Spacecraft and landing method

A spacecraft configured to carry out an attitude change to a target attitude angle for a vertical landing after reentry into the atmosphere in a nose entry and to land after the attitude change, comprising:

• a body;
• a rocket engine installed on the body;
• an aerodynamic element which is installed on the body and on which an aerial force acts;
• a measurement quantity acquiring system configured to acquire at least one measurement quantity of the spacecraft;
• and
• a control device configured to calculate an operation quantity for an operation of at least one of a gimbal angle of the rocket engine and an aerodynamic characteristic of the aerodynamic element,
• wherein the at least one measurement quantity contains an angle-of-attack of the spacecraft, and
• wherein the control device is configured to calculate the operation quantity such that the attitude angle of the spacecraft changes to the target attitude angle according to the said angle-of-attack in the attitude change.

A landing method of a spacecraft which comprises a body;

• a rocket engine installed on the body;
• and an aerodynamic element installed on the body for an aerial force to act,
• the landing method comprising:
• (A) reentering a spacecraft into the atmosphere in a nose entry;
• (B) carrying out an attitude change of the spacecraft such that an attitude angle of the spacecraft changes to a target attitude angle in which a vertical landing is carried out, after the (A) step;
• and
• (C) carrying out the vertical landing of the spacecraft after the attitude change,
• wherein the (B) step comprises:
• acquiring at least one measurement quantity of the spacecraft;
• and
• calculating an operation quantity to operate at least one of a gimbal angle of the rocket engine and an aerodynamic characteristic of the aerodynamic element according to the measurement quantity by a non-linear optimal control using a stable manifold method such that the attitude angle of the spacecraft changes to a target attitude angle.