152 results about "Planet" patented technology

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The present invention discloses an apparatus for quickly finding a planet by using a mobile phone, including: a digital telescope, an electronic compass, a pan / tilt configured to install the digital telescope, a mobile phone, a PC terminal, and a data converter. The digital telescope includes a telescope housing. A main camera configured to photograph target starry sky and a planet-finding camera configured to search for and photograph a target planet are disposed at one end that is of the telescope housing and that faces starry sky. The present invention is used more easily when a user's professional level is reduced.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

According to the out-of-focus holographic measurement method of the radio telescope based on planetary zooming, a planet is used as a source for out-of-focus observation, a beam pattern of an actually observed planet is obtained through deconvolution, a theoretical far-field model of the planet is established, and the theoretical far-field model of the planet is compared with the actually observed beam pattern to calculate a redundancy value. And continuously updating the coefficient of the Zernike polynomial by minimizing the redundancy value and iterating until the optimal phase model is determined, and determining the phase error on the aperture plane according to the phase model. According to the out-of-focus holographic measurement method, the planet is introduced to serve as a radio source, the measurement precision and stability are improved, the real-time measurement effect and the multi-frequency calibration capability are enhanced, the calibration accuracy and the overall performance of the Tianmar radio telescope are remarkably improved, many limitations of a traditional surface type measurement method are solved, and the measurement precision and the measurement stability are improved. For example, the measurement speed is slow, additional hardware equipment is needed, the influence of weather is large, and the application range is limited.

The invention discloses a test platform and a test method for simulating lunar soil penetration in a low-gravity environment based on bottom friction, and belongs to the technical field of low-gravity simulation devices. Simulated lunar soil is placed in the simulation box; the simulation box is arranged on the support adjusting unit; wherein the inclination angle of the simulation box is adjusted by adjusting the length of the support adjusting unit, so that the gravity of the moon is simulated; the monitoring unit penetrates through the simulation box and then penetrates into the simulated lunar soil, and the penetration resistance in the simulated lunar soil is monitored. The low-gravity environment of the moon can be simulated, and the low-gravity environments of other planets can also be simulated by applying the method principle provided by the invention; meanwhile, the method provided by the invention can be used for calculating the inclination angle alpha of the corresponding test bed according to different lunar soil or star soil materials (the friction coefficients mu of different materials are different).

The invention relates to a method for eliminating a double-planetary-calendar forecast error based on post-event precise ephemeris. The method comprises the following steps: forecasting a satellite position of the day at an ephemeris reference moment based on double planetary calendars and an SDP4 model; calculating the satellite position of the ephemeris reference moment on the day based on the post-event precise ephemeris of the double planetary calendars on the ephemeris reference moment on the day, and taking the satellite position as a reference satellite position; acquiring a satellite position forecast error by comparing the difference between the forecast satellite position and the reference satellite position of the day at the ephemeris reference moment, and fitting the satellite position forecast error of the satellite in one orbit period to obtain an error function of the double-planetary-calendar forecast satellite position; and performing error elimination on the forecast satellite position of the target date according to the error function to obtain the forecast satellite position after error elimination. By adopting the method, the satellite position forecasting error of the double planetary calendars can be eliminated, and the precision of the double planetary calendars for medium and long term forecasting is improved.

A personal planetarium projection system is provided. The system may comprise a light source, a removable star disc comprising a transparent star and planet pattern, and a focus lens mechanism for focusing the light source through the star disc. The system may also comprise an optical zoom lens for projecting light passing through the star disc onto a projection surface to produce a projected image. The zoom lens enables different magnifications of the projected image.

The invention discloses a planetary atmospheric trace gas spectrum telemetering and in-situ fusion detection system and method, and belongs to the technical field of deep space exploration. The detection system has a telemetering mode and an in-situ detection mode, and comprises a telescope module, a laser light source module, a heterodyne spectrum telemetering module, an in-situ absorption spectrum module, a gas sampling and enriching module and a signal acquisition, processing and control module. In the on-orbit stage, a heterodyne spectrum telemetering module is adopted, and a laser light source and sunlight signals are subjected to frequency mixing for atmospheric component telemetering; and after the detector enters an atmospheric descending section, the in-situ absorption spectrum module performs in-situ absorption spectrum measurement by utilizing the detection light of the same laser light source. By performing space-time fusion and joint inversion on the data acquired in the two modes, coherent detection from large-range general survey to fixed-point detailed survey is realized, the problems of load separation of telemetering and in-situ detection and difficulty in data fusion are solved, and the detection efficiency, the data consistency and the integration level of the system are greatly improved.

Described herein is a method for wireless transmission of energy in space, wherein a constellation of transmitting satellites orbiting around a celestial body, such as the planet (P) Earth or the Moon (L), are equipped with a laser apparatus for sending a beam of coherent electromagnetic waves to an orbiting satellite or another receiving target, such as a mobile vehicle or a fixed base on said generic celestial body, in order to transmit energy thereto. The total power transmitted is divided among the orbiting satellites in the constellation, resulting in less contraindications than in the case of a single transmitting system with equivalent total power. The advantage of such division among a constellation of satellites mainly consists of shorter periods of solar eclipse, since sunlight is necessary for the operation of the transmission system. The receiving target or satellite converts the beam of electromagnetic waves into electric energy.

A compact vibratory burrowing probe, particularly beneficial in low gravity space exploration environments, uses lateral or stirring-like vibrations to fluidize a surrounding regolith, thereby decreasing the penetration resistance, and compensating for the light overhead weight to improve the burrowing action of the probe into the surface of the terrain of explored moons, planets, or asteroids. Included is a novel vibratory mechanism capable of imparting the novel lateral or stirring vibration, as well as a more conventionally oriented longitudinal vibration.

The invention discloses a method for analyzing nitrogen isotope in lunar soil, and relates to the technical field of lunar soil analys.The method comprises the steps that an analysis system composed of a heating cavity and a quadrupole mass spectrometer is prepared, and a connecting pipe is provided with a control valve; preparing a plurality of mixed gases of carbon monoxide and nitrogen in different proportions, measuring and recording the gas pressure linear change slope through an analysis system, and establishing a database; lunar soil is put into a heating cavity to be heated, precipitated gas is measured, the slope is recorded, the mixing proportion is determined according to the measured slope and a database, and the nitrogen isotope ratio is obtained by deducting the amount of carbon monoxide. The method effectively avoids carbon monoxide interference, improves measurement accuracy, is simple and convenient to operate, reduces in-orbit measurement load weight, and provides a reliable analysis means for scientific research of the moon and the planet.

A star infiltration device and method of measuring the gravitational acceleration and soil-bearing capacity of a star are provided. The infiltration device is multifunctional and has a variable ramming frequency intensity. It comprises an infiltrator in which a rammer is driven by solenoid coils to move up and down in a conducting pipe to cause the infiltrator to penetrate a layer of star soil. Planetary gravitational acceleration is measured while the infiltrator is in the penetration state, star soil softness is evaluated during the penetration process, and star soil thermal parameters and temperature fluctuations are measured after penetration.

The invention discloses a method for accurately measuring a nano ion probe olivine Mg isotope micro-region and applying a moon sample, particularly relates to application of a nano ion probe (SIMS) technology in magnesium isotope analysis, and particularly relates to a method for carrying out high-resolution and high-precision magnesium isotope analysis and on-line matrix effect correction by utilizing a nano ion probe (NanoSIMS). The method comprises the following steps: (1) synthesizing an olivine reference substance with a coverage Fo value (magnesium-iron ratio) range of 0-90 by using a high-temperature and high-pressure experimental method, and verifying composition uniformity and isotope stability of the olivine reference substance through an electron probe (EMPA) and a multi-receiving inductively coupled plasma mass spectrometry (MC-ICP-MS); (2) optimizing NanoSIMS instrument parameters, and realizing synchronous detection of 24Mg < + >, 26Mg < + >, 28Si < + > and 56Fe < + > through a static multi-collection mode; (3) based on the ratio of 24Mg / (24Mg + 56Fe), proposing a biphase Hill equation to correct the matrix effect, and realizing online correction; and (4) analyzing the geological sample by using the method, and revealing the chemical and isotope change characteristics of the micron scale. The method has high resolution (1 [mu] m) and high precision (0.4 per thousand to 0.6 per thousand), and is suitable for micro-area isotope analysis in the fields of planetary science and geochemistry.

The application discloses a small-sized separated penetrator for in-situ detection of celestial bodies, and relates to the technical field of penetrator equipment, comprising an aluminum honeycomb buffer module, which comprises an external protective shell and an aluminum honeycomb, and has the beneficial effects that the application is provided with in-situ detection of high-speed penetration of celestial bodies, and discloses a small-sized separated penetrator, which comprises a planet soil penetration module and a star table detection module, and realizes autonomous separation in the impact penetration process, the star table module can realize star table detection and communication with an orbiter, the penetration module is internally provided with an energy storage device and an impact hammer, and can continue to penetrate and dive relying on the energy storage device after impact; the star table module is connected with the penetration module through flexible wires, and can supply power and signal transmission to the latter, the technology enables the penetrator with the modular characteristic to have the in-situ detection capability of planet soil profile, aims to expand the application mode of the penetrator for celestial body detection, and provides a scientific basis for the research of star table structures.

Provided are a method for controlling an artificial object, a device for controlling an artificial object, and an artificial object provided with the device for controlling an artificial object, whereby an artificial object is controlled with a high degree of freedom without requiring a special propellant. Provided is a control method for controlling an artificial object (100) in the vicinity of a planet or satellite including the earth located in a cosmic space, the control method accelerating the injection of electrons, increasing the potential of the artificial object (100) compared to a state in which no electron is emitted, promoting the capture of electrons present in the vicinity of the artificial object (100) compared to the state in which no electron is emitted, and increasing the potential of the artificial object (100) in the vicinity of a planet or satellite including the earth located in the cosmic space. The electrons captured by the accelerated injection change the momentum or / and angular momentum of the artificial object (100) by a reaction generated in accordance with the momentum imparted to the electrons after the accelerated injection.

This is a self-replicating nanofactory which uses nano-electron lithography to assemble copies of itself along with nanoscale precise products. The device is 100 nm×100 nm×100 nm in size making it a type of nanomachine that assembles products being a nanofactory. The device is composed of carbon nanotubes, silicon carbide and silica which are naturally available in the form of carbon dioxide and silicon dioxide on many planets and asteroids in the universe. This device uses sugar to power itself as the carbon based nanomachines being cells and bacteria use as a power source which can be naturally sourced in a environment as well.NameCityStateCountryWestPendletonINUSNanoroboticsLLCAssignee:West Nanorobotics LLCAppl. No.:63 / 474,335Filed:Aug. 9, 2022

The present invention discloses a target structure registration measurement method and system for planet and asteroid exploration. The method is implemented by a time-of-flight camera installed on a satellite. The method comprises: receiving images and depth information of the surface environment of a target star body collected regularly by the time-of-flight camera, fusing the images and depth information, and generating three-dimensional point cloud data; filtering the three-dimensional point cloud data to obtain denoised three-dimensional point cloud data, and storing the denoised three-dimensional point cloud data in a data list; extracting effective area information from the denoised three-dimensional point cloud data to obtain data of the effective point cloud area; then performing iterative closest point method registration to obtain a transformation matrix; extracting the denoised three-dimensional point cloud from the data list, transforming it using the transformation matrix, and obtaining registered overall three-dimensional point cloud data; and extracting features from the registered overall three-dimensional point cloud data to obtain distance information, position information, and shape information of the surface of the target star body.

The present invention discloses a low-gravity environment simulated lunar soil penetration test platform and test method based on bottom friction, belonging to the technical field of low-gravity simulation devices, including a support adjustment unit; a simulation box, in which simulated lunar soil is placed; the simulation box is arranged on the support adjustment unit; wherein the inclination angle of the simulation box is adjusted by adjusting the length of the support adjustment unit to simulate the gravity of the moon; a monitoring unit, which penetrates into the simulated lunar soil after passing through the simulation box, and monitors the penetration resistance in the simulated lunar soil. The present invention can simulate the low-gravity environment of the moon, and the method principle proposed in the present invention can also simulate the low-gravity environment on other planets; at the same time, the method proposed in the present invention can calculate the corresponding test platform inclination angle α for different lunar soil or star soil materials (different materials have different friction coefficients μ).

A gear arrangement (1) for a multi-stage planetary gear system, comprising a planet carrier (2) of a first planetary stage and a sun gear (3) of a second planetary stage of the planetary gear system, wherein the planet carrier (2) has a central recess (4) with an inner contour, an axial region (5) of the sun gear (3) has a complementary outer contour and is inserted into the central recess (4) of the planet carrier (2) such that the planet carrier (2) and the sun gear (3) are connected to one another in a rotationally fixed manner to form the gear arrangement (1), characterized by a securing element (6) arranged between the sun gear (3) and the planet carrier (2), which securing element extends circumferentially around the sun gear (3) and establishes a positive connection between the sun gear (3) and the planet carrier (2) by engaging in a groove (7) formed on the inner circumference of the planet carrier (2) and by engaging in a groove (8) formed on the outer circumference of the sun gear (3).

The off-focus holographic measurement method of the planet zoom-based radio telescope of the application carries out off-focus observation on a planet as a source, obtains an actual observed beam pattern of the planet through deconvolution, establishes a theoretical far-field model of the planet, compares the theoretical far-field model of the planet with the actually observed beam pattern to calculate a redundancy value, continuously updates coefficients of Zernike polynomials through minimization of the redundancy value and iteration until an optimal phase model is determined, and determines a phase error on an aperture plane according to the phase model. The off-focus holographic measurement method of the application introduces a planet as a radio source, not only improves measurement accuracy and stability, but also enhances real-time measurement effect and multi-frequency calibration capability, significantly improves calibration accuracy and overall performance of the Tianma radio telescope, and solves many limitations of traditional surface measurement methods, such as slow measurement speed, need of additional hardware devices, great influence of weather, limited application range and the like.

Software-defined space domain awareness systems, comprising a network of a plurality of sensor nodes operating in orbit, each node comprising a hosted payload configured to operate as a network participant in a multi-service SDA network. The hosted payload having a space domain awareness sensor, a processing unit configured to execute a software stack, and a standardized hardware and data interface for integration with satellite, planetary lander, planetary rover platforms or ground / planetary observatories (i.e., earth, moon or another planet). The software is configured to implement SDA algorithms including object detection, object identification and object characterization, autonomously execute tasking decisions using onboard data and shared information from other sensor nodes, synchronize and distribute tracking data via interoperable protocols across the network, and perform real-time propagation of object states and associated uncertainties. The network thus provides decentralized dynamic participation and the sensor nodes providing observation data and receiving tasking directives by the network.

The invention discloses a sky wave propagation time delay correction method for improving the equivalent height of an ionized layer. The method comprises the following steps: converting obtained geographical location information of a long-wave transmitting station and a signal receiver into latitude and longitude information; the latitude and the longitude corresponding to the position information of the sky wave signal ionosphere reflection point are obtained by combining a long wave transmitting station; obtaining an annual day and an hour moment corresponding to the emission time of the long-wave emission station for emitting the time service signal; inputting the solar activity F10.7 index and the geomagnetic activity planet index corresponding to the annual day, the hour moment and the emission time into an ionized layer equivalent height model to obtain an ionized layer equivalent height value; obtaining the sight distance extreme value of the radio signal through the ionosphere equivalent height value, and obtaining the actual signal propagation path length of the sky wave signal through the sight distance extreme value; and further acquiring the propagation time delay of the sky wave signal, and acquiring the complete propagation time of the sky wave signal from the long-wave transmitting station to the signal receiver through the propagation time delay. According to the invention, the propagation time delay precision of sky wave signals and the time service precision of a long-wave time service system are improved.

A primary sun gear is inserted into the center of a primary planet carrier, a primary planet gear is placed on the edge of the primary planet carrier, a cylindrical roller A is placed in the primary planet gear, a primary planet gear cover covers a primary planet gear shaft, a secondary sun gear is inserted into the center of a secondary planet carrier, and a secondary planet gear cover covers a secondary planet gear shaft. A secondary planet gear is placed on the edge of a secondary planet carrier, a cylindrical roller B is placed in the secondary planet gear, a secondary planet gear cover is inserted into a secondary planet gear shaft cover, an output shaft is connected with a secondary sun gear, the primary planet gear and the secondary planet gear are sleeved with a shell, and the primary planet gear and the secondary planet gear are meshed with a gear arranged in the shell. The speed reducer has the advantages of balanced operation, noise and vibration reduction, convenience in assembly and disassembly, bearing load enhancement, reduction of the overall dimension of the speed reducer and good heat dissipation performance.

A planetary drive includes static and freely rotating outer rings having different diameters, sun gear, and multiple planet gears disposed around the sun so that their axis of rotation is rotated relative to the drive axis, causing each planet to contact each ring at a point along its length. The sun contacts each planet at a point between its contact points with the rings, such that the force at the contact points is enough that the resulting traction can transmit torque with minimal backlash. A carrier supports the planets such that each can rotate about both its own axis and the drive axis. There may be involute teeth or other surface features on parts of the rings, planets, and sun. In a sun-less configuration, the drive is actuated by the carrier. In a single-stage version, the freely rotating ring is absent and output is obtained from rotation of the carrier.

An electromechanical actuator and shading device comprising such an electromechanical actuator. An actuator (11) includes a reduction gear (19), which includes a first stage (37) and a second stage (39), and a centering shaft (71). The first stage (37) includes a bearing (76), which includes a first bore (77) and a second bore (78). The bearing (76) is mounted inside a bore (74) of a planet carrier (66) of the first stage (37) with an interference fit. The centering shaft (71) is mounted inside the first bore (77) of the bearing (76) with a loose fit. In addition, a shaft (59) of a sun pinion (40) of the first stage (37) is mounted inside the second bore (78) of the first bearing (76) with a loose fit. Figure for the abbreviation: Figure 6.

The present invention relates to an aerostat (1) for carrying out transport and / or observation missions on a planet with an atmosphere, the aerostat comprising: an inflatable body (2) designed to be pressurised by a gas lighter than the atmosphere, a payload (3) configured to have at least one scientific instrument installed on-board, and a solar energy generator (7) arranged between the inflatable body (2) and the payload (3).

Various examples are provided related to a space-based imaging approach for characterizing objects in space Earth or other planetary body. In one example, a method for characterizing objects in space includes illuminating an object in space about Earth or other planetary body with a narrow band, continuous wave (CW) radio beam transmitted by a transmitting telescope; receiving return signals from the object by receiving telescopes in an array, at least one receiving telescope in orbit; and generating a high resolution image of the object from the received return signals utilizing a near-field correction. In another example, a space-based imaging system includes an array of telescopes including a transmitting telescope that can illuminate an object in space; a plurality of receiving telescopes that receive return signals reflected by the object; and processing circuitry that generates a high resolution image of the object from the received return signals.

The present invention discloses a method and device for estimating the internal dielectric constant of an asteroid based on a single-station orbital radar, relating to the field of planetary exploration. The method primarily comprises: separating diffraction waves from single-station orbital radar recordings, determining the number of diffraction points within the asteroid and the range of values ​​for the scanned dielectric constant; setting a diffraction point and a scanned dielectric constant value within the asteroid, solving the eikonal equation to obtain the travel time of the diffraction wave, and calculating the superposition energy of the diffraction waves within a fixed time window starting from the travel time; repeating the previous steps until all positions within the asteroid and the range of values ​​for the scanned dielectric constant are traversed; selecting several local maxima from all the superposition energies, determining the diffraction point positions and scanned dielectric constant values ​​corresponding to all the maxima; and interpolating the results to obtain the dielectric constant distribution within the asteroid. Implementing the method and device for estimating the internal dielectric constant of an asteroid based on a single-station orbital radar provided by the present invention can quickly and accurately obtain the internal dielectric constant distribution of the asteroid.

The invention discloses a device for dynamically simulating and demonstrating interstellar transfer of a spacecraft. The device comprises a first simulated planet, a second simulated planet, a simulated orbit, a central control unit and a lamp strip, the first simulation planet and the second simulation planet are respectively used for simulating two real planets; setting the position and the shape of a simulation orbit in a three-dimensional space according to the orbit position, the orbit shape and the orbit parameters of a real spacecraft transferred between two real planets and according to a preset reduction proportion; the lamp strip is arranged on the simulation track and covers the whole simulation track; the position of the LED lamp which flickers currently on the lamp strip represents the current position of the spacecraft running on the orbit; the lamp strip simulates the running speed of the spacecraft through the light flickering speed of the LED lamps, and the higher the light flickering speed of the lamp strip is, the higher the running speed of the spacecraft is. The device can vividly and visually display the operation process of the spacecraft between two planets.