115 results about "Launch control" patented technology

The invention discloses a fire fighting truck applicable to high-rise and super high-rise building fire suppression, comprising a truck chassis (1), a command control equipment (2), an launch control equipment (3), an equipment compartment (4), an launching apparatus (5), an ejection device (6), a fire extinguishing bomb (7), a turret control apparatus (8) and a photoelectric detection equipment (9), wherein, the command control equipment (2) and the launch control equipment (3) are arranged in the co-pilot position of the cab of the truck chassis (1); the equipment compartment (4) is arranged behind the cab and is fixed on the truck chassis (1) with bolts; the launching apparatus (5) is arranged on the truck chassis (1) and is fixed with screws; the ejection device (6) is arranged and fixed on the launching apparatus (5); the fire extinguishing bomb (7) is arranged within the ejection device (6); the turret control apparatus (8) is distributed on the truck chassis and the launching apparatus for accomplishing the actions of leveling the truck body and controlling the launching apparatus.

The invention provides a launching method of a guided missile safe launching system. The safe launching system comprises a launching control system and a launching box/barrel. The launching control system comprises an ignition power source and a launching control unit. The launching control unit comprises a combat launching command relay, an engine ignition relay and a resistor. The launching box/barrel comprises a napalm bomb mechanism microswitch. After an initiating explosive device is connected with the resistor in parallel, one end of the circuit is sequentially connected with the napalm bomb mechanism microswitch, a first set of contact switches of the engine ignition relay and a first set of contact switches of the combat launching command relay in series; the other end of the circuit is grounded and then is sequentially connected with a second set of contact switches of the engine ignition relay and a second set of contact switches of the combat launching command relay in series. According to the safe launching system, the safety performance in missile launching can be improved.

The embodiment of the invention provides a carrier rocket test system, and relates to the technical field of rocket test launching. The system comprises an execution module used for receiving a parsed test launch control instruction sent by a parsing module and executing the parsed test launch control instruction; the execution module comprises at least one execution device; the execution module comprises a rear-end measurement and control device, and the rear-end measurement and control device is used for receiving the analyzed test launch control instruction, determining the instruction type of the analyzed test launch control instruction, determining a target execution device for executing the analyzed test launch control instruction from at least one execution device according to the instruction type, and sending the test launch control instruction to a target execution device; and a target execution device which is used for executing the analyzed test launch control instruction and returning an execution result to the rear-end measurement and control device. According to the embodiment of the invention, automatic testing in the test launch control process of the carrier rocket is realized, and a large amount of manual operation and manual interpretation are avoided.

The invention discloses a launcher for a meteorological sounding rocket. The launcher for the meteorological sounding rocket comprises a connecting rod, a shaft pin A, a shaft pin B, a first gasket, afirst nut, a second nut, an orientator, a supporting seat and a traction chassis. The launcher for the meteorological sounding rocket is stable in overall structure and suitable for operation under severe weather conditions; a launching angle adjusting mechanism adopts a connecting rod mechanism for driving a screw rod to transmit by a motor; the orientator adopts four guide rails to be combinedwith a middle ring A and a middle ring B to form a launching rail, the launching caliber is 122 mm, the maximum angle of the high-low launching angle is not less than 80 degrees, the height of the launcher in the transportation state is not larger than 3 m, and the stability is high; a supporting part adopts the motor to drive a trapezoidal lead screw shaft to rotate to drive the connecting rod tomove front and back so as to achieve the purpose of adjusting the launching angle, and a manual mode can be quickly switched; and a rocket operation automatic parameter recording instrument or a wireless launching controller can be used for control, and a high-power lithium battery is carried, so that the field power supply problem is solved.

The invention discloses a test launch control system and method. The system comprises a test launch control rear end, a telemetering device and a launch device; the test launch control rear end comprises a main controller, a data server and a switch, the main controller and the data server are both connected with the switch, and the main controller is used for obtaining data of the data server through the switch; the telemetering device is connected with the switch and is used for performing wireless communication with a target object and storing the data of the target object in the data server through the switch; and the launch device is used for launching the target object. A rocket test launch control system in the prior art seriously depends on a launch site, copper core cables need to be arranged due to the fact that the distance between a front end and a rear end is long, and the manpower and material resource cost is high. With the test launch control system and method of the invention adopted, the above technical problem is solved.

The embodiment of the invention provides a ground test launch control system. The ground test launch control system comprises: a test launch control computer in which a computer program for controlling rocket test and launch is pre-stored; and a universal interface adapter which is in data communication with the test launch control computer through an Ethernet communication bus. The universal interface adapter comprises a back plate and rocket-ground communication interface modules arranged on the back plate, each rocket-ground communication interface module is in data communication with the back plate through a back plate bus, and each rocket-ground communication interface module is further used for being in data communication with electrical equipment on a rocket. The universal interfaceadapter is used for converting an instruction sent by the test launch control computer into a control signal of the on-rocket electrical equipment and sending the control signal to the on-rocket electrical equipment through the rocket-ground communication interface modules, and is used for receiving a working state signal fed back on the rocket through the rocket-ground communication interface module and sending the working state signal to the test launch control computer. The ground test launch control system provided by the embodiment of the invention realizes miniaturization and multifunction of ground test equipment.

The invention discloses an aircraft and ground cooperative test launch control system and control method, and relates to the technical field of aircraft test launch control. The system comprises a remote launching controller which is used for generating a third control instruction for controlling the launching of an aircraft, a ruggedized computer which is used for sending a first control instruction and a second control instruction, and forwarding the third control instruction generated by the remote launching controller to a test-launch-control all-in-one machine, a ground power supply whichis used for supplying power to the test-launch-control all-in-one machine, and the test-launch-control all-in-one machine is used for sending a test instruction to other equipment on the aircraft andsending obtained test data to the ruggedized computer; and when the ruggedized computer judges that the test data are normal, the test-launch-control all-in-one machine is further used for carrying out launch control on the aircraft. According to the invention, an integrated aircraft and ground cooperative test launch control architecture which takes tests on the aircraft as a main part and takesground tests as an auxiliary part is constructed, so that overall miniaturization, light weight and portability are realized, and the operation complexity and the use and maintenance cost of the system are reduced.

The invention discloses a carrier rocket digital power supply and distribution control system and a test method thereof. The system comprises a plurality of switches. The plurality of switches receivedigital instructions sent by the ground test launch controller through the Ethernet so as to execute closing or opening actions; the carrier rocket digital power supply and distribution control system sends collected test data to the ground test launch control system through the Ethernet for analysis. Digital instructions and test data are transmitted through the Ethernet, and the problem that acable used for ground test launch control is not used any more after a rocket takes off and becomes redundant load on the rocket is solved.

The invention relates to a launch control unmanned aerial vehicle and belongs to the field of aircrafts. The launch control unmanned aerial vehicle comprises an unmanned aerial vehicle body, an undercarriage, a high-pressure gas cabin and a controller. The undercarriage is arranged below the unmanned aerial vehicle body. The controller is arranged on the unmanned aerial vehicle body. The high-pressure gas cabin is arranged on the unmanned aerial vehicle body and connected with the controller. An internal through hole of the undercarriage is connected with the high-pressure gas cabin. Accordingto the launch control unmanned aerial vehicle, the principle is simple, the structure is simple, launch control is achieved, the head-start effect is achieved, a power supply is saved, and the higherendurance ability is achieved.

The invention discloses an integrated measurement, launch and control method and device for a liquid carrier rocket. The device comprises a first measurement and control combination and a second measurement and control combination which are connected with each other through a cable. The first measurement and control combination is in network connection with the rear-end control computer, is in cable connection with the liquid carrier rocket, and is used for receiving control of the rear-end control computer and performing related detection and control on an electrical system on the rocket in the measurement and launching process of the liquid carrier rocket; the second measurement and control combination is in network connection with the rear-end control computer, is in cable connection with a ground controlled object, and is used for receiving the control of the rear-end control computer and performing related detection and control on the ground controlled object in the measurement and launch process of the liquid carrier rocket; therefore, the ground controlled object and the rocket electrical system are matched with each other in the testing and launching process of the liquid carrier rocket.

The application discloses an ignition safety system of a multistage rocket engine and a detection method of the ignition safety system. The ignition safety mechanism of a multistage rocket engine comprises a ground testing and launching control system, an N-stage ignition safety mechanism and an N-stage intelligent detection combination, wherein the N-stage intelligent detection combination is used for detecting and recording the operating states of corresponding all stages of ignition safety mechanisms, and transmitting the operating states to the ground testing and launching control system;and the ground testing and launching control system is used for detecting the insurance states and the operating states of the ignition safety mechanisms and receiving the recorded operating state ofthe ignition safety mechanisms, detected by the N-stage intelligent detection combination, and according to the insurance states and/or the operating states of the ignition safety mechanisms, detecting the safety states of the ignition safety mechanisms. Through the adoption of the ignition safety system of the multistage rocket engine and the detection method of the ignition safety system disclosed by the invention, all the stages of the ignition safety mechanisms are connected in series, so that the design complexity of a cable network is simplified, and the weight of the cable network is reduced.

The invention relates to the technical field of space flight and aviation, and discloses a carrier rocket control system and method. The system comprises a ground test launch control system, a carrier rocket body, a sensor, a central computer, an output controller and an execution mechanism, and the output controller is connected with the ground test launch control system, the central computer and the execution mechanism. The carrier rocket body is connected with the sensor and the execution mechanism, the sensor is connected with the central computer, and the control process of the carrier rocket body comprises a ground test stage, a pre-launching preparation stage and a flight stage. The technical scheme of the embodiment of the invention has the advantages of strong real-time performance, high reliability, multitask processing, easy expansion and the like.

The invention discloses an artificial weather modification catalytic operation device as well as a control system and control method thereof, and belongs to the technical field of artificial weather modification safe operation. The operation device comprises a parachute compartment, an instrument compartment, a control compartment, a battery compartment, a rotor compartment, a catalyst scatteringcompartment and an engine compartment which are arranged in sequence in a rocket body as well as a tail wing arranged at the tail of the rocket body, wherein a control circuit, a navigation circuit and a safe lunch circuit are arranged in the control compartment, and the control circuit controls rocket ignition, device flight and catalyst scattering. The novel catalyst scattering operation deviceis improved and designed by organic combination of a rotor unmanned aerial vehicle and a rocket, and safe lunch of the operation device is carried out through an improved lunch controller; and compared with the prior art, the operation device improves the accuracy, effectiveness and safety of artificial weather modification catalytic operation, realizes reuse and greatly reduces the cost of artificial weather modification operation.

An unmanned aerial vehicle launching frame is characterized in that the unmanned aerial vehicle launching frame comprises a base frame, a front supporting assembly and a rear supporting assembly; the front supporting assembly is arranged at the front end of the base frame to support the front portion of an unmanned aerial vehicle, and the rear supporting assembly is arranged at the rear end of the base frame and can support the tail portion of the unmanned aerial vehicle; the rear supporting assembly comprises a rear supporting column, a U-shaped support and a self-locking spring, the rear supporting column is fixed to the base frame, and the two ends of the U-shaped support are hinged to the rear supporting column; the self-locking spring is connected with the base frame and the U-shaped support, the self-locking spring acts the elastic effect on the U-shaped support which is further provided with a placement frame matched with the an unmanned aerial vehicle tail cross beam, and the top end of the placement frame is provided with a U-shaped groove; and the unmanned aerial vehicle tail cross beam can be placed in the U-shaped groove. The unmanned aerial vehicle launching frame is of a pure mechanical structure, a control circuit does not need to be controlled, the structure is simple, the weight is low, carrying is convenient, the use range is wide, the requirements for unmanned aerial vehicle launching under different bad conditions can be met, and a launching controller is not needed.

The invention discloses a wireless temperature measurement emission controller for the low-frequency acquisition of the surface temperature of a piston of an internal combustion engine and belongs to the technical field of engines, electronic circuits and communication. The wireless temperature measurement emission controller comprises a temperature signal acquisition module, the output end of the temperature signal acquisition module is connected with an AD conversion module, and the output end of the AD conversion module is connected with a wireless emission module. According to the controller of the invention, the temperature signal collector and the AD module are designed, so that the whole structure of the controller is small and light, the installation of the controller in a narrow and complex environment in an engine cylinder is facilitated, the temperature measurement requirements of reliability and thermal load tests in an engine are met, power supply to the controller is realized through a power supply module, the anti-static capability of the controller is improved, abnormality caused by transient interference events such as static electricity is prevented, the stability of the working state is improved, the controller effectively adapts to the complex motion environment of the piston, and improves the reliability of real-time measurement.

A test launch and control system disclosed by the application is characterized in that the first input end and the second input end of a main control circuit are connected with the output ends of a test control terminal and a launch control terminal respectively, and the first output end is connected with the input end of a circuit system on a launch object; the main control circuit is used to generate a test/launch control signal according to a test/launch instruction sent by the test/launch control terminal and send to the circuit system, thereby carrying out the ground/launch test on the launch object, wherein the main control circuit comprises a main control chip circuit and a time delay output circuit, the first input end and the second input end of the main control chip circuit are used as the first input end and the second input end of the main control circuit respectively, the output end of the main control chip circuit is connected with the input end of the time delay output circuit, and the first output end of the time delay output circuit is used as the first output end of the main control circuit. According to the application, by utilizing the time delay output circuit, the situation that an unstable signal outputted by a main control chip during the electrification and reset period causes the misoperation of the launch object, is avoided, and the safety and the reliability can be improved effectively.

The invention discloses a simulation test system and method for a carrier rocket, the system comprises a simulation test launch control system, a rocket motion simulation system and a central computer, and the central computer is respectively connected with the simulation test launch control system and the rocket motion simulation system; the rocket motion simulation system is used for performing six-degree-of-freedom simulation on a control system of the carrier rocket to generate initial rocket motion and attitude information; the simulation test launch control system is used for sending to-be-bound parameters to the central computer so as to bind flight initialization parameters of the carrier rocket; the central computer is used for performing navigation guidance control calculation based on the bound parameters and sending a control instruction to the rocket motion simulation system; and the rocket motion simulation system is also used for performing six-degree-of-freedom simulation on the control system of the carrier rocket based on the control instruction to obtain new rocket motion and attitude information. The system can complete the automatic binding of the initialization parameters of the flight control software, and greatly simplifies the test operation process.