Двигательная установка. AJ10. [Редактировать]

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1Стоимость (двигателя), млн. долл.1990-01-012.5

Найдено 221 документов по запросу «AJ10». [Перейти к поиску]


Дата загрузки: 2017-03-09
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0.07/5
... second stage used an Aerojet AJ10-118K engine that delivered approximately...) 1,122 kg (2,474 lb) Aerojet AJ10-118K Thiokol Star 48 motor... time Max. payload Contractors b Aerojet AJ10-118K Thiokol Star 48B Rocketdyne... lb) (511,190 lb) Aerojet AJ10-118K Thiokol Star 48B Rocketdyne...



Дата загрузки: 2017-03-18
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... I/O SA_DQS#[3] N9 DDR3 I/O SA_DQ[40] AJ10 DDR3 I/O SA_DQS#[4] AH7 DDR3 I/O SA_DQ...[41] DDR3 I/O AH9 VSS GND AJ10 SA_DQ[40] DDR3 I/O AH10 VTT0... REF VCAP0 AW50 PWR VAXG AJ10 REF VCAP0 AW53 PWR VAXG... GFX_VID[3] CMOS O AK60 VCAP2 PWR AJ10 VAXG AJ2 CFG[5] AJ70 VSS...



Дата загрузки: 2017-02-06
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0.03/5
... lpddr2 NA 0.1 PUy/ PDy(2) LVCMOS - AJ10 lpddr22_dq25 0 IO L L 0 vddq_ lpddr2 NA... lpddr22_ dq23 - - - - - - - - AJ9 lpddr22_ dq24 - - - - - - - - AJ10 lpddr22_ dq25 - - - - - - - - AH10 lpddr22_ dq26... LPDDR22 data bit 25 IO - AJ10 lpddr22_dq26 LPDDR22 data bit 26... / F2 / G1 / H1 / H2 / AJ9 / AJ10 / AH10 / AH11 / AJ12 / AJ13 / AH13...



Дата загрузки: 2017-02-06
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0/5
... AJ7 AH9 AG5 AH5 AJ9 AJ10 AH11 AJ11 AH15 AJ15 AG11... AH14 AK13 AJ13 AJ11 AH11 AJ10 AH10 AE15 AF15 AG14 AE14...+ AK11 AJ11 SATA_TX3+ SATA_TX3- AK10 AJ10 SATA_RX3SATA_RX3+ AJ15 SATA_CAL AJ16 AK16... AE15 AG23 AD9 AF16 AH10 AJ10 AD15 AH16 C1 J1 M1...



Дата загрузки: 2016-12-29
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0.18/5
SATELLITE LAUNCHER DIRECTORY Delta Delta was originally developed as an "interim space launch vehicle" using the Thor intermediate-range ballistic missile as a first stage with second and third stages from the US Navy's Vanguard launcher. Development by Douglas (now McDonnell Douglas) began in 1959 with an unsuccessful first launch attempt in May 1960. Of the 177 Deltas launched to date, only 11 have failed, and there have been 43 successful launches in a row since 1977. Delta has evolved dramatically since 1960. Milestones include: 1964, addition to the liquid-propellant first stage of three solid-rocket boosters (SRBs); 1968, a new solid-propellant third stage (Thiokol TE364-3); 1973, a new second-stage engine (Aerojet AJ10), along with inertial guidance, nine SRBs, and a longer thirdstage motor (TE364-4); 1980, introduction of the PAM third stage; and 1982, an improved second stage (Aerojet AJ10-118K engine). The result has been a remarkable growth in geosynchronous transfer orbit payload, from 41kg in 1960 to 1,270kg today—a factor of 30 increase. Nasa plans two final Delta launches in 1986—Delta 178 and 179—to launch geostationary weather satellites Goes G and H. A further three Deltas are being modified for military use. Production ceased in 1984 at Delta 182. In 1984 Transpace Carriers agreed to take over marketing and production of Delta from Nasa, but to date the company has failed to secure a customer. The Delta "family" marketed by TCI includes two second-stage and three thirdstage options and is able to place payloads from 900kg to 1,270kg in geostationary transfer orbit. The three main versions are the Delta 3914, 3910/PAM, and 3920/PAM. payload); multiple restart capability; gimballed nozzle; cold gas reaction control; avionics including inertial guidance. Third stage 3 9 1 4 (TE364-4) 1 tonne CTPB solid propellant; 6-8 tonnes nominal thrust; 3 9 1 0 / 3 9 2 0 / P A M (Star 48 motor); 2 tonnes HTPB solid propellant; 6-8 tonnes nominal thrust; 85sec burn time (adds 174kg to GTO payload); spin table for payload. Programme First launch May 1960 (failed); 179th and final Nasa launch scheduled for 1986. Scout Conceived by Nasa as a low-cost launch vehicle, Scout was developed by Chance Vought (now LTV) by integrating four existing solid-rocket motors into a 16-tonne vehicle suitable for a wide range of tasks. Development began in 1959 under a $1 million Nasa contract, and the first Scout was launched in July 1960, becoming the first solid-propellant vehicle to place a payload in orbit. Since 1960, Scout's loadcarrying capability has increased fourfold, from 60kg to 205kg into a 550km orbit. Of the 106 flights to date, 14 have been failures. A further 12 launchers are scheduled, one for Nasa, five for the US Air Force, and six for the US Navy. In addition, a further Ten Scout launches are being discussed. Scout remains in production. Configuration Four-stage solidpropellant expendable launch vehicle; strapdown inertial guidance. Performance 21-4-tonne take-off weight; 63-5 tonnes take-off thrust; 205kg payload into 550km orbit. First stage Algol III: PBAN solid propellant; 63.5 tonnes average thrust; 82sec burn time; aerodynamic control. Second stage Castor II: CTPB solid propellant; 27 tonnes thrust; 40sec burn time; hydrogen peroxide reaction control system. Third stage Antares III: H T P B solid propellant; 9 tonnes thrust; 48sec burn time; hydrogen peroxide reaction control system. Fourth stage Altair III: PBAN solid propellant; 2 - 7 tonnes thrust; 35sec burn time; spin stabilised. Programme First launch July 1960; 106 launches to date; 14 failures. Production of the Delta launch vehicle ceased in 1984, but five more remain to be used Configuration Three-stage expendable launch vehicle; liquid-propellant first stage augmented by nine solid-rocket boosters; liquid-propellant second-stage; solid-propellant third stage; inertial guidance. Performance 190-tonne take-off weight; take-off thrust 3 9 1 4 287 tonnes, 3 9 1 0 / 3 9 2 0 325 tonnes; GTO payload 3 9 1 4 0-9 tonnes, 3 9 1 0 / P A M 1-1 tonnes, 3 9 2 0 / P A M 1-3 tonnes. Boosters Nine Castor IV solid-propellant (CTPB) motors; each 38-5 tonnes average sea-level thrust; 3 9 1 4 five boosters fired at lift-off, four at altitude; 3 9 1 0 / P A M and 3 9 2 0 / P A M six boosters fired at liftoff and three at altitude to increase GTO payload by 20-30kg. First stage liquid propellants (liquid oxygen/kerosene); RS-27 engine; 94 tonnes sea-level thrust; gimbal/vernier control. Second stage 3 9 1 4 / 3 9 1 0 : 4-5 tonnes liquid propellants (N 2 0 4 and 50:50 hydrazine/UDMH); TR-201 engine; 4-5 tonnes thrust; 3 9 2 0 6 tonnes liquid propellants (same); AJ10-118K engine; 4-3 tonnes thrust (adds 160kg to GTO 40 FLIGHT INTERNATIONAL, II January 1986



Дата загрузки: 2016-12-29
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0.14/5
... O PCIE0TXN1 AK17 O PCIE0TXP1 AK16 O PCIE1REFRES AJ10 A PCIE1RXN0 AN14 I PCIE1RXP0 AN15 I PCIE1RXN1... SGMII0RXN3 AM25 HOUT AF30 PCIE1REFRES AJ10 SGMII0RXN4 AN23 HYPLNK0CLKN AJ8 PCIE1RXN0... VSS AK28 SGMII0TXP1 AM14 PCIE1RXP1 AJ10 PCIE1REFRES AK29 SGMII0TXN1 AM15 VSS...



Дата загрузки: 2017-01-04
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0.2/5
... 1 1 1 2K_F 0402 L7 K2 AC2 AJ10 H_DINV#[3..0] 20 mil H_AVREF R27... AG2 AG22 AG31 AG8 AH24 AJ10 AJ13 AJ16 AJ17 AJ20 AJ23.../GPIO36 SATA3GP/GPIO37 AJ12 GPI21 AJ10 AF11 GPI36 AG11 LCDID1 2 +3VALW...



Дата загрузки: 2017-01-04
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0.21/5
...(6) VLDT_2(7) VLDT_2(8) VLDT_2(9) AG11 AG12 AJ10 AH10 AG9 AG10 AJ8 AH8...(6) VLDT_2(7) VLDT_2(8) VLDT_2(9) AG11 AG12 AJ10 AH10 AG9 AG10 AJ8 AH8... RXP0 C478 C479 103P 103P AJ10 AH10 SP_RXN0 SP_RXP0 TXP1 TXN1...



Дата загрузки: 2017-03-18
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0/5
.../Other VSS AM13 Power/Other AJ10 Power/Other VSS AM16 Power.../Other AG30 VCC Power/Other AJ10 VSS Power/Other AH1 VSS...



Дата загрузки: 2017-01-16
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0.1/5
..., AG10, AG28, AH9, AH27, AJ8, AJ10, AJ28, AK7, AK9, AK29, AL6..., AG10, AG28, AH9, AH27, AJ8, AJ10, AJ28, AK7, AK9, AK29, AL6... VSS AK12 VSS AL15 VSS AJ10 CVDD AK13 VDDAHV AL16 VDDAHV...