An Analytical Guidance Method for the Martian Atmosphere Entry Section with Parachute Opening Point Altitude Tracking

A technology of height tracking and entry section, which is applied in the field of deep space exploration and can solve problems such as the loss of height at the opening point

Active Publication Date: 2020-06-16
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Claims
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Problems solved by technology

In the actual flight process, when there are uncertainties in the state of the atmospheric entry point and system parameters, and there are disturbances such as gusts of wind during the flight, the trajectory tracking correction process will cause the altitude loss of the parachute opening point

Method used

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  • An Analytical Guidance Method for the Martian Atmosphere Entry Section with Parachute Opening Point Altitude Tracking
  • An Analytical Guidance Method for the Martian Atmosphere Entry Section with Parachute Opening Point Altitude Tracking
  • An Analytical Guidance Method for the Martian Atmosphere Entry Section with Parachute Opening Point Altitude Tracking

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Embodiment 1

[0087] Such as figure 1 As shown, a method for designing an analytical guidance law for the atmospheric entry section of a parachute opening point height tracking disclosed in this embodiment, the specific steps are as follows:

[0088] Step 1. Establish the dynamic model of the probe in the Mars atmosphere entry section, and solve the nominal trajectory according to the initial conditions;

[0089] The motion state vector of the detector is x=[r, θ, φ, γ, ψ] T , with energy E=μ / r-V 2 / 2 is the independent variable, then the dynamic model of the atmospheric entry section is formula (1):

[0090]

[0091] Among them, r is the distance between the probe and the center of mass of Mars, V is the speed of the probe, θ is the longitude, φ is the latitude, γ is the flight path angle, ψ is the azimuth, ψ=0 means pointing east, and the roll angle σ is unique The control variables of , D and L are the lift force and drag acceleration received by the detector respectively, and the ...

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Abstract

The invention discloses a Mars atmosphere entry section analytic guidance method with umbrella opening point height tracking, wherein the method belongs to the field of deep space detection. The method comprises the following steps of establishing a Mars atmosphere entry section detector dynamic model; solving an analytic guidance law for tracking the umbrella opening point height according to a small perturbance theory; setting a guidance target to a weighted value of the umbrella opening point height and the umbrella opening point voyage, solving a costate control variable according to the guidance target, realizing re-designing and storage of the costate control variable, introducing the solved costate control variable into the analytic guidance low for tracking the umbrella opening point height; dividing Mars atmosphere entry section guidance into four periods of pre-deflection, voyage tracking, voyage-height tracking and transverse voyage tracking, and applying the analytic guidance low for tracking the umbrella opening point height in the voyage tracking period and the voyage-height tracking period. The method has advantages of realizing simultaneous tracking for the voyage and height of the umbrella opening point through reasonably utilizing limited control capability of the detector, reducing umbrella opening point height loss and furthermore satisfying a voyage precision requirement.

Description

technical field [0001] The invention relates to an analytic guidance method for the Mars atmosphere entry section for tracking the height of the parachute opening point, and belongs to the field of deep space exploration. Background technique [0002] The Martian atmospheric entry stage is the initial stage of the probe's entry, descent, and landing process. The state of its parachute opening point (that is, the end of the atmospheric entry stage) and the parachute opening accuracy have an important impact on the final landing success or failure. Future Mars landing missions hope that the probe can land on the surface of Mars with high altitude and complex terrain with high precision. Correspondingly, improving the parachute opening height and parachute accuracy of the probe has become one of the key considerations when designing the guidance method for the entry phase. [0003] The Mars Science Laboratory mission adopts the terminal control guidance method in the atmosphere...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 崔平远赵泽端于正湜高艾朱圣英
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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