68 results about "Biplane" patented technology

A microscopy system is configured for creating 3D images from individually localized probe molecules. The microscopy system includes a sample stage, an activation light source, a readout light source, a beam splitting device, at least one camera, and a controller. The activation light source activates probes of at least one probe subset of photo-sensitive luminescent probes, and the readout light source causes luminescence light from the activated probes. The beam splitting device splits the luminescence light into at least two paths to create at least two detection planes that correspond to the same or different number of object planes of the sample. The camera detects simultaneously the at least two detection planes, the number of object planes being represented in the camera by the same number of recorded regions of interest. The controller is programmable to combine a signal from the regions of interest into a 3D data.

The present invention is a 2 passenger aircraft capable of vertical and conventional takeoffs and landings, called a jyrodyne. The jyrodyne comprises a central fuselage with biplane-type wings arranged in a negative stagger arrangement, a horizontal ducted fan inlet shroud located at the center of gravity in the top biplane wing, a rotor mounted in the shroud, outrigger wing support landing gear, a forward mounted canard wing and passenger compartment, a multiple vane-type air deflector system for control and stability in VTOL mode, a separate tractor propulsion system for forward flight, and a full-span T-tail. Wingtip extensions on the two main wings extend aft to attach to the T-tail. The powerplants consist of two four cylinder two-stroke reciprocating internal combustion engines. Power from the engines is distributed between the ducted fan and tractor propeller through the use of a drivetrain incorporating two pneumatic clutches, controlled by an automotive style footpedal to the left of the rudder pedals. When depressed, power is transmitted to the ducted fan for vertical lift. When released, power is transmitted to the tractor propeller for forward flight. The aircraft can also takeoff and land in the conventional manner with a much larger payload, and is easily converted to amphibious usage. Landing gear is a bicycle arrangement with outriggers. The aircraft combines twin engines, heavy-duty landing gear, controlled-collapse crashworthy seats with a low stall speed and high resistance to stalls to eliminate any region of the flight regime where an engine or drivetrain failure could cause an uncontrollable crash.

The invention relates to an orthopedic robot navigation device and a positioning system. The orthopedic robot navigation device comprises a machine seat and a four-freedom degree biplane positioning mechanism, wherein the four-freedom degree biplane positioning mechanism is arranged on the machine seat and connected with the machine seat. The four-freedom degree biplane positioning mechanism comprises a first series connection mechanical arm, a second series connection mechanical arm and a straight lever-shaped guide device, wherein the first series connection mechanical arm comprises a first horizontal motion assembly, a first vertical motion assembly and a first cardan joint which are connected in series; the second series connection mechanical arm comprises a second horizontal motion assembly, a second vertical motion assembly and a second cardan joint which are connected in series; both the first horizontal motion assembly and the second first horizontal motion assembly are connected with the machine seat; and the straight lever-shaped guide device realizes the self positioning by being clamped with the first cardan joint and the second cardan joint respectively. The device is arranged at the side surface of the wounded limb, realizes the accurate positioning by the straight lever-shaped guide device and is suitable for a bone fixing operation of any wounded limb part, thereby more favorably meeting the requirement of the operation.

The present invention provides an unmanned airborne reconnaissance vehicle having a fuselage, a forward wing pair and a rearward wing pair vertically separated by a gap and staggered fore and aft therebetween such that a general biplane configuration is formed. The present invention provides a pair of wing tip plates for joining the wing tips of the forward and rearward wings. The unmanned airborne reconnaissance vehicle of the present invention includes a power plant to propel the vehicle through the air and a generally T-shaped tail having a vertical stabilizer including a rudder and a full span elevator.

One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. 1.) having a horizontal rotor, a. providing lift and propulsion, and communicating at or near its centre to structural elements, or fuselage, b. Upon or within the fuselage structure is attached a platform, to which a payload, or occupant or pilot, d. is secured in such a manner as to permit a movement, or range-of-motion, of the payload, as a means of weight-shifting, or mass-balancing, of the vehicle for stability and control in flight. At least two planar elements, or descent-vanes, c.i & c.ii are connected to a structural element of the fuselage at a location which provides vertical and horizontal separation between the rotor and the descent-vanes, thus creating a tandem, biplane arrangement of two aerodynamically active elements which are aerodynamically balanced to provide stability and controllability in hovering flight, in forward flight, and in un-powered gliding and vertical descents. Other embodiments are described and shown.

A tumor is tracked in sequences of biplane images by generating a set of segmentation hypotheses using a 3D model of the tumor, a biplane geometry, and a previous location of the tumor as determined from the pairs of biplane images. Volume prior probabilities are constructed based on the set of hypotheses. Seed pixels are selected using the volume prior probabilities, and a bi-plane dual image graph is constructed using intensity gradients and the seed pixels to obtaining segmentation masks corresponding to tumor boundaries using the image intensities to determine a current location of the tumor.

A biplane X-ray imaging system is provided. The biplane X-ray imaging system has two recording units disposed in different planes. Each of the recording units has an X-ray detector and an X-ray source. The first recording unit is a phase-contrast recording unit for phase-contrast X-ray imaging. The second recording unit is a conventional recording unit for conventional x-ray imaging.

The invention discloses a time-triggered Ethernet switch based on a biplane and a packet switching method, which mainly solve the problem that the deterministic and real-time performances of the existing time-triggered Ethernet switch forwarding a time-triggered TT service are poor. The device comprises an input shunting module (1), a clock synchronizer (2), a time-triggered TT switching plane (3), an event-triggered ET switching plane (4) and an output arbitration module (5). The input shunting module is respectively connected with the clock synchronizer, the TT switching plane, and the ET switching plane, to complete switch clock synchronization and to forward the TT service frame and the ET service frame respectively; the TT switching plane and the ET switching plane are both connectedwith the output arbitration module to select a service frame which is preferentially sent and to complete sending of data. The time-triggered Ethernet switch based on a biplane and the packet switching method in the invention can ensure absolute priority forwarding of the time-triggered TT service, reduce the forwarding delay of the time-triggered TT service, and can be applied to a time-triggeredswitching network with high speed and low delay.

An embodiment of the invention discloses a high tibial biplane osteotomy navigation guide plate. The guide plate comprises an upper split guide plate and a lower split guide plate which are fixedly connected by two connecting rods. An osteotomy guide groove is formed between the upper split guide plate and the lower split guide plate. Two non-parallel kirschner wire fixing guide holes are formed in the middles of the upper split guide plate and the lower split guide plate. Parallel guide holes are formed in the upper part of the upper split guide plate. One side of the upper split guide plateis provided with an angle guide backup plate. The upper split guide plate and the lower split guide plate are respectively provided with an upper angle positioning rod and a lower angle positioning rod in a vertical corresponding mode, and the end portions are respectively connected with an upper angle positioning guide hole and a lower angle positioning guide hole. The guide plate can not only eliminate the difference between experiences of doctors in a surgery, but also greatly reduce the operation time and the amount of bleeding during the surgery to achieve the best ideal state of osteotomy. The recovery time of a patient is greatly reduced, postoperative complications are reduced, and expenses in the recovery period are saved.

The invention discloses a biplane ultrasound-guided radioactive seed implantation system for prostate. The system comprises a fixing seat, a supporting column, a universal joint arm, a fixing clip, astepper and an implantation template, wherein the stepper comprises a main frame, one end of the main frame is fixedly connected with a template supporting frame, and a scale ruler is arranged on theside wall of the main frame; a hollow lead screw of a coarse-fine adjustment mechanism is arranged in the main frame, and a first angle line is arranged on a rotating frame of a clamp; the template supporting frame is movably connected with the implantation template, and a second angle line and an angle value are arranged on the implantation template; the second angle line on the implantation template corresponds to the first angle line on the stepper, and the position of a puncture needle corresponding to a sagittal plane scanning image is quickly determined by adjusting the sagittal plane scanning angle of a biplane ultrasonic probe, so that operation time is shortened; coarse and fine adjustment units of the coarse-fine adjustment mechanism are coaxial, operation can be performed conveniently and quickly with only one hand during the operation, and operation efficiency is improved; the system is flexible and simple to operate, can be sterilized at high temperature, and is easy to disassemble and assemble and convenient to carry and store.

The invention provides a deformation biplane, and belongs to the technical field of airplanes. The deformation biplane comprises a plane body, upper wings, lower wings and an empennage, wherein a control device and a power device are arranged in the body; the empennage is positioned at the tail of the plane body; the upper wings are similar to conventional wings and are symmetrically distributed on the left side and the right side of the upper end of the plane body; the lower wings are symmetrically distributed on the left side and the right side of the lower end of the plane body; and each lower wing comprises a retractable rod, a folding wing rib, a flexible skin and a retracting device. A plurality of small wing ribs are arranged on each folding wing rib; small holes are separately formed in the small wing ribs, and each folding wing rib is serially connected to the corresponding retractable rod through the corresponding small holes; each flexible skin is divided into two parts, andone part of each flexible skin wraps the corresponding folding wing rib while the other part of each flexible skin is rolled in the retracting device; the roots of the lower wings are fixed by the retracting devices; the retractable rods and the retracting devices are adjusted through a control device; and when the biplane flies in air, a biplane mode and a monoplane mode of the biplane can be switched. The deformation biplane is simple in structure, advantages of a monoplane and advantages of a biplane are combined, the flying efficiency is high, and the deformation biplane is multipurpose.

The invention relates to a millimeter wave one-dimensional single-pulse biplane reflecting antenna. The millimeter wave one-dimensional single-pulse biplane reflecting antenna comprises a polarization grid reflecting board, a polarization twist and focusing reflecting board and a feed source, wherein the polarization twist and focusing reflecting board is located below the polarization grid reflecting board and is electrically insulated from the polarization grid reflecting board; the feed source is arranged in the center of the polarization twist and focusing reflecting board and penetrates through the polarization twist and focusing reflecting board. The millimeter wave one-dimensional single-pulse biplane reflecting antenna has the advantages that on the condition of ensuring the performance, the longitudinal dimension is effectively decreased. The feature of a low section is achieved, the purpose of reducing the overall dimension is achieved, in addition, the feed source shielding effect can be effectively avoided, the overall radiation performance of the antenna is improved, the polarization purity can be effectively improved, the cross-polarization rejection ratio can be greatly improved by adjusting the dimension of a polarization grid of an upper polarization grid layer, and therefore higher polarization purity is obtained.

An ultrasound system with a matrix array (500) probe (10) operable in the biplane mode is used to assess stenosis of a blood vessel by simultaneously displaying two color Doppler biplane images (60a, 60b) of the vessel, one a longitudinal cross-sectional view (60a) and the other a transverse cross-sectional view (60b). The two image planes intersect along a Doppler beam line (68) used for PW Doppler. A sample volume graphic (SV) is positioned over the blood vessel at the peak velocity location in one image, then positioned over the blood vessel at the peak velocity location in the other image. As the sample volume location is moved in one image, the plane and/or sample volume location of the other image is adjusted correspondingly. Spectral Doppler data (62) is then acquired and displayed from the sample volume location.

The invention relates to a laser straightness interferometer light path system which solves the problem of low measuring sensitivity of the traditional straightness interferometer. The laser straightness interferometer light path system comprises a laser head (1), an assembly (A), a double optical wedge (11) and a biplane reflecting mirror (12). The assembly (A) is formed by binding a polarizing beam splitter (6), a reflecting mirror (7), a pyramid prism (8) and quarter wave plates (9) and (10) into an integer. The double optical wedge (11) is formed by binding an upper wedge and a lower wedge, and the bottom surface of the upper wedge is opposite to that of the lower wedge. f1 light and f2 light emitted by the laser head (1) respectively pass through the upper wedge and the lower wedge of the double optical wedge (11) after beam splitting by the assembly (A), vertically irradiate the two reflecting planes of the biplane reflecting mirror (12), and go back the same way. A measured object and the double optical wedge (11) move along the Y direction; when a displacement is generated in the Z direction, i.e. a straightness error exits, the f1 light and the f2 light produce opposite optical path differences, and thus, the straightness error value can be calculated out. The invention has high measuring sensitivity, compact structure, low cost and convenient assembly.

The invention discloses a method for measuring an electric parameter of a gallium arsenide pseudomorphic HEMT (high electron mobility transistor) material and relates to a method for measuring the electric parameter of a semiconductor material. The method is used for measuring a carrier concentration and a mobility in the gallium arsenide pseudomorphic HEMT material by a non-contact Hall measurement method and comprises the following steps of: measuring an incident power, a reflection power and a Hall effect microwave power of the measured gallium arsenide pseudomorphic HEMT material by a microwave Hall measurement device; calculating conductance tensors of a measured sample in different magnetic fields; and calculating the carrier concentration and the mobility of the gallium arsenide pseudomorphic HEMT material. The method disclosed by the invention is nondestructive, is convenient and rapid, has high efficiency and can be used for accurately measuring the carrier concentration and the mobility in the gallium arsenide-based biplane doped pseudomorphic HEMT material. The defects that the existing measurement method is fussy to operate, has low efficiency and a certain error and cannot really and completely reflect the electrical properties of the material are overcome.

The invention is a mechanical flapping wing flying device similar to the flying of birds and insects. The swing fulcrum a on the two driving rods is constrained on the horizontal slide rod outside the casing, the two circular trajectory points m are constrained in the inner ring groove of the casing, and the two linear trajectory points b are connected in parallel; the fixed point G on the two zoom wings is connected to the two driving rods The upper corresponding points are hinged, and the upper zoom point S of the two zoom wings is hinged with the end holes outside the staggered racks in the side slots of the two drive rods; when the drive pin is stuck, the power is input from the parallel connection to drive the wings to flutter. During the double-wing flight, the angle of the flapping wings can be changed at any time or the wings can be locked at will, and the conversion is fast and reliable. The wings can be equipped with a zoom-wing mechanism that alternately bends up and down. When the wings flap, the inertial impact at the turn-back point has double crank rollers. The mechanism absorbs and any point on the wings has alternating changes of gradual acceleration and gradual deceleration, so the flying posture is beautiful and natural. There are monoplanes and biplanes, and a variety of fixed and zooming wings. It can develop popular manned flapping-wing aircraft and unmanned flapping-wing aircraft for various purposes.

A sailboat having a hull, a sail assembly and a keel is additionally equipped with an assembly of stationary or pivoted hydrofoils—the object of the present invention. The foils are mounted on both sides of the hull and placed above and below center of mass (C.G.) of a sailboat in a biplane manner that allows efficiently compensating yacht's roll. The assembly of stationary hydrofoils of the present invention, which upper foils can go out of water when a yacht is heeling over also develop momentums efficiently compensating wind list. Another embodiment of the present invention, which comprises hydrofoils assembled in a triplane manner, allows efficiently compensating wind list at low sailboat speed. Biplane assembly of pivoted hydrofoils of the present invention allows compensation all adverse momentum affecting a sailing vessel.