61 results about "Drogue parachute" patented technology

A parachute control system is actuated primarily by drogue parachute drag force. Drag force is used as a proxy for vehicle airspeed. The control system uses altitude and force sensors combined with a chronograph to determine the state of a deployed drogue parachute. It then compares the sensed condition with a condition defined by preset altitude, force, and time values. Once both altitude and drogue parachute drag force are below certain maximum values and within pre-determined time windows, an event trigger signal is generated.

The invention discloses a controllable air-drop parachute, which comprises a drogue parachute, a main parachute, a control rope, a balancing pole, an execution motor, a measurement and control system and a suspender, wherein the main parachute is connected with the control rope; the control rope is connected to the execution motor through the balancing pole; an output end of the execution motor is connected with the control rope; an input end of the execution motor is connected with an output end of the measurement and control system; and an input signal of the measurement and control system is given by the balancing pole and a positioning system. The controllable air-drop parachute has the advantages of compact and simple structure, high universality, high practicability and low cost; an unmanned automatic device is additionally arranged on the basis of the conventional parachute for reconstruction; air-drop efficiency of supplies can be greatly increased; and various unnecessary losses and the like are avoided.

A system for deploying a deployable structure in an aircraft, comprising a drogue parachute, at least one deployable structure, a riser line attached to the drogue parachute and the at least one deployable structure, wherein when the drogue parachute is deployed, a tension is applied to the riser line, and a parachute deployment system, wherein the parachute deployment system is configured to utilize the applied tension to deploy the at least one deployable structure.

The invention discloses a spreading device for integrally throwing small cluster unmanned aerial vehicles. The spreading device is composed of a cluster loading nacelle, a brake parachute assembly, alocking and releasing mechanism, a single launching canister and the small unmanned aerial vehicles. The cluster loading nacelle is hung on the lower portion of a wing of the unmanned aerial vehicle carrier, during launching, only the small unmanned aerial vehicle in the single launching canister needs to be unlocked at the designated height, other catapulting mechanisms are not needed, and the control process is simple. The cluster loading nacelle is integrally thrown, and the collision risk between the small unmanned aerial vehicle and a carrier aircraft in the launching process is reduced.A cluster loading nacelle short-interval quick unlocking and throwing mode is adopted, one-time multi-frame quick aerial launching of small cluster unmanned aerial vehicles can be achieved, and the launching efficiency is high. A cluster loading nacelle overall speed reduction mode is adopted, and the structure is simple; the aerial carrier can be launched in an airspace higher than the combat height of the small unmanned aerial vehicle; and when the small unmanned aerial vehicle reaches a safe distance from the cluster loading nacelle, the propeller is started, and the small unmanned aerial vehicle flies to a predetermined area for networking.

The present invention relates to a skydiving equipment with a drogue parachute which is intended to capture the deployment bag until the opening, and to suspend the parachutist(s) in a horizontal position during the free fall, while distributing the tension forces of a drogue parachute (1) such that the ripcord operation is effortless. This arrangement includes first and second fastening straps and releasable fastening means fastening the drogue parachute (1) drogue bridle (2) to the parachute pack (18) at the desired level of the main container (10). Connecting means, which consist of a three-ring system, connect the upper tab (61) and the lower tab (51) to the drogue parachute (1) drogue bridle (2). The connecting means are operational to effortlessly cause the release of the upper tab (61) and the lower tab (51) out of the drogue bridle (2) simultaneously or successively.

The invention discloses a mechanical brake parachute unfolding device and unfolding method for a missile, and relates to the field of brake parachutes. The brake parachute unfolding mechanism for themissile comprises a missile body, a lifting lug, an air-drop release plug, a brake parachute cabin and a brake parachute unfolding mechanism, wherein the missile body is connected with a hanging framethrough the lifting lug and the air-drop release plug which are installed on the missile body, one end of the brake parachute cabin is connected with the missile body, the other end of the brake parachute cabin is provided with the brake parachute unfolding mechanism, and the brake parachute unfolding device for the missile can be used for opening a parachute at a specific height in a mechanicalmode so as to open the brake parachute. According to the technical scheme, the brake parachute can be stably and reliably opened, the safety in the using process is guaranteed, and the device can be applied to the civil field.

A selection is made between single stage and multistage parachute deployment for a vehicle based at least in part on vehicle state information. In the event multistage parachute deployment is selected, a drogue parachute is deployed during a first deployment stage and afterwards, a main parachute is deployed during a second deployment stage. In the event single stage parachute deployment is selected, at least the main parachute is deployed in a single stage where in the event the drogue parachute is deployed during the single stage, the drogue and main parachute are deployed simultaneously.

A parachute release apparatus for controllably and timely releasing a drogue parachute from a descending, aerially delivered cargo platform. The parachute release apparatus is comprised of a pendant body with multiple parallel plates. Cavities are defined between each two parallel plates of the pendant body. Latch mechanisms are disposed on either side of the pendant body. Each latch mechanism is comprised of an articulating outer and inner plate. Within each cavity is a pair of release arms which articulate with the pendant body. Either release arm engages with the inner latch plate of each latch mechanism. The latch mechanisms are maintained in a latched configuration by a cut loop attached to extension arms on either outer latch plate, and are released by a pyrotechnic cutter disposed on the cut loop. A plurality of suspension straps are coupled with the apparatus, which are enshrouded in a bifurcated sleeve.

The invention relates to a motion modeling and decoupling method for an air-launched cruise aircraft with a brake parachute. The method comprises the following steps: step 1, carrying out dynamics andkinematics modeling on a parachute ejection system; 2, solving the acceleration of a connection point by using rigid body kinematics and dynamics knowledge; 3, carrying out equal decoupling by usingthe acceleration of the connection point of the projectile body and the brake parachute; 4, carrying out connection comparison simulation with a spring. The invention has the advantages that 1, the parachute ejection system is regarded as spherical hinge connection, an original simplified six-degree-of-freedom parachute ejection model connected through a spring is expanded to nine degrees of freedom, the simulation calculation precision and the calculation efficiency are improved, and higher numerical calculation stability is achieved; 2, the analytical solution precision of the rigid hinge interaction force of the missile-parachute system model is higher, more actual conditions can be simulated, and reference can be provided for parameter design of an air-launched weapon pilot with a brake parachute;.

The invention discloses an active opening type parachute, comprising a parachute cover and parachute ropes (5), wherein the parachute cover is composed of an outer parachute cover (1) and an inner parachute cover (2); a sealed air bag is arranged between the outer parachute cover (1) and the inner parachute cover (2) which are connected by a connecting thread (3); a compressed gas tank (4) is arranged at one corner of the parachute cover; a valve on the compressed gas tank (4) is connected to a control parachute rope among the umbrella ropes (5); a retractable circular hole (6) is formed at the topmost end of the parachute cover; and pull ropes (7) are connected to the two sides of the circular hole (6). The area of a thrust surface of the parachute cover can be controlled in an active manner; the dropping speed of the parachute can be adjusted; the parachuting height can be effectively reduced; and as the parachute bag is small, the parachute is convenient for carrying, short in parachute opening time and easy for control.

The invention relates to a refueling hose joint drogue parachute framework limiting structure which comprises ropes with rope rings arranged at two ends, framework pieces with U-shaped through holes,screws and retaining blocks. Each U-shaped through hole is composed of a wide groove and two elongated grooves communicated with the wide groove, each framework piece form a rope hanging strip betweenthe corresponding two elongated grooves, the two rope rings on a same rope are respectively hung on the rope hanging strips of each adjacent two framework pieces, the retaining blocks extend into thewide grooves from one sides of the framework pieces and enable the rope rings not to go out of the rope hanging strips, the screws are in threaded connection with the retaining blocks on the other sides of the framework pieces, and the screws after being in threaded connection clamp the framework pieces to prevent the same from going out. The limiting structure is simple in structure, small in size, light in weight, convenient to mount and demount and less prone to breakage.

The invention discloses a cluster-type small-volume target damage image collecting system and a collecting method thereof. According to the cluster-type small-volume target damage image collecting system, a plurality of collecting devices provided with brake parachute devices are arranged in a groove of a host ammunition, and a cover plate is installed on a shell body of the host ammunition through a connecting part; the collecting devices and the brake parachute devices are correspondingly connected to a mooring rod part through triggering parts; when the host ammunition is launched, a control system sends a separation signal to the connecting part, the connecting part is broken, the triggering part is pulled by the mooring rod part, thus the collecting devices are triggered to start, andmeanwhile parachute packs of the brake parachute devices are opened; the collecting devices collect image data below and send the image data outward; image collection is synergistically conducted through a plurality of sensors, the collecting field of the image collection is effectively enlarged, and thus the effectiveness of detecting the droppoint area of the ammunition is improved; and the three-mode image information collection combines infrared, ultraviolet and visible light, a plurality of the collecting devices collect by division of work, and the image information of a multispectral band in the droppoint area of the ammunition is obtained.

The invention discloses a sewing method for a drogue parachute opening spring, which relates to the field of parachutes. The method comprises the following steps of S1, first fixing a conical spring protective sleeve together with a conical tip of a conical spring; next, compressing a big end of the conical spring; compressing the conical spring to 3/5-4/5 of the length of the conical spring in a natural extending state; and then respectively tying and fixing two ends of diameters of the first circle to the third cycle of the big end of the spring by using two ends of a smooth nylon yarn rope; S2, folding the middle section of the smooth nylon yarn rope, exerting the folded end to penetrate through a central hole of a bottom enclosing cloth, and tying a fixture at the folded end so as to prevent the folded end from jumping into the conical spring protective sleeve; S3, integrally sewing the big end of the conical spring protective sleeve and the bottom enclosing cloth; and S4, untying the smooth nylon yarn rope from the folded end so that the conical spring is flipped. The sewing method for the drogue parachute opening spring, disclosed by the invention, is advantaged in that the difficulty in sewing the spring protective sleeve and the bottom enclosing cloth can be reduced, the sewing quality can be effectively ensured and the method can be conveniently and effectively operated by workers.

The invention discloses a launch type parachute dynamic test device which comprises a gun body system, a test bomb system and a pressing disc system. The gun body system comprises a gun bore, an air bore and a locking mechanism; the test bomb system comprises a bomb cylinder, the head of the bomb cylinder is provided with an instrument cabin, the tail of the bomb cylinder is provided with an opening, a tested parachute pack containing a tested parachute is arranged in the bomb cylinder, and the tested parachute is connected to the instrument cabin; the pressing disc system comprises a pressingdisc which blocks the tail of the bomb cylinder and separates the air bore from the gun bore in a sealed mode; a pilot parachute is arranged on the air bore side of the pressing disc, a pressing discrecovery parachute pack provided with a pressing disc recovery parachute and a braking parachute is arranged on the gun bore side of the pressing disc; the pilot parachute is used for guiding the test bomb system and the pressing disc system to be straightened; and the pressing disc recovery parachute is used for recovering the pressing disc system, and the braking parachute is used for decelerating and synchronizing the pressing disc system and the test bomb system after the pressing disc system and the test bomb system are separated in the air and recovering the tested parachute pack. According to the invention, actual parachute opening conditions and limit parachute opening speeds of various parachutes can be simulated, the test cost is low, the test efficiency is high, and the effective test data acquisition rate is high.

The invention belongs to the technical field of aviation, and particularly relates to a brake parachute opening and separation control algorithm for a manned spacecraft reentry capsule, which comprises the following steps of: providing a current pitch angle speed q and a current yaw angle speed r by using an inertial measurement unit in the manned spacecraft reentry capsule to calculate an attitude angle change rate RSS of the reentry capsule; controlling the brake parachute to be opened by comparing the return capsule attitude angle change rate RSS with the RSS parachute opening threshold value, judging the brake parachute separation condition by comparing the return capsule attitude angle change rate RSS with the RSS separation threshold value or comparing the OF value with the OF separation threshold value, or sending a brake parachute separation instruction when the pitch angle speed q is located at the falling edge and within the specific interval range. According to the algorithm, the oscillation amplitude of the return capsule in the period from brake parachute opening to main parachute opening is remarkably reduced, and the situation that the large bottom faces forwards and is not beneficial to main parachute opening is reduced.

The speed reduction device comprises a main channel, a main channel front opening is formed in the position, at the front end of the speed reduction device, of the main channel, a main channel rear opening is formed in the rear end of the speed reduction device, two or more front backflow channels are further arranged in the speed reduction device, and one end opening of each front backflow channel is communicated with the inner wall of the main channel in a beveling mode in the direction facing the main channel front opening. The other port of the front backflow channel is led out from the front end position of the speed reduction device, and the direction of the leading-out port is the same as or close to the direction of the front opening of the main channel. The speed reducer adopts the structure of the front backflow channel and the rear backflow channel, so that in the speed reduction process, reverse thrust of fluid can be fully utilized, the speed reduction efficiency is improved, and dependence on reverse thrust of a brake parachute and an internal machine is reduced; the inner wall of each channel of the speed reducer adopts a rotatable spherical convex surface structure, so that the friction force between fluid and the inner wall can be reduced, turbulent flow and turbulent flow generated when the fluid moves in a pipeline are reduced, the vibration and noise of a machine are reduced, and the power conversion efficiency is improved.

The invention discloses a wind resistance deceleration system capable of shortening the braking distance of a vehicle, the system comprises a start button, a controller and a deceleration system, the deceleration system is composed of a sliding cavity, a sliding column driving device, a sliding column, a servo device and a deceleration parachute; when the vehicle is braked emergently at a high speed, a driver finds that the speed reduction degree of the vehicle is too small, the start button can be pressed down, after the controller receives a start signal, the deceleration system is instructed to work, the deceleration parachute is automatically opened, the vehicle is decelerated through wind resistance, and the wind resistance can be controlled by controlling the opening angle of the deceleration parachute; according to the system, on the basis of not changing the original dynamics of the vehicle, the driving resistance of the vehicle is increased, the braking distance of the vehicle is shortened, the operation such as steering of the driver cannot be affected, meanwhile, the wind resistance can be automatically adjusted, the structure is simple, and the application is easy.

The invention relates to the technical field of aerospace, and relates to a reducer capable of buffering landing. The technical problem that existing deceleration technology is insufficient is solved.According to the technical scheme, after a lander reaches a predetermined height, a deceleration umbrella is wrapped around the outer surface of an air bag so as to protect and enhance the air bag. The technical measure comprises a canopy, a traction rope, a base, a first air bag, a first air generator, a second air bag, a second air generator and a landing cabin. The first air bag is of a closedair bag-like structure, and is capable of expanded through inflating, the lower end of the first air bag is fixedly connected with the base, and the upper end of the first air bag is fixedly connected with the landing cabin. The second air bag is of a closed air bag-like structure, and is capable of expanded through inflating, and the lower end of the second air bag is fixedly connected with thelanding cabin. When the first air bag and the second air bag are inflated and expanded, the landing cabin is clamped between the air bags. The reducer has the beneficial effects that when the landingcabin lands, the canopy and the traction rope are wrapped around the outer peripheries of the first air bag and the second air bag, the strength of the first air bag and the strength of the second airbag are enhanced, and then the protection of the landing cabin is enhanced.