公开(公告)号：WO1986007465A1

公开(公告)日：1986-12-18

申请号：PCT/US1986001139

申请日：1986-05-29

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  DeLEO, Richard, V. ,  HAGEN, Floyd, W.

IPC: G01P05/165

CPC classification number: G01P5/165 ,  Y10T29/49428 ,  Y10T29/49995

Abstract: A short multiple static pressure sensing probe (10) that is compenstated for both subsonic and supersonic speeds in the same probe and a family of such probes for different aircraft with each of the probes in the family having a common barrel (14) configuration except for the final shaping of compensation surfaces (51, 52, 53, 54) and the location of static pressure sensing ports (23, 35). In an assembly operation, heaters (46) and interconnecting wires, bulkheads (19, 32, 33) and pressure tubing (18, 37) are arranged, internal to the probe, to be clear of predetermined areas in which static pressure ports may be located. In a finishing operation, compensation surfaces (51, 52, 53, 54) are produced and static pressure ports (23, 35) are created at selected locations in the predetermined areas, thus avoiding damage to internal parts. A preferred arrangement of compensation surfaces (51, 52, 53, 54) facilitates multiple subsonic and supersonic compensation by providing at least two regions of relatively constant, but selectable, supersonic compensation pressures that coincide along the length of the barrel (14) with two regions of variable subsonic pressures. The supersonic compensation in this preferred arrangement is adjusted to the desired levels by selecting two of the compensation surfaces (51, 52, 53, 54). The subsonic compensation is then adjusted by selecting a second two of the compensation surfaces (51, 52, 53, 54) and the location of the static pressure ports (23, 35).

公开(公告)号：WO1991011789A1

公开(公告)日：1991-08-08

申请号：PCT/US1991000272

申请日：1991-01-14

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W.

IPC: G08B21/00

CPC classification number: G01P5/17

Abstract: A preassembled air data sensor probe and air data transducer assembly (10) has permanently connected flexible tubing (13, 14, 15, 16) coupling the air data transducer fittings and the sensor fittings (13A, 14A, 15A, 16A). The flexible tubing (13-16) permits the air data sensor (11) and air data transducer (20) to be installed into an air vehicle (18) after having been preassembled and pretested for leaks at the factory. The permanently connected assembly (10) avoids the need for calibration or pressure checks after installation on the aircraft (18). The preassembled flexible tubing (13-16) permits manipulation of the transducer (20) to mount it into its proper location even in tight quarters. The flexible tubing (13-16) can have a section that acts as a drain trap (41) for accumulating ingested water.

公开(公告)号：WO1990010492A1

公开(公告)日：1990-09-20

申请号：PCT/US1990001076

申请日：1990-02-27

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W.

IPC: B01D53/26

CPC classification number: G01P5/165

Abstract: A water separating device (10, 460D) for a pressure measurement such as static, pitot measurement system provides a passageway (82, 420A, 436A, 460A) having a portion formed as a plurality of ports (41, 420B, 436B, 460E) therethrough such that liquid water, and solid water such as snow and ice from atmospheric air are substantially removed from the air so that desired parameters such as temperature or pressure can be measured. Separation of water, snow and ice using ports (41, 420B, 436B, 460E) as disclosed eliminates additional chambers for collecting same and eliminates drain systems and drain valves.

Abstract translation: 用于诸如静态皮托测量系统的压力测量的水分离装置（10,460D）提供具有形成为多个端口（41,420B，436B，460E）的部分的通道（82,420A，436A，460A） 从而使空气中的液态水以及诸如雪和冰的固体水从空气中大量地除去，从而可以测量诸如温度或压力的期望的参数。 使用如所公开的端口（41,420B，436B，460E）分离水，雪和冰消除了用于收集它们的另外的室，并且消除排水系统和排水阀。

公开(公告)号：WO1994014075A1

公开(公告)日：1994-06-23

申请号：PCT/US1993011558

申请日：1993-12-01

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W.

IPC: G01P05/165

CPC classification number: G01P5/165 ,  G01P13/02

Abstract: A deployable probe (10) has pressure ports (21A, 22A, 23A, 24A) positioned radially around a longitudinal probe axis. The probe (10) mounts within a pressure chamber (30) such that it can reciprocate from a retracted position where the pressure ports (21A, 22A, 23A, 24A) are contained within the pressure chamber (30) for measuring static pressure to a deployed position where air flows generally orthogonal to the longitudinal axis of the probe (10) and into the pressure ports (21A, 22A, 23A, 24A) such that differential pressures in oppositely facing pressure ports can be sensed for measuring relative flow magnitude and flow angles.

Abstract translation: 可展开的探针（10）具有位于纵向探针轴线径向的压力端口（21A，22A，23A，24A）。 探头（10）安装在压力室（30）内，使得其能够从压力端口（21A，22A，23A，24A）被容纳在压力室（30）内的缩回位置往复运动，用于将静压测量到 其中空气大体垂直于探针（10）的纵向轴线正交并进入压力端口（21A，22A，23A，24A），从而可以检测相对面对的压力端口中的压差，以测量相对的流量大小和流量 角。

公开(公告)号：WO1987001606A1

公开(公告)日：1987-03-26

申请号：PCT/US1986001859

申请日：1986-09-12

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W. ,  DELEO, Richard, V.

IPC: B01D19/00

CPC classification number: G01P5/17 ,  B01D53/26 ,  G01L19/0007

Abstract: A unitized drain manifold apparatus (10) for removing water from air in a conduit of an air data sensor system (9) for an aircraft (10) comprises a manifold (11) having a plurality of drain cavities (13) therein. Each drain cavity (13) has a center chamber portion (15) and two end drain chambers (23) positioned vertically above and below the center chamber portion (15) when the aircraft (10) is at rest. The end drain chambers (23) are used for accumulation of water which is separated from the air pressure signal. The cavities (13) are each equipped with two drain passageways (28) such that the accumulated water can be removed from the manifold (11) in normal or inverted positions. The positioning of the external drain passageways (28) permits water accumulation and removal to occur independently of the spatial orientation of the sensor (9) and manifold (11) and the symmetry of the manifold (11) permits it to be mounted on either side of the aircraft (10).

公开(公告)号：WO1993003326A1

公开(公告)日：1993-02-18

申请号：PCT/US1992005875

申请日：1992-07-14

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W.

IPC: G01C21/00

CPC classification number: G01P13/025

Abstract: An angle of attack sensor (10) is provided with ports (20, 21, 22, 23) for sensing flow angles in desired planes based upon differential pressure at the ports (20, 21 or 22, 23) when a reference axis of the sensor (10) changes relative to the flow stream. Impact pressure (qcm) is also measured, and the angle of attack is calculated by subtracting the pressures at the angle sensitive ports (20, 21 or 22, 23), and dividing by the measured impact pressure (qcm). At higher angles of attack, the denominator qcm approaches and passes through zero. It has been discovered that if the angle of attack ratio is inverted at some point when the denominator qcm approaches zero, the useable range of indication of angle of attack can be greatly extended.

公开(公告)号：WO1989002061A1

公开(公告)日：1989-03-09

申请号：PCT/US1988002794

申请日：1988-08-15

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W. ,  DELEO, Richard, V.

IPC: G01C21/00

CPC classification number: G01P5/165 ,  G01P13/025

Abstract: An air data sensor comprises a shaft probe (15) having a sharp edge orifice pitot port (24), and a tapered leading end (21) which blends into the main barrel portion (20) of the probe (15) a short distance downstream from the pitot port (24). Sets of sensing ports (31, 32, 33, 34) are utilized and at least one pair of ports (31, 32) or (33, 34) is oriented on a common axis and facing in opposite directions. By using the pressures sensed in more than one combination of ports, that is by co-using the pressure signals, static pressure, impact pressure, angle of attack and angle of sideslip can be derived. The ports (31, 32, 33, 34) are positioned on the tapered forward section (21), rearwardly of the pitot port (24) before the full size of the barrel (20) is reached, and are positioned very close to the leading end (24) for reliable readings at high angles of attack.

公开(公告)号：WO1985002903A1

公开(公告)日：1985-07-04

申请号：PCT/US1984001981

申请日：1984-12-03

Applicant: ROSEMOUNT, INC.

Inventor： ROSEMOUNT, INC. ,  HAGEN, Floyd, W.

IPC: G01C21/10

CPC classification number: G01P5/175 ,  G01L19/0007

Abstract: Sensing instrument (10) for sensing the angular position of the longitudinal axis (17) of a cyclindrical sensor body (14) of an object moving relative to a fluid medium with respect to a first plane. Such object has a leading end portion (15) joined to the sensor body (14) and exposed to the fluid medium. A first pair of pressure sensing ports (20 and 21) are on the object and face in the upstream direction and have their axes lying in a second plane at right angles to said first plane and disposed at predetermined angles with respect to the axis (17) of the object. A second pair of pressure sensing ports (22 and 23) on the object have their axes lying in the first plane, such axes being disposed at predetermined angles with respect to the axis (17) of the object. A single pressure port (16) on the object has an axis coinciding with the axis (17) of the object. The improvement comprises the leading end portion (15) of the sensor body (14) defining a spherical segment of one base.

Abstract translation: 用于感测相对于第一平面相对于流体介质移动的物体的环形传感器主体（14）的纵向轴线（17）的角度位置的传感仪器（10）。 这种物体具有接合到传感器主体（14）并暴露于流体介质的前端部分（15）。 第一对压力传感端口（20和21）位于物体上并且在上游方向上面，并且它们的轴线位于与所述第一平面成直角的第二平面中并相对于轴线（17）以预定角度设置 ）的对象。 物体上的第二对压力传感端口（22和23）的轴线位于第一平面中，这些轴相对于物体的轴线（17）以预定的角度设置。 物体上的单个压力端口（16）具有与物体的轴线（17）重合的轴线。 该改进包括传感器主体（14）的前端部分（15），其限定一个基部的球形段。

公开(公告)号：WO1985001578A1

公开(公告)日：1985-04-11

申请号：PCT/US1984001474

申请日：1984-09-17

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  HAGEN, Floyd, W.

IPC: G01L07/00

CPC classification number: G01P5/165 ,  G01L19/0007

Abstract: A sensing instrument (24) is used for sensing atmospheric pressure and the output is connected in a method of operation to provide accurate measurement information. The instrument (24) comprises an enclosure (26) that has a shape exposed to a fluid medium, which fluid medium may be moving at a certain velocity relative to the sensing instrument. The sensing instrument has at least one port (28) open to the fluid medium for sensing the velocity of the medium and for measuring a pressure of the fluid medium. The measured pressure is corrected for the effects of the velocity of the medium according to the formula PATM=PM + K2 V where PATM is atmospheric pressure, PM is measured pressure in the enclosure means, K2 is a constant that is a function of the shape of the enclosure means, the shape of the port means and the density of the medium and V is the velocity of the medium.

Abstract translation: 感测仪器（24）用于感测大气压力，并且输出以操作方法连接以提供精确的测量信息。 仪器（24）包括具有暴露于流体介质的形状的外壳（26），该流体介质可相对于感测器具以一定速度移动。 传感仪器具有至少一个通向流体介质的端口（28），用于感测介质的速度并用于测量流体介质的压力。 根据公式PATM = PM + K2 V 2对介质的速度的影响进行校正，其中PATM是大气压，PM是围封装置中的测量压力，K2是作为一个函数的常数 外壳形状的形状，端口装置的形状和介质的密度，V是介质的速度。

公开(公告)号：WO1983000217A1

公开(公告)日：1983-01-20

申请号：PCT/US1982000855

申请日：1982-06-24

Applicant: ROSEMOUNT INC.

Inventor： ROSEMOUNT INC. ,  DeLEO, Richard, V. ,  HAGEN, Floyd, W.

IPC: G01C21/00

CPC classification number: G01P5/165

Abstract: Un tube statique multiple monté avec des entretoises permet d'obtenir, comme cela est illustré, des systèmes multiples séparés de mesure de pressions statiques et utilise une sonde (10) avec des ensembles séparés (23, 24 et 35, 36) d'orifices de détection de pression pour chaque système. La sonde (10) est conçue avec une configuration de surface qui établit des conditions de pression statique sensiblement identiques pour chaque ensemble d'orifices de détection (23, 24 et 35, 36), la longueur axiale de la partie cylindrique (14) de la sonde de détection (10) étant maintenue à un minimum et les effets de pression provenant des structures adjacentes telles que l'entretoise (13) étant compensées. La structure comprend une partie cylindrique (14) de la sonde (10) ayant une configuration d'ondes annulaires en surface (27, 28, 29, 30) avec des sections de diamètres différents qui provoquent des changements importants et uniformes de la pression le long de la sonde (10) pour établir des zones de niveaux de pression positives et négatives pour une compensation aérodynamique. Les positions des orifices (23, 24 et 35, 36) pour les systèmes séparés sont sélectionnées à partir d'un profil de pression de la sonde, de sorte que les orifices se trouvent dans des zones de pression désirées.