UA108839U - DEVICES FOR AUTOMATIC DISCONTINUATION OF THE TARGET UNIT - Google Patents

Abstract

The UAV automatic parachute device is equipped with a parachute, a retaining lock, a servo mechanism for the lock actuator, loops through which the slings are held, and a shock sensor connected via a communication channel to a descent control board that pulses the servo mechanism of the lock actuator. The retaining lock is located in the fuselage, two front and two rear inner hinges, which are arranged in pairs and symmetrically on both sides in the fuselage through which the openings are held and the lower working ends are engaged by the stem of the inner retaining lock two rear and two front upper loads, the ends of the cargo slings are secured to the central suspension sling, and the lower working ends of the cargo slings are engaged by the stem of the inner retaining lock, and the impact control sensor is ultrasonic and connected to the serv. Lock Actuators using electrical cables.

Description

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The useful model belongs to the technical means of preventing the destruction of an unmanned aerial vehicle (UAV) while dragging it along the ground with a parachute.

It is known that parachute descent is the main way of performing a safe landing of winged unmanned aerial vehicles intended for operation in non-aerodrome conditions. As an example, we can name UAV Ogadapplu Tapdo (Canada) (trans:/Lumlu.agadappu. sotu), "Orbiter" (Israel) (trans:Loruag.gy/29512-rriaogyeg.piti), "Orlan" (Russia). (per:/rr-Ia.gy/oria-opap-10/,, "Luna" (Germany) (peEr:/lymlmy. etirep2begod.Dae/rgodikie/iagoppepsuziet/zreziyKayopep.piti) and other Sptappei (Aegia! Mepisie5 apa

Tagdei5. IN5 dap'eb5. INB SiobaI and itiea 2010. 21,100,101). Along with the positive features of parachute systems, they have a number of disadvantages, one of the 3 main ones being the destruction of the UAV by the parachute itself when dragging the UAV along the ground. Thus, in the presence of a surface wind with a speed of 7-10 m/s, which is almost twice the speed of parachute descent, the dome of the parachute on the ground does not always "go out" and is very often filled. Depending on the area, it can develop a sufficient force (in three- four times more than the weight of the UAV) to drag the UAV along the ground and significantly destroy it until it is complete, that is, bringing the UAV to an unusable state.

To prevent the destruction of the UAV from being dragged along the ground, devices for manual (remote) and automatic detachment of the parachute filled on the ground from the UAV are used.

Devices for manual (remote) decoupling control are not common, due to incorrect activation of the decoupling due to the demolition of the UAV by the horizontal component of the wind and its significant deviation from the planned landing point; mostly they are used as backups. The devices for automatic release of a parachute from

BLA

The method of landing the aircraft, system and device (UAV manufactured by IZKABEYA

AEVOBRACE IMO Go) (pr /Llymly. ai.so.P/2013/36720-ep/Vyzipe55Ageaz. OpitappeyaAiigZuzietv5.azrh). The device for automatic release of the parachute, which is implemented in the Vigi Eue 400 UAV, consists of an external control unit for the parachute slings (retaining lock, external sling loops), a servo mechanism for the lock drive, which is controlled by the descent control board, which is connected by a communication channel with the tracking system

From the contact of the plane with the surface (impact sensor) (patent M/O2007086055 (A1), IPC 8В63835/52; вб4с39/02; Вб64017/80; Вб64Е1/02, published on 02.08.2007). This device is selected as the closest analogue.

The deployment of the parachute release device is initiated by the impact sensor, which detects the impact of the UAV fuselage on the ground. At the same time, the appropriate impulse is sent from the descent control board to the servomechanism, which in turn opens the external retaining lock, the corresponding cargo slings are disconnected from the fuselage, and the parachute is released from the UAV. This makes it impossible to open the dome again, since there is no load on the cargo slings (mechanical resistance from the UAV, which is stationary on the ground).

A significant drawback of the known device is the external location of the cargo slings on the fuselage of the UAV, the external location of the release lock, as well as the lack of advance opening of the release lock drive servo mechanism.

The external location of the cargo slings on the fuselage of the UAV and the lock leads to the need to use external sling loops, which increases aerodynamic resistance, complicates the design and, accordingly, complicates the pre-flight installation of the parachute.

The lack of anticipation of the opening of the servo mechanism of the release lock drive leads to partial dragging of the UAV on the ground, and in the case of strong wind, i.e. the presence of its significant horizontal component, to its overturning and damage to the UAV.

The impact sensor may not work if ground conditions (grass, soft ground, etc.) cause the UAV to slow down in the last few centimeters before touchdown.

The useful model is based on the task of improving the device for automatic unhooking of a parachute from a UAV by simplifying its design, reducing aerodynamic resistance, and anticipating the moment of direct unhooking of cargo slings from the lock, which will make it possible to increase the efficiency of UAV operation in non-aerodrome conditions.

The task is solved by the fact that the device for automatic release of the parachute from

A UAV equipped with a parachute, a retaining lock, a servo mechanism for the lock drive, loops through which the slings are passed and an impact sensor, which is connected to the descent control board through a communication channel, which provides an impulse to the servo mechanism of the lock drive, has a retaining lock placed in the fuselage , two front and two rear internal loops, which are located coaxially and parallel on both sides in the fuselage, through the holes of which the two rear and two front cargo slings of the parachute are attached to the rod of the internal retaining lock with their lower working ends, and the upper ends of the cargo slings are fixed to the central suspension sling, and the lower working ends of the cargo slings are hooked to the rod of the internal retaining lock and the shock control sensor is made of ultrasonic and which is connected to the servo mechanism of the lock drive by means of an electric cable.

The use of an internal retaining lock and the internal arrangement of cargo straps allows to reduce the aerodynamic resistance of the UAV in flight due to the absence of protruding elements of the device above the aerodynamically "clean" surface of the fuselage. In addition, the internal arrangement of the cargo slings simplifies slinging by removing the external sling loops and, accordingly, simplifies the pre-flight installation of the parachute.

The use of an ultrasonic sensor to trigger the activation of the servo mechanism of the lock drive allows you to measure and set the immediate height of the activation of the servo mechanism of the lock drive, which ensures the opening of the lock in anticipation of the impact.

Accordingly, at the moment of contact with the ground, the UAV is guaranteed to be disconnected from the cargo straps of the parachute, which makes it impossible for it to be partially dragged along the ground or overturned and damaged in case of strong wind.

The essence of the useful model is explained by the drawings, in which: fig. 1 shows the device for automatic release of the parachute of an unmanned aerial vehicle, installed in the fuselage of the UAV, which is in the state of the released parachute and the closed internal retaining lock; fig. 2 shows the view of the ultrasonic sensor installed in the UAV; fig. C shows a device for automatic release of the parachute of an unmanned aerial vehicle, installed in the fuselage of the UAV, which is in the state of released parachute and open internal retaining lock (parachute release).

The elements of the useful model are marked with the following numerical positions: 1 - the fuselage of the UAV 2 - the front internal loop, through the hole of which the front cargo sling of the parachute is passed

C - the rear internal loop, through the hole of which the rear and front cargo slings of the parachute are passed

Z 4 - cargo slings of the parachute 5 - central suspension sling of the parachute b - drive of the servo mechanism 7 - rod of the internal retaining lock 8 - electric cable 9 - ultrasonic sensor 10 - descent control board 11 - lower working ends of the front and rear cargo slings 12 - upper ends of the cargo slings

A device for automatic detachment of a parachute from a UAV, equipped with a parachute, a retaining lock, a lock actuator servomechanism, loops through which slings are passed and an impact sensor, which is connected through a communication channel to a descent control board that supplies an impulse to the lock actuator servomechanism, which is made in such a way that the retaining lock (7) is placed in the fuselage (1), two front (2) and two rear (3) internal loops, which are placed in pairs and symmetrically on both sides in the fuselage (1), through the holes of which the the lower working ends of the two rear and two front cargo slings of the parachute (4) are attached to the stem of the internal retaining lock (7), and the upper ends of the cargo slings (4) are fixed to the central suspension sling (5), and the lower working ends of the cargo slings (4) is hooked to the rod of the internal retaining lock (7), and the shock control sensor is made of ultrasonic (9) and is connected to the servo mechanism of the lock drive (b) with the help of an electric cable (8).

Internal front (2) and rear (3) loops are attached to the fuselage of the UAV (1) (Fig. 1) from the inside, through which the slings are passed and which are sling-conducting and at the same time sling-retaining. Two front and two rear cargo slings (4) are passed through their holes, and their lower working ends are hooked to the rod of the internal retaining lock (7). The upper ends of the front and rear cargo slings (4) are inseparably attached to the central suspension sling (5). A servomechanism drive (6) is installed to actuate the rod of the internal retaining lock (7). The drive of the servomechanism of the retaining lock (7) is connected by an electric cable (8) to the ultrasonic sensor (9).

The ultrasonic sensor (9) (Fig. 2) is installed together with the corresponding controller on the descent control board (10) in the tail part of the UAV.

During the operation of the ultrasonic sensor (9) (emission and reception of an ultrasonic signal reflected from the ground), a control signal occurs, which, after appropriate processing in the controller, taking into account the required height of operation above the ground (precession), rearranges the lever of the servo mechanism (6) together with the lock rod (7) to the position of unhooking the parachute.

Fig. 3 shows a view of the device for automatic release of the parachute after landing the UAV; the internal retaining lock (7) is in the open state, the lower working ends of the front and rear cargo lines (11) are released from the lock, and the upper ends of the cargo lines (12) together with the central suspension line (5) are sagging, which is a sign of "fading" of the dome the parachute is on the ground and the parachute makes it possible to refill it.

Sources of information: 1. pnr:Loruaggi/29512-Briaogtriieg.piti 2. pErulimly ai. co. P/2013/36720-ep/Vyvipe55Ageaz. OptappedAigZuzietv. avrh 3. pearls agadapiu.sot/ 4. pnr/rr-ia.gy/oria-opap-10/ 5. ppr/Lymlu.eti-rep2grego de/rgodikov/dgoppepzuzivt/5regiiKaiopep.piti 6. Optappea Aegia! Mepisie5 apa Tagdeiv. IN5 dapiev. INZ Spobai Gitiea 2010. p. 21,100,101 7. Patent MLMO2007086055 (JSC), IPC B63835/52; B64C39/02; B64017/80; Vb4E1/02, publ.

Claims (1)

02.08.2007. UTILITY MODEL FORMULA A device for automatic release of a parachute from a UAV, equipped with a parachute, a retaining lock, a servo drive mechanism for the lock, loops through which the slings are passed and a shock sensor 25, which is connected through a communication channel to the descent control board, which supplies an impulse to servo mechanism of the lock drive, which is distinguished by the fact that the retaining lock is located in the fuselage, two front and two rear internal hinges, which are located in pairs and symmetrically on both sides in the fuselage, through the holes of which are passed and the lower working ends are engaged with the stem of the internal retaining lock and two forward cargo lines of the parachute, Zo, with the upper ends of the cargo lines attached to the central suspension line, and the lower working ends of the cargo lines hooked to the rod of the internal retaining lock, and the impact control sensor is made of ultrasonic and which is connected to the servo mechanism of the lock drive by means of an electric cable . and oh I and. Ж Wo w she z z v NN nn NI I SHO shi en UVO ee z u dennia Sp nn nn yi ben rt dit se Pina non i, y she iya t shk i dya Fig. 1 y y TY ko i - still oo - iz h y N ooo nny nn NNI Ok She y I is K odn K KE i y en y MN i in oho V i in TLUMU Kz h she 0 still drink y y di y OZ pi dni I U already a zzhe tt x Pk NN x h i de tower oi: u diddlpd kN ut men she Her one diet deya Fig. и: и also и: in VZ. g ne PASM s KO g: y Tu t s i KV that b i ih Shina | y dity vvazo y I y Bony oon shin nn y V VC zh V ES AT ks : ov t gu Vinnyi EE SHKTIDy t KY y KOLI W t U still u TO Zhenya Poitya shi zh Van NU o Z o. melon х че я ше он acts SY and k Ko х. Z: PAM Men o en Y ke OH ko NI ne po A stalsyyutii V j o i s J Ye re rei Kaya u shk song V. o i u What Ekran dah Y koki Still VYAKOYUY MO soline jo I'M FROM