54 results about "Sounding rocket" patented technology

The invention discloses a solid-liquid power sounding rocket land launching sequential control system which comprises a main control computer, a ground sequential control system and a rocket-mounted single chip computer control system, wherein the main control computer sends a control command to the ground, sequential control of a rocket-mounted engine igniter is achieved through the ground sequential control system which is further used for conducting the sequential control on a rocket-mounted engine liquid path valve and the rocket-mounted single chip computer control system, and meanwhile opening and closing condition information of the rocket-mounted engine igniter and the liquid path valve is obtained and sent to the main control computer. The sequential control of a rocket-mounted engine pressurized valve is achieved by the rocket-mounted single chip computer control system, and meanwhile the closing and opening condition information of the rocket-mounted engine pressurized valve is obtained and sent to the main control computer through the ground sequential control system. The solid-liquid power sounding rocket land launching sequential control system has the advantages of solving the key problems of matching the solid-liquid power sounding rocket ground sequential control with a rocket-mounted sequential control circuit and meeting millisecond level requirements of launching sequential errors.

The invention relates to a device for acquiring rocket-borne data of a solid-liquid power sounding rocket. The device is mainly used for acquiring, processing, monitoring and storing signals output by three uniaxial accelerometers, a pressure transmitter for measuring the pressure of an oxidizing agent storage tank, a pressure transmitter for measuring the pressure of a high-pressure gas cylinder capable of pressurizing the oxidizing agent storage tank, a pressurization working condition conversion electromagnetic valve, an auxiliary circuit blow-off self-locking electromagnetic valve and a main circuit blow-off self-locking electromagnetic valve. According to a rocket-borne data acquisition circuit, core functions of sequential control, data acquisition, signal conditioning, switching value conversion, data caching, data storage, data remote transmission and the like of the data acquisition device can be realized by a control chip; and other functions of voltage stabilization, protection, power supply, electricity conversion control, clock input and the like are required to be realized besides the core functions. By the device, thrust which is actually generated by a solid-liquid rocket engine and accelerations of the rocket in three axial directions can be totally monitored and compared at the working stage of the engine.

The invention discloses a control system of a solid-liquid dynamic sounding rocket. The control system is composed of a ground test launching control part and a rocket-borne control part. The control system is mainly used for realizing the following three tasks: converting ground power supply of a rocket-borne device to rocket-borne power supply, completing test preparation before launching the solid-liquid dynamic sounding rocket to realize the functions of launching control, security control, and the like, and carrying out variable thrust control on the solid-liquid dynamic sounding rocket and monitoring, collecting and recording the states. The invention provides a solid-liquid dynamic aircraft control system. By utilizing the solid-liquid dynamic aircraft control system, the functions of monitoring, ignition testing, emergency danger eliminating, and the like to the important rocket-borne device can be realized before the rocket is launched, the rocket-borne control part can realize thrust adjustment control according to control requirements after the rocket is started, and liquid propellant main road and side road channel valves are controlled according to the control requirements to clear residual propellant in a channel after the flight mission is finished. Meanwhile, real-time data acquisition and recording on parameters for reflecting working conditions of a solid-liquid rocket engine are carried out by the rocket-borne control part in the entire flight process.

The invention discloses a rocket-borne monitoring system of a solid-liquid dynamic sounding rocket. The rocket-borne monitoring system is composed of a rocket-borne thrust adjustment controller and a rocket-borne data monitor. The controller and the monitor are both composed of a plurality of monitoring and testing modules. The rocket-borne monitoring system is mainly used for realizing the following four tasks: converting power supply of the rocket-borne monitoring system from ground power supply to rocket-borne power supply, completing control to actions of relative valves according to thrust adjustment control, carrying out monitoring recording on working conditions of a rocket-borne device, and realizing reset control to the rocket-borne device. By utilizing the rocket-borne monitoring system of the solid-liquid dynamic sounding rocket, control to liquid propellant booster valves, main road and side road channel valves is realized in the flight process of the rocket according to control requirements, the function of thrust adjustment is completed, and safety of a conveying system is ensured. The real-time working conditions of a solid-liquid rocket engine can be effectively reflected by data monitoring results.

The invention provides an experimental device for ground expansion of a rocket-borne electronic extensible rod. The device is used for simulating control of expansion of the electronic extensible rod in the separation of a hood of a sounding rocket on the ground. The device comprises a base with a sliding way, an extension spring, a screw, an electromagnet, a circular ring, a cylindrical pin and electrical pure iron, wherein the base is fixed on a rotary platform; a screw hole seat and a pin hole seat are arranged at left and right ends of the base in opposite direction; the lower part of thescrew hole seat is fixed with one end of the extension spring; a threaded hole for mounting the screw is formed on the upper part of the screw hole seat; the electromagnet is embedded into the lower part of the pin hole seat; the upper part of the pin hole seat is a limiting part; a pair of small holes is formed on the limiting part correspondingly; the circular ring is placed between the pair ofsmall holes and fixed by inserting the cylindrical pin; the electrical pure iron is shaped like a Chinese character 'Tu'; a circular hole through which the cylindrical pin penetrates is processed on the upper half part of the electrical pure iron; the lower half part of the electrical pure iron is used for fixing the other end of the extension spring; and the bottom of the electrical pure iron isnested in the sliding way on the base.

The invention relates to a rocket-borne image acquisition and compression method and a system which are suitable for a sounding rocket. The system comprises a power supply management module, several rocket-borne simulation cameras, an image video decoding unit, an image compression unit, a central control unit, a data transmission unit and a watchdog unit, wherein the power supply management module provides power for the whole system; the image video decoding unit is used to carry out digitization on image data of the simulation cameras; the image compression unit is used to carry out wavelet transformation and compression on the image data; the central control unit is used to control the image compression unit and the image video decoding unit, switch among the plurality of cameras and pack and output the image data; the data transmission unit is used to complete buffer and transmission of the image data and convert parallel bus data into synchronous 422 bus data; the watchdog unit is used to monitor software of the whole system. The system is used for realizing image acquisition on the sounding rocket. The system possesses the characteristics that cost is low; power consumption is low; temperature adaptability is good and reliability is high.

The invention provides a Langmuir probe sensor used on a sounding rocket. The Langmuir probe sensor comprises an upper hemisphere (1), a lower hemisphere (2), a connecting rod (4), a telescopic rod and a signal wire, wherein the upper hemisphere (1), the lower hemisphere (2) and the connecting rod (4) are in cavity structures; the upper hemisphere (1) and the lower hemisphere (2) are connected through an insulating partition plate (3); one end of the connecting rod (4) penetrates in along a central shaft at one side of the spherical surface of the lower hemisphere (2); the connecting rod (4) and the lower hemisphere (2) are connected and fixed through an insulating pad (6) embedded in one end of the connecting rod (4), the other end of the connecting rod (4) is connected and fixed together with the telescopic rod; one end of the signal wire is connected with the upper hemisphere (1), the other end of the signal wire (1) penetrates through the insulating pad (6) and the inner cavity of the upper hemisphere (1), and is guided out from the inner cavity of the connecting rod (4); the upper hemisphere (1) is used as a collecting electrode, and the lower hemisphere (2) is used as a protective pole.

The invention relates to a parachute assembly applicable to rockets, which comprises a cylinder-shaped cabin body (1) the two ends of which are connected with other parts of a rocket; the side wall of the cabin body (1) is provided with a hatch where a hatchcover (2) and a hatchcover opening device are arranged; the hatchcover (2) is connected with a retarding parachute body through a hauling rope, the retarding parachute body is connected with a main parachute body through a retarding parachute connecting rope, and the main parachute body is connected with the cabin body (1) through a main parachute connecting belt. According to the appearance structure characteristic of a meteorocket (or a sounding rocket), in the parachute assembly, the hatch and the hatchcover thereof are arranged on the side wall of the cabin body and the parachute hatchcover is released in side direction of the cabin body, thus overcoming the defects in the prior art, without designing a rocket detaching mechanism and with simple structure and low cost; and the separated rocket body is avoided, thus causing no interference on the parachute, with good safety and reliability; and the interfaces among each part of the rocket are simple, thus improving the parachute assembly quality and reducing the using failure rate.

The invention relates to a sea data processing realization method based on a low-altitude sounding rocket. The method comprises the following steps: a data scope is limited, a landing phase point of the sounding rocket is extracted, the landing phase point of the sounding rocket is determined, according to phenomenon of linear change of air pressure at a vertical direction with height, a highest point of the rocket is a lowest point of the air pressure, an air pressure gradient detection method is employed to determine a start point of the decrease phase, and the landing phase data is extracted; and an observation data stabilization point of the landing phase is continuously determined; the data is subjected to Rendal error control, whether a certain essential factor sequence in the observation data is in a reasonable value range is determined, a moving average method is used for filtering the essential factor to obtain a novel essential factor sequence, by comparing a relation betweena mean square deviation K of the corresponding essential factors before and after filtering and m times of mean square deviation, exception handling is carried out on the observation data, and an interpolation is used for substituting an abnormal value. The method can increase the quality of the sea data.

The invention provides a high-precision control system of a sounding rocket emission device. The full-automatic erection and rotation function of the sounding rocket emission device can be achieved, the beneficial effects of being easy to operate, high in precision, high in response, high in reliability, good in safety performance and the like are achieved, according to the control system, closed-loop control is adopted in an erection device and a rotation device of the emission device, and the problems that due to hydraulic system pressure drop, the erection angle deviation, large cost, poorsafety, and difficult maintaining happen are solved. During use, initial pitching angle calibration is carried out through a tilt angle sensor, a control unit is used for giving the relative rotationangle to a pitching encoder, a closed-loop control emission device reaches the set target pitching angle, the directional precision of the pitching angle reaches 0.1 degree, the rotation device is driven by a servo motor, during use, firstly, a dual GPS system achieves the initial autonomous direction, a control unit is used for giving the relative rotating angle for a direction encoder, the servomotor drives the rotation device to achieve direction adjustment, the direction angle orientation accuracy reaches 0.2 degree, accordingly, and high-precision control over the pitching angle within the range of 0 to 90 degrees and the direction angle within the range being +/-180 degrees of the emission device can be achieved.

The invention relates to a container-less material processing system. The container-less material processing system comprises a temperature control module, a position control module, a physical property measurement module, a sample processing module and an integrated control module. The container-less material processing system has an excellent ground static suspension technology base and can process multiple samples at each batch, and heating temperature of samples can reach 3000 DEG C; through modularized and integrated design, on-track maintenance, sample replacement and function expansion can be realized; real-time experiment states can be accurately mastered; the system further has properties of novel structure, good versatility, stronger functions and wider adaptation surfaces and is a new-generation scientific material experiment system capable of satisfying scientific research demands of multiple types of materials; contain-less high undercooling material processing and heat physical property measurement can be carried out under the ground and space environments; relevant scientific material experiments can be carried out in various spacecrafts such as microgravity airplanes, sounding rockets, recoverable satellites and space stations.

The invention relates to a meteorological and sounding rocket decision-making and launching system of a semi-submersible unmanned detection vessel. The system comprises a launching decision-making unit, a measurement and control unit and a wireless receiver, wherein the measurement and control unit is used for monitoring rocket self-inspection and power-on of a sonde, controlling rocket firing, and controlling opening and closing of a rocket compartment; the wireless receiver is used for performing self-inspection on the sonde, receiving data sent back by the sonde, and transmitting the data to the measurement and control unit; and the launching decision-making unit is used for receiving a launching instruction, acquiring sailing posture information of the vessel from a main control unit, deciding whether to execute rocket launching program or not according to the inclination angle and rotational angular velocity of the vessel, and acquiring sounding data from the measurement and control unit. The invention further relates to a meteorological and sounding rocket decision-making and launching method of the semi-submersible unmanned detection vessel. According to the system and the method, the technical problem of sounding rocket launching on the unmanned vessel is completely solved, manpower and material resources are saved, and the launching decision-making unit can choose an opportunity to launch the rocket under the sea condition of relatively large wind waves.

The invention discloses a deceleration control method of a recoverable sounding rocket, The method comprises: (1) designing a deployment angle of a recoverable sounding rocket reducer varying with time below a first height, so that the speed of the sounding rocket when it descends to the second altitude range falls within the range of the set speed, the overload on the arrow body in the descendingprocess does not exceed the designated overload, and the structural stress of the reducer is always smaller than the allowable stress of the material in the unfolding process; Step 2) When the recoverable sounding rocket returns and when it reaches the first altitude, the recoverable sounding rocket reducer is deployed according to the deployment angle designed in Step 1). The deceleration control method of the invention ensures that the overload on the arrow body in the descending process does not exceed 10g all the time, and the load is not damaged due to excessive overload; the structuralstress of the reducer is always less than the allowable stress of the material during the unfolding process, and the reducer structure will not be damaged.

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 provides a multiple sounding rocket test and launch control rocket selection system. The system can improve the maneuverability of the implementation of sounding missions, realize automatic rocket selection of rockets and rapid wireless power-on of a sonde, and fill the blank that a conventional carrier rocket test and launch control system only has one rocket test and launch channeland switch, test and launch technology of multiple carrier rockets cannot be carried out at a far end. Firstly, an individual soldier can completely complete rocket selection and the power-on of thesonde on launch control software of a test and launch control far end controller, which greatly improves the maneuverability of the implementation of the sounding emissions and finally realizes automatic switching and launching of the multiple sounding rockets. Secondly, The test and launch control system realizes the automatic rocket selection and the wireless power-on of the sonde, avoids manualdocking of rocket launching interfaces and manual power-on of the sonde when the rockets are replaced in the past, shortens the time for re-launching of the rockets, and meets the requirement of launching a sounding rocket again in short time.

The invention relates to a method for deflecting space debris comprising steps of:

• • launching (E2) a thruster (2) by means of a sounding rocket (1) at a target altitude close to that of the one or more debris to be deflected.
  • generating (E3) by the thruster a gas cloud (G) above the sounding rocket.

The invention provides a gravity wave parameter calculation method and device and a terminal, and relates to the technical field of gravity wave. The method comprises the following steps of: obtainingan original temperature profile on the basis of detection data obtained by detecting atmospheric temperature by a sounding rocket; fitting the detection data by adoption of a preset processing methodso as to obtain a background temperature profile, wherein the preset processing method comprises a moving average polynomial fitting method with a filter coefficient or a Kalman filter algorithm; solving a difference value between the original temperature profile and the background temperature profile so as to obtain a temperature disturbance profile; and calculating a gravity wave parameter on the basis of the temperature disturbance profile, wherein the gravity wave parameter comprises gravity wave spectrum power density. According to the method, the correctness of the gravity wave parameter can be effectively improved.

The invention relates to a thrown type anti-stabilizing wing mechanism for a sounding rocket and belongs to the technical field of sounding rockets. The anti-stabilizing wing mechanism comprises a pinpushing device, a nut, an airfoil and a spring. The airfoil is fixedly installed on the outer wall of a sounding rocket body through the pin pushing device and the nut. The spring is put between theairfoil and the rocket body in a compressed state. Under control of a time schedule controller of the sounding rocket, the pin pushing device pushes out a hinge pin and the nut, and the airfoil is separated from a rocket body under the thrust action of the spring. Through the anti-stabilizing wing mechanism, the static stability level of the sounding rocket at the flight low-speed stage can be lowered effectively, and thus the influence of environmental wind on the rocket initial stage is reduced greatly. The anti-stabilizing wing mechanism is thrown away after the flight to preset time, thusthe sounding rocket recovers to the original aerodynamic configuration state, stability of the flight process of the sounding rocket is ensured, and precise control over a sounding rocket trajectory is achieved.

In order to overcome the defects of the existing target function determining method in the aspects of optimization efficiency and optimization result in the sounding rocket aerodynamic configuration design optimization process, the invention provides a determining method of a sounding rocket aerodynamic configuration optimization objective function. By using the minimum momentum loss of aerodynamic resistance along the trajectory as the starting point, the invention provides the determining method of the sounding rocket aerodynamic configuration optimization objective function. The determining method comprises the following steps of: (1) giving initial trajectory data at the rocket ascending stage; (2) performing initial trajectory data preprocessing, and determining trajectory feature points; (3) calculating the weighting coefficient of each feature point; and (4) using the minimum weighting resistance coefficient of the trajectory feature points as the sounding rocket aerodynamic configuration optimization objective function. The determining method has the advantages that the sounding rocket aerodynamic configuration optimization efficiency is obviously improved; the optimization result performance is improved; and the determining method is applicable to the appearance design of various sounding rockets in each design stage, and can be popularized and applied to the aerodynamic configuration optimization objective function determination of other aircraft.

The invention discloses a sounding rocket system. The sounding rocket system comprises a sounding rocket and a launching device; the launching device comprises a fixed platform, a movable platform located above the fixed platform and a ball pin assembly supported between the fixed platform and the movable platform; the ball pin assembly comprises a ball clamped by the movable platform and matchedwith the spherical surface of the movable platform, a pin shaft connected to the ball and movably connected with the fixed platform, and an adjusting thread sleeve in threaded connection with the pinshaft and used for driving the pin shaft to do lifting motion in the axial direction of the pin shaft so as to adjust the relative inclination angle between the movable platform and the fixed platform; and a plurality of empennages capable of being supported on the movable platform are arranged on the outer peripheral wall of the sounding rocket tail section in the circumferential direction, and the lower end faces of the empennages are flush with the lower bottom face of the sounding rocket tail end. According to the sounding rocket system, the landing leg type simple launching device is adopted, so that the launching requirement of the simple sounding rocket can be met; and simple and rapid rocket launching tasks can be carried out in a site with simple facilities, so that the dependenceof the sounding rocket on a special launching site is reduced.

The invention discloses a model rocket suite for spaceflight science popularization education, and belongs to the technical field of science popularization education of sounding rockets. The model rocket suite comprises a rocket shell, an empennage and a parachute bag, wherein the rocket shell is formed by coaxially connecting a rocket nose cone, a rocket parachute cabin section rocket body, a connecting piece and a rocket power section rocket body in sequence; a window is formed in the peripheral face of a rocket parachute cabin section rocket body, and a rocket parachute cabin section cover plate is installed at the window in a sealed mode through a shearing bolt, an aluminum alloy bolt and a parachute cabin section sealing piece; the parachute bag is arranged in a rocket body of a rocket cabin section; a flight control panel is installed in a rocket body of a rocket power section through a control panel fixing piece; and a rocket engine is installed in the tail end of the rocket power section rocket body through an engine force bearing piece and an engine positioning plate. The rocket is in modular design and is divided into the recovery section rocket body comprising the parachute cabin section and the rocket body comprising the engine power section, the two parts can be independently manufactured and used in cooperation, and the rocket is good in universality and high in repeated utilization rate.

The invention discloses a small solid-liquid sounding rocket for teaching science popularization, and belongs to the field of solid-liquid hybrid engines. The small solid-liquid sounding rocket comprises a rocket shell, an empennage, a parachute recovery device, a gas cylinder, a valve and an engine thrust chamber. The rocket shell is formed by inserting a nose cone and a cylindrical skin, the parachute recovery device, the gas cylinder, the valve and the engine thrust chamber are sequentially installed in the rocket shell from the head to the tail, and the engine thrust chamber is fixed to the tail end of the skin through a thrust chamber fixing ring; the parachute recovery device is adopted for recovery; and by utilizing the characteristics that nitrous oxide takes a liquid form as a main body in a high-pressure gas cylinder and the saturated vapor pressure of nitrous oxide is high, an oxidant can be conveyed in a self-pressurization manner, so that the structure of an oxidant supplysystem is simplified, and the negative quality of the system is reduced. The rocket is suitable for science popularization and teaching demonstration, the structure of the solid-liquid hybrid engineis clearly displayed, and the principle of the solid-liquid hybrid engine can be clearly known through the structure.

The invention discloses an active cruise return type liquid sounding rocket. The active cruise return type liquid sounding rocket comprises a fairing, an instrument cabin, a kerosene storage box, an inter-box rod system, a liquid oxygen storage box, a rear transition section and a tail section which are sequentially arranged. The tail section is provided with a liquid oxygen kerosene engine. The active cruise return type liquid sounding rocket further comprises a plurality of grid fins and a plurality of return support legs. The grid fins are arranged on the instrument cabin. One part of eachreturn leg is arranged on the rear transition section, and the other part of each return leg is arranged on the tail section. The active cruise return type liquid sounding rocket has the technical effects of being capable of being repeatedly used, capable of carrying multiple effective loads, controllable and low in cost.