Abstract: In the described embodiments, a spacecraft is powered by paralleled solar panels, which supply power to a load. The panels are ORed together, and each is controlled by a switched shunt, which provides coarse control of the load voltage. A control loop senses the load voltage, and logic selects those shunts which are conductive at any particular time in a manner which tends to maintain the load voltage constant. The control loop may undesirably become unstable because of gain changes caused by changes in solar panel insolation. A further controller adjusts the clock frequency at which the shunts are switched in a manner which tends to stabilize the loop. The further controller responds (a) to the current of one or more of the panels, (b) to the frequency of oscillations across the load, or (c) to both.

Abstract: Aluminum-lithium plates are butt-welded by juxtaposing the plates and making a preliminary weld from the rear or root side of the seam. An initial weld is then made from the face side of the seam, which may cause a defect in the root portion. A full-size X-ray is made and overlain over the seam to identify the defects. The defect is removed from the root side, and rewelded. Material is then removed from the face side, and the cavity is rewelded. The procedure repeats, alternating from the root side to the face side, until the weld is sound.

Abstract: A spacecraft (10) carries a solar panel (17) which rotates to follow the sun, and also carries various thrusters (20). Thruster plume impingement on the solar panel affects the torque applied to the spacecraft body (12) in a manner which depends upon solar panel angle. The errors in the thrust during stationkeeping tend to perturb attitude, especially early in the maneuver, because of the delay inherent in the attitude control loop. A torque bias is summed with the residual torque demand signal to correct for the errors in torque. The torque bias signal is generated by a Fourier model of the torques, updated by an adaptive tuning filter, so that successive stationkeeping maneuvers progressively adapt the amplitude and phase of the Fourier coefficients in a manner which tends to minimize the residual torque demand and attitude error. Thus, the torque bias signal automatically approaches the correct value.

Abstract: A spacecraft (10) has an attitude sensor (20) mounted on its body (12). The sensor must be maintained near a temperature setpoint. Each sensor (20) produces its own temperature-indicative signal. Each attitude sensor is coupled to a thermally conductive instrument platform (18). A standoff (21) supports the platform (18) away from a baseplate (16) and the spacecraft body (12). The standoff (21) includes a thermally conductive portion (22) adjacent the platform (18), and a nonconductive portion (24) remote from the platform. An electric heater (26) is connected to the thermally conductive portion (22) of the standoff (21). A temperature sensor (28) thermally coupled to the platform (18) generates platform temperature signals. A filter (212) high-pass filters either the platform temperature signals or the attitude sensor temperature signals, to form filtered signals. A combining circuit (218) combines the filtered signals with the other temperature signals, to make composite temperature signals.

Abstract: A Tripulse method determines the orientation or attitude of a phased-array antenna located at a remote site, such as an aircraft or spacecraft. Three pulses are transmitted from the phased-array antenna in an estimated direction toward a coherent receiver, with a sum beam, and with first and second difference beams formed by reversal of the phase of certain elements above a first axis of symmetry, and to one side of a second axis of symmetry. The received signals are processed in a manner which determines the error between the assumed direction and the actual direction of the receiver. To determine the rotational position of the array antenna, the same steps are performed for a second remote receiver, and additional processing determines the complete attitude, including yaw, of the phased-array antenna. The coherent receiver may use the first transmitted pulse as a reference, or it may use a separate reference signal.

Abstract: A hermetically sealed housing for plural GaAs chips includes a body made from Al/SiC. The body defines a peripheral seal ring support surface, an electrical connector insert support surface and an end wall to which a ceramic insert is mounted. The insert includes a first portion with an upper surface within the sealed housing, Which upper surface is coplanar with the upper surface of the body, for convenient HDI film connections to the chips and electrical connector inserts. The refractory electrical conductors extend from the upper surface of the first portion of the insert to an exterior terminal portion of the insert. The terminal portion of the insert is spaced from the first portion of the insert by a non-terminal portion containing no terminals. The non-terminal portion of the insert is coplanar with the seal ring support surface of the body, and contiguous therewith.

Abstract: Semiconductor devices made in highindium-content semiconductor material have advantageous properties, but similar substrate materials are hard to handle. A buffer layer makes a lattice-constant transition between a GaAs substrate and a high-indium epitaxially deposited semiconductor such as those lattice-matched to InP. The buffer layer is an epitaxial layer including atoms of two Group III elements, and atoms of two Group V elements, with the ratio of the atoms of at least one group varied along the depth of the buffer layer, in a manner which makes a transition of the lattice constant between that of the substrate and the high-Indium semiconductor material. The Group III elements are gallium and aluminum, and the Group V elements are arsenic and antimony.

Abstract: A low-cost rocket or thruster has a low-cost propellant injector, in which fluid fuel and oxidizer are injected into a combustion chamber. The walls of the combustion chamber are protected from the high temperatures of the combustion by a grain of solid propellant, the surface of which tends to melt andor vaporize in the presence of combustion temperatures, and thereby protects the walls of the chamber. The low-cost propellant injector may not mix the fluid fuel and oxidizer effectively, so that pockets of noncombusted gas may occur within the chamber. The ratio of fluid fuel and oxidizer is selected to be slightly oxidizer-rich, so that any pockets of unburned gas tend to be oxygen-rich. When the pockets come into contact with the solid fuel, the excess oxygen combusts with the gaseous solid fuel, and when the mixture is near stoichiometric, the fluid fuel combusts.

Abstract: A switching converter achieves improved regulation range by the use of a saturable reactor in series with a transformer primary. The saturable reactor uses a conventional magnetic pot core including a magnetic shell and center post. The location at which the post joins the shell is perforated to reduce the cross-section of magnetic material, so that, at low reactor currents, incremental inductance is established by the gap between post and lid, and at high reactor currents, the incremented inductance is established by saturation at the base of the post. Perforation at the base of the post also results in generation of heat at a location immediately adjacent the flat bottom of the pot core.

Abstract: An apparatus and method for radar detection of spectral moments and other spectral characteristics of echoes includes an agile antenna which directs an antenna beam in a direction for a dwell interval. A clutter filter reduces clutter. In order to eliminate the need for fill pulses to stabilize the clutter filter, the clutter filtering is accomplished by matrix multiplication of the echo signal in each range bin by the inverse of the covariance matrix for that range. This reduces the dwell at each range interval, and provides a stream of pulse-to-pulse information at each range interval. The pulse-to-pulse data in each range interval is spectrum analyzed to extract the desired spectral information, which is displayed.

Abstract: An arrangement for coordinating positional and angle information made on separate relatively moving platforms, such as aircraft, having independent coordinate systems, uses measurements of a common reference made on both platforms. The measurements are transmitted to a common location. Measurements made at a first time are processed to determine two of three coordinate transformation angles. After a period of time, a second set of measurements is used to determine the third coordinate transformation angle. In a particular embodiment of the invention, the direction of motion of one of the platforms is controlled to be orthogonal to a coordinate axis of the other platform. When the coordinate transformation is determined, it can be used to coordinate or align navigation instruments, weapons, or the like. In one embodiment of the invention, a missile is directed toward a target, in a situation in which the target is viewed from the missile and another moving vehicle.

Abstract: A spacecraft includes a plurality of solar panels interconnected with a power coupler and an electrically operated device to provide power to the device when the solar cells are insolated. The solar panels are subject to bending distortion when entering or leaving eclipse. Spacecraft attitude disturbances are reduced by mounting each of the solar panels to an elongated boom made from a material with a low coefficient of thermal expansion, so that the bending of one panel is not communicated to the next. The boom may be insulated to reduce its bending during changes in insolation. A particularly advantageous embodiment mounts each panel to the boom with a single mounting, which may be a hinge. The single mounting prevents transfer of bending moments from the panel to the boom.

Abstract: Improved throughput is provided in a spacecraft TDMA cellular communications system by in-call signalling without the need for flag bits, while still allowing the in-call signaling to be differentiated from other traffic. The terrestrial locations include mobile user terminals and gateways which provide connections to the land telephone line system. The spacecraft includes a transmitter and receiver, and an antenna which forms a plurality of spot beam footprints, in which the terrestrial terminals are located. Each of the terrestrial terminals transmits signals to, and receives signals from, the spacecraft. Each of the terrestrial terminals includes an encoder/decoder, for encoding at least call maintenance control signals, for temporarily interrupting the traffic signals to allow another action. The control signals may have bit content which exceeds the bit-carrying capability of the TDMA bursts, so transmission of the control signals must extended over a plurality of bursts.

Abstract: A communications system includes first and second ground stations and a spacecraft repeater. Data signals are transmitted between ground stations by way of the repeater, together with spread-spectrum ranging signals. Uplink rain attenuation is compensated for changing the transmitted power at the ground stations. The amount of downlink attenuation is determined by measuring the total carrier-to-noise ratio in three paths, station 1 to station 2, station 2 to station 1, and station 1 to station 1. With these three values of total attenuation, the two downlink attenuations and the number of active signals traversing the repeater can be determined. The downlink attenuations are converted to uplink attenuations, and used to control the transmitters.

Abstract: A spacecraft includes heat-radiating panels. Heat-generating boxes such as TWTs are mounted on shelves which are inside the spacecraft, where they cannot radiate to space. The shelves are coupled by bent heat pipes to the exterior radiating panels.

Abstract: A spacecraft includes a three-axis attitude control system. When velocity change thrusters are fired, their plumes impinge on a solar array, at angles which vary with the solar array position. This causes disturbance torques which vary with the solar array position. Disturbance torque information signals or torque bias signals which depend upon the solar array angle are summed with the torque demand signals which control the attitude control system during firing of the velocity change thrusters, to modify the attitude correction torques. The bias torque signals are generated by a Fourier processor based upon stored Fourier coefficients together with signals from a solar array angular position sensor.

Abstract: A ranging system for a communications spacecraft (14) overlays a Gaussian noise signal over a broadband channel which also carries information or traffic signals. The noise is used to establish the range between a ground station (12) and the spacecraft (14). The range is determined by delaying the Gaussian noise in a controllable delay (32), and autocorrelating the delayed noise with the noise returned over the communications channel from the spacecraft. The ranging system (FIG. 4) reduces the bandwidth of the noise in a filter (18) during initial acquisition, to color the noise and broaden the autocorrelation peak (FIG. 3a). The broad peak shortens the initial search time. Once the peak is initially found, the noise bandwidth is progressively broadened to narrow the autocorrelation peak (FIG. 3c) and to give a more accurate indication of range.

Abstract: The loop filter of a sigma-delta analog-to-digital converter (ADC) includes a multistage loop filter coupled to the output port of an input summer stage, for receiving difference signals therefrom. The loop filter includes a plurality of cascaded stages. All but one of the cascaded stages includes first and second cascaded half-stages, and that one of the stages includes at least one half-stage. The last one of the cascaded half-stages in the loop filter is coupled to the input port of an ADC stage for coupling loop-filtered difference signals or resonated signals thereto. The ADC stage produces the desired output digital signals. A DAC is coupled to the output of the ADC stage, for generating an analog replica of the desired digital output signals, and for coupling the replica to the input summer stage for aiding in generating the difference signals.

Abstract: A half-wave brushless, four-phase DC motor includes sets of four stator windings fed at 90.degree. phase increments by four switches. The 0.degree. and 180.degree. windings are wound about their magnetic stator poles in bifilar conductor pairs, and the 90.degree. and 270.degree. windings are similarly wound. The bifilar windings are connected to generate the same directions of magnetic fields as the prior-art windings. As a result of the bifilar windings, the magnetic fields of the windings tend to be identical, and all the inductances of each winding tend to be transformer-coupled to the other winding of the bifilar pair. During sequential turn-off of the switches in normal operation, the coupled inductance causes a voltage kick which is poled so it can be damped, and the energy returned to the source, by a diode coupled across the other switch of the bifilar pair.

Abstract: A speech signal has its characteristics extracted and encoded (16), transmitted over a limited-data-rate path (18) and is decoded (20) and synthesized (22) at the receiving end. The characteristics include line spectral frequencies (LSF), pitch and jitter. The LSF are extracted by autoregression, and splitvector quantized (SVQ) in a single frame, and, in parallel, in blocks of two, three and four frames. The SVQ codes have equal length and are evaluated for distortion in conjunction with a threshold. The threshold is varied in such a manner as tend to select for transmission those codewords which maintain a constant data rate into a transmit buffer. A single-bit jitter bit, and encoded pitch value, are product coded with the selected LSF codeword, and all are transmitted over the data path (18) to the receiver. The receiver decodes the characteristics, and controls a pitch generated (1226) in response to the pitch value and a random pitch jitter in response to the jitter bit.