70 results about "Reaction control system" patented technology

The invention discloses a re-entry attitude control method of a reusable launch vehicle (RLV), and aims at solving the technical problem of an existing method that the distribution efficiency of an RCS (Reaction Control System) instruction is low. According to the technical scheme, the re-entry attitude control method comprises the following steps: firstly, designing all combinations in all control directions of all thrusters in all control directions of an RCS; adopting an integer linear planning method to realize real-time instruction distribution in a determined required moment direction combination; solving the integer planning method by using a genetic algorithm. Control instruction distribution of the RCS is converted into a dimension-lowering integer linear planning method; compared with a background technology, the requirements of the RLV re-entry attitude control are combined; the amplitudes of the thrusters and the fuel combustion of the RCS are considered, and an offline design optimal table is not needed under the condition that the thrusters have the fault, so that the complexity of the thrusters is reduced; the real-time efficiency of the RCS instruction distribution is improved through the dimension-lowering treatment; the RCS fault reconstruction of minimum RCS energy consumption and instruction moment tracking errors is realized.

A reaction control system controls a reactive force to be applied to an operating device operated by a driver of a vehicle. The system includes a device for measuring a steering speed of steering of the operating device; a device for measuring a steering torque applied to the operating device; and a reactive force correcting device for correcting the reactive force in a manner such that the corrected reactive force increases at least when the measured steering speed is zero, and that the higher the measured steering torque, the higher the corrected reactive force is. The reactive force correcting device may correct the reactive force in a manner such that the higher a speed of the vehicle, the higher the corrected reactive force is. A non-effectivity range of the steering torque in which the corrected reactive force is not influenced by the steering torque may be defined.

Pulsed detonation engines (PDEs) are adapted for use in reaction control systems (RCS), such as thrusters for orbital correction and control (e.g., for earth-orbiting satellites), divert thrust generation and control for space-based interceptor devices, and for missile trajectory correction and motion control. According to one aspect of the invention, PDEs are adapted for motion control of so-called “kill vehicles,” which are small devices, typically launched from satellites, for strategic missile defense.

Methods and apparatuses are provided for managing a plurality of thrusters in a platform. The method and apparatuses comprise operating the plurality of thrusters in the platform with a thruster control system. The methods and apparatuses comprise estimating a vehicle response resulting from the operation of the plurality of thrusters to form an estimated vehicle response. The methods and apparatuses also comprise comparing the estimated vehicle response to a desired vehicle response to develop objective function errors. Also, the methods and apparatuses comprise developing a number of commands configured to correct the objective function errors.

A microchannel chip reaction control system of the present invention is characterized by being provided with a microchannel chip 1 having at least two microfluidic channels 1a and 1b for introducing reagent solutions A and B and a microfluidic reaction channel 1c formed by joining the two microfluidic channels 1a and 1b to each other, analysis means 2 for analyzing a product C obtained from the microfluidic reaction channel 1c, and control means 3 for controlling conditions for the reaction in the microchannel chip 1 on the basis of analysis results obtained from the analysis means 2.

The invention relates to a precisely controlled biomass gas and biomass carbon preparation system. The preparation system comprises three continuous working units of a charging unit, a pyrolytic reaction unit and a discharging unit, wherein the charging unit is provided with a helical charging device, and helical blades of the helical charging device are arranged densely and sparsely; the pyrolytic reaction unit is provided with a pyrolytic reaction body, a helical propulsion device and an air supply device are arranged in the pyrolytic reaction body, and the helical propulsion device is provided with band-shaped blades which are arranged densely and sparsely and are provided with rake teeth; the discharging unit is provided with a helical discharging device and an air material conveying system; and a pyrolytic reaction control system is arranged on the pyrolytic reaction unit and is used for finely controlling and integrally optimizing the material height, the material propulsion speed, the pyrolytic reaction temperature and the reaction intensity so as to maximally improve the pyrolytic efficiency. The preparation system has the advantages of good and stable quality of biomass gas and biomass carbon, wide application field, capability of treating a wide range of biomasses and organic wastes, and high automation level.

The present invention is a constant volume rocket motor that uses a non-detonating constant-volume, bipropellant combustion process in pulse-mode operation. Opening and closing of the combustion chamber exhaust outlet is controlled by an actuated reciprocating thrust valve (RTV). Fuel enters the combustion chamber at low pressure with the RTV closed. The valve opens after or during combustion when combustion chamber pressure is at or near maximum. The motor has applications in reaction control systems and attitude control systems in spacecraft.

A fuel depot in space is provided. The fuel depot has a collapsible housing with a guidance, navigation, and control (GNC) system, a power management system, and a reaction control system (RNC). Connected to the housing are a plurality of fuel tanks that are connected via collapsible rods. The fuel tanks have pipe systems that are in communication with a plurality of pumps to transfer fuel from the tanks through a refueling arm and into a spacecraft during refueling.

An unmanned aircraft comprises:

• • a drive system to thrust the unmanned aircraft during a flight;
  • a reverse thrust system to reverse thrust the unmanned aircraft during a landing;
  • a controller operationally coupled to the reverse thrust system; and
  • a detector to detect and notify to the controller that the unmanned aircraft is in an uncontrolled situation during the flight.

The controller is then adapted to activate the reverse thrust system in order to reverse thrust the unmanned aircraft in-flight upon notification from the detector that the unmanned aircraft is in an uncontrolled situation.

The invention relates to a device and a method used in high-gravity electrochemical reaction and belongs to the technical field of electrochemical reaction under special conditions. The device comprises: a centrifuge, a strong electricity transmission system, a weak electricity transmission system, a gas transmission system, an image collection system, an electrobath system and an electrochemical reaction control system. The rotation of a centrifuge rotator is used for creating a high-gravity field in a test glass and the electrochemical reaction is carried out in the high-gravity field; electrochemical signals, temperature control signals and image signals are transmitted through a conducting ring of the weak electricity system; the power required by the temperature rising of the electrobath is transmitted through a power ring of the strong electricity system; the online collection of the gases generated by the electrochemical reaction or the control of the atmosphere inside the electrobath are realized by the gas transmission system; the reaction process on the electrode surface and the interface state are monitored by the image collection system; the electrochemical reaction is carried out in the electrobath. The device and the method have the advantage of synchronous realization of multi functions and are suitable for the research and application of electrochemical reaction process under high-gravity environment.

The invention discloses a combined pneumatic control method for an aerodynamic rudder/reaction control system of a hypersonic flight vehicle, and belongs to the field of hypersonic flight vehicle design. As for the hypersonic flight vehicle which has a flat lifting body structure with a flat lower surface and a smaller side edge radius and has a sharp leading edge and a large sweepback body, a pair of expanding type body wing flaps is arranged on the windward side of the lower surface of the rear edge. With adoption of the combined pneumatic control method provided by the invention, reaction control system nozzles are arranged in front of the body wing flaps, pitching control of the flight vehicle is realized through deflection and jet of the body wing flaps, and rolling control of the flight vehicle is realized through differential motion and jet of the body wing flaps; the reaction control system nozzles are arranged on the side edge of the flight vehicle, and yaw control of the light vehicle is realized through jet. Through beneficialinterference of jet flow to the peripheral flow field of the aerodynamic rudder, the comprehensive control efficiency and the response speed of the aerodynamic rudder/reaction control system are increased, and the aerodynamic performance of the flight vehicle is improved. The control method has the characteristics of wide flight application range, high control efficiency and good economy.

The invention relates to the technical field of carrier rockets, in particular to a carrier rocket sublevel recovery landing system and method.The carrier rocket sublevel recovery landing system comprises a recovery landing device arranged on the ground or a ship, and the recovery landing device comprises a landing buffer mechanism; rocket engines which are arranged on the rocket sub-stages, and the rocket engines are used for controlling the rocket sub-stages to slow down; a thrust vector control device which is used for changing the thrust direction of the rocket engine; an inertial measurement system which is used for measuring the attitude and position of the rocket sublevel in real time; a GPS system which is used for measuring the position of the rocket sublevel in real time; a RCS reaction control system which is arranged on the rocket sub-stage, and before the rocket sub-stage enters the atmosphere, the RCS reaction control system enables the rocket sub-stage to turn over and target landing aiming before the reentry section; a pneumatic rudder which is arranged on the rocket sub-stage; and a rocket-borne computer which is arranged on the rocket sublevel.

The invention relates to an SCWO (supercritical water oxidation) reaction control system. The SCWO reaction control system comprises an oxidizing agent conveying pipeline, a fuel conveying pipeline, a material conveying pipeline, a reactor, a gaseous product discharge unit, a liquid product discharge unit and a control unit, wherein the control unit comprises sensors, field execution components, controllers and an upper computer, the field execution components are connected with the controllers through input and output modules, and the sensors, the controllers and the upper computer are in signal connection through a communication protocol; the sensors and the field execution components are arranged on the oxidizing agent conveying pipeline, the fuel conveying pipeline, the material conveying pipeline, the reactor, the gaseous product discharge unit and the liquid product discharge unit. The control unit is used for realizing the control processes such as starting, stopping, emergency stop, temperature adjustment, pressure adjustment and the like of the system, system operation data can be effectively acquired, stored and analyzed, reliable basis is provided for process adjustment and optimization, and necessary conditions are provided for stable, safe and reliable operation of the system.

A distributed control system for emergency response is composed of three layers: user interface (presentation layer), management center (session layer) and agan (execute layer.). The information transferred between the center and agent follows coding protocol. The user interface receives the performance and alarm data transferred from the management center and sends the control information to agent process through the management center. The management center receives the performance data transferred from each agent, and then the data interpreted into the information of user readable is transferred to the user interface. According rules the management center writes alarm data to log and triggers a response. The invention can manage computers effectively, monitor working order of each computer and deals with violation with accuracy and automatically.

There is provided an air flow deflector apparatus for a thrust reverser system of an engine of an air vehicle. The air flow deflector apparatus is movable between a stowed non-reversing position and a deployed thrust reversing position, to deflect an air flow out of the engine, and to provide an effective reverse thrust for the thrust reverser system. There is further provided an air flow deflector assembly for a structure. The air flow deflector assembly has the air flow deflector apparatus, an extender member, and a recessed housing disposed in the structure. The air flow deflector assembly has an air flow deflector actuator that moves the air flow deflector apparatus between a stowed position and a deployed position adjacent to a reverse efflux air flow exit portion of the structure. The air flow deflector assembly deflects a reverse efflux air flow away from being re-ingested into the structure.

The invention relates to the technical field of chemical pharmacy, in particular to a continuous-flow tubular reaction system and a reaction control system. The reaction system includes a feeding device, a mixing device, a pre-heating device and a reaction device, wherein the feeding device, the mixing device, the pre-heating device and the reaction device are communicated in sequence; reaction tubes in the reaction device are communicated in sequence through communicating devices, and the reaction control system includes an input device used for selecting a preset reaction model and a control unit which used for outputting a control signal according to the selected reaction model and controlling normal operation of the continuous-flow tubular reaction system according to the reaction condition. According to the continuous-flow tubular reaction system and the reaction control system, the mixing effect is good, the reaction condition is controlled precisely, the reaction efficiency and the yield are improved, the size and the occupied space are relatively small, the production cost is reduced, the spirally wound reaction tubes are adopted, the mixing effect is good and the service life of equipment is long.

The invention discloses a transient jet flow test method for a pulse wind tunnel. The transient jet flow test method comprises the following steps: firstly, determining a Laval nozzle Mach number of a jet flow test model and pulse wind tunnel mainstream duration according to pulse wind tunnel transient jet flow test requirements; then designing and processing a gas storage pipe; installing a jet flow test model, and debugging each system; measuring nozzle outlet airflow parameters; and finally, carrying out a pulse wind tunnel transient jet flow test. By using the transient jet flow test method, the stable jet flow formation time of the jet flow test model is synchronous with the wind tunnel mainstream, the duration time exceeds the effective test time of the wind tunnel mainstream, and the jet flow test model can be automatically closed after the set jet flow duration; the device can simulate a complex flow field structure formed by mutual interference between transverse jet flow formed when a reaction control system of an aircraft works and external streaming of the aircraft, and is particularly suitable for simulating an aerodynamic thermal environment on the surface of the aircraft with the transverse jet flow and evaluating the influence of jet flow interference on aerodynamic characteristics of the aircraft.

The invention discloses a cane juice stoving neutralization reaction control system which comprises a control main board (1) for controlling the neutralization reaction, wherein the control main board comprises a pH value analyzing module (101), an ultrasonic control module (102), a stirring control module (103), a heating control module (104) and a velocity control module (105). According to the cane juice stoving neutralization reaction control system disclosed by the invention, the mode of feedback regulation is sufficiently utilized to regulate the neutralization reaction process in real time, and the cane sugar velocity, the cane sugar solution pH value and the temperature of primary heating and secondary heating of a stoving neutralization reaction device are accurately and controlled, and the mixing degree of lime milk and SO2 is greatly improved.