RU2070711C1 - High-speed rocket deceleration device - Google Patents

Abstract

FIELD: rocketry, in particular, survival high-speed research rockets, ammunition ejected from air carriers, rocket stages. SUBSTANCE: high-speed rocket deceleration device has the main parachute in a container, initial deceleration device located in the rear part of the container, assemblies for attachment of the main parachute and initial deceleration device - all arranged in tandem i the rocket tail section. The device for attachment of the main parachute is made in the form of a compression spring telescopically installed on the central rod before the parachute container rigidly joined to the rocket body between its rear end shoulder and front bottom enveloping the spring of the sleeve installed in the rocket body and furnished in the rear part with a collet, internal shoulder and bevel engageable with the mating bevel of the external shoulder made in the front part of the main parachute container, installed inside the rocket body and connected to it by a destructible retaining member. Made in the rocket body before the rear end of the sleeve is an internal annular groove, whose width exceeds the length of the sleeve collect section, and the destructible retaining member is installed before the front thrust turn of the spring on the central rod. EFFECT: enhanced reliability. 4 dwg

Description

 The invention relates to the field of rocket technology and can be used in the construction of rescued high-speed research missiles, as well as for braking ammunition, for example, dropped from air carriers at high speeds, or missile stages.

 As a rule, parachute systems are used to rescue such missiles, while ensuring an acceptable parachute launch speed is possible either by turning on the parachute at the point of the trajectory at which the rocket has a velocity of the order of 150-200 m / s, or by aerodynamic braking of the rocket up to the speed that allows the parachute to enter .

 For high-speed, and especially hypersonic missiles, basically the second way is permissible, since under conditions of significant kinetic heating in the flight of the rocket, its flight until it reaches an acceptable speed for launching a parachute, exceeding the conditions for combat use in time, will distort the real picture conditions for the use of nodes and blocks, i.e. untrustworthy information (especially regarding the effect of kinetic heating).

 There are various designs of braking devices for auxiliary missiles with two-stage braking, first using the initial braking device (brake flaps or auxiliary parachute), and then using the main parachute.

 An example of such a device is an auxiliary rocket [1] containing an initial braking device in the form of brake flaps and a main parachute, while the brake flaps, before opening, are part of the rocket glider.

 The disadvantages of this device are the impossibility of using it for high-speed, especially hypersonic, rockets, the glider of which experiences great aerodynamic heating in flight, and, in addition, the need to rescue the entire mass of the rocket, including useless (the first stage of braking, etc.), with a parachute system , which leads to the need to increase the area of the parachute, and this reduces the reliability of the disclosure and, due to the greater windage, increases the drop zone of the salvaged rocket and, accordingly, the search zone.

 To a large extent, these failings are deprived of a fail-safe braking system for a high-speed projectile [2], which is the prototype of the present invention and contains a main parachute located in a container at the rear of the projectile, as well as an initial braking device (auxiliary parachute) located at the rear of the main parachute container. An auxiliary parachute is put into operation at a given moment using a pyrotechnic release device and, when opened, extinguishes the velocity of the projectile to the value necessary for entering the main parachute.

 The input of the main parachute is also carried out after the activation of the pyrotechnic release device. The auxiliary parachute in this case pulls out the main dome, after which it is reset.

 The main disadvantage of the described device is its lack of reliability associated with the use of temporary pyrotechnic devices for decoding the auxiliary and main parachutes, which have a large variation in response time, which at high flight speeds can lead to the introduction of the main parachute at an unacceptably high speed.

 The aim of the invention is to increase reliability by using free-stream energy as the drive for unlocking the main parachute, which automatically unlocks the device when it reaches a certain value.

 To achieve this goal in the known braking device for a high-speed rocket, containing the main parachute in the container tandemly located in the rear part of the rocket and the initial braking device located in the rear of the container, the main parachute fixation-release device is made in the form of a compression spring telescopically mounted in front of the container a parachute made movable and interacting with its front part with the collet part of the cup enclosing the spring held in the original polo destructible locking element, while the spring force at the end of the stroke is chosen equal to the value of the pressure head on the shields at an acceptable speed of parachute insertion.

 This design solution provides increased reliability of rescue by automatically entering the main parachute upon reaching the rocket speed acceptable for the introduction of the parachute.

 Comparison of the claimed technical solution with the prototype made it possible to establish its compliance with the criterion of "novelty." In the study of other well-known technical solutions in this technical field, signs that distinguish the claimed solution from the prototype were not identified, and therefore they provide the claimed technical solution with the criterion of "inventive step".

 In FIG. 1 shows a longitudinal section through a braking device in its initial position; in FIG. 2 is a longitudinal section of the device during operation of the first braking stage; in FIG. 3 is a longitudinal section of the device at the moment of disengagement of the parachute container from the body; in FIG. 4 is a longitudinal section of the device during operation of the main parachute.

 The proposed braking device for a high-speed rocket is located in the rear of the rocket body 1 (Fig. 1) and contains an initial braking device in the form of brake shields 2 pivotally mounted on the container 3 of the main parachute 4 and held in a folded position by a cap 5 fixed on a shear body 1 with a pin 6. In the back of the container 3 in the central socket there is a pusher 7 with a pyro-retarder 8 and a powder hinge 9.

 The front part of the container 3 is provided with a shoulder 10 with a bevel 11 that interacts with the reciprocal bevel of the shoulder 12 of the collet part 13 of the glass 14 with a front bottom 15.

 In the housing 1 of the rocket, the central rod 16 with the rear end collar 17 is rigidly fixed 17. A compression spring 18 is installed between the collar 17 and the front bottom 15 of the cup 14, and a washer 19 is installed between the spring 18 and the bottom 15, covering the shear element 20.

 An annular groove 21 with a length “a” (FIG. 2) of at least the length of the collet portion 13 of the cup 14 is also made in the missile body 1, while the rear end face 22 of the groove is located in front of the rear end face 23 (FIG. 1) of the cup by the length “b”.

 The container 3 is held in the housing 1 by means of fixing balls 24 located in the holes of the shank 25 of the housing 1 and the groove 26 of the container 3 and kept from falling out by the cap 5.

 The dome of the main parachute 4 is placed in the container 3, the top of the dome with thread 27 is screwed to the rear bottom of the container with a screw 28, and the slings 29 are attached to the thimble 30 of the connecting rope 31, the opposite thimble 32 of which is fixed to the rear end of the central rod 16.

 The operation of the device is as follows. When launching a rocket (applying a pulse to the engine’s ignition), a pyro-moderator 8 is simultaneously initiated, the burning time of which is selected from the condition of ensuring the operation of the initial braking device at a given point in time of flight. At the end of the operation of the pyro-moderator, a powder hitch 9 is triggered, and the pusher 10 is thrown out under the action of powder gases in the direction opposite to the direction of rocket movement, dropping the cap 5 (cutting pin 6) and releasing the balls 24 and the brake flaps 2.

 Under the action of the oncoming flow, the shields 2 open (Fig. 2), while under the action of the shields the container 3 moves backward, squeezing the balls 24 by the wall of the groove 26, while the cup 14 moves with the container, cutting the shear element 20 and compressing the spring 18 through the washer 19 , until the rear end of the washer, having selected the gap "in" (Fig. 1, 2), rests against the end "g" of the rod 16.

,
где C_x коэффициент лобового сопротивления щитков;
ρ удельная плотность воздуха;
v текущее значение скорости ракеты;
S_щ суммарная площадь консольной части щитков.The further flight of the rocket takes place with the flaps 2 open (Fig. 2), with the container 3 extended from the rocket casing 1 by an amount “b” relative to the initial position, and pressed as much as possible by a spring 18. In this case, the braking force from the aerodynamic pressure, determined by from the dependence for the drag:

,
where C _{x is the} drag coefficient of the shields;
ρ specific gravity of air;
v current value of the speed of the rocket;
S _u total area of the cantilever part of the flaps.

,
где v_g скорость, допустимая для введения в действие основного парашюта.When the rocket’s speed drops under the action of the braking force, there comes a moment when the force of the most compressed spring 18 begins to exceed the axial force transmitted from the shields to the parachute container, compressing the spring, and it unclenches and acts through the washer 19 on the glass 14, respectively, on the container body moves them forward, while the characteristic of the spring 18 is selected so that its total working stroke h = δ + b, while at the end of the stroke the spring force is provided

,
where v _{g is the} speed allowed for the introduction of the main parachute.

 At the end of the working stroke, the rear end 23 of the cup 14 extends beyond the rear end 22 of the groove 21 (Fig. 3), and the collet part 13 of the cup 14 is able to be squeezed under the action of the bevel 11 of the collar 10 of the container onto the reciprocal bevel of the collar of the collet part 13 from the compressive action of the spring 18 on the glass 14, and from the braking force on the container of the parachute. The container is disconnected from the glass, and the container 3 is ejected from the rocket body under the influence of an aerodynamic load on the guards, while with a thread 27 it pulls the canopy of the parachute 4, slings 29 and the connecting rope 31. Next, the thread 27 breaks and the container 3 is dropped, filling canopy of the parachute and the further launch of the rocket on the main parachute (Fig. 4).

 Thus, in the proposed technical solution, in comparison with the prototype, the canopy of the main parachute is automatically opened when the rocket reaches a speed acceptable for the introduction of the parachute, which increases reliability and ensures the rescue of high-speed missiles.

Information sources
1. Burgess E. Guided jet weapons. M. Foreign Literature, 1958, p. 127.

 2. US patent N 3713387, CL. 102-4, 1973.

 3. Ostoslavsky I.V. Titov V.M. Aerodynamic calculation of the aircraft. Oborongiz, 1947, p. twenty.

Claims (1)

 A device for braking a high-speed rocket, comprising a main parachute in a container arranged in tandem at the rear of the rocket, an initial braking device located on the rear of the container, fixation units for the main parachute and initial braking devices, characterized in that the fixation unit for the main parachute is made in the form of a compression spring, telescopically mounted in front of the parachute container on a central rod rigidly connected to the rocket body between its rear end collar and the front bottom its spring of the cup mounted in the rocket body and provided at the rear with a collet with an inner shoulder and a bevel that interacts with the reciprocal bevel of the outer shoulder made on the front of the main parachute container mounted inside the rocket body and connected to it by a destructible fixing element, while the body the missile is equipped with an inner annular groove made in front of the rear end of the cup, and the width of the groove exceeds the length of the collet part of the cup, and in front of the front supporting coil of the spring a central rod mounted erodible fixing member.

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