Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

Provided is a method of controlling horizontal translational motion of a rocket without changing the attitude of the body and without increasing manufacturing costs and operation costs. This allows for accurate execution of rocket landing operation. A rocket control system includes a gimbal actuator that controls a steering angle of a gimbal mechanism located on a lower side of the body of the rocket with respect to the center of gravity; a fin actuator that controls a steering angle of an attitude control fin located on an upper side of the body of the rocket with respect to the center of gravity; a measurement unit that measures a physical quantity related to motion of the body of the rocket and a control unit that controls the gimbal mechanism and the attitude control fin according to a result of measurement by the measurement unit to control horizontal translational motion of the rocket.

A Space Traffic Management (STM) system comprising a Space Traffic Management System Service Supplier (S3) interface for sending a space conjunction request to a Conjunction Assessment Supplier (CAS) interface, and a Space Situational Awareness Supplier (SSA) interface for receiving and fulfilling space object data requests. The system further comprising the Conjunction Assessment Supplier (CAS) interface for receiving the space conjunction request from the S3 interface, requesting and receiving the space object data from the SSA interface, and generating and sending a conjunction data message to the S3 interface. The system enables coordination of an automated service for spacecraft owner operators to anticipate and avoid a space traffic conjunction using the conjunction data message.

A Space Traffic Management (STM) system comprising a Space Traffic Management System Service Supplier (S3) interface for sending a space conjunction request to a Conjunction Assessment Supplier (CAS) interface, and a Space Situational Awareness Supplier (SSA) interface for receiving and fulfilling space object data requests. The system further comprising the Conjunction Assessment Supplier (CAS) interface for receiving the space conjunction request from the S3 interface, requesting and receiving the space object data from the SSA interface, and generating and sending a conjunction data message to the S3 interface. The system enables coordination of an automated service for spacecraft owner operators to anticipate and avoid a space traffic conjunction using the conjunction data message.

The embodiments herein disclose a retrofitted or in built or add-on kit/device for airborne vehicles to reduce the aerodynamic drag thereby increasing performance parameters/metrics of the vehicles. Drag reduction is achieved through shape/contour optimization, and/or heat/energy/fluid addition to the flow in neighbourhood of the vehicle. The device is designed with an external surface to offers the minimum drag. The device is configured to deposit heat/energy/fluid in neighbourhood of flying vehicle in several ways by generating/injecting hot gases in neighbourhood of vehicle for energy/heat addition, thereby causing maximum drag reduction. Heat/energy/fluid is added through the nozzles in the add-on kit/device.

The embodiments herein disclose a retrofitted or in built or add-on kit/device for airborne vehicles to reduce the aerodynamic drag thereby increasing performance parameters/metrics of the vehicles. Drag reduction is achieved through shape/contour optimization, and/or heat/energy/fluid addition to the flow in neighbourhood of the vehicle. The device is designed with an external surface to offers the minimum drag. The device is configured to deposit heat/energy/fluid in neighbourhood of flying vehicle in several ways by generating/injecting hot gases in neighbourhood of vehicle for energy/heat addition, thereby causing maximum drag reduction. Heat/energy/fluid is added through the nozzles in the add-on kit/device.

A part of a spacecraft, for instance an upper stage, is configured to re-enter into the atmosphere and to be reused for several missions. The part is equipped with a reusable kit comprising non-ablative heat shields, for example constructed with an outer surface formed of Ceramic Matrix Composites, such as Ultra High Temperature Ceramic Matrix Composites, and optionally at least one decelerator and/or at least one parachute and/or parafoil system.

A part of a spacecraft, for instance an upper stage, is configured to re-enter into the atmosphere and to be reused for several missions. The part is equipped with a reusable kit comprising non-ablative heat shields, for example constructed with an outer surface formed of Ceramic Matrix Composites, such as Ultra High Temperature Ceramic Matrix Composites, and optionally at least one decelerator and/or at least one parachute and/or parafoil system.

A process for manufacturing a cross-linked product has improved charring and thermal stability properties in which there is cross-linking of a benzoxazine monomer.