201results about "Launch systems" patented technology

Systems and methods for providing a space launch service platform (SLSP) that integrates artificial intelligence and data analytics to support launch operations. The SLSP may connect to multiple data sources, collect data, and standardize the collected data according to regulatory and operational standards. The SLSP may evaluate launch safety and risks using standardized data and generate a situational analysis for decision-making. The SLSP may provide graphical overlays and decision-support tools to highlight optimal launch windows and potential risks.

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.

Stackable satellites with a large diameter antenna that are configured to stack within each other like fully overlapping shallow bowls and to fit tightly within the area in a pay load fairing. The bowl-shaped satellites allow the satellites to nest within each other so that many satellites can be stacked within the height limits of the launch vehicle pay load fairing. A cradle is used to hold the stack, and tensions cables keeps the satellites in compression during launch. The satellite is an antenna with the bus integrated into the antenna structure. The antenna occupies the entire diameter / footprint of the satellite and thus can be matched up with the cross section of the fairing. This allows the largest possible antenna size to be launched without a complex deployment mechanism.

The invention relates to the technical field of spaceflight launching, and provides a swarm-type spaceflight launching system and method, and the system comprises a honeycomb system, a nectar source system, and a bee passage system. The honeycomb system is a technical area for spaceflight launching, is connected with the nectar source system through the bee passage system and is used for completing a satellite-rocket combination; the plurality of nectar source systems are arranged around the honeycomb system, and each nectar source system comprises a plurality of emission positions; the bee passage system is connected with the transmitting position and the honeycomb system and comprises a plurality of traffic roads. According to the scheme, a large number of satellites with different orbits can be launched in a short time, and the satellite launching efficiency is improved.

A system and method are disclosed for softly capturing, protecting, and landing a spacecraft returning from space using a VTOL (vertical takeoff and landing) aircraft including drones and helicopters. The spacecraft is decelerated by a parachute. One or more VTOL drones transport a waterproof pocket that catches and captures the descending spacecraft in the air. In this way, the spacecraft is protected inside the pocket and, after continuing to descend, makes a soft landing in a body of water. In another embodiment, a recovery helicopter, which is a type of VTOL aircraft with heavy-lift capabilities, is used to directly catch the returning spacecraft. One or more VTOL drones are attached to the lower end of a recovery cable suspended from the helicopter. These drones carry a clutch that directly, quickly, and accurately catches the descending spacecraft without interfering with the parachute. In this way, the spacecraft is caught and protected by the helicopter while maintaining the floating function of the parachute.

A controlled reactor comprises a reactor core thermally coupled to one or more heat pipes and an active cooling loop. A fluid may be circulated through the active cooling loop. A heat exchanger is thermally coupled to the active cooling loop and extracts heat from the fluid as the fluid is circulated through the active cooling loop. A heating system may be provided to deliver the heat extracted by the heat exchanger to a community. A thermoelectric generator may be provided to convert heat extracted by the heat pipes to electricity for delivery to the community.

A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.

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.

Systems and methods using VTOL (vertical take-off and landing) aircrafts including drones and helicopters for soft capture, preserving, and landing of a returning spacecraft from space are disclosed. The spacecraft is decelerated by parachutes. One or multiple VTOL drones transport a water impermeable pocket meeting and capturing the descending spacecraft in the air. The spacecraft is thus preserved inside the pocket and keeps descending and then softly lands in a body of water. In another embodiment, a recovery helicopter, one type of VTOL aircraft with heavy payload lifting capacity, is used to directly catch the returning spacecraft. One or multiple VTOL drones are coupled to the bottom end of a recovery cable hung from the helicopter. These drones bring a clutch quickly and precisely catching the descending spacecraft directly without interrupting the parachutes. The spacecraft is thus caught and preserved by the helicopter with lifting function of the parachutes maintained.

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.

A reusable payload module (2; 2') as part of an upper stage (12) of a space rocket (1) is provided with a fairing (20A) which, when the payload module (2) is closed, surrounds a payload receiving space (21) and forms an outer shell (20; 20') of a fuselage (29) of the payload module (2; 2'), which is rotationally symmetrical to a payload module longitudinal axis (XN) which runs coaxially with or parallel to a longitudinal axis (XR) of the space rocket (1), and is characterized in that the fairing (20A) forming the outer shell (20; 20') has at least two surface sections (23, 24) which can each be pivoted outwards about a pivot axis (X23, X24).

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 present invention relates to a system and method of mobile orbital launchers. The mobile launcher of the present invention mainly consists of the launch vehicle and launch related subsystems. All the systems will fit on a trailer which is capable of going anywhere via road or sea. It will carry the vehicle in a horizontal position and after reaching the required location, it will articulate and make the vehicle vertical to get ready for launch. The system and method of the present invention have all the subsystems which enable the launch without any hindrance.

Method for synchronized sequencing of takeoff of a space launcher comprising one or more on-board computers, a plurality of on-board fluidic equipment including a propulsion system, and a plurality of on-board electrical equipment, this method being implemented in the on-board computer(s) and comprising reversible steps of control / command of the fluidic equipment and reversible steps of control / command of the electrical equipment, said reversible steps of a respectively electrical and fluidic nature being followed respectively by an irreversible step of starting a flight sequence and an irreversible step of starting the propulsion system of the launcher. The reversible steps of control / command and the irreversible steps of start are directly controlled by the on-board computer(s) of the launcher. See Figure 2

An autonomous flight safety system (AFSS) is described that incorporates an autonomous flight termination unit (AFTU) that enables AFSS monitoring of various termination conditions, for example, used to activate a flight termination system if a termination condition is detected. Such termination conditions include boundary limit detection (e.g., whether the vehicle position is outside or protruding outside of a planned flight envelope), as well as body instability detection (e.g., whether pitch and yaw rates exceed some threshold indicating vehicle instability). For example, the AFTU may incorporate a three-axis gyroscope sensor and implement an instability detection process based on information obtained via the sensor. The instability detection process may include, for example, a BID algorithm that may be implemented by the AFTU to monitor the vehicle's angular velocity, to determine if the vehicle is no longer under stability control, and to issue a termination command when a termination condition is detected.

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 reserve satellite cluster including a plurality of satellites stands by at an orbit altitude lower than an orbit altitude of a steadily operated satellite cluster in a satellite constellation. In a case where a satellite configuring the steadily operated satellite cluster has been lost, a satellite, existing around a lost orbital position that is an orbital position where a satellite has been lost in the steadily operated satellite cluster, among satellites configuring the reserve satellite cluster is injected into the lost orbital position in an orbit.

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.