167 results about "Asteroid" patented technology

The invention provides a novel, low-cost, spin-stabilized lander architecture capable (with appropriate system scaling tailored to the attributes of the target) of performing a soft-landing on a solar-system body such as Earth's Moon, Mars, Venus, the moons of Mars, Jupiter, Saturn, Uranus and Neptune, selected near-Earth and main-belt asteroids, comets and Kuiper belt objects and even large human-made objects, and also moving about on the surface of the target solar-system body after the initial landing in movement akin to hopping.

The invention provides a simulator of a star sensor. The simulator comprises a collimating objective lens, wherein a focal plane of the collimating objective lens is provided with a star point target; the star point target is imaged at infinity through the collimating objective lens; a light splitting component is arranged between the collimating objective lens and the star point target; the focal plane of a light splitting optical path on the side face of the light splitting component is also provided with a detection target; the star point target is fixed on a focal plane adjusting mechanism; and a target lighting device is used for lighting the star point target. In the simulator, a technology which is different from the scheme of the conventional star simulator is adopted, so that the problem of poor accuracy of simulation of angular distance between stars of the conventional star simulator is solved; and the simulator can be used for extremely-high-accuracy simulation of a star and asteroid array of an asteroid autonomous navigation extremely-high-accuracy star sensor, verification of measurement accuracy and autonomous navigation and positioning accuracy of the star sensor, and has broad application prospect in research of a deep space autonomous navigation sensor.

A hand-held electronic celestial object-locating device assists in identifying a celestial object or directing a user to a desired celestial object. The device is useful for locating or identifying any celestial object including stars, constellations, planets, comets, asteroids, artificial satellites, and deep sky objects to name a few. The device utilizes sensors for 3-axis magnetic field and 3-axis gravitational field detection. The device utilizes a processor and an electronic database to perform the required calculations. The device's database may be updated through access to the Internet through which the updates may be purchased.

The invention discloses a folding lightweight landing mechanism and relates to the landing mechanism of a lander. The invention aims at solving the problems of large volume, complexity in a buffer structure and high cost of the existing landing mechanism of the lander during the launching process. The folding lightweight landing mechanism comprises a triangular space truss type support, a buffer component, an instrument platform and three landing legs, wherein the triangular space truss type support comprises a triangular support, a star-shaped support, a space truss connecting rod component, three groups of main landing leg connecting components and three groups of auxiliary landing leg connecting components, the triangular support and the star-shaped support are arranged at the upper part and the lower part, the triangular support is connected with the star-shaped support through the connecting rod component, the three landing legs are distributed and connected on the periphery of the triangular space truss type support through the main landing leg connecting components and the auxiliary landing leg connecting components, and the triangular space truss type support is connected with the instrument platform through the buffer component. The folding lightweight landing mechanism is applicable to lander exploration activities for asteroids, comets, the moon, the Mars and the like.

The invention discloses a deep-space asteroid sample collection detector which comprises a detector housing, a sampling device, a protection device, a recovery device, a heat insulation material, and a control unit; when the asteroid detector lands, mechanical grippers on the protection device are unfolded; a motor-driven lead screw allows a flexible extending material to extend to a limit length so as to be used as a conveying pipeline for dust particle samples and be used for protection of the detector; then the sampling device launches ejection balls which bump the asteroid surface through the pipeline of the protection device; the sputtered dust particles are introduced into the recovery device of the detector through the conveying pipeline of the protection device, and are packaged isolatedly. The invention is an integrated device with the functions of asteroid sample collection, recovery, and packaging, and protection of the detector itself during the sampling process is also considered.

The invention relates to a full-coverage multi-channel multi-frequency band measuring and control system of a deep space electric propulsion asteroid spacecraft, comprising a star service computer and a plurality of deep space responders and an ultra high frequency (UHF) relay transceiver which are connected with the star service computer; the deep space responders are further connected with multiplexers and high-stability crystal oscillators, and the multiplexers are connected with all-directional receiving antennas and large-diameter directional antennas; the deep space responders are also connected to the input ends of low-power solid-state amplifiers and high-power traveling wave tube amplifiers through switch arrays, and the output ends of the low-power solid-state amplifiers and the high-power traveling wave tube amplifiers are connected to all-directional transmitting antennas and low-gain transmitting antennas through the switch arrays; and the UHF relay transceiver is connected with a relay transceiving antenna. According to the invention, the full-coverage multi-channel multi-frequency band measuring and control system of the deep space electric propulsion asteroid spacecraft can meet all-process star-earth remote control, remote detection, range finding and other requirements of the deep space asteroid spacecraft as well as the relay communication requirements of the asteroid spacecraft simultaneously, and has the advantages of high reliability, resource saving and low cost.

The invention relates to an autonomous landing navigation control ground test verification system under a small celestial body (asteroid and comet) microgravity environment and belongs to the technical field of ground semi-physical simulation. The autonomous landing navigation control ground test verification system under the microgravity environment specifically comprises a small celestial body surface topography simulation part, a base part, a lander mounting platform and an external measurement part, wherein the lander mounting platform comprises a mounting platform body, multiple flotation air legs, one small-thrust nozzle, wherein the multiple flotation air legs are fixed at the bottom of the mounting platform body in a regular polygon shape, so as to realize a high-pressure air cushion, so that frictionless motion is realized; the small-thrust nozzle is arranged in the inverse direction of to-be-simulated microgravity and used for generating a thrust so as to serve as the microgravity borne by a lander; the external measurement part is used for measuring space states such as the position and posture of the lander mounting platform relative to the small celestial body surface topography simulation part. The system can simulate different microgravities by virtue of changing the thrust of the nozzle and has the advantages of simplicity in test, rapidness, and the like.

A hand-held electronic celestial object-locating device assists in identifying a celestial object or directing a user to a desired celestial object. The device is useful for locating or identifying any celestial object including stars, constellations, planets, comets, asteroids, artificial satellites, and deep sky objects to name a few. The device utilizes sensors for 3-axis magnetic field and 3-axis gravitational field detection. The device utilizes a processor and an electronic database to perform the required calculations. The device's database may be updated through access to the Internet through which the updates may be purchased.

An asteroid microgravity surface touring mechanism comprises claw attachment devices (5), rotary drill devices (6) and creeping devices (7), and the claw attachment devices (5), the rotary drill devices (6) and the creeping devices (7) are mounted on a lander body (4). The creeping devices (7) are 6-degree-of-freedom mechanism arms, each group of the creeping devices include three creeping devices at intervals, and two groups of the creeping devices are alternate in attachment and movement to realize turning and integral translation movement of the touring mechanism. The claw attachment devices (5) are in annular array layout on the basis of bionic beetle microtrichia seizing attachment technology and used for providing ground normal attachment force to realize attachment to rough and hard asteroid surfaces. The rotary drill devices (6) are mounted at tail ends of the mechanical arms respectively, and a group of the rotary drill devices (6) provide the ground normal attachment force by means of inward oblique rotating. The asteroid microgravity surface touring mechanism has the advantage that reliable attachment of asteroid probes and continuous mobile survey of multiple target points are realized under uncertain conditions of asteroid microgravity environments and surface terrain geological characteristics.

The present invention relates to an asteroid attachment trajectory robust optimization method, belonging to the technical field of planetary landing. The method comprises a step of using a linear covariance method to deduce the error spreading equation of an asteroid attachment process according to the mathematical model of uncertain factors of an initial state, thrust direction and size, a target celestial parameter and the like, a step of achieving the purposes of suppressing error spreading and improving landing trajectory robustness are achieved through introducing a tracking guide strategy in the trajectory optimization process. According to the method, the fuel consumption in a lander attaching process can be saved, at the same time, the influence of parameter uncertainties on trajectory can be reduced. According to the asteroid attachment robust optimization method, the linear covariance method is used to quantitatively describe the influence of random variables on a landing process, a tracking guide strategy is considered in the trajectory optimization process, thus the spread of various errors can be inhibited in the tracking process, and the purpose of improving the landing precision is achieved.

The invention provides a twin asteroid detection autonomous cooperation optical navigation method, which belongs to the field of autonomous navigation. The method provided by the invention comprises the steps that when the position of a main star is known and the position of a slave star is not known, the dynamic equation of detectors is established under the inertial coordinate system of a double-asteroid system; according to the navigation system used by the detectors, the line-of-sight observation model of the main star and the slave star and a ranging angle measurement model between the detectors are established; an unscented Kalman filter for twin asteroid navigation is designed; orbital prediction gives the position and velocity of two detectors and the priori estimate of the position of the slave star as the initial state; the dynamic equation and an observation equation are combined, and the unscented Kalman filter is used for estimating to determine the position and velocity of two detectors and the position of the slave star in real time. According to the invention, the method has the advantages of good real-time performance and high navigation precision; the unscented Kalman filter is used for estimation, which does not need to linearize a nonlinear system, and does not need to calculate a Jacobian matrix; and the method has the advantages of simple implementation and good convergence.

A hand-held electronic celestial object-locating device assists in identifying a celestial object or directing a user to a desired celestial object. The device is useful for locating or identifying any celestial object including stars, constellations, planets, comets, asteroids, artificial satellites, and deep sky objects to name a few. The device utilizes sensors for 3-axis magnetic field and 3-axis gravitational field detection. The device utilizes a processor and an electronic database to perform the required calculations. The device's database may be updated through access to the Internet through which the updates may be purchased.

The invention belonging to the technical field of polymer synthetic chemistry relates to a preparation method of an ABC miktoarm star-structured polymer. The Omega-end contains both protective hydroxyl and active hydroxyl or sulfhydryl compound as initiators, the active hydroxyl or the sulfhydryl are utilized to initiate a second monomer to carry out ring-opening polymerization, after being blocked, the polymerized active hydroxyl becomes inert group, and then the protected hydroxyl in the middle of a chain section is deprotected under the acidic environment. The hydroxyl is utilized to initiate a third monomer to carry out ring-opening polymerization, or after the hydroxyl is modified as a bromine atom, the third monomer is initiated to carry out atom transfer radical polymerization, or after the hydroxyl is modified as trithiocarbonate group, the third monomer is initiated to prepare the ABC miktoarm star-structured polymer by reversible addition fragmentation chain transfer (raft) polymerization. The invention can combine different polymerization mechanisms to broaden the types of ABC miktoarm star-structured polymer.

The invention relates to an asteroid orbital transfer method. According to the asteroid orbital transfer method, an asteroid orbit is changed through a tether formation flight system composed of a solar sail and an asteroid. The asteroid orbital transfer method comprises the steps that the solar sail backwards and horizontally throws out a tether lock connected with a tether, the solar sail captures the tether lock after circling the asteroid for a circle, and is in butt joint with the tether lock, and then the tether is retracted so that the tether can be bound to the surface of the asteroid; the solar sail is thrown off through autorotation of the asteroid; the light pressure borne by the solar sail is adjusted by adjusting the posture of the solar sail, acting force is transmitted to the asteroid through the tether, and the autorotation speed of the asteroid is gradually reduced through the acting force; after the autorotation speed of the asteroid is reduced, the asteroid is transferred to a low-energy transfer orbit through adjustment of the posture of the solar sail. The asteroid orbital transfer method has the advantages that the threat caused by the asteroid to the earth is removed, the structure and the ingredients of the asteroid cannot be damaged, long-term orbital transfer can be carried out, and therefore the asteroid can be controlled to serve as a transfer station for interplanetary exploration of the human.

The invention discloses an autonomous navigation method for a satellite relative to asteroid vision. The method comprises the following steps: designing a theoretical flight track parameter of the satellite in order to track and observe an asteroid; establishing an autonomous navigation system state model according to a track dynamical model of the satellite relative to a target asteroid under a geocentric inertial coordinate system; proposing a theoretical light condition and an imaging condition which is met by a satellite star sensor shall in order to observe the asteroid; calculating a theoretical azimuth angle and pitch angle of the asteroid relative to the satellite; adjusting a practical optical axis of the satellite star sensor to be consistent to a theoretical direction; practically observing the asteroid and establishing an observation equation which takes a unit direction vector and a distance as observed quantity; and adopting Unscented kalman filtering for establishing satellite position and velocity. According to the invention, the position error of the satellite can be effectively corrected; the navigation precision can be increased; the method is suitable for the autonomous navigation of the satellite for tracking the target asteroid; high-precision navigation information is supplied to the satellite for tracking the target asteroid; and a reference is supplied for the design of an autonomous navigation system for the satellite.

This system of the control and protection of the terrestrial climate relies mainly on civilian airlines burning (preferably price-subsidized) sun-shading (sun-blocking/sun-reflective) fuels in the high levels of the atmosphere in order to reduce the intensity of the solar radiation reaching the Earth's surface. The use of sun-blocking airline fuels for the protection of the Earth from solar radiation parallels the use of sun-blocking skin-creams for the protection of the individual. The invention parallels the cooling effect on the Earth's climate caused by major volcanic eruptions, collisions of the Earth with asteroids, or the cooling effect one could expect after a major nuclear war. This invention proposes the creation of a controlled mini “nuclear winter”, in other words of a cooling caused by the increased refraction of the atmosphere or by the increased shading of the terrestrial surface by particulates in the high levels of the atmosphere.

The invention provides an optical and pulsar fusion type self-navigating method based on observability analysis. The optical and pulsar fusion type self-navigating method comprises the following steps of firstly, mounting an optical sensor and a pulsar sensor on a detector to respectively detect a gazing direction of a single asteroid and time that pulse reaches the detector; secondly, respectively establishing an observation equation of optical navigation and an observation equation of pulsar navigation, and combining the observation equations to be an observation equation of a fusion navigation system; and finally, selecting an asteroid capable of being detected and a pulsar as measurement navigational stars, and calculating a navigation position and a navigation speed by using standard Kalman filtering.

Some implementations include a method for operating a centrifuge-based-flight simulator in at least one of several different modes: a heightened G-force mode, a normal G-force mode; and transition modes (i.e., ramp-up or ramp-down modes) between the heightened G-force and normal G-force modes. During the normal-G-force mode the simulator ceases planetary motion altogether or substantially decreases rotations to replicate a plurality of flight conditions that physically imparts, on the trainee during operation of the simulator, a G-force that is not greater than approximately one (1) G. The reduction of planetary motion while maintaining realistic motion and force sensations that are appropriate for the virtual-flight conditions being experienced allows realistic flight simulation experience for the trainee and reduces the negative effects of constant planetary motion.

The invention discloses a symmetrical rotary excavating and pneumatic conveying composite sampler suitable for asteroid. The symmetric rotary excavating and pneumatic conveying composite sampler comprises a detector interface, gas pipelines, gas valves, unfolding outer cylinders, unfolding inner cylinders, flexible corrugated pipes, mounting flanges, a sampling front end, a closing channel, a flexible channel, a lower unfolding channel, an upper unfolding channel, a recovery channel and a sample recycling container; wherein the unfolding outer cylinders are connected with the detector interface through a flange structure; the gas pipelines and the gas valves are arranged inside the unfolding outer cylinders respectively; the flexible corrugated pipes are connected with the sampling front end through the mounting flanges; the closing channel, the flexible channel, the lower unfolding channel and the upper unfolding channel are sequentially connected; the sampling front end is connectedwith the closing channel; the upper unfolding channel is connected with the recycling channel, the sample recycling container is connected with the recovery channel; the sample recycling container andthe recovery channel are all positioned inside the detector interface. According to the device, the sampling which is strong in geological characteristic adaptability, low in reaction force, simple and reliable, fast and efficient is achieved.

The invention discloses an asteroid orbit identifying method based on observation angle data. The method comprises steps as follows: calculation of the change rate, that is, calculation of the observation angle data along with the time change rate; calculation of the angular velocity; screening of the angular velocity: the angular velocity of a current observation arc section is compared with a given threshold, and whether data of the section belong to an asteroid or a man-made earth satellite or are undetermined is judged preliminarily; correlation judgment: observation forecast is performed by using orbit elements of the catalogued man-made earth satellite, theoretically calculated values and measured values of all observation epochs are compared, if the error is small enough, the arc section is judged to belong to the man-made earth satellite, and otherwise, the arc section belongs to the asteroid. The method is convenient and easy to implement, can be applied to multiple research fields related to astronomical observation as well as quick recognition of near-earth asteroids, and wins precious early warning and emergency time for follow-up work.

The invention discloses a landing detecting sensor and a landing area obstacle detecting method for planetoid detection. The landing detecting sensor comprises an optical system and an electronic system. The optical system emits four measuring light beams to the surface of a planetoid so as to form four measuring points in the surface of the planetoid, wherein the four measuring light beams are located in different directions and every three measuring points are not in the same straight line. The optical system measures the distance information of each measuring light beam. According to the distance information d of the th measuring light beam, an azimuth angle [theta], and a pitch angle [phi], the electronic system acquires a position vector n = d[cos[phi]cos[theta] cos[phi]sin[theta] sin[theta], acquires a plane normal vector intersection angle of every two planes according to the position vector, compares the plane normal vector intersection angles with a predetermined value, and determines that the four measuring points are in the same plane if all plane normal vector intersection angles are less than the predetermined value or otherwise, determines that the four measuring points are not in the same plane. A problem of fast determining the relative distance between the landing detecting sensor and the planetoid and a problem of landing area obstacle detection are solved.