IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0178440
(2005-07-12)
|
등록번호 |
US-7373849
(2008-05-20)
|
우선권정보 |
GB-0416204.6(2004-07-16) |
발명자
/ 주소 |
- Lloyd,Peter Gregory
- Stein,Paul Jonathan
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
7 |
초록
▼
A method for deploying a reconnaissance sonde, including the steps of: incorporating at least one environmental sensor and an associated communication device into a robust, aerodynamically efficient casing; deploying the sonde by imparting a spin and a directional velocity to the casing, sufficient
A method for deploying a reconnaissance sonde, including the steps of: incorporating at least one environmental sensor and an associated communication device into a robust, aerodynamically efficient casing; deploying the sonde by imparting a spin and a directional velocity to the casing, sufficient to carry the sonde into a region of interest; and establishing communication with the communication device, thereby enabling data from the sensor(s) to be transmitted to a remote location. A sonde for remote data collection is also provided, including at least one environmental sensor, an energy source and communication means. The sonde is generally shaped as a discus or saucer, a clay pigeon or skeet, for deployment by applying a spin and directional velocity to the sonde.
대표청구항
▼
The invention claimed is: 1. A method for deploying a reconnaissance sonde for providing information regarding a region of interest, said method comprising: providing a reconnaissance sonde incorporating an energy source, at least one environmental sensor and an associated communication device in a
The invention claimed is: 1. A method for deploying a reconnaissance sonde for providing information regarding a region of interest, said method comprising: providing a reconnaissance sonde incorporating an energy source, at least one environmental sensor and an associated communication device in a robust, aerodynamically efficient casing; deploying the sonde by imparting an axial spin and a radial directional velocity to the casing, sufficient to carry the sonde into the region of interest; and after the sonde has arrived in the region of interest, communicating with the communication device, whereby said sonde is enabled to transmit to a remote location sensor data from said at least one sensor, which sensor data characterize said region of interest. 2. The method according to claim 1, further comprising: placing a launching device on a vehicle; driving the vehicle through or alongside a region of interest; launching at least one reconnaissance sonde into the region of interest; withdrawing the vehicle from the region of interest; and establishing communication between the sonde and an operator located outside of the region of interest. 3. The method according to claim 1, where the step of deploying the sonde is performed by a mechanical launcher. 4. The method according to claim 1, where the step of deploying the sonde is performed by hand, by throwing the sonde in a manner which imparts to it both a radially oriented linear velocity and a rotational velocity about an axis that is oriented to provide gyro stabilization of the sonde in flight. 5. 6. A reconnaissance sonde for remote data collection, said sonde comprising: an outer casing; at least one environmental sensor, an energy source and communication device contained in said casing; wherein: the outer casing is shaped as one of a discus, a saucer, a clay pigeon and a sheet, for deployment of said sonde by applying an axial spin and a radial directional velocity to the outer casing; and the communication device is configured to operate when the sonde has arrived at a desired location in a region of interest, and to transmit data that characterize said region of interest, from the at least one sensor, to a remote location. 7. The sonde according to claim 6, wherein said casing is made of resilient material. 8. The sonde according to claim 6, further comprising a resilient ring around its outer periphery, for partially absorbing the shock of landing. 9. Sonde according to claim 6, wherein: the casing comprises upper and lower parts; and a cavity is formed between said upper and lower parts, for storage of the energy source, communication and control circuitry, and at least one sensor. 10. The sonde according to claim 6, wherein communications and control circuitry are provided on at least one circuit board, mounted inside the casing, between shock absorbing means. 11. The sonde according to claim 6, wherein the casing is formed in a single moulded part, including the energy source, communication and control circuitry, and the at least one sensor embedded therein. 12. The sonde according to claim 6, further comprising retractable antennas. 13. The sonde according to claim 6, wherein the at least one environmental sensor comprises at least one component selected from the group consisting of: a video camera; a gas detector; a detector of biological species; a microphone; a seismometer; a radiation detector; a humidity detector; an air pressure sensor; and a presence and/or motion detector. 14. A method for launching a remote data collection sonde having at least one environmental sensor, an energy source and a communication device with retractable antennas, all of which are contained in an outer casing that is shaped as one of a discus, a saucer, a clay pigeon and a skeet, said method comprising: deploying the sonde by imparting an axial spin and a radial directional velocity to the casing, sufficient to carry the sonde into a region of interest; after the sonde has arrived in the region of interest, communicating with the communication device, whereby said sonde is enabled to transmit to a remote location sensor data from said at least one sensor, which sensor data characterize said region of interest; maintaining the antennas in a retracted position during storage, during launching and during flight; and moving the antennas to an operational position after deployment of the sonde in said region of interest. 15. The method according to claim 14, wherein: the antennas are spring-loaded, and are initially latched into the retracted position; and impact of landing causes the latching to release, allowing the spring-loaded antennas to move under the action of the springs into their operational position.
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