70results about "Launch systems" patented technology

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).

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 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).

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.

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.

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

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.

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.

The motorized launch system includes a vehicle having at least one electrically conductive coil arranged to interact with at least one ultra-high conductivity material track in the guide rail when the vehicle is moved through the guide rail. The drive device drives the vehicle at a speed at which a current is induced in the track, the current being sufficient to suspend the vehicle and to inhibit the vehicle from colliding with the guide rail and the track by electric suspension when the vehicle is moving along the track, and drives the vehicle at a firing speed to launch the vehicle from the guide rail. The firing speed is at least as high as the first speed. The controller controls the release mechanism to release the payload from the vehicle to launch the vehicle from the rail while the at least one drive device drives the vehicle at the launch speed.

“Space launcher equipped with an auxiliary propulsion system and auxiliary propulsion system equipping a space launcher” Space launcher (1) comprising a first stage equipped with a first propulsion system dedicated to the intra-atmospheric flight phase of the launcher and a second stage (E2) designed to receive a payload, comprising a main engine (10) and an auxiliary propulsion system (APS) integrating two auxiliary propulsion units (APUs) (13, 16) and a set of reaction control thrusters (RCS) responsible for attitude control of said second stage during the extra-atmospheric flight phase of the launcher. See Figure 1

A spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. According to one example, a spacecraft docking station may include a frame enclosing an area, and a net-like mesh coupled to the frame and filling the area enclosed by the frame. An autonomous robot may be coupled to the net-like mesh. One or more vessels may be coupled to the frame and / or the net-like mesh, where the one or more vessels include a propulsion mechanism. Other aspects, embodiments, and features are also included.

Disclosed are a toroidal tank (1) for a vehicle, wherein the toroidal tank (1) is designed as a bladder (6,8) tank for the storage of bi-propellant, and a space vehicle.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing 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 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 captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing 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 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 captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

The present invention relates to an engine (2) for applying a change in velocity, in magnitude and / or direction, to a spacecraft (1), in particular for deorbiting the spacecraft, wherein the engine is designed as a solid-propellant rocket engine with a solid propellant (24) and the engine is designed and configured such that the engine remains operational under space conditions predefined for the mission of the spacecraft at least until the end of a predefined operational period (100) of the spacecraft or at least during a predefined, substantial part (204) of a mission duration (200) of the spacecraft. The invention further relates to a spacecraft comprising such an engine.

A method for producing a spacecraft structure includes launching from Earth into a space environment a partially manufactured form of a spacecraft structure, and extruding the partially manufactured form into an extruded spacecraft structure, the extruding taking place in a zero gravity condition in the space environment.

A launch vehicle with a rocket body having a longitudinal axis which has at least one propulsion stage which can be driven by a reaction propulsion system acting predominantly parallel to the longitudinal axis, wherein the launch vehicle is provided with a plurality of rotors which can be driven by means of a respective rotor drive and whose respective rotor axis is aligned substantially parallel to the longitudinal axis of the rocket body, is characterized in that a separate takeoff stage is provided which is coupled or can be coupled to the rocket body and / or the propulsion stage, which is coupled to or can be coupled to and decoupled from the separate takeoff stage, which has the plurality of outer rotors, in that the outer rotors are arranged in the manner of a multi-copter radially outside the rocket body and surrounding the rocket body.

A rocket assembly including a main housing extending from a first end to a second end and having a longitudinal axis between the first and second ends. A plurality of tubes, extending from a first end to a second end, with the second end of each tube connected with the first end of the main housing. At least a subset of the plurality of tubes are pivotal relative to the main housing from a first orientation wherein a longitudinal axis of the tube is substantially parallel with the main housing longitudinal axis and a second orientation wherein a longitudinal axis of the tube is substantially parallel with the main housing longitudinal axis.

A method for producing an HTS crystal 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. Another method for producing an HTS crystal 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.

This application relates to a stacked satellite mass launch system, belonging to the field of satellite technology. It includes a mounting base pressure rod and multiple satellites stacked on a mounting base. A positioning assembly is provided between adjacent satellites. The positioning assembly includes a positioning post and a sleeve. The positioning post is fixedly disposed on the bottom wall of the satellite, and the sleeve is fixedly disposed on the top wall of the satellite, for inserting the positioning post to define the position of adjacent satellites. A first elastic element is provided inside the sleeve for driving the positioning post out of the sleeve. The pressure rod is hinged to the mounting base and has a clamping assembly for applying clamping force to the satellites. When the satellites separate, the clamping assembly unlocks, and under the action of the first elastic element, the upper-layer satellite is pushed, causing the positioning post to disengage from the sleeve, at which point the upper-layer satellite can be unlocked and separated.

A device for launching a projectile, comprising a chamber (1) provided with a side wall (7) and an ejection window (4). An arm (2) is rotatably mounted about a shaft (3) in the chamber (1). A shoe (8) is attached to the arm (2) and receives the projectile (5). The shoe (8) moves circularly in the chamber (1). The shoe (8) comprises a nozzle (10) connected to a source of a first gas (11), for ejecting a flow of first gas and causing the shoe (8) to advance inside the chamber. The side wall (7) defines a track (12) supporting the shoe in a radial direction (ZZ). The track (12), the shoe (8) and a second gas define an aerodynamic bearing between the track (11) and the shoe (8) so that the track (12) reacts at least part of the forces of the shoe (8) in the radial direction (ZZ).