Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB3161671A
Inventor
Murray J Neufeld
Walter M Smotrys
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Co
Original Assignee
Hughes Aircraft Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hughes Aircraft CofiledCriticalHughes Aircraft Co
Publication of GB1349907ApublicationCriticalpatent/GB1349907A/en
B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
Abstract
1349907 Spin stabilized device HUGHES AIRCRAFT CO 6 July 1971 [6 July 1970] 31614/71 Heading B7W A spin-stabilized device 10, such as a spacecraft, has a spin axis 14 passing through its centre of mass 16 and includes two first means 28, 30, mounted in a plane passing through the axis 14 at opposite sides of the axis, to produce thrust parallel to the axis, and two second means 24, 26, mounted similarly, to produce thrust directed through the centre of mass 16. The thrust means are mounted on a planar external surface 22 perpendicular to the spin axis, with each first means adjacent a respective second means. Continuous actuation of both of the first means provides translation in the direction of the spin axis with little or no torque about the centre of gravity, while operation of one only provides precession control. Actuation of one or both of the second means also provides motion along the spin axis, while pulsed operation of one only of the second means can provide a component of thrust perpendicular to the axis.
Optimization problems in the mechanics of low- thrust space flight(Low thrust space flight mechanics and optimal control of low thrust engine spacecraft)
Optimization problems in the mechanics of low-thrust space flight(Trajectory optimization problems in mechanics of low thrust propulsion for solar sail and power limited space flights)
Visual requirements for landing on the moon(Investigation of visual requirements for landing spacecraft on Moon and subsequently achieving rendezvous with command module in orbit)
Boundary layer equations and boundary conditions for them in the case of motion in a slightly rarefied gas with supersonic speeds(Boundary layer equations and boundary conditions for motion in slightly rarefied gas with supersonic speed)
On a certain solution of the problem of motion of a gyroscope on gimbals(Heavy gyroscope motion in gimbal suspension for arbitrary housing gravity center, showing steady solutions with respect to nutation angle)
On the solution of certain system of dual integral equations and its application in the theory of elasticity(Elasticity theory with mixed boundary conditions for elastic layer and semispace discussed, using dual integral equations solution)
The response of linear systems to transient excitation(Equations of transient motion of linear systems solving methods including analytical, progressive and shock-spectra for application to aircraft, packaging, etc)
Comparison of the SAO-1969 gravity field with surface gravity(Comparison of Smithsonian Astrophysical Observatory 1969 gravity field representation with surface gravity)
Transactions of the first lectures dedicated to the development of the scientific heritage of K. E. Tsiolkovskiy(Scientific studies of aviation and space flight problems by Russian scientist Tsiolkovskiy)
Analysis of one- and two-gimbal attitude gyros in a satellite application(Satellite attitude control using one- and two- gimballed roll gyros and gyrocompasses)
Experience with Fehlberg's integration method in the calculation of optimum interplanetary transfer orbits at low-thrust acceleration(Fehlberg integration method used to calculate optimum interplanetary transfer orbits at low thrust acceleration)
Satellite motion for arbitrary eccentricity and inclination around the smaller primary in the restricted three-body problem(Perturbation technique to study three-body problem of motion of close satellite)
Present and future developments in gas dynamic experimentation(Trends in aerothermodynamic simulation at very high Reynold numbers for hypersonic aircraft-space shuttles and planetary entry)
Relativistic equations governing the structure of radiative configurations of spherical symmetry and in slow motion(Relativistic stellar structure equations for spherically symmetric configurations in slow motion, using Einstein gravitational field and conservation equations)
The hostile kinetic environment on sea, on land, in the air and in space(Human and chimpanzee tolerance tests to rocket sled deceleration, impact and windblast relevant to space flight)
The effect of viscosity and anisotropy in the pressure on the azimuthal motion of the solar wind(Steady state symmetrical model for solar wind near equatorial plane, investigating effects of magnetic forces, viscosity and anisotropic pressure on azimuthal motion)
Optimal control of a composite system composed of an engine of limited discharge velocity and an engine of limited power(Optimal control of composite spacecraft propulsion system incorporating high thrust-weight ratio chemical engine and low thrust ion engine)