EP2119998A1 - Système de lancement - Google Patents

Système de lancement Download PDF

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Publication number
EP2119998A1
EP2119998A1 EP08275016A EP08275016A EP2119998A1 EP 2119998 A1 EP2119998 A1 EP 2119998A1 EP 08275016 A EP08275016 A EP 08275016A EP 08275016 A EP08275016 A EP 08275016A EP 2119998 A1 EP2119998 A1 EP 2119998A1
Authority
EP
European Patent Office
Prior art keywords
mortar
cap
uav
projectile
diagram
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP08275016A
Other languages
German (de)
English (en)
Inventor
designation of the inventor has not yet been filed The
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
BAE Systems PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by BAE Systems PLC filed Critical BAE Systems PLC
Priority to EP08275016A priority Critical patent/EP2119998A1/fr
Priority to EP09746104A priority patent/EP2276994B1/fr
Priority to PL09746104T priority patent/PL2276994T3/pl
Priority to PCT/GB2009/050507 priority patent/WO2009138787A1/fr
Priority to AT09746104T priority patent/ATE537419T1/de
Priority to US12/992,506 priority patent/US8584985B2/en
Priority to BRPI0912709A priority patent/BRPI0912709A2/pt
Priority to CA2723964A priority patent/CA2723964A1/fr
Priority to AU2009247788A priority patent/AU2009247788B2/en
Priority to ES09746104T priority patent/ES2378879T3/es
Publication of EP2119998A1 publication Critical patent/EP2119998A1/fr
Priority to ZA2010/08021A priority patent/ZA201008021B/en
Priority to IL209245A priority patent/IL209245A0/en
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/045—Rocket or torpedo launchers for rockets adapted to be carried and used by a person, e.g. bazookas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41B—WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE OR COMBUSTIBLE PROPELLANT CHARGE; WEAPONS NOT OTHERWISE PROVIDED FOR
    • F41B3/00—Sling weapons
    • F41B3/02—Catapults, e.g. slingshots

Definitions

  • the present invention relates to a launch system for air vehicles. More specifically, the present invention relates to launching unmanned air vehicles (UAVs) that are unable to be launched by hand.
  • UAVs unmanned air vehicles
  • the present invention provides an apparatus for launching an unmanned air vehicle, comprising a mortar launcher, a mounting means for mounting an unmanned air vehicle on said mortar launcher; a cap comprising a mating surface suitable for mating with the head of a mortar round; wherein the cap is connected with a bungee rope to an unmanned air vehicle.
  • An advantage of the present invention is that mortars are eminently portable and are readily available in most armed forces, so the invention allows a launch system compatible with equipment readily available already.
  • the base 10 of the mortar launcher to which one end, the fixed end, of the mortar launcher tube 50 is hingedly fixed, is put in position on the ground at the desired launch site.
  • the fixed end is a closed end of the mortar tube 50.
  • the mortar launcher tube's other end, the free end is supported by a stand 60 that rests on the ground and thus supports the end of the tube 50.
  • the free end of the mortar tube 50 is open, allowing a fin-stabilised mortar 80 to be inserted into the tube 50 and to exit the tube 50 when launched.
  • the UAV 20 is mounted on takeoff runners 30 that are formed on top of the mortar launcher tube 50 in this embodiment, using a custom latch 100 to only release the UAV 20 when it is moving in the correct direction. It should be noted that alternative arrangements are possible for how the UAV 20 is mounted on the mortar launcher tube 50 and these are discussed below.
  • the engine of the UAV 20 is started at this point, so that when the launch is complete it can continue flying, while the mortar round 80 will drop to the ground.
  • a mortar round 80 is placed in the free end of the mortar launcher tube 50 and held in place by a standard issue slipper plate 110.
  • the slipper plate 110 is connected to a pull chord 70 with a pin.
  • a cap 90 is placed over the free end, or muzzle, of the mortar launcher tube 50 and the slipper plate 110.
  • One end of a bungee rope 40 is attached to the cap 90.
  • the other end of the bungee rope 40 is attached to a hook 120 underneath the nose of the UAV 20.
  • the slipper plate 110 is shown in more detail in Figure 26 and can hold a mortar round 80 in place near the muzzle of the mortar launcher tube 50 because each mortar round 80 has two grooves 130, shown in Figure 25 , near the nose end of the mortar round 80 into which the edges of the slipper plate 110 insert, preventing the mortar round 80 moving further into the mortar launcher tube 50 as the slipper plate 110 is larger than the muzzle diameter of the mortar launcher tube 50.
  • FIG. 2 there is shown the apparatus of Figure 1 but now during the first step of operation.
  • the safety chord 70 is pulled by the operator, pulling the slipper plate 110 out of the grooves 130 that hold the mortar round 80 in place at the muzzle of the tube 50, causing the mortar round 80 to drop down the mortar launch tube 50 to the bottom of the mortar launch tube 50 from the top of the mortar launch tube 50.
  • FIG. 3 there is shown the apparatus of Figure 1 during the second step of operation.
  • the firing pin of the mortar charge 80 is triggered when it hits the bottom of the mortar launch tube 50, initiating the propellant and thus the mortar round 80 rapidly accelerates up the mortar launch tube 50.
  • FIG 4 there is shown the apparatus of Figure 1 during the third step of operation.
  • the mortar round 80 hits the cap 90, mating with a contacting face 140 of the cap 90, which is designed to mate with the nose of the mortar round 80.
  • a contacting face 140 of the cap 90 which is designed to mate with the nose of the mortar round 80.
  • FIG. 5 there is shown the apparatus of Figure 1 during the fourth step of operation.
  • the mortar round 80 continues out of the mortar launch tube 50 along with the cap 90, the mortar round 80 having mated with the cap 90.
  • cap 90 is also connected to one end of the bungee rope 40, the other end of the bungee rope 40 being fixed to the nose of the UAV 20, the bungee rope 40 absorbs the initial shock of the mortar launch and starts to stretch between the stationary UAV 20 and the moving mortar round 80.
  • the tension in the bungee rope 40 is sufficient, the bungee rope 40 starts to pull the UAV 20 in the direction of travel of the mortar 80 and cap 90, causing it to gradually accelerate rather than accelerating at the same high acceleration as the mortar round 80.
  • FIG. 6 there is shown the apparatus of Figure 1 during the fifth step of operation.
  • the bungee rope 40 has been extended as far as the respective forces will allow it, so the custom latch 100 releases UAV 20 as enough force is pulling the UAV 20 to allow it to take off and the UAV 20 leaves the takeoff runners 30 with a suitably high acceleration to take off but not with too high an acceleration to cause damage to the UAV 20.
  • FIG. 7 there is shown the apparatus of Figure 1 during the final step of operation.
  • the UAV 20 is travelling under its own propulsion as it is airborne and at a suitable speed to continue flying, while the mortar shell is losing momentum, so the UAV overtakes the mortar 80 and cap 90, causing the bungee rope 40 to come loose around 0.5 seconds after firing the mortar.
  • the bungee rope 40, cap 90 and mortar shell 80 fall to the earth.
  • the hook 120 to which the bungee rope 40 is connected only allows the mortar round 80 to pull the UAV 20, but not to cause drag as once the mortar is no longer pulling the UAV 20 forwards, the ring 150 to which the bungee rope is connected (see Figures 28 and 29 ).
  • two bungee ropes 40 are used and these are mounted on opposite sides of the cap 90 to stabilise the trajectory of the mortar once it mates with the cap 90, and this also prevents the cap 90 rotating in flight.
  • the inside, contacting, face 140 of the cap 90 decreases in diameter from one open end 170 to the other open end 160, so that the mortar round 80 mates with the cap 90 when it is launched as it becomes lodged in the cap 90 when the diameter of the cap 90 decreases to the substantially the diameter of the widest diameter of the mortar shell 80.
  • the bungee ropes are not attached directly to the holes using bolts, as the fin of the mortar round can wear away the bungee ropes 40. Instead, metal rods or wire 190 are bolted to the holes 180 in cap 90 and the bungee ropes are connected to the ends of these rods/wires 190.
  • Figure 27 shows a fin-stabilised mortar 80 as would be suitable for use with the invention once mated with the cap 90.
  • Figures 16 , 17 , 18 , 19 , 20 , 21 , 22 , 23 and 24 show a preferred mounting means that would replace the take-off runners 30 with a stand-alone frame 200 that is positioned above the mortar launcher 50.
  • the frame 200 can be folded to allow it to fit into restricted spaces.
  • the frame 200 is mounted on four telescopic legs 210 (shown in more detail in Figure 22 ), to allow for it to be set up on substantially non-flat surfaces. It has two folding sides 220 (shown in more detail in Figure 23 ) that are folded out in a C shape to provide the largest clearance for a UAV 20 mounted on top of the mortar launcher 50, in order to give maximum clearance for any rear-mounted propellers.
  • Each folding side 220 has a wing-shaped wedge 230 (shown in more detail in Figures 20 and 21 ) mounted roughly centrally that mates with the rear of the each wing of the UAV 20 such that the UAV 20 is supported by its wings on the folding sides and prevented from sliding backwards down the folding sides 220 by the wing-shaped wedges 230 mating with the rear of each wing.
  • Figures 12 to 15 show the frame 200 when arranged over a mortar launcher 50 and with a UAV 20 in place.
  • cap 90 Other forms of cap 90 are conceived, the essential features being a mating surface for the mortar shell 80 and some means by which to connect the bungee rope 40.
  • the bungee rope 40 could be replaced with other means, such as a spring.
  • starting the propulsion means of the UAV 20 before launching it using the method of the invention reduces the force needed to launch the UAV 20, and thus also increases the weight of UAV 20 that it is possible to launch using this method. It is also possible, however, to use this method to launch a UAV 20 without having the propulsion means on until the UAV 20 is in the air.
  • Another means for connecting the bungee rope 40 to the UAV 20 is by use of a glider release latch instead of a hook.
  • Other means are envisaged, including an electronic release mechanism triggered by either a time or by force measurements, but the essential feature is that the release occurs before or at the point when the mortar ceases to pull the UAV 20 forwards and instead acts as drag.
EP08275016A 2008-05-13 2008-05-13 Système de lancement Ceased EP2119998A1 (fr)

Priority Applications (12)

Application Number Priority Date Filing Date Title
EP08275016A EP2119998A1 (fr) 2008-05-13 2008-05-13 Système de lancement
US12/992,506 US8584985B2 (en) 2008-05-13 2009-05-13 Launch system
PL09746104T PL2276994T3 (pl) 2008-05-13 2009-05-13 System wyrzutni
PCT/GB2009/050507 WO2009138787A1 (fr) 2008-05-13 2009-05-13 Système de lancement
AT09746104T ATE537419T1 (de) 2008-05-13 2009-05-13 Abwurfsystem
EP09746104A EP2276994B1 (fr) 2008-05-13 2009-05-13 Système de lancement
BRPI0912709A BRPI0912709A2 (pt) 2008-05-13 2009-05-13 componente conjugado para encaixar com um projétil, e, aparelho e método para lançar um veículo dotado de asa
CA2723964A CA2723964A1 (fr) 2008-05-13 2009-05-13 Systeme de lancement
AU2009247788A AU2009247788B2 (en) 2008-05-13 2009-05-13 Launch system
ES09746104T ES2378879T3 (es) 2008-05-13 2009-05-13 Sistema de lanzamiento
ZA2010/08021A ZA201008021B (en) 2008-05-13 2010-11-09 Launch system
IL209245A IL209245A0 (en) 2008-05-13 2010-11-10 Launch system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08275016A EP2119998A1 (fr) 2008-05-13 2008-05-13 Système de lancement

Publications (1)

Publication Number Publication Date
EP2119998A1 true EP2119998A1 (fr) 2009-11-18

Family

ID=40161001

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08275016A Ceased EP2119998A1 (fr) 2008-05-13 2008-05-13 Système de lancement

Country Status (1)

Country Link
EP (1) EP2119998A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110857146A (zh) * 2018-08-24 2020-03-03 北京理工大学 搭载多架旋翼无人机的运载系统
CN110888461A (zh) * 2019-12-05 2020-03-17 西安毫米波光子科技有限公司 一种舰载小型固定翼无人机起飞姿态调整装置
CN113630131A (zh) * 2021-07-21 2021-11-09 西北工业大学 一种用于水下发射的发射结构及安装方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2748529A (en) * 1953-07-06 1956-06-05 Charles R Swan Toy rocket and parachute
US4410151A (en) * 1979-08-30 1983-10-18 Vereinigte Flugtechnische Werke-Fokker Gmbh Unmanned craft
DE3234351A1 (de) * 1982-09-16 1984-05-17 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Anlassvorrichtung fuer ein propellertriebwerk eines unbemannten flugkoerpers
US4666105A (en) * 1984-10-10 1987-05-19 Messerschmitt-Boelkow-Blohm Gmbh Unmanned aircraft

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2748529A (en) * 1953-07-06 1956-06-05 Charles R Swan Toy rocket and parachute
US4410151A (en) * 1979-08-30 1983-10-18 Vereinigte Flugtechnische Werke-Fokker Gmbh Unmanned craft
DE3234351A1 (de) * 1982-09-16 1984-05-17 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Anlassvorrichtung fuer ein propellertriebwerk eines unbemannten flugkoerpers
US4666105A (en) * 1984-10-10 1987-05-19 Messerschmitt-Boelkow-Blohm Gmbh Unmanned aircraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110857146A (zh) * 2018-08-24 2020-03-03 北京理工大学 搭载多架旋翼无人机的运载系统
CN110888461A (zh) * 2019-12-05 2020-03-17 西安毫米波光子科技有限公司 一种舰载小型固定翼无人机起飞姿态调整装置
CN110888461B (zh) * 2019-12-05 2022-11-22 西安毫米波光子科技有限公司 一种舰载小型固定翼无人机起飞姿态调整装置
CN113630131A (zh) * 2021-07-21 2021-11-09 西北工业大学 一种用于水下发射的发射结构及安装方法

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