Methods, systems, and apparatus for designing, constructing and using instrument landers for in situ exploration of small solar system bodies, such as asteroids and comets. In one aspect, a lander includes a CubeSat-style platform; instrument packaging, wherein the CubeSat-style platform and the instrument packaging are configured and arranged for an uncontrolled descent, hopping landing on a surface of a body in a solar system, where a descending trajectory for the lander is designed based on gravitational force and solar radiation, with no lander-based propulsion; and a mobility mechanism configured and arranged to self-orient the lander on the surface of the body in the solar system.

A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form.

Spacecraft multifunction connecting mechanisms, and associated systems and methods are described herein. A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.

Atmospheric thrust stages, multi-stage launch systems including the same, and related methods. A multi-stage launch system includes a launch vehicle configured to transport a payload to a payload destination. The launch vehicle includes an atmospheric thrust stage (ATS) with a plurality of airbreathing engines configured to provide thrust to the launch vehicle for a vertical launch of the launch vehicle The ATS is configured to be retrieved and reused subsequent to returning to Earth. A method of transporting a payload to a payload destination includes powering a launch vehicle that includes an ATS and a second stage by providing thrust with a plurality of airbreathing engines of the ATS to propel the launch vehicle, decoupling the second stage from the ATS, powering the second stage to transport the payload to the payload destination, and returning the ATS to Earth.

An explosive separation joint system having an expandable tube containing a mild detonating fuse (MDF) in separable portions of the joint. The MDF extends into a detonation manifold at a first port, an end of the MDF having booster bonded thereto. An external initiating ordnance transfer line enters the manifold at an initiating ordnance (IO) port, has an IO end tip and provides a detonation impulse train where each detonating component is axially aligned within a passageway with the next detonating component. In embodiments, particular detonating components of the detonation train are fixed in place where other detonating components are movable. Each detonating component that is not in direct contact with a preceding detonating component in the detonation train is in direct linear access.

The present invention relates to an apparatus including a self-regulating current source, which utilizes a switching regulator to provide high efficiency power conversion and a high-side current monitor, but instead of driving the feedback input with a voltage divider to set the output voltage, the self-regulating current source utilizes a high-side current sense resistor with an operational amplifier optimized for current sensing, to drive the feedback input to the switching regulator, thereby creating a self-regulating constant current source. By adjusting the gain of the operational amplifier, the user can directly set the optimized current needed for using the apparatus in a variety of deployment devices, including satellite and pyrotechnic applications.

A spacecraft system includes a plurality of spacecraft in a stack. The stack has one or more layers, each layer includes at least two spacecraft, and each spacecraft is releasably coupled to one or more adjacent spacecraft in the stack. The spacecraft system also includes a controller configured to, for each layer, (i) cause the layer to release from the stack, and (ii) after the layer releases from the stack, cause the at least two spacecraft in the layer to release from each other.

A grapple-fixture deployment device allows for an easy, quick, and safe disposal of an unnecessary payload from a space station. The grapple-fixture deployment device includes a space station remote manipulator system (SSRMS)-securing module, a separation system, a payload-securing module, a first attachment mechanism, and a second attachment mechanism. The SSRMS-securing module allows the grapple-fixture deployment device to be attached to the robotic arm apparatus of a mobile servicing system (MSS). The separation system is a spacecraft deployment system that is used to eject the payload-securing mechanism from the rest of the grapple-fixture deployment device. The payload-securing module allows the grapple-fixture deployment device to be attached to a payload. The first attachment mechanism is used to attach the SSRMS-securing module to the robotic arm apparatus of a MSS. The second attachment mechanism is used to attach the payload-securing module to the payload.

A multiple payload set for a launch vehicle, wherein the multiple payload set includes a plurality of payloads. The plurality of payloads is interconnected via a non-self-supported connection structure before assembly of the multiple payload set to a dispenser body. Each payload includes first attachment means attachable to the connection structure. The connection structure includes second attachment means attachable to a ground support equipment, GSE, during attachment of the multiple payload set to the dispenser body.