33results about How to "Improve task adaptability" patented technology

An adaptive speech recognition system is provided including an input for receiving a signal derived from a spoken utterance indicative of a certain vocabulary item, a speech recognition dictionary, a speech recognition unit and an adaptation module. The speech recognition dictionary has a plurality of vocabulary items each being associated to a respective dictionary transcription group. The speech recognition unit is in an operative relationship with the speech recognition dictionary and selects a certain vocabulary item from the speech recognition dictionary as being a likely match to the signal received at the input. The results of the speech recognition process are provided to the adaptation module. The adaptation module includes a transcriptions bank having a plurality of orthographic groups, each including a plurality of transcriptions associated with a common vocabulary item. A transcription selector module in the adaptation module retrieves a given orthographic group from the transcriptions bank on a basis of the vocabulary item recognized by the speech recognition unit. The transcription selector module processes the given orthographic group on the basis of the signal received at the input to select a certain transcription from the transcriptions bank. The adaptation module then modifies a dictionary transcription group corresponding to the vocabulary item selected as being a likely match to the signal received at the input on the basis of the selected certain transcription.

The present invention relates to the technical field of unmanned aerial vehicles, especially to an unmanned aerial vehicle taking-off and landing method and system based on a mobile platform. The mobile platform is provided with a control device configured to control taking-off and landing of the unmanned aerial vehicle, the unmanned aerial vehicle taking-off and landing method comprises a taking-off process and a landing process, the taking-off process comprises the steps that: the control device sends a taking-off command to the unmanned aerial vehicle, the unmanned aerial vehicle determinesthat when the unmanned aerial vehicle itself meets a taking-off condition, the unmanned aerial vehicle executes the taking-off motion, and the landing process comprises the steps that: the unmanned aerial vehicle collects relative position information between the unmanned aerial vehicle itself and the mobile platform and flies to the position above the mobile platform to execute landing motion when determining that the unmanned aerial vehicle meets a landing condition until landing onto the mobile platform. The method and the system allow the unmanned aerial vehicle to achieve taking-off andlanding on a support platform in a mobile state so as to enlarge the motion range of the unmanned aerial vehicle and reduce the time cost of the unmanned aerial vehicle for task execution.

The invention provides a space capturing and locking device. The space capturing and locking device comprises a driving structure and a driven structure. The driving structure comprises a shell assembly, a driving assembly, a transmission assembly, an upper plate auxiliary assembly and three sets of finger assemblies. The shell assembly is used for supporting and being connected with the driving assembly, the transmission assembly, the upper plate auxiliary assembly and the finger assemblies. The upper plate auxiliary assembly comprises rollers. The finger assemblies comprise four-bar mechanisms. The driving assembly drives the transmission assembly, the transmission assembly converts rotational motion into linear motion, the transmission assembly controls the finger assemblies to move upwards and downwards, the three sets of finger assemblies are closed due to compression of the rollers when moving downwards, and then the driven structure matched with the driving structure is clamped. The four-bar mechanism is in linkage when the finger assemblies move upwards, the finger assemblies are driven to be opened, and then the driven structure is released. The space capturing and locking device can be used for capturing and locking of a space mechanical arm on a small aircraft, and the advantages of being low in weight, small in size, large in tolerance and diverse in capture object are achieved.

The invention discloses an air-to-ground guided missile projection glide-section guidance method including speed process constraint and multi-terminal constraint. The method comprises the steps of dividing the resistance consumed energy into a part for overcoming the gravity and a turning maneuver part according to the characteristic that the lift-drag ratio of an aircraft is not great when a projection section nearly stays at an equilibrium gliding state, and respectively acquiring an expression; solving by utilizing the energy conservation law, and obtaining a corresponding relation of a terminal speed and longitudinal distance, so that the terminal speed constraint problem can be solved by utilizing the general guidance law; finally designing a speed control feedback by utilizing a normal control boundary and an axial control boundary, so that a guidance law which can simultaneously meet the requirements of terminal height, terminal angle, terminal speed and maximal speed constraint can be obtained. The air-to-ground guided missile projection glide-section guidance method has the advantages that the multi-constraint guidance problem of the projection glide section can be solved by adopting a closed-loop analysis guidance method, so that not only can good task adaptability be realized, but also convenience in engineering realization can be realized.

The invention discloses an unmanned aerial vehicle cluster area covering method and device based on virtual potential field functions. The method comprises the following steps that firstly, target area geometrical center coordinates are calculated according to convex polygonal target area vertex coordinates; then, according to the area vertex coordinates, the geometrical center coordinates, unmanned aerial vehicle absolute position measurement values, and relative position measurement values of unmanned aerial vehicles relative to nearby unmanned aerial vehicles, virtual attraction and repulsion functions are calculated; finally, by judging whether the unmanned aerial vehicles enter a target area or not, decision-making unmanned aerial vehicles adopt different movement rules, and it is achieved that unmanned aerial vehicle clusters continuously cover the area. By adopting the method, the unmanned aerial vehicle clusters can continuously cover any convex polygonal area, and unmanned aerial vehicles are uniformly distributed in the area. Compared with a traditional area coverage method, the method has the advantages of small calculation amount control, little information processing amount and diversified coverage area shapes. In addition, the invention also provides a device applying the method.

The invention provides a trailing edge variable camber wing driven by piezoelectric fiber materials. The wing comprises a leading edge fixing section with the invariable camber, a trailing edge flexible deformation section with the variable camber and a piezoelectric fiber composite material driver used for adjusting the change degree of the trailing edge flexible deformation section. The trailingedge flexible deformation section comprises a flexible wing rib, a stringer, a deformation skin, a segmented deformation skin and a segmented deformation skin fixing device. Voltage excitation is applied to the piezoelectric fiber composite material drivers, generated torque is transmitted to the flexible wing rib structure through the skin, and continuous and smooth change of the shape of the trailing edge of the wing is achieved. The wing structure mass can be greatly reduced, noise is reduced, the stealth characteristic is improved, the corresponding deformation control system is combined,accurate control over wing camber changes in the flight process can be achieved, the maneuvering and stall characteristics of an airplane are improved, and the task adaptability of the airplane is greatly enhanced.

The invention discloses a trapezoid layout tandem tilt wing aircraft and a tilting mechanism thereof. Tandem wing layout, trapezoidal power system arrangement, multiple control surfaces and electric power system differential combination control are adopted, so the aircraft integrates vertical takeoff and landing functions and high-speed hover performance advantages, and also has the long-enduranceand long-range characteristics of a fixed wing aircraft and the hovering and vertical takeoff and landing characteristics of a helicopter. The vertical takeoff and landing and the air fixed wing modecruising are completed through the tilting wing layout, so the requirements for a taking off and landing place are reduced, and the cruising efficiency is improved; the trapezoid dynamic system layout can improve the efficiency of propellers; the roots of wings and a fuselage are fused, and the tilting sections of the wings and the fuselage section fused wing roots are connected and rotate relative to each other, so the mounting and positioning precision of the wings is improved; and the multi-control surface layout of the wings makes the control surfaces on the wings generate the rudder effect by using rotor wake during the vertical takeoff and landing, and attitude control participating in the vertical take-off and landing state reduces the control surfaces of a vertical fin, so the structural efficiency is improved.

The invention discloses a travelling robot adapted to the seabed environment. The travelling robot adapted to the seabed environment comprises a robot body, a robot leg assembly, a visual system, a lighting system and a power supply and control system. The robot body is composed of a body upper shell and a body lower shell. The robot leg assembly is composed of six robot legs which are of the same structure. Each robot leg is composed of a front-and-rear swinging joint assembly, an upper-and-lower swinging joint assembly, a thigh joint assembly and a calf. The visual system is composed of a left side camera and a right side camera. The lighting system is composed of a left side lamp and a right side lamp. The power supply and control system comprises a power supply, a control module and a sealing cylinder, the power supply and the control module are packaged in the sealing cylinder in a sealed mode, and the sealing cylinder is connected and fixed to the inner surface of the body lower shell through a bolt. The travelling robot adapted to the seabed complex environment has high adaptability to the seabed environment, the system practicability is high, very good expandability is achieved, and continuous large range exploration of the seabed environment parameters can be effectively completed.

According to the tool spacecraft system oriented to on-orbit control, docking mechanisms are installed on the upper portion and the lower portion of a spacecraft base of the system, a plurality of rigid mechanical arms and a plurality of flexible mechanical arms are installed on the spacecraft base, and end effectors are installed at the tail ends of the flexible mechanical arms and the tail ends of the rigid mechanical arms. The technical problems that a space robot only has a rigid mechanical arm and does not have a flexible mechanical arm, the space robot cannot adapt to narrow space and complex structure operation, the number of the mechanical arms is small, only one or two mechanical arms are arranged, the executable task is single, the function is limited, and a tail end operation mechanism carried by a traditional space robot is single and cannot give consideration to multiple tasks are solved. The tool spacecraft system is provided with four rigid mechanical arms with 7 degrees of freedom and two flexible arms with 12 degrees of freedom, and the six mechanical arms are arranged, so that the diversity of operable tasks of the spacecraft system is greatly improved, the function of the spacecraft system is expanded, and the reliability of executing the tasks of the spacecraft system is improved.

The invention relates to an aerospace aircraft on-orbit operation relative position attitude joint control method; aiming at the limited thrust and saturation characteristics of an engine, the methodcan realize integrated control of a random target attitude and a random target position through multiple feedback compensation measures; the method is high in efficiency, high in task adaptability, simple in flow, and easy to realize, thus solving the problems that an existing on-orbit operation relative position and relative attitude control method is strong in repeatability, large in workload, and poor in the task adaptability. The joint control method is based on an adaptive engine distribution method that does not depend on an engine layout form, and a distribution algorithm of different engine layout results does not need to be redesigned, thus effectively simplifying the design flow; for an aircraft in multichannel coupling engine layout configuration, the method is strong in task adaptability.

The invention provides a task-driven low-orbit satellite broadcast distribution device, method and system and a medium. The task-driven low-orbit satellite broadcast distribution device comprises a route selection unit, a storage unit, a framing unit, an encryption unit, a coding scrambling unit, a rate control unit and a radio frequency processing unit. According to the invention, storage playback broadcast or real-time broadcast control can be performed on to-be-distributed data according to the working condition and the receiving capability of a ground terminal in a flying area, and the system has a multi-gear transmission rate adjustable capability, and has the advantages of high distribution efficiency, good task adaptability, compatibility with real-time broadcast, simple engineeringimplementation and the like; reference and basis are provided for future satellite data broadcast distribution design.

The invention provides a drug-target protein affinity prediction method and system, and belongs to the technical field of biological information processing based on artificial intelligence. The method comprises the following steps: respectively coding a drug chemical molecule and a target protein molecule in a drug-target protein pair to be detected to obtain a drug input representation and a target protein input representation ; and processing the drug input representation and the target protein input representation by using a drug-target protein affinity prediction model to obtain a drug-target protein affinity prediction value. A meta-learning algorithm is utilized to effectively mine the correlation between different subtasks; and the task unevenness between different subtasks is relieved by using the regularization item, the task adaptability of the drug-target protein affinity prediction model is improved, the drug-target protein affinity prediction model with generalization performance is obtained, the accuracy of unknown drug-target protein pair affinity prediction is improved, and the cold start problem in the aspect of drug-target protein affinity prediction is effectively solved.

The invention relates to an aerodynamic configuration of an aircraft. The aircraft comprises two parts, wherein the front part comprises a sweepforward wing edge-sharpening wing body syzygy and an outer wing section and the rear part comprises a triangular wing edge-sharpening wing body syzygy and an outer wing section. Left and right sweepforward wings arranged at the front part and left and right triangular wings arranged at the rear part are connected in series on the same horizontal plane; and wing roots of the left and right sweepforward wings and the left and right triangular wings are connected in parallel and then connected in series. Front edges and rear edges of the sweepforward wings and the triangular wings are respectively jointed together. Front edges of the sweepforward wings are jointed at an aircraft head part; rear edges of the sweepforward wings are combined with inner wing sections of the front edges of the triangular wings together; and the rear edges of the triangular wings are jointed at the aircraft tail. The sweepforward wings are connected with the triangular wings, so that the structure is firmer. Meanwhile, the invention has the advantages of a sweepforward wing airplane and a triangular wing airplane, complements the defects of the sweepforward wing airplane and the triangular wing airplane and has better performances.

The invention provides a double-frequency ultrahigh-resolution depth-sounding side-scan sonar system, which relates to the technical field of sonar, can realize depth-sounding side-scan double-frequency-band work, and not only meets a wide-coverage scanning task, but also meets an ultrahigh-resolution identification requirement. The system comprises a double-frequency sonar transducer array used for transmitting a sonar signal with a preset frequency and receiving an echo signal; a sonar electronic extension which generates broadband linear frequency modulation signals meeting the Ping rate requirement, transmits the broadband linear frequency modulation signals to the double-frequency sonar transducer array for signal conversion and emission, and processes echo signals received by the double-frequency sonar transducer array; a control module used for controlling the sonar electronic extension set to work; and a sensor used for monitoring carrier environment data and providing a clock signal for the sonar electronic extension set. The double-frequency sonar transducer array adopts a multi-subarray broadband transducer array, and data of different subarrays are selected for processing and calculation according to needs during depth measurement and side scanning signal processing. The technical scheme provided by the invention is suitable for the underwater measurement process.