A bumper is provided on an outer side of a structural body of a spacecraft with a predetermined gap between the bumper and the structural body. The bumper includes: a first layer that is provided on the outer side and that is formed from an impact resistant material; a second layer that is provided on an inner side being on a side of the structural body with respect to the first layer, the second layer having holes; and a third layer that is provided on the inner side with respect to the second layer, the third layer including a resin.

A bumper is provided on an outer side of a structural body of a spacecraft with a predetermined gap between the bumper and the structural body. The bumper includes: a first layer that is provided on the outer side and that is formed from an impact resistant material; a second layer that is provided on an inner side being on a side of the structural body with respect to the first layer, the second layer having holes; and a third layer that is provided on the inner side with respect to the second layer, the third layer including a resin.

A pressurized structure panel for forming a pressurized space pressurized inside includes a panel structure having a panel body to receive the pressure, a rib provided in the panel body, and a hollow part formed by the panel body and the rib, a radiation shielding material provided in the hollow part, and a debris bumper provided outside the panel structure and provided spaced apart from the panel structure by a certain spacing. The radiation shielding material includes a material containing hydrogen atoms in molecules.

A pressurized structure panel for forming a pressurized space pressurized inside includes a panel structure having a panel body to receive the pressure, a rib provided in the panel body, and a hollow part formed by the panel body and the rib, a radiation shielding material provided in the hollow part, and a debris bumper provided outside the panel structure and provided spaced apart from the panel structure by a certain spacing. The radiation shielding material includes a material containing hydrogen atoms in molecules.

A method for estimating collision between a satellite in orbit and at least one piece of space debris having a time of closest approach to the satellite is disclosed including: obtaining the reference orbit of the satellite; determining an ephemeris of state transition data representative of the trajectory of the reference orbit; communicating the reference orbit and the ephemeris of state transition data to the satellite. The method includes the steps on board the satellite of: determining the true orbital position of the satellite; propagating the true orbit; calculating a probability of collision between the satellite and the piece of debris.

A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

A self-healing shield panel for protecting a spacecraft against High Velocity Particles (HVPs). The self-healing shield includes an exterior layer and an interior layer connected to define a cavity which contains a dilatant fluid with a plurality of spheroids. The kinetic energy from HVP impact is dispersed by the plurality of spheroids and absorbed by the dilatant fluid. The plurality of spheroids within the cavity move to block a puncture hole in the shield.

A self-healing shield panel for protecting a spacecraft against High Velocity Particles (HVPs). The self-healing shield includes an exterior layer and an interior layer connected to define a cavity which contains a dilatant fluid with a plurality of spheroids. The kinetic energy from HVP impact is dispersed by the plurality of spheroids and absorbed by the dilatant fluid. The plurality of spheroids within the cavity move to block a puncture hole in the shield.

In some examples, an impact shield structure for use on a lower earth orbit spacecraft comprises a capture layer to absorb debris incident thereon.

In some examples, an impact shield structure for use on a lower earth orbit spacecraft comprises a capture layer to absorb debris incident thereon.