CN113022897A - Low-impact parachute opening device for recovering fairing - Google Patents
Low-impact parachute opening device for recovering fairing Download PDFInfo
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- CN113022897A CN113022897A CN202110158357.2A CN202110158357A CN113022897A CN 113022897 A CN113022897 A CN 113022897A CN 202110158357 A CN202110158357 A CN 202110158357A CN 113022897 A CN113022897 A CN 113022897A
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- 238000000926 separation method Methods 0.000 claims abstract description 12
- 238000010008 shearing Methods 0.000 claims description 16
- 238000009413 insulation Methods 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000010304 firing Methods 0.000 claims 2
- 239000011810 insulating material Substances 0.000 claims 1
- 230000000452 restraining effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 description 10
- 230000008569 process Effects 0.000 description 8
- 239000012774 insulation material Substances 0.000 description 5
- 239000002360 explosive Substances 0.000 description 3
- 230000000977 initiatory effect Effects 0.000 description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 238000004401 flow injection analysis Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
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- 238000011105 stabilization Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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Abstract
The invention relates to a low-impact parachute opening device for rocket fairing recovery, which comprises a parachute, a parachute-launching rocket, a parachute cabin structure, a connecting belt, a separable electric connector, an ignition cable, a connecting rope and the parachute cabin structure; before working, the parachute launching rocket and the parachute are constrained inside the parachute cabin structure, the parachute launching rocket is connected with the parachute bag through a connecting belt, the parachute canopy is constrained inside the parachute bag and is not fixedly connected with the parachute bag, one end of the parachute canopy is connected with the parachute canopy, and the other end of the parachute canopy is fixedly connected with the parachute cabin structure; one end of the parachute launching rocket is connected with the cabin cover, the other end of the parachute launching rocket is provided with a pin shaft and an electric igniter, the pin shaft is connected with the parachute bag through a connecting belt, the electric igniter is connected with one end of an ignition cable, the other end of the ignition cable is connected with a separable electric connector plug, a separable electric connector socket is fixedly arranged on the parachute cabin structure, and the parachute cabin structure is fixed on the fairing base; meanwhile, the parachute-launching rocket is fixedly connected with the separation plug end of the separable electric connector through a connecting rope.
Description
Technical Field
The invention relates to a device for parachute opening of a fairing of a carrier rocket, and belongs to the field of spacecraft recovery systems.
Background
In recent years, the recovery of the carrier separated materials including the fairing, the booster and the sub-class becomes a research hotspot at home and abroad, and the difficulty of the recovery of the fairing is as follows: the fairing is of a thin shell structure, the strength is low, the appearance is irregular, the reentry process is uncontrolled flight, and angular velocity still exists at the moment of parachute opening; the parachute can be rapidly unfolded outside the fairing influence area, and the parachute with the angular speed of more than 15 square meters can be rapidly unfolded to effectively brake the angular speed of the fairing body, otherwise the parachute is easily wound with the fairing. This requires both the use of a parachute with a large area and a high parachute pull-out speed.
The recovery system often uses the initiating explosive device as an actuating mechanism for parachute opening, and the parachute is quickly ejected by the initiating explosive ejector generally, for example, if the parachute of the scale is directly ejected by the traditional ejector, great recoil can be generated, and the fairing is damaged; if a small guide umbrella is ejected to pull out a large umbrella, the umbrella opening speed is reduced, and the risk of winding with the fairing is increased.
Disclosure of Invention
The technical problem solved by the invention is as follows: overcome the not enough of current catapult pop out the parachute package technique, provide an parachute opening device for rocket radome fairing is retrieved, can realize that the great large-scale parachute reliably pulls out fast, the aerodynamic force that the parachute of this scale produced can make the radome fairing gesture rapid stabilization, and the parachute opening device can not threaten radome fairing structural strength simultaneously, effectively improves and retrieves the success rate.
The technical scheme of the invention is as follows: an parachute opening device for recovering rocket cowling comprises a parachute, a parachute-shooting rocket, a parachute cabin structure, a connecting belt, a separable electric connector, an ignition cable, a connecting rope and the parachute cabin structure;
before the parachute opening device works, the parachute launching rocket and the parachute are constrained inside the parachute cabin structure, the parachute launching rocket is connected with the parachute bag through a connecting belt, the parachute canopy is constrained inside the parachute bag and is not fixedly connected with the parachute bag, one end of the parachute canopy is connected with the parachute canopy, and the other end of the parachute canopy extends out of the parachute cabin and is fixedly connected with the fairing base; one end of the parachute launching rocket is connected with the cabin cover, the other end of the parachute launching rocket is provided with a pin shaft and an electric igniter, the pin shaft is connected with the parachute bag through a connecting belt, the electric igniter is connected with one end of an ignition cable, the other end of the ignition cable is connected with a separable electric connector plug, a separable electric connector socket is fixedly arranged on the parachute cabin structure, and the parachute cabin structure is fixed on the fairing base; meanwhile, the parachute launching rocket is fixedly connected with a separation plug end of the separable electric connector through a connecting rope;
when the parachute opening device works, the ignition cable supplies power to an igniter of the parachute-launching rocket, the parachute-launching rocket is ignited to generate thrust, the shearing pin is cut off, the restraint of the structure of the parachute cabin is broken, the parachute cabin flies out, when the connecting band is straightened, the parachute-launching rocket drives the parachute bag to fly out of the parachute cabin together, the parachute rope and the parachute canopy are pulled out step by step, the parachute is opened, and then the parachute drives the fairing to fly through the hanging band connecting point on the fairing.
Preferably, the parachute opening device for rocket fairing recovery further comprises a through cable, wherein one end of the through cable is connected with an external power supply device, the other end of the through cable is led into the interior of the parachute cabin structure through an opening in the side wall of the parachute cabin structure, and the through cable is connected with the separable electric connector plug and is in butt joint with the ignition cable.
Preferably, the umbrella cabin structure comprises a cabin cover, an inner cylinder, an outer cylinder, a guide cylinder and a bottom plate;
the inner cylinder, the outer cylinder and the guide cylinder are cylindrical cylinders with openings at two ends, one end of the outer cylinder and the bottom plate are jointly fixed on a base of the fairing, the other end of the outer cylinder covers the hatch cover, the inner cylinder is positioned in the outer cylinder, one end of the inner cylinder is fixed on the bottom plate, the other end of the inner cylinder is suspended, the parachute is positioned between the inner cylinder and the outer cylinder, the guide cylinder is positioned in the inner cylinder, one end of the guide cylinder is fixed on the bottom plate, the other end of the guide cylinder is suspended, the hatch cover is fixedly connected to the top of the parachute-shooting rocket, the upper part of the parachute-shooting rocket is fixed on the inner cylinder through N shearing pins, axial constraint of the parachute-shooting rocket is achieved; the parachute-shooting rocket is restrained and fixed together through a shearing pin on the inner cylinder and the guide cylinder, the parachute is restrained together through the inner cylinder, the outer cylinder and the cabin cover, and N is larger than or equal to 1.
Preferably, the parachute launching rocket is concentrically mounted with the inner barrel and the outer barrel.
Preferably, the maximum thrust of the parachute-launching rocket is less than 5kN, so that the load for separating the parachute from the fairing does not exceed 5 kN.
Preferably, the outer surfaces of the outer barrel and the hatch cover are covered with heat insulation materials for preventing the heat of the reentry heat flow from heating the hatch cover and the parachute launching rocket.
Preferably, a layer of heat insulation material is arranged between the hatch cover and the parachute to prevent the parachute from being damaged due to wake jet of the parachute-launching rocket.
The parachute opening device for rocket fairing recovery further comprises a socket mounting plate, and the separable connector is fixed through the socket mounting plate located on the inner side of the guide cylinder.
The constraint force provided by the N shear pins can reliably bear the mechanical environment of launching and reentry of the fairing and is smaller than the initial thrust peak value of the rocket during working, so that the shear pins can be reliably cut off after the rocket is ignited and fly out of the inner cylinder.
The umbrella-shooting rocket is connected with the connecting belt through a pin.
Compared with the prior art, the invention has the beneficial effects that:
(1) the parachute opening device integrates the structures of the parachute, the parachute launching rocket and the parachute cabin into one device, the parachute opening load is far lower than the impact load of the traditional catapult to the fairing, the first-stage parachute with larger size can be rapidly unfolded after the parachute opening device works, the attitude stability of the fairing is realized, and the recovery success rate is effectively improved;
(2) the guide cylinder assists the shear pin to restrain the parachute-launching rocket, so that the bearing state of the shear pin can be optimized, the bearing capacity of the whole device to the mechanical environment in the takeoff process is improved, and the movement state of the parachute-launching rocket relative to the fairing is more stable;
(3) the parachute launching rocket and the parachute are concentrically arranged, so that the posture stability of the parachute launching rocket in the parachute pulling process is facilitated, and the threat of aerodynamic heat to the parachute launching rocket in the reentry process is prevented;
(4) the device can be assembled into an assembly before being butted with the fairing, has simple interface with the fairing and low requirement on installation matching, and is beneficial to the optimization of the whole rocket assembly process.
Drawings
FIG. 1 is a cross-sectional view of an parachute opening device for rocket fairing recovery in accordance with an embodiment of the present invention;
the various components in the figures are numbered as follows:
the parachute comprises an outer heat insulation layer 1, a cabin cover 2, a shear pin 3, an inner heat insulation layer 4, a parachute pack 5, a parachute-shooting rocket 6, an outer cylinder 7, an inner cylinder 8, a guide cylinder 9, an ignition cable 10, a connecting band 11, a connecting rope 12, a socket mounting plate 13, a transfer cable 14 and a bottom plate 15, wherein the outer heat insulation layer 2 is a cabin cover, the shear pin 3 is a shear pin, the inner heat insulation layer 4 is an inner heat insulation layer, the parachute pack 5 is a parachute-;
FIG. 2 is a top view of the parachute opening device for rocket fairing recovery of the embodiment of the invention after sequence parts 1-5 are removed;
FIG. 3 shows a deployed state of an parachute opening device for rocket fairing recovery according to an embodiment of the invention.
Detailed Description
The invention is further illustrated by the following examples.
As shown in figure 1, the parachute device for recovering the rocket fairing provided by the invention comprises a parachute, a parachute-launching rocket, a parachute cabin structure, a connecting belt, a separable electric connector, an ignition cable, a connecting rope, a parachute cabin structure and other parts.
Before the parachute opening device works, the parachute launching rocket and the parachute are constrained inside the parachute cabin structure, the parachute launching rocket is connected with the parachute bag through a connecting belt, the parachute canopy is constrained inside the parachute bag and is not fixedly connected with the parachute bag, one end of the parachute canopy is connected with the parachute canopy, and the other end of the parachute canopy extends out of the parachute cabin and is fixedly connected with the fairing base; one end of the parachute launching rocket is connected with the cabin cover, the other end of the parachute launching rocket is provided with a pin shaft and an electric igniter, the pin shaft is connected with the parachute bag through a connecting belt, the electric igniter is connected with one end of an ignition cable, the other end of the ignition cable is connected with a separable electric connector plug, a separable electric connector socket is fixedly arranged on the parachute cabin structure, and the parachute cabin structure is fixed on the fairing base; meanwhile, the parachute-launching rocket is fixedly connected with the separation plug end of the separable electric connector through a connecting rope.
When the parachute opening device works, the ignition cable supplies power to an igniter of the parachute-launching rocket, the parachute-launching rocket is ignited to generate thrust, the shearing pin is cut off, the restraint of the structure of the parachute cabin is broken, the parachute cabin flies out, when the connecting band is straightened, the parachute-launching rocket drives the parachute bag to fly out of the parachute cabin together, the parachute rope and the parachute canopy are pulled out step by step, the parachute is opened, and then the parachute drives the fairing to fly through the hanging band connecting point on the fairing.
Preferably, the parachute opening device for rocket fairing recovery further comprises a patch cable, wherein one end of the patch cable is connected with an external power supply device, the other end of the patch cable is led into the interior of the parachute cabin structure through the opening of the side wall of the parachute cabin structure, and the patch cable is connected with the separable electric connector plug and is in butt joint with the ignition cable.
The parachute, the parachute-launching rocket and the parachute cabin are integrated into a device, the parachute opening load is far lower than the impact load of a traditional catapult to the fairing, the first-stage parachute with larger size can be rapidly unfolded after working, the fairing posture is stable, and the recovery success rate is effectively improved.
As shown in fig. 2, the umbrella cabin structure comprises a cabin cover, an inner cylinder, an outer cylinder, a guide cylinder and a bottom plate; the outer cylinder, the inner cylinder and the guide cylinder are concentric cylindrical metal structural members, and the diameter of the outer cylinder is larger than that of the inner cylinder and is larger than that of the guide cylinder.
The inner tube, the urceolus, the guide cylinder is both ends open-ended cylinder tube-shape, urceolus one end is fixed on the base of radome fairing jointly with the bottom plate, the other end covers the hatch cover, the inner tube is located inside the urceolus, one end is fixed on the bottom plate, the other end is unsettled, space between urceolus and the inner tube is used for holding the parachute, the parachute is between inner tube and urceolus, the guide cylinder is located inside the inner tube, one end is fixed on the bottom plate, the other end is unsettled, penetrate umbrella rocket top fixed connection hatch cover, upper portion is fixed on the inner tube through N shearing round pin, fix on the inner tube through shearing. The lower part of the parachute launching rocket extends into the guide cylinder and is in clearance fit with the guide cylinder but is not connected with the guide cylinder, and the guide cylinder is used for assisting the shearing pin to realize radial constraint of the parachute launching rocket and limiting the degree of freedom of the parachute launching rocket in the radial direction; the parachute-shooting rocket is restrained and fixed together through a shearing pin on the inner cylinder and the guide cylinder, the parachute is restrained together through the inner cylinder, the outer cylinder and the cabin cover, and N is larger than or equal to 1.
Preferably, the parachute launching rocket is concentrically mounted with the inner barrel and the outer barrel.
Preferably, the maximum thrust of the parachute-launching rocket is less than 5kN, so that the load for separating the parachute from the fairing does not exceed 5 kN.
Preferably, the outer surfaces of the outer barrel and the hatch cover are covered with flexible heat insulation materials, and the outer heat insulation layers are outer heat insulation layers and are used for preventing heat of re-entering heat flow from heating the hatch cover and the parachute launching rocket. Preferably, a layer of flexible heat insulation material is arranged between the hatch cover and the parachute, and is an inner heat insulation layer, so that the parachute damage caused by wake flow injection of the parachute-shooting rocket is prevented.
Preferably, the parachute opening device for rocket fairing recovery further comprises a socket mounting plate, and the separable connector is fixed by the socket mounting plate located inside the guide cylinder.
The fairing takes off, and the reentry process has complex mechanics and temperature environment, needs the device reliably to install, and the rocket can fly away from the fairing fast and pull out the parachute after receiving the work order. Therefore, as a preferable scheme, the constraint force provided by the N shear pins together can reliably bear the mechanical environment of launching and reentry of the fairing and is smaller than the initial thrust peak value of the rocket during working, so that the shear pins can be reliably sheared and fly out of the inner cylinder after the rocket is ignited.
Preferably, the parachute launching rocket is connected with the connecting band through a pin.
Compared with the traditional fire catapult, the catapult has the following biggest difference in the aspects that: the agent of the ejection type initiating explosive device burns fast, can produce instant big thrust to make the parachute package obtain an initial velocity, and the reaction force of thrust then acts on the recovery thing, and the agent that the parachute-shooting rocket used burns slowly, and thrust duration is long to directly act on the parachute package, make the parachute package accelerate away from the zero speed for the recovery thing.
Example (b):
the invention provides an umbrella opening device for recovering rocket cowling, which comprises an outer heat insulation layer 1, a hatch cover 2, a shearing pin 3, an inner heat insulation layer 4, a parachute pack 5, a parachute launching rocket 6, an outer cylinder 7, an inner cylinder 8, a guide cylinder 9, an ignition cable 10, a connecting band 11, a connecting rope 12, a socket mounting plate 13, a transfer cable 14 and a bottom plate 15.
The device is connected with the fairing cover body through screw holes of a bottom plate 15 and an outer cylinder 7, an inner cylinder 8 is arranged on the inner side of an outer cylinder 9, and a guide cylinder 9 is arranged on the inner side of the inner cylinder 8 and is connected with the bottom plate 15 through screws; the parachute pack 5 is arranged between the inner cylinder 8 and the outer cylinder 7 and is connected with a pin at the bottom of the parachute-shooting rocket 6 through a connecting band 11, the parachute-shooting rocket 6 is arranged on the inner side of the inner cylinder 8, the upper part of the parachute-shooting rocket is fixedly connected with the cabin cover 2 and then fixed with the inner cylinder 8 through the shearing pin 3, and the lower part of the parachute-shooting rocket realizes radial restraint through the guide cylinder 9; the outer cylinder 7, the inner cylinder 8 and the guide cylinder 9 are all fixed on the bottom plate 15 through screws; the parachute-launching rocket 6 is ignited through an ignition cable 10 and a switching cable 14, and a separable electric connector is arranged between the ignition cable 10 and the switching cable 14.
Fig. 1 shows a state in which the present invention is fixed to a cowl. Wherein, the outer heat insulation layer 1 is fixed on the upper surface of the hatch cover 2 in a binding mode, the hatch cover 2 is fixed with the inner cylinder 6 through a shear pin, one end of the parachute-shooting rocket 6 is fixedly connected with the hatch cover 2 through a screw, the other end of the parachute-shooting rocket realizes radial constraint through the guide cylinder 9, and the axial direction is free of constraint; one end of an ignition cable 10 is connected with an igniter of the parachute-launching rocket 6, and the other end of the ignition cable is a separation plug and is butted with a separation socket of the adapter cable 14; the separation plug is connected with a pin at the bottom of the parachute-launching rocket 6 through a connecting rope 12, and the separation socket is fixed on a socket mounting plate 10 on the inner side of the guide cylinder 7; the parachute pack 5 is of an annular structure, is arranged between the inner cylinder 8 and the outer cylinder 7 and is connected with a pin at the bottom of the parachute shooting rocket 4 through a connecting belt 11, and the inner heat insulation layer 4 is arranged between the upper part of the parachute pack 3 and the hatch cover; the inner cylinder 8 and the guide cylinder 9 are fixed on the bottom plate 15, and the bottom plate 15 and the outer cylinder 7 are connected with the fairing body together through screw holes.
FIG. 2 is a top view of the parachute opening apparatus for rocket fairing recovery after removing the sequence parts 1-5; as can be seen from fig. 2, the parachute-launching rocket and the parachute adopt a concentric layout mode.
FIG. 3 shows the state that the parachute-launching rocket 6 of the present invention is pulled straight the connecting band 11 and starts to pull the parachute pack 5 after working, at this time, the shear pin connecting the hatch 2 and the inner cylinder 8 is cut off, and in the rocket motion process, the connecting rope 12 for pulling off the separation plug is pulled straight before the ignition cable 10, so that the separation plug of the ignition cable and the separation socket of the adapting cable 14 can be ensured to be pulled off reliably by the parachute-launching rocket 6; as the parachute-launching rocket 6 continues to move, the inner heat insulation layer 4 is sleeved on the towing belt of the parachute pack 3 under the action of inertia.
4 nozzles are arranged at one end close to the hatch cover, after ignition, the propelling force of the 4 nozzles causes the shearing pin to be sheared off and the separable electric connector to be separated, thereby removing all constraints and flying away from the cover body; after the connecting belt 11 is straightened, the parachute bag 5 is carried to fly away from the cover body, and the parachute cord canopy is gradually pulled out to finish the parachute opening. In the whole working process, only when the shear pin is removed, a load equivalent to the propelling force of the fairing is generated, and the fairing cannot be damaged mechanically. The parachute launching rocket is provided with two constraints, one constraint is provided with 4 shear pins, and the other constraint is provided with a cable; the restraint of the shear pin is released by the thrust shear and the restraint of the cable is released by the separable electrical connector.
In this embodiment, the flexible thermal insulation material is alumina fiber wrapped by aramid silk, and the thickness of the alumina fiber is 15 mm.
In the embodiment, the bearing shearing force of a single shearing pin is not less than 750N, 4 parachutes which are used for a 15 square meter (the weight of which is 6kg) of a fairing of a carrier rocket can be used at the same time, the parachute can be opened within 1s, the load generated on the fairing is not more than 5kN, and if the catapult is used as a power source and reaches the same parachute opening speed, the recoil of the fairing reaches 50kN, and compared with the load generated on the fairing, the load is reduced by about 90%; therefore, the parachute-opening impact load recovery device can be used for recovering the fairing with weaker bearing capacity, can realize quick parachute opening of a larger parachute while effectively controlling parachute-opening impact load, and has outstanding advantages in dealing with the problem that the posture is unstable when the fairing is recovered.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. An parachute opening device for recovering rocket fairings is characterized by comprising a parachute, a parachute-shooting rocket, a parachute cabin structure, a connecting belt, a separable electric connector, an ignition cable, a connecting rope and the parachute cabin structure;
before the parachute opening device works, the parachute launching rocket and the parachute are constrained inside the parachute cabin structure, the parachute launching rocket is connected with the parachute bag through a connecting belt, the parachute canopy is constrained inside the parachute bag and is not fixedly connected with the parachute bag, one end of the parachute canopy is connected with the parachute canopy, and the other end of the parachute canopy extends out of the parachute cabin and is fixedly connected with the fairing base; one end of the parachute launching rocket is connected with the cabin cover, the other end of the parachute launching rocket is provided with a pin shaft and an electric igniter, the pin shaft is connected with the parachute bag through a connecting belt, the electric igniter is connected with one end of an ignition cable, the other end of the ignition cable is connected with a separable electric connector plug, a separable electric connector socket is fixedly arranged on the parachute cabin structure, and the parachute cabin structure is fixed on the fairing base; meanwhile, the parachute launching rocket is fixedly connected with a separation plug end of the separable electric connector through a connecting rope;
when the parachute opening device works, the ignition cable supplies power to an igniter of the parachute-launching rocket, the parachute-launching rocket is ignited to generate thrust, the shearing pin is cut off, the restraint of the structure of the parachute cabin is broken, the parachute cabin flies out, when the connecting band is straightened, the parachute-launching rocket drives the parachute bag to fly out of the parachute cabin together, the parachute rope and the parachute canopy are pulled out step by step, the parachute is opened, and then the parachute drives the fairing to fly through the hanging band connecting point on the fairing.
2. The parachute opening device for rocket fairing recovery as recited in claim 1, further comprising a patch cable having one end connected to an external power supply and the other end leading into the interior of the parachute bay structure through an opening in the sidewall of the parachute bay structure, wherein the patch cable is connected to the separable electrical connector plug and mated to the firing cable.
3. An parachute opening device for rocket fairing recovery as recited in claim 1, wherein said parachute bay structure comprises a bay cover, an inner barrel, an outer barrel, a guide barrel, and a base plate;
the inner cylinder, the outer cylinder and the guide cylinder are cylindrical cylinders with openings at two ends, one end of the outer cylinder and the bottom plate are jointly fixed on a base of the fairing, the other end of the outer cylinder covers the hatch cover, the inner cylinder is positioned in the outer cylinder, one end of the inner cylinder is fixed on the bottom plate, the other end of the inner cylinder is suspended, the parachute is positioned between the inner cylinder and the outer cylinder, the guide cylinder is positioned in the inner cylinder, one end of the guide cylinder is fixed on the bottom plate, the other end of the guide cylinder is suspended, the hatch cover is fixedly connected to the top of the parachute-shooting rocket, the upper part of the parachute-shooting rocket is fixed on the inner cylinder through N shearing pins, axial constraint of the parachute-shooting rocket is achieved; the parachute-shooting rocket is restrained and fixed together through a shearing pin on the inner cylinder and the guide cylinder, the parachute is restrained together through the inner cylinder, the outer cylinder and the cabin cover, and N is larger than or equal to 1.
4. An parachute opening apparatus for rocket fairing recovery as recited in claim 3, wherein said parachute-launching rocket is mounted concentrically with the inner and outer barrels.
5. An parachute opening apparatus for rocket fairing recovery as recited in claim 1, wherein said parachute-launching rocket has a maximum thrust of less than 5kN, such that parachute-fairing separation loads do not exceed 5 kN.
6. The parachute opening device for rocket fairing recovery as recited in claim 1, wherein the outer surface of the outer barrel and the hatch cover is covered with a heat insulating material for preventing the re-entering heat flow from heating the hatch cover and the rocket for launching the parachute.
7. The parachute apparatus of claim 1, wherein a layer of thermal insulation is disposed between the canopy and the parachute to prevent damage to the parachute caused by wake jet of the rocket launching the parachute.
8. An parachute opening device for rocket fairing recovery as recited in claim 1, further comprising a socket mounting plate, wherein said separable connector is secured by the socket mounting plate inside the guide tube.
9. The parachute opening device for rocket fairing recovery as recited in claim 1, wherein the N shear pins together provide a restraining force capable of reliably bearing the mechanical environment of fairing launch and reentry, and less than the initial thrust peak value of the rocket during operation, so that the rocket after firing can reliably shear the shear pins and fly out of the inner barrel.
10. An umbrella unfolding apparatus for rocket fairing recovery as recited in claim 1, wherein said parachute-launching rocket is pinned to said attachment straps.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110158357.2A CN113022897A (en) | 2021-02-04 | 2021-02-04 | Low-impact parachute opening device for recovering fairing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110158357.2A CN113022897A (en) | 2021-02-04 | 2021-02-04 | Low-impact parachute opening device for recovering fairing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319866A (en) * | 2020-07-16 | 2021-02-05 | 西安航天化学动力有限公司 | Piston type recovery device of civil rocket |
| CN113720570A (en) * | 2021-08-30 | 2021-11-30 | 航宇救生装备有限公司 | Rocket sled pneumatic brake system suitable for high mach |
| CN114180107A (en) * | 2021-12-07 | 2022-03-15 | 北京空间机电研究所 | Heat-insulation-prevention speed reducing umbrella cabin device for fairing parachute recovery |
| CN114194419A (en) * | 2021-11-29 | 2022-03-18 | 北京空间机电研究所 | Parachute system suitable for carrier rocket radome recovery |
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|---|---|---|---|---|
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319866A (en) * | 2020-07-16 | 2021-02-05 | 西安航天化学动力有限公司 | Piston type recovery device of civil rocket |
| CN113720570A (en) * | 2021-08-30 | 2021-11-30 | 航宇救生装备有限公司 | Rocket sled pneumatic brake system suitable for high mach |
| CN114194419A (en) * | 2021-11-29 | 2022-03-18 | 北京空间机电研究所 | Parachute system suitable for carrier rocket radome recovery |
| CN114180107A (en) * | 2021-12-07 | 2022-03-15 | 北京空间机电研究所 | Heat-insulation-prevention speed reducing umbrella cabin device for fairing parachute recovery |
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Application publication date: 20210625 |