862results about "Cosmonautic component separation" patented technology

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.

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.

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.

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.

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.

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.

The locking and releasing device for the spacecraft comprises a base, a shell, a sliding sleeve, a pin puller, a split nut assembly and a first spring, the base is of a cylindrical structure, and a first mounting plate and a second mounting plate are fixed to the two axial ends of the base correspondingly; the sliding sleeve slidably sleeves the base and is connected with the first mounting plate through the first spring. The shell sleeves the sliding sleeve at an interval and is fixed to the first mounting plate and the second mounting plate. The pin puller is mounted on the shell, and one end of the pin puller extends into the shell; a plurality of notches evenly distributed in the circumferential direction are formed in the side wall of the base, a first through hole communicated with the interior of the base and used for ejecting the locking rod is formed in the middle of the first mounting plate, a split nut assembly used for locking the locking rod is mounted in the base, and a plurality of sets of connecting lug plates evenly distributed in the circumferential direction are fixed to the outer side wall of the split nut assembly. The multiple sets of connecting lug plates are arranged in one-to-one correspondence with the multiple notches and penetrate through the notches through connecting rods to be hinged to the sliding sleeve.

End effectors and systems may capture, release, and / or create a mating engagement between the end effector and a target object, such as in capture and launch applications, grasping applications, or pick-and-place applications. The end effectors are tolerant of positional and rotational misalignment of the target object, and may include a plurality of roller wheels, one or more of which is arranged in a non-parallel plane with respect to one or more other roller wheels. Control devices enable operation of these and other end effectors in a portable, self-contained system that a single operator can use in a hand-held or wearable form factor. The control devices may include a drive system for power transfer, manual and automatic leveling or angular positioning mechanisms, and / or operator-mounting features. Related methods may involve capture and release, pick-and-place, and / or grasping operations performed with the disclosed control device and one or more end effectors coupled thereto.

The utility model provides a spacecraft space rendezvous and docking structure and a spacecraft, and relates to the technical field of spacecraft parts, the spacecraft space rendezvous and docking structure comprises a first docking piece, a second docking piece, a guide structure and a buffer structure, the first docking piece is used for being installed on a spacecraft body, and the second docking piece is used for being installed on the spacecraft body. The second butt joint piece is used for being installed on a body of another spacecraft. The first butt-joint piece is provided with a butt-joint part, the guide structure is arranged on the edge of the butt-joint part, and when the second butt-joint piece is close to the first butt-joint piece, the guide structure abuts against the edge of the second butt-joint piece so that the second butt-joint piece can move along the guide structure; the buffer structure is installed on the butt joint part, and when the second butt joint piece is close to the first butt joint piece, the buffer structure abuts against the second butt joint piece and is used for being pressed and shrunk. According to the spacecraft space rendezvous and docking structure, the guiding function and the buffering function can be achieved through the guiding structure and the buffering structure respectively, and the stability of a spacecraft in the space interaction docking process is effectively guaranteed.

Container for collecting space debris. Space debris ingress through container's openable access port. A barrier deployment mechanism has a rotatable roll of flexible material on a frame assembly. A barrier translation mechanism translates the frame assembly towards or away from the access port to adjust the size of the compartment. When unwound, the roll forms a compartment for containing the space debris within the interior of the container, thus forming an obstruction between the compartment and access port.

A tiered spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. A first tier includes a first frame enclosing a first area. A first net-like mesh is coupled to the first frame and fills the first area enclosed by the first frame. A second tier includes a second frame enclosing a second area. A second net-like mesh is coupled to the second frame and fills the second area enclosed by the second frame. A plurality of support beams attach the first frame to the second frame. A lander is used to slow and stop a spacecraft on a celestial body. The lander includes a first and a second webbed structure and a decelerator coupled to the first webbed structure and / or the second webbed structure. The decelerator maintains a tension in the first and / or second webbed structure below a predetermined threshold.

The invention discloses a stacked multi-star release mechanism adopting modular components, which is characterized by comprising a base (1), a separation seat (2), a T-shaped pressing rod (3), a pressing rod control block (4), a large pressing rod (5), a stacking column (6), a pressing cover (7), a hinge (8), a pressure spring A (9), a push rod component (10) and a pressing screw (11). The separation seat (2), the hinge (8) and the push rod assembly (10) are all modular assemblies, are simple in structure and easy to assemble and produce, and can be compatible with stacking columns in various forms.

The invention relates to a large-bearing memory alloy driven unlocking separation nut mechanism, and belongs to the technical field of spaceflight structures. The memory alloy separation nut comprises a shell assembly, a split nut assembly, a bearing force transmission assembly, a memory alloy driving assembly and a nut separation assembly, a modular design concept is adopted, configuration design is carried out on the memory alloy separation nut according to three functional parts of driving, transmission and execution, the bearing efficiency and the unlocking reliability are improved in a targeted mode, and the memory alloy separation nut is suitable for being used for a large-scale industrial production. The unlocking impact is reduced, and the separation nut is more convenient to use.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

Provided is a bracket for use in a hold and release mechanism (“HRM”) system for releasably holding a deployable payload in a stowed configuration. The bracket includes a conical portion for nesting with a conical portion of a second bracket for forming a first separation interface therebetween. The conical portion of the bracket is configured as a cone and the conical portion of the second bracket is configured as a cup. The bracket includes one or more bracket connectors for connecting the bracket to the deployable payload or a platform on which the deployable payload is stowed. The second bracket connects to whichever of the deployable payload or the platform the first bracket is not connected.

The invention discloses a multi-degree-of-freedom electromagnetic ejection separation and adsorption integrated space interface device, and belongs to the field of mechanical structure design. An existing boarding load separation method is complex in operation, poor in safety, low in separation freedom degree and low in response speed. The controller is used for controlling the posture adjusting mechanism to work according to the sensed position of the boarding load, driving the electromagnetic ejection mechanism to be aligned with the boarding load, receiving alignment information that the electromagnetic ejection mechanism is aligned with the boarding load, controlling the electromagnetic ejection mechanism to work, and locking the boarding load in a clamping and attractive force generating mode; according to locking information that the electromagnetic ejection mechanism and the boarding load are locked, a posture adjusting mechanism is controlled to drive the electromagnetic ejection mechanism and the boarding load to be aligned with the task target; according to the sensing result that the electromagnetic ejection mechanism and the boarding load are aligned with the task target, the electromagnetic ejection mechanism is controlled to be opened, and the electromagnetic ejection mechanism generates repulsive force to eject the boarding load to the task target. The hosting load is separated and captured more safely, and the degree of freedom is higher.

Device for separating a second part from a first part, including a first interface intended to be fixed to the first part and a second interface intended to be fixed to the second part, a docking stud passing through the first and second interfaces and being held at the first interface by a separation nut and at the second interface by a first nut / locknut assembly, the docking stud being covered by a cap secured to the second interface and intended to receive it once the separation nut has broken and the first and second interfaces have been separated, and a retraction spring is provided to extract the docking stud from the first interface, propel it towards a damping material fixed at the bottom of the cap and hold it there by its residual holding force alone.

The invention relates to the technical field of spacecraft docking and docking interfaces, and discloses a standard interface device for spacecraft docking and docking, which comprises a first docking assembly and a second docking assembly, the first docking assembly and the second docking assembly adopt identical configuration design, and through dynamic switching of active and passive working modes, when one is an active end to execute capturing and locking functions, the other is a passive end to execute capturing and locking functions; and vice versa, two-way exchange of active and passive performance is realized, flexible docking requirements of spacecrafts with different roles are met, and the interface universality is improved. The capturing and locking assembly at the waist of the first butt-joint assembly comprises symmetrical locking arms and can be opened and closed to achieve rigid locking, the two butt-joint assemblies are each provided with a T-shaped structure used for bearing and a butterfly-shaped structure, the design breaks through the function fixing limitation of a traditional connector, position deviation is corrected through the butterfly-shaped structures, loads are evenly transmitted through the inverted-T-shaped structures, and the locking effect is good. The design is simplified, and the universality, the adaptability and the connection reliability are improved at the same time.

The invention relates to a multi-satellite stacking point type separation mechanism which comprises a carrying support, a satellite bearing frame, a connection unlocking device, a separation electric connector assembly and a travel switch assembly. Spring separation device mounting interfaces are reserved in the satellite bearing frames, each layer of satellite bearing frame is fixedly connected with each layer of flat satellite body, and the lowermost layer of satellite bearing frame is connected with a carrying support; the connecting and unlocking device is installed at the connecting position of every two adjacent layers of satellite force bearing frames, and connecting and orderly unlocking between each layer of satellites, the bottom layer of satellites and the carrying support are achieved. The separation electric connector assembly and the travel switch assembly are installed on each layer of satellite force bearing frame and provide separation on-off signals for the carrier rocket and each layer of satellites respectively, and the separation electric connector assembly further supplies power to each layer of connection unlocking device. The mechanism is good in connection rigidity, reliable in connection and locking and reliable in separation, and can adapt to launch tasks of carrier rockets with different stacking layer numbers of flat satellites.

The device for holding down a mobile structure, e.g., a payload, to a launch vehicle and for releasing the payload comprises a base structure fixed to the launch vehicle, a plate fixed to the payload, a releasable actuator, a release payload mechanism and a release rod are driven to movement in an axial direction relative to the base structure upon activation of the actuator. The base structure and the plate comprises mating surfaces including a concentric shear feature capable of transferring combined shear, axial, and moment loads between the base structure and the plate, with a single point of preloaded axial-only retention.

Connecting device for establishing a mechanical connection between a first body (11) and at least one second body (12), comprising a first connecting element (20) and a second connecting element (22) cooperating therewith, wherein the second connecting element (22) has an engagement portion (27) for a coupling portion (28) of the first connecting element (20), and wherein the first connecting element (20) and the second connecting element (22) are designed to form a positive connection when connected to one another, characterized in that the engagement portion (27) is formed on a holding component (29) which is connected to a core of the second connecting element (22), wherein the holding component (29) and / or the second connecting element (22) consists of or comprises a thermoplastic material, and in that at least one spring (3) is provided,which applies a force which repels the two connecting elements (20, 22) and / or the two bodies (11, 12) from each other and moves the two connecting elements (20, 22) away from each other above a predetermined temperature threshold (T1).

The invention relates to the technical field of lunar cabin section assembly and butt joint, and discloses a large-deformation flexible inflation channel for lunar cabin section assembly and butt joint, which comprises a sealed flexible channel and at least two groups of deformation control air bags, the two ends of the sealed flexible channel are respectively connected with a butt joint frame and a butt joint ring, and the deformation control air bags are arranged on the outer side of the sealed flexible channel; the deformation control air bag controls the overall pose and rigidity of the sealed flexible channel through inflation and deflation so as to compensate pose deviation between the butt joint cabin sections and balance internal loads generated by butt joint, the large-deformation flexible inflation channel is assembled on the lunar surface cabin sections in a butt joint mode, and the large-deformation flexible inflation channel can be folded and unfolded on the lunar surface in a lossless, efficient and repeated mode. Multiple properties such as wear resistance and puncture resistance and good air tightness are achieved, and multiple times of connection, separation and reconstruction of the cabin section can be achieved; the air bag can be controlled through deformation to balance the internal pressure load, prevent the cabin section from overturning and the like according to the posture change and the load; and the method also has high reliability and long-term service capability, and adapts to pose changes caused by lunar soil settlement.

The present invention discloses a device for space tether cutting and tether connection, which includes a tether cutting unit and a tether connection unit. The tether cutting unit includes a cutting motor, a first transmission chain, a second transmission chain, a driving arm, a clamping arm, a retractable anvil, and a cutting blade. The output shaft of the cutting motor is respectively connected to the first transmission chain and the second transmission chain. The end of the first transmission chain is connected to the driving arm, and the end of the second transmission chain is connected to the cutting blade. The clamping arm is connected to the driving arm, and the retractable anvil cooperates with the cutting blade to cut the tether. The tether connection unit includes a connection motor, a third transmission chain, a tether connector, and a slider. The output shaft of the connection motor is connected to the slider through the third transmission chain, and the slider drives the tether connector to move for tether connection.

A launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.

A method includes providing an image to a feature extraction model to generate feature data. The image depicts a portion of a first device and a portion of a second device. The feature data includes coordinates representing key points of each of the first and second devices depicted in the image. The method also includes obtaining position data indicating a position in 3D space of a connector of the first device. The method further includes providing the feature data and the position data to a trained autonomous agent to generate a proposed maneuver to mate the connector with a connector of the second device.

A connector (4, 4') with a load transfer rod (40, 40') designed to transfer forces and / or moments from a first support body (42) connected or connectable to the load transfer rod (40, 40') to a second support body (44) connected or connectable to the load transfer rod (40, 40') is characterized in that the load transfer rod (40, 40') has a first rod element (41) and at least a second rod element (43) which are connected to each other in a joining section (45, 48) of the load transfer rod (40, 40') by means of a joining device (46), wherein the joining device (46) has a lower tensile and / or compressive strength than the respective rod element (41, 43) above a predetermined temperature threshold.

The invention discloses a motor-driven steel ball locking mechanism based on gear and thread pair linkage, and belongs to the technical field of spacecraft on-orbit docking. The mechanism comprises a motor serving as a power source, wherein an output shaft of the motor is fixedly connected with a cylindrical gear; the cylindrical gear is in meshed connection with a locking mechanism through a gear; a butt joint conical rod is arranged above the locking mechanism, and the locking mechanism is used for capturing and locking the butt joint conical rod. When a guide taper sleeve in the locking mechanism makes contact with the butt joint taper rod, a contact switch is triggered, a motor is started, a thread pair is driven to move through gear transmission, a locking screw is made to move axially, and a steel ball is controlled to lock or unlock the butt joint taper rod. The contact switch is triggered through contact between the guide taper sleeve and the butt joint taper rod, space dust and radiation interference are avoided, autonomous capture is achieved, and the butt joint precision is remarkably improved. The mechanism is highly integrated and modularized and can be adjusted according to requirements of different spacecrafts, the size and weight of the spacecrafts are reduced, and the utilization efficiency of spaceflight resources is improved.