40 results about "Air-to-air missile" patented technology

The invention discloses a remote air-to-air missile multi-platform cooperative guidance system and a realization method thereof. The multi-platform cooperative guidance system comprises an early warning plane module, a ground base radar detecting module, an aerial carrier module, a friend plane module, a remote air-to-air missile module, a target information space-time normalizing module and a target information fusion module. The realization method comprises the following steps: 1. an early warning plane, a ground base radar guided aerial carrier and a friend plane fly to a war area; 2. the radar of the friend plane operates to detect a target, and the aerial carrier launches an air-to-air missile; and 3. the targets detected by the radar of the early warning plane, the ground base radar and the radar of the friend plane are fused, and the friend plane carries out midcourse guide on the air-to-air missile. By adopting a multi-platform combat network formed by the early warning plane, the ground base radar, the aerial carrier and the friend plane to provide high-accuracy target information for the remote air-to-air missile, and adopting the friend plane to perform midcourse guide on the remote air-to-air missile, a remote target can be attacked stealthily and accurately.

The invention relates to an intiative reclaim control method of the air to air missile experiment missile. The method is added with an intiative reclaim control module and a built-in ballute in the inner of the missile, when the experiment occurs with fault or completes the flying test, the intiative reclaim control module is automatically started. The Control missile adopts the high dropping trajectory to reach the set deceleratatoin attitude-adjusting, then gives the parachute opening control signals, opens the deceleratatoin drag-parachute, completes the ntiative reclaim of the missile reclaim. After the missile reclaim control technology is adopted, the test personnel on the ground obtains the precious software working state and the flying test data in the flying, which realizes the effective utilization of the flying test missile. The technology advances the failure analysis and the zero adjustment work, which is of evident importance to accelerate the development speed of the missile.

A method and system is proposed for use by a moving station (such as a jetfighter) for radar tracking of a moving target (such as an air-to-air missile). The proposed method and system involves the use of a hybrid FSK/LFM (Frequency Shift Keying & Linear Frequency Modulation) scheme for acquiring a collection of raw radar data, a first Gaussian-noise filter array of one-stage linear Kalman filters for S/N-enhancement of the raw radar data, a trilateration module, and a second Gaussian-noise filter array of one-stage linear Kalman filters for S/N-enhancement of the trilateration-resulted radar data. These features allow the radar tracking of moving objects to be more fast and accurate.

The invention discloses a semi-strapdown air-to-air missile guidance method based on a sliding mode variable structural theory. The semi-strapdown air-to-air missile guidance method comprises the following steps of 1, acquiring a missile-target line-of-sight turn rate differential model under a line-of-sight coordinate system; 2, acquiring a motion tracking sliding mode guidance rule; and 3, acquiring an expected line-of-sight turn rate xd. According to the method, a sigmoid function is applied to the sliding mode surface design of the motion tracking sliding mode guidance rule, the missile-target line-of-sight angular rate is improved at the initial guidance stage, the estimation to the target motion state is improved, the missile-target line-of-sight angular rate is made to be zero at the last guidance stage, the miss distance is lowered, and the missile hit precision is improved.

A method for improving nighttime visual awareness of a pilot flying an aircraft carrying an air-to-air missile including one or more one gimbaled imaging sensor. The method includes providing a helmet for the pilot, a helmet tracking system for determining the attitude of the helmet relative to the aircraft, and a helmet-mounted display. The method also includes determining a current imaging sensor viewing direction of the imaging sensor of the air-to-air missile, sampling an image from the imaging sensor of the air-to-air missile and displaying the image on the helmet-mounted display. The determining and the displaying are performed so that the image displayed on the helmet-mounted display viewed by the pilot is spatially aligned with the scene viewed by the imaging sensor.

The invention belongs to air-to-air missile recovery technology, and relates to a hatch cover of an air-to-air missile recovery compartment, which includes a hatch cover substrate [1], a B-type hook [2], an explosion bolt connection seat [4], a hatch cover substrate [1] and a missile bomb The body has the same arc surface, the explosive bolt connection seat [4] is located on the inner arc surface of the hatch cover base plate [1] near the end of the missile head, and the Type B hook [2] is located on the inner arc surface of the hatch cover base plate [1]. Near one end of the missile tail, a drogue parachute suspension point [3] is arranged between the Type B grab [2] and the explosion bolt connection seat [4]. The invention realizes the reliable connection between the hatch cover and the projectile body with a simple hatch cover form, saves the space of the recovery cabin, and provides a larger installation space for the recovery umbrella system; the hatch cover forms an effective windward section, so that the hatch cover can Under the joint action of the power and the thrust of the explosive bolt, the guiding parachute is quickly taken away from the missile body, avoiding the structure of the airfoil and rudder surface of the missile body, and an effective parachute opening channel is formed.

A projectile, (Cruise Munition Detonator Projectile or CMDP), can be fired from a tank, modified grenade launcher or gun using a laser range finder, radar or manual input (dialer or keypad) range selector. The CMDP will prevent, neutralize and eliminate enemy close infighting. The CMDP can defend aircraft against SAM, shoulder launched missiles, and air-to-air missiles. The CMDP will travel a predetermined programmed distance and detonate in front of or behind, over or beside, or in the mist of a target. The CMDP allows small forces to strategically neutralize larger forces with devastating effect. The CMDP is a force multiplier and an anti-personnel weapon.

The invention relates to an air-to-air missile direct force/aerodynamic finite time anti-saturation control method. In order to avoid the singularity of the traditional terminal sliding mode, a new integral sliding surface is proposed, which can converge the system state to the equilibrium position for a given finite time. An integral sliding mode controller that can deal with the bounded disturbance and the input saturation problem is designed,, and the virtual control torque needed to build a missile overload is obtained based on the longitudinal motion model of the missile. Controlled distribution is used to map the desired control torque to the aerodynamic rudder surface and direct force device. Both theoretical analysis and digital simulation show that the proposed controller enablesthe composite control missile to track an overload command signal for a limited time, and the closed loop system is stable.

Techniques are disclosed for producing and/or optimizing jamming codes for use in directional infrared countermeasures (DIRCM) systems. In some embodiments, Fourier analysis may be implemented to produce jamming codes which more efficiently (e.g., time efficient, power efficient) and/or more reliably (e.g., no frequency gaps) achieve optical break-lock (OBL) of infrared (IR)-seeking missiles/threats over a broad range of frequencies (e.g., short-wavelength IR, mid-wavelength IR), as compared to heritage jamming code methodologies. Some embodiments may be implemented in military/defense applications (e.g., protection of military/tactical aircraft or other vehicles); some other embodiments may be implemented in non-military/commercial applications (e.g., protection of domestic, civilian, and/or commercial aircraft or other vehicles). Some embodiments may be implemented to protect against IR-seeking air-to-air missiles (AAMs), surface-to-air missiles (SAMs), and/or man-portable air-defense systems (MANPADS/MPADS). Numerous configurations and variations will be apparent in light of this disclosure.

The invention relates to an air-to-air missile telemetry antenna shielding cover, which belongs to the microwave telemetry technology and relates to the improvement of an air-to-air missile telemetry cabin test device. It is a hollow cylinder made of magnetic isolation material with a circular or regular hexagonal cross-section. The hollow cylinder is composed of two symmetrical half-tubes with the same structure. Each half-tube is composed of a half-tube wall[ 1], composed of two end covers [2], there is a hinge mechanism [3] on one side of the two half cylinders along the axial direction, forming a hinge connection between the two half cylinders; on the axial side of the two half cylinders There is a locking mechanism [4] on the other side. The invention can ensure that the intensity of electromagnetic waves radiated by the transmitting antenna of the telemetry cabin to the space meets the requirements of the national standard for radiation damage to the human body, avoiding radiation damage to the human body caused by electromagnetic waves radiated by the telemetry cabin; at the same time, avoiding the multi-path reflection of personnel walking and the environment The impact on the telemetry test ensures the normal progress of the telemetry test.

The invention belongs to the radar technology, and relates to the improvement of the feed source of the broadband parabolic antenna of the air-to-air missile radar seeker. It includes a feed source composed of four double-ridged horn antennas with the same structure. The double ridges of the horn extend out of the horn mouth surface, and the protruding height h=2~5mm. The ridge curve equation of each double ridge horn greatly reduces the size of the mouth surface of each double ridge horn in the present invention, reducing the size of the horn mouth surface. Shading, which improves antenna efficiency and facilitates use on small missiles.

The invention belongs to the information processing technology of the infrared air-to-air missile seeker, and relates to the improvement of the subdivision circuit of the light-mechanical scanning component of the scanning imaging seeker. The digital subdivision circuit of the optical-mechanical scanning component of the scanning imaging seeker is characterized in that it consists of two signal conditioning circuits with the same structure, a frequency detection circuit [4], a phase detection circuit [5] and a pulse generation circuit [ 6]; the signal conditioning circuit is composed of a DC blocking capacitor C, an AGC amplifier [1], an A/D converter [2], and a pulse converter [3]; the frequency detection circuit [4] is composed of a counter [8] and a high-speed clock [9]; the phase detection circuit [5] is composed of a D flip-flop [10]; the pulse generating circuit [6] is composed of a divider [11], a frequency divider [12], a clock delay [13], a NOT gate [14], the first gating switch [15], the second gating switch [16] form. The invention has high signal processing precision, strong anti-interference ability, simple circuit, small size and high reliability; it reduces the difficulty of system debugging and improves the debugging efficiency.

The invention discloses a domestic self-destruction device for a missile imported from Russia, which can meet all self-destruction conditions of an air-to-air missile imported from Russia so as to make self-destruction response, thereby realizing the self-destruction of the missile. The self-destruction device can pass a whole missile test of test equipment for the missiles imported from Russia, and can meet requirements of training exercises. The hardware design adopts a scheme of combining a digital circuit with an analog circuit, wherein the digital circuit takes a high-performance CPLD (complex programmable logic device) chip as a core, and the analog circuit takes a high-performance operational amplifier and a comparer as main elements; and the hardware comprises a system clock, the CPLD control chip, a lateral overload sensor, a lateral overload ultralimit judgment circuit, a deviating angle speed ultralimit judgment circuit, a self-destruction control logic, a test module, an adapter and a power supply module. Figure 1 is a system chart.

The invention belongs to the simulation test technology and relates to the improvement of a simulation test device for an air-to-air missile guidance system. It includes the electronic components of the missile flight control system, and is characterized in that a PC104 computer, an A/D acquisition card, a pulse generator and the electronic components of the flight control system are connected to form a flight control system simulator. The flight control simulator of the present invention can provide a complete guidance system simulation environment required except for the seeker, and its electrical and mechanical interfaces are the same as those of the flight control system products, which truly simulates the work of the flight control system and can replace real products to participate in The test does not require the participation of large-scale equipment such as turntables, and is not limited by the number of uses and time, which not only saves costs, but also facilitates the test, and provides a large amount of experimental data for the design and verification of the guidance system.

The invention relates to an ignition safety device, in particular to a return mechanism of an air-to-air missile solid rocket motor ignition safety device. The return mechanism of the air-to-air missile solid rocket motor ignition safety device of the present invention is arranged on the ignition safety device, and it is composed of a follower screw, a tension spring, a fixing screw and a spring support. Wherein, the ends of the two torsion arms of the tension spring are torsion arm earrings, the first torsion arm earring is inserted into the follower screw, and the second torsion arm earring is inserted into the fixing screw, and the fixing screw is arranged on the spring support , and the spring support is fixedly arranged on the ignition safety device, and the follower screw is connected with the ignition safety device. When the tension spring is deformed, it can provide thrust for the follower screw, which can be converted into a torque greater than the friction torque of the ignition safety device, preventing the ignition safety device from staying in the middle position outside the safe position and the combat position, thereby effectively avoiding air-to-air Misfired missiles occurred, increasing safety.

The invention discloses a wireless electric fuse signal treatment device and an air-to-air missile. The wireless electric fuse signal treatment device comprises a signal input module, a signal treatment module and an executing module; the signal input module is used for receiving an echo signal which is reflected by a target and used for determining the distance between the air-to-air missile and the target, the signal treatment module is connected with the signal input module and used for determining whether the distance between the air-to-air missile and the target reaches the preset distance of the threshold value or not according to the echo signal reflected by the signal input module, and if yes, the delaying triggering time of a fuse on the air-to-air missile is determined according to judged data of an aerial carrier radar over target tracing; and the executing module is connected with the signal treatment module and used for triggering the executing module to move so that the fuse can be triggered in a delayed mode according to the determined delay triggering time. According to the wireless electric fuse signal treatment device and the air-to-air missile, control precision is high, and hit and damage intensity on vital parts of the target are improved.

The invention discloses a bidirectional initiating explosive device plug connection state identification method comprising a missile-borne computer plug, an initiating explosive device plug and a testequipment plug; based on original pins, four pins are additionally arranged on each of the missile-borne computer plug, the initiating explosive device plug and the test equipment plug; furthermore,a missile resistance detection circuit is added to a missile-borne computer connected with the missile-borne computer plug, and a test equipment resistance detection circuit is added to test equipmentconnected with the test equipment plug; the missile resistance detection circuit and the test equipment resistance detection circuit are matched with the four additionally-arranged pins of each of the missile-borne computer plug, the initiating explosive device plug and the test equipment plug, and thus the connection state of the bidirectional initiating explosive device plug can be accurately detected; therefore, the problem that after the aircraft loading operation of an air-to-air missile is completed, missile mounting operation personnel and a carrier aircraft pilot cannot check the connection states of the missile-borne computer plug and the initiating explosive device plug is solved, so that the risk of missed connection of the missile-borne computer plug and the initiating explosive device plug is thoroughly avoided.

The invention relates to the control problem of missile elastic body, in particular to a structural filter for eliminating elastic vibration of air-to-air missile body. It consists of an input terminal Vin, an output terminal Vout, an operational amplifier and a bridge resistance-capacitance network. The structural filter of the invention meets the application requirements of a certain type of missile. In addition to meeting the required amplitude-frequency and phase-frequency characteristics, it also has the advantages of novel design ideas, small size, compact structure and easy adjustment.

The invention provides a carrier-borne stealth multi-purpose fighter aircraft model specially used for a floating-island-type aircraft carrier. The carrier-borne stealth multi-purpose fighter aircraft model comprises a body, a detector, a cockpit, an engine, electronic warfare jamming bombs, air-to-ground guided missiles, air-to-air missiles, antiship missiles, empennage supports, empennages, an antisubmarine torpedo, an antisubmarine missile, a combined-type balance frame tail vane and a fire control radar. Through the stealth technology, the fighter aircraft can effectively avoid radar tracking, is convenient to attack, transfer and camouflage flexibly and is not easy to be found by enemies; the fighter aircraft is equipped with the electronic warfare jamming bombs, the air-to-air missiles, the antiship missiles, the antisubmarine torpedo and an anti-submarine missile strike device, so that striking range of the fighter aircraft is enlarged; the fighter aircraft can strike to the air, to the ground and to the sea, thereby greatly improving battlefield survival rate and sudden strike capability of the fighter aircraft; and meanwhile, serving as a teenager national defense education model, the stealth multi-purpose fighter aircraft model displays developmental level of modern aircraft carrier and fighter stealth technology, and plays an active promotion role in education of youth's ocean view and national defense awareness.

The invention provides a fastening device for the outer portion of a rocket engine. The fastening device comprises a fastening wrapping belt, and is characterized in that the two ends of the fastening wrapping belt are provided with a first connecting end and a second connecting end correspondingly, and the first connecting end and the second connecting end are provided with movable connecting devices matched with each other. The fastening device for the outer portion of the rocket engine is simple in structure, reliable and practicable and is used for fixing pins in pin connecting structures in the radial direction, and the pins large in fit clearance are effectively prevented from disengaging from the interiors of pin holes; and pneumatic shaping is effectively conducted on the outer profile of an air-to-air missile, and the missile pneumatic resistance is reduced.

A new type of ground telemetry checkpoint, which belongs to the air-to-air missile test technology, specifically relates to the improvement of a ground telemetry checkpoint, which is characterized in that an external adapter board is fixedly connected to the rear panel of the industrial control computer, and an adapter is arranged on the external adapter board , the above-mentioned adapter is corresponding to the connector drawn out from the back panel of the industrial control computer through the connector, and is correspondingly connected with the joint drawn out from the back panel of the industrial control computer through the connector. In this method, without changing the hardware structure of the main working board and the basic skeleton of the computer, by adding an adapter board outside the computer, it is a good solution to the problem that the external connection cable of the checkpoint is easily caused by long-term suspension strain. Poor contact leads to hidden dangers of unreliable telemetry signal reception. This solution has been applied to several ground telemetry checkpoints.