165 results about "Orbital control" patented technology

A star sensor attitude-determination method during the autonomous orbital control fault recovery includes: (1) predicting the satellite inertia attitude according to data measured by a gyro; (2) calculating the filtering modified innovation amount according to the inertia attitude of the satellite and the optical axis vector and the lateral axis vector under an inertial coordinate system which are measured and output by the star sensor, and calculating the error of the innovation amount between the front and the back periodicals, which is used for judging the consistency of star sensor data; (3) judging the consistency of the star sensor data; (4) fixing the attitude of the star sensor according to the two vectors; (5) introducing the star sensor which is combined with the gyro for the correction of the satellite attitude under the condition that the star sensor data arranges the initial value of the attitude estimation. The method can improves the reliability of the orbital control fault recovery, saves the time for the fault recovery and ensures that the orbital control is accurately recovered in time.

An active satellite dispenser is preferably attachable to a reusable launch vehicle for deployment of one or more satellites into one or more desired orbits. The active satellite dispenser includes a center mast that releasably receives the satellite(s), a liquid propellant rocket, and an orbital control system on an avionics pallet. In the preferred embodiment, a pressurized gas selectively pressurizes the propellant tanks (which may include fuel and oxidizer tanks), to provide propellant to the rocket. In operation, the launch vehicle releases the satellite dispenser in a first deployment orbit. The active dispenser rocket and orbital control system then transport the active dispenser and satellite(s) into the final deployment orbit. In the preferred embodiment the active dispenser can operate multiple times to place individual satellites in different orbits.

The invention relates to the research field of a microgravity simulating platform of a space robot, in particular to a microgravity air floatation target satellite simulator system with five degrees of freedom. The system consists of three parts, namely a movement simulator, a satellite simulator and a ground control panel. The movement simulator simulates the states of zero gravity, low friction and micro interference of a base satellite; the satellite simulator has a basic single-shaft attitude adjustment and track control function under a condition that a satellite provided by the movement simulator is in a track movement simulating environment, comprises a sensor, a controller and an actuating mechanism (a counteractive flywheel and a cold gas injecting system), and is provided with auxiliary systems such as a power system, a wireless communication assembly, a structural component and the like; and the ground control panel provides a basic function of the wireless data communication between a target satellite and the ground, and realizes the control on the target satellite and the receiving, storage and display of the data.

The invention discloses a wireless communication module and a wireless communication satellite using the module, relates to a wireless communication module and a wireless communication satellite, and solves the problems that the conventional satellites have complex structure, poor reliability and poor safety and are not favorable for tests. In the wireless communication module, a radio frequency antenna is connected with a radio frequency signal transmitting/receiving end of a radio frequency chip circuit; a signal end of the radio frequency chip circuit is connected with a signal end of a microcontroller; and an external data acquisition and control signal end of the microcontroller is a baseband data input/output end of the wireless communication module. In the wireless communication satellite, a power supply provides working power for a measurement and control system, a satellite management system, an attitude and orbit control system and an effective load management and control system; and the measurement and control system, the satellite management system, the attitude and orbit control system and the effective load management and control system form a wireless network through four wireless communication modules. The wireless communication module and the wireless communication satellite using the module are applied to the field of high-reliability and high-safety satellite communication.

A filtration unit for a swimming pool or spa, is disclosed, the filtration unit including a support base (20); a filter housing (30) mounted on top of the support base; and a recess (21) in the support base, the recess adapted to receive a pump (60), at least in part. A multi-port valve (50) is laterally mounted to the filter housing wherein an orbital control arm (54) of the multi-port valve may be moved in a substantially vertical plane to select alternative operations of the filtration unit. The unit may further include a top with space for electronic controls and/or chemicals.

The invention discloses a satellite orbit simulation method and device. The method comprises the following steps: acquiring total simulation parameters; according to the total simulation parameters, combining different conditions of numbers of satellites to obtain orbit parameters of satellites to be simulated under an inertial system respectively; when satellite orbit transfer orbital control requirements exist, realizing incremental computation of a speed needed by satellite transfer orbital control through calling an orbit optimization program, so as to calculate a total acceleration of the satellites; and finally, calling an orbit dynamic calculation program to finish satellite orbit simulation. Aiming at the satellites with the different numbers, the satellite orbit simulation is carried out and an applicable range of a simulation program is wide; and furthermore, the satellite transfer orbital control can be realized through calling the orbit optimization program, and the simulation program is open so that development and expansion are facilitated.

The invention discloses a track control method for a space rendezvous ground guide section with limited orbit maneuvering, aiming to realize high-precision track control of the space rendezvous ground guide section under the condition of limited orbit maneuver. The technical solution is to first determine the orbital maneuvering scheme of the tracking spacecraft as five orbital maneuvering schemes, determine the orbital control parameters M1~M5 that need to be calculated; calculate the orbital control parameter M1 after the tracking spacecraft enters orbit, and upload it to the tracking spacecraft. The maneuvering system performs the first orbital maneuver; after the first, second, and third orbital maneuvers are completed, the orbital control parameters M2, M3, and M4 are calculated respectively, and uploaded to the tracking spacecraft, and the orbital maneuvering system performs the second, third, and fourth maneuvers Orbital maneuvering; finally implement the fifth orbital control according to the orbital control parameter M5 (obtained when calculating M4). The invention has less number of track maneuvers, lower requirements on the attitude control system, improves the track control accuracy of the ground guidance section under the condition of limited track maneuvers, and has fast calculation speed and good real-time performance.

The invention discloses a high-integration three-unit cubic satellite capable of maneuvering orbital transfer. The cubic satellite comprises a satellite basic platform, and the satellite basic platform comprises a main force bearing structure, a solar cell array, a satellite computer, a lithium battery pack, a power supply control panel, a UV antenna, a UV communication machine, an attitude measurement and control system, other related accessories and a propulsion and control system; and the control system comprises a double-pulse solid rocket thruster, an ignition control panel of the double-pulse solid rocket thruster, a cold air micro thruster, a pulse modulation module of the cold air micro thruster, a mass moment executing mechanism and a mass center adjusting mechanism. The three-unit cubic satellite has the thrust vector control capability and is high in integration degree, rapid orbital transfer and attitude orbit control of the cubic satellite can be conducted, large-range orbital maneuver of the satellite is achieved, and the application field of the cubic satellite is greatly expanded.

Provided is a system adopting a mobile project robot to drill holes. The system adopting the mobile project robot to drill the holes comprises a BIM tunnel hole drilling model, a CPIII railway control net, and the project robot, wherein the CPIII pathway control network comprises a control point location column. The project robot comprises a pathway mobile platform, a power system, a industrial computer, six axles mechanical hand, a PLC controlling system, a positioning system, a photograph system, a rebar detecting instrument, a real time laser hole depth detector, a electric hammer and a dust-precipitating system are installed on the railway mobile platform. According to the system adopting the mobile project robot to conduct tunnel drilling, the drilling quality is high, the consistency is good, the system is efficient, reliable, safe and fast, and the human cost is saved, at the same working hours, tunnel drilling working distance can approach the several times of the artificial drilling holes.

The invention discloses a formation configuration reconstruction optimization using a finite element method. The finite element method is used for dividing the formation reconstruction time into a series of equally spaced intervals, and the problem of solving the reconstruction path is transformed into an optimization problem; therefore, the limitation problem of the traditional reconstruction method is overcome, and the reconstruction of a satellite formation is realized. In the optimization process, the optimal orbit control quantity and the corresponding reconstructed orbit state quantity in each time subinterval are determined according to the numerical iterative method; and the iteration and correction are performed again on the loading of the control acceleration applied by a small thrust engine to the spacecraft in the optional subinterval and the reconstruction orbit state quantity considering the criteria of controlling the total fuel consumption to be minimum, the control opportunity, and the safety factor to avoid collision among spacecrafts.

The invention provides a multi-stage health state acquisition method for a low-orbit remote sensing satellite navigation positioning system. The multi-level health management comprises: equipment-level health management and system-level health management; wherein the equipment-level health management comprises equipment operation health management and equipment function health management; the system-level health management comprises: a navigation positioning system operation health management and navigation positioning system function health management. The implementation body of the system-level health management comprises a satellite-borne computer, an orbit control subsystem and a payload subsystem, wherein information interaction exists between the satellite-borne computer and a navigation and positioning system in a low-orbit remote sensing satellite. The invention provides a multistage health management method for a low-orbit remote sensing satellite navigation positioning system. Compared with single-level health management, the management means are more diverse, the health state is more comprehensively reflected, the limitation of fault handling in single-level health management is solved, and on-orbit autonomous safe operation of the low-orbit remote sensing satellite can be more powerfully guaranteed.

The invention relates to a satellite scanning system and discloses a space scanning bracket with a self-balancing function. The space scanning bracket with the self-balancing function comprises an azimuth scanning bracket (5) which is arranged on an arc-shaped bracket (4), the azimuth scanning bracket is provided with two sliding rails and two sliding blocks, and the arc-shaped bracket (4) is provided with an internal arc and an arc-shaped sliding rail. A loading instrument (7) and a balance weight (1) are arranged on two sides of the azimuth scanning bracket (5) and do oscillatory scanning with speed in the opposite direction on the sliding rails of the azimuth scanning bracket (5) through rollers, the product of rotation inertia and rotation speed of the loading instrument encircling a rotation center and the product of rotation inertia and rotation speed of the balance weight encircling the rotation center are equal in number and opposite in direction. The space scanning bracket with the self-balancing function solves the problems of a complex control system, a high manufacturing cost and unreasonable structure design and the like existing in an existing scanning mechanism and achieves the beneficial effects of relieving the burden of the satellite attitude and the orbital control system, reducing the development cost, prolonging the satellite service life and the like.

The invention discloses an orbit maintaining method for an ultra-low orbit satellite. The method comprises the steps: setting satellite parameters and atmospheric parameters, building an orbit dynamics model according to the satellite parameters and the atmospheric parameters, and enabling the satellite parameters to comprise satellite orbit parameters, satellite basic parameters and initial satellite orbit control parameters; an optimization model is constructed, the initial satellite orbit control parameters are optimized according to the optimization model, the orbit dynamics model, the satellite orbit parameters and the satellite basic parameters, optimized orbit control parameters are obtained, and the optimization model comprises a plurality of optimization constraint conditions; According to the optimized orbit control parameters, an air suction type propulsion system is controlled to collect air and exhaust the air, so that orbit maintenance of the ultra-low orbit satellite is realized. The technical problem that in the prior art, an ultra-low earth orbit satellite is difficult to maintain in orbit for a long time is solved.

The invention discloses a satellite attitude control method based on variable control periods. The satellite attitude control method includes the steps of S1, selecting corresponding control periods and controller parameters according task requirements; S2, using original data collected by a gyro to calculate inertial angular speed according to the control periods; S3, using attitude information output by an attitude sensor to calculate a satellite attitude determined angle; S4, using the inertia angular speed obtained in S2 and the attitude determined angle obtained in S3 to calculate controlmoment; S5, using the control moment to transmit control pulse width to an actuator; S6, returning to S1 to repeat a new round of satellite attitude control to achieve variable-period satellite attitude control. The satellite attitude control method has the advantages that different control periods and controller parameters are selected according to different task requirements, restriction of thecalculation quantity of attitude control tasks and computer hardware conditions is broken through, and high-precision transfer orbital control and high-precision, long-term and reliable earth observation tasks are completed.

The invention provides a phase maintaining method based on a reference satellite. The phase maintaining method comprises the following steps: (1) calculating a boundary value of satellite phase drift;(2) after constellation networking, calculating the phase of each satellite in the constellation; (3) respectively taking each satellite in the constellation as a target satellite, and calculating the phase angle drift amount of other satellites in the constellation relative to the target satellite; (4) calculating an accumulated value of the phase angle drift amount; (5) selecting a satellite with the minimum phase difference design nominal value and the minimum phase angle drift critical threshold relative to the target satellite as a reference satellite, judging the satellite needing phasemaintenance, and predicting the phase maintenance time; and (6) when the phase difference of the satellite needing phase maintenance relative to the reference satellite is close to a threshold value,orbit control is carried out on the satellite needing phase maintenance according to the phase angle drifting direction, and adjustment and maintenance of the relative phase are achieved. According to the method, the defect of multiple times of absolute site maintenance is overcome, and the complexity of constellation configuration maintenance is reduced.

The invention discloses a small satellite orbit control optimization method based on orbit control deviation moment coefficient calibration. The method comprises the steps of step 1, determining telemetry data in an orbit control task of an on-orbit satellite; step 2, calibrating an orbit control deviation moment coefficient according to the telemetry data in step 1; step 3, performing the orbit control task according to the calibration result of the orbit control deviation moment coefficient in step 2, and adjusting the attitude of the satellite to an orbit control task attitude; step 4, performing angular momentum bias on all shafts according to the calibration result of the deviation moment coefficient; and step 5, executing the orbit control task, and after the orbit control task is completed, adjusting the satellite to a long-term working attitude. The orbit control task optimization method is targeted for the conditions that only an orbit control thruster is installed on a smallsatellite and the control capacity of a flywheel set is limited.

The invention provides an orbit control frequency analysis method and device for Walker constellation configuration maintenance. The method comprises the following steps of calculating the maximum permissible drift distance of a phase under the condition of the maximum permissible drift distance of the right ascension of different ascending nodes, determining an ascending node right ascension maximum allowable drift amount, a phase maximum allowable drift amount, a relative ascending node right ascension average drift rate and a relative phase average drift rate, according to the ascending node right ascension maximum allowable drift distance, the phase maximum allowable drift distance, the relative ascending node right ascension average drift rate and the relative phase average drift rate, calculating the orbit control frequency of the constellation satellite in the life cycle under the absolute configuration maintaining method, and taking the maximum allowable attenuation height as a constraint, and calculating the orbit control frequency of the constellation satellite in the life cycle under the relative configuration maintenance method. The method is suitable for the configuration maintenance of the low-orbit large-scale Walker constellation.