19results about "Cosmonautic ground equipments" patented technology

The invention is notably directed to an aircraft carrier ground vehicle (10), which comprises a chassis (102), a landing platform (104), a coupling mechanism (106), and an actuation mechanism (108). The landing platform is designed to accommodate an aircraft (20). The coupling mechanism connects the landing platform to the chassis to form a kinematic pair, in which the landing platform is rotatably mounted on the chassis. The actuation mechanism is adapted to rotate the landing platform relative to the chassis, to allow an aircraft to land on the landing platform as the vehicle moves along a landing direction of the aircraft and compensate for an inclination angle of the aircraft on landing, in operation. The aircraft carrier ground vehicles may further be designed to allow taxiing and take-off of the aircraft. The invention is further directed to related aircraft carrier ground vehicle systems, which include several vehicles that are swarmed for landing an aircraft, as well as aircraft landing and take-off methods.

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 application relates to a detachable guide rail type launch vehicle pre-launch heating and keeping warm device, which comprises a detaching mechanism and a heating and keeping warm mechanism; in a storage state, the detaching mechanism and the heating and keeping warm mechanism are independent of each other and are stored separately; in a heating working state, the heating and keeping warm mechanism is lifted by the detaching mechanism, and the heating and keeping warm mechanism heats and keeps warm the vehicle; and in a launch separation state, the detaching mechanism takes the heating and keeping warm mechanism away from the guide rail type launch device of the guide rail type launch vehicle, so that the vehicle can normally leave the rail. The application can ensure normal heating and keeping warm functions before and after the small and medium-sized vehicle is erected, and can make the heating and keeping warm device reliably detach through manual or electric ways 5 minutes before the vehicle is launched, so that the normal launch of the vehicle is not affected.

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 application discloses a kind of transport, erecting and self-adaptive leveling integrated equipment for small spacecraft, including carrying chassis, erecting mechanism, self-adaptive leveling platform and intelligent control system.Carrying chassis is used to execute transport and parking locking;Intelligent control system is based on launch site surveying and mapping and ideal vertical attitude model, constructs optimal kinematics solution matrix;Data fed back using multidimensional inclination sensor are used to carry out forward reasoning, drive self-adaptive leveling platform to complete coarse leveling;In the process that spacecraft is erected to vertical state by erecting mechanism, based on control error function and PID algorithm closed loop adjustment platform parameter, realize dynamic accurate leveling.The application solves the problems of low efficiency, easy to produce coupling interference and poor environmental adaptability of traditional split type equipment, realizes high-precision automatic collaborative control for complex field terrain, and greatly shortens the launch preparation period.

This invention discloses a propellant venting connector docking and locking device for venting propellant from a rocket being recovered and suspended from a robotic arm on a launch tower. The docking and locking device includes an installation platform; an installation plate driven by a first drive mechanism to rotate vertically on the installation platform; multiple rocket-holding mechanisms evenly distributed circumferentially on the installation plate, driven by a second drive mechanism to synchronously move radially toward each other towards the center and synchronously move radially away from each other towards the center; multiple rocket-bearing mechanisms evenly distributed circumferentially on the installation plate to support the rocket; an industrial robot is installed on the installation plate, and a connector is provided at the end effector of the industrial robot. The connector is driven by the industrial robot to dock with the rocket's venting port and is used to vent the propellant. This invention can effectively reduce the safety risks to personnel involved in the handling of rocket propellant after recovery and improve the efficiency of propellant venting and handling.

Systems and methods disclosed herein are for determining a pre-launch center of gravity (CG) of at least one component of a launch vehicle which may be subject to shifts or changes in CG after launch. The systems and methods may include a tool with an adapter base which may be configured to attach to the component and may include counterweights or segmented weights. The tool may be hoisted with the component for first CG measurements and may be hoisted independently of the component for second CG measurements. The first and second CG measurements may be used to determine the CG of the component of the launch vehicle.

The application provides a kind of offshore aerospace launch and recovery ship power positioning fault-tolerant anti-interference method, belongs to offshore aerospace launch and recovery ship automatic control technical field;The method of the application is mainly oriented to the research of offshore aerospace launch and recovery ship power positioning control considering unknown external marine environment interference and mixed faults of thrusters, uses interference observer and bias fault observer and multiplicative fault adaptive observer, solves the online estimation and inhibition of unknown external marine environment interference on offshore aerospace launch and recovery ship power positioning and the estimation and compensation problem of mixed faults of offshore aerospace launch and recovery ship thrusters;By using a composite fault-tolerant anti-interference controller to correct the tracking feedback control error problem, effectively enhance the anti-interference ability of offshore aerospace launch and recovery ship, improve the reliability of offshore aerospace launch and recovery ship control, so that the expected position of offshore aerospace launch and recovery ship reaches the expected effect.

The objective is to safely recover the rocket that has descended into orbit after satellite separation, and to reuse the recovered rocket. [Solution] A rocket is launched from a rocket launch site located between 30 and 50 degrees latitude, and a rocket recovery method is used to recover the rocket, which has descended into orbit after satellite separation, in an area different from the rocket launch site. The recoverable rocket 202a is equipped with an atmospheric deceleration device, and the recoverable rocket 202a recovered by the above rocket recovery method is transported to the rocket launch site by a reusable rocket transport means. The rocket launch site then performs a rocket launch method to launch the recoverable rocket again.

This invention provides a transport and assembly device with gravity unloading function. Four gravity unloading units are installed on the transport vehicle. Each gravity unloading unit includes a planar air-bearing support mechanism, a support column, a vertical hydraulic cylinder, and a spherical air-bearing support mechanism. These four gravity unloading units support the loading platform. The operator manually drives the loading platform to perform six degrees of freedom of position adjustment, bringing the assembly to the target assembly position. During position adjustment, the planar air-bearing support mechanism provides translational and rotational degrees of freedom around the vertical axis. The four vertical hydraulic cylinders and the spherical air-bearing support mechanism above them provide tilting freedom in any direction and vertical movement freedom, while also providing support force to counteract the gravity of the loading platform and its load. This allows the operator to drive the loading platform to adjust its position with only a small operating force.

The present application relates to propellant transfer equipment technical field, specifically for a kind of rocket propellant transfer pipeline automatic docking device and control method, to solve the problems of traditional propellant transfer pipeline manual docking low efficiency, poor precision, and there is propellant leakage security risk, specifically includes: movable base, plug removal unit, joint docking unit, positioning detection unit, interface sealing unit and controller.The present application realizes the accurate identification and positioning of target by positioning detection unit, three-dimensional mechanical arm drives plug removal unit and joint docking unit, realizes the automatic removal of transfer port plug and the automatic docking of propellant transfer pipeline, and interface sealing unit detects the sealing performance of docking.The present application does not need manual intervention, and the docking efficiency is more than 5 times higher than manual, suitable for aerospace, chemical and other fields high-risk, high-purity propellant transfer scene requiring.

A test device (1) for testing vibration effects on moving components (5) is described, wherein the test device (1) has a linear drive unit with a rail (2) extending in a longitudinal movement direction (LB) and a slide (3) mounted linearly movable on the rail (2) and a control unit (9) designed for controlling the test device (1). The linear drive unit has an electromagnetic or electrodynamic drive actuator and is designed to move the carriage (3) on the rail (2), wherein the linear drive is configured for superimposed low-frequency and high-frequency acceleration and deceleration of the carriage.

The application discloses a telescopic rocket recovery tower and relates to the technical field of rocket recovery, aiming to solve the problem that the prior art cannot be flexibly adjusted according to the height requirements of different models of rockets and can only be adapted to single or a few rockets of the same height specification. The device comprises a primary tower, a secondary tower, a main hydraulic lifting driving mechanism, a transverse hydraulic driving mechanism, a mechanical arm and a control assembly. The main hydraulic lifting driving mechanism is installed in the middle of the primary tower base, the telescopic end of the main hydraulic lifting driving mechanism is provided with multiple layers of transverse hydraulic driving mechanisms in the circumferential direction, and the telescopic end of the transverse hydraulic driving mechanism is connected with the secondary tower. The height of the secondary tower is coarsely adjusted through the main hydraulic lifting driving mechanism, the width of the tower is adjusted through the transverse hydraulic driving mechanism, the recovery requirements of different models of rockets can be flexibly adapted, and the device has the advantages of stable structure, high adjustment precision, high automation degree and wide adaptation range.

A multi-launcher space launch assembly includes a movable platform for the assembly, transporting, and vertical positioning of varied launchers. The platform cooperates with a fixed table and a jet deflector, which are situated in a launch area. The infrastructure also includes adaptable fluid refuelling modules compatible with various flow and pressure profiles. The system is adapted to accommodate variations in the height and diameter of launchers by way of modular components.

This invention provides a propellant refueling connector and refueling device, including a connector body, a fixed frame on the outside of the connector body, a movable frame in front of the fixed frame, a cylinder, and a hook. The movable frame is axially movable. The cylinder body is connected to the fixed frame, and the piston rod is connected to the movable frame. The front end of the hook extends out of the front end of the connector body, and the rear end is hinged to the fixed frame via a first hinge shaft and also hinged to the movable frame via a second hinge shaft, with the second hinge shaft located outside the first hinge shaft. An elastic device is provided between the fixed frame and the movable frame, and the elastic device is sleeved on the outer periphery of the piston rod. In this technical solution, a flange-shaped movable frame is provided on the refueling connector, which drives the hook to move. An elastic device is added between the movable frame and the fixed frame. During the refueling process, even if the air path that drives the piston rod to extend malfunctions, the elastic force of the elastic device can still ensure that the connector and the refueling port are properly locked and sealed, ensuring the normal operation of the refueling.

This invention discloses a hydraulic control system and control method, belonging to the field of aerospace technology. The hydraulic system includes a hydraulic power unit integrated within a container, comprising a hydraulic oil tank, a motor pump group, a safety valve group, and a flow divider valve group. An erection control unit is connected to an erection cylinder for erection and leveling. A leveling control unit is connected to a launch pad leveling cylinder for lifting and leveling. A tilting control unit is connected to a tilting cylinder. An accumulator is connected to the inlet of the tilting control unit, used to supply oil to drive the tilting support to avoid obstacles after receiving a takeoff command. The return ports of each control unit are connected to the hydraulic oil tank. The control method includes erection, leveling, accumulator pressurization, rapid tilting, and erector frame leveling steps. This invention uses a container-integrated hydraulic power unit to achieve mobile launch without reliance on external support; the flow divider valve group supplies oil independently, ensuring no interference between units; the accumulator instantaneously releases oil to drive the tilting support to quickly avoid obstacles, resulting in fast response, high reliability, and easy rapid deployment and withdrawal.

Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process.

The application provides an assembly process of a spacecraft, and belongs to the technical field of spacecraft production and assembly. The application solves the technical problem of low efficiency of the existing assembly process of the spacecraft. The assembly process of the spacecraft comprises the following steps: cabin plate subassembly: installing and fixing functional elements on corresponding +Z cabin plates, -Z cabin plates, +X partition plates, -X partition plates, +X cabin plates, -X cabin plates, +Y cabin plates and -Y cabin plates; pre-test assembly: sequentially combining the -Z cabin plates, the +X partition plates, the -X partition plates, the +Z cabin plates, the +X cabin plates and the -X cabin plates and forming assembly through connecting pieces; normal-pressure thermal cycle test: exposing the spacecraft after the pre-test assembly to a preset high-low temperature alternating test environment for test under normal-pressure conditions; cabin sealing and assembly: assembling the +Y cabin plates and the -Y cabin plates to the spacecraft after the normal-pressure thermal cycle test through connecting pieces. The assembly process of the spacecraft can improve the efficiency while ensuring the assembly quality of the spacecraft.