公开(公告)号：EP0499741B1

公开(公告)日：1995-07-12

申请号：EP91310147.3

申请日：1991-11-04

Applicant: The Cessna Aircraft Company

Inventor： Gonzalez, Cesar

IPC: F02B19/10 ,  F02M59/32 ,  F02M45/02

CPC classification number: F02M59/32 ,  F02B1/04 ,  F02B19/108 ,  F02B19/1085 ,  F02M45/06 ,  F02M59/08 ,  F02M63/02 ,  Y02T10/125

公开(公告)号：EP0453249A3

公开(公告)日：1993-03-03

申请号：EP91303400.5

申请日：1991-04-17

Applicant: The Cessna Aircraft Company

Inventor： Gonzalez, Cesar

IPC: F02B75/26

CPC classification number: F02B75/26 ,  F01B3/02 ,  F02B3/06

Abstract: A barrel-type internal combustion engine (10) has a plurality of axially-parallel cylinders (14) containing reciprocatory pistons (18), arranged in a circular pattern around a drive shaft (16) with their axes parallel to the drive shaft axis. The drive shaft is supported in a cylinder block (12) in a cantilevered manner by sleeve bearings (22, 24). A wobble spider (20) is rotatably supported on an offset portion (17) at one end of the drive shaft (16) by further sleeve bearings (25, 26). A first roller bearing (28) is positioned between the offset portion (17) of the drive shaft (16) and the wobble spider (20), and another roller bearing (30) is positioned at the opposite end of the drive shaft (16) acting in opposition to the first roller (28) between the drive shaft (16) and the cylinder block (12) to support thrust loads.

公开(公告)号：EP0453249A2

公开(公告)日：1991-10-23

申请号：EP91303400.5

申请日：1991-04-17

Applicant: The Cessna Aircraft Company

Inventor： Gonzalez, Cesar

IPC: F02B75/26

CPC classification number: F02B75/26 ,  F01B3/02 ,  F02B3/06

Abstract: A barrel-type internal combustion engine (10) has a plurality of axially-parallel cylinders (14) containing reciprocatory pistons (18), arranged in a circular pattern around a drive shaft (16) with their axes parallel to the drive shaft axis. The drive shaft is supported in a cylinder block (12) in a cantilevered manner by sleeve bearings (22, 24). A wobble spider (20) is rotatably supported on an offset portion (17) at one end of the drive shaft (16) by further sleeve bearings (25, 26). A first roller bearing (28) is positioned between the offset portion (17) of the drive shaft (16) and the wobble spider (20), and another roller bearing (30) is positioned at the opposite end of the drive shaft (16) acting in opposition to the first roller (28) between the drive shaft (16) and the cylinder block (12) to support thrust loads.

Abstract translation: 桶型内燃机（10）具有多个沿轴向平行的圆柱体（14），其包含往复运动的活塞（18），绕圆周方向以驱动轴（16）的方式布置，其轴线平行于驱动轴的轴线。 驱动轴通过套筒轴承（22,24）以悬臂方式支撑在气缸体（12）中。 摆动齿轮（20）通过另外的套筒轴承（25,26）可旋转地支撑在驱动轴（16）的一端的偏移部分（17）上。 第一滚子轴承（28）位于驱动轴（16）的偏移部分（17）和摆动齿轮（20）之间，另一个滚子轴承（30）位于驱动轴（16）的相对端 ）与驱动轴（16）和气缸体（12）之间的第一辊（28）相对作用以支撑推力载荷。

公开(公告)号：EP0200337A3

公开(公告)日：1987-10-14

申请号：EP86302082

申请日：1986-03-20

Applicant: The Cessna Aircraft Company

Inventor： Voisard, Walter Bryan

IPC: B64C11/38

CPC classification number: B64C11/38

Abstract: A variable pitch propeller has blades (36), the position of which, at relatively low pitch angles is controlled by a beta valve through a lever (23) and a feedback collar (25), the position of the collar being controlled by a plurality of beta feedback rods (55). There is one rod (55) for each blade of the propeller, and the movement of the rods (55) is controlled by a blade yoke (50) which has arms (52) partially encircling the rods (55). A lost motion connection in the form of a sleeve (60) is carried on each of the rods (55) and is movable against a retraction spring (62) by the arms (52). A movable stop mechanism (75) engages the feedback rods (55) at a particular low blade angle position and temporarily interrupts the movement of the feedback rods (55) while the sleeves (60) move to a seated position against the retraction spring (62), and thereafter the movement of the rods (55) is again picked up, accompanied by movement of the stop mechanism (75) against a spring (80). The lost motion connection represented by the sleeve (60) permits movement of the blades under control of the beta feedback valve without accompanying movement of the feedback rod which causes a shifting of the blades to a still lower pitch position, thereafter followed by reclosing of the feedback valve with continued movement of the rods (55).

公开(公告)号：EP0915250B1

公开(公告)日：2003-04-16

申请号：EP97308937.8

申请日：1997-11-06

Applicant: Cessna Aircraft Company

Inventor： Gonzalez, Cesar

IPC: F02M37/00 ,  F02M37/20 ,  B64D37/32

CPC classification number: F02M37/0047 ,  B64D37/32 ,  F02M37/007 ,  F02M37/0088 ,  F02M37/20

公开(公告)号：EP0915250A1

公开(公告)日：1999-05-12

申请号：EP97308937.8

申请日：1997-11-06

Applicant: The Cessna Aircraft Company

Inventor： Gonzalez, Cesar

IPC: F02M37/00 ,  F02M37/20 ,  B64D37/32

CPC classification number: F02M37/0047 ,  B64D37/32 ,  F02M37/007 ,  F02M37/0088 ,  F02M37/20

Abstract: A fuel injection type aircraft fuel system for piston aircraft engines includes gravity flow fuel tanks (18, 19) in the aircraft, a pressurized fuel metering unit (14) on the aircraft engine (12), a fuel line (26, 38, 40, 42) connecting the metering unit to the fuel tanks, and an engine driven pump (16) in said fuel line positioned in the engine compartment (13). A vapor separator (60) is provided in said fuel line between the engine driven pump (16) and the fuel metering unit (14). A first vapor vent line (44) connects the vapor separator (60) to the fuel tanks (18, 19). A fuel reservoir (28) is provided in said fuel line between the fuel tanks and the engine driven pump. A submerged auxiliary pump (30) is located in said reservoir (28) to charge the system; an auxiliary pump bypass valve (34) is connected in parallel to said auxiliary pump; and a second vapor vent line (46) is connected between the reservoir (28) and the fuel tanks (18, 19).

Abstract translation: 用于活塞式飞机发动机的燃料喷射型飞机燃料系统包括飞行器中的重力流动燃料箱（18,19），飞机发动机（12）上的加压燃料计量单元（14），燃料管线（26,38,40 ，42）将所述计量单元连接到所述燃料箱，以及位于所述发动机室（13）中的所述燃料管路中的发动机驱动泵（16）。 在发动机驱动泵（16）和燃料计量单元（14）之间的所述燃料管线中设置有蒸气分离器（60）。 第一蒸气排放管线（44）将蒸汽分离器（60）连接到燃料箱（18,19）。 燃料箱（28）设置在燃料箱和发动机驱动泵之间的所述燃料管路中。 一个浸没式辅助泵（30）位于所述储存器（28）中以对系统充电; 辅助泵旁通阀（34）与所述辅助泵并联连接; 并且第二蒸气排放管线（46）连接在储存器（28）和燃料箱（18,19）之间。

公开(公告)号：EP0854301A1

公开(公告)日：1998-07-22

申请号：EP97304897.8

申请日：1997-07-04

Applicant: The Cessna Aircraft Company

Inventor： Gonzales, Cesar

IPC: F16C7/02

CPC classification number: F16C7/023

Abstract: A two piece connecting rod assembly (30) for an axial cylinder-type internal combustion engine includes a pair of opposed, side-by-side connecting rods (32, 34). Each connecting rod has a bearing sleeve (36, 37) at each end for pivotal engagement with respective universal joint trunnions (54, 49) connected to a piston (20) and spider (16) respectively. The two rods (32, 34) are connected to each other at their centers with their bearing sleeves (36, 37) spaced apart in concentric relation through a pair of raised bosses (40, 38) having mating surfaces (44, 42), and a bolt (46) for retention of the two rods (32, 34) as a unified structure.

Abstract translation: 用于轴向汽缸式内燃机的两件式连杆组件（30）包括一对相对的并排连接杆（32,34）。 每个连杆在每个端部处具有轴承套筒（36,37），用于分别与连接到活塞（20）和星形轮（16）的相应万向接头耳轴（54,49）枢转接合。 两个杆（32,34）在它们的中心处通过一对具有配合表面（44,42）的凸起凸起（40,38）以同心关系彼此间隔开的轴承套筒（36,37）彼此连接， 和用于保持两个杆（32,34）为一体结构的螺栓（46）。

公开(公告)号：EP0453249B1

公开(公告)日：1996-07-03

申请号：EP91303400.5

申请日：1991-04-17

Applicant: The Cessna Aircraft Company

Inventor： Gonzalez, Cesar

IPC: F02B75/26

CPC classification number: F02B75/26 ,  F01B3/02 ,  F02B3/06

公开(公告)号：EP0715160A2

公开(公告)日：1996-06-05

申请号：EP95308572.7

申请日：1995-11-29

Applicant: The Cessna Aircraft Company

Inventor： Gonzalez, Cesar ,  Cheek, James

IPC: G01L23/22

CPC classification number: G01L23/225 ,  G01L23/222

Abstract: The invention relates to a detonation indication system for an internal combustion piston engine of an aircraft, which senses detonation by means of a sensor comprising a piezoelectric force transducer (12) installed under a the spark plug of each cylinder of the engine. The transducer produces an on-going combustion pressure-induced charge signal which is converted into a voltage signal by a charge converter (14). A comparator gating circuit (16) removes, from the voltage signal, signal components, associated with intake and exhaust strokes, which occur below a predetermined combustion pressure. A high-pass frequency filter (18) then removes signal components associated with low frequency changes in combustion pressure. The output from the filter (18) is applied to an RMS-to-direct current converter (20) which converts the output into a direct current voltage proportional to the RMS value of the filter output. The output from the converter (20) is applied to peak and hold circuitry (22) which holds the peak value of the converter output corresponding to the most severe detonation event which occurs during an adjustable reset time period. A digital display (24) is provided which receives signals from the circuit (22) corresponding to the peak values occurring during successive reset periods and provides a numerical read-out indicative of the severity of the associated detonation events.

Abstract translation: 本发明涉及一种用于飞行器的内燃活塞发动机的爆震指示系统，其通过包括安装在发动机的每个气缸的火花塞之下的压电力传感器（12）的传感器来感测爆震。 换能器产生正在进行的燃烧压力感应充电信号，该电荷信号由电荷转换器（14）转换成电压信号。 比较器门控电路（16）从电压信号中去除发生在预定燃烧压力以下的进气和排气冲程的信号分量。 然后，高通滤波器（18）去除与燃烧压力的低频变化相关联的信号分量。 来自滤波器（18）的输出被施加到RMS到直流电流转换器（20），其将输出转换成与滤波器输出的RMS值成比例的直流电压。 来自转换器（20）的输出被施加到峰值保持电路（22），其保持与在可调整的复位时间段期间发生的最严重的爆震事件相对应的转换器输出的峰值。 提供数字显示器（24），其接收来自电路（22）的信号，该信号对应于在连续复位周期期间出现的峰值，并且提供指示相关爆震事件的严重性的数字读出。

公开(公告)号：EP0007378B1

公开(公告)日：1984-01-25

申请号：EP78900274.8

申请日：1978-10-30

Applicant: CESSNA AIRCRAFT COMPANY

Inventor： MOORE, Nathaniel, Newton

IPC: G01C19/36 ,  G01C17/28 ,  G05D1/08

CPC classification number: G01C19/44 ,  G01C17/28 ,  G01C19/28 ,  G01C19/36 ,  Y10T74/1254

Abstract: A gyroscopic device of the type having a short-circuited rotor winding or conductor (10) so shaped so as to produce axial and radial flux components when rotated in the earth's magnetic field is coupled to a coaxial sensing coil (15) coaxial which gyroscopically stabilized thereby, signals induced in the sensing coil due to the axial flux component of the rotor is used to derive magnetic heading information and there is provided at least one further coil (41) on the supporting body and inductively linked to the sensing coil and rotor such that when the sensing coil is gyroscopically stabilized by the rotor, the coil supported on the supporting body in relation to the gyroscopically stabilized sensing coil is such that any changes in angular orientation of the supporting body relative to the gyroscopically stabilized sensing coil introduces changes in the signal voltages induced in the coils. The further coil on the supporting body may be excited with one or more excitation signals of a frequency different than the angular speed of the rotor (10) and constituted by pairs of orthogonally related coils on all three axes namely, the roll (41, 42), pitch (43, 44) and yaw (45, 46) axes. The coil located on the yaw axis is coaxial with the gyroscopically stabilized sensing coil in the rest position and is used for eliminating ambiguities.