36 results about "Martian surface" patented technology

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.

The present invention relates to an anti-interference fault-tolerant control method of a Mars lander. Firstly, building the attitude kinematics and the dynamics model of the Mars lander; secondly, designing a wind interference estimator to estimate the gust influence on the Mars lander aiming at the influence of the gust at the powered lowering stage at the surface of the Mars so as to perform compensation through a feedforward channel; thirdly, designing an execution mechanism partial failure observer to estimate and compensate the partial failure value of the Mars lander execution mechanism; and finally, recombining the gust interference estimator, the execution mechanism partial failure observer and a PD attitude controller, and constructing a fault tolerance controller of partial failure of the Mars lander execution mechanism. The anti-interference fault-tolerant control method of Mars lander has high anti-interference ability and high reliability, and has a higher practical engineering value compared with a traditional Mars lander control method.

The invention relates to a geometrical orbit and gesture determining method and system for deep space landing and a deep space lander. The method comprises the following steps: firstly, determining adirection vector of the lander relative to the Mars and the distance from the lander to the center of the Mars; solving the height from the lander to the surface of the Mars according to the distancefrom the lander to the center of the Mars and the radius of the Mars; establishing an inertial coordinate system xIyIzI to obtain a gesture matrix from the inertial coordinate system to a body coordinate system; further solving the inertial position and the inertial speed of the lander. According to the method and system, geometrical orbit and gesture determination is carried out by using a distance and speed measuring sensor automatically. Under the circumstance that IMU in a power falling section fails, orbit and gesture determination can be carried out by means of the distance and speed measuring sensor so as to achieve initial standard capturing of autonomous navigation, the dependent degree of the inertial navigation system to the initial standard is alleviated, and the robustness andthe failure tolerant capability of the autonomous navigation system of soft landing are improved. The algorithm is an analytical algorithm which is convenient for on-star algorithm, thereby laying afoundation for implementing a soft landing task successfully.

The invention discloses a Mars floating detection system. The system comprises a floating system, an inflation system and a landing cabin, wherein the floating system comprises an overpressure balloon, a tying rope, an instrument cabin and a track controller, the track controller comprises a main rod, a main wing, an empennage and a balance weight, the main wing is connected to the middle of the main rod, the empennage and the balance weight are arranged at the two ends of the main rod respectively, the instrument cabin is tied below the overpressure balloon through the tying rope, and the track controller is tied below the instrument cabin; the inflation system is arranged in the landing cabin and used for inflating the overpressure balloon. The system is carried by a lander to reach thesurface of the Mars, and when the meteorological condition of the surface of the Mars is good, the inflation system inflates the overpressure balloon until the floating system lifts off and is separated from the landing cabin; then the floating system is separated from the inflation system, and the inflation system is left in the landing cabin; and after the floating system reaches a preset height, detection work is started, and different areas are detected through Mars atmospheric motion. Movement is not limited by Mars topography and geomorphism, and the detection range is wider.

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 belongs to the technical field of spaceflight test control and relates to a design method of aerospace instruments, in particular to a design method for repeatedly using a floating detector system on the Martian surface. The floating detector system is composed of a floating detector, a mooring rope, a mechanical arm and a movable floating detector base. The design method comprises six steps and has the advantages that the floating detector system can be used repeatedly, survey with unlimited times on one area of the same Martian target location can be achieved in theory, and different three-dimensional weather resource collection of flying height of the flying detector can be achieved in different time periods of the same area.

The present invention relates to a Mars environment simulation experiment device and an experiment method. The experiment device comprises: a vacuum cabin body for providing a vacuum environment; a vacuum control unit connected with the vacuum cabin body for forming a vacuum in the vacuum cabin body Environment; a humidity control unit, comprising a temperature-controlled heater, an airtight container placed on the temperature-controlled heater, and a gas configuration part communicated with the airtight container, deionized water is contained in the airtight container, and the The gas configuration part communicates with the vacuum cabin body; the gas supply unit communicated with the gas configuration part is used to provide Martian atmosphere. The invention can truly simulate the environmental atmosphere, humidity, pressure, temperature and ultraviolet radiation conditions on the surface of Mars, and at the same time realize the precise control of the above-mentioned environmental humidity, pressure, temperature and ultraviolet radiation on the surface of Mars, and can also realize the electric field environment on the surface of Mars The simulation provides a comprehensive experimental platform for Mars environment-related research, with a wide range of applications.

The invention discloses a semi-analytic Mars entry guidance method, comprising the following steps: taking the lander of the Mars atmosphere entry section as the research object, setting the Mars atmosphere to be stationary relative to the Mars surface, and giving the definition of the Mars fixed coordinate system and the coordinates The three-degree-of-freedom center-of-mass motion equations of the lander under the system; the three-degree-of-freedom center-of-mass motion equations of the lander under the fixed coordinate system of Mars are processed to obtain a numerical prediction model for the terminal longitudinal error, considering centrifugal acceleration and At the same time, the prediction model is updated online to ensure high-precision longitudinal error prediction; taking the predicted terminal longitudinal error as the correction object, the principle error generation mechanism of ETPC guidance is analyzed and improved, and the analysis method is designed. Terminal pitch error correction. The invention obviously improves the landing precision, and the obtained parachute opening point spread is very close to the calculation result obtained by the high-precision NPC guidance, which shows the validity of the method.

The invention relates to a Mars in-situ spectroscopic combination experiment device and an experimental method. The experimental device includes a Mars environment simulation experiment device for simulating the Martian surface environment and an in-situ spectroscopic combination for in-situ spectrum testing in a Martian environment The experimental device, wherein the Mars environment simulation experiment device includes a vacuum cabin, a vacuum control unit connected to the vacuum cabin, a humidity control unit connected to the vacuum cabin, a first air supply unit connected to the humidity control unit, and a vacuum control unit connected to the vacuum cabin. The temperature control unit connected with the body; the in-situ spectrum test simulation experiment device is arranged outside the vacuum chamber, and is used for the joint test of the remote Raman spectrum and the remote LIBS spectrum. The present invention can truly simulate the Martian environment including temperature, humidity and atmosphere, and can also conduct in-situ testing on the spectrum of mineral samples in the Martian environment, to study the influence of environmental parameters on the spectrum of mineral samples, and at the same time perform single and multi-dimensional analysis of mineral content Quantitative analysis of variables.

The invention discloses a self-rotating rotorcraft using the random detection of Martian atmospheric circulation and its use method, which includes a rotor shaft and a rotor hub, and also includes a wind sensor, a foldable blade, a propeller, a fuselage and a rudder surface, the The wind sensor is set on the top of the rotor hub to monitor the wind direction and wind speed on the surface of Mars. The foldable blade is installed on the top of the rotor shaft through the rotor hub. It is in a folded state when launching, and the blade unfolds after reaching the surface of Mars. The number of the propellers is 4, which are arranged in the shape of a "ten" at the root of the rotor shaft; the rudder surface is symmetrically arranged on the upper surface of the fuselage, and the upper surface of the fuselage is also provided with solar cells; the inside of the fuselage A storage battery connected to the solar cells is provided. The present invention is different from the current scientific detection forms of Mars orbiter and landing patrol device, and utilizes Martian atmospheric circulation to carry out random on-site detection, which can be applied to the "Mars Green Home" project, and has a broad application prospect in the field of deep space detection.