36 results about "Martian surface" patented technology

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 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.