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3568 results about "Spacecraft" patented technology

A spacecraft is a vehicle or machine designed to fly in outer space. A type of artificial satellite, spacecraft are used for a variety of purposes, including communications, Earth observation, meteorology, navigation, space colonization, planetary exploration, and transportation of humans and cargo. All spacecraft except single-stage-to-orbit vehicles cannot get into space on their own, and require a launch vehicle (carrier rocket).

Temperature measurement and calibration platform in space vacuum environment

The invention relates to a temperature measurement and calibration platform in space vacuum environment. The temperature measurement and calibration platform is favorable for realizing the simultaneous calibration of contact type temperature measurement and non-contact type temperature measurement, so the temperature measurement and calibration platform is served for heat vacuum and heat balance experiments of spacecrafts such as satellites, spaceship and the like. The temperature measurement and calibration platform comprises a constant temperature bath, wherein a double-sub-cavity vacuum cavity, the double-sub-cavity vacuum cavity comprises a first vacuum cavity body and a second vacuum cavity body, the first vacuum cavity body and the second vacuum cavity body are connected with a vacuum pumping device through a three-way valve, standard temperature indicator sensors are respectively arranged on the outer wall of the first vacuum cavity body and on the outer wall of the second vacuum cavity body, the standard temperature indicator sensors are connected with a temperature secondary meter, a laser light path reflecting device is arranged in the vacuum cavity of the first vacuum cavity body for calibrating a non-contact type temperature measuring system based on the tunable diode laser absorption spectrum technology, and the vacuum cavity of the second vacuum cavity body is used for accommodating a temperature sensor for calibrating a contact type temperature measuring system adopting the temperature sensor.
Owner:BEIJING DONGFANG MEASUREMENT & TEST INST

Spacecraft assembly simulation technique-based virtual assembly system and virtual assembly method

InactiveCN101739478ASpecial data processing applicationsProcess designAssembly planning
The invention relates to a spacecraft assembly simulation technique-based virtual assembly system. The virtual assembly system comprises a CAD modeling module, a virtual assembly planning module and an assembly process design module, wherein the CAD modeling module is used for designing components and tooling tools, and assembling the components together by defining a series of matching constraint relations so as to obtain an assembling model of products; the virtual assembly planning module is used for establishing a geometrical constraint-based virtual environment, planning an optimized assembly sequence according to disassembly directions, disassembly tools and precedence constraint information recorded in the virtual environment for execution, verifying the optimized assembly sequence, and performing simulation evaluation in the virtual environment; and the assembly process design module is used for designing a product structure tree and a process step catalog, editing process steps and assembling a technological process. The CAD modeling module is connected with the virtual assembly planning module through a CAD modeling interface so that models generated in the CAD modeling module are guided into the virtual assembly planning module; and the process planning result in the virtual assembly planning module is guided into the assembly process design module through a Mockup interface.
Owner:BEIJING INST OF SPACECRAFT ENVIRONMENT ENG

Autonomously identifying and capturing method of non-cooperative target of space robot

The invention relates to an autonomously identifying and capturing method of a non-cooperative target of a space robot, comprising the main steps of (1) pose measurement based on stereoscopic vision, (2) autonomous path planning of the target capture of the space robot and (3) coordinative control of a space robot system, and the like. The pose measurement based on the stereoscopic vision is realized by processing images of a left camera and a right camera in real time, and computing the pose of a non-cooperative target star relative to a base and a tail end, wherein the processing comprises smoothing filtering, edge detection, linear extraction, and the like. The autonomous path planning of the target capture of the space robot comprises is realized by planning the motion tracks of joints in real time according to the pose measurement results. The coordinative control of the space robot system is realized by coordinately controlling mechanical arms and the base to realize the optimal control property of the whole system. In the autonomously identifying and capturing method, a self part of a spacecraft is directly used as an identifying and capturing object without installing a marker or a comer reflector on the target star or knowing the geometric dimension of the object, and the planned path can effectively avoid the singular point of dynamics and kinematics.
Owner:HARBIN INST OF TECH

Spacecraft attitude integral sliding mode fault tolerance control method taking consideration of performer fault

The invention relates to a spacecraft attitude integral sliding mode fault tolerance control method taking consideration of a performer fault and provides a robustness attitude active fault tolerance control method based on an integral sliding mode surface for problems of the performer fault, external disturbance and control moment amplitude limits in a spacecraft attitude control process. The method comprises steps that firstly, a spacecraft attitude dynamics model taking consideration of the performer fault and containing external disturbance is established; secondly, on the condition that a performer is not in fault, a designed nominal controller can guarantee system stability, and input saturation amplitude limits can be easily satisfied through adjusting controller parameters; lastly, the fault information is introduced to design an integral sliding mode controller, robustness of external disturbance and the performer fault can be effectively improved, system stability is analyzed on the basis of an Lyapunov method. The method is advantaged in that stability of the attitude control system is guaranteed when a spacecraft operating on orbit generates the performer fault, and relatively strong fault tolerance capability and external disturbance robustness are realized.
Owner:BEIHANG UNIV

Small-size spacecraft butt-joint mechanism

ActiveCN103625656AAchieve posture correctionPosture correction is easyCosmonautic component separationButt jointEngineering
The invention discloses a small-size spacecraft butt-joint mechanism, relates to a spacecraft butt-joint mechanism and aims at solving the problems that an existing small-size spacecraft butt-joint mechanism is fierce in collision, low in positioning precision, and large in control difficulty in the butt-joint process and unstable enough after butt-joint. A connecting sleeve and three arc-shaped enclosing plates are arranged between an upper driven disc and a lower driven disc; a first guide plate is arranged at one end of each arc-shaped enclosing plate; a second guide plate is arranged at the other end of each arc-shaped enclosing plate; the adjacent first guide plates and three second guide plates form a V-shaped positioning slot; three brackets are uniformly distributed between the upper drive disc and the lower drive disc along the same circumference; a stepped motor is fixed in the center of the lower drive disc; the stepped motor is connected with a lead screw; a threaded lifting disc is screwed on the lead screw; the lower end of each locking claw penetrates through a slide path and is hinged with the threaded lifting disc, and each locking claw is contacted with the surface of a roller; the upper end of each locking claw is arranged in the corresponding V-shaped positioning slot. The small-size spacecraft butt-joint mechanism disclosed by the invention is mainly used for capturing and butt-joint of a small-size spacecraft.
Owner:HARBIN INST OF TECH +1

System and method for performing 4-dimensional navigation

A system and method are disclosed for computing a vehicle's motion in four dimensions (e.g., three spatial dimensions and time) and reliably predicting the vehicle's arrival time at a predetermined location, by providing a graphical display to an operator of the vehicle's progress that enables the operator to adjust the vehicle's movement and achieve the desired arrival time. Specifically, a system and method are disclosed for computing the movement of an aircraft in four dimensions, predicting its arrival time at a predetermined waypoint, and displaying (in a highly intuitive format) the aircraft's progress in achieving that desired arrival time. The pilot can then adjust the movement (e.g., speed) of the aircraft in accordance with the parameter(s) displayed, in order to achieve the desired arrival time. Thus, for example, numerous aircraft could be scheduled to arrive at a specific final approach waypoint at a predetermined rate (e.g., one aircraft per minute), which would enable the traffic controllers to optimize runway traffic without having to stack the aircraft in holding patterns and thereby waste fuel. Notably, although an example of an aircraft navigation and control system and method is disclosed, the system and method can be implemented for any type of vehicle (e.g., aircraft, spacecraft, ship, submarine, bus, train, automobile, etc.) whose operator desires to reach a particular location at a specified time.
Owner:HONEYWELL INT INC

Different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method

The invention relates to a different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method. The different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method aims at solving the problems that the uncertainty of inertia of a spacecraft is not considered in the prior art, the convergence time can not be freely adjusted depending on the state initial value, and compensating moment generated in the singular direction of a flywheel needs to be designed artificially. The method comprises the particular steps that 1, a tracking satellite and a target satellite are supposed to be located on a different-surface crossover track, and the expected posture needs to be determined; 2, an expected posture tracking control rule is designed; 3, buffeting of the expected posture tracking control rule is eliminated; 4, the expected posture of the crossed points of the tracking satellite and the target satellite changes along with distance between the crossed points of the tracking satellite and the target satellite, a configuration scheme of an execution mechanism is determined according to the expected posture tracking control rule, and the expected posture control torque is solved. The different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method is applied to the field of satellite control.
Owner:HARBIN INST OF TECH

Autonomous integrated navigation system

The invention relates to an autonomous integrated navigation system which belongs to the technical field of navigation systems. The SINS (Strapdown Inertial Navigation System)/SAR (Synthetic Aperture Radar)/CNS (Celestial Navigation System) integrated navigation system takes SINS as a main navigation system and SAR and CNS as aided navigation systems and is established by the following steps: firstly, designing SINS/SAR and SINS/CNS navigation sub-filters, calculating to obtain two groups of local optimal estimation values and local optimal error covariance matrixes of the integrated navigation system state, then transmitting the two groups of local optimal estimation values into a main filter by a federal filter technology for fusion to obtain an overall optimal estimation value and an overall optimal error covariance matrix, and finally, performing real-time correction on the error according to the overall optimal estimation value so as to obtain an optimal estimation fusion algorithm of the SINS/SAR/CNS integrated navigation system. The autonomous integrated navigation system, disclosed by the invention, is less in calculation amount and high in reliability, is applicable to aircrafts in near space, aircrafts flying back and forth in the aerospace, aircrafts for carrying ballistic missiles, orbit spacecrafts and the like, and has wide application prospect.
Owner:NORTHWESTERN POLYTECHNICAL UNIV

Method for controlling rigid spacecraft for target attitude tracking

The invention relates to a method for controlling a rigid spacecraft for target attitude tracking, and belongs to the technical field of the high-precision and high-stability attitude tracking control of spacecrafts. The method solves the problem that when the attitude tracking spacecraft runs in a low orbit in outer space, the conventional control method cannot eliminate the inherent flutter of a sliding mode variable structure. The method comprises the following steps: 1, establishing a kinetic model and a kinematic model of the rigid spacecraft; 2, setting an attitude tracking error and anexpected attitude parameter of the rigid spacecraft, and combining the attitude tracking error and the expectation attitude parameter with the kinetic model and the kinematic model to establish a mathematical model for the attitude tracking; 3, adopting a control algorithm of a sliding mode variable structure controller to adjust a control law of the mathematical model which is established in thestep 2 and is used for the attitude tracking, and simultaneously combining an observation result of a disturbance observer to modify the control law; and 4, controlling the rigid spacecraft by using the modified control law obtained in the step 3 to realize the attitude tracking. The method is suitable for the attitude tracking of targets running in the outer space.
Owner:HARBIN INST OF TECH
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