公开(公告)号：WO1988005112A1

公开(公告)日：1988-07-14

申请号：PCT/US1987003441

申请日：1987-12-23

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  PETERS, Rex, B.

IPC: E21B47/00

CPC classification number: E21B47/04 ,  E21B47/022

Abstract: A system and method for precisely and continuously estimating the path length between the entrance of a borehole and a probe (10) which is supported by an elastic cable (14) and carries a gyrocluster (42) and accelerometer cluster (40). The precise estimate of borehole path length is used to aid the inertial navigation performed within the survey system and is selectively determined by integration of either the rate at which the probe (10) moves along the borehole or a compensated cable feed rate that is based on the rate at which the cable (14) passes into or out of the borehole with correction being made for changes in temperature and gravity induced cable stretch. Selection of the rate to be integrated at any given time being determined by whether the rate at which probe (10) moves along the borehole exceeds the compensated cable feed rate by a predetermined amount.

公开(公告)号：WO1988002868A1

公开(公告)日：1988-04-21

申请号：PCT/US1987002567

申请日：1987-10-07

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  CHISHOLM, John, P.

IPC: G01S01/16

CPC classification number: G01S1/56 ,  G01S1/10

Abstract: Independent guidance and monitoring integrated into an MLS landing system and a scaled-down MLS take-off or missed approach guidance system useable at small airports. An added fixed beam precision guidance system is integrated into the MLS time sequence format. The fixed beam guidance system is based upon the concept of using paired fixed overlapping beams, sequentially radiated by different fixed antennas (80 and 81), oriented to left and right of a prescribed guidance path. The paired beams overlap at the prescribed guidance path in such a manner that an aircraft departing or making a missed approach on such path will intercept equal signal intensities to indicate an on-course condition. Conversely, when the aircraft is off-course to one side of the prescribed path, it will intercept a stronger signal intensity for the fixed guidance beam which is directed to that side of the prescribed path and a weaker signal intensity for the fixed beam which is directed to the other side of the prescribed path.

Abstract translation: 独立的指导和监测整合到一个MLS着陆系统和一个缩小的MLS起飞或错过的方法指导系统可用于小型机场。 增加的固定光束精度指导系统被集成到MLS时序格式中。 固定光束引导系统基于使用成对固定重叠光束的概念，该成对固定重叠光束被定向在规定引导路径的左侧和右侧的不同固定天线（80和81）顺序辐射。 成对的光束在规定的引导路径处重叠，使得在这种路径上离开或进行错过的飞行器将拦截相等的信号强度以指示在线状态。 相反，当飞机离规定路径的一侧偏离时，它将拦截针对指定路径那侧的固定引导梁的较强的信号强度，对于固定梁的信号强度较弱， 指向规定路径的另一边。

公开(公告)号：WO1987006335A1

公开(公告)日：1987-10-22

申请号：PCT/US1987000871

申请日：1987-04-15

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  VERMILION, Everette, E.

IPC: G01C03/08

CPC classification number: G01C5/005 ,  G01S5/12 ,  G01S13/003

Abstract: A method and apparatus for passively determining the altitude (HP) above the ground of an aircraft (P) by use of an active emitter carried on a second aircraft (S) at a higher altitude (HA). Specifically, the altitude (HP) of the aircraft (P) is determined by measuring the time difference between direct path radiation (R1) and reflected path radiation (R2), taking into account the distance (DA) between an upper antenna (TA) which receives the direct path radiation (R1) and a lower antenna (BA) which receives the reflected path radiation (R2) and the angles of travel (A1, A2) relative to the vertical between the direct path radiation and the reflected path radiation.

公开(公告)号：WO1987006043A1

公开(公告)日：1987-10-08

申请号：PCT/US1987000632

申请日：1987-03-23

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  MULLER, Hans, R.

IPC: G08B23/00

CPC classification number: G05D1/0615 ,  G01C23/005

Abstract: An aircraft performance instrument having a first indicator (38) which represents the line of level flight of the aircraft and a second indicator (40) representative of the maximum permissible angle of attack of the aircraft. The separation between the two indicators is a measure of the take-off performance capability of the aircraft. It also represents degraded performance due to a wind shear condition thereby providing the pilot with guidance as to how to respond to wind shear.

公开(公告)号：WO1987002469A1

公开(公告)日：1987-04-23

申请号：PCT/US1986002222

申请日：1986-10-20

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  MERHAV, Shumel, J.

IPC: G01P15/08

CPC classification number: G01P9/00 ,  G01P15/08

Abstract: Method and apparatus for processing signals supplied by accelerometer assemblies (12) in which one or more accelerometers are cyclically displaced in a predetermined manner so that signals representing the specific force experienced by the accelerometers and the angular rate experienced by the accelerometers are produced. The signal processor (10) separately estimates the signal components of the signal being processed and provides an error signal (e) by subtracting the estimated signal components from the signal being processed (26). The error signal (e) is fed back through circuitry (30-56) that controls the magnitude of the estimated signal components so that the value of each estimated signal component rapidly converges to the value of the signal components of the signal being processed. In an arrangement for determining the angular rate of one or more pairs of cyclically displaced accelerometers, the signal processor (10) includes a signal component that is in-phase with the signal that oscillates the accelerometer pair, a signal component that is in phase quadrature with the signal that displaces the accelerometer pair and a signal component that corresponds to random unmodulated additive noise.

Abstract translation: 用于处理由加速度计组件（12）提供的信号的方法和装置，其中一个或多个加速度计以预定方式循环移位，从而产生表示加速度计所经受的特定力的信号和加速度计所经历的角速率。 信号处理器（10）分别估计正在处理的信号的信号分量，并通过从被处理的信号中减去所估计的信号分量来提供误差信号（e）（26）。 误差信号（e）通过控制估计信号分量的大小的电路（30-56）反馈，使得每个估计信号分量的值迅速收敛到被处理信号的信号分量的值。 在用于确定一对或多对循环移位的加速度计的角速率的装置中，信号处理器（10）包括与振荡加速度计对的信号同相的信号分量，相位正交的信号分量 信号使位移加速度计对和对应于随机未调制的加法噪声的信号分量。

公开(公告)号：WO1986005039A1

公开(公告)日：1986-08-28

申请号：PCT/US1986000321

申请日：1986-02-12

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  McCORMICK, Willis, G.

IPC: H01S03/00

CPC classification number: G01C19/661 ,  H01S3/097 ,  Y10S315/07

Abstract: Prior power supplies adapted to provide power to the lasers of multiple ring laser gyros were inefficient in that they were required to have power output capabilities far in excess of that required to sustain laser operations. Such inefficiency is greatly reduced by the present power supply comprising a DC power source (30) for producing a firing voltage at a first terminal (40) and a sustaining voltage at a second terminal (42), and interface means (50) associated with each laser (12, 13, 14) for coupling the laser to the first and second terminals. The firing voltage is capable of firing each laser, and the sustaining voltage is capable of sustaining current flow through each laser after firing. Each interface means comprises a resistor (52, 53, 54) connecting the laser to the first terminal and a diode (55, 56, 57) for connecting the laser to the second terminal such that the diode does not permit current flow between the first and second terminals.

公开(公告)号：WO1986004983A1

公开(公告)日：1986-08-28

申请号：PCT/US1986000385

申请日：1986-02-21

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  GROVE, Michael, M.

IPC: G01C21/00

CPC classification number: G01C5/005

Abstract: Warning systems that monitor the altitude above ground and descent rate of an aircraft and generate a warning if the descent rate of the aircraft is excessive for the altitude in which the aircraft is flying are well suited to aircraft whose flight and operational characteristics are readily predictable but not as suitable for aircraft, such as tactical aircraft whose operating conditions are not so predicable. To overcome this problem, the criteria for providing the warnings are altered (30, 32) as a function of flight configuration, as detected by gear position (16) and whether or not a mission selector switch (18) indicates the aircraft is in a tactical mode.

Abstract translation: 监测飞机高度高于飞机高度的飞行器的下降速率过高的警告系统，如果航空器的飞行高度过大，就会产生警告，这种飞机飞行和操作特性是易于预测的，但是 不适合飞机，如其操作条件不可预测的战术飞机。 为了克服这个问题，提供警告的标准被改变（30,32）作为飞行配置的函数，由齿轮位置（16）检测，以及任务选择器开关（18）是否指示飞行器处于 战术模式。

公开(公告)号：WO1986004037A1

公开(公告)日：1986-07-17

申请号：PCT/US1986000036

申请日：1986-01-08

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  BRADY, Arthur, R.

IPC: B64C25/02

CPC classification number: G01G19/07 ,  G01G3/12

Abstract: A mounting and mounting method for a sensor (21) positioned within a tubular axle (15) of an aircraft (10) undercarriage which will provide an output voltage proportional to the angular deflection of an axle for computation of aircraft gross weight. The sensor (21) is not affected by cross-sectional distortions of the tubular axle under loading, undesirable frictional effects at the interface between the sensor mounting and the tubular axle and differential angular deflections of the axle. The cylindrical mouting member (20) for the sensor (21) has a pair of O-rings (35, 36) adjacent opposite ends thereof which are positioned to space the periphery of the mounting member from the bore of the tubular axle (15) and which are under radial compression and act to provide uniform radial compressive forces applied about the full circumferential periphery of the cylindrical mounting member (20) and absorb distortions of the axle (15) by elastic deformation thereof. At least one (36) of the O-rings (35, 36) is axially compressed for increased radial compression between the cylindrical mounting (20) and the tubular axle (15) to further improve the action in immunizing the sensor (21) from distortion effects in the axle (15) and maintain the sensor in the desired position endwise of the tubular axle.

公开(公告)号：WO1986001622A1

公开(公告)日：1986-03-13

申请号：PCT/US1985001653

申请日：1985-08-30

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  VERMILION, Everette, E. ,  PATERSON, Noel, S.

IPC: G08B23/00

CPC classification number: G05D1/0607 ,  G01C5/005

Abstract: A system (10) using altitude (16), barometric altitude rate (14), airspeed (18), landing gear position (20) and the state of the arming of the weapons of the aircraft (20) for providing warning (34) to the pilot of a tactical aircraft in the event that the descent rate of the aircraft is excessive for the altitude at which the aircraft is flying.

Abstract translation: 系统（10）使用高度（16），气压高度（14），空速（18），起落架位置（20）和用于提供警告的飞机（20）武器的布防状态（34） 如果飞机的下降率对于飞机飞行的高度过大，则应用于战术飞机的飞行员。

公开(公告)号：WO1986000130A1

公开(公告)日：1986-01-03

申请号：PCT/US1985001082

申请日：1985-06-07

Applicant: SUNDSTRAND DATA CONTROL, INC.

Inventor： SUNDSTRAND DATA CONTROL, INC. ,  KIRKPATRICK, Gordon, S.

IPC: G01C19/64

CPC classification number: G01C19/70

Abstract: A body dithered laser gyro assembly adapted so that the natural frequency of the assembly can readily be predicted and adjusted. In one embodiment, the laser gyro assembly comprises a base (10), resilient support means (12) mounted to the base, coupling means (30, 40, 50) mounted to the support means, a laser gyro (20) mounted to the coupling means, and drive means (70) connected to the base and to the coupling means. The drive means imparts a dither motion to the coupling means, and the coupling means in turn couples such dither motion to the gyro. The coupling means can include a diaphragm (40) having inner (124) and outer (122) portions, the inner portion of the diaphragm being connected to the drive means, and the outer portion coupled to the laser gyro. The inner and outer diaphragm portions may be connected by a plurality of beams (126) through which the dither motion is coupled.