A Modified Bipolar Translinear Cell with Improved Linear Range and Its Applications

This paper presents a technique to extend the linear input voltage range of a sinh mixed translinear cell proposed by Fabre [1]. This technique extends the linear operation range of the circuit by inserting common-anode-connected pairs into the mixed translinear cell. Then the relationship between the output current and the input voltage is developed to be linear. The transconductance gain can be adjusted electronically while keeping its linearity. The performance of the proposed circuit is verified by mathematical analysis and by SPICE simulations. Finally, applications of the proposed cell in a floating resistor and a CCCII for designing an instrumentation amplifier are presented

Application of trajectory optimization techniques to upper atmosphere sampling flights using the F-15 Eagle aircraft

Atmospheric sampling has been carried out by flights using an available high-performance supersonic aircraft. Altitude potential of an off-the-shelf F-15 aircraft is examined. It is shown that the standard F-15 has a maximum altitude capability in excess of 100,000 feet for routine flight operation by NASA personnel. This altitude is well in excess of the minimum altitudes which must be achieved for monitoring the possible growth of suspected aerosol contaminants

A differential game solution to the Coplanar tail-chase aerial combat problem

Numerical results obtained in a simplified version of the one on one aerial combat problem are presented. The primary aim of the data is to specify the roles of pursuer and evader as functions of the relative geometry and of the significant physical parameters of the problem. Numerical results are given in a case in which the slower aircraft is more maneuverable than the faster aircraft. A third order dynamic model of the relative motion is described, for which the state variables are relative range, bearing, and heading. The ranges at termination are arbitary in the present version of the problem, so the weapon systems of both aircraft can be visualized as forward firing high velocity weapons, which must be aimed at the tail pipe of the evader. It was found that, for the great majority of the ralative geometries, each aircraft can evade the weapon system of the other

Application of trajectory optimization techniques to upper atmosphere sampling flights using the F4-C Phantom aircraft

Altitude potential of an off-the-shelf F4-C aircraft is examined. It is shown that the standard F4-C has a maximum altitude capability in the region from 85000 to 95000 ft, depending on the minimum dynamic pressures deemed acceptable for adequate flight control. By using engine overspeed capability and by making use of prevailing winds in the stratosphere, it is suggested that the maximum altitude achievable by an F4-C should be in the vicinity of 95000 ft for routine flight operation. This altitude is well in excess of the minimum altitudes which must be achieved for monitoring the possible growth of suspected aerosol contaminants

Optimum Pre-Emphasis for Frequency Modulation Applications

Frequency modulated communication receiving systems that operate under varying RF input power conditions use a generalized preemphasis schedule that provides improved communication reception. In many instances, a receiving system operates with a stable RF input power. The optimization of FM systems, operating with a stable RF input power, requires the use of a particular pre-emphasis schedule. Typical FM systems are not frequency modulated with a constant modulation index for all baseband frequencies. Instead, they use a signal pre-emphasis circuit at the transmitter and a complementary de-emphasis circuit at the receiver to optimize system operation. Preemphasis and de-emphasis are required whenever the noise amplitude varies significantly for different frequencies in the baseband (Figure la). FM pre-emphasis at the transmitter accentuates certain baseband frequencies with respect to other frequencies in the baseband (Figure Ib). The complementary FM deemphasis at the receiver de- accentuates those frequencies in the baseband that were originally pre-emphasized by the transmitter, and maintains a constant output signal to noise ratio density throughout the baseband (Figure Ic)

Development of high energy density primary batteries Fourth quarterly report, 22 Mar. - 21 Jun. 1966

High energy density primary batteries for space flight applications - electrolyte systems, cell systems, and positive electrode constructio

Development of high energy density primary batteries 200 watt hours per pound total battery weight minimum Final report, 10 Jun. 1964 - 9 Jun. 1965

High energy density lithium-anode primary cells developed with energy-to-weight ratios over 200 watt hours per poun

Development of high energy density primary batteries First quarterly report, 22 Jun. - 21 Oct. 1965

Electrode and electrolyte studies for lithium- copper fluoride batterie

Application of differential game theory to role-determination in aerial combat

The development of criteria which specify the roles of pursuer and evader as functions of the relative geometry and of the important parameters of the problem are discussed. A reduced-order model of the relative motion is derived and discussed. In this model, the two aircraft move in the same plane at unequal but constant speeds, and with different maximum turn rates. The equations of relative motion are of third order, the dependent variables being the relative range, bearing, and heading of the two aircraft. Termination of the pursuit-evasion game is defined by either the heading-limited or the range-limited end condition. These are geometric conditions for which the evading aircraft is in front of the other, with the relative heading and relative range satisfying certain inequalities. Retrograde solutions to the equations of relative motion were used with the derived optimal terminal maneuvers to find where an assumed set of end conditions could have begun