51 results about "Rocket (weapon)" patented technology

The multi-channel data acquisition system provided by the present invention includes an acquisition computer, an acquisition display and an acquisition end printer, the acquisition computer is equipped with a plurality of A / D acquisition cards and a buffer, and each A / D acquisition card input terminal is provided with a voltage Isolation conditioner, the acquisition computer is connected to the control computer and the echo computer through the back end of the Ethernet, the control computer is installed with a dual-screen display card, and connected to the master and slave monitors and the control terminal printer respectively, and the echo computer is connected to the echo display and the echo printer. The invention also provides a method for multi-channel data acquisition. The invention has the advantages of being able to measure multiple channels, suitable for multi-signal recording occasions, convenient display and printing of data and waveforms, high degree of automation and accuracy, and conducive to intelligent acquisition, especially suitable for rocket launching and weapon testing , petrochemical and other dangerous and heavily polluted on-site signal detection and recording occasions.

In an aiming or sighting device and an aiming method for determining the impact point of a ballistic flying body such as a rocket or a tube weapon projectile, specific characteristic values of the ballistic flying body are stored in a memory and an evaluating stage produces control signals in response to the specific characteristic values and in response to actual supplied system parameters. The control signals are transmitted to a display and to an adjustment drive. A model of the trajectory of the ballistic flying body is produced on the basis of all respective possible actual system parameters in an evaluating stage, whereby the trajectory is subdivided into at least two phases, each with a respective submodel. The submodel of the first phase is thereby a model with three or six degrees of freedom and the submodel of the second phase is a model with three degrees of freedom. An input unit permits adjusting the mode of operation and the correction of the impact location.

The invention discloses a ground-air defense product adversarial simulation training system. The system comprises a guiding and adjusting system, a training monitoring system, a training control system, a blue army simulation system, a weapon control system and a simulation cylinder bomb. The system can simulate a vivid threatening environment, cover various typical targets and simulate common sudden combat patterns such as maneuvering, formation and anti-radiation attack; and the electromagnetic scattering characteristic is consistent with that of the typical combat targets; a vivid electromagnetic environment can be simulated, and an own mutual interference environment and common interference patterns such as oppression and spoofing of enemies can be constructed; training management functions such as guidance, planning, evaluation and the like can be assisted for a superiors commander; main firepower platform display control information, position deployment and main platform activityscenes can be recorded in real time; actual installation can be connected, a simulated rocket projectile is launched, and the actual operation feeling of an operator is improved.

The invention discloses a pole piece protecting method (film forming agent soaking method) for prolonging a dry storage life of a zinc-silver battery. A formed and dried positive pole piece and a formed and dried negative pole piece are respectively soaked in film forming agents with different concentrations for a certain time and then thin protective films are generated on the surfaces of the pole pieces; through the adoption of the protective films, substance and energy exchanging between the pole pieces and outside environment is isolated, the positive pole decomposition is greatly reduced and the oxidation of the negative pole is further suppressed, so that the capacity loss of the battery is reduced. Through the adoption of the pole piece protecting method disclosed by the invention, the dry storage life of the zinc-silver battery can be prolonged from the current 5-8 years to 12 years or longer; and moreover, the protected pole piece has no influence on pole piece discharging. The pole piece protecting method for prolonging the dry storage life of the zinc-silver battery, disclosed by the invention, has the advantage that the dry storage life of the zinc-silver battery is prolonged and is used for weaponries with higher requirements on long storage life, such as missiles and rockets.

The invention discloses a preparation method of a bionic room-temperature self-repairing polyurethane material. The preparation method comprises the following steps: firstly, preparing an isocyanate-terminated hydroxyl-terminated polybutadiene prepolymer, then respectively introducing a disulfide bond and a benzenediol bionic group onto the molecular chain of the prepolymer, and finally, curing a reaction product to obtain the self-repairing polyurethane material. The method has the advantages of simple process conditions, easily controlled flow, high safety, low cost, high yield and convenience in batch production. A one-pot multi-step mode is adopted in the preparation process of the self-repairing polyurethane, and the tedious preparation process of a traditional self-repairing material is simplified. The reasonable combination of the bionic structure and the dynamic disulfide bond ensures that the product has room-temperature self-repairing capability, is particularly suitable for the field of composite solid propellants, and can be widely applied to the national defense and military fields such as carrier rockets and missile weapon systems.

The invention discloses a modular rocket stable launching platform for a small naval vessel and a control method of the modular rocket stable launching platform. A plurality of sets of transmission mechanisms are adopted, multi-mode control can be carried out according to different sea conditions, excellent performances such as a fault-tolerant control mechanism, high flexibility, strong resistance to stormy wave and the like are achieved, and a very high application value is achieved in the field of small naval vessel launching; and in order to cope with the high overload and vibration environment at the moment of launching, an instantaneous launching supporting device and a specific driving control method thereof are adopted, and an electromagnetic field drives the instantaneous launching supporting device to play a role only in the micro-time domain at the moment of rocket launching so as to counteract the high overload of weapon launching, and a special drive circuit enables a small naval vessel launching system to have high dynamic property, high launching support rigidity and high impact resistance under the condition of low power.

The invention belongs to the technical field of antennas, and discloses a planar slot array antenna, a radar, a wireless communication system and a millimeter wave antenna. The planar slot antenna array is provided with a planar slot array, a feed plate, a power division network and an output plate, wherein the base material of the planar slot antenna array is fiber-reinforced special engineeringplastic; a chemical plating layer, a metallized signal layer and a protective layer are sequentially arranged on the base material; and the planar slot antenna array 1 comprises 44 isolation square cavities, 44 radiation slots and 6 excitation waveguide cavities, and the power division network 3 is formed by cascading a plurality of waveguide power dividers with equal arm length and equal power division. Compared with a traditional metal planar waveguide slot antenna, the planar slot array antenna has the advantages of light weight, weight reduction by 30% or more, simple processing, low production cost, wide frequency band and efficiency, high gain, far wireless signal propagation distance and high temperature resistance; and the structural mass of aerospace rockets and missile weapons can be reduced, and the effective load and the fighting capacity of the aerospace rockets and missile weapons are improved.

The invention relates to a small-sized rocket projectile capable of being used as a cruise missile radar reflection character equivalent target. The small-sized rocket projectile comprises a rocket engine and a target warhead, wherein the rocket engine comprises a combustion chamber, a spray pipe and a plurality of wings, the front end of the combustion chamber is connected with the target warhead, the rear end of the combustion chamber is connected with the spray pipe, the wings are distributed on the outer circumference of the spray pipe, the target warhead is of a hollow structure, and the cross section of the target warhead is of a polygonal shape; and a metal foil wraps the combustion chamber of the rocket engine. In flight, the small-sized rocket projectile is stable in posture, the trajectory repetition is good, and the small-sized rocket projectile can be used for a super-short-range radar to test a maximal detection distance, a capture target speed and a tracking recognition capacity of targets such as the cruise missile; the small-sized rocket projectile can also be used as a reactive beacon of the radar for the detection tracking continuity of a dynamic target; the small-sized rocket projectile can also be used as a substitution target bullet in the combined test of a super-short-range weapon system; and the test cost can be greatly reduced.

A projectile and method for stopping aerial vehicles. The projectile comprises a shell—and a bunch of filaments. The bunch is wound in a coil and placed inside the shell. The projectile according to the solution may be brought to a target by different methods and utilising different means. For example, the projectile may be fired with compressed air or a propulsion charge, by using a compressed air weapon or rocket launcher. In addition, the projectile may be taken to the target by using a rocket or aerial vehicle.

The invention provides a multifunctional launching training device based on modular design. According to the multifunctional launching training device based on the modular design, the problem that different ammunition can be launched through the same launching barrel is solved, meanwhile, rapidly filling can be carried out after launching so that next launching can be carried out, the impact force, the explosive force and the acousto-optic effect in the launching process can be truly simulated, the real launching condition of weapons in the real confrontation process can be simulated, and great significance can be achieved for improving the short-distance actual combat ability of soldiers. According to the technical scheme for solving the problem, the multifunctional launching training device is characterized in that the multifunctional launching training device comprises a launching barrel, a guiding module used for performing image transmission on a launching target is connected to the lower portion of the launching barrel in a sliding mode, and the guiding module is connected with the launching barrel in a sliding mode, a rocket projectile bearing block or a signal projectile launching module are connected above launching barrel in sliding manner, and the multifunctional launching training device has the advantages that the multifunctional launching training device is ingenious in structure, simple and practical.

The invention provides an electronic remote control antagonism type combined toy. The electronic remote control antagonism type combined toy is composed of an electronic control moving object target machine and an antagonism emitter; a part structure of an existing single electronic remote control toy is innovatively designed; an antagonistic electronic signal control instruction emission and receiving device and the like are additionally arranged on the basis of a remote control signal emission and receiving device of a common electronic remote control toy; respective characteristics of remote control movement toys including air vehicles, ships and vehicles, and weapon-imitated toys including guns, rockets, guided missiles and the like are combined, and new toy combination and control game modes are created; a single person can play the single toy, and users can also be paired or participate in interaction with a plurality of persons to control the combined toy to play attacking and defending games, so that control functions for the interactivity, the competitiveness and the antagonism of the toy are improved, and game effects including interestingness, participation and cooperation are enhanced.

The invention relates to a military vehicle weapon carrying and installing structure. The installing structure comprises a weapon mounting seat welding assembly, and the weapon mounting seat welding assembly is fixed with a frame longitudinal beam; the bottom of the weapon mounting seat welding assembly is provided with a jack and a seat disc structure, and the rear end of the weapon mounting seatwelding assembly is provided with a left large frame supporting structure, a right large frame supporting structure and a hydraulic oil cylinder. The weapon mounting seat welding assembly carrying aweapon is fixedly connected with the frame longitudinal beam and fixed with the frame longitudinal beam, and the weapon mounting seat welding assembly serves as an important component of an integratedframe and participates in integrated rigidity and strength design of the whole frame, so that the whole structure is compact, rigidity and strength are high, integration level is high, reliability ishigh, and mounting precision is high; the installing structure is high in light weight level, capable of carrying weapons such as artillery, rocket guns and guided missiles, capable of adapting to bearing and mounting of various weapons and capable of resisting strong recoil impact.

The utility model discloses a variable-rigidity high-reliability shock absorber which comprises a gasket, a low-rigidity shock absorption ring, a high-rigidity shock absorption ring, a low-rigidity shock absorption column, a high-rigidity shock absorption column and a sleeve. The section of the sleeve is in an inverted-T shape, the sleeve comprises a hollow cylinder and a circular ring fixed to the lower portion of the hollow cylinder, the hollow cylinder is sleeved with the low-rigidity vibration reduction column and the high-rigidity vibration reduction column, the outer diameter of the low-rigidity vibration reduction column, the outer diameter of the high-rigidity vibration reduction column and the inner diameter of a supporting lug hole of a vibration-reduced object are the same, and the outer diameter of the low-rigidity vibration reduction column is larger than the inner diameter of the supporting lug hole of the vibration-reduced object. The low-rigidity vibration reduction column and the high-rigidity vibration reduction column are installed in a supporting lug hole of an object subjected to vibration reduction in a combined mode, and the gasket and the sleeve are installed in a combined mode. The shock absorber disclosed by the utility model has the characteristic of variable stiffness, can adapt to different working conditions, and can meet the comprehensive shock absorption requirements of small load in orbit of space equipment and large load launched along with a rocket, and the comprehensive shock absorption requirements of small load of airborne weapons in hanging flight along with an airplane and large load in autonomous flight after launching.

The invention discloses an expandable combined aircraft. The expandable combined aircraft comprises at least two parallel fuselages, the two adjacent fuselages are connected through a connecting wing,an outer wing is arranged at the outer side of the portion, located at the side end, of each fuselage, and the fuselages and the connecting wing and / or the fuselages and the outer wings are fixed through fixing devices. The parallel fuselages are connected through the connecting wing and the fixing devices to achieve modularization design of the aircraft, the aircraft capable of being formed by combining multiple single unmanned aerial vehicles is obtained, different load task requirements can be met by increasing the length of the connecting wing or the number of the fuselages and connectingwings, and therefore a freight house, an investigatin device, radar weapon, a guided missile rocket and other devices can be hung below the aircraft.

The invention relates to a double-propellant configuration barrel rocket gun, in particular to a smoothbore barrel rocket gun using a double-propellant configuration rocket projectile, and aims to solve the problem that a large-power weapon is long in barrel and large in dead weight due to the fact that killing power of a traditional light weapon and a medium and small caliber gun is limited by barrel bore pressure at present. And the practical requirements that the weapon hit precision is superior to or at least not lower than that of an existing traditional barrel gun and the weapon and ammunition cost does not exceed that of the existing traditional barrel gun can be met. The main technical advantages of the invention are concentrated in the field of medium-and-small-caliber and limited-range direct aiming gun and gun weapons, and can be applied to infantry light weapons, such as pistols (individual self-defense weapons), submachine guns, automatic rifles, sniper rifles and light and heavy machine guns, and medium-and-small-caliber direct aiming artillery, such as tank cannons, antitank cannons, air defense cannons and aviation machine cannons.

The application provides a modular airborne detection and attack micro-rocket launching device, which comprises a weapon station module, a shell cabin module and a female head, a male head and a transmission module are respectively electrically connected to two ends of an electric control module and are controlled by the electric control module; a rotating shaft rotates along an axis; the shell cabin module is detachably connected to the rotating shaft and rotates with the rotating shaft; a shell cabin body is used for accommodating spare bullets; the female head is detachably connected to the male head, at this time, the weapon station module, the female head and the shell cabin module are in a non-integral structure, and the weapon station module, the female head and the shell cabin module can be separately disassembled, so that the modules of the modular airborne detection and attack micro-rocket launching device cannot be separately maintained, the maintenance convenience of the modules of the modular airborne detection and attack micro-rocket launching device is improved, in addition, the shell cabin module is detachably connected to the rotating shaft and rotates with the rotating shaft, so that the angle of the shell cabin module relative to the transmission module can be adjusted.

The utility model relates to the technical field of army teacher training auxiliary tools, and discloses a weapon launching bidirectional acousto-optic smoke effect simulation device, which comprises a device main body, and a bidirectional initiating explosive device is fixedly connected in the device main body. According to the weapon launching bidirectional acousto-optic smoke effect simulation device, through cooperative arrangement of the device main body, a limiting groove, a reset spring and a fixed suction cup, the device main body is rotationally clamped into a 40mm rocket barrel during training use, and then the reset spring is driven to be compressed; when the device main body is rotated and clamped to a proper position, the fixed sucking disc stops moving and is adsorbed on the inner wall of a 40mm rocket barrel for anti-skid fixation, and when the device main body needs to be separated, the device main body can be pulled out by rotating and loosening the fixed sucking disc, so that the anti-skid adsorption and fixation effects on the weapon launching two-way acousto-optic smoke effect simulation device and the 40mm rocket barrel are achieved; the operation is simple, and the possibility of loosening and falling off is low.

The invention discloses an underwater rocket thrust performance testing device, which relates to the technical field of underwater weapon thrust testing, which can simulate the underwater working environment of the rocket, objectively reflect the working performance of the underwater rocket, and further improve the Provide technical reference for optimized design. The device includes a rocket engine, a thrust test bench, a data acquisition system, a high-pressure water vapor bottle, and a temperature control box. The underwater rocket thrust performance test device provided by the invention can realize the thrust test in the underwater environment, simulate the working process of the missile engine in the real environment, and overcome the defect that the traditional ground thrust test method does not consider the influence of the water medium. The control completes multi-channel data acquisition, high-pressure water vapor inlet flow control, and online calculation of underwater projectile thrust performance parameters. The data obtained by this method can more objectively and truly reflect the working conditions of underwater bombs, and has the advantages of high precision and strong reliability.

The invention provides a portable self-rotating rocket projectile weapon. The portable self-rotating rocket projectile weapon adopts a launcher-rocket projectile integrated structure, fully utilizes the characteristics of low launching condition, high direct shooting precision and simple structure of a self-rotating rocket projectile, and is provided with a special disposable launcher to form theportable self-rotating rocket projectile weapon; and the defects that a traditional rocket projectile weapon is high in production cost, a launching position is easily exposed, and an individual soldier is not easy to carry and operate can be overcome. The rocket projectile weapon comprises a launcher and a rocket projectile, and the rocket projectile is a self-rotating rocket projectile with a turbine nozzle; the launcher is a disposable launcher and comprises a launcher body, four launcher supports, a sighting device and an ignition device. The launcher body serves as a storage and transportation barrel and a launching tube of rocket projectiles at the same time, and the launcher body can stretch and retract relatively in the axial direction; the launcher support can be folded and unfolded relative to the launcher body, and the sighting device and the ignition device are installed on the launcher body; and the ignition device is used for igniting and launching rocket projectiles.

The present invention discloses a method for testing the dynamic parameters of barreled weapons, comprising: dividing each launch tube of a launch box into a launch unit and multiple test units, wherein the launch unit is located at the center of the test unit; fixing multiple sensors arranged at equal intervals along a circumference using a fixed sensor mechanism, and fixing the sensors inside the test unit. The fixed sensor mechanism also serves as a pressure-bearing unit for the gas jet, which is then transmitted to the sensors; grouping the test units equidistant from the launch unit center; rotating the fixed sensor mechanism to adjust the sensor positions so that the sensors of the test units in the same group are located on concentric circles centered on the launch unit, the number of concentric circles being the same as the number of sensors in the fixed sensor mechanism, each concentric circle forming a test group; and collecting test data from multiple test groups to obtain data at different radial positions. This method solves the problem of impact equal-diameter testing of the gas jet during the launch of a box-type rocket launcher.

1. The name of the design product: rocket controller. 2. The use of the design product: the design product is mainly used with the overall assembly of the rocket launcher, can aim at the target to complete the precision strike, and at the same time display the working state of the rocket launcher, such as launch preparation, so that the shooter can know the weapon condition at any time. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: perspective view.

A projectile and method for stopping aerial vehicles. The projectile (101) comprises a shell (120) and a bunch of filaments (105). The bunch (105) is wound in a coil and placed inside the shell (120). The projectile (101) according to the solution may be brought to a target by different methods and utilising different means. For example, the projectile (101) may be fired with compressed air or a propulsion charge, by using a compressed air weapon or rocket launcher. In addition, the projectile (101) may be taken to the target by using a rocket or aerial vehicle.

The invention relates to the aviation lifesaving rocket sled test technique and relates to a speed measuring method for a rocket sled test. A test device comprises a vehicle-mounted signal acquisitionmemory, magnetoelectric sensors and a permanent magnet, wherein the vehicle-mounted signal acquisition memory and the magnetoelectric sensors are mounted on a sled vehicle body; the permanent magnetis mounted on the side of a track; the magnetoelectric sensors are respectively connected to the vehicle-mounted signal acquisition memory; and the vehicle-mounted signal acquisition memory is connected to a computer. The two or more magnetoelectric sensors are mounted on a sled vehicle along the heading direction to form multi-point detection. Measuring points respectively obtain data of the running speed of the sled vehicle and can be backups for each other so as to improve the reliability of the speed measuring operation. Based on the new distance difference and time difference between themeasuring points formed along the heading direction, a higher-precision speed value in a shorter interval can be obtained through difference calculation. The speed measuring method for the rocket sledtest can be widely applied to the tests, requiring high-precision speed parameters for testing and control, of railcars relating to aviation, aerospace, weapons and the like.

The invention discloses an underwater rocket projectile thrust performance testing device, and relates to the technical field of underwater weapon thrust testing. The underwater rocket projectile thrust performance testing device can simulate the underwater working environment of a rocket projectile, objectively reflects the working performance of the underwater rocket projectile, and provides technical reference for further optimization design of the underwater rocket projectile. The device comprises a rocket projectile engine, a thrust test bench, a data acquisition system, a high-pressure steam bottle and a temperature control box. The underwater rocket projectile thrust performance test device provided by the invention can realize underwater environment thrust test, simulates the working process of a projectile body engine in a real environment, overcomes the defect that a traditional ground thrust test experimental method does not consider the influence of an aqueous medium, and completes multi-path data acquisition, the control over the water inlet flow of high-pressure water vapor, and online calculation of underwater elastic thrust performance under the control of a computer. The data obtained by the method can reflect the working condition of an underwater projectile more objectively and truly, and has the advantages of high precision, high reliability and the like.

The rocket weapon or launcher launch system is characterized in that it includes: a base platform, which is fixed on the ground when in use; an erecting platform, one end of which is rotatably fixed on a fixed position of the base platform; The erecting platform is rotatably connected, and the other end is a free end, wherein a locking structure is provided at a position away from the fixed position of the base platform, and when the erecting platform is erected and rotated to a predetermined angle, the free end of the inclined support platform It is fixed and locked on the base platform by a locking structure arranged on the base platform. The invention adopts a purely mechanical structure scheme to complete the design of the box-type rocket launching device, solves the problem of launching tasks under the conditions of low-cost, fast-paced and high-reliability development, has the characteristics of easy operation, low cost, and high strength, and broadens the range of box-type rocket launchers. Type of rocket launch mode.

The invention relates to a new type of rapid rocket design and simulation analysis method. By building a task management system, a data management system, and an advanced rocket weapon design simulation integration platform framework, the customized development and integration of design tools and processes are completed, and the Task management, data management, cross-tool efficient collaborative work for the entire rocket product development process, as well as the accumulation and inheritance of relevant theoretical and empirical knowledge. The present invention sorts out the multi-professional business in the rocket weapon design process, integrates various software tools of various professions, conducts the data flow between the software, and conducts unified management of the simulation process data, and then solidifies and forms a standardized design for the rocket The process realizes the rapid analysis and optimal design of the overall rocket project, improves the efficiency and capability of rocket project development, and provides a powerful means for the rapid and in-depth comprehensive research and development of modern rocket weapons.

The invention relates to a nano-scale metal powder material, in particular to a powder material special for space-based weapons, which is prepared by the following steps: under a temperature between -5 and 5 DEG C, the high-frequency cutting frequency between 5000 and 5500 times per minute, processing the raw materials into special nano-iron powders whose the powder particle is in a shape of irregular ball; and respectively selecting the powder materials with the particle distribution of D3 = 42.21nm, D25 = 262nm, D50 = 500nm, D75 = 677.2 nm, D97 = 930.3 nm; then, using a DQ coating method to carry out anti-oxidation coating for the iron powder particles; and carrying out surface treatment. The metal powders can be made into metal bars which are provided with a small booster rocket; the small booster rocket is carried on a space platform 1,000 kilometers away from the ground at ordinary times, and can powerfully attack the targets on the earth through relying on satellite guidance.

The invention relates to the technical field of weapons, in particular to a novel low-recoil bore-free launching device which comprises a chainless ammunition supply system, a gun barrel, a gun barrel and a gun barrel. The gun box is installed on the top face of the chainless ammunition supply system and used for wrapping the integrated type launching ammunition; the electric firing device is mounted on one side of the gun box and used for firing the integrated firing ammunition; the motor driving mechanism is installed on the side provided with the electric firing device and used for driving the integrated firing ammunition to move. According to the invention, the concept of a traditional gun shooting weapon structure is broken through, the rotating tube weapon, the multi-tube rocket gun and the chainless bullet supply launching principle are integrated, and the structure and the launching principle of the weapon are innovated in all directions.

The invention discloses a rocket smoke bomb application strategy optimization method based on an SQP algorithm, and the method comprises the steps: building a rocket smoke bomb outer trajectory mathematical model, obtaining a smoke bomb trajectory equation, building a nonlinear optimization model with the minimum bomb consumption as a target function, determining a constraint condition, solving the mathematical model through a sequential quadratic programming SQP algorithm, and optimizing the smoke bomb application strategy. And obtaining an optimal feasible solution. According to the scheme, the nonlinear optimization model with minimum bullet consumption as a target function is constructed, constraint conditions can be flexibly adjusted according to whether a false target exists or not, on the premise that a true target is protected, enemy weapons can be induced to find and attack the false target, the probability of successful defense of the defense target is improved, and the defense efficiency is improved. The incoming flight weapons are effectively shielded and interfered by using the optimal number, arrangement, launching pitch angle and detonation time of smoke bombs, so that equipment resources are saved, and defense deployment and combat support with a higher cost-effectiveness ratio are realized.

The invention discloses a missile cylinder-out sinking angular velocity calculation method, electronic equipment and a storage medium, and the method comprises the following steps: abstracting a missile in a cylinder-out process as a rotation rigid body, moving in a longitudinal plane under single-point support, and setting gravity, thrust, support force and kinetic friction force; based on the momentum of momentum theorem and the missile motion constraint equation, a rigid body motion model of the missile out-of-cylinder process is established; and the rigid body motion model is used for substituting the instantaneous state variable value of the missile out of the cylinder, motion parameters until the missile is completely out of the cylinder are solved through integration, and the reference value of the missile sinking angular velocity is obtained. The method can replace an existing numerical statistical method based on a missile cylinder-out test, supports prediction of the sinking angular velocity at the beginning of design, can lay a foundation for early-stage optimization of an overall scheme, saves test cost in economy and time, has good expansibility, and is suitable for weaponry such as various cylinder-type launched missiles, rocket projectiles and the like.