30 results about "Mars landing" patented technology

The invention provides an anti-interference composite online guiding method of the atmosphere entering period of a Mars lander. The method includes the following steps of a, establishing a Mars lander atmosphere entering period kinetic model, and introducing Mars atmosphere density uncertainty interference into the Mars lander atmosphere entering period kinetic model; b, establishing an interference observer, wherein the interference observer estimates the Mars atmosphere density uncertainty interference; c, designing a prediction-correction guiding rule, wherein the prediction-correction guiding rule updates to-be-determined parameters of the heel angle amplitude; d, compositing the interference observer in the step b with the prediction-correction guiding rule in the step c to obtain an anti-interference composite guiding rule, wherein the anti-interference composite guiding rule complements for the Mars atmosphere density uncertainty interference through the estimation value of the Mars atmosphere density uncertainty interference.

The invention provides a static locating method for a mars lander based on a surrounder, based on tracking and measuring a detector, the wireless distance and speed measurement between the surrounder and the lander is measured; the surrounder emits a wireless signal in a manner of double-trip measurement; and after being in transparent transmission of the lander, the wireless signal is sent to the earth to be treated by the mars measuring data. The landing locating precision obtained by multi-circle measurement of the lander can reach dozens km magnitude. The static locating method for a mars lander based on a surrounder provided in the invention can help the ground tracking and measuring and make up the defects of long underground flame distance and hard tracking and measuring difficulty of the lander; and the use ratio of the equipment on the mars can be improved without increasing extract cost by the equipment on the surrounder.

The invention discloses a heat insulation component for heat control of a Mars Landing machine. The heat insulation component comprises a thin layer structure, structure support pieces, first aerogel blocks, second aerogel blocks, honeycombs and skins, wherein the second aerogel blocks are filled inside the honeycombs and clamped between the upper skin and the lower skin so as to form a honeycomb plate, the first aerogel blocks and the structure support pieces are arranged on the first surface of the honeycomb plate, the thin layer structure is covered on the outer surface of the first aerogel blocks, and both the first aerogel blocks and the second aerogel blocks are composite SiO2 aerogel materials. The invention further discloses a manufacturing method for the heat insulation component. By utilizing the heat insulation component based on SiO2 aerogel, the problem that the aerogel material is difficult to use due to poor mechanical property is solved, and the heat insulation component is excellent in heat insulation performance and capable of effectively meeting requirement on heat insulation under the environment on the surface of the Mars, has obvious effect of light weight, can reduce the weight of a Mars lander, and is resource saving.

This disclosure proposes a method and system for determining a Mars landing site based on the yield rate of Martian dust devils, including: acquiring high-resolution Mars remote sensing time-series image pairs in the same area at different times; identifying the acquired Mars remote sensing time-series image pairs to obtain Mars landing newly generated dust devil trajectory in the area; based on the above trajectory, obtain the overlapping area of ​​the Mars landing area, the observation time interval, and the number of newly generated dust devil objects observed in the image pair to calculate the dust devil yield rate; calculate the landing area image Centering, the coverage area of ​​the dust devil object track newly generated in each Martian day, and then calculate the number of Martian days required to cover the entire landing area area on the basis of the newly generated dust devil track area in each Martian day, namely Mars rover solar panel cleaning cycle; determine the Mars landing site based on the dust devil production rate and the Mars rover solar panel cleaning cycle. Select the landing and inspection area with the optimal cleaning cycle for the subsequent Mars rover inspection mission after a successful Mars landing.

The invention provides a device for centering postures of a Mars landing capsule. The device comprises a base plate (1), a support (2), a connecting shaft (3), a torsional spring (4), a centering ring (5) and a compressing and releasing device (6). Under the conditions that the size, the weight and the energy supply of the device are limited strictly, an initiating explosive device acts to release the compacted torsional spring, and therefore the centering ring is driven to center the postures of the Mars landing capsule. The device for centering the postures of the Mars landing capsule has the advantages of being simple in structure, safe, reliable, small in size and light in weight. As the effective means for guaranteeing the correct postures of the landing capsule on the Mars, the device for centering the postures of the Mars landing capsule can be directly applied to development for a landing capsule in the first Chinese Mars landing detecting task, and can also provide reference for design of Chinese follow-up small-scale planet landing capsules.

The invention discloses a method for estimating the interruption of Mars atmosphere entry capacity based on multiple models, relates to a method for estimating the interruption of Mars atmosphere entry capacity, and belongs to the technical field of deep space exploration. The implementation steps of the present invention are as follows: Step 1: Establish the dynamic equation of the Martian atmosphere entry section. Step 2: Establish the radio measurement model and the radio measurement interruption model of the Martian atmosphere entry section, which are used in step 3 to correct the position and velocity information of the probe. Step 3 combines the radio model, interruption model and filtering algorithm of step 2 to solve the state of the detector, and estimate the state of the detector. The invention can effectively suppress the divergence problem of the state estimation of the detector when the radio measurement is interrupted, and improve the reliability and state estimation accuracy of the autonomous navigation system of the detector in the Mars atmosphere entry section. The invention can provide technical support and reference for the design of the radio navigation scheme adopted in the atmospheric entry section in the future Mars landing detection.

The invention discloses an aerodynamic layout structure of a Mars landing patrol device, relates to the technical field of aerodynamic layout of the patrol device, and comprises: a cabin body, which is a revolving body structure, and the cabin body includes a head and a rear body arranged sequentially from bottom to top , transition body and tail; the center of mass of the cabin is set on one side of the axis of the rotary structure; the trim wing is telescopically embedded in the rear body, and the trim wing is set on the other side of the axis of the rotary structure. When it is out, the angle of attack of the Mars landing rover can be changed to 0°; the aerodynamic layout structure of the Mars landing rover offsets the center of mass of the cabin, and the rover can enter at an angle of attack without deploying the trim wings. Extend the trim wing in front of the parachute, so that the angle of attack of the patrol device returns to 0°, ensuring the safety of the parachute, which greatly shortens the use time of the trim wing and reduces the requirements for the action mechanism and heat protection system of the trim wing.

A parachute evasion method for a Mars lander based on off-line analysis of parachute landing points, involves the field of guidance and control technology, and aims at the problem that the parachute back cover assembly will cover the lander when the lander is separated from the parachute back cover assembly in the prior art. Problem, this application uses the Monte Carlo simulation method to determine the distribution of the landing point of the parachute back cover assembly offline, and uses the aerodynamic parameters to pull the deviation to ensure that the shortest and longest empty time of the parachute and the combination of different wind directions are included in the simulation In the above, the parachute scatter ellipse covers various extreme conditions, and the results are more conservative and reliable. During the landing process, the landing point of the lander is predicted based on polynomial guidance, and the maneuvering is only applied to the situation where the parachute falls within the scattered area of ​​the parachute, and the maneuvering goal is to make the lander move the shortest distance to reach outside the parachute scattered area.

A method for the atmospheric entry section navigation of a mars lander based on a sampling point inheritance strategy relates to the technical field of navigation guidance and control, in particular to a method for the atmospheric entry section navigation of the mars lander. The invention aims at solving the problem that the precision is low when the status of the lander is estimated according to the conventional filtering method. The method comprises the following steps: in a filtering beginning cycle, providing a sampling point and a sampling point weight according to sampling point generating rules of unscented Kalman filtering; providing a lander status predicted value x' and a lander status variance Px according to a transmitted sampling point and a generated weight; calculating a measurement predicted value y', a variance Py and a covariance Pxy according to unscented Kalman filtering rules; updating measurement and correcting the estimate value of the lander status; estimating x'<+> and a lander status variance Px<+> according to the lander status, correcting the transmitted sampling point Xi and obtaining the sampling point Xi<+> with the corrected value. The method has higher status estimate precision and is suitable for navigation in the atmospheric entry section of the mars lander.

A multi-strategy obstacle avoidance logic and control method for Mars landing adopts a cooperative control strategy of coarse obstacle avoidance and parachute-back cover combination avoidance for a new requirement of unified avoidance of a parachute-back cover combination and landform obstacles in the aspect of control strategy. In a hovering fine obstacle avoidance stage, on the basis of laser three-dimensional imaging, a redundancy strategy of binocular fine obstacle avoidance by using an optical obstacle avoidance sensor and a multifunctional obstacle avoidance sensor optical obstacle avoidance module is added. According to the strong time sequence requirements of mars in the entering, descending and landing processes, working time sequences of data transmission, information interaction and the like among an entering and descending control unit, a multifunctional obstacle avoidance sensor and a optical obstacle avoidance sensor are provided, and it is guaranteed that the obstacle avoidance task is completed autonomously and rapidly in a short time.

The invention relates to a Mars lander anti-interference controller under the harmonic interference at an unknown frequency. Firstly, an attitude kinematics and dynamics model for a Mars lander is built up. Secondly, the harmonic influence caused by structural uncertainty during the severe friction with the atmosphere is determined for a lander engine, and the disturbing influence of the unknown-frequency harmonic on an interference observer is estimated. Furthermore, the compensation is conducted by a feed-forward path. Thirdly, a gesture instruction is tracked by a sliding-mode controller. Finally, the interference observer for the unknown-frequency harmonic and the sliding-mode controller are combined to construct an anti-interference controller. The anti-interference controller is strong in anti-interference property. Compared with a conventional Mars lander controller, the above Mars lander anti-interference controller is better in adaptability and anti-interference capability.

The present invention relates to a Mars landing track optimization control method based on convex optimization. The method comprises the following steps of: (1) establishing a Mars landing dynamical model and performing convex optimization; (2) taking fuel optimization as a target to perform single off-line optimization to obtain a nominal track; and (3) employing a moving horizon model to performprediction and control to perform track of the nominal track to complete landing control. Compared to the prior art, the convex optimization and the moving horizon model prediction and control are effectively combined to effectively reduce the accumulated errors caused by modeling errors and interferences and improve the landing precision.