75 results about "Planet" patented technology

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 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.

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 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.

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.

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.

The application discloses a lunar orbit and libration parameter solving and forecasting method and system, and the method comprises the following steps: considering the interaction among the mass point gravity model based on the post-Newtonian framework, the moon figure, other planet mass points in the solar system and the influence of the earth figure, a high-precision lunar orbit dynamics model is established under the general relativity framework; considering the lunar moment of inertia and the lunar torque, a double-layer lunar libration attitude dynamics model is established; when the initial conditions of integration meet the preset accuracy, an adaptive step integrator and an adaptive step integrator with time delay effect are used to respectively forecast the orbit parameters and the libration parameters, and initial products of the orbit and the libration parameters with time sequence labels are obtained; when the initial conditions of integration do not meet the preset accuracy, an automatic differentiation-based nonlinear solver is used to process historical observation data, and the optimal solution of the to-be-estimated parameters in the initial conditions is obtained, and re-forecasting is performed.

The application discloses a kind of unloading method and device of asymmetric configuration satellite angular momentum, the method includes: by solar sensor, the solar vector under satellite body system is acquired, and the solar vector is converted into the solar vector under orbit system;The included angle β of the solar vector under the orbit system and orbit plane is calculated, and the rotation angle of solar wing rotation axis and the preset angle of biasing axis are set according to the included angle β of the solar vector under the orbit system and orbit plane;The angular momentum of flywheel system is calculated and is converted into the angular momentum under satellite body system;According to the modulus of satellite to be unloaded angular momentum and preset unloading threshold value are compared, according to the comparison result, it is judged whether magnetic moment device unloading needs to be started, and according to the comparison result, the control instruction of magnetic moment device is output.The application effectively reduces angular momentum accumulation and space moment accumulation;With the advantages of saving fuel, low power consumption requirement and high attitude stability, it provides a theoretical basis for angular momentum unloading of weak magnetic field planet explorer.

The utility model provides an earth around-the-sun revolution instrument with an invariable earth axis direction. The earth around-the-sun revolution instrument comprises a globe, an ecliptic turntable, a central shaft body and a perpendicular incidence plane disc, the globe comprises an earth model, an earth axis and a base. The base is rotationally connected with the ecliptic turntable through a bearing piece and is in transmission connection with the central shaft body through a transmission belt; the globe and the ecliptic turntable can be driven by external force to do revolution motion along the central shaft body; the direct plane disc is used for simulating a direct point of the sun to the globe and is arranged at the top of the central shaft body; when the globe revolves, the direction of the earth axis is not changed, and the perpendicular incidence point reciprocates between the south and north return lines of the earth model. The terrestrial globe is in transmission connection with the central shaft body through a transmission belt to form a planetary belt transmission mechanism, so that the revolution motion is ensured, the earth axis direction is maintained to be constant, the knowledge error of earth axis deviation during revolution of a traditional teaching aid is corrected, and the annual movement rule of a direct solar radiation point between south and north return lines is accurately reproduced.

The application discloses a kind of light frequency signal interplanetary gravity potential difference measurement methods, comprising: respectively establishing light clock light frequency comparison system on two planets needing to measure gravity potential difference, to construct planet-planet three-frequency combination light frequency comparison link;According to the planet-planet three-frequency combination light frequency comparison link constructed, bidirectional light frequency signal transmission, reception and reflection between two planets are carried out, respectively record the emission frequency f1 of planet one to planet two to planet one link, reflection frequency and receiving frequency, the emission frequency f2 and receiving frequency of link;According to the one-way frequency transmission model between stars, in combination with the frequency recorded, extract the gravitational redshift frequency shift between two planets;According to the relationship between gravitational redshift frequency shift and gravity potential difference, the gravity potential difference between two planets is calculated.

1. Name of the designed product: Eight-planet weight simulation table 2. Use of the designed product: Introducing the mass of eight planets through weight bearing by referring to various planets and celestial bodies in the universe. 3. Design points of the designed product: Combination of shape, pattern, and color. 4. Picture or photo best indicating the design points: Front view. 5. The claimed design includes color.

According to the intelligent non-convex asteroid shape inversion method based on the optical variation curve and constrained by physical information, physical prior information is fused through a deep learning network (PINAS-Net), and rapid and accurate non-convex asteroid three-dimensional shape inversion is achieved. Specifically, light variation curve data and a scattering parameter c serve as input, features of all curves are extracted through a light variation curve feature extraction module (LCFEM), interaction features among multiple curves are captured through a Transform encoder, and 1024-dimensional global features are obtained; meanwhile, expanding a scalar scattering parameter c into 16-dimensional features, fusing the 16-dimensional features with global features, and importing the 16-dimensional features into the network as physical constraints; and rough point prediction is carried out based on the fused features, and a fine point cloud shape is obtained through a Transform decoder and three-layer up-sampling. The method provided by the invention is verified on observation data and simulation data of a plurality of asteroids (433 Eros, 9 Metis and 21 Luteria), and a reconstruction result is highly consistent with a reference model. Assessment indexes show that the intersection-to-union ratio (IoU) of the method for the non-convex region can reach 0.81, the Chamfer distance is 0.046, and compared with a traditional KTM method, the inversion speed and precision are remarkably improved. The method provides a new technical means for asteroid shape inversion and physical parameter estimation, and has an important planet defense value.

The invention relates to a lunar surface repeatable telescopic gallery bridge mechanism, and belongs to the technical field of star surface base equipment room assembly channel mechanisms. One end of a follow-up connecting mechanism is connected with a fixing device, and the other end of the follow-up connecting mechanism is connected with one end of a channel folding and unfolding mechanism; a walking mechanism is arranged on the lower portion of the other end of the channel folding and unfolding mechanism. The lockable transmission wheel set is used, so that the passing stability of personnel and goods is ensured, and the reliability is highest. In the traction unfolding and butt joint process of the traction mechanism, pitching and yawing movement at a certain angle can be carried out; the requirements that the planet surface has an unstructured terrain and assembly interfaces between equipment have attitude differences are met. According to the method, the requirements of large-error pose assembly working conditions and the folding-unfolding ratio are met.

The invention relates to the technical field of planetary science and celestial body material analysis, and particularly discloses a lunar soil micron-sized particle sample capturing method which comprises the following steps: on an original substrate containing target particles, performing in-situ identification and phase classification on the particles by adopting a non-destructive spectrum means, generating a particle positioning map with serial number marks; preparing a microprobe with a flexible adhesion tip, and coating the flexible adhesion tip with an adhesion medium; the microprobe is controlled to make contact with target particles, the target particles are captured in a lossless mode through the adhesion force of the adhesion medium, and the target particles are separated from the substrate; transferring the microprobe capturing the target particles into a packaging medium, performing unique identification on a packaging body, and establishing a traceable file; a mild adhesion mode of the fiber tip and the embedding medium is adopted, the physical capture success rate of nearly 100% is achieved, and one-by-one independent treatment of single particles can be achieved.