocket separation device is installed, a first end of the connecting rod 10 is fixed on a satellite 60, a second end of the connecting rod 10 penetrates through an adapter 70, and the locking rod 20 is sleeved on a second end of the connecting rod 10 through the locking separation hole 21 and abuts against the adapter 70. When the separation action is carried out, the locking rod 20 moves for a certain distance under the driving of the pin shifter 41 and drives the locking separation hole 21 to move, so that the end part of the connecting rod 10 can pass through the locking separation hole 21 to realize the unlocking of the connecting rod 10 and the locking rod 20, at the moment, the second end of the connecting rod 10 passes through the locking separation hole 21 under the driving of the ejection assembly 30 to realize the separation of the connecting rod 10 and the locking rod 20, finally, the connecting rod 10 and the satellite 60 move towards the direction far away from the adapter 70 under the action of the ejection assembly 30 to realize the separation of the star and the arrow, through the arrangement of the device, the unlocking and separation actions of the satellite 60 are acted on the same position, the assembly space of the installation surface of the satellite 60 is effectively saved, the effective load capacity of the satellite 60 is increased, the moving direction of the locking rod 20 is vertical to the moving direction of the connecting rod 10 or not on the same straight line, and the influence on the connecting rod 10 when the locking rod 20 moves can be effectively avoided, so that the driving force of the ejection assembly 30 can meet the launching requirements of the microsatellite 60.
In this example, the locking bar 20 is further disposed against a side of the adapter 70 remote from the satellite 60.
In some embodiments, as shown in fig. 3-4, the ejection assembly 30 includes:
the fixed sleeve 31, the fixed sleeve 31 is fixed on the adapter 70, the connecting rod 10 passes through the fixed sleeve 31 and is connected with the fixed sleeve 31 in a sliding way;
the compression spring 32, the surface of the connecting rod 10 is provided with an abutting protrusion 11, the compression spring 32 is located inside the fixed sleeve 31 and sleeved on the surface of the connecting rod 10, the upper end of the compression spring 32 abuts against the abutting protrusion 11, and the lower end of the compression spring 32 abuts against the adapter 70.
Specifically, the fixing sleeve 31 facilitates connection and fixation between the ejection assembly 30 and the adapter 70, and can limit the connecting rod 10 and protect and guide the compression spring 32, when the connecting rod 10 is installed, the fixing sleeve 31 is fixed on the adapter 70, the compression spring 32 is sleeved on the surface of the connecting rod 10, the upper end of the compression spring 32 abuts against the abutting protrusion 11, the second end of the connecting rod 10 penetrates through the fixing sleeve 31, and the lower end of the compression spring 32 abuts against the surface of the adapter 70 and compresses the compression spring 32. After the lock rod 20 moves for a certain distance, the connecting rod 10 passes through the locking separation hole 21 under the elastic force of the compression spring 32, so that the connecting rod 10 is separated from the lock rod 20, and finally, the separation of the star and the arrow is realized.
In this embodiment, further, the end of the fixing sleeve 31 away from the satellite 60 is provided with an opening to facilitate the installation of the compression spring 32 and the retaining sleeve 34.
In some embodiments, as shown in fig. 3-4, the ejection assembly 30 further includes a retaining nut 33, the retaining nut 33 threadably coupled to the second end of the linkage 10, and the locking rod 20 positioned between the retaining nut 33 and the compression spring 32.
Specifically, after the connecting rod 10 passes through the locking separation hole 21, the locking rod 20 is moved to drive the side wall of the locking separation hole 21 to be attached to the connecting rod 10, the fixing nut 33 is screwed into the second end of the connecting rod 10, the fixing nut 33 abuts against the lower surface of the locking rod 20 under the elastic force of the compression spring 32, the upper surface of the locking rod 20 abuts against the adapter 70, locking of the connecting rod 10 and the locking rod 20 is achieved, meanwhile, lifting of the connecting rod 10 can be achieved by adjusting the fixing nut 33, adjustment of the compression amount of the compression spring 32 can be achieved by lifting of the connecting rod 10, and finally, adjustment of impulse during separation of stars and arrows is achieved.
In some embodiments, as shown in fig. 3-4, the second end of the connecting rod 10 is provided with a shoulder 12, and the locking rod 20 is located between the shoulder 12 and the retaining nut 33. Specifically, after the upper surface of the locking rod 20 abuts against the adapter 70, the fixing nut 33 is continuously adjusted, the connecting rod 10 continues to descend until the shoulder 12 abuts against the upper surface of the locking rod 20, and the clamping force of the shoulder 12 and the fixing nut 33 on the locking rod 20 can be adjusted by rotating the fixing nut 33, so that the locking rod 20 can slide; through the arrangement of the shaft shoulder 12, the descending of the connecting rod 10 can be limited, and the phenomenon that the spring is excessively compressed, so that the elastic force of the spring is too large to influence the separation between the star and the arrow is avoided.
In some embodiments, as shown in fig. 3 to 4, the abutting protrusion 11 extends to the end surface of the connecting rod 10 in a direction away from the compression spring 32, and one end of the abutting protrusion 11 away from the compression spring 32 is provided with a first radial extending protrusion 13, and the first radial extending protrusion 13 is fixed on the satellite 60.
Specifically, first radial extension arch 13 is fixed with satellite 60 realization through bolt 15, the butt arch 11 extends to the terminal surface of connecting rod 10 and can avoid the setting that should first radial extension arch 13 to cause inconvenience for the production of connecting rod 10, and can avoid first radial extension arch 13 to take place deformation under the long-term compression of compression spring 32, and simultaneously, make things convenient for connecting rod 10 to insert the inside of locating fixed sleeve 31 and make things convenient for fixed sleeve 31 spacing, and can increase the interval between each fixing bolt 15, make things convenient for the installation of connecting rod 10.
In some embodiments, as shown in fig. 3-4, the surface of the fixed sleeve 31 is provided with a second radially extending protrusion 311, the second radially extending protrusion 311 being fixed to the adapter 70. In particular, the second radially extending projection 311 facilitates fixation between the fixing sleeve 31 and the adapter 70.
In some embodiments, as shown in fig. 3-4, the ejection assembly 30 further includes a retaining sleeve 34, the retaining sleeve 34 is disposed on the surface of the connecting rod 10 and located between the compression spring 32 and the abutment protrusion 11, and the upper end of the compression spring 32 abuts against the retaining sleeve 34. Specifically, the provision of the spacer 34 makes it possible to achieve abutment of the compression spring 32 and the abutment projection 11 while reducing the outer diameter of the abutment projection 11 as much as possible, and at the same time, avoids abrasion of the connecting rod 10.
In some embodiments, as shown in fig. 3-4, the end face of the connecting rod 10 is open with weight-reducing slots extending toward the interior of the connecting rod 10. 14. Specifically, the lightening slots 14 reduce the weight of the connecting rod 10, facilitating the catapult separation of the satellites 60 while minimizing the dead weight of the satellites 60.
In some embodiments, as shown in fig. 1-4, the locking disengagement aperture 21 comprises:
the lock hole 211, the lock rod 20 is sleeved on the surface of the connecting rod 10 through the lock hole 211, and the second end of the connecting rod 10 is abutted against the surface of the lock rod 20;
the separation hole 212 is communicated with the lock hole 211, a communication opening 213 for the connection rod 10 to pass through is arranged between the lock hole 211 and the separation hole 212, and when the lock rod 20 is pulled, so that the connection rod 10 passes through the communication opening 213 and enters the separation hole 212, the connection rod 10 is ejected out of the separation hole 212 towards the satellite 60 under the action of the ejection assembly 30.
Specifically, in the present embodiment, the outer diameter of the fixing nut 33 is larger than the aperture diameter of the locking hole 211, and the aperture diameter of the separation hole 212 is larger than the aperture diameter of the fixing nut 33. During installation, the connecting rod 10 passes through the lock hole 211, and then the fixing nut 33 is screwed, so that locking between the connecting rod 10 and the lock rod 20 can be realized, during separation, the connecting rod 10 horizontally moves, so that the connecting rod 10 passes through the communicating opening 213 and enters the separation hole 212, the connecting rod 10 passes through the separation hole 212 under the action of the elastic force of the compression ejection assembly 30, and unlocking and separation of the connecting rod 10 and the lock rod 20 are realized. Through the arrangement of the lock hole 211, convenience is provided for the installation of the connecting rod 10, and the locking of the connecting rod 10 before the separation is facilitated.
In some embodiments, as shown in fig. 3 to 4, the inner wall of the locking hole 211 has a circular arc structure, and the connecting rod 10 is attached to the inner wall of the locking hole 211 far from the separation hole 212. Specifically, the inner wall of the locking hole 211 is arc-shaped, so that when the locking rod 20 moves, the impact between the connecting rod 10 and the locking hole 211 is reduced, the inner wall of the locking hole 211 and the connecting rod 10 are prevented from being jammed, the inner wall of the locking hole 211 and the inner wall of the connecting rod 10 far away from the separation hole 212 are attached to each other, the connecting rod 10 can be better limited, and the connecting rod 10 is prevented from shifting before unlocking.
In this example, further, the inner wall of the lock hole 211 has a rectangular structure, and the width of the lock hole 211 is equal to the width of the communication opening 213.
In some embodiments, as shown in fig. 1 and 3, the detaching device further includes an actuator 40, and the actuator 40 is fixed to an end of the lock lever 20 and serves to drive the lock lever 20 to slide in a direction perpendicular to the link 10. Specifically, in the release operation, the lock lever 20 is driven by the actuator 40 by the movement of the actuator 40.
In some embodiments, driver 40 is a pin puller 41, and pin puller 41 is secured to the end of locking lever 20 by a pin 42. Specifically, the pin puller 41 is an initiating explosive device, and when disengaged, the pin puller 41 is activated to provide a driving force for the movement of the lock lever 20.
In this case, further, the actuator 40 may be replaced with a non-explosive device such as an electromagnet, a cylinder, or a memory alloy device.
The satellite and arrow separation system provided in the embodiment of the present application, as shown in fig. 1 and 3, includes a satellite and arrow separation device 50, and further includes:
a satellite 60, the satellite 60 being fixed to a first end of the link 10;
the adapter 70, the adapter 70 is located on the periphery of the satellite 60, the second end of the connecting rod 10 passes through the adapter 70, the ejector is fixed on the adapter 70, and the locking rod 20 is connected with the adapter 70 in a sliding mode.
Specifically, because the satellite-rocket separation device 50 is provided with the connecting rod 10, the locking rod 20 and the ejection assembly 30, the locking separation hole 21 is formed in the surface of the locking rod 20, when the satellite-rocket separation device is installed, the first end of the connecting rod 10 is fixed on the satellite 60, the second end of the connecting rod 10 passes through the adapter 70, and the locking rod 20 is sleeved on the second end of the connecting rod 10 through the locking separation hole 21 and abuts against the adapter 70. When the separation action is carried out, the locking rod 20 moves for a certain distance and drives the locking separation hole 21 to move, so that the end part of the connecting rod 10 can pass through the locking separation hole 21 to realize the unlocking of the connecting rod 10 and the locking rod 20, at the moment, the second end of the connecting rod 10 passes through the locking separation hole 21 under the driving of the ejection assembly 30 to realize the separation of the connecting rod 10 and the locking rod 20, finally, the connecting rod 10 and the satellite 60 move towards the direction far away from the adapter 70 under the action of the ejection assembly 30 to realize the separation of the star and the arrow, through the arrangement of the device, the unlocking action and the separation action of the satellite 60 are both acted on the same position, the assembly space of the installation surface of the satellite 60 is effectively saved, the effective load capacity of the satellite 60 is increased, the moving direction of the locking rod 20 is vertical to the moving direction of the connecting rod 10 or not on the same straight line, and the influence on the connecting rod 10 when the locking rod 20 moves can be effectively avoided, so that the driving force of the ejection assembly 30 can meet the launching requirements of the microsatellite 60.
In this case, further, the number of the satellite-rocket separation devices 50 is 2, and the same lock rod 20 is shared by the 2 satellite-rocket separation devices. Specifically, the satellite 60 and the adapter 70 are connected firmly through 2 satellite-arrow separation devices, and unlocking and separation of the 2 satellite-arrow separation devices can be simultaneously realized through controlling the lock rod 20.
In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise contact of the first and second features not directly but through another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description of the present application, it is to be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise" indicate orientations or positional relationships based on the orientation or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present application and for simplicity in description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be considered as limiting the present application.
It should be noted that all the directional indications in the embodiments of the present application are only used to explain the relative position relationship, the motion situation, and the like between the components in a certain posture, and if the certain posture is changed, the directional indication is changed accordingly.
In this application, unless expressly stated or limited otherwise, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In addition, descriptions in this application as to "first", "second", etc. are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
In the description herein, reference to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.
In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present application.
While embodiments of the present application have been shown and described, it will be understood by those of ordinary skill in the art that: numerous changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the application, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. The low-impact unlocking satellite-rocket separation device is characterized by comprising:
a link having opposite first and second ends, the first end of the link being secured to the satellite and the second end of the link passing through the adapter;
the surface of the lock rod is provided with a locking separation hole, and the lock rod is sleeved at the second end of the connecting rod through the locking separation hole and is clamped with the connecting rod;
the ejection assembly is connected with the connecting rod, the locking rod moves for a certain distance and is separated from the clamping connection with the connecting rod, and the connecting rod penetrates through the locking separation hole towards the satellite under the action of the ejection assembly.
2. The low impact unlocking star and arrow separation device of claim 1 wherein the ejection assembly comprises:
the fixing sleeve is fixed on the adapter, and the connecting rod penetrates through the fixing sleeve and is in sliding connection with the fixing sleeve;
the surface of the connecting rod is provided with a butting protrusion, the compression spring is positioned in the fixed sleeve and sleeved on the surface of the connecting rod, the upper end of the compression spring is abutted against the butting protrusion, and the lower end of the compression spring is abutted against the adapter.
3. The low impact unlocking satellite-rocket separation device as claimed in claim 2, wherein said ejection assembly further comprises a fixing nut, said fixing nut is in threaded connection with said second end of said connecting rod, and said locking rod is located between said fixing nut and said compression spring.
4. The low impact unlocking satellite-rocket separation device as claimed in claim 3, wherein a surface of said connecting rod is provided with a shaft shoulder, and said locking rod is located between said shaft shoulder and said fixing nut.
5. The low impact unlocking satellite-rocket separation device as claimed in claim 2, wherein said abutment protrusion extends to the end surface of said connecting rod in a direction away from said compression spring, one end of said abutment protrusion away from said compression spring is provided with a first radially extending protrusion, and said first radially extending protrusion is fixed on the satellite.
6. The low impact unlocking satellite-rocket separation device as claimed in claim 1, wherein the end surface of the connecting rod is provided with a weight reduction groove extending towards the inside of the connecting rod.
7. The low impact unlocking satellite-rocket separation device as claimed in claim 1, wherein said locking separation holes comprise:
the lock rod is sleeved on the surface of the connecting rod through the lock hole, and the second end of the connecting rod is abutted against the surface of the lock rod;
the separation hole, the separation hole with the lockhole intercommunication, the lockhole with be provided with the confession between the separation hole the intercommunication mouth that the connecting rod passed, the pulling the locking lever makes the connecting rod passes the intercommunication mouth and enters into when the separation hole, the connecting rod is in pop out towards the direction of satellite under the effect of ejection subassembly the separation hole.
8. The low-impact unlocking satellite-rocket separation device as claimed in claim 7, wherein the inner wall of the lock hole is of a circular arc structure, and the connecting rod is attached to the inner wall, away from the separation hole, of the lock hole.
9. The low-impact unlocking satellite-rocket separation device as claimed in claim 1, wherein the separation device further comprises a driver, the driver is a pin shifter, and the pin shifter is fixed at the end of the lock rod through a pin shaft and used for driving the lock rod to move towards the direction perpendicular to the connecting rod.
10. A satellite and rocket separation system, comprising the satellite and rocket separation device according to any one of claims 1-9, and further comprising:
a satellite secured to a first end of the link;
the adapter, the adapter is located all sides of satellite, the jettison device is fixed in on the adapter, locking lever sliding connection in the surface of adapter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176589.7A CN113879569A (en) | 2021-10-09 | 2021-10-09 | Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176589.7A CN113879569A (en) | 2021-10-09 | 2021-10-09 | Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113879569A true CN113879569A (en) | 2022-01-04 |
Family
ID=79005851
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111176589.7A Pending CN113879569A (en) | 2021-10-09 | 2021-10-09 | Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113879569A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114353603A (en) * | 2022-01-13 | 2022-04-15 | 北京中科宇航技术有限公司 | Separation unlocking device for non-explosive device star and arrow |
| CN114577073A (en) * | 2022-03-01 | 2022-06-03 | 航天科工火箭技术有限公司 | Explosion bolt buffer device |
| CN114735249A (en) * | 2022-06-09 | 2022-07-12 | 北京劢亚科技有限公司 | Locking and unlocking mechanism for satellite launching box |
| CN115180186A (en) * | 2022-08-17 | 2022-10-14 | 北京凌空天行科技有限责任公司 | Satellite-rocket separation mechanism |
Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB858986A (en) * | 1958-11-25 | 1961-01-18 | Cecil Coleman Ltd | An improved projectile toy |
| US3398640A (en) * | 1965-12-23 | 1968-08-27 | Oerlikon Buehrle Holding Ag | Rocket launcher device |
| EP0296936A1 (en) * | 1987-06-16 | 1988-12-28 | AEROSPATIALE Société Nationale Industrielle | Drive mechanism for fast and controlled separation of two coupled elements |
| US20080078887A1 (en) * | 2006-09-12 | 2008-04-03 | Lockheed Martin Corporation | Apparatus Comprising a Payload Ejection Mechanism |
| US20090108138A1 (en) * | 2007-10-30 | 2009-04-30 | Raytheon Company | Space object deployment system and method |
| CN202751817U (en) * | 2012-09-22 | 2013-02-27 | 关海涛 | Toy ejector |
| CN204223193U (en) * | 2014-10-31 | 2015-03-25 | 北京宇航系统工程研究所 | The tight device of quick connection lock |
| CN205124200U (en) * | 2015-11-12 | 2016-03-30 | 易事特集团股份有限公司 | Fixing structure for circuit board |
| CN106184826A (en) * | 2016-07-11 | 2016-12-07 | 上海宇航系统工程研究所 | Satellite and the rocket spring separator |
| CN106742082A (en) * | 2016-12-14 | 2017-05-31 | 哈尔滨工业大学 | A kind of skin asterism formula separator |
| CN207157486U (en) * | 2017-08-05 | 2018-03-30 | 北京海利天梦科技有限公司 | Unmanned plane wing rapid dismounting apparatus |
| CN109724461A (en) * | 2018-12-19 | 2019-05-07 | 湖北航天飞行器研究所 | A kind of locking mechanism of vehicle transmitting system |
| CN209344007U (en) * | 2019-03-07 | 2019-09-03 | 上海电气集团股份有限公司 | A kind of repulsion operating mechanism of belt lock catch |
| CN111284731A (en) * | 2020-01-16 | 2020-06-16 | 清华大学 | Electromagnetic locking and releasing mechanism for separating star from arrow and electromagnetic locking and releasing method |
| US20200189771A1 (en) * | 2017-09-01 | 2020-06-18 | Ruag Space Ab | Separation device for spacecraft and a method for separation |
| CN210942314U (en) * | 2019-08-12 | 2020-07-07 | 重庆零壹空间科技集团有限公司 | Elastic separation mechanism |
| CN113120260A (en) * | 2021-05-14 | 2021-07-16 | 上海宇航系统工程研究所 | Thermally-induced fusing steel ball lock pressing and releasing mechanism |
| CN213746910U (en) * | 2020-12-10 | 2021-07-20 | 浙江万事兴电器有限公司 | Stove foot mounting structure |
| CN113386984A (en) * | 2021-08-04 | 2021-09-14 | 北京中科宇航技术有限公司 | Satellite and rocket separation unlocking driving device |
| CN113428390A (en) * | 2021-08-04 | 2021-09-24 | 北京中科宇航技术有限公司 | Memory alloy driven satellite release device |
-
2021
- 2021-10-09 CN CN202111176589.7A patent/CN113879569A/en active Pending
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB858986A (en) * | 1958-11-25 | 1961-01-18 | Cecil Coleman Ltd | An improved projectile toy |
| US3398640A (en) * | 1965-12-23 | 1968-08-27 | Oerlikon Buehrle Holding Ag | Rocket launcher device |
| EP0296936A1 (en) * | 1987-06-16 | 1988-12-28 | AEROSPATIALE Société Nationale Industrielle | Drive mechanism for fast and controlled separation of two coupled elements |
| US20080078887A1 (en) * | 2006-09-12 | 2008-04-03 | Lockheed Martin Corporation | Apparatus Comprising a Payload Ejection Mechanism |
| US20090108138A1 (en) * | 2007-10-30 | 2009-04-30 | Raytheon Company | Space object deployment system and method |
| CN202751817U (en) * | 2012-09-22 | 2013-02-27 | 关海涛 | Toy ejector |
| CN204223193U (en) * | 2014-10-31 | 2015-03-25 | 北京宇航系统工程研究所 | The tight device of quick connection lock |
| CN205124200U (en) * | 2015-11-12 | 2016-03-30 | 易事特集团股份有限公司 | Fixing structure for circuit board |
| CN106184826A (en) * | 2016-07-11 | 2016-12-07 | 上海宇航系统工程研究所 | Satellite and the rocket spring separator |
| CN106742082A (en) * | 2016-12-14 | 2017-05-31 | 哈尔滨工业大学 | A kind of skin asterism formula separator |
| CN207157486U (en) * | 2017-08-05 | 2018-03-30 | 北京海利天梦科技有限公司 | Unmanned plane wing rapid dismounting apparatus |
| US20200189771A1 (en) * | 2017-09-01 | 2020-06-18 | Ruag Space Ab | Separation device for spacecraft and a method for separation |
| CN109724461A (en) * | 2018-12-19 | 2019-05-07 | 湖北航天飞行器研究所 | A kind of locking mechanism of vehicle transmitting system |
| CN209344007U (en) * | 2019-03-07 | 2019-09-03 | 上海电气集团股份有限公司 | A kind of repulsion operating mechanism of belt lock catch |
| CN210942314U (en) * | 2019-08-12 | 2020-07-07 | 重庆零壹空间科技集团有限公司 | Elastic separation mechanism |
| CN111284731A (en) * | 2020-01-16 | 2020-06-16 | 清华大学 | Electromagnetic locking and releasing mechanism for separating star from arrow and electromagnetic locking and releasing method |
| CN213746910U (en) * | 2020-12-10 | 2021-07-20 | 浙江万事兴电器有限公司 | Stove foot mounting structure |
| CN113120260A (en) * | 2021-05-14 | 2021-07-16 | 上海宇航系统工程研究所 | Thermally-induced fusing steel ball lock pressing and releasing mechanism |
| CN113386984A (en) * | 2021-08-04 | 2021-09-14 | 北京中科宇航技术有限公司 | Satellite and rocket separation unlocking driving device |
| CN113428390A (en) * | 2021-08-04 | 2021-09-24 | 北京中科宇航技术有限公司 | Memory alloy driven satellite release device |
Non-Patent Citations (1)
| Title |
|---|
| 任海辽等: "能量可调式小型化星箭弹簧分离装置结构设计及研究", 国际太空, no. 9, 25 September 2016 (2016-09-25), pages 61 - 64 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114353603A (en) * | 2022-01-13 | 2022-04-15 | 北京中科宇航技术有限公司 | Separation unlocking device for non-explosive device star and arrow |
| CN114353603B (en) * | 2022-01-13 | 2023-11-14 | 北京中科宇航技术有限公司 | Non-initiating explosive device satellite and rocket separation unlocking device |
| CN114577073A (en) * | 2022-03-01 | 2022-06-03 | 航天科工火箭技术有限公司 | Explosion bolt buffer device |
| CN114577073B (en) * | 2022-03-01 | 2024-02-02 | 航天科工火箭技术有限公司 | Explosion bolt buffer device |
| CN114735249A (en) * | 2022-06-09 | 2022-07-12 | 北京劢亚科技有限公司 | Locking and unlocking mechanism for satellite launching box |
| CN114735249B (en) * | 2022-06-09 | 2022-08-16 | 北京劢亚科技有限公司 | Locking and unlocking mechanism for satellite launching box |
| CN115180186A (en) * | 2022-08-17 | 2022-10-14 | 北京凌空天行科技有限责任公司 | Satellite-rocket separation mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113879569A (en) | Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system | |
| US4842218A (en) | Pivotal mono wing cruise missile with wing deployment and fastener mechanism | |
| US6446906B1 (en) | Fin and cover release system | |
| JP5620209B2 (en) | Restraint and release device | |
| CN111954625B (en) | Satellite configuration and method of separation thereof | |
| CN110104161B (en) | Folding tail unfolding mechanism and unfolding method thereof | |
| US11505318B2 (en) | Container retention and release apparatus having integral swaybrace and retention features | |
| CN113277124B (en) | Unlocking separation device based on split nut | |
| CN107128511B (en) | Novel reusable connection and separation device for miniature satellite | |
| CN211685687U (en) | Stage cold separation structure for carrying rocket | |
| CN113184227B (en) | Passive space locking and releasing device | |
| US11512927B2 (en) | Multi-mission munition adapter | |
| EP0955236B1 (en) | Single hook ejector rack for miniature munitions | |
| CN208576736U (en) | A kind of multiple spot compresses the Payload Attach Fitting of synchronous release | |
| CN112693627A (en) | One-rocket multi-satellite stacked launching method | |
| US3216322A (en) | Bomb rack adapter | |
| US8052444B1 (en) | Latching release system for a connector assembly | |
| EP3061690B1 (en) | Air delivery lock and system | |
| US20110240799A1 (en) | Decoupling Mechanism for a Store | |
| US11767096B2 (en) | Systems and methods for indicating release of a canopy of an aircraft | |
| CN112124638A (en) | Compaction release device and spacecraft | |
| RU2500591C1 (en) | Aircraft compartment separation system | |
| CN117755528A (en) | Separating mechanism facing microsatellite | |
| CN113184229A (en) | Linkage type space clamping jaw releasing device | |
| WO2009130690A2 (en) | Ejectable pylon for airborne payloads |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |