WO2000038987A1 - Dispositif de suspension d'une charge utile dans un lanceur spatial - Google Patents
Dispositif de suspension d'une charge utile dans un lanceur spatial Download PDFInfo
- Publication number
- WO2000038987A1 WO2000038987A1 PCT/FR1999/003302 FR9903302W WO0038987A1 WO 2000038987 A1 WO2000038987 A1 WO 2000038987A1 FR 9903302 W FR9903302 W FR 9903302W WO 0038987 A1 WO0038987 A1 WO 0038987A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- stops
- launcher
- hydraulic
- elastic
- pressure
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
-
- 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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2230/00—Purpose; Design features
- F16F2230/18—Control arrangements
Definitions
- the present invention relates to a device for suspending a payload in a launcher of said payload in space and, more particularly, to such a device of the type which comprises means for absorbing forces installed between first and second rigid annular members centered on the longitudinal axis of the launcher and secured respectively to said launcher and to said payload, and to means for controlling said force absorption means adapted to adapt the rigidity of the device to various phases of the flight of the launcher.
- FIG. 1 also shows a payload such as a satellite 4 mounted on a second stage 5 of the launcher, by means of an adapter in the form of a frustoconical skirt 6, the satellite being conventionally protected by a cover 7 during crossing the atmosphere.
- a payload such as a satellite 4 mounted on a second stage 5 of the launcher, by means of an adapter in the form of a frustoconical skirt 6, the satellite being conventionally protected by a cover 7 during crossing the atmosphere.
- the thrusts developed by the auxiliary thrusters 2, 3 apply intense forces to the envelope of the first stage, in particular at the attachment points 8, 9 of the thrusters 2, 3 on the first floor.
- this countermeasure consists in installing a suspension device constituted by an annular chamber with flexible wall, filled with a fluid, between the satellite and the launcher, for example at the level of the large base 6b of the skirt 6, which receives the satellite at its other base 6a.
- the "surge" of forces received by the annular chamber in line with the attachment points 8, 9 are uniformly distributed annularly by the fluid in the chamber, the skirt 6 then undergoing perfectly symmetrical forces which do not asymmetrically deform this skirt. The integrity of the satellite is thus safeguarded during the operation of the auxiliary thrusters 2, 3.
- Means are provided, moreover, for varying the pressure of the fluid contained in the annular chamber.
- this pressure can be lowered by a relatively high value ensuring good mechanical cohesion of the launcher and of the skirt 6, necessary in particular during the operation of the auxiliary thrusters 2, 3, to a lower value making it possible to absorb and to absorb forces such as vibrations or shocks propagating in the launcher, in particular during the separations of the stages of the launcher and of the cover 7.
- the object of the present invention is precisely to produce a device for suspending a payload in a launcher of said payload in space, which does not have these drawbacks and which, in particular, makes it possible to vary the stiffness of this suspension so as to adapt this stiffness to the particular conditions encountered during the successive phases of the flight of the launcher, while having high operating reliability and a moderate cost of production.
- the invention aims to produce such a device capable of having a high stiffness during the ordinary phases of flight of the launcher, capable of giving it good mechanical cohesion, and a lower stiffness during extraordinary phases of this flight, such as those corresponding to the separation of the cover or to the separation of the stages of the launcher, these phases generating shocks and / or vibrations which must be absorbed or damped before their propagation to the satellite.
- a device for suspending a payload in a launcher of said charge in space comprising means force absorbing elastics installed between first and second rigid annular members centered on the longitudinal axis of the launcher and secured respectively to said payload and said launcher, and to means for controlling said elastic force absorption means capable of adapting the rigidity of the device to various phases of the flight of the launcher, this device being remarkable in that said control means comprise at least a plurality of hydraulic stops each arranged axially between said first and second rigid annular members, said stops being movable at least between a first position or they rigidly couple said annular members and a second position wherein said elastic force absorption means are activated.
- the softening thus obtained of the suspension of the payload allows the filtering of the shocks which appear during the extraordinary flight phases mentioned above.
- the stiffness of the suspension device is varied by suitably controlling hydraulic stops of conventional design, the sealing of which can be ensured for a moderate cost, at the level of reliability required in the space industries.
- said elastic force absorption means are constituted by a plurality of elastic stops, said pluralities of elastic and hydraulic stops being nested one inside the other.
- the hydraulic stops are under pressure.
- the control means comprise a circuit for supplying liquid to said hydraulic stops, said circuit comprising a cylinder making it possible to selectively vary the pressure of said liquid between at least first and second values controlling the positioning of the stops. hydraulic in their first and second positions, respectively.
- FIG. 1 schematically represents part of a satellite launcher of the prior art, described in the preamble to this description,
- FIG. 2 is a schematic plan view of the device according to the present invention.
- FIGS 3A and 3B are views in axial section of an elastic stop forming part of the device of Figure 2, in two different operating states of this stop, - Figure 4 is a view in axial section of a stop hydraulic forming part of the device according to the invention,
- FIG. 5 is a diagram of a circuit for controlling the pressure of the liquid present in the hydraulic stops of the device according to the invention.
- the device according to the invention is arranged at a plane P perpendicular to the axis X of the launcher (see FIG. 1), this mean plane P can be located at any level between the bases 6a and 6b of the skirt 6, advantageously at the base 6b.
- the device generally takes a circular shape. It is essentially composed of first and second annular members superimposed axially, between which are installed a plurality of elastic stops 12 ⁇ and a plurality of hydraulic stops 13j. It is associated with another mechanical device whose structure and functioning are the subject of the French patent application filed today by the applicant and entitled "Device for supporting a payload in a launcher of said payload". We can refer to this request for more details on this device, the function of which is to prevent the transmission to the satellite of the "surges of effort" mentioned in the preamble to this description. It is therefore not, strictly speaking, part of the device according to the present invention which has the function of preventing the transmission to the satellite of shocks or vibrations.
- the distributions of the abovementioned stops are regular and nested one inside the other.
- FIGS 3A, 3B and 4 which respectively represent partial views in axial section of the device according to the invention, taken along the section lines III and IV of Figure 2, passing through an elastic stop 12 ⁇ and a hydraulic stop 13 ⁇ , respectively, it being understood that the other stops of the same type are identical to those which we will describe.
- the first and second annular members are referenced 10 and 11, respectively, the annular member 10 being fixed on the skirt 6 secured to the satellite 4 and the annular member 11 on the second stage 5 of the launcher, by circular distributions bolts such as those referenced 15 and 16 respectively.
- the annular member 11 itself comprises first and second annular flanges 17, 18 respectively, secured by bolts such as that referenced 19.
- the first flange 17 takes the form of an axis ring parallel to the axis X of the launcher, this ring extending two axially spaced radial annular flanges, one 17a projecting outward to be crossed by bolts such as that referenced 19, the other 17b being turned inward to be taken in an annular groove delimited by rings 20a, 20b assembled by bolts such as 21.
- the ring 20b is itself fixed to the second stage 5 by bolts such as the bolt 16 mentioned above.
- Skids 22, 23 allow the edge 17b of the flange 17 to slide in the groove delimited by the rings 20a, 20b (see FIG. 3B), transverse to the axis X of the launcher, to ensure decoupling capable of suppressing transmission of "surge” of efforts during the operation of the auxiliary thrusters 2, 3, as explained in detail in the aforementioned French patent application filed today by the applicant and entitled “Device for supporting a payload in a launcher of said payload "request to which reference will be made for more details on this point.
- the second flange 18, mounted coaxially on the first by bolts such as that referenced 19, takes the form of a crown hollowed out with bores on its two axially spaced bases.
- the annular member 10 comprises a flange 29 which takes the form of a ring with an axis parallel to the axis X of the launcher, this ring extending from two radial annular flanges spaced apart axially, one (29a) being traversed by the bolts such as 15, for fixing the device according to the invention to the skirt 6, the other (29b) being traversed by bolts such as 31, to be secured to plates 30 for loading the springs 25, 26 (at right of the elastic stops 12 ⁇ ), and by bolts such as that referenced 31 'to be secured to plates 32 for stopping the pistons 28 (in line with the hydraulic stops 13j).
- FIG. 3A it appears that a clearance exists between the flange 18 and the annular rim 29a on the one hand, and between the flange 18 and the plate 30 on the other hand.
- the skirt 6 and the satellite 4 are carried by the springs 25, 26 of the elastic stops 12i.
- This suspension then has a flexibility which is a function of the stiffness of these springs.
- the flange 18 is shown in abutment against the flange 29a of the flange 29. If these flanges are blocked in this position, it is understood that the springs have no effect on the suspension of the skirt 6 and of the satellite 4, this suspension then being very stiff. According to the present invention it is by an appropriate control of the pressure of the incompressible liquid which fills the chambers 27 of the hydraulic stops 13j that one passes from the "flexible" suspension illustrated by FIG. 3A to the "stiff" suspension illustrated by Figure 3B.
- This contact establishes a firm connection between the two annular members 10 and 11, then mechanically coupled.
- the satellite is then rigidly coupled to the launcher.
- the piston 28 By reducing the pressure in the chamber 27 of the hydraulic stops 12i, the piston 28 approaches the bottom of the chamber 27 by eliminating the rigid mechanical connection previously established between the annular members 10, 11. The satellite and the skirt are then carried by the springs 25, 26 of the elastic stops (see FIG. 3A) and are suspended loosely on the launcher.
- FIG. 7 shows the typical graph of the variations of the pressure established in the hydraulic abutments, in the phases of the flight of the launcher illustrated in FIG. 6. During the separations (in d and e), the pressure is suddenly reduced, from 70 bars to 0 bars for example, then quickly restored, once separation is complete.
- FIG. 5 A circuit for controlling this pressure is shown diagrammatically in FIG. 5.
- This essentially comprises a cylinder 40 provided with a movable piston 41 whose displacements serve to control the pressure of the fluid, advantageously constituted by an incompressible liquid, filling liquid the line 42 and the hydraulic stops 13 j , under pressure, a cylinder chamber 40 being connected to this line 42 by means of a valve 43 while the other cylinder chamber is connected to a drain valve 44.
- a line 45 equipped with a non-return valve 46 is used to initially fill, on the ground, the stops 13j and the chamber of the cylinder 40 which communicates with these stops, with a liquid under high pressure, of about 70 bars, for example, the valve 44 then being closed to isolate the other chamber of the cylinder, filled with gas under pressure.
- a liquid under high pressure of about 70 bars
- the pressure is suddenly reduced by simultaneously opening the valve 43 and the valve 44 for emptying the cylinder chamber which is filled with gas under pressure. This flows in a vacuum until the pressure in this chamber falls to the required value, of the order of 0 to 25 bars for example.
- the piston 41 then moved to the left, from the point of view of the drawing, to position 41a.
- This sudden expansion of the volume offered to the liquid under pressure in the line 42 and the hydraulic stops 13j causes a drop in pressure of the liquid and a reduction in the pressure applied to the hydraulic stops, which then drops to a value of between 0 and 25 bars approximately. , for example, to activate the elastic stops 12 ⁇ mounted parallel to the hydraulic stops 13j.
- a high gas pressure (approximately 70 bars) is restored in the cylinder 20, by recharging it with a pressurized gas from a reservoir 47 (after phase d) or a reservoir 48 (after phase e).
- These tanks can be conveniently constituted by pyrotechnic chokes with controlled ignition. It now appears that the invention makes it possible to achieve the aims aimed at, namely achieving a device for suspending a payload in a launcher, capable of protecting the latter from shocks or vibrations occurring during different phases of flight , by a suitable adaptation of the stiffness of the suspension, this device being of simple and reliable structure and flexible operation.
- stops are integrated into the same annular flange 18, which allows the chambers in which these stops are housed to be produced by means of conventional numerical control machining means.
- the hydraulic stops are themselves of conventional structure, with annular seals, perfectly mastered technology which makes it possible to be assured of the reliability of the device, as is essential in a space vehicle.
- the device according to the invention does not suffer from the problem mentioned in the preamble of this description, relating to excessive stiffening of the envelope of an annular chamber with flexible wall, when the pressure prevailing in the envelope is high.
- the invention is not limited to the embodiment described and shown which has been given only by way of example.
- the elastic and hydraulic stops could be inclined on the longitudinal axis of the launcher so as to ensure the absorption of shocks with axial propagation as with radial propagation.
- each of the elastic stops 12 ⁇ could comprise only one spring placed in a single bore, in the manner of the single piston of the hydraulic stops 13 and the latter could comprise two head-to-tail bores, in the manner of the bores of the elastic stops. 12 ⁇ .
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99964726A EP1140628A1 (fr) | 1998-12-29 | 1999-12-28 | Dispositif de suspension d'une charge utile dans un lanceur spatial |
US09/868,641 US6588707B1 (en) | 1998-12-29 | 1999-12-28 | Device for suspending a payload in a launch vehicle |
JP2000590911A JP2002533268A (ja) | 1998-12-29 | 1999-12-28 | 打上げビークルにペイロードを懸架するための装置 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9816561A FR2787764B1 (fr) | 1998-12-29 | 1998-12-29 | Dispositif de suspension d'une charge utile dans un lanceur spatial |
FR98/16561 | 1998-12-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2000038987A1 true WO2000038987A1 (fr) | 2000-07-06 |
Family
ID=9534607
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR1999/003302 WO2000038987A1 (fr) | 1998-12-29 | 1999-12-28 | Dispositif de suspension d'une charge utile dans un lanceur spatial |
Country Status (5)
Country | Link |
---|---|
US (1) | US6588707B1 (fr) |
EP (1) | EP1140628A1 (fr) |
JP (1) | JP2002533268A (fr) |
FR (1) | FR2787764B1 (fr) |
WO (1) | WO2000038987A1 (fr) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE515850C2 (sv) * | 2000-09-18 | 2001-10-15 | Saab Ericsson Space Ab | Anordning och metod vid en rymdfarkost |
CN100436261C (zh) * | 2006-08-25 | 2008-11-26 | 郑钢铁 | 卫星整体减振隔振装置 |
US7905453B2 (en) * | 2006-12-21 | 2011-03-15 | Intelsat | Piggyback equipment panel payload arrangement, a device for and method of attaching a hosted secondary piggyback payload and adapter to be used for a piggyback secondary payload arrangement for launching the piggyback equipment panel secondary |
US7866607B2 (en) * | 2006-12-21 | 2011-01-11 | Intelsat | Piggyback satellite payload arrangement, a device for and method of attaching a piggyback satellite payload and adapter to be used for a piggyback satellite payload arrangement for launching the piggyback satellite |
JP2012131410A (ja) * | 2010-12-22 | 2012-07-12 | Mitsubishi Heavy Ind Ltd | アダプタおよびペイロード打ち上げ用ロケット |
JP5888671B2 (ja) * | 2011-11-24 | 2016-03-22 | 株式会社Ihiエアロスペース | 振動緩和装置 |
US9828117B2 (en) * | 2016-02-04 | 2017-11-28 | United Launch Alliance, L.L.C. | Tensioning apparatus and system for clamping joints |
CN106184827B (zh) * | 2016-07-19 | 2018-05-29 | 哈尔滨工业大学 | 主被动一体式整星隔振装置 |
US10562650B2 (en) * | 2017-06-28 | 2020-02-18 | The Boeing Company | Corrugated payload adaptor structure |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4536114A (en) * | 1983-07-01 | 1985-08-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable length strut with longitudinal compliance and locking capability |
US5226616A (en) * | 1991-10-17 | 1993-07-13 | General Dynamics Corporation, Space Systems Div. | Multi-position support structure connecting a payload to a booster rocket |
EP0727351A2 (fr) * | 1995-02-17 | 1996-08-21 | Trw Inc. | Amortisseur à contrÔle actif |
WO1998032658A1 (fr) | 1997-01-29 | 1998-07-30 | Centre National D'etudes Spatiales | Dispositif de suspension d'une charge utile dans un lanceur spatial |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2614896A (en) * | 1950-05-06 | 1952-10-21 | Pierce Mary Brush | Adjustable dampening bearing support |
US4776539A (en) * | 1985-10-10 | 1988-10-11 | Orbital Research Partners, L.P. | Cradle apparatus for supporting payloads in a space vehicle |
US6345788B1 (en) * | 1999-05-27 | 2002-02-12 | Trw Inc. | Composite structure element with built-in damping |
US6357699B1 (en) * | 2000-05-25 | 2002-03-19 | The Boeing Company | Device for controlled release of tension |
-
1998
- 1998-12-29 FR FR9816561A patent/FR2787764B1/fr not_active Expired - Lifetime
-
1999
- 1999-12-28 JP JP2000590911A patent/JP2002533268A/ja active Pending
- 1999-12-28 US US09/868,641 patent/US6588707B1/en not_active Expired - Lifetime
- 1999-12-28 WO PCT/FR1999/003302 patent/WO2000038987A1/fr not_active Application Discontinuation
- 1999-12-28 EP EP99964726A patent/EP1140628A1/fr not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4536114A (en) * | 1983-07-01 | 1985-08-20 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable length strut with longitudinal compliance and locking capability |
US5226616A (en) * | 1991-10-17 | 1993-07-13 | General Dynamics Corporation, Space Systems Div. | Multi-position support structure connecting a payload to a booster rocket |
EP0727351A2 (fr) * | 1995-02-17 | 1996-08-21 | Trw Inc. | Amortisseur à contrÔle actif |
WO1998032658A1 (fr) | 1997-01-29 | 1998-07-30 | Centre National D'etudes Spatiales | Dispositif de suspension d'une charge utile dans un lanceur spatial |
Also Published As
Publication number | Publication date |
---|---|
FR2787764B1 (fr) | 2001-02-16 |
FR2787764A1 (fr) | 2000-06-30 |
EP1140628A1 (fr) | 2001-10-10 |
JP2002533268A (ja) | 2002-10-08 |
US6588707B1 (en) | 2003-07-08 |
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