The invention relates to the novel usage of shear-thickening and rheopectic non-Newtonian fluids as shock absorbers intended absorbing acceleration or impact via submergence of an object to be protected entirely into non-Newtonian fluid. Additionally, this invention relates to the novel usage of shear-thickening and rheopectic non-Newtonian fluids as shock absorbers capable of absorbing the force of impact or acceleration and effectively dissipating the force away from the object to be protected over an extended duration (greater than an instantaneous impact) more effectively than traditional shock absorbers.

The invention relates to the novel usage of shear-thickening and rheopectic non-Newtonian fluids as shock absorbers intended absorbing acceleration or impact via submergence of an object to be protected entirely into non-Newtonian fluid. Additionally, this invention relates to the novel usage of shear-thickening and rheopectic non-Newtonian fluids as shock absorbers capable of absorbing the force of impact or acceleration and effectively dissipating the force away from the object to be protected over an extended duration (greater than an instantaneous impact) more effectively than traditional shock absorbers.

An aircraft is capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. An additional breathable gas supply is provided to be activated only during a flight phase during which aerobic propulsion is interrupted, and is capable of supplying the control system of the manned cabin environment instead of the system associated with the aerobic propulsion means.

An aircraft is capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. An additional breathable gas supply is provided to be activated only during a flight phase during which aerobic propulsion is interrupted, and is capable of supplying the control system of the manned cabin environment instead of the system associated with the aerobic propulsion means.

A deformable closure mechanism for an aperture that may include an aperture seal that has a seal seat between an internal support structure and an external support structure. A barrier structure may be configured to resealably close the aperture, and have a central membrane and a barrier sealed that is inflatable in order to engage the barrier structure with the aperture seal.

A method for thermally stabilizing a communication satellite in orbit around the Earth relies on the discrete rotational symmetry of the pattern of antenna beams of the satellite. Exploiting the symmetry, the orientation of the satellite is changed from time to time by rotating the satellite through a symmetry angle of the rotational symmetry. Because of the symmetry, the beam pattern is unchanged after the rotation; but, because the rotation angle is less than 360°, a different side of the satellite is exposed to sunlight. The use of different thermal radiators and thermal shields on different sides of the satellite means that the thermal budget of the satellite is different after the rotation. By judiciously applying rotations as needed, as the orbit's orientation relative to the Sun evolves in time, it is possible to achieve effective control on the thermal budget of the satellite.

A system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a “pusher” launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

A system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a “pusher” launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

A transfer type contra-rotating geomagnetic energy storage-release delivery system is disclosed. The system includes a control system, a three-axis control moment canceller and an energy system, which are arranged on a delivery mother spacecraft, and the delivery mother spacecraft is connected, through support rod structures, with a strong magnetic moment generating device, a contra-rotating transmission mechanism and two delivery connection rod structures arranged at the two ends of the contra-rotating transmission mechanism, the strong magnetic moment generating device is arranged between the contra-rotating transmission mechanism and the delivery mother spacecraft, the two delivery connection rod structures are provided with slidable mass blocks respectively, and the strong magnetic moment generating device and the contra-rotating transmission mechanism provide energy through the energy system. The strong magnetic moment generating device is free of accelerated rotation of an attitude, thereby decoupling the dual coupling.

Embodiments described herein may relate to systems and methods for navigating to a supply request. An alert device may be controlled to issue alerts to draw the attention of bystanders to associated supplies for a situation. An illustrative method involves (a) receiving, by a computing system, a transmission indicating a situation at a designated location; (b) the computing system determining an approximate target area associated with the designated location; (c) the computing system making a determination that an alert device is located within the approximate target area; and (d) in response to the determination that the alert device is located within the approximate target area, the computing system executing instructions to activate at least one alert on the alert device indicating the situation and the designated location of the situation.