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1477results about "Cosmonautic component separation" patented technology
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Pressing and releasing device for stacked flat satellites and using method of pressing and releasing device
ActiveCN119190423ACosmonautic vehiclesCosmonautic component separationElectric machineryStructural engineering
The invention provides a pressing and releasing device for stacked flat satellites and a using method of the pressing and releasing device, and belongs to the technical field of satellite launching. The problem that a pressing and releasing device of a stacked flat satellite cannot meet the requirement is solved. The spiral unlocking, pressing and releasing mechanism comprises four spiral unlocking, pressing and releasing mechanisms, the four spiral unlocking, pressing and releasing mechanisms are all arranged on a carrying adapter and connected with the outer side of a star body, and each spiral unlocking, pressing and releasing mechanism comprises a stacking column, a releasing screw and a driving motor; the stacking columns comprise a plurality of middle stacking columns, a top stacking column and a bottom stacking column, the middle stacking columns are sequentially arranged in the axial direction, the top stacking column is arranged at the upper end of the uppermost middle stacking column, the bottom stacking column is arranged at the lower end of the lowermost middle stacking column, and the bottom stacking column is connected with the carrying adapter. The device is mainly used for pressing and releasing stacked flat satellites.
Owner:HARBIN INSTITUTE OF TECHNOLOGY SATELLITE TECHNOLOGY CO LTD
Locking and releasing device based on connecting rod type structure
Owner:BEIJING WEINA STAR TECH CO LTD +2
Method of space transportation using a distributed network of space tugs
Disclosed are systems and methods for a distributed space transportation network. Satellite launches to orbit are more efficiently performed by large rockets. Modern satellites are in smaller form factor, leaving the large launch rockets with excess capacity. Small satellite operators can use ride-shares, but do not have efficient options for delivering their satellites to their desired destination and may be forced to operate their satellites in compromise orbits. The disclosed distributed space transportation network maintains a fleet of space tugs, which can dock with satellites in space at an initial arrival destination and transport the satellites to their final destinations. In one embodiment, the space tugs can dock with satellite depots to obtain fuel and repairs.
Owner:MONTERO USA INC
Non-pyrotechnic secondary satellite and rocket locking and separating device
ActiveCN119142556AHigh separation reliabilityhigh strengthCosmonautic vehiclesCosmonautic component separationShape-memory alloyStructural engineering
The invention relates to a non-pyrotechnic secondary satellite and rocket locking and separating device which comprises a shape memory alloy primary separating assembly, a pressing and releasing assembly and a turntable four-claw secondary clamping and separating assembly, and the shape memory alloy primary separating assembly is arranged in a box body of the pressing and releasing assembly; one end, extending out of the shell, of a grooving bolt shaft of the shape memory alloy first-stage separation assembly penetrates through a through hole of the separation block to be connected with a nut, and the shape memory alloy rod provides driving force for the shape memory alloy first-stage separation assembly to jointly form a first-stage unlocking mechanism; a clamping jaw guide groove of the rotary table four-jaw two-stage clamping and separating assembly is fixed to the bottom plate, a rotary table controls a clamping jaw set to be locked, and clamping jaws are connected with a separating block of the pressing and releasing assembly to jointly form a two-stage unlocking mechanism. When the device is locked, after being locked by the shape memory alloy first-stage separation assembly, the device is locked by the turntable four-claw second-stage clamping separation assembly; when the device is separated, the device is unlocked by the turntable four-claw secondary clamping and separating assembly, and then is unlocked by the shape memory alloy primary separating assembly.
Owner:UNIV OF SHANGHAI FOR SCI & TECH
Systems, methods, and devices for robotic capture of a free flyer or other unsupported object
Systems, methods, and devices for robotic capture of an object are provided. A system for robotic-based capture of a free flyer object includes a grapple fixture for mounting to the free flyer object and an end effector for capturing the free flyer object by interfacing with the grapple fixture. The grapple fixture includes a base and a deflectable probe. The end effector includes a probe guiding surface for deflecting and guiding a probe tip of the probe through an opening in the probe guiding surface and into a grappling position. The end effector includes a probe sensing element for sensing when the probe tip is in the grappling position and triggering a capture mechanism. The capture mechanism grapples the probe tip and an actuator retracts the capture mechanism to a predetermined position to establish a load-bearing interface between the free flyer object and the end effector.
Owner:MACDONALD DETTWILER & ASSOC INC
Material transfer interfaces for space vehicles, and associated systems and methods
Material transfer interfaces for space vehicles, and associated systems and methods, are disclosed. A representative system includes a coupling mechanism including a support structure, a latch-arm base movably connected to the support structure, and a latch arm pivotably connected to the latch-arm base. Another representative system includes a service valve portion, a coupling portion configured to receive the service valve portion, and a coupling mechanism for coupling the service valve portion to the coupling portion. The coupling mechanism can include latch arms positioned to pivot between a position in which the latch arms are pivoted outwardly and a position in which the latch arms are pivoted inwardly to capture the service valve portion. The latch arm can be carried by a latch-arm base that translates relative to a support structure of the coupling portion. Material transfer interfaces can include self-aligning ports having faces that engage each other with cup-and-cone structures.
Owner:ORBIT FAB INC
Satellites and satellite stacks for launch
A satellite stack includes satellites arranged in a stack, where each satellite in the stack has a planar portion with an associated support structure and a subsystems housing containing satellite subsystems extending along an edge of the planar portion. For each satellite, a height of the subsystems housing is greater than a combined height of the planar portion and the associated support structure. Each satellite is oriented at a nonzero rotational angle with respect to the satellite immediately beneath, such that no satellite has its subsystems housing positioned directly above the subsystems housing of the satellite immediately beneath.
Owner:HUBBLE NETWORK INC
Conductive line, transfer device, and space solar beam energy transportation method
PendingUS20250157685A1Batteries circuit arrangementsCosmonautic vehiclesBeam energyEngineering physics
This application presents ideas for devices that solve energy generation problems and space exploration. This application show idea that is using device such using conductor / element or device. And this application show idea that is using device such using conductive line or carrier device. This application show idea that is using device such using photon or particle related device.
Owner:NISHIZAWA KATSUYA
Connecting rod configuration separation mechanism for pressing and releasing stacked satellite assembly
PendingCN120756680ACosmonautic vehiclesCosmonautic component separationClassical mechanicsStructural engineering
The invention relates to a connecting rod configuration separation mechanism for pressing and releasing a stacked satellite assembly, and belongs to the technical field of spaceflight separation mechanisms, the connecting rod configuration separation mechanism comprises a stacking device and pressing separation devices, the stacking device is installed on the corner of each satellite of the stacked satellite assembly, each pressing separation device comprises a pressing mechanism and a rotating mechanism, and the rotating mechanism is installed on the stacking device. The pressing mechanisms are installed on the stacking device of the top satellite, the rotating mechanism is installed on the stacking device of the bottom satellite, the satellites are sequentially stacked through the stacking devices on the corners to form a stacked satellite combination, each pressing mechanism comprises two pressing rods, the pressing mechanisms are connected with the rotating mechanism through the two pressing rods, and the rotating mechanism is connected with the rotating mechanism through the two pressing rods. According to the mechanism, reliable compression connection of a plurality of stacked satellites can be achieved, the action of the mechanism is released from constraint during separation, separation of the stacked satellites is achieved, and the mechanism has the advantages of being simple in structure, large in bearing capacity, small in separation impact, large in separation margin and the like.
Owner:BEIJING INST OF ASTRONAUTICAL SYST ENG
Petal type butt joint interface driving device for space on-orbit assembly
The invention belongs to the technical field of space docking, and particularly relates to a petal type docking interface driving device for space on-orbit assembly. The butt joint interface driving device comprises a driving module, a fixing module, a locking module, an active interface and a passive interface. The locking module is in contact connection with the driving module, and the driving module and the active interface are connected with the fixing module through bolts to jointly form an active butt joint module. When the two modules are in butt joint, the petal type active and passive butt joint interfaces of different structures are connected with each other, and a locking push rod in the locking module is driven by a motor to push a locking sleeve and a lock pin to reach and leave a lock groove, so that active locking and unlocking are achieved. The butt joint interface driving device is simple and compact in structure, small in overall size, light in weight, high in reliability and suitable for rapid butt joint and separation between a space modular robot and a mechanical arm, and power-off self-locking of the motor can be achieved.
Owner:BEIJING INST OF TECH
Release device and release system for stacked panel satellites
ActiveCN119262348ACosmonautic vehiclesCosmonautic component separationSatellite technologyStructural engineering
The invention provides a release device and a release system for stacked panel satellites, and relates to the technical field of panel satellites. The release device comprises a first release device, a second release device and a base; the first release device has an initial state and a release state, in the initial state, the first end of the first release device is connected with the base, the second end of the first release device is in compression joint with the top of the stacked panel satellite, and in the release state, the first end is disconnected with the base, and the second end is separated from the top of the stacked panel satellite; the second releasing device has an initial state and a releasing state, in the initial state, the third end of the second releasing device is connected with the base, the fourth end of the second releasing device is in compression joint with the middle, located between the top and the bottom, of the stacked panel satellites, and in the releasing state, the third end can move relative to the base, and the fourth end is separated from the middle of the stacked panel satellites; the release state of the first release device can trigger the release state of the second release device, so that the problem of separation collision when the stacked panel satellites are released is reduced or avoided.
Owner:SHANGHAI SATELLITE NETWORK RESEARCH INSTITUTE CO LTD
Ultra-large planar array type space computing power center
ActiveCN121158245ACosmonautic environmental control arrangementPV power plantsEnergy schedulingSatellite bus
The invention discloses a super-large plane array type space computing power center, and belongs to the field of space technologies and space infrastructures. The space computing power center is deployed in a morning and evening orbit and comprises a plurality of computing power satellites which are physically docked in orbit through a docking mechanism. Each computing power satellite comprises a satellite platform, and a computing power load, a condensation type energy system and a space pump drive fluid loop system which are arranged on the satellite platform, and a docking mechanism for inter-satellite in-orbit physical docking is also assembled on the satellite platform. A plurality of computing power satellites form a planar array type rigid whole body through the docking mechanism, and energy scheduling among the light condensation type energy systems is realized based on the docking mechanism. According to the space computing power center, through multi-satellite physical docking and energy collaborative scheduling, the energy utilization efficiency and the power supply reliability of the system are improved.
Owner:BEIJING ORBITAL CHENGUANG TECHNOLOGY CO LTD
Rotation separation attitude adjustment method based on quaternion
The invention discloses a quaternion-based rotation separation attitude adjustment method, which comprises the following steps of: aiming at attitude requirements and angular velocity requirements of satellite separation, dividing a program angle planning process into two stages: a first stage is a directional attitude adjustment stage, and forward backward pushing is carried out through a satellite separation time point to obtain an attitude quaternion corresponding to the angular velocity of 0; taking the result as a program quaternion at the attitude adjustment ending moment; the second section is a rotation starting, stabilizing and racemization section, and according to the angular speed requirement, the quaternion of a rotation starting, stabilizing rotation and racemization program is designed; after the attitude of the rocket body is adjusted to the attitude adjustment end moment program quaternion, the angular velocity is linearly accelerated from 0 to the angular velocity required by separation according to the rotation starting, stable rotation and racemization program quaternion, and the satellite separation attitude and the angular velocity both reach expected values at the separation moment. According to the method, a universal solution is provided for one-time safe separation of multiple satellites, the problem of attitude solution ambiguity in the attitude adjusting process is avoided, high universality is achieved, and the reliability of one-time safe separation of the multiple satellites is guaranteed.
Owner:BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
Thermal management system for structures in space
ActiveUS20250051039A1Photovoltaic supportsCollapsable antennas meansElectrical batteryThermal management system
An antenna assembly has a solar layer having one or more solar cells generating solar power, an antenna layer connected to the solar layer and having electronic components utilizing the solar power generated by the solar layer, and a thermal dissipation device dissipating heat locally at the antenna assembly. A large number of antenna assemblies are connected to form an antenna array in which heat is generated locally at each antenna assembly and dissipated locally at each antenna assembly.
Owner:AST & SCIENCE LLC
Large spaceflight load based on modular design
ActiveCN119099878Aincrease flexibilityImprove use efficiencyCosmonautic vehiclesCosmonautic power supply systemsButt jointModular design
The invention provides a large spaceflight load based on modular design. The large spaceflight load comprises a platform, a docking mechanism, a solar wing / antenna integrated system and a mechanical arm. The docking mechanism is arranged in the platform; the solar wing / antenna integrated system is arranged at the bottom of the platform; the two ends of the mechanical arm are connected to mechanical arm bases arranged on the platform respectively, two-dimensional rotation can be achieved with one base as the axis, and an information / power supply link between loads is established through the mechanical arm. The butt joint mechanism comprises a driving end and a driven end which are connected with each other, when the load is in a butt joint preparation state, the driving end is converted into an extension state from a contraction state, extends out of the side face of the platform and is connected with butt joint hole sites of different loads, and when butt joint is completed, a butt joint lock of the head is locked, and butt joint of the different loads is achieved. According to the load, automatic assembly can be achieved in the on-orbit assembly, replacement and maintenance process, other auxiliary devices are not needed in the assembly process, the flexibility is high, and the use benefits of the system are ensured.
Owner:CHINA ACADEMY OF ELECTRONICS AND INFORMATION TECHNOLOGY OF CHINA ELECTRONICS TECHNOLOGY GROUP CORPORATION
Spacecraft interstage unlocking device and spacecraft
PendingCN119408746Aavoid impactavoid destructionCosmonautic vehiclesCosmonautic component separationMechanical engineeringSpacecraft
The invention relates to the technical field of spacecrafts, and discloses a spacecraft interstage unlocking device and a spacecraft, the spacecraft interstage unlocking device comprises a protection cover, and the protection cover is connected with a first cabin section; the connecting piece penetrates through the second cabin section in a limiting manner and movably penetrates through the first cabin section and the top surface of the protective cover; a limiting groove is formed in the side wall of one end, extending into the protective cover, of the connecting piece; the locking mechanism is arranged in the protective cover and comprises a lock hook and a lock piece, the lock hook is rotationally connected to the inner wall of the protective cover, one end of the lock hook is bent to form a hook part, the lock piece is movably arranged in the protective cover and has a locking position and an unlocking position, and when the lock piece is located at the locking position, the lock piece abuts against the lock hook to limit rotation of the lock hook; when the lock piece is located at the unlocking position, the lock piece is separated from the second cabin section along with the first cabin section, and the connecting piece moves along with the second cabin section and drives the lock hook to rotate till the hook part is separated from the limiting groove. The spacecraft comprises the spacecraft interstage unlocking device. And testability is achieved, and the using impact force is low.
Owner:KUAIZHOU AEROSPACE TECHNOLOGY CO LTD
Satellite deck coupling connection mechanism, satellite and satellite deck coupling connection method
ActiveCN120773930AArtificial satellitesCosmonautic component separationRemote sensingBolt connection
The invention discloses a satellite deck coupling connection mechanism, a satellite and a satellite deck coupling connection method, belongs to the technical field of satellite structures, and particularly relates to the satellite deck coupling connection mechanism and the satellite deck coupling connection method. The problems of low assembly efficiency, uncontrollable thermal stress and difficulty in on-orbit maintenance in the existing bolt connection technology are solved; the mechanism comprises interlocking units which are arranged on the butt joint edges of the two cabin plates in pairs. The satellite cabin plate coupling connection mechanism, the satellite and the satellite cabin plate coupling connection method are applied to modular cabin plates of spacecrafts such as the satellite and the like, and bolt-free interlocking connection aims at overcoming the defects of traditional bolt connection in the aspects of rapid disassembly and assembly, thermal deformation adaptability and the like.
Owner:HARBIN GONGDA SATELLITE TECH CO LTD
Ring-synchronized separation adapter for separating payload in space environment
ActiveUS12358654B1Cosmonautic vehiclesCosmonautic component separationComputer hardwareSpace environment
The present invention relates to a ring-synchronized separation adapter for separating a payload in a space environment, and more specifically, to a ring-synchronized separation adapter for separating a payload in space environment, in which the ring-synchronized separation adapter has a configuration in which a plurality of segmented clamp portions are simultaneously fastened or unfastened by rotating a drive member making contact with all of the plurality of segmented clamp portions, so that accuracy in separation of the payload is improved, explosion is not utilized, and stability of the ring-synchronized separation adapter is improved as a whole.
Owner:SPACEBEY INC
Multiple hold down and release device for restraining and releasing a payload from a spacecraft, and methods to release a payload from a spacecraft and to install such a multiple hold down and release device
Multiple hold down and release device for restraining and releasing a payload (3) from a spacecraft (4), and methods to release a payload (3) from a spacecraft (4) and to install such a multiple hold down and release device. The device comprises: - a plurality of hold-down assemblies (19, Figure 3) placed on the periphery of the device, each one of them comprising a hold-down bracket (11, Figure 4) configured to be attached to the payload (3) and a hold-down support (20, Figure 4), both of them with conical mating surfaces (10, 10', Figure 4), each hold-down support (20) comprising at least one torsion spring (9, Figure 4) around an axis (17, Figure 4), - a plurality of pairs of connecting levers (5), each one of the connecting levers (5) comprising a first end (14, Figure 4) configured to be coupled to a corresponding hold-down support (20) such that each corresponding lever (5) is articulated with the corresponding hold-down support (20) through an axis (17); and a second end (15, Figure 4) opposite to the first end (14), - a plurality of restraint cables (6) that join the second ends (15) of each pair of connecting levers (5) and are arranged radially with a central area where the restraint cables (6) cross, and - a central release actuator (1) configured to be able to cut the restraint cables (6).
Owner:AIRBUS DEFENCE & SPACE SAU
Low earth orbit mechanical deployable structure
An antenna array has a plurality of square or rectangular antenna assemblies. Each assembly includes a first antenna assembly surface with a solar cell and a second antenna assembly with one or more antenna elements. The antenna assemblies are interconnected without gaps therebetween to form a first contiguous array surface comprised of the first antenna assembly surfaces and a second contiguous array surface comprised of the second antenna assembly surfaces. The antenna assemblies are connected together by mechanically stored-energy connectors, such as spring tape, that self-deploy the array in space without the use of electric energy.
Owner:AST & SCIENCE LLC
Satellite capture module and orbital service vehicle
PCT designated stage expiredWO2025088493A1Cosmonautic vehiclesCosmonautic component separationClassical mechanicsMechanical engineering
A satellite capture module (1) comprises: a main structure (10) extended about a main axis (X); a deployment system (40) configured to move said main structure (10); a plurality of arms (20) mounted on said main structure (10) around said main axis (X); a plurality of anchoring members (30) configured to engage an anchoring structure (103) of a target satellite (100), each anchoring member (30) being mounted on a respective arm (20) of said plurality of arms (20); wherein each arm (20) is movable between a first configuration in which said anchoring member (30) is placed at a first radial distance from said main axis (X) and a second configuration in which said anchoring member (30) is placed at a second radial distance from said main axis (X) greater than said first radial distance.
Owner:D ORBIT SPA
Spacecraft servicing devices and related assemblies, systems, and methods
ActiveUS12240630B2Cosmonautic propulsion system apparatusArtificial satellitesServicing equipmentClassical mechanics
Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.
Owner:NORTHROP GRUMMAN SYSTEMS CORP
Method and apparatus for the stabilisation of a satellite formation
PCT designated stage expiredWO2024252252A1Cosmonautic vehiclesCosmonautic propulsion system apparatusClassical mechanicsOrbit
The invention relates to a method for stabilization of the orbital motion set-up of a group of satellites (2, 3, 4, 5, 6,.... n) bound to a tether (10). To such end, the tension (T) of the tether (10) that connects two or more satellites is controlled in order to keep them in the desired flight formation. This effect is obtained by perturbing a satellite (2, 3, 4) to generate a. tension component (T) in the tether, which results in a recoil force that brings the system back into a condition of equilibrium. According to a preferred embodiment, the tension (T) of the tether (10) is obtained by adjusting the disposition of one or more aerodynamic surfaces (20, 21, 30, 31) provided on the satellites (2, 3) at the ends of the tether.
Owner:POLITECNICO DI TORINO
Spacecraft payload hold down and release device and method
ActiveUS20240425208A1Cosmonautic vehiclesCosmonautic component separationControl theoryTorsion spring
A multiple hold down and release device for restraining and releasing a payload from a spacecraft performs methods to release a payload from a spacecraft and install a multiple hold down and release device. At a periphery, the device includes hold-down assemblies. Each assembly has a hold-down bracket configured to attach to the payload and a hold-down support, both having conical mating surfaces. Each hold-down support includes a torsion spring(s) around an axis. In pairs of connecting levers, each lever includes a first end coupling to a corresponding hold-down support such that each corresponding lever is articulated with the corresponding hold-down support through an axis; and a second end opposite the first end. Restraint cables join second ends of each pair of connecting levers and are arranged radially with a central area where the restraint cables cross. A central release actuator is configured for cutting the restraint cables.
Owner:AIRBUS DEFENCE & SPACE SAU
Separating and unlocking mechanism
The invention discloses a separating and unlocking mechanism. The separating and unlocking mechanism comprises a base; the separating and pushing assembly comprises a fixed shell and a push rod, the fixed shell is detachably arranged on the base, and the push rod penetrates through the fixed shell and is slidably arranged on the fixed shell; the locking piece is detachably connected with the push rod and is positioned outside the fixed shell; the connection unlocking assembly comprises a guide rod and a clamping jaw structure, the guide rod is connected with the end, deviating from the locking piece, of the push rod, the separation unlocking mechanism adopts a connecting rod linkage assembly to control the locking piece to unlock the push rod, single-point faults are avoided, and reliability is improved; the separation pushing assembly and the connection unlocking assembly form an independent unlocking module, the structure is compact, the space is saved, multi-stage unlocking control is achieved, the unlocking and locking stability is improved, the operation convenience is improved, unlocking lagging is avoided, and the requirement for unlocking force is reduced.
Owner:AEROSPACE SCI & IND KET TECH CO LTD
Explosive bolt collecting device, aerospace craft separation system and aerospace craft
The invention provides an explosive bolt collecting device, an aerospace craft separation system and an aerospace craft, the collecting device is installed on a separation body of the aerospace craft, the collecting device is provided with a collecting hole, the collecting hole is provided with a collecting opening, and the collecting hole extends inwards from the collecting opening in the first direction; wherein the sectional area of the collecting hole is gradually reduced in the first direction. When the separated body of the aerospace craft is separated, the explosive bolt is detonated, the broken connecting piece flying out of the explosive bolt at a high speed moves in the collecting hole in the first direction, the broken connecting piece of the explosive bolt extrudes the inner wall face of the collecting hole to form self-locking, the broken connecting piece cannot rebound, and the risk that normal work of other equipment is affected is reduced; and meanwhile, the risk that the broken connecting piece rebounds back to the mounting hole of the explosive bolt is reduced, the separation system is high in working reliability, and smooth and safe separation of the separated body of the aerospace craft is facilitated.
Owner:BEIJING LINGKONG TIANXING TECH CO LTD
Four-redundancy travel switch self-power-on method and structure
PendingCN119429189AReliable powerachieve balanceCosmonautic vehiclesCosmonautic power supply systemsControl signalRocket
The invention provides a four-redundancy travel switch self-power-on method and structure, and the method employs four travel switch contacts which are connected to two ends of a power-on control signal of a satellite power supply controller in a mode that every two contacts are connected in parallel and then are connected in series. The satellite is provided with two satellite and rocket separation pressing points, each pressing point is provided with two travel switches, and travel switch contacts of the pressing points are connected in series. According to the invention, the release of any satellite-rocket separation pressing point can be ensured, the power supply controller can be triggered to be powered on autonomously, and the reliable power-on of the satellite can still be ensured when any travel switch fails.
Owner:SHANGHAI SATELLITE ENG INST
System for making object cooperative and method for making object cooperative
To provide a system capable of eliminating a complicated function or a high-precision control necessary when a service satellite approaches an outer space non-cooperative object or the like for providing an on-orbit service or removing debris. A cooperative objectification system 1, which cooperatively objectifies an outer space non-cooperative object C existing in an outer space, comprises: a spacecraft S configured to move in the outer space; and a cooperative interface M attached to a surface of the outer space non-cooperative object C by the spacecraft S.
Owner:ASTROSCALE JAPAN
Connecting, pushing and punching device integrating multiple functions of connecting, unlocking and pushing and punching
ActiveCN119218450Acompact structureImprove energy utilizationCosmonautic vehiclesCosmonautic component separationImpactPiston
The invention discloses a connecting, pushing and punching device integrating multiple functions of connecting, unlocking and pushing and punching. The connecting, pushing and punching device comprises a connecting bolt, a split nut, a piston barrel, a pushing-out rod, a shell, a base body, a connecting nut, a pressing ring, a spring, a pressing ring bolt and an actuating air source. Wherein one end of the connecting bolt is connected with the split nut, the piston cylinder and the base body, and the other end of the connecting bolt is connected with a second connected piece through the connecting nut; the split nut is arranged in the piston cylinder; the push-out rod is arranged in the piston cylinder; the piston cylinder is arranged in the shell; the inner wall of the base body is connected with the outer surface of the shell; the outer surface of the base body is sleeved with the pressing ring. The pressing ring is connected with the first connected piece through a pressing ring bolt. The spring is arranged in the shell; and the actuating air source is connected with the shell. The invention has the advantages of compact structure, high connection efficiency, small unlocking impact, stable and adjustable thrust, controllable acting impulse, good sealing performance, light structural weight and convenience in installation.
Owner:BEIJING INST OF ASTRONAUTICAL SYST ENG
A wall-mounted ring unlocking device for picosatellites
ActiveCN115009540BArtificial satellitesCosmonautic component separationStructural engineeringMechanical engineering
This invention patent discloses a wall-mounted ring unlocking device for picosatellites, specifically related to the technical field of spacecraft structures. It includes a base, a locking and releasing mechanism, a pressing ring, a thrust mechanism, and a docking ring. The base is fixedly connected to the satellite bottom plate. The locking and releasing mechanism is used for locking and releasing the pressing ring. The pressing ring is an unclosed ring structure, and both ends of the pressing ring are connected to the locking and releasing mechanism. The thrust mechanism is used to push the docking ring to separate in a direction away from the base. The technical solution of this invention solves the problems of the existing picosatellite separation mechanism, such as complex structure, heavy weight, and large unlocking impact, and enables the safe release of picosatellites.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS