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公开(公告)号：WO2004013574A2
公开(公告)日：2004-02-12
申请号：PCT/US0324091
申请日：2003-08-01
Applicant: DRAPER LAB CHARLES S
Inventor： MARTORANA RICHARD T , ASH MICHAEL E
CPC classification number: G01V1/52 , G01V11/002
Abstract: An environmentally mitigated navigation system includes a thermal isolating chamber, an inertial measurement unit that can include individual gyroscopes and accelerometers for making inertial measurements, and a temperature control system; the temperature control system includes a thermoelectric cooling system, which in a powered mode maintains the inertial measurement unit at a substantially predetermined temperature, and a phase change device for maintaining the inertial measurement unit or inertial sensors at substantially a predetermined temperature in an unpowered mode; the phase change device substantially maintains the predetermined temperature by changing phase to define a stable temperature window for the inertial measurement unit or individual sensors to make inertial measurements during the unpowered mode as well as during the powered mode.
Abstract translation: 环境减轻的导航系统包括热隔离室，惯性测量单元，其可以包括单独的陀螺仪和用于进行惯性测量的加速度计，以及温度控制系统; 温度控制系统包括热电冷却系统，其以动力模式将惯性测量单元维持在基本上预定的温度;以及相变装置，用于将惯性测量单元或惯性传感器维持在基本上预定温度的无动力模式; 相变装置通过改变相位来维持预定温度，以定义用于惯性测量单元或各个传感器的稳定温度窗口，以在无动力模式期间以及在动力模式期间进行惯性测量。
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公开(公告)号：WO2004013573A3
公开(公告)日：2004-06-17
申请号：PCT/US0323977
申请日：2003-08-01
Applicant: DRAPER LAB CHARLES S
Inventor： ASH MICHAEL E , MARTORANA RICHARD T
CPC classification number: E21B47/022 , G01V1/52 , G01V11/002
Abstract: An omnidirectional borehole navigation system is provided which features a housing (32) for traversing a borehole (18); a gimbal system (34) including at least one outer gimbal connected to the housing and at least one inner gimbal nested in and connected to the outer gimbal; a solid state three-axis gyro assembly mounted on the inner gimbal; a solid state three-axis accelerometer assembly mounted on the inner gimbal; gyro logic circuits on the inner gimbal responsive to the three-axis gyro assembly to produce the inertial angular rate about each gyro input axis; accelerometer logic circuits on the inner gimbal to produce the non-gravitational acceleration along each accelerometer input axis; and a microprocessor responsive to the gyro logic circuits and the accelerometer logic circuits for determining the attitude and the position and velocity of the housing in its borehole.
Abstract translation: 提供了一种全向钻孔导航系统，其具有用于横穿井眼（18）的壳体（32）; 一种万向节系统（34），包括至少一个连接到壳体的外部万向架和至少一个嵌入并连接到外部万向架的内部万向架; 安装在内部万向节上的固态三轴陀螺仪组件; 安装在内部万向节上的固态三轴加速度计组件; 响应于三轴陀螺仪组件的内部万向架上的陀螺逻辑电路产生围绕每个陀螺仪输入轴线的惯性角速度; 内部万向节上的加速度计逻辑电路，沿着每个加速度计输入轴产生非重力加速度; 以及响应于陀螺逻辑电路和加速度计逻辑电路的微处理器，用于确定壳体在其钻孔中的姿态和位置和速度。
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公开(公告)号：WO0232762A3
公开(公告)日：2004-01-08
申请号：PCT/US0131631
申请日：2001-10-11
Applicant: DRAPER LAB CHARLES S
Inventor： MARTORANA RICHARD T , ANDERSON JAMIE , SPEARING SIMON MARK , KESSLER SETH , APPLEBY BRENT , BERGMANN EDWARD , GEORGE SEAN , JACOBSON STEVEN , FLYER DONALD , DRELA MARK , KIRKOS GREGORY , MCFARLAND WILLIAM JR
CPC classification number: F42B15/105 , B64C39/024 , B64C2201/042 , B64C2201/084 , B64C2201/102 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64C2201/185 , B64C2201/201
Abstract: A flyer assembly (10) is adapted for launching with, transit in, and deployment from an artillery shell (22). The flyer assembly (10) includes a jettisonable shroud (12) and a flyer (14). The flyer (14) is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer (14) is positionable within the shroud (12) with the flyer axis parallel to the shroud axis and the shell axis. The flyer (14) includes a body member disposed about the flyer axis, and a foldable wing assembly (20) mounted to the body member. THe wing assembly (20) is characterized by a plurality of nested wing segments (32) when the flyer is in the first state. THe wing assembly (20) is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly (10) is launched from an artillery cannon, and can thus reach a target quickly, without expending energy stored with theflyer. During launch, the flwyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along eht flyer axis.
Abstract translation: 传单组件（10）适用于从炮弹（22）发射，转运和展开。 传单组件（10）包括可喷射的护罩（12）和传单（14）。 飞翼（14）适于在处于第一状态时承受沿飞行器轴线的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单（14）可定位在护罩（12）内，飞翼轴线平行于护罩轴线和外壳轴线。 传单（14）包括围绕飞行器轴线设置的主体构件和安装到主体构件的可折叠翼组件（20）。 当翼片处于第一状态时，翼组件（20）的特征在于多个嵌套翼段（32）。 翼组件（20）可配置成展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件（10）从炮兵炮发射，并且因此能够快速地达到目标，而不会消耗与飞行器一起存储的能量。 在发射过程中，飞镖耦合到护罩上，以便在飞行器沿着飞行器轴线的加速期间将传单的一部分保持在张紧状态。
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公开(公告)号：WO0232762A9
公开(公告)日：2003-02-20
申请号：PCT/US0131631
申请日：2001-10-11
Applicant: DRAPER LAB CHARLES S
Inventor： MARTORANA RICHARD T , ANDERSON JAMIE , SPEARING SIMON MARK , KESSLER SETH , APPLEBY BRENT , BERGMANN EDWARD , GEORGE SEAN , JACOBSON STEVEN , FLYER DONALD , DRELA MARK , KIRKOS GREGORY , MCFARLAND WILLIAM JR
CPC classification number: F42B15/105 , B64C39/024 , B64C2201/042 , B64C2201/084 , B64C2201/102 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64C2201/185 , B64C2201/201
Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load an high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.
Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 机翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高温环境的高负载，并且可以承受大约16,000g的安装载荷。
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Patent Agency Ranking
公开(公告)号：AU2003265338A8
公开(公告)日：2004-02-23
申请号：AU2003265338
申请日：2003-08-01
Applicant: DRAPER LAB CHARLES S
Inventor： MARTORANA RICHARD T , ASH MICHAEL E
Abstract: An environmentally mitigated navigation system includes a thermal isolating chamber, an inertial measurement unit that can include individual gyroscopes and accelerometers for making inertial measurements, and a temperature control system; the temperature control system includes a thermoelectric cooling system, which in a powered mode maintains the inertial measurement unit at a substantially predetermined temperature, and a phase change device for maintaining the inertial measurement unit or inertial sensors at substantially a predetermined temperature in an unpowered mode; the phase change device substantially maintains the predetermined temperature by changing phase to define a stable temperature window for the inertial measurement unit or individual sensors to make inertial measurements during the unpowered mode as well as during the powered mode.
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公开(公告)号：AU2003265338A1
公开(公告)日：2004-02-23
申请号：AU2003265338
申请日：2003-08-01
Applicant: DRAPER LAB CHARLES S
Inventor： ASH MICHAEL E , MARTORANA RICHARD T
Abstract: An environmentally mitigated navigation system includes a thermal isolating chamber, an inertial measurement unit that can include individual gyroscopes and accelerometers for making inertial measurements, and a temperature control system; the temperature control system includes a thermoelectric cooling system, which in a powered mode maintains the inertial measurement unit at a substantially predetermined temperature, and a phase change device for maintaining the inertial measurement unit or inertial sensors at substantially a predetermined temperature in an unpowered mode; the phase change device substantially maintains the predetermined temperature by changing phase to define a stable temperature window for the inertial measurement unit or individual sensors to make inertial measurements during the unpowered mode as well as during the powered mode.
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公开(公告)号：AU2003261318A8
公开(公告)日：2004-02-23
申请号：AU2003261318
申请日：2003-08-01
Applicant: DRAPER LAB CHARLES S
Inventor： MARTORANA RICHARD T , ASH MICHAEL E
Abstract: An omnidirectional borehole navigation system is provided which features a housing for traversing a borehole; a gimbal system including at least one outer gimbal connected to the housing and at least one inner gimbal nested in and connected to the outer gimbal; a solid state three-axis gyro assembly mounted on the inner gimbal; a solid state three-axis accelerometer assembly mounted on the inner gimbal; gyro logic circuits on the inner gimbal responsive to the three-axis gyro assembly to produce the inertial angular rate about each gyro input axis; accelerometer logic circuits on the inner gimbal to produce the non-gravitational acceleration along each accelerometer input axis; and a microprocessor responsive to the gyro logic circuits and the accelerometer logic circuits for determining the attitude and the position and velocity of the housing in its borehole.
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公开(公告)号：AU2003261318A1
公开(公告)日：2004-02-23
申请号：AU2003261318
申请日：2003-08-01
Applicant: DRAPER LAB CHARLES S
Inventor： ASH MICHAEL E , MARTORANA RICHARD T
Abstract: An omnidirectional borehole navigation system is provided which features a housing for traversing a borehole; a gimbal system including at least one outer gimbal connected to the housing and at least one inner gimbal nested in and connected to the outer gimbal; a solid state three-axis gyro assembly mounted on the inner gimbal; a solid state three-axis accelerometer assembly mounted on the inner gimbal; gyro logic circuits on the inner gimbal responsive to the three-axis gyro assembly to produce the inertial angular rate about each gyro input axis; accelerometer logic circuits on the inner gimbal to produce the non-gravitational acceleration along each accelerometer input axis; and a microprocessor responsive to the gyro logic circuits and the accelerometer logic circuits for determining the attitude and the position and velocity of the housing in its borehole.
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公开(公告)号：AU3038702A
公开(公告)日：2002-04-29
申请号：AU3038702
申请日：2001-10-11
Applicant: DRAPER LAB CHARLES S
Inventor： MARTORANA RICHARD T , ANDERSON JAMIE , SPEARING SIMON MARK , KESSLER SETH , APPLEBY BRENT , BERGMANN EDWARD , GEORGE SEAN , JACOBSON STEVEN , FLYER DONALD , DRELA MARK , KIRKOS GREGORY , MCFARLAND WILLIAM
Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.
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