132results about "Launch systems" patented technology

The system and method for decelerating space objects moving at high velocities are provided. The system comprises at least one closed volume containing a combination of gas, liquid, solid particles, or a mixture thereof. The volume can be transported to the targeted location using a range of means, including a chemical gun, light gas gun, electromagnetic coil gun, superconducting quench gun, a rocket, or a combination thereof. The volume is strategically positioned on the trajectory of the moving object. Upon penetrating the walls of the volume, the object passes through it, experiencing deceleration.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled with the spaceplane and / or the rocket plane or several gliders, takeoff from a runway and ascends to a staging altitude and speed under the carrier aircraft power. After staging, the tow aircraft will pick up the spaceplane or the rocket plane or the glider from the carrier aircraft in flight. The towed spaceplane or the rocket plane or the glider continues ascending and accelerating by the tow aircraft. The spaceplane or the rocket plane will disconnect from the tow aircraft and continue to ascend and accelerate in an atmosphere by using the ramjet engine. The spaceplane or the rocket plane equipped with a propulsion unit is used to place the spacecraft into the earth orbit. The glider will disconnect from the tow aircraft and lands in designated place. Gliders can be used for instantly delivering of correspondence, parcels, and civil goods from a supplier to wide variety of individual consumers or corporate customers.

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 reusable orbital vehicle (14) for a space transport system (10) comprises a fuselage (22) the shape of which widens in a direction extending from the front end (24) of the reusable orbital vehicle to a rear end (26) of said fuselage (22) and inside which there is defined a housing (32), and a crew-evacuation vehicle (34) housed in said housing (32) and oriented in such a way as to be extracted from the housing (32) in a direction (D1) directed from said rear end (26) of the fuselage (22) toward said front end (24) of the reusable orbital vehicle (14).

The invention relates to the technical field of spaceflight, and particularly discloses a satellite combination structure and a satellite launching control method. The satellite combination structure comprises a first satellite and at least two second satellites; the second satellites are arranged on the same side of the first satellite side by side, the second satellites are connected with the first satellite through separation mechanisms, and every two adjacent second satellites are connected through a separation mechanism; the first satellite comprises a propelling system and a first force bearing structure, the propelling system comprises a main propeller and a fuel tank, the fuel tank is located in the first force bearing structure, and the main propeller is connected to the outer side of the bottom of the first force bearing structure. Therefore, complex structures such as an upper stage or a propulsion power cabin do not need to be additionally arranged, under the condition that the satellite function and the on-orbit deployment condition are guaranteed, the carrying capacity is effectively saved, new space junk is avoided, meanwhile, the satellite launching cost is saved, and the system construction cost is reduced.

To provide a system, apparatus and method for a satellite thermal enclosure.SOLUTION: A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle, and the shroud 200 includes a frame 210 supporting a flexible thermal blanket 212 enclosing the satellite.SELECTED DRAWING: Figure 3

Provided is a core material that may be smoothly produced as a result of improvements in the texture and strength of the base material thereby having excellent light weight property and strength. The present invention is a core material having a structure including a collective body of hollow columnar cells compartmentally formed by cell walls. The cell walls include a sheet material in which discontinuous reinforcing fibers (Cf) are dispersed in a form of monofilament.

A device comprises a tube with a tube HTS solenoid, wherein a projectile in a sabot comprising a sabot HTS solenoid. A method comprises disposing a seed HTS crystal on a growing crystal in contact with an a-b plane of the seed HTS crystal to grow the growing crystal, wherein the a-b plane is perpendicular to a c-axis. A method comprises disposing a seed HTS crystal on a growing crystal in contact with a b-c plane of the seed HTS crystal to grow the growing crystal, wherein the b-c plane is perpendicular to an a-axis. A device comprises a reinforced HTS material in a graphene casing, wherein the HTS in the graphene casing includes a cooling channel and a return channel.

A propulsion-based payload transporter (PPT) and methods of its operation are provided. The PPT may operate in a gravitational field such as that on the lunar surface. Via rocket engines that produce thrust, the PPT is configured to descend onto and over a payload to be moved. Once in position with respect to the payload, latches engage with the payload so as to secure the payload in a payload holding bay of the PPT. The rocket engines produce thrust with an exhaust plume that is angled away from the payload to avoid payload damage. The rocket engines, which are located at the sides of the payload holding bay, produce thrust to propel the PPT and the payload in a substantially horizontal trajectory with respect to gravity and toward a landing destination.

The invention relates to the area of space science, in particular, to the area of industrialization of outer space and, directly, to the facilities for inserting and moving various objects in circumplanetary cosmic space. It is intended to solve geocosmic problems in industrial-scale volumes - to carry out research and development, special-purpose, touristic and other types of works and services in outer space and stabilize global climate. Artificial orbital ring complex by Yunitski is made in the form of a ring satellite (1), located in a circular orbit (5) around a natural cosmic body (2) in the equatorial (4) plane (3), which comprises: structural frame (7), utilities (8) and communications (9), power units (10), transition galleries (11) positioned in annular housing (12) with protective shell (13), gate chambers (14) with docking units (15), configured to dock with space vehicles (16), residential (19) and research-production (20) units, equipped with systems of control, life support, active and passive (17) protection against the harmful effects of space (18). The structural frame (7) is longitudinally tensioned, and the ring satellite (1) is in circular motion in orbit around the natural cosmic body (2) with velocity V0, m / sec, defined by the ratio: 1≤V0 / V1H≤1.01, where V1H, m / sec, - first space velocity for the equatorial circular orbit of the location of the ring line connecting the centers of mass of the cross sections of the artificial orbital ring complex, at altitude of H0, m, defined by the ratio: 0.02≤H0 / R0≤0.5, where R0, m, - radius of natural cosmic body (2) in equatorial (4) plane (3).

This invention is embodied in a system and device for transporting assets (small satellites, commodities, or other payloads) in space. The preferred system comprises a scaffold of relay stations strategically orbiting one or more celestial bodies. The orbits are complimentary to each other so that the relay stations can transfer mass from one station to another. In this way, the system can support different logistical networks connecting the space between orbits such as Low Earth orbit (LEO), geostationary orbit (GEO), and Low Lunar orbit (LLO), and even between Earth and Mars.

The invention relates to a method for manufacturing a cylindrical, thermoplastic composite part, the method comprising: - positioning a cylinder (3) made of thermoplastic pre-impregnated fibrous material in a vacuum moulding tooling (10), at least one vacuum bag (12) being situated facing the cylinder, and - consolidating the cylinder in the vacuum moulding tooling, during which a vacuum is drawn so that the at least one bag applies a shaping pressure to the cylinder, the cylinder being subjected to a heat treatment comprising (i) sweeping (B) its circumference with a local heating, of extent (E24) limited to a sector of the cylinder, in a relative movement in relation to the cylinder about its axis, and (ii) cooling, after this local heating, so as to fix the shape of the cylinder. Fig. 1

The present invention is embodied in systems and devices for transporting assets (small satellites, goods, or other payloads) in outer space. A preferred system comprises a scaffold of relay stations strategically orbiting one or more celestial bodies. Since the orbits are complementary to each other, the relay stations can transport mass objects from one station to another. In this way, the system can support various logistics networks connecting space between orbits such as low Earth orbit (LEO), geostationary orbit (GEO), and low lunar orbit (LLO), as well as space between Earth and Mars.

The invention provides a flat plate satellite mixed stacking layout structure and a releasing method, and the layout structure comprises a large flat plate satellite and a small flat plate satellite; the small flat satellites are stacked and placed in a supporting cabin of the rocket to form a first vertical layer; each layer of the first vertical layer comprises two small-sized plate satellites which are laid flatly; the large flat plate satellites are stacked at the top end of the first vertical layer to form a second vertical layer; the two side faces, away from each other in the tiling direction, of the two small flat plate satellites of each layer of the first vertical layer are aligned with the two corresponding side faces of the large flat plate satellite respectively. By means of the layout structure, efficient utilization of the space of the fairing can be achieved.

The invention relates to a transport system (1) intended to be installed on a space launcher (100) comprising:an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended to receive a passenger which is movable in rotation about an axis (0) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4);a passenger interface for each at least one seat (4) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed relative to said at least one seat (4);a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed on the at least one seat (4) from the acceleration of said at least one seat (4), the control unit (6) being configured to monitor the rotation of the at least one seat (4) during the operation of the transport system (1) in order to maintain the position of the seat (4) fixed relative to the load factor experienced by the passenger throughout the flight.

Orbital Elevator with Magnetic Rail Propulsion System: The invention relates to an orbital elevator designed to transport payloads between Earth and geostationary orbit. The system uses an ultra-strong, multi-strand cable made of carbon nanotubes to withstand gravitational and centrifugal forces. A transport module (climber) equipped with magnetic rails is in continuous contact with the cable, enabling stable, frictionless propulsion and precise control of movement along the cable. An integrated emergency braking system allows the climber to be stopped if necessary, thus enhancing transport safety. The ground base, which anchors the cable, includes a control center to monitor the movement of the modules and maintain structural tension. An orbital counterweight completes the system, stabilizing the cable through dynamic equilibrium.

A satellite assembly and apparatus for transporting a satellite into space are disclosed. The satellite assembly includes a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame that supports a flexible blanket that encloses the satellite.

A spacecraft (100) for functioning as an upper rocket stage (second stage or third stage) of a rocket during launch and as an orbital space station in orbit is disclosed The spacecraft (100) includes a payload section (Z3) have a plurality of modules adapted to facilitate orbital operation of the spacecraft (100). A central zone includes a compartmentalized tank module operationally coupled to the payload section (Z3). The central compartmentalized tank module having a plurality of compartments (7) adapted to store propellants during launch, transition into pressurized habitable compartments suitable for habitation and storage after venting and purging of residual propellants. A propulsion zone (Z1) is adapted to provide thrust during ascent and is adapted to detach from the central compartmentalized tank module upon achieving orbit.

Described are methods and systems for single-board satellite architectures.

The invention relates to a multi-satellite stacking system. The multi-satellite stacking system comprises a rocket adapter and a plurality of satellites which are sequentially stacked on the rocket adapter and locked by a release device. The release device comprises a locking part and an ejection part, the locking part comprises a first locking piece and a second locking piece which are movably connected, the first locking piece and the second locking piece are tensioned by a releaser, the first locking piece is hinged to the rocket adapter, the top end of the second locking piece presses the end face of the topmost satellite, and after the releaser releases, the second locking piece moves towards the topmost satellite through a first elastic piece to be unlocked; the ejection part is movably connected with the rocket adapter and pre-presses the first locking piece through the second elastic piece, and after the second locking piece is unlocked, the ejection part ejects the first locking piece through the second elastic piece. The multi-satellite stacking system disclosed by the invention has very high engineering implementation value, the unlocking and ejection processes of the release device are precisely connected, the release clamping stagnation of the multi-layer satellites is avoided, the safety of satellite release is improved, and the multi-satellite stacking system has the advantages of high compression rigidity, light weight, high bearing capacity, reliable separation and the like.

The integrated ultra-low orbit constellation carrier platform comprises an air inlet cabin section, a middle cabin section and a tail cabin section, the air inlet cabin section comprises an air inlet, the middle cabin section comprises a radio frequency ionization chamber, an electric control solid propeller storage cabin and a satellite storage cabin, the tail cabin section comprises a magnetic jet acceleration pipe, a propellant supplement mechanism and an electric control solid rocket upper stage, the air inlet, the radio frequency ionization chamber and the magnetic jet acceleration pipe are connected to form an air-breathing electric propulsion system of the carrier platform. The satellite is connected with the corresponding electric control solid rocket upper stage in a launch channel. In the satellite transportation into orbit networking stage, the electric control solid rocket upper stage carrying the satellite is ejected from the cabin, the electric control solid rocket upper stage uses electric control solid propellant as a propellant working medium and can be repeatedly ignited and started, after reaching a target orbit, the satellite is separated from the electric control solid rocket upper stage and is unfolded and networked by itself, and the electric control solid rocket upper stage returns to the carrier platform for fuel supplement by relying on the remaining fuel, and is ready to start the next satellite transportation task.

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.

This invention discloses a low-impact ejection mechanism for the release and recovery of tethered satellites, comprising at least one ejection assembly. The ejection assembly includes a satellite sub-satellite, an ejection module, a locking module, a tether deployment / retraction module, and a velocity limiting module. This invention enables the ejection, release, and recovery locking of the satellite sub-satellite, can be repeatedly used in ground simulation experiments for the release and recovery of tethered satellites, and facilitates the adjustment of the satellite sub-satellite's attitude for successful recovery. This invention can eject the satellite sub-satellite at a certain velocity without generating significant resistance during recovery and locking, and can autonomously and repeatedly conduct ejection-recovery experiments through a control system. The velocity limiting module can automatically lock according to a set acceleration value to avoid impact during satellite release.

The invention relates to an arrow blocking mechanism capable of achieving movable filling and on-orbit self-locking positioning and an application method, and belongs to the technical field of spaceflight launch, the mechanism comprises an outer threaded sleeve, a moving body, a bearing, a sliding block, a guide sleeve, a seat ring, a fastening jackscrew, a thrust washer, an inner threaded rod and a hand wheel, the mechanism integrates the three functions of carrier filling, positioning and erecting and arrow blocking, and the structure is simple. A heavy arrow pulling device is omitted, and the method specifically comprises the steps that 1, horizontal rail injection filling of the carrier is achieved; 2) the carrier is ensured to be positioned and self-locked on the rack, so that the butt joint between other mechanisms and electromechanical interfaces is reliable; and (3) during launching, the arrow is reliably positioned and blocked, launching vibration impact is borne, a certain guiding effect is provided for the carrier, the whole force transmission part is designed in the orientator body, the motion is reliable, the safety is higher, and mechanical potential safety hazards caused during loading of the carrier and test launching are avoided.

A rocket propulsion and satellite deployment system, comprising a rocket comprising at least a base sector, an operating sector, and a transport sector; the base sector comprises a propellant and is configured to transport the sectors to a mission target; the operating sector comprises a rotating robotic arm pivoted to the operating sector; the transport sector is configured to hold a load intended to be delivered to the target by means of a rotation of the rotating robotic arm with respect to the operating sector, accelerating the load itself which is subsequently released in a direction opposite to the speed of the rocket, increasing, due to conservation of momentum, the speed of the rocket itself. The system is based on a so-called 'useful propellant', consisting of the satellites, rovers and orbiters themselves, which, through the rotational acceleration system, are used to increase the speed of the rocket in space. As well as providing an alternative to traditional propulsion, this system provides an innovative way of putting satellites into orbit, especially in non-earth orbit, which can also be used for longer missions with more than just one target.

A debris removal satellite (300) includes a capture device (135), a thruster (341) of a chemical propulsion method, and a propellant tank (342) to store chemical fuel. A solar array wing (371) is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite (300) is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite (300) captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device (134) with the capture-target debris being captured, so as to prevent the capture-target debris from intruding into the congested orbit region.

A propulsion-based payload transporter (PPT) and methods of its operation are provided. The PPT may operate in a gravitational field such as that on the lunar surface. Via rocket engines that produce thrust, the PPT is configured to descend onto and over a payload to be moved. Once in position with respect to the payload, latches engage with the payload so as to secure the payload in a payload holding bay of the PPT. The rocket engines produce thrust with an exhaust plume that is angled away from the payload to avoid payload damage. The rocket engines, which are located at the sides of the payload holding bay, produce thrust to propel the PPT and the payload in a substantially horizontal trajectory with respect to gravity and toward a landing destination.

The present technology is directed to thrusting rails for launch vehicles, and associated systems and methods. Certain embodiments of the thrusting rails can include a first rail housing portion having a cavity and a second rail housing portion having a projection positioned at least partially within the cavity. The rails can include a bellows positioned within the cavity and an elongated tube positioned within the bellows. The elongated tube can include a vent opening in a lateral wall of the elongated tube. A shield can be positioned between the vent opening at the bellows and a sleeve can be positioned within the elongated tube. The sleeve can be constructed from a fibrous material and positioned to retain an ordnance within the elongated tube.

A power supply unit for a launch vehicle is disclosed. The power supply unit comprises a protective housing and, within the housing, a control module and a battery holder configured to receive a plurality of replaceable lithium-ion battery cells. The control module comprises a power switching and distribution module, and a battery management and monitoring system module. The power supply unit has several advantages including improved safety, and reduced size and weight.