242 results about "Planet Mars" patented technology

The invention aims at providing a Mars wind tunnel with sand and dust simulation. The wind tunnel is horizontally arranged in a vacuum container and comprises a collector, a stable section, a contraction section, a test section, an ejector section, an outlet diffusion section, an ejector, and a first diffusion section. The test section is connected with the first diffusion section; the first diffusion section is connected with the ejector section; the ejector section is connected with the diffusion section, a transitional equal straight section is arranged between the ejector section and the diffusion section, and the ejector is arranged at the inlet of the ejector section. The diffusion angle of the first diffusion section is not more than 5 degrees, and the cross section area of the inlet of the ejector section is larger than that of the outlet of the test section. Compared with the prior art, simulation of the wind speed of 5-100 m/s in a large-span range can be achieved under the air pressure of 100 Pa only by consuming a small amount of air, the flow field of the test section is uniform and stable, and the sand and dust environment of the Mars can be simulated under the low air pressure.

The invention relates to a simulation method of a Mars object for deep space exploration, which belongs to the field of deep space exploration application. In order to solve the problems in the prior art of lacking of a method for simulating the location, size, contour, imaging orientation and imaging gray level of Mars and existing technical gaps in engineering practices, the simulation method of the Mars object for deep space exploration is proposed. The simulation method includes transforming a center coordinate of Mars from a heliocentric ecliptic coordinate system to a display plane coordinate system and a projector coordinate system, calculating an imaging size of Mars according to an imaging field of view of a Mars explorer and the relative distance between Mars and the Mars explorer, simulating illuminated areas of Mars which are illuminated by the sun and unilluminated areas which are not illuminated by the sun, calculating an imaging orientation of the contour of Mars according to the relation of relative positions among the sun, Mars and the Mars explorer, and mapping a magnitude of Mars to the gray level of a computer to display on an interface. The simulation method of the Mars object for deep space exploration is applicable to the simulation software of deep space exploration.

The invention provides a combined autonomous navigation method of a mars exploration approach section. The combined autonomous navigation method comprises the following steps: the step 1 of using a spacecraft-mounted sun sensor to measure the viewing direction of the sun and using a spacecraft-mounted solar-spectrum velocity-measurement navigation sensor to measure the relative movement velocity of a mars explorer to the sun; the step 2 of using a wireless responder to obtain distance and relative velocity information with a mars surrounding device; the step 3 of establishing an orbital dynamics equation and establishing a navigation system model under a J2000.0 heliocentric ecliptic inertial coordinate system and using a corresponding navigation filtering algorithm to obtain autonomous navigation position and velocity information. The combined autonomous navigation method disclosed by the invention avoids depending on ground wireless information, can achieve autonomous navigation of a spacecraft in a flying process by only needing optical information from the sun and the wireless information from the mars surrounding device, can establish a system equation of an autonomous navigation system of the explorer, utilizes different navigation filter algorithms to achieve real-time estimation of navigation information of the explorer and is simple, easy, practical and free of time delay.

The invention discloses a method for predicting the surface flow transition position of a Mars entering device, and the method comprises the steps: carrying out computational fluid mechanics simulation based on a Mars atmosphere model by employing a thermochemical non-equilibrium model, and obtaining the streaming field data of the Mars entering device; generating a transition prediction grid by taking the molded line of the Mars entering device as a reference, and interpolating the streaming field data into the transition prediction grid to obtain transition prediction flow field data; calculating the total enthalpy of the flow field based on the transition prediction flow field data, obtaining the outer edge position of the boundary layer, carrying out the integral calculation on a first Reynolds number based on the momentum loss thickness in the boundary layer in the normal direction of the wall surface, and calculating a second Reynolds number based on the roughness height; and taking the first Reynolds number and the second Reynolds number as transition criteria, respectively calculating a first transition criterion and a second transition criterion, and obtaining the transition position of the surface flow of the Mars entering device based on the first transition criterion and the second transition criterion. Thus, the surface flow transition position of the Mars entering device can be predicted via the method.

The invention discloses a comprehensive environment heat balance test system for a Mars detector single-machine product. The system comprises a Mars environment simulation chamber, a solar irradiationsimulation system, a Mars atmosphere simulation system, a Mars surface wind simulation system, a temperature control system and a test piece support system, wherein the Mars environment simulation chamber is a horizontal and capsule-shaped cabin body, container gates which can be opened are arranged at the two ends of the cabin body, and the Mars environment simulation chamber is mainly used forforming a closed space without obvious leakage and maintaining a special atmospheric environment in the cabin. The system can provide comprehensive stress environment tests of five parameters including gas atmosphere, wind speed, pressure, solar irradiation and environment temperature on the surface of Mars, and is easy to operate and good in generalizability.

The invention discloses a star sensor and gyro combined calibration method suitable for Mars detection, and a Mars detector is allowed to complete the combined calibration of the star sensor and the gyro under any attitude reference in a full life cycle. In the steady-state flight process of the Mars detector, a calibration algorithm is constructed under the inertial reference according to measurement models of the star sensor and the gyroscope. Compared with the prior art, the star sensor and gyroscope combined calibration method suitable for the Mars detection has the advantages that the Mars detector can perform combined calibration of the star sensor and the gyroscope in any attitude in an inertial space, the calibration arc section is improved, and the reliability of the combined calibration of the star sensor and the gyroscope is improved.

The invention relates to a hybrid laser radar for Mars atmosphere detection. The hybrid laser radar comprises a single set of optical transceiver module for obtaining back scattering signals from Mars atmosphere molecules and dust; a coherent balance detection module which mixes the local oscillation light and the atmospheric echo signal into an intermediate frequency electric signal and converts the intermediate frequency electric signal into a high-speed analog electric signal, so a Mars atmospheric wind field is obtained through data processing; a single-photon direct detection module which is used for measuring photon electric signals of each channel to obtain photon count of each channel; and a data processing module which obtains the concentration of polarized light and Mars aerosol particles. The laser power and the echo signal stability are calibrated by using the signal-to-noise ratio of coherent detection and the photon number of direct detection, and the method is used for detecting the content of carbon dioxide gas. The hybrid laser radar has the advantages of large dynamic range and small data processing calculation amount by using single photon direct detection, and also has the advantages of high coherent detection sensitivity and good weak signal amplification performance, and the problem of multi-atmosphere parameter detection of the Mars atmosphere detection laser radar is solved under the condition that the load weight and complexity are not increased.

The invention relates to the technical field of deep space exploration, and discloses a deep space communication system suitable for a phobos detection task. On one hand, a Mars polar satellite running on a special polar orbit is arranged on the Mars side, obstacles between the detector and the Mars polar satellite are always prevented from appearing to block decimetric wave communication. The purpose of uninterrupted full period of the decimetric wave communication link from the phobos to the Mars is achieved; on the other hand, at least three revolution satellites around the sun are used asinter-planet relay satellites, the purpose that the laser wave communication link between the planets is not interrupted in the whole period can be achieved; and at least three geosynchronous satellites are used as satellite-ground relay satellites, so that the purpose of uninterrupted full period of the satellite-ground Ku wave communication link can be achieved, the purpose of uninterrupted fullperiod of the complete communication link from the phobos to the ground is finally achieved, and the phobos detection task is ensured not to be affected by communication interruption.

The invention discloses a multi-directional driving task autonomous management control method suitable for Mars detection. The method comprises the following steps: S1, according to driving constraints of a solar wing mounting and driving shaft of a Mars detector, a driving shaft of a directional antenna and a driving shaft of an X relay antenna, establishing a small-amplitude dynamic attitude reference capable of realizing multi-directional coverage on a nominal attitude reference in combination with an on-orbit sun vector, an earth vector and a lander vector, and providing a feasible attitude for autonomous management of multiple rotating parts; and S2, autonomously and dynamically tracking and pointing to respective targets according to a dynamic attitude reference established in the S1, a solar wing rotation range constraint, a directional antenna rotation range constraint and an X relay rotation range constraint, and autonomously feeding back the dynamic adjustment of the attitudereference after the rotation constraint range is exceeded so as to realize simultaneous pointing of multiple rotations. The method is simple and feasible, and the pressure of on-orbit time-sharing work of different rotating parts is reduced.

The invention provides a Mars rover moving system traction performance test device, andbelongs to the technical field of Mars detection test equipment. The test device comprises a support base for supporting a tested Mars rover; aresistance moment loading mechanism which is used for being connected with wheels of the tested Mars rover and loading resistance moment to the wheels of the tested Marsrover; a traction loading mechanism which is used for being connected with a body of a tested Mars rover and applying traction force to thetested Mars rover in the walking process of the Mars rover; and a vacuum tank and temperature control mechanism which is used for containing the tested Mars rover and controlling the control vacuum degree and temperature of the test environment. The resistancemomentloading mechanism and the traction force loading mechanism are both arranged in the vacuum tank and temperature control mechanism. Compared with the prior art, the performance test of the Mars rover moving system on the ground can be realized, the wheel load and the wheel resistance moment required by different geomorphic characteristics can be simulated, and the requirements of 0-3000N traction force loading technical indexes and loading precision can be met.

An autonomous mobile mechanically deployed spaceport is disclosed to provide a self-leveling stable landing pad for lunar and Martian descending and ascending spacecraft and which alleviates rocket plume blast effects upon surface soils and volatiles during spacecraft descent and ascent. The autonomous mobile mechanically deployed spaceport is a mechanically deployed unfolding flying landing pad to allow spacecraft to land on the Moon and Mars and alleviates rocket plume blast effects upon surface soils and volatiles.

The invention relates to an autonomous thrust system and method for the safety of the separation of a Mars exploration surrounding device. The system comprises a large thrust system, a small thrust system, and a non-thrust direction small thrust system, and can work in three working modes; under the first air injection mode, the large thrust system is used for the orbit control of the Mars exploration surrounding device; the small thrust system is adopted to control the Y-axis and Z-axis attitudes of a Mars detection surrounding device body coordinate system; in the first air injection mode, when the thruster in the small thruster system breaks down, the first air injection mode is switched to the second air injection mode; the large thrust system is adopted to control the Y-axis and Z-axis attitudes of the track of the Mars exploration surrounding device and the body coordinate system; in the first air injection mode, when the large thruster breaks down, the first air injection mode is switched to the third air injection mode; the large thrust system is adopted to control the Y-axis and Z-axis attitudes of the track of the Mars detection surrounding device and the body coordinatesystem; and in the three modes, the non-thrust direction small thrust system is adopted to control the X-axis attitude of the Mars detection surround device body coordinate system.

The invention provides a Mars rover moving system vibration loading mechanism and a performance testing device and belongs to the technical field of Mars detection testing equipment. The mechanismis used for carrying out vibration loading on a tested Mars rover and comprises a first vibration platform, a vibration loading assembly and a second vibration platform which are sequentially arranged from top to bottom, the first vibration platform is used for being arranged at the bottom of a wheel of the tested Mars rover, the vibration loading assembly is arranged between the first vibration platform and the second vibration platform, and the vibration loading assembly is connected with the second vibration platform. Compared with the prior art, the amplitude and frequency of the wheels are adjusted through the eccentric distance adjusting structure, single-degree-of-freedom vibration loading of the tested Mars rover within the range of 0-10 Hz is achieved, the mechanismis simple, testingis accurate, and precision is high.

The invention relates to a leg type landing and buffering device capable of being repeatedly used. The leg type landing and buffering device is characterized in that foot pads are connected with support leg main supporting columns through ball hinge connecting heads, metal rubber blocks are arranged between ball hinges and the foot pads, one-way dampers and long springs are arranged between innersleeves and outer sleeves, the one-way dampers do not have damp in the compression process and have damp in the stretching process, the long springs compress so that impact kinetic energy can be stored, after the maximum compression amount is reached, the one-way dampers work, the springs slowly restore to the original lengths, so that the attitudes of landing legs are restored, a load box is connected with an upper frame and a lower frame through a CR-type steel wire rope shock absorber, and is connected with an outer cylinder through a GS-type steel wire rope shock absorber, and the outer cylinder is connected with an inner cylinder through adjustable dampers and short springs. According to the leg type landing and buffering device, multiple shock isolation mechanisms are formed, so thatthe shock isolation efficiency is improved, and the leg type landing and buffering device can be repeatedly used, and is suitable for being used in landing and detection activities of planets such asthe earth, the moon, the mars and the minor planet.

The invention discloses a Mars probe autonomous orbit determination method by considering a sun vector, and the method enables a Mars probe to complete the orbit determination just through a sun sensor and a Mars sensor carried by the Mars probe in a sun-around flight process of a ground fire transfer section without depending on the ground support. The Mars detector performs orbit extrapolation according to the orbit recursion model; while the Mars sensor is used for measuring the position of the Mars probe relative to the Mars, solar vector measurement is introduced to further restrain the orbit extrapolation error. Compared with the prior art, the orbit determination method has the beneficial effects that the Mars detector can obtain stable observed quantity under the condition that a tracking Mars target is lost or a Mars sensor breaks down, and the reliability of orbit autonomous determination is improved.

The invention discloses an autonomous management method suitable for a propulsion system in Mars exploration. Faults of the propulsion system are divided into attitude control thruster leakage, rail control pipeline overpressure, pressure reducing valve static pressure overpressure, propulsion system underpressure and attitude control pipeline overpressure; the priority of the fault processing ofthe attitude control thruster leakage is the highest; the priorities of the fault processing of the other four faults are the same, and the fault processing is carried out in sequence according to a fault occurrence time sequence. According to the autonomous management method for the attitude control thruster leakage, a current thruster is switched out, so that other thrusters can be switched in.According to the autonomous management method for the rail control pipeline overpressure, a valve on a rail control pipeline is opened and closed. According to the autonomous management method for thepressure reducing valve static pressure overpressure, the pressure of a pressure reducing valve is reduced through gas path pressure balance. According to the autonomous management method of the propulsion system underpressure, a storage tank is pressurized; according to the autonomous management method for the attitude control pipeline overpressure, pressure relief is conducted on an attitude control pipeline. According to the method, the safety and reliability of the propulsion system in the whole Mars detection process are improved.

The invention relates to a dynamic imaging simulation method for a high-resolution optical camera of a Mars orbiter. The dynamic imaging simulation method comprises the following steps: S1, importingorbital dynamic parameters; S2, performing camera orientation parameter calculation and imaging model establishment; S3, importing a three-dimensional model and a visual position under the position, posture and illumination parameters; S4, generating a dynamic simulation image; s5, generating a multispectral and panchromatic image; and S6, simulating various degradation effects: for the generatedsimulation images, considering the influence of geometric factors, optical device degradation factors and transmission distortion factors on the images, respectively establishing influence models, andsequentially calculating various influenced simulation images according to pixel-level traversal to generate final simulation degradation images. Compared with the prior art, the method considers various degradation effects such as satellite geometric offset, optical device degradation, transmission distortion influence and the like, dynamically generates optical simulation images under various influence factors, and has dynamism, tightness, simulation and transportability.

The invention discloses a collaborative dynamic path planning method for multiple Mars aircrafts, and belongs to the technical field of Mars exploration. The method comprises the following steps: firstly, determining an off-line cooperative path of a Mars aircraft in a known threat environment by using an off-line cooperative path planning method, and realizing designated area coverage and off-line obstacle avoidance for known threats; secondly, determining a condition that the Mars aircraft detects unknown threats in advance and a starting point and an ending point of local dynamic path planning; and finally, determining a local dynamic obstacle avoidance path of the Mars aircraft to the new threat by using a local dynamic path planning method, and merging the obtained offline cooperative path and the local dynamic path to obtain a final flight path of the Mars aircraft. The multi-Mars aircraft path planning method provided by the invention not only can perform offline collaborative search detection, but also can perform local dynamic obstacle avoidance, meets the requirements of Mars aircraft detection tasks, and has a relatively good engineering application value.

The invention relates to a spark surface gas component simulation device and method. In order to solve technical problems that an existing ground simulation scheme has large simulation errors and cannot truly and accurately simulate the pressure environment of the surface of Mars, the invention provides a device and a method for simulating gas components on the surface of Mars. The gas componentson the surface of the Mars are considered to the maximum extent, an atmospheric state of the Mars can be simulated close to the actual atmospheric state, and technical support is provided for a real and accurate environment simulation test of a Mars detector on the ground.