97 results about "Planet" patented technology

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.

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.

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 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.

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.

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.

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.

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.

The utility model discloses a planetary gear reducing mechanism which comprises a first-stage planetary transmission mechanism and a second-stage planetary transmission mechanism. The first-stage planetary transmission mechanism comprises a first-stage sun wheel shaft, a first-stage planet carrier and a first-stage gear ring; a first-stage sun gear is arranged on the first-stage sun gear shaft; a plurality of first-stage planet wheel shafts are arranged on the first-stage planet carrier, and first-stage planet wheels meshed with the first-stage sun wheel and the first-stage gear ring are arranged on the first-stage planet wheel shafts; the second-stage planetary transmission mechanism comprises a second-stage sun wheel shaft, a second-stage planet carrier and a second-stage gear ring; a second-stage sun gear is arranged on the second-stage sun gear shaft; the second-stage planet carrier comprises an inner planet carrier and an output planet carrier and is provided with a plurality of second-stage planet wheel shafts, the second-stage planet wheel shafts are provided with large planet gears meshed with the second-stage sun wheel and small planet gears meshed with the gear ring, and the pitch diameter of the large planet gears is larger than that of the small planet gears; and the first-stage planet carrier is in transmission connection with the second-stage sun wheel shaft. The utility model further discloses a joint actuator.

A planetary gear (1), in particular for use on an actuator (2) of an adjustable roll stabilizer (3) for a motor vehicle, wherein the planetary gear (1) comprises a sun gear (21; 31), a ring gear (22; 32) and a planet carrier (23; 33), which are arranged coaxially with one another with respect to a common axis of rotation (7), wherein the sun gear (21; 31) is in meshing engagement with a plurality of planets (27; 37), each mounted on the planet carrier (6) so as to be rotatable about a planet axis (24; 34), along an inner tooth engagement line (26; 36), and the planets (27; 37) are each in meshing engagement with an inner side of the ring gear (22; 32) along an outer tooth engagement line (25; 35), is characterized in that the inner tooth engagement line (26; 36) and the outer tooth engagement line (25; 35) are inclined to one another deviating from the parallelism to form a wedge angle (α), wherein the planets (27;37) each have a conical toothing with a cone angle (β) opposite to the wedge angle (α) and the planetary axis (24; 34) of each of the planets (27; 37) lies on the bisector of the wedge angle (α).

1. Name of the design product: Medal (The movement of stars and planets Y4492). 2. Use of the design product: Used as a medal for awarding or a souvenir. 3. Design key points of the design product: The combination of shape and pattern. 4. Picture or photo that best shows the design key points: Perspective view 1. 5. Left view, right view, top view, and bottom view are omitted.

The present disclosure provides a multi-asteroid exploration trajectory generation method, system and storage medium; for the first d time transfer of the multi-asteroid exploration trajectory, the undetermined Fourier coefficients of the position vector function are solved through the boundary conditions of the transfer starting time and the transfer ending time and the preset thrust acceleration constraint, and the corresponding candidate transfer trajectory is generated; wherein the position vector function is obtained by pre-construction using the Fourier series; the candidate transfer trajectory is the trajectory from the first d time transfer of the outgoing asteroid to the candidate target asteroid; according to the transfer cost of each candidate transfer trajectory, the preferred transfer trajectory of the first d time transfer is obtained by screening, and the candidate target asteroid corresponding to the preferred transfer trajectory is taken as the outgoing asteroid of the first d +1 time transfer; and the optimal exploration trajectory is generated according to the preferred transfer trajectories of all transfers. This method can quickly lock the optimal exploration path that can be achieved, greatly shortening the mission planning cycle.

The invention relates to a transmission assembly having a first planetary stage (101) and a second planetary stage (103). The sun shaft (107) of the first planetary stage (101) has an outer cone (115) and the planet carrier (109) of the second planetary stage (103) has an inner cone (119), the outer cone (115) and the inner cone (119) engaging with each other, and wherein a force-fitting and / or form-fitting rotationally fixed connection is present between the outer cone (115) and the inner cone (119).

The invention discloses a system and a method for measuring celestial body radiation noise based on an idle channel of a GNSS (Global Navigation Satellite System) receiver, relates to the crossing field of satellite navigation and radio astronomy detection, fully utilizes the idle channel in the receiver, realizes function expansion through firmware and algorithm upgrading, and does not need to add radio frequency hardware. This means that the idle channel and the navigation channel share the same radio frequency link in the links of the antenna, the feeder line, the low noise amplifier, the down-conversion and the like, so that the noise measurement result is consistent with the real observation condition. The deep fusion of navigation and scientific detection is realized, the baseband output is converted into a real-time radio radiation detector through statistical analysis, and the time sequence data of the equivalent noise temperature of the antenna can be continuously acquired. The data can be directly used for tasks such as sun storm monitoring, moon brightness temperature measurement, space background radiation change analysis and the like, and a real-time data source is provided for radio astronomy, space weather monitoring and planetary scientific detection.

The present invention relates to the field of planetary simulation technology, specifically to a time base conversion and planetary simulation synchronization system. The system includes a time parameter standardization module, a nonlinear time mapping establishment module, a dynamic simulation adjustment module, and a time difference correction module. The present invention ensures seamless conversion between different time bases by standardizing time parameters. It introduces nonlinear time mapping to more accurately simulate time distortion phenomena, enabling the simulation environment to more realistically reflect complex celestial dynamics. By adjusting the simulation time flow rate, it optimizes the management of time flow in the simulation model, ensuring the continuity and efficiency of the simulation. The introduction of time difference correction improves the reliability of simulation data through the precise calculation and real-time correction of theoretical time deviations, optimizes the time flow rate of the simulation platform, and achieves precise matching of celestial motion time, thereby improving the accuracy and consistency of the simulation.

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.

1. Name of the design product: sole (planetary meteorite crater). 2. Use of the design product: sole. 3. Design key points of the design product: lies in the shape. 4. Picture or photo that best shows the design key points: three-dimensional view 1.

A flying object flies in an outer space from the earth to the moon or a planet or near the moon or a planet. The flying object includes a positioning-signal reception device. A ground station includes a positioning-signal transmission device equipped with a directivity-direction control function and has known position coordinates in an earth-fixed coordinate system. The flying object measures position coordinates in the earth-fixed coordinate system by receiving a positioning signal transmitted from the ground station simultaneously from the ground stations at four locations.

The invention relates to a pose measurement and control method of a distributed external shielding planet observation system, and belongs to the field of space astronomical telescopes. The method comprises the following steps: performing primary satellite and secondary satellite formation setting on a telescope; performing relative translation coarse alignment on the primary satellite and the secondary satellite; performing focal length precise adjustment on the primary satellite and the secondary satellite; performing three-dimensional attitude precise alignment on the primary satellite and the secondary satellite; the star shielding cover is arranged between the telescope and the interference fixed star, and the positions and poses of the star shielding cover and the telescope are adjusted. According to the invention, micron-level relative attitude determination and synchronization, centimeter-level formation flight control and arc-second-level measurement resolution can be realized.

The invention provides a solar system planet orbit parameter inversion method and system, and belongs to the technical field of astronomical data processing and celestial body orbit calculation, and the method comprises the steps: obtaining the Chebyshev polynomial order and coefficient of a planet; carrying out time normalization processing on a planet position observation moment, and carrying out planet position accurate calculation by adopting Chebyshev polynomial interpolation; estimating the number of initial Kepler orbits; establishing a mathematical model between the planetary position and the Kepler orbital element, constructing an objective function, and performing Jacobian matrix calculation and orbital element solution iterative optimization processing; and performing quadratic polynomial fitting on the multiple groups of Kepler orbit elements to generate Kepler orbit elements in a quadratic polynomial coefficient form. The method is used for meeting the requirement for low calculation amount of medium-precision solar system planetary orbit parameters and planetary positions in the fields of astronomical research, astronomical observation, spaceflight orbit design, space exploration task planning and the like.

A system includes a plurality of satellites in orbit 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 receive image data from sensors in the imaging device, to increase a positional detection accuracy of the celestial image features by defocusing imaging optics of the imaging device, to capture image data in a volume of the sky as the FOV of the imaging device on each satellite moves in an orbital plane, and generate by a centralized computer at least 1,000 celestial image features using the image data transmitted from each of the satellites.